AN INTERFACE BETWEEN HESCOMP AND CADAM … · Y HESCAD · AN INTERFACE BETWEEN HESCOMP AND CADAM ä...
Transcript of AN INTERFACE BETWEEN HESCOMP AND CADAM … · Y HESCAD · AN INTERFACE BETWEEN HESCOMP AND CADAM ä...
Y HESCAD · AN INTERFACE BETWEEN HESCOMP AND CADAMä FOR THE GENERATION OF HELICOPTER MODELS
Q Liang-Ju LuN-
A. Myklebust, Chairman
Department of Mechanical Engineering
(ABSTRACT)
3-D Interactive CADAM allows for easier construction, modification,
analysis, and display of 3-D geometry surfaces and wire-frames. This
research forms a basis for preliminary aircraft geometric design using
the CADAM system.
The helicopter design program, HESCOMP, originally· a batch mode
program, was coupled with CADAM via the CADAM data base such that the
analysis, design, and redesign of the helicopter geometry and. interior
equipment geometry can be accomplished interactively. HESCAD, a program
which produces the helicopter preliminary design model and enables the
interior equipment design process, is developed. It provides a capability
to evolve rapidly and refine helicopter configurations generated auto-
matically using output from HESCOMP or interior equipment design by
graphically and numerically defining helicopter components through
interactive, on line, computer graphic display devices. Helicopter 3-D
wireframes are automatically produced for any HESCOMP helicopter geometry
output. A method which directs CADAM to analyze the helicopter components
and produce weights, centers of gravity, moments and products of inertia
and to review the results of the analyses directly on the screen is pro-
vided.
This research was sponsored by IBM Corporation Federal Systems Di-
vision under contract No. 417503-DE.
This thesis describes and illustrates the HESCAD program. Detailed
graphical results are also presented.
ACKNOWLEDGEMENTS
I would like to express my gratitude to the following people for
their help and encouragement. Without any one of them, this thesis would
not have been possible.
Dr. A. Myklebust, who served as my major professor, gave me a lot
of help in. my' work. Very few people have touched my life like Dr.
Myklebust. I am a better person today because of his help.
I would like to thank Dr. C. F. Reinholtz for giving me a lot of
valuable suggestions, Dr. R. H. Fries for serving on my advisory and ex-
amining committees, and Mitch Keil for his help in my curriculum and
suggestions in my thesis work. He also helped me in preparing the figures
for this thesis.
I would like to thank my parents who made my education in the U.S.
possible.
Finally, I would like to thank my wife, , for her patience
and support and for taking care of my family duties, leaving me free to
pursue my graduate studies.V
Acknowledgements iv
TABLE OF CONTENTS
1. Introduction and Purpose .................. 1
2. Literature Survey ......................24
3. Introduction to Program HESCAD ...............26
3.1. Background for HESCAD ...................40
3.2. Program Assumptions and Limitations ............40
3.3. Coordinate System for HESCAD ................41
4. System Arrangement for Computer Graphics .........60
5. Error Trace Method .............I........61
6. Input Variables For HESCAD .................67
6.1. Variable Definition ....................67
6.2. Geometry Equations .....................85
6.3. Point Equations ......................86
6.3.1. Single Rotor Helicopter Point Equations ........87
6.3.2. Tandem Rotor Helicopter Point Equations ....... 110
7. Installation and Operation ................. 138
8.· Projection Procedures ................... 142
Table of Contents v
9. Mass Property Analysis .....Y............. 145
10. Example Data and Output ................. 150
11. Conclusions and Recommendations ............. 179
Appendix A. HESCAD Program ................. 180
Appendix B. COLLEC Program ................. 183
Appendix C. Terminology ................... 184
Bibliography ..........................
185Vita..............................-186
Table of Contents vi
LIST OF ILLUSTRATIONS
Figure 1. Single Rotor Helicopter ................ 6
Figure 2. Winged Single Rotor Helicopter ............ 7
Figure 3. Compound Single Rotor Helicopter with Jet Engine . . . 8
Figure 4. Compound Single Rotor Helicopter with Propeller Engine 9
Figure 5. Compound Single Rotor Helicopter Wire—Frame ...... 10
Figure 6. Tandem Rotor Helicopter ................ 11
Figure 7. Winged Tandem Rotor Helicopter ............ 12
Figure 8. Compound Tandem Rotor Helicopter with Jet Engine . . . 13 ·
Figure 9. Compound Tandem Rotor Helicopter with Propeller Engine 14
Figure 10. Compound Tandem Rotor Helicopter Wire-Frame ...... 15
Figure ll. Fenestron Tail Helicopter (Model I) .......... 16
. Figure 12. Fenestron Tail Helicopter Wire-Frame (Model I) .... 17
Figure 13. Fenestron Tail Helicopter (Model ll) ......... 18
Figure 14. Fenestron Tail Helicopter Wire—Frame (Model II) .... 19
Figure 15. Typical Single Rotor Helicopter Geometric Characteristics 20
Figure 16. Typical Tandem Rotor Helicopter Geometric Characteristics 21
Figure 17. Design of Interior Equipment ............. 22
Figure 18. Surfaces Added to the Wire-Frame Model .....°. . . 23
Figure 19. Single Rotor Helicopter Wire-Frame Major Cross-Section 29
Figure 20. Tandem Rotor Helicopter Wire-Frame Major Cross-Section 30
Figure 21. Helicopter Nose Cross-Section ............. 31
Figure 22. Helicopter Cabin Cross-Section ............ 32
Figure 23. Helicopter Tail Boom Cross-Section .......... 33
Figure 24. Single Rotor and Tandem Rotor Helicopter Main Rotor PylonCross-Section ..................... 34
List of Illustrations vii
Figure 25. Tandem Rotor Helicopter Aft Pylon and Single Rotor Heli-copter Vertical Tail Cross·Section .......... 35
Figure 26. Helicopter Wing & Horizontal Tail Cross-Section .... 36
Figure 27. Single Rotor Helicopter Wire—Frame Cross-Section CenterPoints ........................ 37
Figure 28. Tandem Rotor Helicopter Wire·Frame Cross-Section CenterPoints ........................ 38
Figure 29. Construction of Single Rotor Helicopter Fuselage Wire-Frame ......................... 39
Figure 30. Flowchart 1 ...................... 46
Figure 31. Flowchart 2 ...................... 47
Figure 32. Flowchart 3 ...................... 48
Figure 33. Flowchart 4 ...................... 49
Figure 34. Flowchart 5 . ._.................... 50
Figure 35. Flowchart 6 ...................... 51
Figure 36. Flowchart 7 ...................... 52
Figure 37. Flowchart 8 ...................... 53
Figure 38. Flowchart 9 ...................... 54
Figure 39. Flowchart 10 ..................... 55
Figure 40. Flowchart 11 ..................... 56
Figure 41. Flowchart 12 ..................... 57
Figure 42. Point Equation Geometry Environment .......... 58
Figure 43. CADAM Geometry Environment .............. 59
Figure 44. Error Trace and Its Results (Fuselage) ........ 64
Figure 45. Error Trace and Its Results (Pylon) .......... 65
Figure 46. Error Trace and Its Results (Wing) .......... 66
Figure 47. Typical Single and Tandem Rotor Helicopter Rotor Pylonand Vertical Tail Geometric Characteristics ..... 126
List of Illustrations viii
Figure 48. Single Rotor Helicopter Side View Points ...... 127
Figure 49. Single Rotor Helicopter Top View Points (Old Version) 128
Figure 50. Single Rotor Helicopter Top View Points (New Version) 129
Figure 51. Single Rotor Helicopter Primary View Points ..... 130
Figure 52. Tandem Rotor Helicopter Side View Points ...... 131
- Figure 53. Tandem Rotor Helicopter Top View Points (Old Version) 132
Figure 54. Tandem Rotor Helicopter Top View Points (New Version) 133
Figure 55. Tandem Rotor Helicopter Primary View Points ..... 134
Figure 56. Fenestron Tail Helicopter Side View Points ..... 135
Figure 57. Fenestron Tail Helicopter Top View Points ...... 136
Figure 58. Fenestron Tail Helicopter Primary View Points .... 137
Figure 59. CADAM Mass Properties (I) .............. 148
Figure 60. CADAM Mass Properties (II) ............. 149
Figure 61. Tandem Rotor Helicopter (Model I) .......... 163
Figure 62. Tandem Rotor Helicopter Wire—Frame (Model I) .... 164
Figure 63. Tandem Rotor Helicopter (Model II) ......... 165
Figure 64. Tandem Rotor Helicopter Wire-Frame (Model II) .... 166
Figure 65. Utility Helicopter (Model I) ............ 167
Figure 66. Utility Helicopter Wire-Frame (Model I) ....... 168
Figure 67. Utility Helicopter (Model II) ............ 169
Figure 68. Utility Helicopter Wire-Frame (Model II) ...... 170
Figure 69. Scat Helicopter (Model I) .............. 171
Figure 70. Scat Helicopter Wire-Frame (Model I) ........ 172
Figure 71. Scat Helicopter (Model II) ............. 173
Figure 72. Scat Helicopter Wire-Frame (Model II) ........ 174
List of Illustrations ix
Figure 73. Fenestron Tail Helicopter (Model I) ......... 175
Figure 74. Fenestrou Tail Helicopter Wire·Frame (Model I) . . . 176
Figure 75. Fenestron Tail Helicopter (Model II) ........ 177
Figure 76. Fenestron Tail Helicopter Wire-Frame (Model II) . . . 178
List of Illustrations x
LIST OF TABLES
Table l. Number of Points on the Cross·Section .......... 42
Table 2. Constants for Proportional Data Not Provided by HESCOMP(Single Rotor Helicopter) ................ 42
Table 3. Constants for Proportional Data Not Provided by HESCOMP(Tandem Rotor Helicopter) ................ 44
Table 4. TEST Data ........................ 68
Table 5. Helicopter Geometry Input Data ............. 70
Table 6. Single Rotor Helicopter Geometry Output Data ...... 78
Table 7. Tandem Rotor Helicopter Geometry Output Data ...... 83
List of Tables xi
‘l. INTRODUCTION AND PURPOSE
HESCOMP is a helicopter sizing and performance computer program.
The program°s purpose is to provide a means for rapidly developing heli-
copter sizing and mission performance data. HESCOMP can be used to define
design requirements such as weight breakdown, required propulsive power,
and physical dimensions of the aircraft which are designed to meet spec-
ified mission requirements. It is also useful in sensitivity studies
involving performance trade-offs. The program can be used to study any
single, tandem, or coaxial pure, winged, compound, or auxiliary propul-
sion helicopter [1]. The HESCOMP version referred to in this thesis was
written by S. J. Davis, et al. under Naval Air Development Center contract
No. N62269-74-C-0757 and N62269-79-C-C2l7 (first revision November 1974,
second revision October 1979) at Boeing Vertol Company, Philadelphia, PA
19142.l l
HESCOMP can calculate helicopter geometry data but cannot provide
graphical output. The main purpose of this research is to use the HESCOMP
geometrical output (input) data, and the CADAM geometrical data base to
produce three 2-D helicopter orthographic views and a 3-D helicopter
wire-frame, and to develop a procedure for the use of these models in the
design and mass property analysis of components which will be added to
the helicopters.
The program HSCAD [2] was designed to fulfill the above criterion.
It can automatically generate single rotor and tandem rotor helicopters,
with or without wings and with or without auxiliary engines on the wings.
1. Introduction and Purpose 1
(see Fig. 1, 2, 3, 4, 5, 6, 7, 8, 9, 10 ). Based on the HESCOMP output,
the fenestron tail helicopter can also be generated (see Fig 11, 12, 13,
14). At present the generated wireframe has a conventional tail and tail
rotor but a fenestron tail can be produced by projection. Designing and
redesigning helicopter geometry and interior equipment geometry can be
accomplished interactively via HESCAD. This provides the user with an
immediate graphical display of the helicopter shape resulting from
HSCOMP input. The user may proceed to iterate his choice of HESCOMP
input data until all shape conditions have been rendered sufficiently and
the best overall solution is displayed. And the designer can evaluate
helicopter dimensions directly on the screen using the light pen or cursor
and tablet (see Fig. 15, 16). The design of interior equipment can be
carried out in the three 2-D orthographic views and the results can be
projected into the wire-frame model or an isometric View (see Fig. 17).
This will allow viewing of the model and adding components from any
Vantage point by using CADAM 3-D GROUP (TRANSLATE & ROTATE) or WINDOW
(ROT). All geometries may be modified and surfaces may be added to the
wire-frame model if desired (see Fig. 18). After generating all the views
of the helicopter and its components the equipment mass property analysis
may be carried out. The analysis procedures are provided in chapter 9.
In addition, the resulting orthographic views can be passed to CATIA if
desired, through the CADAM-CATIA interface.‘
An interface file, COLLEC [2], was written on unit 10, which provides
a linkage between HESCOMP an HESCAD. The new HESCOMP subroutine COLLEC
collects all HSCOMP input (HI) and output (H0) geometry variables and
all HESCOMP decision (TEST) variables. A helicopter model may be changed
1. Introduction and PurposeU
2
by modifying HESCOMP input data or by modifying its output data. Since
several pieces of helicopter geometry data are not defined by HESCOMP,
constants which are proportions of other dimensions are coded in HESCAD
(Table 1). These constants determine fine features of the helicopter
parts. They may be redefined by user if necessary. Finally, any desired
design changes to the models may be done manually on the CADAM screen.
HESCAD was written and tested on PID CADAM releases 19.1, 19.2 and
20.0 [3]. The 37D and moment of inertia features are only valid on re-
lease 20.0. the reference manual is:
CADAM Interactive User Reference Manual
Volumes 1 and 2, SH20-6510-0[
IBM Corporation
or its equivalent for the version of CADAM.
To effectively utilize the results of this study, users should attend
the CADAM, INC. training classes on CADAM Basic and CADAM Basic—3D as a
minimum.
The principal feature of CADAM used in this study was the Geometry
Interface Module (GIM) [4]. Refer to the installation manual:
CADAM Geometry Interface Installation Guide
SH20-6227-0
IBM Corporation
or its equivalent (for the MDA version) for further information.
1. Introduction and Purpose 3
The component of the GIM which allows direct entry of geometric data
to the CADAM data base or "drawfile" is CADCD ("cadcard"). Although this
work was done in a VM/CMS environment, procedures for invoking the CADCD
main program (HESCAD in this case) are similar for CADAM under MVS. These
procedures are described for both VM and MVS in the GIM installation
manual referenced above.
Description of the interface between CADAM and CATIA [5] may be found
in the documentation for Dassault Systems, Inc. CATIA.
CATIA VM/CMS Utilities Manuall
SH20·6505
IBM Corporation
Current CADAM model sizes for HESCAD models range from 10,000 to
11,000 words. Additional unnecessary geometry, such as node points, have
been commented out of the HESCAD code to save model space, but may be
readily restored.
2-D geometry may be changed piece by piece or in groups to 3-D ge-
ometry by using 8-D MISC and providing Z-coordinate information. The 3-D
wire-frames may be changed by using 3-D GROUP, 3-D MISC or 3-D MISC-2 in
3-D mode and 3-D window. Detailed procedures are described in chapter 8.
Finally, note that HESCAD has numerous diagnostic messages and error
exits. At present when a rare error occurs (such as a needed variable
is computed by HESCOMP to be zero due to incorrect HESCOMP input) a mes-
sage is written on unit six by HESCAD and frequently by CADCD as well.
This causes HESCAD to terminate. As a result, all remaining (correct)
1. Introduction and Purpose h
geometry is not written to the CADAM data base. If desired, diagnostic
messages may be placed adjacent to geometry calls, or they may be invoked
by subroutine calls, thereby eliminating error exits. CADCD will continue
to produce geometry in the presence of these errors. If errors occur,
the HESCOMP input and output should be scrutinized to assure that impor-
tant geometric variables are not zero.
l. Introduction and Purpose 5
l
E
IN
*8EL8E:2:*Ho4-|ocz.2¤o¤·•·i
_ VJ
. .-1
.» ;_
¤—•*
.\&{.~I1
. Introduction and Purpose 6
IItil uaI
lä J.....% mu Ü |‘i E". ‘HJ 1:YIY g—o
I JI!2s-•B22&°„ ·•-I
cn·¤EJ·•-I
26 _N
0
\ co
_\
v.1.
Introduction and Purpose 7
Ii E-‘-'
• Ü
\\ImI7/ÄÜ
ü‘ *·
·-5H·•-I2V‘HI3:1.oE
:2*2§ocz
ELc
-5 ·
ä„x‘ ·_
‘i
* . E?
.}1.Introduction and Purpose 8
I Kwu-o
¤·•-1
§I’ (
2
= 2:1% I gu 6Ü
u ·- Q
Ö ·63
cx..-:24-I••·|3z-•.3¤„o-3
6E
. »-«
~8ocz
ps
s:
2"
E
\ \¤
='‘E 26.
1. Introducgign and purpose 9
II.
WAII||\ ,/AU|I|\\_ i 1 rr ‘l\
WI ·¤~??ääI!•I=I
I’*=1¤I ‘1 Sg: EF!•·····I!|u!
I g sv II = ;·;!!!!{;„~e'\ ‘¢A<·„¤-•\IQ9[IIMI
/"":$:=1'!
";;;||s'I‘ g;g;:!I·t‘ :„
VI.:1
‘;1‘-\’!?i'r‘2 A "II .“IIIII 2IIHII H\99
äIIII1 8W =‘
. Z? {9179 äH
W 0v-1
- ~S ¤¤.5ä wI A 2
¤ I 3_ 1 1 Q-, äN / „„
g I gg é z>j§¤;, ¤
g I I ,'N. 99¢QVI "‘
ÖQQ4§»,:.s\~,4%I11
/49W 0%
I
W I
1. Introduction and Purpose 10
HV
E
wW
1. Introduction and Purpose ll
gngä
ID-•8
\\\xR
20
1®®\
§
"\
·
·~
·
~
=
1.Introduction
and PurPose
12
'Ü
.2EBEl 6
MM
V
Q;_§
E
W
_„6
0
ä
1. I
E2
¤troduCt. on and PuIP13
·HQ)
E.ÜF E
P1 Erl HÜ 3V 3i
EIäéä
„ E1 4)
- 'U11 ä1
E-•
"”*=·1°\ &/ §
§\’®x §LH
1. Introduction and Purpose 14
€'>_
„//lääé:‘\\ܤ~„_
··’\§~’€*'Ö\
GJ°' ä1 ·1
‘ .§=E8.9.EH— 2£
C
/·Ii,
Ä}
;
_
§
1+*---, M 1 ·1/VIIW 1111*1 E1 1
¤•., «, 1 Q)
Ä} *5
»/‘iE:*’=I¤I 1/ \S§N|$
"?‘3\Ii!’
l. Introduction and Purpose·
15
lu —
M Q)
;~ll 2
WIY _,| -2:
O« EQ.)4-JIH¤«O.3
1-4é’‘ •-4
·•-I
„ ~ EQO
,1 1 _• .;\ Q)\‘\\$;?
°"
x\\\
·
t$*}«\\
1. Introduction and Purpose 16
. .5}/4:::,,,,N IY(NfI'I"I'
N · 0.IMIN‘ :· .-wm ·Ir NY •· “~ HNI:_ In. _J I:•. 4 N 4 :1. •|
NF'; INMNP‘· ·¢ ¢lN!IN:! ^U ‘v¤ 4 Y -·
—· *'*\‘! :N .„ .I|ÄEEQEFP ~.N
N ECU$-4Fl-• .NW 'G)
:2Y---N
„ . I, · °SV E"- g
N $-4N 4-»UI
N 0N ä‘II‘$ fa\- ai
" zlßüßi 8•||\I\¤“ ;,(HQ,{I¤,\ ::4·: |||II\}“ N -.1/~_Q_h. ,,_
.. I.NTN
Ng\\\N=N;}N ßazf¤‘
E / x '‘i§¢ ' ’ßh
1. Introductien and Purpose 17
E
Q
H
1-I&/Q
._
ug•.3
\_xf~www‘,
www
Q
www
5
www1r-4
Inoducti°n and
PuYPOS9
16
•Nl4,·;,Q;Ä"‘
\‘lll!\ ee»‘
[4'
·°‘ —"
IV /\N· ·$““\\\1\ . /|IIIIIl[} :/[IIIIIInI
N ä/'N1//1;Ü·, N
G)
NAV äN 3
In qzxägh
. ¤¤IZIV.? 4g(I)
äUF-=•
NiN\\\\\&\\¢ /”’/”«W
'//1/1, .1 4_=\!EN\\-1 ,~§ß¢¢¢z¢W ¤?g2\N\\\\\“ C JÄHM.¤III\III\"
V A7 Ö‘
"\\¥¥}M ‘
'»N;;‘gN<Ä.~.„=‘A. QYWAD
1191. Introduction and PurP°S°
3s 4N
J? 7Q · -
ä
V Inl
{I‘ 6
I
E _ I
§
i}I
84§\ 2 nn
0U
‘ JF7/.
=> Iéßäjj
*6
*1’ W!} ,
°°
«__ FI~
N
'— !n_ —F _ E
2
q 8U
é° g 3
— H
FF!§
H
6-
I3
2
cz.
QO-2
x
E
FQ-
*6IZ2*.
vv
.5
Ȥq
6E
®*‘°
·· Ä
-
F9 6 6
"""‘F 'xäég
II "„;
’
1.IntroduCtj_ou and Purpose
20
8
161 li 21 g,U
2 _V*
J 6 E 8 ä1_ " 1 _[ 1 *1 ·¤ ä gg—, : U
—~,,,_l
‘Ü
’_'
é ·‘2 2 lI‘
Es B .‘-"
14--*
V ‘ ‘ III = 2ä
3 3 E. O2 i
2 B„\ {
é
Gx G!
„\ ”/
2 3 2II—
I 2«‘. 2-„(¢ gg•
19
1. Introduction and Purpose 21
Q 6
E]— 2
2 E,4E
N
iB
re 6•*
F ,. \·2 6
]. . II1tIOduCt io
6
n and purpose 22
/0,, ,AÜÄ [A
. ,1,1m:ß[Cg,
/1 A 1 /,/1
s ‘KßS,;/,4 441.> 11 1 11O
1,1,11111{ };,,·1· $C1·1 $,1/1/ 1 1 1 ,,11111“,,,11',11111/ 1
0 Q1-,Ä "'\ , 1,1111:-1,·. ;;,111«;;;111«;;,11111 0S ·. 1,1. 1,- 1 ,,111 ,,,11 ,,1,
[Q1, , 1/,1 ¤ 11// ,1111/ ,111// ,,11 'ÜQ} Ö O
P ,1111/ 1 Z}· '
·„ 1_ ,’,1 ,1111/$,,11*//$,111/$$
//1 <1 cp,1
,. <¤' - '
1 1 T1 ' 111 1 1 1 "‘1l}, '-I1 111111//0 ¤>1 111'§ 71 " I
L4„‘'·,*1'1 " " ,·_<[}.'·1 ’'_·‘Ä111'1’ ,1/ "'
/1,*11.1",Ü‘ ,;;;/11 1;ci1 <jé,1 g 3
1 ,· 1 1111 ·,_1,1'1,( 1,14)
1//// ,1///'1," l ¤~
7 ,,11 ,, 11_ „\1 ,1,,1 A ,1,1,,,,1 , 1
1 .'
'U
1Ü U
,;f,' , 1‘¤
12,1 cn
· ao•-O
•'/ 4;1-.• gn
--4
•E,-,/
,111
1 . Introduction and Purpose Z3
2. LITERATURE SURVEY
The products of the aircraft industry very often consist of complex
geometries and usually require frequent changes to be made prior to their
final design. Complex geometries lead to the tedious task of determining
the product weight, mechanical geometry data, mechanical and aerodynamic
performance, and the work space. Changing a single variable in the design
many times results in the recomputation of all aircraft aerodynamics,
statics, mechanical performance and design logistics.
Because of the two criteria mentioned above, CAD was applied in the
aircraft industry many years ago.
In the late l950's McDonnell Aircraft Company began to develop a CAT
(computer-aided technology) system, and in 1959, the first computer-
stored loft surface was generated. In 1974, the CRT project [6] was
formed, in which 15 basic graphic modules were developed. In 1977, CGSA
(computer graphics structural analysis) and CADD (computer-aided design-
drafting) were developed to aid aircraft structural analysis and design.
In 1969 J. J. Sciarra generated a 3-D helicopter fuselage to make
helicopter fuselage Vibration analyses [7].
In 1978 J. B. Ashbaugh et al. designed the DSPOBJ program to display
and modify 3-D surfaces used for the definition of aircraft geometries
[8].
The man-computer graphics (MCG) techniques developed at Lockheed-
Georgia Co. have already been used successfully in several areas associ-
ated in the design and manufacture of aircraft [9].
2. Literature Survey 24
The major emphasis of CAD in the aircraft design process appears to
address computer graphic techniques and structure analyses. There are a
number of aircraft design programs developed in the aircraft industry,
but few of these are based on CADAM. The recently announced Version 2
or Release 20 of PID CADAM has substantially improved the 3-D features
of the CAD system. CADAM 3-D Interactive and CADAM Interactive Design
include several new functions which will assist in the computer—aided
design of aircraft and their interior equipment.
2. Literature Survey 25
e3. INTRODUCTION TO PROGRAM HESCAD
HESCAD produces single or tandem rotor, pure or winged helicopter
pictures via HESCOMP geometric data. HESCAD consists of three parts:
creation of single rotor helicopters; creation of tandem rotor helicop-
ters; and creation of fenestron tail helicopters. The pure or winged
helicopter design, and jet engine or propeller engine design can be
specified by TEST data for the three kinds of helicopters mentioned above.
Since a number of minor geometrical quantities needed for the models are
not provided by HESCOMP, these values are coded into the subroutines as
constants (Table 2). Some of these constants determine the location of
the main rotor pylon, wing, primary engine, jet and propeller engine.
The 2-D helicopter model is divided into seven parts: body, wing, main
° rotor pylon, vertical tail, jet engine nacelle, propeller engine nacelle
and primary engine nacelle. The location of every part can be easily
changed by simply changing certain parameters (Table 2). The 3-D heli-
copter wire-frame is divided into 13 geometric characteristic cross-
sections (see Fig. 19, 20): nose (see Fig. 21), cabin (see Fig. 22), tail
boom (see Fig. 23), main rotor pylon (see Fig. 24), vertical tail (aft
pylon for tandem) (see Fig. 25), wing (see Fig. 26), jet engine nacelle,
propeller engine nacelle, primary engine nacelle, main rotor blade, aft
rotor blade, main rotor shaft and aft rotor shaft. There is a center
point specified for each cross-section (see Fig. 27, 28), thus the lo-
cation of the cross—section (i.e. helicopter parts) can easily be adjusted
by a change in certain parameters (Table 2). Each part is drawn by one
3. Introduction to Program HESCAD 26
subroutine and can be modified using only two geometric parameters; the
width and the length. According to these two parameters, a set of ge-
ometric points is generated by the subroutine, so the boundary points
(sizing control points) of the cross-section are defined. The helicopter
characteristic cross-section can be accomplished by connecting these
points using certain geometrical elements. In the program, the following
curve segments were used:
•straight line
•circle
•ellipse
• spline
Splines which interpolate parabolic, elliptical and higher order
data are produced in the three orthographic views.·
It is assumed that all the cross-sections are symmetric. A set of
equally spaced points is then specified around the cross·section and then
linked in a certain direction by splines, straight lines and radii, to
produce the wire-frame. Fig. 29 gives an example of the procedures to
construct the wire-frame. The wire-frame model nose is made up of el-
liptical cross—sections which vary parabolically in size. The single
rotor helicopter tail boom has elliptical cross-sections that vary line-
arly. Since cabin, wing, pylon and vertical tail cross-section outline
are composed of circular arcs and straight line segments and the cross-
section shapes are not proportional in their longitudinal directions,
parameterization of the resulting curve with equal spacing becomes dif-
ficult. A method was developed which uses a sum of error elements to
3. Introduction to Program HESCAD 27
equally space the points. As a result, the number of points and the
number of splines around the each part can be freely changed without
sacrificing equal spacing. Table 1 shows the recommended number of
splines to be drawn around the helicopter parts.
Note that all points including these wire-frame nodal points have
been commented out to reduce model space. The points may be easily re-
stored by removing the C°s in column one of the program.
3. Introduction to Program HESCADA
28
.2F-
§ Eäg EEI °' u: Eé ä*= E(Egg §§; ääEéé §gT ~3:
Egs“3’
Eng äRg-ä @4, *3<
— Z "",.. og *:1 Hg 9v ¢g‘g 3« d 5 2. H •-• *·‘\ 2T23 2 ,.1 iH }-G^3
** Tg.? 3 TE2 Tg SE? Egg *\\' .
H,2 E3 ||‘8Ü•-UE>< \°‘\®ß 3*;*
3., E‘H I') .*2
ä2:2\ siöää *·
"SE .29äää - ~‘“
gas 33Eäé Z4 ;
3. Introduction to Program HESCAD 29
§§ 32 — E6¤;¤ää§.§ .„ ZEä)-§§
EE c:
s> "‘ - E5 ä
¤·mgg䧑<ä
%? mg EP g”%äg EE
¤ V?é'T
22m EVääé$.gE䧧E
°”T?
3. Introduction to Program HESCAD 30
MAJ
CCWi" STARTING POINT
MIN
CENTER POINT
HELICOPTER NOSE ELLIPSE CROSS-SECTION
CROSS-SECTION MAJ R MIN R
2 (K2•A•SF2/4)••0.5 (Kl•DD/4)••0.5
3 (K2•A•SF2/4)••0.5 (Kl•DD/2)/••0.5
4 (K2•A•SF2/4)••0.5 (KI•DD•3/4)••0.5
_
<·<A=O.5•(H0(6)+HI(8))•HI(IO)DD•(O.5•(HO(6)+HI(8))•HI(lO)•SF2
Kn=(HI(8)•sF1)••2/A
K2·H0(6)••2/(4•A)
Figure 21. Helicopter Nose Cross-Section
3. Introduction to Program HESCAD 31
W
STARTING POINT
4 SEG! SEG9 6SEG2 SEGB
3 7
SEG3 SEG7Hi
CENTER POINTI3 9
_ $664 SEG6
I2 SEG5 IO
!vI¤H0
(6)Figure22. Helicopter Cabin Cross-Section
3. Introduction to Program HESCAD 32
MIN
ccwSTARTING POINT
Mw
CENTER POINT
ISINGLE Roma PELICCPTER TAILBGH cnoss-sacuou
RRRRR·RR=*RRR RR R(3•|·D(4)/4•A|¤.El+0.25•HI(8))/2 (2•(3•HI(ß)/4•A£_E2)+0,2§•|··|I(6))/2
IQ (I-|)(4)/2•AßE|-•·Q,2§•|·|I(ß) V2 (2•(H0(4)•ANGI.E2)+0.2t5•I-l3(6) )/2
I3 (I··D(4)/4•AbI3I..E|+0.25•HI(8) 1/2 (2•I·D(4)/4•AßGLE2)+0.25•I·IJ(6) 1/2
I4 o.2s•MI(61/2 o.2¤•Mo<6>/2
·¤ANGl.EI¤ATAN(0.4•H/|·D(4)) M-•-erm
ANGLE2•ATAN(0.2•H/I-D(4)) W·H¤I6I
Figure 23. Helicopter Tail Boom Cross-Section
3. Introduction to Program HESCAD 33
u.
mu
cemen norm3 sunum mm
; _‘ SEG! 3•Ia ‘
H ses: sem wa
67 $63
_ SINSLE novon retxconren mm noron nvtou cnoss-secuou
I L 1np I-IJ(36)/(I/l-l3(38)+|)/|·I0(¥•3) |-ß([Q)•|•ß(37)
umen noron PELICÜTER mm noron nvtou CROSS-SECTIGJ
ILTIPI-D(80)/(I/E-II(82)+|)/|·D(77) H¤<841•H¤<8¤>
Figure 24. Single Rotor and Tandem Rotor Helicopter Main Rotor PylonCross-Section
3. Introduction to Program HESCAD 34
1.
1:1:11
sumruo vorm2
$61 4
1-1 $62 $64 1-1/2
66 $6:1
_ cemen vorm
_ srN61.e ROTM I-ELICOPTER veRTrcA1. TAIL CROSS-SECTIGI
I L1TIP2•|~D(27)/(I/|·KJ(29)•|)/|·I)(25) H0(32)•Ho(271/(1-10129)+11/1-1o(2:*>)
R®T 2•1-10127)/(Ho(29)+1)/1-1o(26) H0(32)•+10(27>/(Ho(29)+1)/1-10126)
TAmen ROTGY HELICIPTER AFT vvtou CROSS-SECTICN
ILTIP2•no1721/(1/1-101741+1)/1-101701 H¤<'/6)••·•¤<7$)
Rom- 2•+1o1‘721/(1-10174)+1)/1-1000) I>D(75)•|··D(73)
Figure 25. Tandem Rotor Helicopter Aft Pylon and Single Rotor Heli-copter Vertical Tail Cross-Section
3. Introduction to Program HESCAD 35
L
CCW
.; 2 szon STARTING POINTH SEG2
T 3 sass 4CENTER POINT
R -= 4L
’5
COMPOUNO HELICOPTER WING CROSS-SECTION
TIP (H0(IO)-H0(6))/(I/H0(|3)+|)/H0(8) I-IO(I5)•I-IO(II)
ROOT (I-IO(I0)-I-IO(6))/(HO( I3)+I )/I-IO(8) I-IOI I4)•I-IOI I I)
SINGLE ROTOR HELICOPTER HORIZONTAL TAIL CROSS-SECTION— L ÄTIP 2•I-IO(20)/(I/I-IO(22)+I)/HO(I8) I~IO(23)•I-IO(2I)
ROOTFigure26. Helicopter Wing & Horizontal Tail Cross~Section
3. Introduction to Program HESCAD 36
,, ä § E ä ä E ää ä g”t. ‘6 6 ‘
_ E 36 Eäääääää 2 gg
6 § ä5Q9: é CQ
. *3\ a sg? L5 6 2« · ä·g6„ 2 :2ä Z gg2626
;I=„~
\ **26 3ä 82ää _
°‘v
\ { xnjä _ 8Üi M2? 266 25 ®31ä§~%;é B 6 ·3E6 63; 633 6f \«¢*° za 2E§'{§_
U 6
33éä "‘
3 äg éä
3. Introduction to Program HESCAD 37
ä 2
2222 2 ;22222%, Sä;· i é 2 2 ä LLJ -8ääsz ä Ü E äg 3 2
ä ä éE §
ä
22 2 ‘@ 2222 2S2 2 2 2;) 225,22Sg
2222 2
Ä ,,22222\ 22 2
222 2222222222
2 22 EE222
3. Introduction to Program HESCAD 38
W
I
W. W
2__.....Ä
ä
I. 0RAw cnoä-sacuous
2. DRAW POINTS
3. DRAW SPLINES
Figure 29. Construction of Single Rotor Helicopter Fuselage Wire-Frame
3. Introduction to Program HESCAD 39
3.1. BACKGROUND FOR HESCAD
Since both HESCOMP and CADAM GIM are coded in FORTRAN IV, HESCAD is
coded in FORTRAN IV and compiled with VSFORTRAN using the option LANGLVL
= 66. HESCAD is designed to satisfy the software specifications as de-
scribed by the following flowcharts which were developed using hierar-
chical decomposition. The flowcharts for HESCAD and the major
modifications to HESCOMP are shown in Fig. 30 through 41. A number of
subroutines called at the lowest levels are not shown in these flowcharts.
These subroutines generate various high-level geometric features usually
representing cross-sections.l
The corresponding HESCAD code is described in Appendix A.
3.2. PROGRAM ASSUMPTIONS AND LIMITATIONS
The first step toward the successful use of any program is to un-
derstand the program°s assumptions and limitations. In the HESCAD program
the following assumptions are made:
l. All the HESCOMP output (input) data is consistent.
2. No zero geometry data is permitted.
These assumptions are required to generate correct geometry models.
Otherwise, the helicopter geometry model may be truncated. The limita—
tions of HESCAD are as follows:
3. Introduction to Program HESCAD 40
The number of points specified around the helicopter cross-section
must be kept within the given range. The lower limit of the number of
the points drawn on the cross-section should be satisfied (see table 1)
for the typical HESCOMP output, i.e. at least one point is drawn on seg-
ment 1 and segment 2 for cabin cross-section (see Fig. 44), one point on
segment 2 for main pylon and vertical tail (aft pylon) cross-section (see
Fig. 45), and one point on segment 2 for wing cross-section (see Fig. 46).
3.3. COORDINATE SYSTEM FOR HESCAD
Each view generated is defined relative to its own local reference
axes. The pivot was defined in the center of main rotor. The basic axes
system was defined in the primary view. The location of the local axes
system of the top view, side view and wire-frame relative to the basic
axes system are in terms of the displacement of the local origin. The
geometric environment of the point equations and CADAM are illustrated
in Fig. 42 and Fig. 43.
Table 1. Number of Points on the Cross-Section
Variable range Description
LPTOT 15 - 50 Points on the cabin cross-section outline
LPTVT 20 - 50 Points on the vertical tail (aft pylon)cross-section outline
LPTVT 12 - 50 Points on the wing cross-section outline
3. Introduction to Program HESCAD 41
Table 1. (continued)
Variable range Description
LPTPT 20 - 50 Points on the main pylon cross-section out-line
LPTAT 5 - 15 Points on the aft rotor shaft cross-sectionoutline
LPTST 5 - 15 Points on the main rotor shaft cross-sectionoutline
LPTET 8 - 25 Points on the engine cross-section outline
Table 2. Constants for Proportional Data Not Provided by HESCOMP
·--- SINGLE ROTOR HELICOPTER -·—-
SIDE VIEW COEFFICIENTS (Subroutine SSV)
Variable range data Description
B 1.0 - 2.0 1.0 Distance between pylon and rotor
C1 0.2 · 0.25 0.25 A percentage of wing span, "C2*H0(10)"is the X coordinate of the points to de-termine the jet engine's location
C2 0.2 - 0.25 0.25 A percentage to determine the cabin arcin the side view
SF1 0.3 - 0.45 0.4 The percentage of nose height (measuredfrom the belly) which marks the start ofthe windshield
SF2 0.5 - 0.65 0.6 The percentage of nose height (measuredfrom the tip) which marks the start ofthe windshield
3. Introduction to Program HESCAD 42
Table 2. (continued)
TOP VIEW COEFFICIENTS (Subroutine STV)
Variable range data Description
0 0.6 - 0.85 0.66 A percentage of body length, "C='=HO(2)"is the X coordinate of the point to de—
termine the wing°s location
C2 0.2 - 0.25 0.25 A porooncogo of wing span, "02i=H0(10)"is the Y coordinate of the points to de-
_ . termine the jet engine's location
PLM 0.2 - 0.35 0.3 '_._ _A percentage of main pylon length, todetermine main pylon location in X di-
__ rection (0<PLM<l)
SF2 0.5 - 0.65 . 0.6 A percentage of nose length from the tip,defining the start of the windshield
PRIMARY VIEW BOEFEQCIENTS (Subroutine SPV)
‘Qj‘ js}Variable range data ° Description
B 1.0 - 2.0{
1.0 Distance between pylon and rotor
C1 0.6 - 0.85 0.66 A porooniogo of body length, "c1+=H0(2)"is the X coordinate of the point to de-termine the wing°s location
PLM 0.2 - 0.35 0.3 A percentage of main pylon length, todetermine main pylon location in X di-rection (0<PLM<l)
3. Introduction to Program HESCAD 43
Table 3. Constants for Proportional Data Not Provided by HESCOMP
-——- TANDEM ROTOR HELICOPTER ----
SIDE VIEW COEFFICIENTS (Subroutine TSV)
Variable range data Description
B 1.0 - 2.0 1.0 Distcance between pylon and rotor
C 0.2 - 0.25 0.25 A percentage to determine the cabin arcin the side view
Cl 0.2 - 0.25 0.25 A percentage of wing span, "C2*HO(10)"is the X coordinate of the points to de-termine the jet engine°s location
SFl 0.3 - 0.45 0.4 The percentage of nose height (measuredfrom the belly) which marks the start ofthe windshield
SF2 0.5 - 0.65 0.6 The percentage of nose height (measured- from the tip) which marks the start of
the windshield
TOP VIEW COEFFICIENTS (Subroutine TTV)
Variable range data Description
c 0.45 - 0.55 0.5 A percentage of body 1obgub, "C*H0(2)"is the X coordinate of the point to de-termine the wing's location
C2 0.2 — 0.25 0.25 A percentage of wing span, "C2*HO(10)"is the Y coordinate of the point to de-termine the jet engine's location
PLM 0.2 — 0.35 0.3 A percentage of main pylon length, todetermine main pylon location hi X di-rection (0<PLM<l)
3. Introduction to Program HESCAD 44
Table 3. (continued)
TOP VIEW COEPFICIENTS (Subroutine TTV)
Variable range data Description
SF2 0.5 - 0.65 0.6 A percentage of nose length from the tip,defining the start of the windshield
PRIMARY VIEW COEFFICIENTS (Subroutine TPV)
Variable range data Description
B 1.0 - 2.0 1.0 Distance between pylon and rotor
C 0.45 - 0.55 0.5 A percentage of body length, "C*H0(2)"is the X coordinate of the point to de-termine the wing°s location
PLM 0.2 · 0.35 0.3 A percentage of main pylon length, todetermine main pylon location in X di-rection (0<PLM<l)
3. Introduction to Program HESCAD 45
*~¤ sumPESCGP
I
CGPUTATIE
2
GLLECT ALLGEGETRICVARIABLES
WRITEVARIABLES
TO DIS< FILE
STARTFESCAD
I3
ET DATA
4
7*9* smsta EI-SEROTE?
6SINSLE TAE
PEFEM ALL PERFEM ALLIPPUT EUETRY IIÜUT EGETRYCALLS TO CADAM CAlJ..S TD CADAH(SINSLE ROTE) (TANIM ROTE)
0
CLEAN LP_ APD STEE DGE.
ERRE HAMLINB
Figure 30 . Flowchart l¤
3. Introduction to Program HESCAD 46
I · I cm. 1.oA¤sR
THEN OPTIND¤; ELSEAND
IFLAG=I7
CALL CDLLEC”
(IDENT) THENWRITE’G•om•trtcdata h¤• b••n
urt1t•n on unltNDISK’
WRITE’DPTIND=__„mu•t b• I
Tor CADAM LtnK’
CONTINUE
Figure 31. Flowchart 2
3. Introduction to Program HESCAD 47
ä OI 6
SST LP
°°""‘°" nova oaosarnxcsT¤ +¤<~>
GEGETRY DATA
2 7
/LNIT/NI„NJ•
FG? READ.WRITE„orsx 110 T° "'°‘"’(ALSO IN MAIN)
3 a
/TEST/. . . ·MVS TSSTT¤
~ IN BLAN( COOMZN(ALSO IN LOACERI
·‘•9
/GEG4/DBARNLGJSFOR GEORETRICAL HRITE IEENT.
VARIABLES NOT IN HI.!·D„TE$TBLAN( CGMEN . CN LNIT
(ALSO IN rDISKPRINTI .2)
5
ENDCQ.LEC
DIMENSIGITSS’l’„HI,I·DI£|T(20)
Figure 32. Flowchart 3
3. Introduction to Program HESCAD 48
I
CLMIN/LNIT/NI,ND,
NIISKV /GEL)!/HI.!-¤.TESTINTEGE?
¤?AHID„USERID•GRQP
2
DIIENSILNHI.!-D.TE$T„
IENT.LSERID„mAHID.GRaP
3 .
DATAUS€RID.GRt1PDATA(TO SET
LP VIEHS)
4
READ ECM FILE‘CN PDISK INTO
HI.!-D.TEST
5
IIJVE FIRST FIVEHCROS W IEIT
_ TO DRAHID
6
START MARINE
CALL CADU
Figure 33 . Flowchart43
. Introduction to Program HESCAD 49
I
SPV
START PRIMARY(FRGITWIEW
DRAMALL GEUETRY
END VIEW
STV
START Tt]? VIEWDRAM
ALL GEUETRYEN) VIEW
SSV
START SIDE VIEWDRAM
ALL GEGETRYEND VIEW
4
DRAMWIREFRAME
!@EL
B0 ERRORs1~¤.E Eggs
Figure 34. Flowchart 5
3. Introduction to Program HESCAD 50
IBIIIY-S
FRGJT VIEWPYLOJ8„rDSE•
TAIl.BGII„B®Y•ROT€R8„NABELI..ES
2TI-EN H.SE
WINBS-S 6FRINT VIEW WIIGS?
ELSEHN?
SBROJTIPE
Hl vw-S 7mom vxau mw Auxzumv ELSE
NA$.LEéRypéxsw PRGLLSIW?
SlBRü.I'|'I!£S DE
6
==¤•=¤¤—¤—¤HiFRGJTVIEW
ANITIGIAL NACH.LE•CGPGETS PRIPELLGR
SBRGJTIIES
I2FINISI-I·S
FINAL ELDENTS
EN)SPV
Figure 35 . Flowchart 6
3 . Introduction to Program HESCAD 51
IB®Y-S
TW VIE!PYLG87rUSE•
TAIL.BC!I4„B®Y•ROT¢RS„NACEI.LES
2T}-EN CGPGID?
ELSEHIFBS-S 6ELSE
FRINT VIEWHIW
S.BRüI'|'I|€
ll ··=~==·== 7man vzcw Auxzumv
Hlß PRWLLSIGI? _
PRÜELLCR SBRGJTIPESBRGJTIPES
8
•=¤••P¤¤~¤-S@§FRQITVIEH
AWITICNAL NA£.LE•$9GETS PRGELLM .
SLBRGJTIIES
I2
FINISH-S
Figure 36. Flowchart 7
3. Introduction to Program HESCAD 52
I.5.3 gv
IBWV-S
LET SIDE VIEWPYLCNSJDSE
TAILBU)47B®Y„RÜTm$•NÄc¤-LES
2TPD4 ELSE
UIIBS-S6
FRGIT VIEWELSE
HIW$.BROJTIhE
7man vxzw FRONT wxrumv ELSE
NACE..LEd;yp:;IEw PRWLLSICN?
PRÜEU-,£s SBRIIJTIE —
6WMS E EFRCNT VIEW
AWITIGNAL NACE|.I.E„CGPGENTS PRGELLGI
StBR(1ITIP£S
I2FINISH-S
DDSSV
Figure 37 . Flowchart 8
3. Introduction to Program HESCAD 53
1 .6 umen
I
TPV
START PRIMARY(FRONT) VIEW
DRAWALL GEIMETRY
EID VIEW
_ TTV
START TOP VIEW 'DRAW
ALL GEONETRYEND VIEW
TSV _
. START SIDE VIEWDRAW
ALL GEDMETRYEN) VIEW
4TWFRAM
DRAWWIREFRAME
MCDEL
ERRORENDumen EHS
Figure 38. Flowchart 9
3. Introduction to Program HESCAD 56+
I .6. I TPV
I
BCDY-T
FROIT VIEWPYLüI8.&E•
TAILB$I.B®Y•RGTG?S•NACE|.J..ES
2ESETHEN
GGPGIID?
Imä-T 6ESE
FRCNT VIEWWDG
SBRGJTIPE
AUX-T WIMBS-T 7ppm; man Auxxtmzv ELSEwxuämw •·¤¤•=¤—=r¤~#PR(PEI.I..m §ßRQJT
S.BROJTIP€SIü
6GtIPG}D-T AUX-T PURE-T
FRINT VIEWU
ANITIINAL NACELLE .dIPO€I¤|"I’S PRWELLUR
SIBRGITIIES
I2FINISH-T
Figure 39. Flowchart 10
3. Introduction to Program HESCAD 55
I .6.2 TTV
IB®Y-·T
TW VIEWPYLG43„Ni.
[email protected]®Y•ROT$S.NACE.LES
2I'I-EN Ei
. Of!Pü.N)?WIMBS-T 6Ei
FRINT VIEW HCNBS?WIN
' SBRGJTIPE
AUX-T Ubi-T 7mom vxsw wxnxmv
EI-$€NACELLE.
WIIÄIEW PRGLLSIM?
susnanmzs S°“°R°“mE
8d}Pt1.N)-T AUX-T PIRE-T
FRIINT VIEWAWITIGIAL NACELLE„CGPGBITS PRCPEJJR
SLBRCUTIPES
I2
FINI94-T
FINAL ELEIENTS
DDTTV
Figure 40. Flowchart ll
3 . Introduction to Program HESCAD 56
l.6.3 TSV
IBQY-T
LET SIE VIEWPYLG|S„hD$E•
TAILB®1•B®Y•R0’TlRS„NACELLES
2TPEN EI.SE
CGPCIID?WIE-T 6FRCNT VIEW WIIGS?
ELSEWIPG
SBRGJTIIE
AUX-T WIIGS·T 7
mom vzsw Auxxumv El-SEuAca.1.:. FRWT VTEV PRGLLSICN?mopaion VING
suanomxrcs$*ß*°'·¤’T*€
6GIPGID-T AUX-T PLRE-T
FRGIT VIEWAWITIINAL NACELI...E•CGÜGETS PRGELLM '
SLBR|1ITI£S
I2FINIS-I-T
FINAL ELEFENTS
QDTSV
Figure 41. Flowchart 12
3. Introduction to Program HESCAD 57
K E- iaX\**
„_A?/ Ä| ·|>- « ; ,,„§|• • >- < Ä 2V
·•··|
>GI-r-'I
>¤
/ E63
_ CD
G-2,·_| „
<¤:3
E4 4-*e ¤
·r-4>< 9% ‘ ‘·-_\‘\ N Q-•
^ 22In
qwvkg-_ 2w · ‘=;·~$@\_;:»
‘°>‘ I
3. Introduction to Program HESCAD 58
1E-X
T/ AQnääeéé , . . - | II' / maß ' 1 •
ALVIP gI E
E°§
' .2" :>«
H4-*_ GJE3
· (D
EQ
E
. >P “‘—l;l_NX\
‘Im \IP
X
>-„
3. Introduction to Program HESCAD $9
4. SYSTEM ARRANGEMENT FOR COMPUTER GRAPHICS
In this research IBM 3250, 3277, and 5080 CAD/CAM workstations and
an IBM 4341 mainframe were used.
The workstation consists of the display buffer, controller, and the
digitally driven display. The feedback between the user and computer is
achieved by the light pen (digitizing tablet and cursor for 5080) , key-
board, and lighted program function keyboard operating back through the
controller.
The IBM 5080 workstation is a high resolution color raster display
system. It consists of the IBM 5085 Graphic Processor Unit, which con-
trols display operations and attachments to the system, an alphanumeric
keyboard, lighted program function keyboard, tablet, dials and raster
display. ·
The IBM 3250 is a vector display. It consists of an alphanumeric
keyboard, lighted program function keyboard, and light pen and vector
display.
The display buffer is used to store the display list and the sequence
of words which defines the views to be drawn on the workstation. Each
word of the display list describes a basic geometry segment. The con-
troller is used to repetitively retrieve the display words from the buffer
in their proper sequence, and to derive certain other commands such as
timing and intensity signals. When the drawing is to be changed , the
controller provides data-handling facilities for accepting information
from the central processor and placing it in the display buffer [10].
4. System Arrangement for Computer Graphics 60
5. ERROR TRACE METHOD
The purpose of the following section is to describe an error trace
method for equal spacing of the cross-section outline.
It is desired to construct a wire—frame with equally spaced segments
in the longitudinal direction. The number of these segments can also be
changed easily. The cross-section outlines consist of various curve
segments, resulting in discontinuous intersections. Also, there is a lack
of proportional relationship between some cross-sections. For example,
the wing cross-section consists of one straight line, a small arc and
another large arc. The intersection of these two arcs does not have a
common tangent. Furthermore there is no proportional relationship be-
tween the wing°s root and tip cross—sections. Mathematically speaking,
it is difficult to divide such discontinuous segments into equally spaced
parts, and prevent occurrence of twisted lines when two cross-sections
are linked. The following technique can overcome this difficulty.
Fig. 22 and A4 show the outline of a cabin cross section. Divide
the cabin cross-section outline into 9 segments. Specify equal arc length
along the perimeter beginning at the "starting point", moving counter-
clockwise.
Equations:
Segment l length: SEGI = W/2.-ZR1
Segment 2 length: SEG2 = Rln/4.
5. Error Trace Method 61
Segment 3 length: SEG3 = H-R1-R2
Segment 4 length: SEG4 = Rzn/4.
Segment S length: SEG5 = W/2.-2R2
Segment 6 length: SEG6 = Rzn/4.
Segment 7 length: SEG7 = H—Rl-R2
Segment 8 length: SEG8 = Rln/4.
Segment 9 length: SEG9 = W/2.-2Rl
Where H is the height of the cabin and W is the width of the cabin
and R is the radius of the cabin arc.l
S = Ltotal/Ntotal = (SEGl+SEG2+...+SEG9)/Ntotal
Where Ltotal is the total length of the cabin cross-section outline
and Ntatal is the number of the points to be drawn on the outline.
The number of points which will be drawn on the segment using arc
length S is:
NP = SEG /Sn n
Where S is the equal spacing arc length.
Comparing the length of segment n and the total length of arcs drawn
on the segment n one can see an error n. This error is always positive.
Specify ERROR0 = 0., the general equation for this technique has the form:
ERROR = SEG -NP *S+ERROR >0.0n n n n-1
5. Error Trace Method 62
For example, the error on segment 1 is error 1 and this error (see
Fig. 44) is:
ERRORI = SEGl—NPl*S >0.0
Then compute the points on segment 2. The number of points which will
be drawn on the segment 2 are:
NP2 = (SEG2+ERROR1)/S
Comparing the length of segment 2 and the total length of arcs drawn
on segment 2 one can see an error 2 (see Fig. 44).
ERRORZ = SEG2-NP2*S+ERR0R1 >0.0
Continue this way until the last point is drawn. In the same way,
other cross section outlines can be divided into equally spaced arcs.
Figure 45 and 46 show the error trace results in pylon and wing. Using
this technique, the user can specify any number of splines or straight
lines around the helicopter cross-section to construct wire-frame . The
suggested number of points drawn on the cross-section is listed in Table
1.
S. Error Trace Method 63
SEG: SEG9
ERROR: ERRORS
ERRCR2 SEM SEGa:::2:20:27
STARTIN3 POINT
SEG}‘
• SEG7
ERRO?3 Z ERRCR6SEG4 SEG6
ERRO:24 ERRQS
SEG5
EERROR DISTRIBUTIGJ
,IÜ¢$l€·7$¢ll¤äT£*l$äÜ
‘„J
0R w 22SPLIIEAS
ORAH 28 SPLIPES
Figure 44. Error Trace and Its Results (Fuselage)
5. Error Trace Method 64
ennone
summe mm-:
SEG? sam
see:amoms
enmmu
ceuven pornr
ERROR ¤1sTR1BuT10N
f..6==’?iiIIIIl\¤
?
·
ß},Ö
0RAw so LINES
Figure 45. Error Trace amd Its Results (Pylon)
5. Error Trace Method 65
CENTER POINT SEGI
SEG2
SEG3 STARTING vormERROR2
ERROR DISTRIBUTION
~¢'~p;§§'
QéllllEE!EE!llll!E!EE==::::::=====55EEEE§§§;'
DRAW 22 LINES
Figure 46. Error Trace and Its Results (Wing)
5. Error Trace Method 66
6. INPUT VARIABLES FOR HESCAD
A file named COLLEC which provides a linkage will be described in
detail in this section. HESCOMP subroutines LOADER, PRINT as well as the
MAIN program are modified. A new subroutine called COLLEC is also added.
The function of COLLEC is to extract all pertinent geometry variables
from the appropriate common block and elsewhere in HESCOMP, and write them
to a sequential disk file for subsequent interpretation by HESCAD.
HESCAD does not require all these variables as input but they are
available for future additions or modifications. General changes to the
model may be made directly to this file, if desired, without using
HESCOMP.I
The following table gives the array locations in HESCAD and the order
in the sequential file for all these variables. Note that HI and HO share
the first 100 records followed by TEST. HI is an echo of the variables
given as input to HESCOMP while HO contains variables ( sometimes the same
ones specified in HI) computed by HESCOMP. The HESCOMP FORTRAN name is
also given, along with a brief description of the variable. If a more
complete description of the variable is needed consult the HESCOMP manual.
6.I. VARIABLE DEFINITION
Table 4, 5 and 6 show all input and output geometric variables col-
lected, a.nd the output by subroutine COLLEC. These variables are placed
in three arrays, and written to a sequential disk file on LUN 10 as shown
6. Input Variables For HSCAD 67
in the program description section. See the HESCOMP manual for further
definition of these variables. The variables named TEST (See Table 3)
are decision variables for computation or helicopter options. H1 vari-
‘ ables designate HESCOMP input while HO variables designate HESCOMP out-
put.
Table 4. TEST Data [1]
Array Variable Fortran Name Description
TEST( 1) OPTID OPTIND 0 = aircraft weight; 1 = aircraft size;2 = performance only; 3 = fuel iter-
. ation
TEST( 2) CNFIND CNFIND 1 = single rotor; 2 = tandem rotor
TEST( 3) AUXIND AUXIND 1 = pure helicopter; 2 = including wing(only); 3 = including auxiliary pro-pulsion (only); 4 = compound (wing &auxiliary propulsion)
~TEST( 4) RDMIND RDMIND 1 = input DM, 0; 2 = input; 3 = input
DMR,CT/0, W/A, c; 4 = input W/A, CT/c
TEST( 5) FIXIND FIXIND O = input fixed size primary engine; 1= prog. size primary engine
TEST( 6) ROTIND ROTIND 1 = short from rotor performance; 2,3= rotor map input; 4,5,6 = L/De rotor
map input
TEST( 7) SWIND SWIND 1 = input Sw; 2 = input W/S; 3 = size
for maneuver
TEST( 8) bwIND BWIND 1 = input bw/D; 2 = input AR; 3 = deter
by prop clear
TEST( 9) AIPIND AIPIND 1 = no independent auxiliary engines;2 = independent auxiliary engines
6. Input Variables im rmscw 68
Table 4. TEST Data [1]
(continued)
Array Variable Fortran Name Description
TEST(10) ENGIND ENGIND O = T/shaft independent auxiliary en-gine; 1 = T/fan or T/jet independent
' auxiliary engine
TEST(11) FIXINDI FXINDI O = input fixed size auxiliary inde-pendent engine 1 = prog. size auxiliary
. independent engine
TEST(12) TRDIND TRDIND 0 = no tail rotor; 1 = prog. usesDTR
trend; 2 = input DTR; 3 = input (T/A)
net
TEST(13) TRSIND TRSIND l = inputUTR; 2 = input CT/¤
_ TEST(14) VTFIND VTFIND 1 = input ARVT, CVT; 2 = input CLD ,ES
VDES, CVT; 3 = input CLDES, VDES, ARVT
TEST(15) HYIND HTIND 0 = no horizontal tail; 1 = fixed sizehorizontal tail; 2 = input tail volumecoefficient
TEST(16) MRPIND MRPIND 0 = input XM/IB; 1,2 = prog. calc XM/IB
TEST(17) FDMIND FDMIND 1 = input ((0/L)/D), rotor posn°s; 2 =input ((0/L)/D), IB
TEST(18) APHIND APHIND 1 = input hp ; 2 = input g/s2
TEST(19) ESCIND ESCIND 1 = size primary engine for T/O only;2 = size primary engine for T/0 orcruise
TEST(20) DTRE/DFAN DTRODF NOM = 1.0; else, fenestron
TEST(21) FANOPH FANOPH NOM = 0.0; else, fenestron
TEST(22) FANOPC FANOPC NOM = 0.0; else, fenestron
6. Input Variables For HESCAD 69
Table 5. Helicopter Geometry Input Data [1]
--—- BODY —---
Array Variable Fortran Name Description
HI( 1) XM/lb DAM 7 Ratio of distance from tip of nose torotor shaft, XM. to main fuselage
length (B) (single rotor helicopter)
HI( 2) (ßTb/dTB) ELTDB Fineness ratio of tail boom
HI( 3) dTT /dT DTBDTB Ratio of average tail boom tip diameterB B . . .to average tail boom diameter (singlerotor helicopter)
HI( 4) kT STING SKTING Tail boom length extending aft rotor' center as a fraction of tail rotor ra-
dius
HI( 5) ((0/L)/D) DAM 8 Tandem rotor overlap/main rotor diam-eter ratio _
HI( 6) X1/£P DAM 9 Distance of forward rotor center fromaircraft nose as a fraction of aircraftnose section length
HI( 7) X /ß DAM 10 Distance from aft rotor center from2 T . . .aircraft tail cone as a fraction of
aircraft tail _
HI( 8) hF HF Height of fuselage (ft)
HI( 9) WF WF1 Width of fuselage (ft)
HI(10) (1/d)P ELDP Fineness ratio of aircraft nose section
HI(ll) (2/d)T ELDT Fineness ratio of aircraft tail section
HI(l2) ZCONST DAM 6 Constant diameter section (cabin)length (ft)
HI(13) ZRW ELRW Length of ramp well (ft)
6. Input Variables For HESCAD 70
Table 5. (continued)
---- HORIZONTAL TAIL ----
Array Variable Fortran Name Description
HI(14) ARHT ARTH Horizontal tail aspect ratio
HI(lS) 2TH ELTHP Horizontal tail moment arm (ft) -measured from rotor center line to tailC/4
HI(l6) (t/C)HT TCHT Horizontal tail mean thickness to chordratio
HI(l7) VH VBARH Horizontal tail volume coefficient
HI(l8) KH SLMH Taper ratio of horizontal tail
HI(l9)SHT
DAM3 Area of horizontal tail. Used whenHTIND = 1
-·—· WING --·—
Array Variable Fortran Name Description
HI(20) Sw DAM 1 Wing platform area (ftz)
HI(21) b /D BWD Ratio of wing span to main rotor diam-W eterHI(22) AR DAM 2 Wing aspect ratio
HI(23) (t/C)R TCR Wing root thickness to chord ratio
HI(24) (t/C)T TCT Wing tip thickness to chord ratio
HI(25) AC/4 DMLC4 Sweep angle of wing quarter chord (de-grees)
6. Input Variables For HESCAD 71
Table 5. (continued)
—--- WING ~-·-
Array Variable Fortran Name Description
HI(26) X SLM Taper ratio of wing
HI(27) CF/C CFC Ratio of download alleviating flapchord to wing chord
HI(28) h'/hF HPHF Ratio of wing height on fuselage (rel-ative to the bottom of the fuselage),h', to the total fuselage height, hp
---- AUXILIARY PROPELLER ENGINE ··--
Array Variable Fortran Name Description
HI(29) YCL YCL Clearance from inboard propeller tipto· inboard propeller tip acrossfuselage (ft)
HI(30) gz ZETA l Propeller over wing tip overlap (frac-tion of radius)
--·- GEN ----
Array Variable Fortran Name Description
HI(3l)ASWET
DSWET Incremental wetted area of aircraft2(ft)
HI(32)ASWET/SF DLSWSW Incremental wetted area of airplane
ratio to fuselage wetted area
6. Input Variables For HESCAD 72
Table 5. (continued)
--—— PRIMARY ENGINE NACELLE —---
Array Variable Fortran Name Description
HI(33) Z1 AZETA1 primary engine nacelle dimensionalfactors
HI(34) Z2 AZETA2 Ditto
HI(35) Z3 AZETA3 Ditto
HI(36) £AIP/2C ELLEP Ratio of air induction system lengthto engine length
—·—· VERTICAL TAIL -—·—
Array Variable Fortran Name Description
HI(37) ARVT DAM 11 Vertical tail aspect ratio
HI(38)XVT
SLMVT Taper ratio of vertical tail
HI(39) (t/C)VT TCVT Vertical tail mean thickness to chordratio
HI(40) ;vT DAM 5 Vertical tail span overlapdistance/tail rotor radius ratio - in-put as a fraction of tail rotor radius
HI(41) b DAM 12 Vertical tail span; only when CNFIND =VT VTFIND and TRDIND = 0
6. Input Variables For HESCAD-
73
Table 5. (continued)
---- AUXILIARY INDEPENDENT ENGINE NACELLE -—·-
Array Variable Fortran Name Description
HI(42) Z4 AZETA4 Auxiliary independent engine nacelledimensional factors
HI(43) Z5 AZETAS Ditto
HI(44) Z6 AZETA6 Ditto
HI(45) ßAIA/£eA ELLEA Ratio of air induction system lengthto engine length
HI(46) AS/SSTR DSSTR Ratio of incremental auxiliary inde-pendent engine nacelle strut platformarea to auxiliary independent enginenacelle strut platform area
HI(47)bNS/dNI
BNSDN1”
Ratio of auxiliary independent enginenacelle strut span to nacelle diameter
---- ROTOR CHARACTERISTICS ·---
Array Variable Fortran Name Description
HI(48) NR ENR Number of rotors
HI(49) DMR DAM 15 Main rotor diameter (ft)
HI(50) OM DAM 16 Main rotor solidity (c=bc/nR)
HI(5l) BT THETM Main rotor blade twist (degrees)M
HI(52) X XC Main rotor blade cutout (end of bladeCMR shank, beginning of rotor airfoil
sections) position as a fraction ofrotor radius
6. Input Variables For HESCAD 74
Table 5. (continued)
---- ROTOR CHARACTERISTICS ----
Array Variable Fortran Name Description
HI(53) XM XMR Main rotor blade attachment point as afraction of rotor radius
HI(54) (t/C) TVCMR Main rotor blade thickness to chord.25R . .ratio @0.25 rotor radius
---- TAIL ROTOR CHARACTERISTICS ----
» Array Variable Fortran Name Description
HI(55) DTR DAM 18 Tail rotor diameter (ft)2
HI(S6) GTR DAM 19 · Tail rotor solidity (G=bc/HR)
HI(57) bTR BTR Blade number of tail rotor
HI(S8) BT THETTR Tail rotor blade twist (degrees)TR
HI(59)XCTR
XCTR Tail rotor blade cutout (end of bladeshank, beginning of rotor airfoil
· sections) position as a fraction ofrotor radius
HI(60)XTR
XTR Tail rotor blade attachment point as afraction of rotor radius
6. Input Variables For HESCAD 75
Table 5. (continued)
-——— TAIL ROTOR SIZING CONDITION ·---
Array Variable Fortran Name Description
HI(6l) GMR/TR G Gap between tail rotor disc and mainrotor disc (ft)
HI(62)KTRS CKTRS Tail rotor solidity multiplicative
factor (used to determine tail rotorsolidity)
---— FORWARD ROTOR PYLON ----
Array Variable Fortran Name Description
HI(63) (t/C)RF FTCRF Forward rotor pylon root thickness tochord ratio
HI(64) (t/C)TF TCTF Forward rotor pylon tip thickness tochord ratio
HI(65) ARFP ARFP Forward rotor pylon aspect ratio (tan-dem rotor helicopter)
HI(66)XFP
SLMFP Taper ratio of forward rotor pylon
HI(67) hp HPI Forward rotor pylon height (ft)1
6. Input Variables For HESCAD 76
Table 5. (continued)
-·-- AFT ROTOR PYLON ----
Array Variable Fortran Name Description
HI(68) (t/C)RA TCRA Aft rotor pylon root thickness to chordratio
HI(69) (t/C)TA TCTA Aft rotor pylon tip thickness to chordratio
HI(70)ARAP
ARAP Aft rotor pylon aspect ratio (tandemrotor helicopter)
HI(7l)XAP
SLMAP Taper ratio of aft rotor pylon
HI(72) hp DAM 13 Aft rotor pylon height (ft)2
HI(73) g/S GS Tandem rotor gap/stagger ratio
---- MISCELLANEOUS ---- .
Array Variable Fortran Name Description
HI(74) d, DI Position of inboard under wing store1 (fraction of wing semi-span)
HI(75) d DZ Position of outboard under wing store
° (fraction of wing semi-span)
6. Input Variables For HESCAD 77
Table 6. Single Rotor Helicopter Geometry Output Data [1]—·-—
BODYArrayVariable Fortran Name Description
HO( l) EF ELFF Length (body + tail boom)
HO( 2) EC ELC Length (cabin)
HO( 3) EB ELB Length (body)
HO( 4)ETB ELTB Length (tail boom)
HO( 5) XM XM Main rotor location
HO( 6) WF WF1 Width
HO( 7) SF SF Wetted area
WINGArrayVariable Fortran Name Description
HO( 8) AR AR Aspect ratio
HO( 9) Sw SW Area
HO(l0) bw BW Span
HO(ll) Cw CBARW Mean chord’
DMLC4 Quarter chord sweep
H0(13) X SLM Taper ratio
H0(l4) (T/C)R TCR Root thickness/Chord
HO(l5) (t/C)T TCT Tip thickness/Chord
6. Input Variables For HSCAD 78
Table 6. (continued)
—·—- WING -—--
HO(16) WG/Sw WSW Wing loading
H0(l7) CF/C CFC Flap chord/Mean chord ratio
-·-· HORIZONTAL TAIL —---
Array Variable Fortran Name Description
HO(l8) ARHT ARHT Aspect ratio
HO(l9)SHT SHT Area
HD(20)bHT BHT Span
H0(2l) CHT CHT Mean chord
H0(22)XHT
SLMM Taper ratio
H0(23) (T/C)HT TCHT Thickness/Chord
H0(24) LTH ELTH Horizontal tail ARM
---- VERTICAL TAIL ·—-·
Array Variable Fortran Name Description
H0(25) ARVT ARVT Aspect ratio
H0(26) SVT SVT Area
H0(27) bVT BVT Span
6. Input Variables For HSCAD 79
Table 6. (continued)
---- VERTICAL TAIL ·---
Array Variable Fortran Name Description
HO(28)CVT
CBARVT Mean chord
HO(29)XVT
SLMVT Taper ratio
HO(30)ZTR ZTR Tail rotor (vert.) location
HO(3l)CVT HVT Tail rotor/Vertical tail overlap ratio
HO(32) (T/C)VT TCVT Thickness/Chord
---- MAIN ROTOR PYLON ----
Array Variable Fortran Name Description
H0(33) AR ARFP Aspect ratio
HO(3k) SFP SFP Wetted area
HO(3S) FAFP FAFP Frontal area
H0(36) HP HPI Height1
HO(37) CFP CBARFP Mean chord
HO(38)XFP
SLMTP Taper ratio
H0(39) (T/C)R TCRF Root thickness/Chord
H0(40) (T/C)T TCTF Tip thickness/Chord
6. Input Variables For HESCAD 80
Table 6. (continued)
---- PRIMARY ENGINE NACELLE --—-A
Array Variable Fortran Name Description
H0(4l) EN ELN Length
HO(42) DN DBARN Mean diameter
H0(43) SN SN Wetted area (total for all engines)
--—- AUXILIARY INDEPENDENT ENGINE NACELLE STRUT ·-—-
Array Variable Fortran Name Description
· HO(44)SSTR
SSTR Wetted area (total)
HO(45) bNS BNS Span
H0(46) CNS CNS Mean chord
---- AUXILIARY INDEPENDENT ENGINE NACELLE ----
Array Variable Fortran Name Description
HO(l+7)LNI
ELNI Length
H0(48) DNI DBARNI Mean diameter
H0(49) SNI SNI Wetted area
6. Input Variables For HESCAD 81
Table 6. (continued)
—-—— MAIN ROTOR ·-·-
Array Variable Fortran Name Description
HO(S0) DM DM Diameter
HO(5l) GM 'SIGMR Solidity
HO(52) NR ENR Number of rotors
HO(53) NO. BLADES BMR Number of blades/Rotor
HO(54)BMR
THETMR Blade twist
HO(5S) XC XC Blade cutout/Radius ratio
_ -——- TAIL ROTOR ----
Array Variable Fortran Name Description
HO(56) DTR DTR Diameter
HO(57)cTR
SIGTR Solidity
HO(58) NO. BLADES BTR Number of blades/Rotor
HO(S9) GTRTHETTR Blade twist
HO(60)XCTR
XCTR Blade cutout/Radius ratio
HO(61) G G Main/Tail rotor GAP
6. Input Variables For HESCAD 82
Table 6. (continued)
---- PROPELLER (AUXILIARY PROPULSION) ----
Array Variable Fortran Name Description
HO(62) DAR DAR Diameter
HO(63)¤AR• SIGAR Solidity
HO(64)NAR ENRI Number of propellers
H0(65) NO. BLADES BLDN number of blades/Propellers
Table 7. Tandem Rotor Helicopter Geometry Output Data [1]
--—· BODY ---—
Array Variable Fortran Name Description
HO(66) AX1 DXl Forward rotor location
H0(67) AX2 DX2 Aft rotor location
HO(68) G/S GVS Rotor GAP/STAGGER ratio
H0(69) (0/L/D) OLD Rotor OVERLAP/DIAMETER ratio
---- AFT ROTOR PYLON ——··
Array Variable Fortran Name Description
HO(70) AR ARAP Aspect ratio
6. Input Variables For HESCAD 83
---- AFT ROTOR PYLON ——-·
Array Variable Fortran Name Description
HOUU SAP SAP wanted areaHO(72) HP HP2 Height
2H0(73) CAP CBARAP Mean chord
HO(74) KAPSLMAP Taper ratio
HO(75) (T/C)R TCRA Root thickness/Chord
HO(76) (T/C)T TCTA Tip thickness/Chord
~-—- FORWARD ROTOR PYLON ···· .
' Array Variable Fortran Name Description
HO(77) AR ARFP Aspect ratio
H0(78) SFP SFP Wetted area
H0(79) FAFP FAFP Frontal area
H0(80)P
HP HPI Height1
HO(8l) CFP CBARFP Mean chord
H0(82) KFPSLMP Taper ratio
HO(83) (T/C)R TCRF Root thickness/Chord
HO(84) (T/C)T TCTF Tip thickness/Chord
HO(8S) GRW GRW Rotor/Wing GAP
6. Input Variables For HESCAD 84
6.2. GEOMETRY EQUATIONS
The point equations are written based on geometric specifications.
For the typical tandem rotor helicopter main rotor pylon and aft rotor
pylon the geometry equations are as follows [1]:
1. Main rotor pylon
X = C /CFP TFP RFP
^11pp = Zhpl/(CR (1 + 1pp11FP
2. Aft rotor pylon
X = C /CAP TAP RAP .
ARAP = 2hP2/(CRAP(l + xAP))
See Fig. 47 and Table 6 for variable definition.
Typical single rotor helicopter main rotor pylon and vertical tail
geometry equations are as follows:
1. Main rotor pylon
^FP = °TFp’°RFP= 2h /(C (1 + X ))ARFP Pl v RFP FP
Z.] Vertical tail
X = C /CV1 Tvr Rvr
6. Input Variables For HESCAD 85
” Mw = bm?/SwSee Fig. 47 and Table 6 for variable definition.
6.3. POINT EQUATIONS
HESCOMP computes dimensions of the model. To produce a CAD model
coordinates of points are needed. Due to the current structure of the
CADAM GIM, coordinate transformations must be applied by the user. For
these reasons, numerous point equations were written according to heli-
copter geometry specifications.
As development of HESCAD progressed, certain methods of generating
geometry are exchanged for others which are deemed more suitable. In this
case the previous point equations are retained in the code for possible
future use. During development of the geometry, some points were written
to the CADAM drawfile for Verification. These point CALLs were subse-
quently commented out to reduce the model size. If major manual (at the
CADAM scope) design changes are to be made to the helicopter model, it
may be advantageous to restore these point CALLs by removing the C°s in
column one. These points equations are taken directly from the first
formal release of HESCAD code (September 1985).
6. Input Variables For HESCAD -86
6.3.1. SINGLE ROTOR HELICOPTER POINT EQUATIONS
Single Rotor Helicopter Side View Point Equations
See Fig. 48 and Fig. 56 for the location of the points corresponding to
these coordinates.
B IS THE DISTANCE BETWEEN PYLON AND ROTOR.
B=l.
- C AND C2 ARE TO DETERMINE THE CABIN ARCS IN THE SIDE VIEW, Cl IS A PER-
CENTAGE TO DETERMINE THE JET ENGINE NACELLE°S CENTER IN X COORDINATE.
C =O.2
C1=0.25
C2=0.2S ·
C3=HO(32)*HO(28)/2.I
C4 IS A PERCENTAGE TO DETERMINE THE JET' ENGINE OR PROPELLER ENGINE
NACELLE°S CENTER IN Y COORDINATE.
C4=HI(28)I
TTIP=HO(l5)*HO(ll)
TROOT=HO(l4)*HO(ll)
PI=3.14l5926
POINTS FOR BODY
XS( l)=-0.5*HO(6)
_ YS( l)=-B—HO(36)-HI(8)+C2*HI(8)
XS( 2)=XS(1)
YS( 2)=-B-HO(36)-C2*HO(6)
XS( 3)=xs(1)+C*HO(6)
6. Input Variables For HSCAD 87
YS( 3)=·B-HO(36)
XS( 4)=-XS(3)
YS( 4)=YS(3)
XS( 5)=0.5*HO(6) l
YS( 5)=YS(2)
XS( 6)=XS(5)
YS( 6)=YS(l)
XS( 7)=-HO(20)/2.
YS( 7)=-B-HO(36)-0.225*HI(8)O
XS( 8)=-XS(7)
YS( 8)=YS(7)
‘XS( 9)=-Cl*HO(l0)
VYS( 9)=-B—HO(36)—C4*HI(8)-HO(48)/2.
XS(lO)=HI(29)+H0(62)
YS(l0)=-B-HO(36)-C4*HI(8)-HO(48)/2.O
POINTS FOR WINGS
XS(ll)=—HO(l0)/2.+TTIP/2.
YS(ll)=-B·HO(36)•C4*HI(8)
XS(12)=-HO(l0)/2.l
YS(12)=YS(ll)+TTIP/2.
XS(13)=XS(l1)
YS(13)=YS(ll)+TTIP
XS(l4)=XS(1)
YS(14)=—B-HO(36)-CA*HI(8)+TROOT
XS(lS)=XS(l4)
YS(l5)=-B~HO(36)—C4*HI(8)
6. Input Variables For HESCAD 88
XS(l6)=—XS(14)
YS(16)=YS(l4)
XS(l7)=—XS(l5)
YS(l7)=YS(lS)
XS(l8)=-XS(ll)
YS(l8)=YS(l1)
XS(l9)=-XS(l2)
YS(19)=YS(l2)
XS(20)=·XS(l3)
YS(20)=YS(l3)
POINTS FOR PYLON
XS(2l)=-HO(39)*HO(37)/2.
YS(21)=YS(3)
XS(22)=·XS(2l)
YS(22)=YS(3)
XS(23)=-HO(40)*H0(37)/2.
YS(23)=—B
XS(24)=—XS(23)
YS(24)=-B
POINTS FOR MAIN ROTOR AND TAIL ROTOR
XS(25)=0.0
YS(2S)=-B
XS(26)=—0.5*HO(50)
YS(26)=0.05*HO(S0)/2.
XS(27)=0.0
YS(27)=0.0
6. Input Variables For HESCAD 89
XS(28)=—XS(26)A
YS(28)=YS(26)
XS(29)=0.35*HO(6)
YS(29)=-B—HO(36)-0.1*HI(8)+HO(30) A
XS(30)=0.5*HO(32)*HO(27)/(HO(29)+l)/HO(2S)
YS(30)=YS(29)
XS(3l)=XS(29)+.l0*HO(56)/2.
YS(31)=YS(29)+0.5*HO(56)
POINTS FOR VERTICAL TAIL
XS(32)=·0.5*HO(32)*HO(Z7)/(HO(29)+l)/HO(25)
YS(32)=·B—HO(36)-0.1*HI(8)+HO(27)-C3
XS(33)=0.0l
YS(33)=YS(32)+C3
XS(34)=·XS(32)ß
YS(34)=YS(32)
XS(35)=—H0(32)*HO(27)/(1/HO(29)+l)/HO(2S)
YS(36)=—B
YS(37)=-B-H0(36)-HI(8)
XS(37)=XS(l)+C2*HI(8)
XS(38)=-XS(37)
YS(38)=YS(37)
POINTS FOR THE PRIMARY ENGINE NACELLES
C XS(39)=XS(8)+0.5*HO(42)
C YS(39)=l.l*YS(4)
6. Input Variables For HSCAD 90
C XS(40)=XS(24)
C YS(40)=YS(8)+0.5*HO(42)
C XS(4l)=-XS(40)
C YS(41)=YS(40)
C XS(42)=-XS(39)
C YS(42)=YS(39)
XS(43)=XS(31)V
YS(43)=YS(31)-HO(56)
SFl DETERMINES THE PERCENTAGE OF NOSE HEIGHT (MEASURED FROM THE BELLY)
WHICH MARKS THE START OF THE WINDSHIELD. V
SF1=0.4
SF2 DETERMINES THE PERCENTAGE OF THE NOSE LENGTH (MEASURED FROM THE TIP)
WHICH MARKS THE START OF THE WINDSHIELD.
SF2=O.6
B=SF1*ABS(YS(21)·YS(37))
. D=HI(10)*SF2
E=SQRT(B*B*D/HI(10))
XS(44)=0.0
YS(44)=YS(37)+ABS(YS(21)·YS(37))*SFl+E
POINTS FOR PLACEMENT OF PRIMARY ENGINE NACELLES
C XS(4S)=XS(2)
C YS(45)=YS(44)-HO(6)/2.
C XS(46)=XS(5)
C YS(46)=YS(45)
C XS(47)=XS(22)-ABS(XS(22)-XS(24))
C YS(47)=YS(22)
6. Input Variables For HESCAD 91
C XS(48)=-XS(47)
C YS(48)=YS(47)
XS(49)=H0(40)*HO(37)/2.+HO(42)/2.
YS(49)=YS(3)+HO(42)/2.
XS(50)=-XS(49)
YS(50)=YS(49)
POINTS FOR HORIZONTAL TAIL
XS(5l)=-HO(20)/2.
YS(5l)=YS(7)+HO(23)*HO(21)/2.
XS(52)=-XS(5l)
YS(52)=YS(S1)
XS(53)=XS(52)
YS(53)=-B—HO(36)-0.225*HI(8)—H0(23)*HO(21)/2.
XS(54)=XS(5l)
YS(S4)=YS(S3)
XS(S5)=XS(2)
YS(55)=YS(5l)
XS(56)=XS(5)
YS(S6)=YS(S1)
XS(S7)=XS(5)2
YS(57)=YS(53)
XS(58)=XS(5S)
YS(58)=YS(S4)
POINTS FOR JET AND PROPELLER ENGINES
XS(59)=-XS(l0)
YS(S9)=YS(lO)
6. Input Variables For HESCAD 92
XS(60)=·XS(9)‘
YS(60)=YS(9)
POINTS FOR FENESTRON TAIL
TVT=H0(28)*H0(32)
XS(61)=-TVT
YS(61)=YS(2l)-0.1*HI(8)+HO(56)/TEST(20)/2.-0.55*TVT
XS(62)=TVT
YS(62)=YS(61)
XS(63)=XS(62)
YS(63)=YS(24)
XS(64)=XS(61)
YS(64)=YS(25)
DATA FOR POINTS XS(65)·-XS(68), YS(6S)——YS(68) FOLLOW IN 'THE PROGRAME
CODE. POINTS FOR FENESTRON SMALL VERTICAL TAIL
XS(69)=-HO(20)/2.-0.2*HO(20)/(1/HO(22)+l)/HO(18)
YS(69)=-B-HO(365·0.225*HI(8)+HO(27)/3.
XS(70)=-H0(20)/2.
YS(70)=YS(69)
XS(7l)=XS(70)
YS(7l)=-B·HO(36)-0.225*HI(8)
XS(72)=XS(70)
YS(72)=YS(7l)-H0(27)/3.
XS(73)=XS(69)
YS(73)=YS(72)
XS(74)=XS(69)
YS(74)=YS(71)
6. Input Variables For HESCAD 93
XS(75)=HO(20)/2.
YS(75)=YS(69)
XS(76)=HO(20)/2.+0.2*HO(20)/(1/HO(22)+1)/H0(l8)
YS(76)=YS(69)
XS(77)=XS(76)
YS(77)=YS(71)
XS(78)=XS(76)
YS(78)=YS(72)
XS(79)=XS(75)
YS(79)=YS(78)
XS(80)=XS(75)
YS(80)=YS(77)
XS(81)=—TVT+0.55*TVT
YS(8l)=YS(2l)-0.1*HI(8)+HO(56)/TEST(20)/2.
XS(82)=TVT-0.55*TVT
YS(82)=YS(81)
Single Rotor Helicopter Top View Point Equations A
See Fig. 49, 50 and Fig. 57 for the location of the points corresponding
to these coordinates.
B IS THE DISTANCE BETWEEN PYLON AND ROTOR.
B=l.I
C IS A PERCENTAGE OF BODY LENGTH, "C*HO(2)" IS THE X COORDINATE OF THE
POINTS TO DETERMINE THE WING°S LOCATION.
C=1/1.2
6. Input Variables For HESCAD 94
C2 IS A PERCENTAGE OF WING SPAN, "C2*HO(10)" IS THE Y COORDINATE OF THE
POINTS TO DETERMINE THE JET ENGINE°S LOCATION.
C2=.25
°PLM° IS A PERCENTAGE OF MAIN PYLON LENGTH TO DETERMINE MAIN PYLON LO-
CATION IN X DIRECTION (0<PLM<1).
PLM=.3
MAJR=O.25*HI(8)/2.
MINR=0.25*HO(6)/2.
POINTS FOR BODY
XT( l)=-HO(S)
YT( l)=0.0
XT( 2)=·HO(5)+0.5*(HO(6)+HI(8))*HI(10)
·YT( 2)=0.5*HO(6)
XT( 3)=XT(2)+HO(2)
YT( 3)=YT(2)
XT( 4)=-HO(5)+HO(3)
YT( 4)=0.75*HO(6)/2.
XT( 5)=-HO(5)+H0(l)
YT( 5)=0.0
XT( 6)=XT(4)
YT( 6)=·YT(‘+)
XT( 7)=XT(3)
YT( 7)=·O.5*HO(6)
XT( 8)=XT(2)
YT( 8)=YT(7)
XT( 9)=0.0
U
6. Input Variables For HESCAD 95
YT( 9)=0.0
POINTS FOR WINGS
l
XT(l0)=C*HO(2)—(HO(l0)-HO(6))/(H0(l3)+1)/HO(8)
YT(10)=YT(2)
XT(ll)=C*HO(2)-(HO(10)-HO(6))/(1/H0(l3)+l)/H0(8)
YT(ll)=HO(10)/2.
XT(12)=C*HO(2)
YT(l2)=YT(l1)
XT(l3)=XT(l2) '
YT(13)=YT(3)
XT(l4)=XT(12)
YT(l4)=YT(7)+1.
XT(1S)=XT(l2)
AYT(l5)=-HO(lO)/2. '
XT(l6)=XT(1l)
YT(l6)=YT(l5) p
XT(17)=XT(l0)
YT(l7)=-YT(l0)
POINTS FOR TAIL ROTORW
XT(18)=XT(S)·HI(4)*HO(56)/2.-0.5*H0(56)
YT(l8)=-.35*H0(6)—0.l0*HO(56)/2.
XT(l9)=XT(5)-HI(4)*H0(56)/2.
YT(l9)=-0.35*HO(6) -
XT(20)=XT(5)-HI(4)*HO(56)/2.+0.5*HO(S6)
YT(20)=YT(18)
POINTS FOR JET AND PROPELLER ENGINES
6. Input Variables For HESCAD 96
XT(21)=(XT(12)+XT(l0))/2.—H0(47)/2.
YT(21)=—C2*HO(l0)—H0(48)/2.l
XT(22)=(XT(12)+XT(10))/2.—H0(47)/2.
· YT(22)=C2*H0(l0)-H0(48)/2.
XT(23)=XT(22)
YT(23)=C2*H0(l0)+H0(48)/2.
XT(24)=(XT(12)+XT(l0))/2.+H0(47)/2.l
YT(24)=YT(23)
XT(25)=XT(24)
YT(25)=YT(22)
XT(26)=XT(22)
YT(26)=·YT(22)V
XT(27)=(XT(12)+XT(l0))/2.-H0(47)/2.-
YT(27)=HI(29)+H0(62)-HO(48)/2.
XT(28)=XT(27)
YT(28)=YT(27)+HO(48)l
XT(29)=(XT(12)+XT(10))/2.+HO(47)/2.
YT(29)=YT(28)
XT(30)=XT(29)
YT(30)=YT(27)
XT(3l)=XT(28)
YT(3l)=-YT(28)
XT(32)=XT(27)
YT(32)=-YT(27)
XT(33)=XT(30)
YT(33)=-YT(30)
6. Input Variables For HESCAD 97
XT(34)=XT(29)
YT(34)=-YT(29)
POINTS FOR
TAILXT(35)=XT(5)-2*HO(27)/(HO(29)+1)/HO(2S)
YT(35)=0.0
XT(86)=XT(5)-2*HO(27)/(1/HO(29)+l)/HO(25)
YT(36)=0.0
XT(37)=-HO(5)+HO(l)-HI(4)*HO(56)/2.
YT(37)=YT(6)*(XT(5)·XT(37))/ (XT(5)·XT(6))
XT(38)=XT(5)-2*HO(20)/(1/HO(22)+1)/HO(18)
YT(38)=0.5*HO(20)
XT(39)=—HO(5)+HO(l)
YT(39)=YT(38)
XT(40)=XT(39)
YT(40)=0.0
XT(4l)=XT(39)
YT(41)=0.0
XT(42)=XT(39)
YT(42)=-0.5*HO(20)
XT(43)=XT(38)
YT(43)=YT(42)
XT(4&)=XT(S)-2*HO(20)/(HO(22)+l)/HO(18)
YT(44)=0.0
XT(45)=XT(A4)
YT(45)=0.0
XT(46)=XT(S)
6. Input Variables For HESCAD 98
YT(46)=MINR
XT(47)=XT(5)
YT(47)=—MINR
XT(48)=XT(5)+MAJR
YT(48)=0.0
XT(49)=XT(47)
YT(49)=-YT(47)
POINTS FOR PRIMARY ENGINE NACELLES
XT(50)=-0.2*HO(41)
YT(50)=·HO(40)*H0(37)/2.-HO(42)
XT(5l)=XT(S0)
YT(51)=-H0(40)*HO(37)/2.
XT(52)=0.8*HO(hl)
YT(52)=YT(5l)n
XT(53)=XT(52)
YT(53)=YT(50)
XT(54)=0.3*HO(4l)
YT(S4)=YT(49)-0.5*HO(42)·
XT(55)=XT(50)
YT(55)=-YT(51)
XT(S6)=XT(50)
YT(56)=-YT(50)
XT(57)=XT(52)
YT(57)=YT(56)
XT(58)=XT(52)
YT(58)=YT(55)
6. Input Variables For HESCAD 99
·XT(59)=XT(54)
YT(S9)=-YT(54)
POINTS FOR MAIN ROTOR PYLON AND VERTICAL TAIL
C XT(60)=XT(5)
C YT(60)=MINR
C XT(61)=XT(5)
C YT(61)=-MINR
C XT(62)=—HO(S)+H0(l)-C·2*HO(27)/(1/HO(29)+1)/HO(25)
C YT(62)=0.5*HO(32)*H0(28)
C XT(63)=XT(62)
C YT(63)=·YT(62)
C XT(64)=XT(35)
C YT(64)=YT(63)
C XT(6S)=XT(64)
C YT(65)=YT(62)
C XT(66)=XT(36)
C YT(66)=YT(62)
C XT(67)=XT(36)l
C YT(67)=YT(63)
C XT(68)=XT(47)
C YT(68)=HO(39)*H0(37)/2.
C XT(69)=XT(47)
C YT(69)=-YT(68)
SF2 IS THE PERCENTAGE OF NOSE LENGTH FROM THE TIP, DEFINING THE START OF
THE WINDSHIELD.
SF2=O.6
6. Input Variables For HESCAD 100
XT(70)=-ABS(XT(l)-XT(2))*(l.-SF2)+XT(2)
YT(70)=0.0
POINTS FOR VERTICAL TAIL
TVT=HO(28)*HO(32)
XT(7l)=-HO(5)+H0(1)-2.5*HO(27)/(HO(29)+1)/HO(25)
YT(71)=0.0
XT(72)=XT(35)+TVT/2.
YT(72)=TVT/2.
XT(73)=XT(72)
YT(73)=-TVT/2.
XT(74)=XT(36)+TVT/2.
YT(74)=TVT/2.
XT(75)=XT(74)·
l
YT(75)=—TVT/2.
POINTS FOR JET ENGINES AND PROPELLER ENGINES
XT(76)=XT(25)O
YT(76)=—YT(2S)
XT(77)=XT(24) p
YT(77)=-YT(24)
XT(78)=XT(27)
YT(78)=HI(29)+HO(62)+HO(62)/2.
XT(79)=XT(27)
YT(79)=HI(29)+HO(62)—HO(62)/2.
XT(80)=XT(31)
YT(80)=-HI(29)-HO(62)+HO(62)/2.
XT(8l)=XT(31)
6. Input Variables For HESCAD 101
POINTS FOR FENESTRON TAIL
XT(82)=-HO(5)+HO(l)-2.5*HO(27)/(HO(29)+1)/HO(25)+TVT
YT(82)=TVT
C XT(83)=XT(71)+TVT
C YT(83)=YT(82)
C XT(84)=XT(83)
C YT(84)=-YT(83)
XT(85)=XT(82)
YT(85)=-YT(82)
A=ABS(-2*HO(27)/(1/H0(29)+l)/H0(2S)+2.5*H0(27)/(H0(29)+1)/HO(25))
B=HO(27)-0.05*HO(27)
C=A*D/BA
XT(86)=XT(71)+C .
YT(86)=0.0
XT(87)=XT(86)+TVT/2.
YT(87)=TVT/2.
XT(88)=XT(87)A
YT(88)=-TVT/2.
POINTS FOR SMALL VERTICAL TAIL
XT(89)=PNEAR1(1)
XT(90)=PNEAR1(1)
XT(9l)=XT(90)
YT(9l)=YT(43)-0.1*(XT(42)-XT(43))
XT(92)=XT(89)-0.6*(XT(89)—XT690))
6. Input Variables For HESCAD·
102
YT(92)=YT(9l)
XT(93)=XT(89)+0.12*(XT(89)—XT(90))
YT(93)=YT(9l)
XT(94)=XT(93) ‘
YT(94)=YT(42)
XT(95)=XT(92)
YT(95)=YT(42)A
XT(96)=XT(9l)
YT(96)=YT(42)
XT(97)=XT(90)F
YT(97)=YT(38)
XT(98)=XT(92)
YT(98)=YT(38)
XT(99)=XT(93)U
YT(99)=YT(38)
XT(100)=XT(99)
YT(100)=YT(38)+0.l*(XT(42)-XT(43))
XT(l01)=XT(98)
YT(10l)=YT(100)
XT(102)=XT(97)
YT(l02)=YT(l00)
Single Rotor Helicopter Primary View Point Equations
See Fig. 51 and Fig. 59 for the location of the points corresponding to
these coordinates.
6. Input Variables For HESCAD 103
B IS THE DISTANCE BETWEEN PYLON AND ROTOR
B=l.
C IS A PERCENTAGE OF BODY LENGTH, "C*H0(2)" IS THE X COORDINATE OF THE
POINTS TO DETERMINE THE WING°S LOCATION.
C1=1/1.2
C2 IS A PERCENTAGE OF BODY HEIGHT, "C2*HI(8)" IS THE Y COORDINATE OF THE
POINTS TO DETERMINE THE WING°S LOCATION.
C2=HI(28)
'PLM‘ IS A PERCENTAGE OF MAIN PYLON LENGTH TO DETERMINE MAIN .PYLON LO-
CATION IN X DIRECTION (0<PLM<1).
PLM=0.3
TROOT=HO(14)*HO(11)1
TTIP=H0(l5)*HO(ll)
MAJRL=0.25*HI(8)/2.
MAJRB=0.75*HI(8)/2.
POINTS FOR MAIN ROTOR AND MAIN ROTOR PYLON
XP( 1)=-H0(S0)/2.
YP( 1)=0.05*HO(50)/2.
XP( 2)=0.0l
YP( 2)=0.0
XP( 3)=HO(50)/2.
YP( 3)=YP(l)
XP( 4)=-PLM*2*H0(36)/(1/HO(38)+1)/H0(33)
YP( 4)=-B
XP( 5)=0.0
YP( 5)=-B
6. Input Variables For HESCAD 104
XP( 6)=(l.-PLM)*2*H0(36)/(1/H0(38)+1)/HO(33)
YP( 6)=-B
XP( 7)=(l.-PLM)*2*HO(36)/(HO(38)+l)/H0(33)
YP( 7)=-B-l.2*HO(36)
XP( 8)=-PLM*2.*H0(36)/(HO(38)+l)/H0(33)
YP( 8)=-B-HO(36)
XP( 9)=-HO(5)+0.S*(HO(6)+HI(8))*HI(10)
POINTS FOR BODY
YP( 9)=YP(8)
XP(l0)=-HO(5)
YP(l0)=·B-0.5*HO(36)
XP(ll)=XP(9)
YP(1l)=-B-HO(36)-HI(8)
XP(l2)=-HO(5)+0.S*(HO(6)+HI(8))*HI(l0)+H0(2)
YP(l2)=YP(l1)
XP(l3)=XP(l2)+HI(l3)*l.1
YP(l3)=YP(1l)-1.
XP(l4)=XP(l2)+HI(l3)
YP(14)=·B—HO(36)-0.8S*HI(8)
XP(lS)=-HO(5)+HO(3)
YP(l5)=-B—H0(36)—0.l*HI(8)-2*MAJRB
XP(l6)=-HO(5)+HO(1)
YP(l6)=·B—HO(36)—0.1*HI(8)-2*MAJRL
XP(17)=-HO(S)+HO(l)
YP(l7)=-B-HO(36)—0.l*HI(8)-MAJRL
XP(l8)=XP(16)
6. Input Variables For HESCAD 105
YP(l8)=A-B-HO(36)—0.l*HI(8)·
XP(19)=XP(15)
YP(l9)=YP(l8)
XP(20)=·HO(5)+0.5*(HO(6)+HI(8))*HI(l0)+HO(2)
YP(20)=YP(8)
POINTS FOR VERTICAL TAIL
XP(2l)=-HO(5)+HO(l)·2*HO(27)/(HO(29)+l)/HO(25)
YP(2l)=YP(18)
x1>(22)=-H0(s)+H0(1)-2=%H0(27)/(1/H0(29)+l>/H0<25)
YP(22)=-B-HO(36)—0.1*HI(8)+HO(27)
XP(23)=-H0(5)+HO(l)
YP(23)=YP(22)
XP(24)=·H0(5)+H0(l)-HI(4)*HO(56)/2.4
YP(24)=-B-H0(36)-0.l*HI(8)+HO(30)
POINTS FOR WINGSV
n
XP(27)=C1*H0(2)—(H0(l0)-HO(6))/(HO(13)+l)/HO(8)+TROOT/2.
YP(27)=YP(ll)+C2*HI(8)
XP(28$=Cl*HO(2)~(HO(10)·HO(6))/(1/HO(l3)+1)/HO(8)+TTIP/2.
YP(28)=YP(27)
XP(29)=C1*HO(2)
YP(29)=YP(27)
XP(30)=XP(27)-TROOT/2.
YP(30)=YP(27)+TROOT/2.
XP(31)=XP(27)
YP(31)=YP(27)+TROOT
XP(32)=XP(28)-TTIP/2.
6. Input Variables For HESCAD 106
YP(32)=YP(27)+TTIP/2.
XP(33)=XP(28)
YP(33)=YP(28)+TTIP
POINTS FOR JET ENGINE AND PROPELLER ENGINES
XP(34)=(XP(30)+XP(29))/2.-HO(47)/2.
YP(34)=YP(27)—HO(48)/2.+H0(62)/2.
XP(3S)=(XP(30)+XP(29))/2.-HO(47)/2.
YP(35)=YP(27)
XP(36)=XP(35)·HO(&8)/2.
YP(36)=YP(35)·HO(48)/2.
XP(37)=XP(34)
YP(37)=YP(36)—H0(48)/2._
XP(38)=XP(34)
YP(38)=YP(36)·H0(62)/2.·
XP(39)=(XP(30)+XP(29))/2.+HO(47)/2.
YP(39)=YP(37)
XP(40)=XP(39)
YP(40)=YP(28)
XP(4l)=XP(40)
YP(4l)=YP(40)
XP(42)=XP(35)
YP(42)=YP(3S)
XP(43)=XP(37)
YP(43)=YP(37)
XP(44)=XP(39)
YP(44)=YP(39)
6. Input Variables For HESCAD 107
PASS XINT1, XINT2 FROM TOP VIEW TO DETERMINE THE LOCATION OF HORIZONTAL
TAIL IN PRIMARY VIEW, T IS THE THICKNESS OF THE HORIZONTAL TAIL.
T=HO(23)*HO(21)
XP(45)=XINTl
YP(45)=YP(l7)
XP(46)=XP(45)+T/2.
YP(46)=YP(&5)+T/2.
XP(47)=XP(&6)
YP(47)=YP(45)·T/2.
XP(50)=XINT2
YP(50)=YP(47)
POINTS FOR PRIMARY ENGINE NACELLES
_ XP(51)=·O.2*HO(4l)
YP(51)=YP(8)
XP(52)=XP(5l)
YP(52)=-B-HO(36)+HO(42)
XP(53)=O.8*HO(4l)
l YP(53)=YP(52)
XP(54)=XP(53)
YP(54)=YP(5l)
POINTS FOR FENESTRON TAIL
XP(S5)=0.5*(XP(l8)-XP(2l))/2.+XP(2l)
YP(55)=(YP(l6)+YP(18))/2.
XP(S6)=XP(l8)·O.4*(XP(23)-XP(22))
YP(56)=YP(l8)+HO(56)/TEST(20)/2.
XP(57)=XP(2l)
6. Input Vaxiables For HESCAD 108
YP(57)=YP(56)
XP(S8)=XP(22)
YP(58)=YP(22)-0.05*HO(27)
XP(59)=XP(22)+0.07*H0(27)
YP(59)=YP(22)
XP(60)=-H0(5)+HO(1)-2.5*HO(27)/(H0(29)+1)/HO(25)
YP(60)=YP(l8)
XP(6l)=XP(5S)
YP(6l)=(YP(l6)+YP(l8))/2.-0.6*H0(56)/TEST(20)
XP(62)=XP(55)-0.45*HO(56)/TEST(20)
YP(62)=YP(S5)-0.45*H0(56)/TEST(20)
XP(63)=XP(S0)
YP(63)=—B—HO(36)·O.45*HI(8)
XP(64)=XP(l8j -
YP(6&)=YP(5S)
POINTS FOR FENESTRON SMALL VERTICAL TAIL
XP(65)=XP(4S)
YP(65)=YP(4S)
XP(66)=XP(50)-0.6*(XP(50)-XP(4S))
YP(66)=YP(45)+HO(27)/3.
XP(67)=XP(50)+0.l2*(XP(50)-XP(45))
YP(67)=YP(66)
XP(68)=XP(50)-0.12*(XP(50)-XP(45)) ‘
YP(68)=YP(45)-HO(27)/3.
XP(69)=XP(50)-0.8*(XP(50)·XP(4S))
YP(69)=YP(68)
6; Input Variables For HESCAD 109
POINTS FOR SINGLE ROTOR HELICOPTER HORIZONTAL TAIL, PASS XINT3, FROM TOP
VIEW TO DETERMINE THE LOCATION OF HORIZONTAL TAIL IN PRIMARY VIEW.
XP(70)=XINT3
YP(70)=YP(45)
XP(7l)=XP(70)+T/2.
YP(7l)=YP(45)+T/2.
XP(72)=XP(7l)
YP(72)=YP(45)—T/2.
XP(73)=XP(l8)I
YP(73)=YP(45)-T/2.
XP(74)=XP(l8)-2*HO(20)/(1/H0(22)+1)/HO(l8)+T/2.
YP(74)=YP(45)-T/2.V
XP(7S)=XP(74)-T/2.~
AYP(75)=YP(45)
XP(76)=XP(74)
YP(76)=YP(&5)+T/2.
6.3.2. TANDEM ROTOR HELICOPTER POINT EQUATIONS
Tandem Rotor Helicopter Side View Point Equations
See Fig. 52 for the location of the points corresponding to these coor-
dinates.
B IS THE DISTANCE BETWEEN PYLON AND ROTOR
B=l.
C IS TO DETERMINE THE CABIN ARC IN THE SIDE VIEW
6. Input Variables For HESCAD 110
C=.2S
Cl IS A PERCENTAGE TO DETERMINE THE JET ENGINE NACELLE'S CENTER IN X CO-
ORDINATE.
C2=.25
C4 IS A PERCENTAGE TO DETERMINE THE JET ENGINE AND PROPELLER ENGINE
NACELLE'S CENTER IN Y COORDINATE.
C4=HI(28)
PI=3.l&l5926
TTIF=H0(l5)*HO(l1)
TROOT=HO(l4)*HO(ll)A
POINTS FOR BODY
XS( l)=-HO(6)/2.
YS( l)=-B-H0(80)-HI(8)+C*HI(8)
XS( 2)=XS(l)
YS( 2)=-B—HO(80)-C*HI(8)
XS( 3)=0.0
YS( 3)=-B-HO(80)
XS( 4)=-XS(2)
YS( 4)=YS(2)
XS( 5)=-XS(l)
YS( 5)=YS(1)
XS( 6)=0.0
YS( 6)=-B-HO(80)-HI(8)
XS( 7)=-HO(75)*HO(73)/2.
YS( 7)=-B-H0(80)
XS( 8)=-XS(7)
6. Input Variables For HESCAD lll
YS( 8)=YS(7)
POINTS FOR JET ENGINE AND PROPELLER ENGINES
XS( 9)=-C2*HO(l0)
YS( 9)=-B-HO(80)-C4*HI(8)-HO(48)/2.
XS(l0)=HI(29)+HO(62)
YS(10)=-B-HO(80)-C4*HI(8)-HO(48)/2.
POINTS FOR WINGSA
XS(11)=-HO(l0)/2.+TTIP/2.
YS(1l)=-B-HO(80)-C4*HI(8)
XS(12)=—HO(lO)/2.
YS(l2)=YS(1l)+TTIP/2.
XS(l3)=XS(ll)
YS(13)=YS(1l)+TTIP
XS(14)=XS(1)A
YS(l4)=-B·HO(80)-C4*HI(8)+TROOT
XS(15)=XS(14)
YS(15)=-B-HO(80)-C4*HI(8)
XS(16)=-XS(14) ·
YS(16)=YS(14)
XS(l7)=-XS(l5)
YS(17)=YS(l5)
XS(18)=-XS(11)
YS(18)=YS(11)
XS(19)=-XS(12)
YS(19)=YS(12)
XS(20)=-XS(l3)
6. Input Variables For HESCAD 112
YS(20)=YS(13)
POINTS FOR FORWARD ROTOR PYLON AND ROTOR
XS(21)=-HO(83)*HO(81)/2.
YS(2l)=YS(3)
XS(22)=-XS(2l)
YS(22)=YS(3)
XS(23)=-H0(84)*HO(8l)/2.
YS(23)=-B
XS(24)=-XS(23)
YS(24)=-B
XS(25)=0.0
YS(25)=—B
XS(26)=—HO(S0)/2.
YS(26)=0.00S*HO(50)
IXS(27)=0.0
YS(27)=0.0
XS(28)=-XS(26)
YS(28)=YS(26)
POINTS FOR AFT PYLON AND ROTOR
XS(29)=0.0
YS(29)=YS(3)+H0(72)+B
XS(30)=XS(28)
YS(30)=YS(29)+0.005*HO(50)
XS(3l)=XS(26)
YS(31)=YS(29)+0.005*HO(S0)
XS(32)=—H0(76)*H0(73)/2.
6. Input Variables For HESCAD 113
YS(32)=YS(3)+H0(72)
XS(33)=0.0
YS(33)=YS(32)
XS(34)=-XS(32)
YS(34)=YS(32)
C XS(3S)=-HI(75)
C YS(3S)=YS(9)
POINTS FOR PRIMARY ENGINE NACELLES
XS(36)=-HO(75)*H0(73)/2.-HO(42)/2.
YS(36)=YS(21)+H0(42)/2.
XS(37)=-XS(36)
YS(37)=YS(36)
DATA FOR POINTS XT(38), YT(38) FOLLOW IN THE PROGRAM CODE, POINTS FOR
CABIN.
XS(39)=XS(2)+C*HI(8)
YS(39)=YS(21)A
XS(40)=-XS(39)
YS(40)=YS(21) _
XS(41)=XS(1)+C*HI(8)
YS(4l)=YS(6)
__ XS(42)=-XS(41)
YS(42)=YS(41)
POINTS FOR JET ENGINE AND PROPELLERS
XS(43)=-XS(9)
YS(43)=YS(9)
XS(44)=-XS(10)
6. Input Variables For HESCAD 114
YS(44)=YS(10)
POINTS FOR AFT PYLON
XS(45)=·HO(75)*HO(73)/2.
YS(45)=YS(3)
XS(46)=—XS(45)
YS(46)=YS(3)
SFl DETERMINES THE PERCENTAGE OF NOSE HEIGHT (MFASURED FROM BELLY) WHICH
MARKS THE START OF THE WINDSHIELD.
SF1=0.4
SF2 DETERMINES THE PERCENTAGE OF THE NOSE LENGTH (MEASURED FROM THE TIP)
WHICH MARKS THE START OF THE WINDSHIELD.
SF2=0.6
B=SFl*ABS(YS(3)-YS(6))I
D=HI(l0)*SF2
E=SQRT(B*B*D/HI(10)) -
XS(38)=0.0
YS(38)=YS(6)+ABS(YS(3)—YS(6))*SFl+E
Tandem Rotor Helicopter Top View Point Equations
See Fig. 53 and Fig. 54 for the location of the points corresponding to
these coordinates.
C IS A PERCENTAGE OF BODY LENGTH, "C*HO(2)" SHOWS X COORDINATE OF THE
WING.
C =0.5
6. Input Variables For HESCADU
115
C2 IS A PERCENTAGE OF WING SPAN, "C2*HO(l0)" FOR BODY'S CENTER TO AUXIL-
IARY ENGINE NACELLE°S CENTER.
C2=.25
MAJR=0.2S*HI(8)/2. ·
MINR=0.25*HO(6)/2.
'PLM° IS A PERCENTAGE OF MAIN PYLON LENGTH TO DETERMINE MAIN PYLON LO-
CATION IN X DIRECTION (0<PLM<1).
PLM=0.3
”POINTS FOR BODY
XT( 1)=-HO(66)
YT( 1)=0.0
XT( 2)=-HO(5)+0.5*(HO(6)+HI(8))*HI(10)
YT( 2)=O.5*HO(6) °
XT( 3)=XT(2)+HO(2)U
YT( 3)=YT(2)
XT( 4)=XT(1)+HO(l)
YT( 4)=MINR~
XT( 5)=-HO(66)+HO(1)+MAJR
YT( 5)=0.0
XT( 6)=XT(‘+)
YT( 6)=·YT(‘•)
XT( 7)=XT(3)
· YT( 7)=-YT(3)
XT( 8)=XT(2)l
YT( 8)=·YT(2)
POINTS FOR FORWARD PYLON
6. Input Variables For HESCAD 116
C XT( 9)=0.0
C YT( 9)=HO(83)*HO(81)/2.
C XT(10)=(l.·PLM)*2.*HO(80)/(HO(82)+l)/HO(77)
C YT(10)=0.0 _
C XT(l1)=0.0
C YT(l1)=—YT(9)
C XT(12)=-PLM*2.*HO(80)/(HO(82)+l)/HO(77)
C YT(12)=0.0
C XT(l3)=(l.-PLM)*2.*HO(80)/(1/HO(82)+l)/HO(77)4
C YT(l3)=0.0
C XT(l4)=0.0I
C YT(14)=-H0(84)*HO(8l)/2.
Cl
XT(l5)=0.0
C YT(1S)=-YT(l4)
C XT(16)=-PLM*2*HO(80)/(1/HO(82)+1)/HO(771
C YT(16)=0.0
POINTS FOR AFT PYLON
XT(17)=XT(5)—2*HO(72)/(H0(74)+l)/HO(70)
YT(l7)=0.0I
XT(18)=XT(l7)+C1
YT(18)=HO(75)*HO(73)/2.
XT(l9)=XP(17)+HO(41)
YT(19)=HO(75)*HO(73)/2.
XT(20)=XT(5)
YT(20)=0.0
XT(21)=XT(19)
6. Input Variables For HESCAD 117
YT(21)=-YT(19)
XT(22)=XT(18)
Y'I’(22)=-YT(l8)
XT(23)=XT(S)-2*H0(72)/(1/HO(74)+1)/H0(70)
YT(23)=0.0
XT(24)=XT(23)+0.5
YT(24)=O.S
YT(27)=HO(76)*HO(73)/2.
XT(2S)=XT(24)
YT(25)=-YT(24)
XT(26)=-HO(66)+HO(1)·HO(67)
YT(26)=0.0
XT(27)=XT(26)
YT(27)=HO(76)*HO(73)/2.
XT(28)=XT(27)
YT(28)=—YT(27)
POINTS FOR PRIMARY ENGINE NACELLES
XT(29)=XT(21)
YT(29)=YT(21)·HO(42)
XT(30)=XT(5)-2*HO(72)/(HO(74)+l)/HO(70)
YT(30)=YT(29)
XT(31)=XT(30)V
YT(31)=YT(21)
XT(32)=XT(30)
YT(32)=—YT(3l)
XT(33)=X'I'(30)
6. Input Variables For HESCAD 118
YT(33)=-YT(29)l
XT(34)=XT(l9)
YT(34)=YT(33)
POINTS FOR WINGS
XT(35)=C*HO(2)
YT(35)=HO(10)/2.
XT(36)=C*HO(2)
YT(36)=YT(2)
XT(37)=C*HO(2)
YT(37)=YT(8)
XT(38)=C*HO(2)
YT(38)=-YT(35)
XT(39)=C*HO(2)-(HO(lO)-HO(6))/(1/HO(13)+1)/HO(8)
YT(69)=YT(6é)
XT(40)=C*HO(2)·(HO(l0)-HO(6))/(HO(13)+1)/EO(8)l
YT(&0)=YT(8)
XT(41)=XT(40)
YT(41)=YT(36)·
XT(42)=XT(39)1
YT(42)=YT(3S)
POINTS FOR JET ENGINES AND PROPELLER ENGINES
XT(43)=(XT(41)+XT(36))/2.-HO(47)/2.
YT(43)=HI(29)+HO(62)+HO(48)/2
XT(44)=(XT(41)+XT(36))/2.+HO(47)/2.
YT(44)=YT(43)
XT(45)=XT(44)
6. Input Variables For HESCAD 119
YT(45)=YT(44)-HO(48)
XT(46)=XT(43)
YT(46)=YT(4S)
XT(47)=(XT(4l)+XT(36))/2.·HO(47)/2.
YT(47)=C2*HO(l0)+HO(48)/2.
XT(48)=(XT(41)+XT(36))/2.+HO(47)/2.
YT(48)=C2*H0(10)+HO(48)/2.
XT(49)=XT(48)
YT(49)=C2*HO(l0)-HO(48)/2.
XT(50)=XT(47)
YT(50)=YT(49)
XT(5l)=XT(&3)A
YT(5l)=HI(29)+HO(62)+HO(62)/2.
XT(S2)=XT(43)
_
YT(52)=HI(29)+HO(62)-HO(62)/2.
XT(53)=XT(43)
YT(53)=-(HI(29)+HO(62)+HO(62)/2.)
XT(S4)=XT(43)
YT(54)=-HI(29)-HO(62)+HO(62)/2.
C XT(5S)=0.0
C YT(S5)=0.0
SF2 IS THE PERCENTAGE OF NOSE LENGTH FROM THE TIP DEFINING THE START OF
THE WINDSHIELD.
SF2=0.6
XT(56)=-ABS(XT(1)-XT(2))*(l.-SF2)+XT(2)
YT(56)=0.0
6. Input Variables For HESCAD 120
XT(S7)=XT(50)
YT(S7)=—YT(S0)
XT(S8)=XT(49)
YT(58)=·YT(49)
XT(59)=XT(58)
YT(S9)=-YT(48)
XT(60)=XT(47)
YT(60)=·YT(47)
XT(61)=XT(46)
YT(6l)=·YT(46)
XT(62)=XT(45)
YT(62)=-YT(45)·
XT(63)=XTQ44)
YT(63)=—YT(44)
XT(64)=XT(43)U
YT(64)=-YT(43)
Tandem Rotor Helicopter Primary View Point Equations
See Fig. 55 for the location of the points corresponding to these coor-
dinates.
B IS THE DISTANCE BETWEEN PYLON AND ROTOR
B=l.
C IS A PERCENTAGE OF BODY LENGTH, "C*H0(2)" IS THE X COORDINATE OF THE
POINTS TO DETERMINE THE WING°S LOCATION.
C=0.5
6. Input Variables For HESCAD 121
C2 IS A PERCENTAGE OF BODY HEIGHT, "C2*HI(8)" IS THE Y COORDINATE OF THE
POINTS TO DETERMINE THE WING°S LOCATION.
C2=HI(28)
'PLM° IS A PERCENTAGE OF MAIN PYLON LENGTH TO DETERMINE MAIN PYLON LO-
CATION IN X DIRECTION (0<PLM<l).
PLM=0.3
TROOT=HO(l4)*HO(ll)
TTIP=HO(l5)*HO(11)
MAJR=0.25*HI(8)/2.{
POINTS FOR MAIN PYLON AND ROTOR
XP( 1)=-O.5*HO(S0)
YP( l)=0.005*HO(S0)
XP( 2)=0.0
YP(
XP( 3)=-XP(l)
YP( 3)=YP(1)
XP( 4)=-PLM*2*HO(80)/(1/HO(82)+l)/HO(77)
YP( 4)=-B
XP( 5)=0.0 w
YP( 5)=-B
XP( 6)=(1.-PLM)*2.*HO(80)/(1/HO(82)+l)/HO(77)
YP( 6)=-B ·
XP( 7)=(1.—PLM)*2.*HO(80)/(HO(82)+1)/HO(77) ·
YP( 7)=-B-HO(80)
XP( 8)=-PLM*2.*HO(80)/(HO(82)+1)/HO(77)
6. Input Variébles For HESCAD 122
YP( 8)=YP(7)
POINTS FOR BODY
XP( 9)=·HO(66)+0.5*(HO(6)+HI(8))*HI(10)
YP( 9)=YP(8)
XP(l0)=-HO(66)
YP(l0)=—B-0.S*(HO(6)+HI(8))
XP(ll)=XP(9)
YP(11)=—B—HO(80)-HI(8)
XP(l2)=XP(ll)+H0(2)l
YP(l2)=YP(11)
XP(13)=XP(l2)+HI(l3)
YP(13)=YP(l2)
OA
‘XP(l4)=XP(l0)+HO(l)
e
YF(l4)=—B-HO(80)-2.*MAJR
XP(1S)=XP(l4)+MAJR
YP(1S)=-B-HO(80)-MAJR
XP(l6)=XP(l4)I
YP(l6)=YP(7)
POINTS FOR AFT PYLON AND ROTOR
XP(l7)=XP(15)-2*HO(72)/(HO(74)+l)/HO(70)+HO(A1)
YP(l7)=YP(7)
XP(18)=XP(l6)-2*HO(72)/(HO(74)+l)/HO(70)
YP(l8)=YP(7)
XP(19)=XP(l6)-2*HO(72)/(1/HO(74)+l)/HO(70)
YP(19)=YP(7)+HO(72)
XP(20)=XP(l6)
6. Input Variables For HESCAD 123
YP(20)=YP(19)
XP(2l)=XP(l5)·HO(67)-HO(50)/2.
YP(21)=YP(19)+0.005*HO(50)+B
_ XP(22)=XP(l6)-HO(67)
YP(22)=YP(19)+B
XP(23)=XP(2l)+HO(50)
YP(23)=YP(2l)
l
XP(24)=XP(22)
YP(24)=YP(19)
POINTS FOR PRIMARY ENGINESl
XP(25)=XP(18)
YP(25)=YP(7)+HO(42)
XP(26)=XP(17)
YP(26)=YP(25)J
POINTS FOR WINGS, PROPELLER ENGINES AND JET ENGINES
XP(27)=C*HO(2)—(HO(10)-HO(6))/(H0(l3)+l)/H0(8)+TROOT/2.
YP(27)=YP(l1)+C2*HI(8)
XP(28)=C*HO(2)·(HO(10)~H0(6))/(l/HO(13)+1)/HO(8)+TTIP/2.l
YP(28)=YP(27)
XP(29)=C*HO(2)
YP(29)=YP(27)
XP(30)=XP(27)-TROOT/2.
YP(30)=YP(27)+TROOT/2.
XP(31)=XP(27)
YP(3l)=YP(27)+TROOT
XP(32)=XP(28)-TTIP/2.
6. Input Variables For HESCAD 124
YP(32)=YP(27)+TTIP/2.
XP(33)=XP(28)
YP(33)=YP(28)+TTIP
XP(34)=(XP(30)+XP(29))/2.-H0(47)/2.
YP(34)=YP(27)-HO(48)/2.+HO(62)/2.
XP(35)=(XP(30)+XP(29))/2.-H0(47)/2.
YP(35)=YP(27)
XP(36)=XP(35)-HO(48)/2.
YP(36)=YP(35)-HO(48)/2.
XP(37)=XP(34)
YP(37)=YP(36)-HO(48)/2.
XP(38)=XP(34)
YP(38)=YP(36)-HO(62)/2.
x1>(69)=(xP(30)+xP(29))/2.+H0(47)/2-
YP(39)=YP(37)
XP(40)=XP(39)
YP(40)=YP(28)
XP(4l)=XP(&O)
YP(4l)=YP(40)
XP(42)=XP(35)
YP(42)=YP(35)
XP(43)=XP(37)
YP(&3)=YP(37)
XP(44)=XP(39)
YP(&4)=YP(39)
6. Input Variables For HESCAD 125
TANDEM ROTOR HELICOPTER
I. MAIN ROTOR PYLCN 2. AFT ROTOR PYLON
c‘“““’I TAP I'“"‘
c
II”° TFP °'I hP2
II I. «= ..| L. C .|RFP RAP
SINGLE ROTOR HELIGGPTER
_ · I. MAIN ROTOR PYLCN 2. AFT ROTOR PYLON
cTvr I"”‘”
c
I I' TPP °'| bVT
I L. ¤ .I L.¤ .IRFP Rvr
Figure &7. Typical Single and Tandem Rotor Helicopter rotor Pylonand Vertical Tail Geometric Characteristics
6. Input Variables For HESCAD 126
s216¤2ss62621s2s6s4s1so22:624424666 2258 42 56I4 Ä 572* II 2*51 . 5«-6754 52I3 531, W" W3 =·¤
I9
II 59_ 2 I5 1 sv 38 6 I7 I6 60 IO l8
Figure 48. Single Rotor Helicopter Side View Points
6. Input Variables For HESCAD 127
7828 2927 II I2 307° un!23 ~22 1, 24 ‘° ‘°·¤ 1:/ 25
2 I3 g\Ü/' 45. I 40.46
*ug 11- 48
/31 44-| 4l ,47§ I4 6 Ia 20
I7 in 7626
_
77 43 422* il-l8°
-32 I6 I5 333I 348I
56 57
66
_
.„ 7
72 746035 5 46
77 77 77°°
5250 53
I
E2 3
7 6 ” ·@ ‘
I. VERTICAL TAIL
2. MAIN ROTCR PYLON AND PRIMARY ENGINE NACELLE
3. MAIN ROTOR BLADE
Figure 49. Single Rotor Helicopter Top View Points (Old Version)
6. Input Variables For HESCAD 1287
7828 2927 II I2 so”
mn!22; I
-
2* 38 39
2 ·<> $:7 25Ä
.21 40.46I un) 6-- 484l ,47
2
_;
I4 6 ua 20I7 äh 7626
_
77¤· en-;‘° ‘“
89
-32 I6 ns 33‘ 3l 348I
56 57
3
_
7
50 53
I
3
7 6 5 @ 4
2 I. VERTICAL TAIL
_ 2. MAIN ROTOR PYLON AND PRIMARY ENGINE NACELLE
3. MAIN ROTOR BLADE
Figure 50. Single Rotor Helicopter Top View Points (New Version)
6. Input Variables For HESCAD 129
22 ,7
23
I „ 3 1 Y2 24
4 69 A1; I9 2I I8
-"1 —*9 1- '°I5
I I I2
SI 33 75 7I 76
3470
36.42 3 li 29 73„ 40.41 ®37 43
‘ 72 74' 39.44
38 G)
14 5 52 53‘ 7 Ä3
®2 5l ® 54
1. WING. PRGPELLER OR JET ENGINE NACELLES
2. AFT RUTUR BLAUE
3. 1-1oR1z0NTAL TAIL
4. PRIMARY ENGINE NAUELLE
Figure Sl. Single Rotor Helicopter Primary View Points
6. Input Variables For HESCAD 130
45 36 23 32 33 29 34 27 25 24 37 46
39 403l 302 4
26 w1|éY7 28I4 g I6
.;-1; 1;.¤¤ V9 ° ° ¤<>I2 I9
II I8
46 9 I5 1 41 42 5 I7 43 I0
Figure S2. Tandem Rotor Helicopter Side View Points _
6. Input Variables For HESCAD 131
4252‘3 Y46
“
BI *5*7 lt
‘°q 49T? J! =·{12 =
·56 s 7
40 VI! 3757 AK! 58.•
Q- QQ64 626l 6364 3Q
.
3 34
32· ]15 I9‘“
" °° '° '° " 2*I4 . 2l
3III
:0 29I
1 2.7
5 ‘
1. MAIN ROTE}? PYLON
2. AFT ROTOR PYLCN
3. ROTOR BLADE
Figure 53. Tandem Rotor Helicopter Top View Points (Old Version)
6. Input Variables For HESCAD 132
4252‘3
ä“
ll
5l *5*7 li ‘°.• gr-| 494n gq 5*
= A2 6 •·
· ¤bA3¤· ¤VT 65* ° X3; ’60 311 6757 AK! 58.„
Q- 5956 62GI 636* 36
3 34=
-
6 32 ns ‘
5 2I‘ 5
7 "
-
30 as
‘\E 32 3
7 *5 4
n. mm norm n=>vn.o~2. Arr norm nvtou6. noron sunos
Figure S4. Tandem Rotor Helicopter Top View Points (New Version)
6. Input Variables For HESCAD 133
HJN
va4-*C':‘6‘
In-
Q-•gn _‘f_*
3 3ä :E
E-
{ 3 ¤¤8 2 ¤ 6 E„ * ”
5Hgg ¤>4-J¤«O
N O— ~•-•·
„—•Q)I
F) H..
"’3N ‘ g
sb EQQ
N F5 Y ··> ¤—M .‘°
vs3 '° vsQ * GJ„„ — Qi '¢ 5
2
6. Input Variables For HESCAD 134
69 70 58 55 56 57 75 76
5l 52
74 77
7l 53
73 72 64 6l 8I 65 66 82 62 63 79 78
(NOTE TI-E POINTS BOT SHOWN IN THIS PICTURE HAVE
BEEN SI-OWN IN SINGLE ROTOR HELICOPTER SIDE VIEW)
Figure 56. Fenestron Tail Helicopter Side View Points
6. Input Variables For HESCAD 135
_, |*2*.:* '=;
\
45 97 IO2 38 IOI 98 IOO 39 99 40 82
174 ·
· 36
5—*é,—·\§•>
75
— 86
88
44 96 9l 43 92 95 93 42 94 4I 85
(N3TE¤ ‘n·£ Poxms mv saw zu THIS PICTLRE HAVE BEEN
saw IN SINELE ROTG? I-ELICCPTER Top VIEW)
Figure 57. Fenestron Tail Helicopter Top View Points
6. Input Variables For HESCAD 136
19a462026719 66 676036766 59
23
‘ I °°l ¤·._ .| e
I- 66
« 6l
‘ 62
IO II I2 I5 65 69 68 63
3l 33
36.42 3° 29
37 *3 5l 54' 39.44 ®38 Q)
1. ums IT MD 1¤R01>E1.L1·:R ausm: m1cE1.1.£
2. PRIMARY Emma NACELLE
Figure 58. Fenestron Tail Helicopter Primary View Points
6. Input Variables For HESCAD 137
7. INSTALLATION AND OPERATION
HESCAD was written under VM/CMS (Release 3) using VSFORTRAN (Release
4.0), using CADAM and CADAM GIM (Releases 19.1, 19.2, and 20.0). In-
stallation instructions and EXEC's are for the VM environment. Similar
PROC°s are supplied with CADAM for the MVS environment. For reference
see:
CADAM Geometry Interface Installation Guide
SH20-6227-0
IBM Corporation
An overview of the installation and operation procedure is as fol-
lows:
1. Install or modify HESCOMP to use the modified routines MAIN,
PRINT1, and LOADER and the new routine COLLEC. These modifica-
tions are described in Appendix B.
2. Edit HESCAD and insert the CADAM group name and sub-group (USER)
name in the DATA statement, "DATA 6R0¤1>/'TBM °/,USERID/'COPT° , 'ER
°/". Compile the program HESCAD. HESCAD calls subroutines from
the CADCD portion of CADAM°s Geometry Interface Module.
7. Installation and Operation 138
3. HESCAD must replace a main program called CADCDMN in the CADAM
library (CADAMLM). Link HESCAD with the CADAM library, replacing
CADCDMN. Note that the OS Linkage Editor is used under VM (i.e.
LKED not LINK).
4. Execute HESCOMP with the appropriate input data. The files on
units S and 6 are the HESCOMP input and output files respectively.
S. HESCOMP will also write a sequential file on unit NDISK (currently
set at 10), in addition to usual output, which contains all nec-
essary geometric and test variables for HESCAD.
6. Execute HESCAD from the CADAM library using the model EXEC°s or
PROC's supplied by CADAM, Inc. HESCAD requires the file produced
by HESCOMP as input on unit NDISK. HESCAD writes an output message
file and geometrical data directly into the CADAM data base with
the group and sub-group (USER) specified in a data statement in
HESCAD. Since the group and user change infrequently and the
model ID changes frequently, the model ID is specified in HESCOMP
input data. The model ID and any geometrical data may be altered
by editing the file written on unit 10. The group and sub-group
must have been previously established along with password file
as specified by CADAM. The file on unit 6 reports on geometry
calls, model size and diagnostic messages from CADCD routines and
HESCAD. The file on unit 10 is the geometry data file produced
by HESCOMP. The file on unit 11 is an echo of this data (HI, HO,
7. Installation and Operation 139
TEST) for verification purposes. Linking VSFORTRAN object mod-
ules with the FORTRAN IV CADAM library may cause the file to read
the problem if LANGLVL=77 was inadvertently specified instead of
LANGLVL=66.
•The first EXEC, CADCDLNK is invoked to link HESCAD in to the
CADAM library to replace MAIN CADCDM.
•The second EXEC, CADCD is invoked to execute HESCAD and write
the model into the CADAM Drawfile. OS versions of these EXEC°s
are provided with CADAM.
7. Log on to CADAM and specify the group and user as coded in HESCAD
along with the appropriate passwords. The output model ID is
taken from the HESCOMP title record, dropping the first six
characters as required by HESCOMP. The orthographic views and
wire-frame are produced in the same units as HESCOMP input. A
note is written with each model that consists of the HESCOMP title
record. Since the data is usually in feet, the note will be
relatively small. The section, "Mass Property Analysis", will
give details on computation of mass properties.
Note that at present, to access a view in. a model produced with
CADCD, even PV, it is necessary to first select that model in AUXVIEW.
This problem and an associated. problem concerning projection between
7. Installation and Operation 140
views in models produced by CADCD is currently being corrected by CADAM,
Inc. as a result of this project.
7. Installation and Operation 141
8. PROJECTWON PROCEDURES
As mentioned above the geometry environment of the three 2-D heli-
copter point equations is different from CADAM. In order to project ge-
ometry segments between 2-D and 3-D wire-frame mode it is necessary to
change these 2-D helicopter coordinate systems into CADAM coordinate
system. In this section detailed procedures are presented.
After selecting the HESCAD model from the CALL list, the procedure
is as follows:
1. Immediately change the name of the model and refile if the original
version is to be saved.
2. Enter AUXVIEW and select (using light pen or cursor) an element in
the primary view.
3. Create a horizontal line and a vertical line passing through PV and
the origins of the other two views (center of rotor).
Since all the origins are initially coincident, select the side
view , create the point at the center of the rotor and at the origin
and measure the separation distance for placement of the equivalent
origin point in PV using the PTS-SPACE function. Do the same for the
top view.
8. Projection Procedures 142
4. Use POINTS-SPACE to place a point in PV on these lines at the TV and
SV origins or just indicate points over the origins.
S. Select the top view in AUXVIEW. Enter GROUP and select /TRAP OUT/.
All of TV is now prepared to be copied into a detail page.
6. Enter DETAIL, select /ERS ORIG/ and push Y/N. TV will be copied into
detail 1. Repeat the procedure for SV and PV, but be sure to modify
the trapped group such that the PV line and origin points are not
copied to the detail.
7. A wire-frame model (except in the fenestron tail case), two origin
points and two lines should now be presented on the screen. Enter
PTS and select the two lines to create the PV origin point.
8. Enter AUXVIEW and create two new views, TV and SV, using these points
and lines. The wire-frame and three empty orthographic views are
created.
9. Decide which point will be used for the computation of mass proper-
ties. Enter each detail, create this point and select it as the pivot
point for the detail. Copy each detail back to the new views. If
the computation point is not easily defined in the detail geometry,
copy the details back using a convenient point such as the nose. Then
use GROUP-TRAP and GROUP-TRANSLATE to move the helicopter to the new
point which has been defined relative to the nose.
8. Projection Procedures 143
Be sure to erase the details to allow extra model space. The views
now recognize each other and projection can be accomplished between any
views.
After finishing, you have a new file with coordinates in the CADAM
coordinate system. The model is ready to be projected into other views.
The projection procedures are as follows:
1. Enter FILE and select /UNITS/ (using light pen or cursor), select 3-D
mode, then select /RETURN/.
2. Enter MISC and select /GEN3D/ then select /NEW PLANE/ to define a
project plane in 2-D helicopter model.
l3. Select a proper segment corresponding to the defined plane in another
2-D helicopter model. At that moment the selected segment is projected
into the wire-frame.
8. Projection Procedures 144
9. MASS PROPERTY ANALYSIS
After the helicopter configuration has been created, the interior.
equipment can be drawn in the primary view, top view and side view using
the light pen. And it can be projected into the wire-frame or an isometric
view. Then the mass property analysis of this equipment can be carried
out. If a plot is desired with the wire-frame moved into a different
orientation, use GROUP—TRANS instead of 3-D WINDOW, since all WINDOW
transformations are set to the default when the drawing is filed. Note
that GROUP-TRANS causes a permanent change of origin while WINDOW does
not.·
Design in the wire-frame view is simplified by a liberal use of
N0—SHOW which may be used to section the wire-frame to ease design.
To enhance visualization, ruled or bicubic surfaces may be added to
the wire-frame. Three different methods of showing surface
parameterization may be used: isometric curves, dots, or surface vectors.
Figure 17 shows a single rotor helicopter with six components added
to the nose. The two outer components are cylindrical and include a
stand. The central component consists of two parts. Figure S9 and 60
show a table generated by CADAM during the mass property analysis routine.
This table is a permanent part of the model. All moments and products
of inertia and the center of mass are given with respect to the view
origins. The sum is automatically computed. The X Y Z axes are those
of the wire-frame. This table was computed using the nose point of the
helicopter as origin.
9. Mass Property Analysis 145
Properties were computed based on an estimated density for circuit
boxes. For example, 1.5% Fe, 7.5% Al, 2.5% Cu, 1% Pb, 2.5% circuit board
material and the balance open, which gives about 40 pounds per cubic foot.
After this estimated density is available for all components and the
components are designed in the model, the mass property computation may
_ be started with CADAM. When helicopter units are given in feet, the mass
property notes will be small but easily handled. It is important to use
window settings for the primary, top, and side views of added components,
an overall view of these three and an expanded view of the mass property
notes. This greatly simplifies the design and mass property computation
since the helicopters are large compared to interior equipment.
After setting windows, points should be defined for starting points
on each object to be analyzed. It is best to analyze objects individually
rather than accumulating results since an error would require a complete
restart. Properties for individual objects can be summed at the end of
the computation process.
There are two methods to specify cross-sections; boundary element
method and centerline method. The boundary element method is most fre-
quently used method.
Mass property computation is accessed by entering the 2-D function
ANALYSIS and selecting MASS PROP. This allows one to compute mass prop-
erties of most 3-D solid objects. Very complex objects that may be dif-
ficult to define for mass property computation may be broken down into
subparts and accumulated or summed at the completion of individual part
definition or analysis. User familiarity with the CADAM section property
9. Mass Property Analysis 146
and volume—weight procedure will make this procedure easy to follow. The
mass properties are as follows:
• Weight and Volume
•Center of Gravity -- X, Y, Z
•Moment of Inertia -— I , I , I
xx yy zz•
Product of Inertia -- P , P , Pxy xz yz
The following are the two methods of calculating object—depth defi-
nition.
1. Body of Revolution Method
Define the part to be analyzed by rotating a planar figure
about an an axis. The axis of revolution lies on the plane with
the z-value of zero.
2. Planar Definition (either parallel or non-parallel)A
Define the depth by selecting lines in an orthogonal view.
The second method is more frequently applied. For more information
refer to the reference manual:
CADAM Interactive User Reference Manual
Volumes 1 and 2, SH20-6510-0
IBM Corporation
9. Mass Property Analysis 147
l‘\
~¤ G)
1 ° 1 2 2 2 2 2 2D. ܧ 2 2 2 2 2
8 8 8 8 8
Nßw A2 22 22 |2 2 2 2 2 2 ZwärEäääää 2
— an n • 0 0 Ä
2 22 2221,¤¤¤¤•,1'¤4
x " cg
gäXLu
2 22222.1111 I I I I I
2 2 2 2 23222221 22:22.n; § '$ S E‘ J A 4
- N H ¢ DX
9. Mass Analysis 143
ääääääää9988399
Säääääää
EäEno r~ äO
„ $1*ääääääää 2D Q
Z
Eääääääää E
N :·A
3
gääaäéääl-·
ä-Nüähüé
9. Mass Analysis 149
'IO. EXAMPLE DATA AND OUTPUT
Representative data and output are shown here for four cases. They
are named UTILITY, TANDEM, FENESTRON and SCAT. UTILITY and SCAT are
produced starting with HESCOMP input data. TANDEM and FENESTRON are
produced by direct modifications to the NDISK HESCOMP to HESCAD interme-
diate file for Verification purposes.
Figures 61 through 76 starting on page 163 show various depictions
of the resulting CADAM models for these four cases. Model II presents
the options of wings auxiliary propulsion and auxiliary propulsion using
propeller engines. The first set of data shows all input and and output
files. Subsequent examples show only the intermediate data files.
The first file is the HESCOMP input file for the UTILITY model.
Following this is the reduced form of the HESCOMP output on unit 6, which
retains only the information pertaining to geometry considerations. The
third file is the output file from the modified version of HESCOMP on unit
NDISK 10 which contains geometrical data (arrays HI, HO and TEST). The
fourth file is the message output file from HESCAD and the CADAM GIM CADCD
routines, on unit 6. These files together with with figures 61, 62 and
63 for the utility helicopter represent all the input and output variables
for a given sample case (with the exception of the HESCAD echo of the”
intermediate file and the linkage—editor diagnostic output).
The fifth, sixth and seventh files are the intermediate file listings
(unit NDISK) for the TANDEM, FENESTRON and SCAT models respectively.
10. Example Data and Output
h150
_ Tandem Rotor Helicopter Input and Output Data
The following data represent the input, output, and test variables
for a HESCOMP model of a tandem rotor helicopter. This file is created
for Verification purpose only (see Fig. 61, 62, 63, 64).
1 0.0 40.76232 6.0000 18.00003 0.3500 16.60004 0.2000 19.16235 0.0 11.16006 ‘0.0 6.50007 0.0 437.11728 6.5000 1.80009 6.5000 200.0 V
10 1.1000 20.000011 1.0000 4.5212 _ 6.0000 5.013 0.0 0.614 0.0 · 0.2115 1.1000 0.1116 0.1500 1.017 0.0170 0.3018 0.9000 4.500019 0.0 34.417720 0.0 12.445121 0.0 2.765622 1.0000 0.900023 0.0 0.150024 0.0 23.368025 0.0 1.500026 0.0 31.651827 0.0 6.890428 0.5 4.593629 4.5 0.600030 0.0 6.039031 0.0 0.800032 0.0 0.200033 0.0400 0.200034 3.0000 15.642035 0.0100 2.250036 0.2000 1.200037 1.5000 6.000038 0.6000 0.6000
10. Example Data and Output 151
39 0.2000 0.350040 1.0000 0.250041 1.1000 4.282842 0.04 1.531443 3.0 23.336444 0.01 1.045 0.2 1.046 0.0 1.047 0.0 4.048 1.0000 1.549 0.0 23.336450 0.0820 42.487251 -10.0000 0.082052 0.2000 1.000053 0.0750 6.000054 0.1000 -10.000055 0.0 0.200056 0.1800 8.514557 4.0000 0.180058 -17.0000 4.000059 0.1500 -17.000060 0.0750 0.150061 0.2500 0.250062 0.0 3.563 0.3500 1.064 0.2500 1.065 0.2000 1.066 0.6000 11.1667 1.2000 1.0 °68 0.0 1.069 0.0 1.070 0.0 1.371 0.0 31.651872 0.0 6.073 0.0 2.5974 0.0 0.675 0.0 0.7576 0.0 0.4677 0.0400 0.200078 3.0000 15.642079 0.0100 2.250080 0.2000 1.200081 0.0 5.000082 0.0 0.600083 0.0 0.550084 0.0 0.4585 0.0 50.086 0.0 0.087 0.0 0.088 0.0 0.089 0.0 0.0
10. Example Data and Output 152
90 0.0 0.091 0.0 0.092 0.0 0.093 0.0 0.094 0.0 0.095 0.0 0.0
A 96 0.0 0.097 0.0 0.098 0.0 0.099 0.0 0.0
100 0.0 0.0
1 2.00002 2.00003 4.00004 2.00005 0.06 1.0000 V7 0.08 0.09 1.0000
10 0.011 0.012 1.000013 1.000014 3.000015 2.0000
. 16 0.017 0.018 0.019 2.000020 1.000021 0.022 0.023 0.0
. 24 0.025 0.0
10. Example Data aud Output 153
Utility Helicopter Input and Output Data
This is a Verification data file for a single rotor helicopter with
a fenestrou tail. The fenestron tail wire-frame is produced by the
projection method mentioned earlier (see Fig. 65, 66, 67, 68).
1 0.0 37.76232 6.0000 6.00003 0.3500 18.60004 0.2000 19.16235 0.0 11.16006 0.0 6.50007 0.0 437.11728 5.5000 1.80009 6.5000 200.0
10 1.1000 20.000011 1.0000 4.5212 6.0000 5.013 0.0 0.614 0.0 0.2115 1.1000 0.1116 0.1500 1.017 0.0170 0.300 ‘
18 0.9000 4.500019 0.0 34.417720 0.0 12.445121 0.0 2.765622 1.0000 0.900023 0.0 0.150024 0.0 23.368025 0.0 1.700026 0.0 31.651827 0.0 6.890428 0.5 4.593629 4.5 0.600030 0.0 6.039031 0.0 0.800032 0.0 0.200033 0.0400 0.200034 3.0000 15.642035 0.0100 2.250036 0.2000 1.200037 1.5000 6.000038 0.6000 0.6000
10. Example Data and Output 154
39 0.2000 0.350040 1.0000 0.250041 1.1000 3.282842 0.0 1.131443 0.0 23.336444 0.0 1.045 0.0 1.046 0.0 1.047 0.0 4.048 1.0000 1.549 0.0 23.336450 0.0820 42.487251 -10.0000 0.082052 0.2000 1.000053 0.0750 8.000054 0.1000 -10.000055 0.0 0.200056 0.1800 8.514557 4.0000 0.180058 -17.0000 6.000059 0.1500 -17.000060 0.0750 0.150061 . 0.2500 0.250062 0.0 3.563 0.3500 1.0
. 64 0.2500 _ 1.065 0.2000 1.066 0.6000 0.067 1.2000 0.068 0.0 0.069 0.0 0.070 0.0 0.071 0.0 0.072 0.0 0.073 0.0 0.074 0.0 0.075 0.0 0.076 0.0 0.077 0.0 0.200078 0.0 15.642079 0.0 2.250080 0.0 1.200081 ‘ 0.0 6.000082 0.0 0.600083 0.0' 0.350084 0.0 0.085 0.0 0.086 0.0 3.087 0.0 0.088 0.0 0.089 0.0 0.0
10. Example Data and Output 155
90 4.5 0.091 0.0 0.092 0.0 0.093 0.0 0.094 0.9000 0.095 0.0 0.0
° 96 0.0 0.0 .97 0.0 0.098 0.0 0.099 0.0 0.0
100 0.0 0.0
1 1.00002 1.00003 1.00004 2.00005 0.06 1.00007 0.08 0.09 1.0000
10 . 0.011 0.012 1.0000 -13 1.000014 3.000015 2.000016 0.017 0.018 0.019 2.0000
° 20 2.000021 1.022 1.023 0.024 0.025 0.0
10. Example Data and Output 156
Scat Helicopter Input and Output Data
The following data represent the input, output, and test variables
for a HSCOMP model of a single rotor helicopter (see Fig. 69, 70, 71,
72).
1 0.0 36.88992 6.0000 9.00003 0.3500 20.4000
V 4 0.2000 16.48995 0.0 12.2400
. 6 0.0 3.50007 0.0 370.54768 6.0000 1.00009 3.5000 0.0
10 1.3000 1.000011 1.1000 0.012 9.0000 0.013 0.0 0.014 0.0 0.015 1.1000 0.016 0.1500 0.017 0.0170 0.018 0.9000 4.500019 0.0 30.103020 0.0 11.638921 0.0 2.586422 1.0000 0.900023 0.0 0.150024 0.0 21.854225 0.0 1.500026 0.0 21.973027 0.0 5.741028 0.5 3.827429 0.0 0.600030 0.0 4.985631 0.0 0.800032 0.0 0.200033 0.0100 0.200034 2.0000 15.642035 0.0100 2.250036 0.2000 1.200037 1.5000 6.000038 0.6000 0.6000
10. Example Data and Output 157
39 0.2000 0.350040 1.0000 0.250041 1.1000 2.282842 0.0 0.282843 0.0 4.057044 0.0 0.045 0.0 0.046 0.0 0.047 0.0 0.048 1.0000 0.049 0.0 0.050 0.0820 39.734951 -10.0000 0.082052 0.0800 1.000053 0.0400 6.000054 0.1000 -10.000055 0.0 0.080056 0.1800 7.554257 4.0000 0.180058 -17.0000 4.000059 0.1500 -17.000060 0.0750 0.150061 0.2500 0.250062 0.0 0.063 0.3500 0.064 0.2500 0.0·65 0.2000 0.066 0.6000 0.067 1.2000 0.068 0.0 0.069 0.0 0.070 0.0 0.071 0.0 0.072 0.0 0.0 ‘
73 0.0 0.074 0.0 0.075 0.0 0.076 0.0 0.077 0.0 0.200078 0.0 15.642079 0.0 2.250080 0.0 1.200081 0.0 6.000082 0.0 0.600083 0.0 0.350084 0.0 0.085 0.0 0.086 0.0 0.087 0.0 0.088 0.0 0.089 0.0 0.0
10. Example Data and Output 158
90 0.0 0.091 0.0 0.092 0.0 0.093 0.0 0.094 0.0 0.095 0.0 0.096 0.0 0.097 0.0 0.098 0.0 0.099 0.0 0.0
100 0.0 0.0
1 2.00002 1.00003 1.00004 2.00005 0.06 1.00007 0.08 0.09 1.0000
10 0.011 0.012 1.0000
‘
13 1.0000 p14 3.000015 2.000016 0.017 0.018 0.019 2.000020 1.000021 0.022 0.023 0.024 0.025 0.0
10. Example Data and Output 159
Fenestron Tail Helicopter Input and Output Data
This is a Verification data file for a single rotor helicopter with
a fenestron tail. The fenestron tail wire·frame is produced by projection
method mentioned earlier (see Fig. 73, 74, 75, 76)
1 0.0 37.76232 6.0000 6.00003 0.3500 18.60004 0.2000 19.16235 0.0 11.16006 0.0 6.50007 0.0 437.11728 5.5000 1.00009 6.5000 0.0
10 1.1000 1.000011 1.0000 0.012 6.0000
”0.0
13 0.0 0,014 0.0 0.015 1.1000 0.016 0.1500 0.017 0.0170 0.018 0.9000 4.500019 0.0 34.417720 0.0 12.445121 0.0 2.765622 1.0000 0.900023 0.0 0.150024 0.0 23.368025 0.0 1.500026 0.0 31.651827 0.0 6.890428 0.0 4.593629 0.0 0.600030 0.0 6.039031 0.0 0.800032 . 0.0 0.200033 0.0400 0.200034 3.0000 15.642035 0.0100 2.250036 0.2000 1.200037 1.5000 6.000038 0.6000 0.6000
10. Example Data and Output 160
39 0.2000 0.350040 1.0000 0.250041 1.1000 3.282842 0.0 1.131443 0.0 23.336444 0.0 0.045 0.0 0.046 0.0 0.047 0.0 0.048 1.0000 0.049 0.0 0.050 0.0820 42.487251 -10.0000 0.082052 0.2000 1.000053 0.0750 8.000054 0.1000 -10.000055 0.0 0.200056 0.1800 8.514557 4.0000 0.180058 -17.0000 8.000059 0.1500 -17.000060 0.0750 0.150061 0.2500 0.250062 0.0· 0.063 0.3500 0.064 0.2500 0.0 .65 0.2000 0.066 0.6000 0.067 ‘ 1.2000 0.068 0.0 0.069 0.0 0.070 0.0 0.071 0.0 0.072 0.0 0.073 0.0 0.074 0.0 0.075 0.0 0.0 _76 0.0 0.077 0.0 0.200078 0.0 15.642079 0.0 2.250080 0.0 1.200081 0.0 6.000082 0.0 0.600083 0.0 0.350084 0.0 0.085 0.0 0.086 0.0 „ 0.087 0.0 0.088
‘0.00.0
89 0.0 0.0
10. Example Data and Output 161
90 0.0 0.091 0.0 0.092 0.0 0.093 0.0 0.094 0.0 0.095 0.0 0.096 0.0 0.0 ‘
97 0.0 0.098 0.0 0.099 0.0 0.0
100 0.0 0.0
1 1.00002 1.00003 1.00004 2.00005 0.06 1.0000 -7 0.08 0.09 1.0000
10 0.07
11 0.012 1.000013
71.0000
14 3.0000 —7
15 2.000016 0.017 0.018 0.019 2.000020 2.0000 ‘
21 1.022 1.023 0.024 0.025 0.0
10. Example Data and Output 162
ikvl---N};
-}
T2
lo
3;
am
Q
P12
.:0
Data and
lr-«
Output
163
Ä"#\=‘—
‘
Q 6i·;*€?>l‘/Ä. \,««g;,;3¤@‘;.;,
;~· :>.¢¢sßpäyf
';t>/
Figure 62. Tandem Rotor Helicopter Wire-Frame (Model I)
10. Example Data and Output 164
Y fni/9
für ff¤sr\E. I §
.2· E
E ‘l·\9
*\10.Example Data and Output 165
.
\_gX_,__&>,IT<¤I*iä€%¤·
- "ye <%;;;·;
'*
\,;;<:>%i/Ä
—·;"|r•0?$>„A//0‘ {gl',
Ö"’ééE;§¤§’
Figure 64. Tandem Rotor Helicopter Wire-Frame (Model II)
10. Example Data and Output 166
I
E
IQ
C?1-1
2,-21-•8:1.ouI!
_ SE·1-11-I-1-1
x S‘·
If;»o
"‘\ 4,-
··‘}•‘(&—
10. Example Data and Output 167
p· ,,
Y/’E~
t4,·;¤‘:•·~?
•§¢;?/*;;1;-£2:;;:,»*‘ ""$$·"I
"§.«¢—-.;\
·
AQ\<§ «·§ ‘~<“x
\\ä ~· §~Q"
¤§‘«v¤=::;=I *2%;*
Figure 66. Utility Helicopter Wire·Frame (Model I)
U10. Example Data and Output 168
Kin-,,
l
Ia
~\gm;„/ A’ = I 1l
1lv
l-C
W^
II-I•-I8
.ä
·H3¤.
.
O
·UI1é’
x
Ü·•·|r-I
»o
\%
<»
w
äE
"*§x\\
1*10.Example Data and Output 169
11 l'1111**:
1 11
·" ~ ·,
„•
il
;7
;* :7,//¢'{ÄMM
0Figure68 . Utility Helicopter Wire-Frame (Model II)
10 . Example Data and Output 170
~Ü
EC•-4
¤>’¤oE
$-404-4¤.0o-4-4•-I
aa~ „-¤
4-»cu-2
$2 cx1 ~oev$-4:3¤0·•-4
[M •
Tg‘
W.
\§§\«~;§.xy
10. Example Data and Output 171
/x/Wyl
‘E ·'
XTAzää-;%-5::;
2;;-/ettttß”‘=-·‘.'=·-¢>?‘kaag,-«=,..•;%;¢&er
iä§é§?§,'é'E?"?\
\ \
A X
I‘\·' \§§&<
Figure 70. Scat helicopter Wire-Frame (Model I)
10. Example Data and Output 172
—ga- EQ
1
A A]W‘ I13~ 8-3‘ Etää1**;;;
x ·ä°
s10.Example Data and Output 173
1
· . ;°/ V ~:‘L
-ßL2;/;:l>·2 <"_;::¢,§;;-nlf, ..—‘:;a¢;;5·’:g::¤=74 ,
Xxa
&
§\$~-
\. —§„·’**"%ggg§\ge >‘*7/
sgFigure72. Seat helicopter Wire-Frame (Model II)
10. Example Data and Output-
174
I. Q21-1
. 8O
. EH
3¤.8
ISI8
_ 1-1·v-4
. :2‘ ‘¤§W
8""'···„,
Q
RTA 53‘ __ Q·r·Iwp Q\v;>
vw.'$sv.Qsää. ·•·%v¤ Weg.’&§;&Q,
¥°‘>‘;‘·;.
10. Example Data and Output 175
-
1 ,..
.--«·;;';;·;‘;:‘1‘Y¢—;-—--—-‘”""‘·::;;§Ü;..¢’ Ä ,.5* *;ä‘===-,;:.·===.··-=-—·‘--‘="""—-,-2"""7”"’--./-gg.-¤¤¤x.;:
-
«aEEä£=l=l=EEi}?'
Y E /
1.IA4Figure74. Fenestron Tail Helicopter Wire-Frame (Model I)
10. Example Data and Output 176
I
1
—
Ü7IÜ
-9
\‘
Ö
gH2.3q;
M,‘:
Qjjgge:
,:3
10
2
Ex
ä’¤
amE2
Pla Dat6 tPut
177
3S
r1
/ 7ezßßsäz
M_.„y_$¢&’ / J
texxäéäaä—;
Fi ure 76. Fenestron Tail Helicopter Wire-Frame (Model II)s
10 . Example Data and Output 178
ll. CONCLUSIONS AND RECOMMENDATIONS
From this research work we can see that CADAM can be used in aircraft
preliminary design. Using HESCAD, the aircraft external geometry en-
velop, interior equipment design, and its mass property analysis can be
developed interactively in the preliminary design.
The error trace method can be developed to satisfy any function curve
whether it is continuous or discontinuous.
The helicopter model may be further improved to approach the real
helicopter model. This can be achieved by changing the cross·section of
_ the model and subsequent interactive modifications.
Each part of the wire·frame helicopter could be modified individ-
ually into macro-geometry and grouped into a scope call function and these
individual parts could be generated by HESCOMP output with different
shapes. Also the interior equipment design procedure and mass property
analysis procedure could be grouped into a scope call function to simplify
the design and analysis procedures. HESCAD could be modified to run
interactively under macro-geometry dialog mode with user menu fields to
define variables not given by HESCOMP.
11. Conclusions and Recommendations 179
APPENDIX A. HESCAD PROGRAM
There are 26 subroutines in HESCAD program. The following table gives
subroutine names and their functions. HESCAD contains 10,199 records
including the HESCOMP interface. The reader who is interested in HESCAD
code should contact IBM Corporation Federal Systems Division, Bodle Hill
Road, Owego, N. Y. 13827 for more information.
HSCAD was developed by Dr. A. Myklebust and L. J. Lu, Department
of Mechanical Engineering, VPI & SU.
_ Function of HESCAD Subroutine
· Subroutine Function
MAIN HESCAD main program
PVNOSE Draws single rotor, tandem rotor and fenestron tail heli-copter primary view nose
SSV Draws 2-D single rotor helicopter side view geometry
STV Draws 2-D single rotor helicopter top view geometry
ROTOR Draws 2-D single rotor helicopter top view and primaryview tail rotor blades and draws tandem rotor helicoptertop view rotor blades.
CCROSS Draws single rotor and tandem rotor tail helicopter topview pylon
CPYLON Draws single rotor helicopter top view vertical tail andtandem rotor helicopter top view aft pylon
Appendix A. HESCAD Program 180
Function of HESCAD Subroutine
(continued)
Subroutine Function
SPV Draws 2-D single rotor and fenestron tail helicopter pri-mary view geometry
PSPLIN Generates parabolic spline used to draw single rotor,tandem rotor and fenestron tail helicopter top view nose
SPS20 Generates parabolic spline through 20 points used to draw2-D fenestron tail helicopter top view vertical tail
TSV Draws 2-D tandem rotor side view geometry
TTV Draws 2-D tandem rotor top view geometry
TPV Draws 2-D tandem rotor primary view geometry
SWFRAM Draws single rotor helicopter 3-D wire-frame
AFTBLS Draws single rotor helicopter 3-D wire-frame aft rotorblades
SHAFTA Draws single rotor helicopter 3-D wire-frame aft rotorshaft
TWFRAM Draws tandem rotor helicopter 3-D wire-frame
CROSS Draws single rotor and tandem rotor helicopter 3-D wire-frame cabin cross-section
PYLONl
Draws single rotor and tandem rotor helicopter 3-D wire-frame main rotor pylon cross-section
ENGINE Draws single rotor and tandem rotor helicopter 3-D wire-frame primary engine, jet engine and propeller enginenacelle cross-section
‘
VTAIL Draws single rotor helicopter 3-D wire-frame vertical tailcross-section and draws tandem rotor helicopter 3-D wire-frame aft pylon cross-section
Appendix A. HESCAD Program 181
Function of HESCAD Subroutine
(continued)
Subroutine Function
ELLIPS Draws single rotor and tandem rotor helicopter 3-D wire-frame nose cross·section
WING Draws compound single rotor and tandem rotor helicopter3-D wire-frame wing cross·section
SHAFTM Draws single rotor and tandem rotor helicopter 3-D wire-frame main rotor shaft cross·section
BLADES Draws single rotor helicopter main rotor blades and drawstandem rotor helicopter main rotor and aft rotor blades
Appendix A. HESCAD Program 182
APPENDIX B. COLLEC PROGRAM
COLLEC is a subroutine which provided a linkage between HESCOMP an
HESCAD. It writes a file on unit 10. COLLEC collects all HESCOMP input
(HI) and output (HO) geometry variables and places them in three arrays.
Also, COLLEC collects HESCOMP decision (TEST) variables and places them
in two arrays.
Appendix B. COLLEC Program 183
APPENDIX C. TERMINOLOGY
Term Description
CAD Computer-Aided Design
CADAM Computer Graphics Augmented Design and Manufacturing,a CAD/CAM program developed by Lockheed Corporation.
CADCD A component of the CADAM geometry interface module.It provides a collection of subroutines which areaccessed. by CALL statements to produce CADAM ele-ments.
CATIA A CAD/CAM program developed by Dassault Systems
GIM The CADAM geometry interface module
PROC A IBM OS job control language procedure ‘
VM CMS The IBM Virtual Machine Conversational Monitor System
DRAWFILE A component of the CADAM database
OS Linkage Editor The linker developed for the IBM 360 Operating System
Appendix C. Terminology 134
BIBLIOGRAPHY
1. Davis, S. J. et al., "User°s Manual for HESCOMP, The Helicopter Sizingand Performance Computer Program," 1979, Technical Report, distrib-uted by Defense Technical Information Center, Defense LogisticsAgency.
2. Myklebust, A. and Lu, L. J., "HESCAD — An Interface Between HESCOMPAnd CADAM For The Generation Of Helicopter Models," VPI CAD/CAM Lab-oratory, Vol. 1, Report No. 801691-1A, To IBM Federal Systems Divi-sion, Sept. 1985.
3. "CADAM Interactive User Reference Manual," Volumes 1 and 2,SH20-6510-0, IBM Corporation.
4. "CADAM Geometry Interface Installation Guide," SH20-6227-0, IBM Cor-poration.
5. "CATIA VM/CMS Utilities Manua1," SH20-6505, IBM Corporation.
6. English, C. H., "Interactive Computer-Aided Techno1ogy," Computer-Aided Design, Vol. 9, No. 4, Oct. 1977, pp. 243-254.
7. Sciarra, J. J., "Helicopter Fuselage Vibration Analysis in Three Di-mensions Using Computer Graphics," Pertinent Concepts in ComputerGraphics, University of Illinois Press, 1969, pp. 365-389.
8. Ashbaugh, J. B. et al., "DSPOBJ - System for Display of Multiple Sets’of Three-Dimensional Data," Computer & Graphics, Vol. 3, No. 2/3-A,1978, pp. 63-70.
9. Boyles, R. Q., "Application of Computer Graphics in Aircraft Design,"Interactive Graphics for Computer-Aided Design, Appendix C, Addison-Wesley Publishing Company, Inc., 1971, pp. 273-294.
10. Prince, M. 1D., Interactive Graphics for Computer-Aided Design,Addison•Wesley Publishing Company, Inc., 1971, pp. 31-32.
Bibliography 185