Space Vehicle Mechanisms · 2018. 10. 26. · Marman Clamp Trunnion Design r.901 10-32 Xa285 LCK...
Transcript of Space Vehicle Mechanisms · 2018. 10. 26. · Marman Clamp Trunnion Design r.901 10-32 Xa285 LCK...
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Space Vehicle Mechanisms
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Mechanisms- Topics Of Presentation
• Adapter/Interstage Separation System
• Interstage/Spacecraft Separation System
• Antenna Feed Deployment System
• Solar Panel Deployment System
• Sensor Cover System
• Star Tracker Cover System
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Mechanisms - Adapter/Interstage Separation System
Marman Clamp
• Load Path - Cylinder To Cone
• Requires 2 Ordnance Devices
• Inherently Redundant
8 Ibm Marman Clamp
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Mechanisms - Adapter/Interstage Separation System
Marman Clamp - General Information
Design Line Load:
• Worst Load Case For Clamp Is +3 g Axial & ±3 g Lateral
• Based On F .E. Model Of Satellite & lnterstage & Rigid Body Analysis Of Solid Motor
• Design Limit Line Load Is 240 lb/in
Strap Tension (Preload):
• Nominal3350 ±350 lb
• Strain Gages On Strap To Assure Within +10% (±350 lb)
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Mechanisms - Adapter/Interstage Separation System
Cross-Section Of Shoe On Rings
Scale 1:1
Gap .05-.08 inches (.08 " Shown)
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Mechanisms - Adapter/Interstage Separation System
(1.75)
Interstage Ring Cross-Section
[.oao-.o�
.115 •• oos -.000
1------------(010.997) ----
96.37• •• so•
"---4---------- 40.b54 '·000 ---, ,.. -.005 JQ(,OIOlCl
1------------(010,749) ---
t-------(041.7 .. 0)-----------
m
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Mechanisms - Adapter/Interstage Separation System
Adapter Ring Cross-Section
R .040· .060
14----t---r-- (12141. 740) ------
J..---+---- 040.659 • "005 ----
•• QOO IO J.OIOlB]
14---- (12139.125) ----
R .010· .030
.500 2X 45" X .03
J.------- (12142.02) -------
(I. 75) ·
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Naval Re5earch Laboratory Washington, DC 20375-5000
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Mechanisms - Adapter/Interstage Separation System
Marman Clamp Shoe Design
26 Aluminum Shoes (7075-T7351)
M.S.y= 2.0, M.S.ult= 2. 7
4 Titanium Shoes (Ti-6Al-4V)
M.S.y= 3.4, M.S.ult= 3.7
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Mechanisms - Adapter/Interstage Separation System
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Mechanisms - Adapter/Interstage Separation System
Marman Clamp Strap Design
1 0 05 o262
IE-I---- 4 0 49 ----�
28 PLCS
Material: 301 Cres 3/4 Hard Sy= 135 kpsi, Su= 175 kpsi
For Max. Tension= 3700 lb MSy= .82, MSu= 1.36
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l\fechanisms- Adapter/Interstage Separation System
Marman Clamp Spacer Design
0 I A� � 45
0 I A� • 25 OIA .144
_[ .063 . 083 1
___i__ ...... ,.__ -�t:r:_:..,:��.=!' r r
For Tmax= 15 in*Ib: MSy= .9
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SHOE
*6-40 BOLT NUT
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Mechanisms - Adapter/Interstage Separation System
Trunnion & Shoe Layout
l D 48
28 PLCS
�- o80
2 PLCS
SEPBOLT HI-SHEAR #SC1005-4 (HIDDEN LINES SHOWN)
NOTE: TRUNNION DIAMETERS ARE Oo90 INCHES
Naval Research Laboratory Washington, DC 20375-5000
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Mechanisms - Adapter/Interstage Separation System
Marman Clamp Trunnion Design
r.901 10-32 Xa285 LCK HELICOIL
.30 � �- -01 a375-24 LaHa THRU -03 a257 THRU 2 PLCS
• Aluminum Trunnions .57 lb Lighter Than Steel
• MSy= 3.8 For AI So Not A Strength Problem
• Will Make Both Steel & AI For Testing
0 I AD D 90
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Mechanisrr•� - Solar Array Drive Assembly
Deployment Sequence:
Stowed
Rotation
Fully Deployed
SV -Mechanisms
10°
Solar Cells
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Solar Cells
'
Solar Cells
Solar Cells
* All Angles Are Relative To The Solar Array Drive Gimbal
) 180° H-rr-----rr---rr--�-__.._ - Rotation
Solar Cells
Solar Cells
' SADA-Deploy/Rot
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Mechanisms - Solar Array Drive Assembly
Solar Array Drive Charateristics:
• 4.0" Diameter X 5.0" Depth Envelope • 340° Range Of Motion • Total Weight= 12 lbs ( 4 lbs/Drive+4lbs
Electronics • Slew Rate: 0 to 200 Steps Per Second • Step Size: 0.02 deg • Max Angular Velocity: 4 deg/s [Gives
Ability To Rotate 340° (Stop-To-Stop) In 85 sec]
0 o Referenoo Angle _/
/ SV -Mechanisms
.......,.so Electric Stop \� (Lim� Sw�dl)
2 Plaoos
"---_ Hard Stop 1 Plaoo
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Mechanisms- Solar Array Drive Assembly
Solar Array Drive
6X ¢·194 THRU . . 188 LOCATED ON� l�l¢.o1o®l cl o®l
SHOWN AT 0' REF POINT (-170' CCW)
6X .164-3;:UNC-28 HELICAL CO L INSERT w¢·63o .620 LOCATED Otl� 1�1¢.010@�
SV-Mechanisms
n�4.405 l"4.395
n�3.520 l"3.510
LJTO 1 RE -13-35P( 453)SR
TBD
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.195 .185
n\2.620 l"2.61 0
11=---1�
n\3.204 l"J.194
n\3.270 l"3.265
1----- 5.00 MA:X ----...;
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Washington, DC 20375-5000
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Mechanisms - Solar Array Drive Assembly
Solar Array Drive
Procurement Status:
• Contracted To Schaeffer Magnetics
CDR December 2, 1992 .
•
• Receive Engineering Model February 1, 1993
• Receive Flight June 1, 1993
SV -Mechanisms
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Naval Research Laboratory Washington, DC 20375-5000
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SV -Mechanisms
Mechanisms - Solar Array Drive Assembly
(i) � � . . . . . .
STOWED
Primary Components
• Solar Array Drive
• Hinges & Link Structure
• Frangibolt Release Devices
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DEPLOYED
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Naval Research Laboratory Washington, DC 20375-5000
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Mechanisms - Solar Array Drive Assembly
Requirements:
• Track Sun Within+ 5o About TheY-Axis
• Array Reorientation Within 5 Minutes (Stop-To-Stop)
• Support Deployed Arrays (0.31 g Loading)
• Minimize Sensor Jitter Due To Array Motion During Mapping
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Naval Research Laboratory SV-Mechanisms Washington, DC 20375-5000
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Mechanisms - Antenna Feed Deployment System
Paraffin Actuator Overview
Shearr Disk
Mounting Ferrule
• Low Weight: Typically 0.125 lb
• Power Requirements: Typically 10 W For 150 sec (Only 5 W for Pin Puller)
• High Reliability: One Moving Part
- Redundant Heaters SV -Mechanisms
Naval Research Laboratory Washington, DC 20375-5000
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Mechanisms - Antenna Feed Deployment System
Characteristics StarSystems Research PIN PP-25 Pin Puller with EH-3525 Actuator
Mechanism Mass:
Pin Retraction Stroke:
Pin Retraction Force:
Lifetime:
Actuator:
Operating Environment:
Maximum Pin Load:
Lead Length:
Nominal Power:
SV -Mechanisms
140 g Max with Actuator
0.30 in Min
20 lbfMin
100 Operations Minimum
EH-3525 Bellows Actuator
- 60°C to + soac
45 lbf 90° to pin axis, acting .235 from pin end
28 in Minimum
5 Wat 28 VDC
Naval Research Laboratory Washington, DC 20375-5000
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Mechanisms - Antenna Feed Deployment System
• StarSystems Research PIN PP-25 Pin Puller with EH -3525 Actuator
Characteristics:
Weight:
Pull Force:
0.31 Ibm
20 lbf
Min. Stroke: 0.30 in SV -Mechanisms
Ant Feed Pin Pull
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Mechanisms - Antenna Feed Deployment System
GlO Fiberglass Antenna Testing
Part # Spring Spring Type Of Results Width iThickness Testing
.SIN X-001 .35" 1/32" General- Demo Cycled over 100 times to goo. ' Failed w hen bent 180°
S/N X-002 .5" 1/32" Life Cycled 15 times to goo
S/N X-003 .35" 1/32" Demo N/A
S/N X-006 .35" 1/32" Life Cycled g21 times to goo
S/N X-005 .35" 1/32" Creep Held at goo. Failed w/in 24 hrs
S/N x-004 .35" 1/3 2" Creep Held at goo. Failed in 128 hrs
S/N 16-001 .35" 1/1 6" Life Cycled 11 times to goo
S/N 16-002 .30" 1/16" Life Cycled 1 0 times to goo
*N ote: All Springs 8 Inches In Length.
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SV -Mechanisms
Mechanisms - Antenna Feed Deployment System
Antenna Mast (G-1 0 Fiberglass)
Carpenter Springs (Graphite-Epoxy)
Note: Pin In Double Shear
Naval Research Laboratory Washington, DC 20375-5000
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Mechanisms - Antenna Feed Deployment System
Requirements:
• Repeatable Location Of Antenna Focus Within + 0.1 (From Maximum Angular Misalignment Of+ 0.25 °)
• Survive Launch, Spin-Up, & Solid Burn Loads When Stowed
• Minimize RF Reflective Material In Field Of View
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Mechanisms - Interstage/ Spacecraft Separation System
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Mechanisms - lnterstage/ Spacecraft Separation System .
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Catcher Fingers
SV -Mechanisms
Bolt Catcher
0.219 _...
Mass = 0.05 Ibm
t
Naval Research Laboratory Washington, DC 20375-5000
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Mechanisms - Interstage/ Spacecraft Separation System
ITl .&
Cup/Cone Piece Parts
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If If! .olo®iA!a$1 UIL·S·774Z
Material: Cres A286 lAW AMS 5757
Naval Research Laboratory
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Mechanisms - lnterstage/Spacecraft Separation System
SV -Mechanisms
3/8" Separation Nut From Hi-Shear
2.00
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0.69 1
2.50
2.85
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Mechanisms - Interstage/Spacecraft Separation System
Cross-Section Of Joint
Installed Preload = 28000 lbf I 3500 lbf per Joint Worst Load Case 3 g Axial
±3 g Lateral
Worst Case Results: Lateral Load = 3000 lbf Joint Load= 25000 lbf Required Jl = 0.12
Non-Contacting Cup Cone
(�
Bolt Catcher
.438 L.247 I
1.954
3/8" Separation Nut (Hi-Shear)
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Mechanisms - Interstage/Spacecraft Separation System
8 Separation Nut System
• .Load Path - Octagon To 8 Points To Cylinder
• 3500 lb Preload - Strain-Serted Bolts
• Redundant Ordnance for Each Nut
3/8" Separation Nuts (8 Places)
12.4lbm / For Nuts, Bolts,
&Ordanance
Naval Research Laboratory Washington, DC 20375-5000
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Mechanisms - Adapter/Interstage Separation System
Part
Str ap
AI Shoes
Titanium Shoes
Trunnions
Sepbolts
Spacers
Nuts & Bolts
Marman Clamp Weight Table
Quantity Mate rial
1 301 Cres, 3/4 Hard
2 6 AI 7075-T7351
4 T i -6A I-4V
4 AI 7075-T7351
2 17-4 PH SST
28 AI 6061-T6
3 0 Steel
Weight Ea. Total Weight (Ibm) (Ibm)
3.4000 3.400
0. 1006 2.616
0.1610 0.644
0.0650 0.260
0.1250 0.250
0.00 1 2 0.03 4
0.0070 0.210
Total Weight= 7.41
Naval Research Laboratory Washington, DC 20375-5000
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Mechanisms - Adapter/Interstage Separation System
Clamp Separator From Hi-Shear #SCOOOl-4
f 5.05 REF FOR -1 +----1-.43_0 _ ______ 5.17 REF FOR -2 ----------A'-
---,r� t--0.125 --+---
• 5000 - 6000 Ibf Ultimate Shear
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Naval Research Laboratory SV-Mechanisms Washington, DC 20375-5000
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SV -Mechanisms
Mechanisms - Solar Array Drive Assembly
Solar Array Drive Sun Tracking
* Rotation Angle Relative To Zero Degrees On Motor Gimbal
Naval Research Laboratory Washington, DC 20375-5000
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A R R A y
R E s p 0 N s E
SV -Mechanisms
Mechanisms - Solar Array Drive Assembly
Example of Solar Array Dynamic Response to Driving Options
*Much Flexibility in How The Arrays Are Driven *Will Test Various Responses - Set Motor Speeds Accordingly
Response= f(motor input, natural frequency, damping characteristics)
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T = 18 sec (Example)
BEGIN MAPPING
TIME
=Mapping Naval Research Laboratory Washington, DC 20375-5000
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SV -Mechanisms
Mechanisms - Solar Array Hinge Assembly
Solar Array Structure - Hinges & Link Assembly
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Naval Research Laboratory Washington, DC 20375-5000
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SV -Mechanisms
Mechanisms - Solar Array Hinge Assembly
Solar Array Drive Motor/ Array Hinge Assembly
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Naval Research Laboratory Washington, DC 20375-5000
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Mechanisms - Solar Array Release Mechanism
DESCRIPTION: Frangibolt Overview
Shape Memory Alloy Actuator To Break Bolt In Tension
28 Vdc Heater Drives Actuator Which Elongates When Heated (90 W for 30 sec)
Notched Bolt Stretches Until It Fails At Notch (Controlled Breakage)
ADVANTAGES:
• Light Weight: Actuator .05 lb
Improved Reliability
Redundant Heaters
No Sliding Friction
Lower Shock
Safer Design Due To Elimination Of Explosives
• Not. Sensitive To EMI ·Can Use Unshielded Wiring
SV -Mechanisms
SEPARATION
SMA ACTUATOR
HIGH STRENGTH ALLOY NUTS, BOLT & WASHERS
NOTCH PROVIDES CONTROLLED SEPARATION
INTEGRAL ELECTRONIC HEATER /INSULATION
Naval Research Laboratory Washington, DC 20375-5000
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Mechanisms - Solar Array Drive Assembly
Frangib�lt Joint Design
Aluminum AI7075-T7351--...... w ..,_ ___ Titanium
Naval Research Laboratory Washington, DC 20375-5000
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SV-Mechanisms
Mechanisms - Solar Array Release Mechanism
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Frangibolt Base Sub-Assembly
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Mechanisms - Solar Array Release Mechanism
Frangibolt Plug Sub-Assembly
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SV -Mechanisms
Naval Research Laboratory Washington, DC 20375-5000
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Mechanisms - Solar Array R.elease Mechanism
Frangibolt Retainer Sub-Assembly
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Mechanisms - Sensor Cover System
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Requirements:
SV -Mechanisms
• Protect Sensors From Debris Contamination
• Repeatable Use (Due To Uncertainties About Delta-V Thruster & ACS Contamination)
Naval Research Laboratory Washington, DC 20375-5000
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COVER ATTACHES TO SHAFT
Mechanisms - Sensor Cover System
Layout Of Sensor Cover System
BEARING SET
INPUT CAM
TORSION SPRINGS ATTACH TO FRAME AND COVER
HINGELINE
BEARING SET
SHEAR PANEL-
PP5501 AND ACTUATOR
-,
Naval Research Laboratory Washington, DC 20375-5000
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Mechanisms - Sensor Cover System
Layout Of Band Drive & Cam
HINGE SHAFT DRIVE BAND
DRIVE CAM
IDLER WHEELS
SHEAR PANELS
LONGE RON PP5501 \.JI ACTUATOR
FRAME
Naval Research Laboratory Washington, DC 20375-5000
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SV -Mechanisms
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Mechanisms - Sensor Cover System
Paraffin Actuator & Binary Latch Drive System
ELGilOY METAL DRIVE BAND
DRIVE CAM
COVER OPEN
PP-5581 LA TCII
IIOP LINEAR MOTOR
��--�1 I J,____, �R ClOSING
COVER CLOSED
BAND ATTACIUAENT PLATES
2 SEP 9
Naval Research Laboratory Washington, DC 20375-5000
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Mechanisms - Sensor Cover System
RETAINING NUT
ROT A TING/THRUST BUSHING
SPHERICAL BUSHING
Bearing Set Detail
THRUST WASHER FRAME
SHAFT
BEARING SET DETAIL
Naval Research Laboratory Washington, DC 20375-5000
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Mechanisms - Sensor Cover System
Labyrinth Seal Geometry
COVER EDGE CLOSE-OUT
HONEYCOMB CORE
THESE SURF ACES CONTACT
FACE SHEETS
0-RING SEAL SHEAR PANEL
LABYRINTH SEAL GEOMETRY
FRAME
Naval Research Laboratory Washington, DC 20375-5000
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Mechanisms - Sensor Cover System
Cover Materials
HONEYCOMB CORE FACE SHEETS
COVER EDGE CLOSE-OUT
ADHESIVE FILM (2 PLACES>
HONEYCOMB CORE
- HEXCEL HRH-310: ARAMID FIBER WITH POL YIMIDE RESIN
FACE SHEETS
- SYNTHETIC QUARTZ WITH POL YIMIDE RESIN
EDGE CLOSE-OUTS
- VESPEL SP-1: POL YIMIDE
ADHESIVE FILM
- CYANATE ESTER
COVER HONEYCOMB MATERIALS
Naval Research Laboratory Washington, DC 20375-5000
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1.000--.-
0.138
0.725
1.730
0
0.310 J SV -Mechanisms
Mechanisms - Sensor Cover System
StarSys Research P-5501 Binary Latch
0.575 Maximum Extentlon
0.540 Switch Signal
0.450 +.015 At Latched Position
0.156 Thru. 4X
2.023 2.308
© 1 t 0.314 0.727
0.000 Retracted Position
2.368
0.125
0.800
0.875-32 UN-2B
Sen Cover-Bin Latch
Naval Research Laboratory Washington, DC 20375-5000
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Mechanisms - Star Tracker Cover System
Requirements:
• Protect Star Trackers From Debris Contamination
• Repeatable Use (Protect From Solid Rocket Contamination And Long Sun Stares)
STAR TRACKER (EACH SIDE)
Naval Research Laboratory Washington, DC 20375-5000
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Mechanisms - Star Tracker Cover System
MLI INSIDE STIFFENING
RING
BEARING HOUSING
FLEXIBLE COUPLING
PARAFFIN ACTUATED
ROTARY BINARY LATCH
LABYRINTH SEAL COVER
MLI UNDER
.030" THK PLATE
Naval Research Laboratory Washington, DC 20375-5000
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Mechanisms - Star Tracker Cover System
14---- 50 825 --�
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Aj TOP VIEW, HOUSING
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Naval Research Laborat9ry Washington, DC 20375-5000
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Mechanisms - Star Tracker Cover Bearings
VIEW A
FLEXIBLE BELLOWS
COUPLING �· 9oo ANGULAR CONTACT
BEARINGS
PARAFFIN ACTUATED
BINARY LATCH
15 IN-LB TORQUE
I. 200
VIEW A
Naval Research Laboratory Washington, DC 20375-5000
-
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Mechanisms - Star Tracker Cover System
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StarSys RF-1035 Rotary Binary Latch
1.750
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4X -.170 1HRU
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Naval Research Laboratory Washington, DC 20375-5000
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Mechanisms - Star Tracker Cover Design Features
SEAL • Non-Contacting Labyrinth Seal Design • Labyrinth Surface Gold Plated To Prevent Vibration
Fretting And Provide Low Coefficient Of Friction
ACTUATOR • High Output Paraffin Actuator Provides Rated 15 in-lb
Opening Torque • Return Spring Provides 5 in-lb Closing Torque
SHAFT BEARINGS
• Preloaded Back-To-Back Angular Contact Bearings For Shaft Stiffness
• Dual Spring Preload Reduces Thermal Expansion Problems And Prevents Unloading During Launch Vibration
• Flexible Coupling Prevents Binding Due To Shaft Misalignment • Pennzane X2000 Oil And Labyrinth Seal Result In Lubricant
Outgassing< 6 X 10-7 gram/yr@ 30 deg. C
Naval Research Laboratory Washington, DC 20375-5000
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Mechanisms- Star Tracker Cover System Weight
ITEM
Paraffin Actuator
Rotary Labyrinth Cover
Stationary Labyrinth
Star Tracker Housing
Shaft and Bearings
Flexible Shaft Coupling
TOTAL
WEIGHT (LBS)
0.5
0.25
0.1
0.9
0.45
0.05
2.25
Naval Research Laboratory Washington, DC 20375-5000
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Mechanisms - Schedule (1 Of 2)
Activity Name MARMAN CLAMP ; ; ; ; ; ; ; ; ; ; : : ; ; ; �.. ; ; ;
,,,,,,, ••••• ,, ... ,,,, .. ,, .. ,, .. ,,,,,,, ............ u••••••••••••••• ...... ,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, ,,,,,,,: ••• ,,,.,,,,,,, ,,,,,,,,,,,,,,,,,,, ·••C·••••••I•••••••I•••••••I•••••••I•••••••) •••••••)••••••4-••••••C·••••••C•••••••I•••••••I•••• .. •I•••••••)••••••-O>•••••• DESIGN AND DRAW/MANUFACTURE � ! ' ' ' ' ! ! ! ! ! ! ! ! ! �! ! ! ! • • • • • • • • • 0 • 0 • 0 • • • • • • ,,,,,,,,,,,,,,,, .. ,,,,,,, .. ,,,,,,,,,,,,,,,,,,,,,,,,.,,,,., .. ,,,,,,,,, .. ,,,,.,,,,,,,,,, .. ,,,,,,,,,,, .. ,,,,,,,,,,,,,,,,,,,,, .. ,,,,,,.,,. r ••••••.•••••••• l •••••••:·•••·•·:· ···�··•••oo1•••••••1•••••••1•••••••J •••••••:•••••••:••••••"':' ••••••�· .. ••••1•••••••J•••••ooz •••••••:•'"''"':'"'"':'"'"'" ORDER SEPERATION DEVICE � ! ! ! I$ mj 1 ! 1 ! 1 !.1 RECEIVE FLIGHT ! 1 ! ...................................................................................................................................... ( ....... : ....... : ....... , ....... � . ... : ....... � ....... : ....... : ....... : ....... � ..... .. � ...... :. ... .a.: .... ... � .. :: ... : ....... : ....... � ....... � ...... :. ..... . DESIGN/MANUFACTURE TESTFIXTURE � 1 1 1 : : 1 1 1 1 1 1 1 1 � •1 1 1 1
;��������:�":����(�::::::.:.�=-:::::::��:::::�:::��:::::::_�::r:�r-I:.Tr:r:.:�::::::i::::I:::J:::::.J::::i::rJ:::::r::;:::J::::t:: :t:::: DESIGN, ANALIZE, AND DRAW JOINT STRUCTURE ! : : : � � l � l � � l l � � �·l � � � ...................... .............................................. .................................................................. : ............... , ....... , ....... ,.. . .. � ....... c ....... ........ ... ... .......... , ....... ,. ...... ,:.. ...... � ....... c ....... , ....... , . ...... , ....... , ...... .:, . ... .. ORDER STRAIN-SERTEDBOLTS � � f ,., ���RE:CEIY(+ :s�LT� : � �� � � � oooooooooooooooooooooooo .. ooooooooooooooooooooooooooooaoooooooo•••oooooooooooooo oooooooooooooooooooooooooooooooooooooooooooooooooooooorooooo••l"''""l"'''"'f'''''"':• •••'t''""' �""'''l''''"'l'"""'l'''' "'f'''''": •ouoo-: oooooo�ooooo••f.•oo•oo•J"'''''I''"'''J "'''''l ''"''":''''''
... �.:.���.�!��.�.:��.:�.:���:.!�.�.��!� .. �.�9..?.:�!:.!:�! ........ ............... L. .... L. .... L. ... .L ... ..!. � ... L .... L ..... L. .... L. ... .L ..... L . .. L ... L .... l... .... h�L. ... .L .... .L .... L .. . TEST SEPARATION JOINT i i i i i i i i iml i i i i i i.. i i i ·:::::::·:::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::i:::::::!:::::::l:::::::l::::::t ::t:::::!:::::::l:::::::l:::::::l:::::::l::::::t:::::t:::::t:::::i:::::::i:I���HANI�Ms ANTENNA FEED ; i i i i i i i i i i i i i i i.iiNSTALLED ...................................................................................................................................... 1 ....... ! .... ) ....... ! ....... � . ... { ....... j ..... ) ....... j ....... j ....... ! .... ...} ...... t ...... j ....... j ....... j ....... j ON FLIGHT MATERIAL SELECTION/ PURCHASE ! : : : > ! l ! ! l l l ! ! ! .lVEHICLE oooooooooooooooooooooooooooooooooooooooooooOOooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooo:ooooo••loooooooJoooooooJooooooo)o ooo(ooooo•oCooooooolooooooolooooooolooooooo)ooooooo)o••oooo)oooooo(•ooooooCooooooOI•••••••I PROTOlYPE BUILD AND TEST ITERATIONS l ' ' : ' ' : ! l l l ! l ! l l.l : : : ooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooooioooooo•ioooooo•iooooooo/oooooo•i• oooioooo•••i•ooooooi•ooooooiooooooo;ooooooo;ooooooo: oooooo.;, ..... , � ....... !.,••oo•:oooo•oo!oooooooi•"'"'�'""'i-""" DESIGN STOW AND RELEASE MECHANISM ! ! ! ! j ! • ! ! ! ! j ! ! ! !.! ! ! j ...................................................................................................................................... i ....... : ....... , ....... ; ....... � . ... : ....... : ....... ; ....... : ....... ; ....... � ....... � ...... � ...... : ....... : ....... : ....... ; ....... � ....... � ...... :., .... .. ORDERACTUATOR i ! ! ; ! ! ! !.! RECEIVEFLIGHT ! ! !A! ! ! ! ...................................................................................................................................... : ....... i ....... i .. � ....... ; . ... c ....... c ..... .. i ....... ; ....... ; ....... ; ....... ; ...... .:. ...... c ....... c ....... i.�----···i···· ... ; ...... ,s. ..... . STOW & RELEASE TESTING (WITHOUT ACTUATOR) � � � � � � �mmt � � � � � � � �·� � � � oooooooooooooooooooooooooouooooooooouoooooooooooooooooooooooooooooooooooo•oooo•oo••••oo•oooooOooooooooooooooooooooooooooo•o••••••Oo•:ooooo••l•oo••••l•oo••••l oooooo•)• ·••(ooooooo(••••••• C•••••••I ooooooofOoOOOoofoOooooo� ooooooO: oooooo(••ooooof.oooooo• I•.Af
"'""'J'""'''J •ooooo")> oooooo FULL SYSTEM TESTING & POSSIBLE MODIFICATIONS l l ! l l l l l l l : ' : ' l ! vl l l l
SV -Mechanisms
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Naval Research Laboratory Washington, DC 20375-5000
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-
Mechanisms - Schedule (2 Of 2)
Activity Name
SOLAR ARRAY DRIVE ASSEMBLY � , , , : � , : : : : : , : : �·1 : : : 0 ................................................................................................................................. : ••••••• i ....... j ••••••••••••••. ; • ••• ,s. •••••• ( ••••••• ( ••••••• j ••..••• j ••••••• ; ••••••• ; ••••••• ; •••••• � •••••• ( ••••••• j ••••••• j ••••••• ; ••••••• ; ••••••• ; •••••• .. HINGE AND DEPLOYMENT DESIGN, ANALIZE AND DRAW j : : : : j j l l l l l l l l �·� j l l , .. ,,,,,,,,,,,,,,,, .. ,, .. ,,,,,,,,,,,,, .. ,,,, .. ,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,,, .. ,.,,,,,,,,,,,,,,,: ••••• ,,l•••••••l•••••••l•••••••t• •••-:-•·••••(•••••••C•••••••I•••••••I•••••••I•••••••t•••••••)•••••·�· .. •••(··•••••r·••••••I•••••••I•••••••J••••••·�··••••
ORDER FRANGIBOLTS l l 1•1 l 1 l 1 l l. R�CEIYE �OL�S l.l l l l : .. ��������0:�:�::������:���:���:��::::::::::::::::::::::::::::::::::::::::::::::::::::::::::r::::r::::r::::r:::::r. �:r::::T::::r::::r:::::r::::::r:::::r:::::r:::::r::J�L::::r:::::r::::r:::::
.TESTING AND POSSIBLE MODIFICATIONS � l l l j l � l j l j l l j j.j j j l oooooooooouoooooooooooooOoOooooooooooooooooOo•oooooOooooooooooOooooooO•••••oooooooooooooooooo••ooooooo•OOoooooooooooooooooooooooooooo:oooo•••I•••••••J•••ooooi•••••••J• ooo�oooooo