space vehicle mechanisms · 2018. 10. 26. · marman clamp trunnion design r.901 10-32 xa285 lck...

__ .... - ---.._ : i

� .. / \ '·

Space Vehicle Mechanisms

/ �· '

I )

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

Naval Research Laboratory SV-Mechanisms Washington, DC 20375-5000

Mechanisms - Adapter/Interstage Separation System

Marman Clamp

• Load Path - Cylinder To Cone

• Requires 2 Ordnance Devices

• Inherently Redundant

8 Ibm Marman Clamp

Naval Research Laboratory Washington, DC 20375-5000


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)



Cross-Section Of Shoe On Rings

Scale 1:1

Gap .05-.08 inches (.08 " Shown)

Naval ReSearch Laboratory Washington, DC 20375-5000

(

.,,.,....-- --,, I

j :, ____ ___ )


(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



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) ·

I

Naval Re5earch Laboratory Washington, DC 20375-5000

I .00 :t .02

EE1

l_ .250 •

;,·-.\


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

;


H

D

D


7

tefnl I.N..IIS OMitllll U'ICIPim I. �"rv'H..IAI.,}f �� IOGI8 •• IUI'I"IoCI: IICJU)MCII 1211 UICI'OitOCS •

4., N


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

' ·l;,.,_ __ I'


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

' . � . ., (

SHOE

*6-40 BOLT NUT


I

I I· I

'T --... --./ ·- ,I


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



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


Mechanisrr•� - Solar Array Drive Assembly

Deployment Sequence:

Stowed

Rotation

Fully Deployed

SV -Mechanisms

10°

Solar Cells

'

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


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


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

63

---. - ]- ----

.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 ----...;

-A-,

Naval Research Laboratory

Washington, DC 20375-5000

\


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

s® e

�� 4.0


SV -Mechanisms


(i) � � . . . . . .

STOWED

Primary Components

• Solar Array Drive

• Hinges & Link Structure

• Frangibolt Release Devices

D ®

0 ·: :· •, .

·

DEPLOYED

@ D

0



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

. ) '-".


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


/�\ ! I \ J

--


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



• 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


'\

) I �

I

·_.


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.


SV -Mechanisms


Antenna Mast (G-1 0 Fiberglass)

Carpenter Springs (Graphite-Epoxy)

Note: Pin In Double Shear



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

0 @

0 @ 0

0


Mechanisms - Interstage/ Spacecraft Separation System

D

c

8 I 7 I

NOTES• \..I'I...ESS OTHERWISE SPECIFIED

1. S'-'lf"ACE AOUGH-lESS 125 J.AICROINCH£5

2. ��?��L�� 'gn�� I �� ... 5H��: EDGES

1} CHEUICAL CONVERSION COAT lAW UIL•C·SS•U, L2:). CLASS l &. PASSIVATE lAW OO·P·lS, TYPE I s. �!fii�,.��tl�I�M�u!�: �A��o-�

oJ. EXCEPT

SV -Mechanisms

b I s

---

�-llt-·>bO R:;r- 2X 0 .Obl ·j'v' ;;- v 0 .1 .. x 100· 1-.VL.._•PL ·�···;·" � �"'.t ,91 lli-}

m•

tl-150 I .750

f--2.10-EIJ

I

'" �""

..

I

I 2 I

RTV·II\

��J.___l ·> ----.__ , ': (.ss) (.61) • PL ....._ ·Q IL.s r ·'·

AR Clll'9

I

6

)

I '" '"' �"" � ..

·01

... Y· .....

, ..

....

.. �ICAliCJol

3

-��i20-42bA02·2·1

==':===::I 4 PL

RTV·II ADHESIVE

·S RVBDER, SIL ICONE U52012bA02 RIVET, ·2·1 100" CSK HEAD

•) f"ING[RS

·I HOUSING

P""'lfoi...W!ICIII -o

Mechanisms - lnterstage/ Spacecraft Separation System .

R

Catcher Fingers

SV -Mechanisms

Bolt Catcher

0.219 _...

Mass = 0.05 Ibm

t


Mechanisms - Interstage/ Spacecraft Separation System

ITl .&

Cup/Cone Piece Parts

-l• .llS·JaN:·za

If If! .olo®iA!a$1 UIL·S·774Z

Material: Cres A286 lAW AMS 5757

Naval Research Laboratory

Washington, DC 20375-5000

Mechanisms - lnterstage/Spacecraft Separation System

SV -Mechanisms

3/8" Separation Nut From Hi-Shear

2.00

I

0.69 1

2.50

2.85


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)


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



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


'\ I

)


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

" i \ 1\ I ' !


SV -Mechanisms


Solar Array Drive Sun Tracking

* Rotation Angle Relative To Zero Degrees On Motor Gimbal


A R R A y

R E s p 0 N s E

SV -Mechanisms


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)

I

I

I.

T=Osec END MAPPING

T = 18 sec (Example)

BEGIN MAPPING

TIME

=Mapping Naval Research Laboratory Washington, DC 20375-5000

(

SV -Mechanisms

Mechanisms - Solar Array Hinge Assembly

Solar Array Structure - Hinges & Link Assembly

'·


SV -Mechanisms


Solar Array Drive Motor/ Array Hinge Assembly

-

-

-

-

I u:rn.al�•·•--•�•au

I, lt.llt.tU.�.�.W_.cK'S,....,...#IAJDtii•\DIIC n.•Till.,..._....,.. . .,..oa,

I

I I I

I I I

I I

--- --· ---,--1------1

...... �. , , -

' '!Jo.CO.o"·l t"l .... � .• ,. - !. ·- �:!��"'==- --------1 I ..... eo ..... -.. .... -···� --�a;;.:;;.::-;--1------:-1 -; • "'-·-.(l>.os:..;,...:-,;.. I ---- --"--j

t - r;::::;;;; �- .-.. 1-- ... -: -

I I''''"' . T

Naval Research Laboratory . Washington, DC 20375-5000

(

0

c

SV -Mechanisms


Motor Male Hinge Sub-Assembly

JJO'li!::): Ul.J\.E5� arnESZ'W'SC. �i!C\�IEU:

l.tsuei!"'J>t:S;. �u�=:.s1� 1. R&\..40\1£ AU.. eua£::SAl.JD S�A2P �S I&'�IVAl.EMT

1'0,01�12,t..D.,.V..'I(

6

•I O�·ME'·OOI .. --·-·-


D

-

c

-�

-

SV -Mechanisms

\.


Solar Array Arm Sub-Assembly I

U0'1'1i�: �5� O'TllmlWISE �CIF&EO:

1. ..., • ....,, �u�� 'v,

I

t, ECi\.40\lliit ALL. SUU� ,I..LJ:) 8HA'2P EDGi:S &.QUIV.AJ....QJT TO ,Oitl CU.O MA)(,

5, JtJe.TAU.I!� RaZ'�IL•':5TD·o40,,E".CCEi�TOl.AIT II.LU.::�C!OJ.AA"TG:Pii!.ll-116'1!,

1---------q,'J'Z .. I

I I I I l--· -a ............ c...

��---.-------.---------Jr·

--�-�


(

\. --

D

c

SV -Mechanisms


Array Male Hinge Sub-Assembly

•·h•"La:.\ •l ....... .., ;.t .. u • ..:t."'" -:;.\)1.'-•��'•LD l· ·.� .... • . .....:� � .. -.. ·..r .... "V '1.. '12,., ... 0"11. t... .. \!) ...... ,.h ..... Su-o E:>.:.ll."'"

(a.,, ..... t,o..'t" TO) ,o,c., u .. :... .........

6

•uv�.ll5)(&o• �

'2.•2.01'2.

1.K�.n.,"!'.g�� i�IJ.LII-J£1 t}OCZ£ tEjtcAA�olol !., r.>·HF?. 'll'tZ..'lF}

I

t..C.'\."'J 'l .. ,.,·o' J 'L••S

1• ��-

....._C.t-)�•"",..'" "1 .. ,. -: ....... """"

-n.:r .... � r.... "\"'f•"'.t�U::O. ............. .,.

6

e,·

I

_,

r 1· . i·

L L


-

-

SV -Mechanisms


Top Panel Hinge Assembly I I

IJDr'l;�·'\lv.JII:-..� ... M-CoO'COI I. IU:I�.U.DOt..,.,�.._,.., ... ,, .... ,UVA-... •'-0

D

c

SV -Mechanisms


Top Panel Male Hinge Sub-Assembly 7

lJOnii'S: lJt.JUi"D!!t OTHiiQ.W�W. �!:•P1i;C! I, 15UCZ' ... .Aec; �o:J•!Y. 'l. l!ln.40/.;; ALL 8UIZE"5 .1.\JO :!�IZP BCG.E'$ G'QlJI\/,A.US:�

TO .ou' CZAr;»� • .!t, \w"'lo1'�\.'- "Pu..-r\o. NuT (l.,.� "U.,o,J �() • P'!:t· 0�1

R.OC.

6

r: ,--,---,--,------.-------r------ ·-1;

M'i1041. ...... �1';J _2-_«_, _1!>_-_.J_o __ �.WI� ·· '\"1 �'-- ��· 'l. e

�'l•c"\O L-'"1 � ..... , ........ , t..a ... -lta . ,':.•"".:,.o.iaf'·�-.. .. 11c.::U:C. �· DSI.t

D

c

SV-Mechanisms


Top Panel Female Hinge Sub-Assembly 7

UOilii":)� UJL.£S'i �.&IZWo� :50ti'C.tPo&:t: i. :>J�,:OA,c.;;: IZO.JQ!olt.JCii:'!o� �

"t, lllii:l·AOI'· ALl.. eucz'-::$ AUO 5H41Z'!? EOG�!. &'9oJ•vA.....-,VT 'TD,OS�P'-',AJ(,

£ IU�T"'U.. tJ:e�l5 P1ii1Z Lt'!.9�5�n Wli"H C�IIC. ..o....!t, R�TAt.JGo,

6

.& O.E'AlJ UJ��SWITW I�P.ZOP"f'-A'.cc,Jt-IOt..,TT·I-'Jl'a, ltJGTAU... lli':.CI;cj�P'fiTZ L4S�11C''I t.J•l� C::�K' HOUI. IZ;'J.AOV'.:a, TAt-)0,

!J, W�\.o �-""' .!,..,. 12 .... � P•t:�. \k,\ -=r::.o. �- O"Jl

[

[ 1-t-+--t-.... -.o-.... -, --+.,....-- �-...,-.�--m-1-------1:1"

S'2•109-cow ·� ,l'lillP\D�b .r�o--,.zuuc.. K -•�a l.Clo L..::c.. t 1-"�·•-,o.-s -1-""'__:_"'"'"• n-.... c-..,-l-o-e•-•-•u..,-0 • .-oa••-4 --It: Pl..Alli,"TIT�J.-f 1'50� '-AL•4Y Pl.AT.1TITAU1Ut,.t .150Tt1E' 'A.l.·4V


( \._

D

-

c

-�

-

SV -Mechanisms


Bottom Panel Hinge Assembly I I

IJOTE!S: U�SSonEJaVIS ':5P';C.IC::ti!'D:

I, f�TALL E!O-�,�ctz�$1WA�tEe5.\lJT':S, A'-JD Hl·LOII::: P'AS�� lAW �"!oO•P&·O•S.

I

'5100·"2.b O�·l.I.'E·OIZ.'�-01

1 ... %0Go-1"'-�

0

0 ,-1.:. 0

�CJ 1/" •I II

':-.. : : - • 'I :I II ,, ,,

0

e�e-n

�-��·0\10·1

LOS·M&•0\09·1 .StoCTIOIJ A-A

I I I

1-1- -1----l------1---------1 c

--- ---1----11--------11,


0

SV -Mechanisms


Bottom Panel Male Hinge Sub-Assembly

OOT_.-3: LlJL.6:"i.6 O'fi.IEIZWieG. 'ef"'G:CJ�I�O: I, 6UQ�ACCE. eouc:liUGSS � t, 15"""'11. AU..ISUIZA:SIUJD wtH.-..eP &bcJiil'� IE.�JVAI.Jiii:ur

'10 ,OI'D IUO � .!. I>I!>T .. Ll. "'-"TE NUT RIVET!; PEg_ I>..., !>!>O·PE.·0�7

!>ECi IOIJ C • C

.'l.;o�·.m 5ECTIO'-I A-A

__ ,_, . ., 7 6

w-·

,,.: ....--.--.--.---.--------.--- lt-l--��1�·--l:'=·!>=l=0·�1��=�=s�.�=·=v=•T�------t---------------------IL.


-

. J

[)

c

SV-Mechanisms


Bottom Panel Female Hinge Sub-Assembly 7

lt..OTE�: LJU..E� �G;.IZtiJI�iL�P&.::.IF•&O!

I, �\Jet:.AC.S, 2'�l..1i.S� I� �. 28'� Al..L et.JZ2S AAlO $-lAIZP �£.� O.J V-\_a.rr

'TO ,OIS G!AO p...tA'K,

&. CLS'At.J IUSE� W'IW I�J'CZOPVI... .A.LCOt-tOL., TT-1·1-&S.

6

IIJ�T� �� pg:� ..... s��BD., Woi"H Ceoc. HOJ!. � T,.a..U:!. • ..,, hl'!o, ..... ._ � ... ...::r ... '\"'" a.,u. 1. .. \.\ �c;o -�- O":a.1

J

_,

..s_l

I

r-or��--·�-�--,�--��-- ��-.-.-,.-,-.-.-,o-----r�--.-,�---------------�,-,1-.-�- �� "''"010�� >l�Po•'J


c

SV -Mechanisms


llaTL'I: uJ&..S."�:t.:�c:,�,m:

I. ��20..JCI,I.It.l�l't.!/. •• �AU..'&.IIIt .. N.IO�CDA·e�P.M&.��Ur

'1b .o•• rz.,.o ......... •• .,.., ... ,..,....,... Nil' QQ• p. ��I T"J"P& ...,,

A I#Pt..Y TIOuJ&a •r.o r:R:f ll"o.A u.Je�•C:AUT IMN JrM.•L·�o.

t;r .. ooo m---

Et-v-·oo

. . 1.

Hinge Pin Lock

5 . .

. 2


(

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



Frangib�lt Joint Design

Aluminum AI7075-T7351--...... w ..,_ ___ Titanium


SV-Mechanisms


Frangibolt Assembly I I I I + _I _I

" " =�::::.�==-� ... �..,"·�

-

G

-

-

-

-

lia&LQ-Ur;�&4o&LL.r.c'�T.UCo.riv-WIIAtuD.n ";,'fi>IC&t.�PT'·ao.ITO.�Oll�FUS,.

""''"'�"'···�

e•·.,..·Uo·•·.,

N·u&•O.•e•Oo

A� •

..... o., .• _ _,;,�--:·r-� . �·-······�

. ..... · � ·-·

-· -- -�· ............. __ Ho .. •!:l�•l t\u•·"""-- · ri"fl' fl' ."1

_, ...... � .. -.. �.! =-n ,�./

1.11 •••• (1.0. •• �, u 0

I

·••,.•·•• l•d.on� I' �• •·'"� "'"� n•·-

H

I•

........ 11""'!_'"'-"'-----1-----1 I� i.S�-7 :�::··

-� I I I • • I I I I I"


D

c

.'


Frangibolt Base Sub-Assembly

NO'f&S: UU\.i'��i!:aMee: t:sF'£.GIP•m: I. �� IW.Koml��:i> � 'l. le'aAO.ili:ALL.et.JQ:C5NJ:J�P6Q::iES�I".ALWU'r

,.0.0'5RA.o "-'A)(. S. �TALL I�EIZ'T5 �cz U�'!#e&:S"7 Wffi.IC:�\IC' HO\.£,

D't.A:>J& TAUcl.

. ,

-�·

6

. � . ·.

D

c

A -��- A

l>O;o,.c-----r-----�------,-------,-------,------,------.. ------o-----Jj��r:;;��V��"�'OO�Y�� SV -Mechanisms

·0 L4i'•OOI =-�

---'i� 6 :··--.-... -

:-\


D


Frangibolt Plug Sub-Assembly

IJO'T;�� LJu...e:'$0 O'n-4E�IAJI':C. 'CIOCJ(;::.IFoC.O; 1. �t..WZI='.t.G& �r..llii.s-s.1�

IJ, elii.A(>,IIiii: ALL..SlJt:Z'.ZS NJD StiASZP �CGE� li:Q..JI��T" 1'0 .01'31Z.AD MAK,

.&, llJ!aTAL.L IJJS�i2'T"5 AN M�'!)�o,�:J W1T\1 C� HOI....G., em.Ao...1lT..IJ....G•

A .APPLV T\OLUBiiii .C£,0 t:cl't" �t\..U t..LJe2tCAt..Jr lAW MR.·L-44010,

c

E

� I

r-r-.---.-:---.-----.------l'r,

Vl"f Off COOl

linJUO,-'l.AL.V OQ•A.•t1'fl/tJ ¢4.•ns c.ot.•·n.�•

!SW � H:!l•-----'

L��':.'.�.:· "§'·"' � A

�=�� A OQII_I_,III'

=:::i�1oo

.. --·-·

--r- ...

···--.--

SV -Mechanisms


Mechanisms - Solar Array R.elease Mechanism

Frangibolt Retainer Sub-Assembly

uc:mi:�: lAJU:'O!il O'THiilZIM�Oi' �PC�p1'1;'0:

1. OUW"ACG" e��n3( 1, U�,..U..�"o\ N..J0 &\A.2P'�:;,'5 lf�I�LZU'r

0 TO .O•O W.O �.

c c

OIC�.I80!:gg; �I.LVSPAC.Iii:O

8

�: I i SE.CTIOl-.1 A. A.

A

---e· ... 7 6

t��!i��i��-��·i��,OO�Y� •.ou•··�.!·�0Cffit4011

,.

.. --·--

SV -Mechanisms · Naval Research Laboratory Washington, DC 20375-5000

\ )

Mechanisms - Sensor Cover System

'

'

\

Requirements:

SV -Mechanisms

• Protect Sensors From Debris Contamination

• Repeatable Use (Due To Uncertainties About Delta-V Thruster & ACS Contamination)


...... \ I

COVER ATTACHES TO SHAFT


Layout Of Sensor Cover System

BEARING SET

INPUT CAM

TORSION SPRINGS ATTACH TO FRAME AND COVER

HINGELINE

BEARING SET

SHEAR PANEL-

PP5501 AND ACTUATOR

-,



Layout Of Band Drive & Cam

HINGE SHAFT DRIVE BAND

DRIVE CAM

IDLER WHEELS

SHEAR PANELS

LONGE RON PP5501 \.JI ACTUATOR

FRAME


SV -Mechanisms

.") I


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



RETAINING NUT

ROT A TING/THRUST BUSHING

SPHERICAL BUSHING

Bearing Set Detail

THRUST WASHER FRAME

SHAFT

BEARING SET DETAIL


I - '\

)


Labyrinth Seal Geometry

COVER EDGE CLOSE-OUT

HONEYCOMB CORE

THESE SURF ACES CONTACT

FACE SHEETS

0-RING SEAL SHEAR PANEL

LABYRINTH SEAL GEOMETRY

FRAME



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


1.000--.-

0.138

0.725

1.730

0

0.310 J SV -Mechanisms


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


/'

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)



MLI INSIDE STIFFENING

RING

BEARING HOUSING

FLEXIBLE COUPLING

PARAFFIN ACTUATED

ROTARY BINARY LATCH

LABYRINTH SEAL COVER

MLI UNDER

.030" THK PLATE


-- -'; - -·�


14---- 50 825 --�

Bl

AI OPEN

Aj TOP VIEW, HOUSING

0 280 �--� �--llof- 0 175

.020

SECTION A-A

.020

SECTION B-B

oOOS

o005

2 PL

Naval Research Laborat9ry Washington, DC 20375-5000

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


I 1.60

I =={

.·

,, 5 NOV 92


.15

StarSys RF-1035 Rotary Binary Latch

1.750

0

.3o -l l-

2.54 1.75 T

4X -.170 1HRU

1.75

.150

t 1.300

.375

1111111111111111181 �lt�� =� PRELIMINARY CONTROL DRAWING


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


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


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

\


') ) /

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

space vehicle mechanisms · 2018. 10. 26. · marman clamp trunnion design r.901 10-32 xa285 lck...

Documents