Welcome. Lancair International Lancair International Inc. manufactures advanced composite structures...
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Transcript of Welcome. Lancair International Lancair International Inc. manufactures advanced composite structures...
Welcome
Lancair International Evolution – Discovery and
Discussion
Lancair InternationalLancair International Inc. manufactures advanced composite structures at its
Redmond, Oregon facility, and has established proprietary relationships with hand-selected vendors in the USA, Europe, Australia and the Philippines. Worldwide, Lancairs are owned and operated in 34 countries on five continents.
HISTORY IN THE MAKINGThe Lancair family of aircraft covers the range of private pilot aircraft from the solid two-seat Lancair Legacy, the economical two-seat Legacy fixed-gear to the four-seat, fixed-gear Lancair ES and the recently completed Evolution rounds out the companies current offering. The PT6 powered turbine will propel the Evolution to incredible speeds of up to 330 kts in pressurized comfort over 1,000 Nmiles.
Lancair’s goal is to continue to play an important part in shaping the future of modern aviation through innovation, technical advancements, design purpose, aesthetics and of course, performance refinements in the entire Lancair family of aircraft.
Redmond AirportLancair
International
• 1983 - Lance Neibauer starts Neico Aviation with the introduction of the Lancair 200 in Gardena, CA.
• 1985 - Lancair 200 flies - Compton, CA• 1986 - Company moves to Santa Paula,
CA • 1987 - Introduction of the 320/360• 1989 - Santa Paula workshop Fast Build
kit introduced• 1990 - Introduction of the Lancair IV• 1991 - Construction of the composite
shop on Cebu, Philippines Molds• 1992 - The Company starts business in
Redmond as Lancair International. That fall the Lancair IV-P was introduced
Milestones• 1994 - Super ES • 1995 – Lancair 320 displayed at Metropolitan Museum of Art in New York City • 1996 - Lancair Certified Aircraft moves to Bend• 1999 - Legacy introduced at Oshkosh • 2003 – Lance Neibauer sells the Company to Joe Bartels in February• 2003.5 - Evolution Design Project Begins• 2004 - Introduced the ES-P at Sun-n-Fun• 2007 – Evolution Public debut• 2008 – First Evolution Prototype Flies and Testing Begins• 2009 - Evolution Piston flies to OSH and then onto Lycoming. First Customer Evolution Flies
• Competencies– Aircraft Design
Lancair excels at aircraft engineering and design. Lancair aircraft are the industries recognized leader in performance and innovation.
– Composite ManufacturingLancair has been designing and manufacturing high strength
composite aircraft for 25 years. Lancair’s products lead their respective market segments in strength and weight efficiency.
– Aviation Technology InnovationLancair has forged a reputation on bringing innovative products
to the personal transportation market and continues to be copied by kit and certified aircraft companies alike throughout the world wide aviation market.
EVOLUTIONDESIGN ON A HIGHER PLANE
Engineering
Evolution Introduction Specifications Performance Design
Flight Characteristics Certification Standards Flight Test Results Loads and Structures Structural Testing
FAA Certification
Evolution Concept
EvolutionReality
• S/N EVO-0001T : 300 hours• S/N EVO-0003T : 180 hours• S/N EVO-0004P: 75 hours• S/N EVO-0002, 0005 – 0019 In process with 2 more scheduled to fly in 2009
• 4 place Turbo-prop or Piston Engine• Pressurized • Retractable gear • Conventional aerodynamic configuration• Full carbon fiber composite airframe
Evolution Turbine Specifications
• L e n g t h - 3 0 f t• H e i g h t - 1 0 f t• W i n g s p a n - 3 7 f t• W i n g A r e a - 1 3 3 f t ^ 2
• W i n g l o a d i n g - 3 2 . 3 # / f t ^ 2
• A s p e c t R a t i o - 1 0 . 3• P T 6 A - 1 3 5 A ( 7 5 0 S H P )• H a r t z e l l 8 2 . 5 ” 4 b l a d e p r o p e l l e r• 1 4 6 g a l l o n s ( S t a n d a r d R a n g e ) / 1 6 8 g a l l o n s ( E x t e n d e d
r a n g e )• E m p t y We i g h t - 2 3 5 0 l b s• G r o s s We i g h t - 4 3 0 0 l b s• U s e f u l L o a d - 1 9 5 0 l b s• P a y l o a d a f t e r f u e l - 8 0 0 l b s w i t h e x t e n d e d r a n g e
t a n k s / 9 5 7 l b s w i t h s t a n d a r d t a n k s
• L e n g t h – 2 8 . 7 f t• H e i g h t - 1 0 f t• W i n g s p a n - 3 7 f t• W i n g A r e a - 1 3 3 f t ^ 2
• W i n g l o a d i n g – 3 2 . 3 # / f t ^ 2
• A s p e c t R a t i o - 1 0 . 3• L y c o m i n g I E 2 P i s t o n ( 3 5 0 H P )• H a r t z e l l 8 2 . 0 ” 3 b l a d e p r o p e l l e r• 1 4 6 g a l l o n s ( S t a n d a r d R a n g e ) / 1 6 8 g a l l o n s
( E x t e n d e d r a n g e )• E m p t y W e i g h t - 2 6 0 0 l b s• G r o s s W e i g h t - 4 3 0 0 l b s• U s e f u l L o a d - 1 7 0 0 l b s• F u l l F u e l P a y l o a d ( 1 2 0 G a l = 7 2 0 l b s ) - 9 8 0 # ’ s
Evolution Piston Specifications
Get Proper numbers for here
Evolution Turbine Performance• 3 3 0 K TA S @ 3 9 G P H @ F L 2 5 0• 3 0 4 K TA S @ 3 0 G P H @ F L 2 8 0• 2 7 0 K TA S @ 2 4 G P H @ F L 2 8 0• Vy 1 0 5 K I A S 3 3 0 0 F P M S L I S A• R O C @ F L 2 8 0 1 5 0 0 F P M• V x 8 5 K I A S • L a n d i n g A p p r o a c h S p e e d 7 9 K I A S• S t a l l S p e e d 6 1 K I A S @ 4 3 0 0 l b s• Ta k e o f f d i s t a n c e 1 4 0 0 f t S L I S A o v e r 5 0 f t• L a n d i n g d i s t a n c e 1 0 0 0 f t S L I S A• 8 7 6 n m w i t h I F R R e s e r v e a t 3 3 0 K TA S• 1 0 1 7 n m w i t h I F R R e s e r v e a t 3 0 4 K TA S
Evolution Piston Performance
• 2 7 0 K TA S @ 2 2 G P H @ F L 2 5 0• 2 4 0 K TA S @ 1 7 . 5 G P H @ F L 2 5 0• Vy 1 0 5 K I A S 2 0 0 0 F P M S L I S A• V x 8 5 K I A S• V L E 1 8 0 K I A S / V F E ( 1 0 ° ) 1 6 0 K I A S • L a n d i n g A p p r o a c h S p e e d 7 9 K I A S• S t a l l S p e e d 6 1 K I A S @ 4 3 0 0 l b s• Ta k e o f f d i s t a n c e 1 2 0 0 f t o v e r 5 0 f t• L a n d i n g d i s t a n c e 1 4 0 0 f t o v e r 5 0 f t• 1 3 0 0 n m w i t h I F R R e s e r v e a t 2 7 0 K TA S• 1 7 0 0 n m w i t h I F R R e s e r v e a t 2 4 0 K TA S
• Side stick controls• Pilot configurable for 5’2” to 6’6”
(5th% Female / 95th% Male)• 4 position seat back angle• Adjustable 6.5” fore-aft• Adjustable rudder pedals
• Crashworthy seats-all occupants• Automatic Climate Control• Enhanced Pilot visibility• AmSafe Airbag Seatbelts
Evolution Cockpit
Evolution Cockpit• G900 flight instruments
• Synthetic Vision• Highway in the Sky• Datalink Weather• Safe Taxi• Approach Plates• TAWS• TCAS
• Automatic Pressurization Scheduling• Dukes Certified Digital Control System
(Developed for the Eclipse jet)• Single cabin door with emergency exit baggage
door
Evolution Features
• Wide track trailing link landing gear (8” stroke)• Single slotted fowler flaps• BRS capable
• Chute tested, rocket design not complete• CAD Designed-CNC masters• Repeatable Tooling• 18 X 4.4 high pressure tubeless tires
• First set of tires lasted 272 landings• Parker High energy brake system
• Wheel and brake system specially designed for Evolution TSO’d• Energy capacity twice that of 6.00 X 6 brakes
N927LE Flight tested utilizing CFR 14 FAR 23 procedures for:
Stall FAR 23.49, 201, 203, 207 Controllability and Maneuverability FAR 23.143(a) Trim FAR 23.161, 677 Reference Landing Approach Speed FAR 23.73 Longitudinal Control FAR 23.145(d) Elevator Control Force in Maneuvers FAR 23.155 Static Longitudinal Stability FAR 23.175 Static Directional and Lateral Stability FAR 23.177 Dynamic Stability FAR 23.181 Vibration and Buffeting FAR 23.251
Flight Characteristics
Lightest test weight 2,805 lbs, Heaviest test weight 4,291 lbs
Forward test CG 120.17” (5.99% of Mean Aerodynamic Chord)
Aft test CG 130.38” (29.95% of Mean Aerodynamic Chord)
The four weight / CG regions are depicted on the weight and balance chart presented in this report. Limited ballast positions dictated the extremes of the envelope actually attainable.
The torque settings used for testing was de-rated MCP – 1280 ft lbs (~460 hp)
Balk landing control (FAR23.77(c))- Excellent
Stalling behavior (FAR23.201, 23.203) - flaps clean, take off, landing, turning flight- excellent
Approach to landing control (FAR23.177) - Excellent
Control harmony - Excellent Visibility over nose- Excellent Ground handling- Excellent
Flight Test Highlights
Get Correct FAR Refs here
Evolution Wt & Cg Envelope
Flight Envelope Loads Structural Testing
Loads and Structures
8
7
6 5
4
3
21
9
10
2400
2600
2800
3000
3200
3400
3600
3800
4000
4200
4400
120.0 121.0 122.0 123.0 124.0 125.0 126.0 127.0 128.0 129.0 130.0 131.0
Fuselage Station [in]
Airc
raft
Wei
ght [
lb]
Flight Envelope Weight and Center of Gravity
*Aircraft loading shown with combination of four people (800 LBS), 140 LBS baggage, and 144 gallons of fuel (1010 LBS)
Loads and Structures
V – n Diagram
V-n DiagramLancair Evolution
4300 LBS Gross Weight
-5
-4
-3
-2
-1
0
1
2
3
4
5
6
7
0 50 100 150 200 250 300
Airspeed (KEAS)
g L
oa
d
Loads calculated per FAR 23 requirements, Subpart C - Structures
Aircraft has three aerodynamic configurations and the Flight Envelope per FAR 23.333 and 23.245
Method based on McMaster using methods acceptable to FAA in previous aircraft certification programs
Evolution Wing with aileon deflection
-0.0500
0.0000
0.0500
0.1000
0.1500
0.2000
0.2500
0.00 50.00 100.00 150.00 200.00 250.00
Spanwise Location, y, inches
Coef
ficien
t of L
ift, C
l
Basic Lift
Additive Lift
Total Lift
Loads and Structure Design
Wing section wind tunnel tested at Texas A&M wind tunnel
Test Loads = Calculated Loads + EV factor (1.28X)
Load Tests Wing
Positive / Negative bending and shear with torsion
Landing Gear Attachments Fuselage Attachments or
Fuselage Wing Box Horizontal Stabilizer Vertical Stabilizer Flaps and Control Surfaces Pressure Vessel
Loads and Structures
Ultimate load test = 192% Limit Load
Evolution Wing Load TestZ Shear
0
1000
2000
3000
4000
5000
6000
7000
8000
0 20 40 60 80 100 120 140 160 180 200 220
Wing Station
Sh
ea
r (L
BS
)
Test
PMAA2 Z Shear
Evolution Wing TestBending Moment
0
100000
200000
300000
400000
500000
600000
700000
800000
0 20 40 60 80 100 120 140 160 180 200 220
Wing Station
Mo
men
t (IN
LB
S) Test
PMAA2 X Moment
Load Tests Wing
Positive Load case is 5.5g
maneuver case at forward CG zero fuel condition
Loads and Structures
Evolution Wing TestAsymmetric Bending Moment
0
100000
200000
300000
400000
500000
600000
700000
0 20 40 60 80 100 120 140 160 180 200 220
Wing Station
Mo
me
nt
(IN
LB
S) Test
PMAA2 X Moment
Load Tests Wing - Fuselage
Attachments 212,500 IN LBS across
center section
Evolution Wing Load TestAsymmetric Z Shear
0
1000
2000
3000
4000
5000
6000
7000
0 20 40 60 80 100 120 140 160 180 200 220
Wing Station
Sh
ea
r (L
BS
)
Test
PMAA2 Z Shear
Loads and Structures
Evolution Wing Load TestZ Shear
-1000
0
1000
2000
3000
4000
5000
6000
0 20 40 60 80 100 120 140 160 180 200 220
Wing Station
Sh
ear
(LB
S)
Test
Landing 2 Z Shear
Load Tests Wing - Landing Gear Attachments
Evolution Wing TestTorsion
-160000
-140000
-120000
-100000
-80000
-60000
-40000
-20000
0
0 20 40 60 80 100 120 140 160 180 200 220
Wing Station (IN)
IN L
BS
mo
men
t
test
Landing 2 YMoment
Load Tests Horizontal Stabilizer Symmetric
Unchecked Va maneuver per FAR 23.423(a) Asymmetric
100 / 55 % per FAR 23 .427(b)
Load Tests Vertical Stabilizer
Three load point with wiffel tree and lead shot
Aft fuselage with symmetric and asymmetric horizontal loads
Load Tests Flaps and Control Surfaces
Ground Vibration Test and Flutter Analysis
Ground Vibration Test Conducted by ISMB Germany
Flutter Analysis Conducted by Norbert Niedbal
FAA Certification Meeting –
Certification by Subpart Standardized Testing Compliance issues (No unique Special Conditions Proposed)
Results – Acceptance & Agreements
Next Phase -
December 1, 2008 with FAA Small Aircraft Directorate
CONCLUSION : • The Evolution design is a completely different design philosophy than any previous Lancair Kit product.• Beginning with FAA Certification Standards as the basis, Lancair invested five years and 5 million dollars in getting it right.• Lancair International is committed to seek engineering solutions for all fleet aircraft not meeting the highest safety standards possible.