NASA Mercury Spacecraft Flight Manual

8/6/2019 NASA Mercury Spacecraft Flight Manual

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PROJEC TMERCURYFAMILIARIZATION

MANUAL

NASA

M_LNNE D SATE LLITE SPA CE Cl_AFT

ON_ DAY M ISS]ION

1 DE CEMB ER 1962

_ MCDONNELL

AIR FORCE, Mendle P ress, Inc. 12 /12 /62 900 (McDonnell A /C Corp.)


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'__NIL /. $EDR 104

_4s 4oc_zent is app licab le to Spa cecr aft No. 20 and its one-

day o_bital mission an_ supersed es basic S EER 10_-18_ da ted 1 June

I_ : _ )ga _ _11 4_e Spacec r aft 1 8-O r b lt Co _at i cn. _ h l s

doc,-_nt cover s Space cr aft No. 20 as del ivere _ bu t does not tn-

cl u ae c h a ng e s ge n e ra te d a fter d e l ive ry.

The purpose of Th is _mnen t is tO presen t a clear oper atio--1

descr lpt ic_ of the spacecraft systems _ laa _or c_-ponen ts. A can-

p a r l so m be t ween _ - / o mpc men t s _11,_. in previ ou s spa c e craf t

a ml th o se I ns t a l le a i n S p a cecr a ft No. 20 can be m a de b y t he use of

e a r li er i s s ues o f +.l_s _ o cw_e n t. Spa cec r a f t r, -- _ ered 2, 3 , 4 , 5_

6, 7, Ii, a n _ 14 a re c o v ered i n th e i Fe b x.,a_ y i_i i ssue o f

i 0_ R e vi sed i August 19 6 1 . Sp a c e cr a ft n,_re _ 9 , 13 , 16 , 18 a nd

19 are cov e r ed i n t he 1 Nove mber 1 9 6 1 i ssue o f _ R i 04- 3 Revised

1 Februa ry 1962.


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SECTION INDEX.

SECTION IINTRODUCTION

S ECTION IICABIN

SECTION IIIMA JO R S TRUCT URA L A SS EMB LIES

S ECTIO N IVEN VIRO NMEN TA L CO NTRO L S YS TEM

S ECTIO N VS TAB ILIZA TIO N CO NTRO L S YS TEM

S ECTIO N VlS EQUEN CE S YS TEM, L A UN CH,RETRO GRA DE O R A BO RT

.SECTION VII.

_SEQUENCESYSTEM, LANDING THROUGH.RECOVERYSECTION VIII

ES CA PE A ND JETTIS ON RO CKET S YS TEM

S ECTIO N IXPO SIGRA DE RO CKET S YS TEM

S ECTIO N X.RET RO GRA DE RO CKET S YS TEM

S ECTIO N XlELECTRICA L P OW ER AN D IN TERIO R LIGHTIN G S YS TEMS

SECTION Xll

CC _MMUNICATION SYSTEMSECTION XlII

N A VIGA TIO N A L A ID S

S ECTIO N XlVIN STRUMEN TATIO N S YS TEMS


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S ECTION I

INTRODUCTION

TABLE OF CONTENTS

TITLE PAGE

Description ................ .................................. .1-3

Cabin ........................................................ ,1 -5Major Structural Assemblies .................... .1-5

Environmental Control System ................. I-5

Stabilization Control System ...................... 1-5

Sequence System ....................................... I-6

Rocket Motors ............................................ 1-6

ElectricalPow e r AndInterior Lighti ng System ............................. 1-6

% Comm unication System. .......................... .1-6

Navigational Aids ...................................... 1-8

Instr umentatio n System ............................. .1-8

1-1


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NNELL SEDR 104

SPIKE

P YLO N JE 1T IS ON R OC KE T

SP ACE CRAFT ADAPTER

RETR O ROCKET ANDPOSIGRA DE R OCKETS

ATLAS "D " MISSILE

FM18-43

Figure 1-1 Spacecraft Prelaunch Conf igurati on

1- 2


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aqO_ONNm_ J. $EDR 104,

I. I_ ZROI UCTI ON TO PROJE CT M_ CURY

z.,z. immmzm z oMercury Sp acecraft deserlbe _ in this m anual is des _ for a

Qne-_ sy earth-orbit ing mtsslcn. _e . _eatc = is an extenstc a of _

three-orbi t an _ six- _bt t flights of the Mercu ry ve hicle.

_e 0he-Day Sp acecraf _ is s_.41 -- tO the earller e_ tlo ns

:eas _t_ 7_ in ches in _Ltm ster a t the v _lest part of the sp sc ecra _t

and 11 5 inches (See Fi gmre 1-2) fro : the hea t shie ld to the ena of the

recovery eyl_ r. _he space craft shape res _les a _mmeate4 co _e

topped by a sho rt cylind er --_ re topped by a shorter tr uncat_L cone.

2he f i rst c_ c ont a i ns th e a str _ ut a nd h i s m_p crting s _ _- _ - , th e

Cyl-_-_l,_ 'r co n t a i n- th e re covery al4s and para c hut e s f c_ la._4._, the _ c c_1

c o _ e Is the 8 n_ -- falr _ whi c h c c _$_ L_ s T _ e bic o ne -- _e mma 8n _ h u _ is on

se nsln g e l e me n t s plus the drogu e c hut e.

Str _lin g the _ t _ -, f _ ng is a t r lm_ u l ar- _ mpe_ tr usvork of

s t eel tu blng f c a _ In _ the es c a pe to wer. T wo s o ll _ propellaD t r ooket s a re

mounted on top of the tower: one escape, _ _ et t l sc n .

At the base of _ spacecraft , a heat sbtel _ of sh latl _ _lass f_ber

composi tion 10 a_tached to _he I mpact _ s kirt. _ _ ,'_.le_e as_m b _

i_s h el_ s ec urel y to _ s pa c e c r a ft un ti l I _. _ * r e_ ro c ket

mo t or p ac k is a tt a e h e a t o the heat . _ l e l _ end is _et t lsone d af te r r e tro -

_ f i r e.

f i r st cone I s a _ oub le- wall stru ct u r e, the inn e r wa ll for min g a

pr e ss u r e ve ss e l ( th e e shin) a nd th e out e r sh e ll for _ a h e a t - _fel_.

_ h e fo ll ow in g paragraphs b ri e f ly des c r i b e th e m at e rial c o ve r e_ in

i 3


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NNELL SEDR 104

_a. < _w

-i

FM18-46 ,

l , ' i gure- 8RollAxisBlo c kDi a gr a m

,%16:


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"_WO_NNi/.L SEDR 104

the right. _e four bas ic ope rations are a lavl_ , repeat ing, mode s_Atch-

ing and torque se it_Lng. Da ta flow pe rtaining to the iad tvid_a! Yaw,

Ro ll and PA tch _ - _e ls is ill ustr a t e d i n Yi_ es 5- 6 , _- 7 a nd 5-8. In

ge ner al, the se d Aa_ are str aigh tfore ard and r equ ire no e_la n atl c _.

Howe ver , t h e me t hod u tili z e d i n d e r lvi_ l _ t i on al informat ion is un ique

to a degre e and warra nts the fo llovA_ d iscuss ion .

Th e p i t c h _al (ver t ical_rr o ) I s pre c essed ec _tinuousl _.

t h e orb lt alpha s e of T _ e n o rmal mssl o n _ s o T _ a t t he s pa a e craft"l o cal

vert ic a l" re fe ren ce rev o lves360 degrees _ m_ n g e a Qh c _ b l tal _ / _ le .

The _rro slaving pr inciples wh ich p er mit DAre ctioaal (:raw) lnfo z 'm _on

to be der ived are as follow: After t-_tial slavi ng an 4 settling of

the ro ll -,_ pith loop s_ the ASCS controls the sp acecr aft to the e_

p itch a _titude _ an _ to level ro ll attit :._. _nitial_, after sep arat ion

s_l s pacecra ft turn around , s_ yaw erro r (as great as 10 _e gr ee s) may

exist d _e to d_ e c t _ -- _ dr if t dur _ boost . Slue e the Roll _*_ of the

v e r t Aes l _ro i s th e _ --e r _=_m_a l , _I s a l i g _w nt of th e s p a c e c raf t

causes the Roll _ -_ o_tp _t to e _nta in an er ror co mponent d ue to _he

c on s t a nt orbi ta l (p itch) angular r a_e. _us a ccm p a r l s c_ of _ h e Ro ll

Ho rizon S_ - -- _r end vert ica l g_ro ro ll ind Aeati_s will pro vide an error

sig n a l produc ing a ro ll _al torqu ing rate . _ 4_s to _ qu _ rat e _h ieh

Is a d ir e c t f tm c_ tlc _of y aw e rr o _ Is u se _ t o s Xa v e th e y a w _i_ b aX o f thed'_ ',-e _' ttmml _., ,.

_ aoth e r a r e a + _ t war ra n t s dAseuss i on i s _ h a_ o f _ orqu e s e l tch l ng ,i.e.,

th e thrust outlart _ th e Reac t io n Contro lSys t em i n c _ unct i_ n wi th th e

v a ri o u s mod es of ASCS op e r a t i on .

5-17


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_NnmAa . SEDR 104

5-10 s e rv e s lw in la_zo4a etlea to t he t o=q _e u-=_te l_lag l_-

Ms vlo r of _ ABCS . _r asz IIm eoasezw a+,lono f eoa t_ol I_=e I, _e 1 _-

havi or v a rie s 8 _e ord l n8 t o th e A BC8 mod e eppropz _ st e a t a gtvea t Jn e . A

=o- ea lle4 " ph ue- pl a n e" plo t of ea _ rat e v s. an gl e i s sh o gn i n t h e

z_A_t c order of F:L _ure 5-10 a _aee mt to a _tea l P i_eh tl le-htsto z7

for t Me "Orbit" ao4e . | ,_:re nt J _C8 4es lga lx_a tt s a plu s or _ 5 .5

de g r ee os e_ll*tlo= aIKm _ t h e n _ o r b i tal &tti1_ :4 e, hi e h i n _ 1 8

reference dto th e Ho r 1 _ m 8 _ _---- _' s e a me d " Ho rizo_ t s l ". _ h e os e_11 * t ion

is nonsiunso l d a lb ec au se of t he dAs ea n t / nuous t orqu e _ n= gz em ; pl te h r at e

is a s _ ,* _e r ave, 8a4 _:Lteh aagl.e s sa _t ooth , bo t h hs vl ns a e hsra _ t _ zist le

p e r i od of 2_ 0 s e co n ds . Poz _ on _ h e ph a s e -pl a n e, th e = Orblt " mode

osetllatl oa ls & Ipmtl_ drift from -_._ deg ree s _elat tve _lteM aa g_e to

+_._ 4e sr ee s relat ive _ite_ (.39. 5o to - _8.5 4 esr ees , re fezeaee 4 to t rue

_). _le &r _ lasts for _te_v o_e -_-:f-_ert _t of two a la -

_te=. I rae_ the e rro: _es +_.5 4eS zees , a 1 _ toz _e _A se ea s e= the

rate to z _ez _e_ , _a e ze _ the se em _ h=:_-_"A04 lS s]_mt drl A'ttag

=l_l_r _ ze ro to .- _-5 d_pree s er _-or.

As a aotlu _ ez a _le , Z__ torq ue_ sW ZteMta g, 7ts uze 5-10 s Mov s the

" _ etrosr a de - HoZ _ "t _r q _= l _e l _a s e- pl aae ,IA,,gzm. Xa t.l_ c a =e _-

t orqu e no z sl e s ar e ut il : _e 4 I nst _ a4of th e 1ov- _ orqu e nossl e s _ ht e h v ere

a d e qu ate to e oatrol t h e Ke nt2 e o=blt os ei l Ast i on. A s erie sof

att l_ o _e

rep e st e =s ec tor s _A t e hes a n _ rate- sFropl e koF f s ee to _ sv l t e h e s are

us e 4 to d e_I n e st e pllk e bouad arle, v l th ln th e ph ue- pla _. A tTp le s l

e_zto_r l_ s hova to llS._mt.'_te t_e mot imz rem_tt_ _ a lar ge d i_ar -

hen ce _ orqu e vhJ Ae I n _ z i s nod e. b _e n th e spa eee_ mot ion r eau lts in a

plt_ h r _ t e v alu e abo ve "_d=e1-A sht-h a n4sta i r st _ p , h l gh n e_tive _ oz _ lue i_

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A S C S A M P -C A L

NOTEONLY THE YAW MI CR O SWITCHES AND AS-

_ S OClAT ED C I RC U I T RY Ai _ S HOWN. ROLL

A ND PI TC H A RE SIMILAR.

T .I" T t[_ SWITCHES SHOWN IN STICK NEUTRAL PO-S IT IO N LO WTORQUESWITC HESCLOSE FIRST.

JJ _ RELAYS DE -ENERGIZED I N FBWP OSITION.

' IHIGHI-

_RCSSOLENOI DICONTRQL _ADvE (TYPICAL)J I RCS T HRUSTCHAMBER (TYPICAL)

,FMIS-131

iFigur e5-9,A.S.C.8.F lyBy W ireControl

5-19


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_Mo_NNELL SEDR104

applie d u n til I _ 1 espacecraft a t tai n s a ne gativ e r a te and r ota te s i n t o

t h e " no - to r q ue" regi o n. Th e i n verse o cc u rs if the retr o r o c k et th r u s t

ec ce n trici t y o r o th e r &'Lsturba n c es forc e the spac e craft i n t o a s lt_ a ti on

ea 111 _ f o r p o sitive t_ t st. _ he ne t e ff e ct o f the torque - swltc h i ng l og ic

sho wn is t o mR1n tai n r a pi d a nd reliable c ont r o l d ur_ th e i mpo r t a n t o pera -

tl c _ o f ret r og r ade fir_.

Othe r mode s o f ope _Ltion requ iring torqu e switc lLtn8 log ic ar e "O rien-

tation" and " Rat e Da_ 0e 3.". D uring o rientation m ode b a th h igh a nd lo w

to rqut_ is ut ilized to ro tate t h e spacecraft t o ne w prese t a ttitudes.

Both h i gh and low t o rqu ( _is a ls o a pp lied du ri ng ra t e d a-_er mode b ut

rate _ r r o si gn a ls E_e ne e d e d a s a b asis for switc h i ng l o gic. In

this ca s e, t or q ue swltc 1 _ n g bo _ d arie s are h o riz ont al li n e s on the l _ase-

pl ane .

2 - 11 . U NITS

5 - 2 .

_ h e _lifi e r Callb ra t or u n lt ca n b e "fu n cti o _s_ F" d ivl_ 1 i u t o

fo u r sectl_ Is . _ le se f u n c t i on a l sec ti_ I s are s lavl uS , repe a ti ng , mode

swit_ and. t o rque sw_tc_.

5- 1 3 . G R0SLA

_Is sect l _ co_te_ s - - T. lif le rs and s_ n e t wo r k s w h ic h a ccep _

roll a _ld pl1 _ _ n _tl o _ fro m +_ HGl _l_zon Sc anne rs s_ gene rate curren ts

to torquer s in the att itade gy ros. _hus , upc_ _._._ ._ fro m an exte rnal

t:L _t_ de_Lce_ the Gyros Roll , Pitch and Ya w 81mbals are al i_aed with

corre spon_11_8 _Lre ottons in , or perpend _culsr to the or bit plane. (Ref.

Para .5-20


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lifCDONNEL L .: _SED R 104' .

RETROGRADE _=(PITCH AXIS EXAMPLE):

I "5"5 _I 0 . 0 I

8.0 _

m' j_+5.5

Ai.e DEGREESj

ORBIT l

TYPICAL :TIME HISTORY (PITCH).

:o5o ,_1 --_o5o ,_. , _ r---L_ oo_T.o. _, ,PUSLE IN SEC._ _ i, _ .65 ...... -i_I I-'---24OSEC. t1 *8 o ._7 _, o_.

+5._--I _,"_'A' -,_ , :-A ._ =0 .252 _!' DI 0._ 7 , !. I

..... l +A +A. _" *e, b.755 .1 ._-4 I .

- :A e . [ )E GR I _ES yS EC.. FMI8-55,

Figure 5-10, To rq ue Logic Phase Plan e Diagram.

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__R 'LL SEDR104

rJ _e re pe at e r s e cti c n is a gr oup o f serv o - me ch a n ism s ( f our i n p res en t

d e sl gn , incl ud i n g _ o f! orp it ch ang l e repeati n g). Attit ude g yro outpu ts,

wh i ch a r e re ee lv e _ at _ e calA br at or in propor a t io n al a r "a n al o g" f o r_,

are amrp lified and use d to dr ive sha i_s _nich se r ve as ro ll, p itch a nd y s_

signal source s for bo_ intern al (torqu ing switching) an_ extern al (d isp lay

an _ teleme'_c 'y) purpose sJ. _e on -ofT reaction contro l of the sp acecr aft

mA_es it des ir ab le to _Lse conduc tive sector s on the sha fts of three o f the

repeat er s. _e secto _ serve as att itude- l_vel re ferences f or torque

5-15. MODE_ _CTION

_is s e c t i on o f t h e calib r at o r establishes the proper a tt it ude a n gl e

bias, t orque swltc h i_ s t at u s, a nd inte r l ock si gn al s corres pc_-_ to the

ASCS mod e c_ , _ , _n_e dby e xte rn al d e vic es .

NO_

_ he s u m of a_ s u ch ex t e rn al _evlce s is, for _ SCS

de sig n purpo s e s a " e a s te r se qu e nc er" w h l ch c oo r d i n ates

a ll au t o ma ti c f un cti ons .

_ h e mode -s wlt ch i n g sec1_ion u se s c_.act, s o lA d - s tat e s witc h i ng ci r c u its.

Altho,_h these cireu it_ cont ain m.,_yt r a ns i s t ors , _i odes , a nd othe r elec-

tr ical ecmpone uts, th_j are of a class _hat is no t er itieall_ de pen den t

upon ref e re nce vo ltag e or _e_ p e r a tur e lev e ls .

_e tor qu e s v i_ h _1_ sec t i on c on t ai ns t r a nsistor a nd diod e el r c u lts

_5 - 2 2


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" __J /U_i ' /.i. SEDR 104

sim ilar to those in the mode-s witch i_ section. Torque s witch ing circuits

re ceive the step- funct ion output s of the att itude gyro repe aters , plus

_e outpu ts o f th e ra t e 8_r o s . Th e la t t e r ( r ate) sig n als c ome fr o m s ect o r

s wlt eh es r ep lacing T_e us ual p r o po r t i on al ra te i_r o p ic ko ffs. Us_

th ese step -wise _ _- _ e atl on s o f at t itu d e a nd r ate c c _ 6 1ti on s, alo_ with

the _le switchi_ sect ion ou tpu t 8efin ing the cur rent pha se of the

missic_ "_ecisicns" are m _ which re sult in ene rgizi ng of th e alq_o-

p ri a _ e Re acti o n Co n _l Valv e s .

_'_._e a c c e l e rati on s wit ch is a he r met ically s eal ed I ns _ n t. q _

b a s ic me ch a n _m c c nsl st s of a ce ntr al_ l oc ate d mess support e d b y a c an -

ti le ver sp ri n g. _ h_ ma ss is _ by the visc ou s s h ea r acti on o f t h e

f l u id w h l eh fit!. t h e c ase. Swi tch a ctu ati on is ca u s e d by t h e d l sp lae_ a e n t

of the m ass element . An Acceleration fo r ce of .O_g, in the ax is nor ._

a nd i n _ he 6 i r ection awa y f r om t he ba s e, is re q u ire d to cl os e t h e ci r c u it.

Me_A-_cal stop s are _ovAded to r estrain the me ?_-ntm an_ to pro tect

e _ a i ns t _ when s ub _ e cte_ to exc e ssiv e acc el era tion.

_ h e f unct ion Of the attit ud e gyros (v e r t i c al and di re cti on al ) is t o

6 et er ml n e a tt it u 6 e a n gles betwe en a se t o f fi xe _ a_s i n th e movi n g s p ace-

craf t an d T_ ref e re n ce a_es which are fixed in the orbital plane bu t _ic h

a r e _ wi th th e loc a l v er tical. Both attit u de g y r o s a re "fre e " g yro-

sc op es wi th slavi n g ca p a b i l i ty . A m e - , - Is i neorp _ t ed f o r ca_ .z_ an _ f o r

el ec trlcal sig n al (syachros) outlnxt s which &ef ine the at t lt u _ e

5-23 .


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_MC_NNELL SEDR 104

of the i_ ros vA_b res pect to Wo sut _J _r l_rl_aa lcul a r axe s. _e

sttltude ID Tos possess unr e str icted nechaatce A t_eedc m in th e ou ter

sz .t.s sad _.+8 3 (a tn Am:) of :e ebaa Aea l _- in the _ --e r exts. Zt

is aote4 +_-t th e deg ree o f _ treed _ do es not aeeesss rtl_ z_ 'le e t

the at tlt-_ies l _Lsslble by amlttslly sl;ee _ the s]p ae ee ra_ % in oz _l_.

Due t o l ta its ttoas in _be Hor tson 8 _--_r s _t_s anq l the repeat e r s ec tion

of th e Awplt tter r _S. tbzator , asD sal eoat_ l o f the _ s lued b e

ls a.tt ,_ to _.+3o 4, , z'o ll a4. ]ru _ _ d .t_ _.+3o of th e -1_. .5 o : it, eh

at titude. H_m ve r, _ e_ot];_m t aslftm e tton , ez eee41a& these lJ_ ts

not pz. e ,,_S.t ee the success of a alsst oa . Xf t_e se l tmLt M are ez eee4e d,

tt; ls z _c(ume s le4 t_lt the _ ru rAl;oh be l _la _e 4 in the _ lX)S_tton. Xn-

l_t _ _ ts are ]A_ volt J _)0 _s st_ 1.e l,lu _se ( _ro ao_r), aaa

26 wlt , I_o e_s (m _o aaa tor que aotor).

.zg .'_he Att itude an4 l _te Indi cator is moun ted, on the upper portlon of

the Natn Inst_ t Paz _I. '_he _adlcator pro _s _ ta41 _at _ns of

S l_e ec ra_ Ra te aa _ At t ll: _ i n "theTmr , Pitch sa4 Boll plaaes. The

att itude i adA eat orssz _: drl ve_ _ _ h e a t_ l _ x d e 8) - _ os _n ohroo ut, is

(t_ the A_ l i_l e r Ca _ Ib _ to r ) . _e &t t i 1 _ l aaA ea tors are osl l-

brs te 4 to l a41 cate _:_e &_t l t ud e_ lt _In & _ of + 180 e x ce p t f or

_e w _al_M -_ _ la 41 _a 1 _ 0e, 80 , u 4 2T0 i n a c l oek . lse 4 1 r ee t l o a.

_e rat e poz tl o a of .tb e la d leat or I s _r l ve_ by th e al nl at _re rst e t r e a s -

a- ee rs . Th e r a n ge o f =:_e Iz_ Aea t l on i s 0 to + 6 / see oa4for a 11

5-24


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_NNELL SEDR 104

three iaAt_tors . _e :_ 11 rate in Aioa t_r has th e a &litio_A r_a_tlit7

of _e tag exter aaA_ mr A'_ebe_t o a _ o f 0 to l_/s ee . 4, , ord e r tomonit or re- ent_ r zo ll _ste.

Th e z a te gyros _e z _ or m e l e ct rica lc i rcu i t sv l t e hln g func ti onsa t

8_eel t l c x_t e s o f 8 _Lr vel oo i 1 _ abou t 8J _8 x ls 1 _e z _a d i o- 1-_t o t h e I_ 8e

of eac h un it, re_erz e d " _ as t h e "_ .- pu tax i s" . Ra t e _ s are us e d. i n t h e

_pt tch , rol l sD _ _ axe JD, :espect ive _. Bach z _te _ e ousts ts of a high8 1 _ r o t or , nounl _ I n a gl m_ ri nK , i n s uch a n m_=e r t hat i t is

to 3 pzeeessabo ut _e a :Ls on _ (the _t 3mt sxls) which is l _dtcu lar

to th e s p in axis of the ro tor . _he o_ s lsn a_ ar e sen era te_ by th e

not ion o f _i_ r s, at tae]_t to th e _eA r ing , _ acro ss th e con tacts

of sector n4.tches. X_ t ]power r eq_tr e_eat s a re se t by 11_ v olts , Ij _X)c_s.

Srm=

_-_ . sz_ _x_Th e Rea ct i on P ..,o _,z_ ',Lysten is use 4 for s_meecra ._ Fmr , _i t e h a n _

o lI con tr o l. The 8 _st, -.ut ili z e sn lt roK e n 8 u pr ess ur e to ez_el h _

gea _e roz id_ _ a bA _L_er in to the _ hz _st elumb er ea_t beds. _ h e

_A_ hten _e _ t e bm_ _zo_ce t_u,t by de oca _ o s_ n _0 %b _ os e n

_e ro zi_e ( l _ j02) ._ h e _ . _s_e n1 8 d Avl d _ I nto thre e d lffe_e n t_ or tl ons .

On e _oz_ion is for e_t_mtt e eon_ol (ABe), one for n auual con tr ol, an_

a r es e rve fu el mt e_ _ be u tilise4 dn x_ag th e z_-ent _-T pha s e o_ the n isslon.

_ h e m 11x ma tlea Ts te m 8_S t h e na _ ua A _ rs _e_ a_e b_i_:_y f_4=43m. W4_ _hthe

e_eept lon o t th e neth _ us_t _o _ the t _Aovof Fuel to the thru st

5-26


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o \ __", 'o _._

N

zz '

FMt8-3A

5-27


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_' ;VICDONNELL ]SEDR 104 i

TOWERRiNG INTERL OCKRELAYS ALSO =NERGIZED.

DD'ToW PR RING INTERLOCKMUST BEE NERG IZEDFO R JET=TISON ROCK ETFiREREL AyTO ENERGIZ E.

FMI8-121 A

Figure 6- 2 La unch Thr ough Staging Bl ock Diagram

6-4


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M_._ONNI II,.L SEDR104

Re lay . After 20 seconds , power will be applied throu gh the con tacts

of the Towe r Jett iso_ 20 Second T ime De lay Re lay _o ener gize t h_

To wer Se p a r atl c _ Bo lt s P o wer Rela_ and t h e Tow e r J e tti s on Wa rn i n g

Li gh t Relay (2 s e c . T. D. ). _ h e Tower Se p aration Bo lts P ower Rela y is

armed by both +h_ Main and Xsolated DC Squ ib Bus through the Squ ib _m

Seiteh. When ene rgized , _h_ I solated _luib Bus power fire s Wo o f the

five squ ibs (2 bol ts) and Main Squ ib Bus pover fires three of the five

squ ibs (3 bol ts. _he Tower Ring Znterlock R elay will also be ener gized

vhen the To wer Separ ation Bol ts Relay is ener gized. As the three seg-men te_ To wer C_-_. R ing separates, the _.h_ee To wer Cl ,w_. R ing T._mtt

Switches return to the no rmal pos ition an_ ,_!nw Iso lated and Main Squib

Bus power through the ir c ontacts. 'l_e Isolated Squib Bus po wer ener gizes

both the _rgency Esc ape Ro cke t Fire Re lay and the Emergen cy Jettison

Rocket F ire _l_ y, _tle the Main Squib Bus power en er gizes both the

Escape R ock et F i r e Rela_ a nd t h e Je ttison Ro c ke t F i r e Re lay. As the con-

tact s o f t he Em erge n c y Jetti s on a nd Je ttison Ro c k et Fire Rela y s a re c on-

n e c te d i n p ar a ll e l, e ithe r rela y _ill fi r e all s q uib s o f the Jetti son

Rock et f r om t h e tw o _i_fere n t pove r sc_rces, m_e _rge n cy Esc a p e a nd

Escape Rocke t F i re Rela ys a r e ec n nec te_ i n t he ia en ti ea l same _n er a nd

will fire 811 squib s o f th e Es cape Rocke t fr om b o th pover sou r ces .

P ower t o e n ergi z e t h e _r g e n e y Jetti son a nd J e tti son Ro c k et F i r e Rela y

i s r ou te_ t h r ough t h e .2g _ us t Relay wh i ch i s e n ergize_ t h r ou g h the S p a c e-

cr aft 1 Seco_ _-_ Del ay an_ Thrus t Cutoff Sensor. _n e .2g sensor p lus the

1 Secon_ Time Delay Relay alloys the Tove _ C_a_ D Ring to separate and the Es-

cape Rocke ts to fir e separ ating th e tower i_cm the spacecra ft v ith the Jetti-

son Rocket un fired . When t h i s i s a e c .- _ll s hed_ t wo e l ec t r ical d i sconn ects b e

t v ee n t h e t o _ar au _ t he sp a c ec ra ft are sepa r ate d a nd r e move po wer f ro m th e6 - _


175/365

_N_m.. SEDR 104.

thre e Tower Sep aration S ensor R elays. _aro _h the d e-ener gized No. 1

Tower Separat ion Se_sc_ Re_, _e green JETT _ 1gh t on the is le-

light panel 111_ ntns tes. _mm the to_ an_ the spa cecra ft sepa rate _

the No. 1 an_ No. 2 Tover Sepa ration Re le_ a re de -ener gize_ s all_

pcver to ener gise the No. 1 awl No. 2 Ma4, Chu te Sys tem Ar m 2 Seco_t

T ime Dele_ Re le_ . After 2 se co nds de ls _ t the Ma:ln _te Re] _Fs az'm _

the 21 ,000 Foot Ba rosv itehe s and _he M ain Chu te Delay 2 Second _mA

Delay Relays. After two sec onds , the 10 ,600 Foo t Baros vAtches are ar med.

_he power c ircuit will ho ld at the s e _ o poin ts m_t_l the spa cecraft

descends do wn throu gh the 21 ,000 foot range , at which time the l and ing

se_e is I n _t la te_. Re fe r tO Se c t lo _ VII o f _ s _m,_.

6 - 5. _ smas_

6-6. z=scazl:_ow

Sec o n d _ is i n iti a t ed by sus tA 1- _r en g ine c utof _ a t _ ch

_he Space craft Ad ap ter Bo lts are f ired, p roviding ac celer attc_ has decayed

to .20g. _e three Po sigrade Rocke ts and the fou _ exp losive electr ical

d i s c onne ct s a r e f ire d _--_ l late_ af ter t h e bol t s a re de t on ate d a n _

r es u lt i n s p ace cr af t s e p a r ation. Sp acec r a ft se p aration is sens ed a nd i n i -

tiat es f iv e secon d s o _ r at e d_ -pI n g whic h Is follo we _ by orb it o _ i ante-

tion in _a l c h t h e spac e c r af t r o t a t e s 18 0 o de g rees a n _ s e tt l es i n t o a 3 4

cr b lt a tt lt u _ e .

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IICDONNELL SEDR 104


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__m_l . SEDR 10 4

6- 7. O PERATION

At appr o_m - te_ y 28 5 sec o nd s after la u n c h , se c o n d s t a g i ng w l ll oc cur

(See F i gure 6-3). A t this tim e a 2 8 vo lt d-e s i gnal fr om the mi s sile

r ill energ i z e the Su e t al ner En gi ne Cu to ff Rela y . Wh e n th e thrus t d _o ps

b e l o w .20 g , th e .20 g Sw I T_ .hin t h e _ ust C_o ff Se nsor clo se s . Power

is then s u pplied through the Spa c e c r a f t Se parat ion 1 Sec o nd Ti me Del a_

e nd S us t sl ner Engine C _ t o ff Relay s a ft e r the 1 Sec o n _ Ti me Dela y t o

energ i ze th e Sp a c e c raft Se p a r ation Bo l t s P o wer a n _ th e Spa c e c raf t Se pa-

r ation Wa rning 2 Seccm_l Ti me De l a_ Re l a y s. Th _o u s h the energ i z e d con -

ta c ts , power fro m _he Ma in an _ Isolated Bus f ire th e Spacecraft Sepa-

rati on Bo l t s . A l s o , Main Bus power i s s u _ pll e d _ o ugh the Warn l ng I A_ h t

Ti me Dell7 Relay to _11,_4 ,._e the red SgP C APNJL E sequen ce L_ht on the

Le_t H and Console . When the tr i-se_ente _ Spacecraft- to-Adapter C_ --T.

separ ates , it allo ws the Spacecraft Adapter Ring v4-tt Sw itch to

close suppl yl_ power to energ ize the Po siErade Ro cket Fire , _or _ency

Pos_r ade Ro cke t Fir e an a th e Spaeecraft _dapter Di sconne ct Squ ib Fir e

Re leys. _ he M ain an_ Isolated Bus ses s, pp _ power _h the ener _zed

con ta cts of th ese rel ays to fire the Po sigr a_e Ro cket s and the four

Spacecraft Ad_pter E_losiva Disconne cts. _e Pos igr a_e Ro cket s create

suff icient thrust to separate _he spa cecraft fr om the adapter. _e

allows the eh,.ee Spac ecraft separa tlc_ T-4_rlt _t_he8 _h_h 8re atta_

to the retro gr ade atr _ps to close. Power fro m the Iso lat ea Squib B us

fl o ws thr ce_ h th e c los e d eo nta e t s a nd ac t iv at es th e _ i Sp a c e c r a ft Sepa -

r at i on sena cr Relay _nich ext l_uishe s the r ed m_ C AP_F_E se quenc e L_ht

-_ _l_,--_--tes the gr een _P C APSULE Sequen ce L_ht. Power thro ugh the

6-8


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MCOO NNmLL $EDR 104

the r un-ou t of the 60 second t_._ del ay the Retro Package is Jettisoned.

_he Retro Pa cka _ separa tion is sensed and re sul ts in the separa tion o f

the th ree Be t ro P ack ag e E l ec t r i ca l U_ilic a ls.

6-1 o . OPEP,ATIO_

The Sat ell l t e Cl o ck Retro F Are S wl t ch i s ar me d by _ In Squib B u s

p ow er _ h ro_ h t h e Spa c ecraft Separa ti on Re la y c onta c ts (See F i g u re 6- 4 ).

Wi th the Re tr o Del a y Switc h i n the "NO RM"pos ition and the Retro F Are

Switch closed by an y of the three pre vious_ men tioned methods , the Retro

Ro c k et Se quen c e Ind icat o r Re la y is activ a te d _11,m_ lat I D_ t h e green RE_R 0

Ind ic a tor Li g ht. Wit h t h e Retr o Delay Switch in th e " IN ST' l _ Os itio n ,

po wer i s s u pp lie d d irect_7 t o t h e c onta ct o f t h e Attit u d e Per mi s si on

Relay No. i by-p as s i n g th e 30 s e cond d el ay. _ he astr onau t ma y _,,_11y

s t ar t th e re t ro se q ue n c e b y p ressi n g the Ret ro Se q u en c e Switc h on t h e

l ef t ha nd cons o le w h ich _1_ e n ergize th e _r g e n cy Re t ro Se qu e n ce Relay

a nd all o w th e no r_ =1 se q u en ce t o b e fo_1 o we d . Th e Retr o In t er lo c k S witch

in th e ASCS Ca li b r a t o r closes allo wi n g po wer to f l ow t hro u gh t h e Em e r -

gen c y Re t r o Fi re No . i Relay and energize t h e No . i and NO. 2 Attitu de

Pe rmis s i on Rel a ys w h e n the spa cecraft is in th e p ro p er pos iti on f o r retr o

r o c k e t firi n g. The re d RETRO ATT Teleli g ht is switche d on whe n the Retr o

Ro c ke t Se qu e nc e Ind ic a tor Re l a y e ne rgizes a t the start o f the Retro Se -

q u ence .

Nor mal_7_ the A ttitude Per mission Relay ex tinguishe s the red REPRO

A_ Te l e li g ht, 111,_-_ n _tl n gthe gr een l ight a nd ener gizi n g the Retr o

Sig n a l La tc h and th e Retr o Ro cket F ire R e lays. Po we r fr o m the Is o late d

S_ u lb Bu s i s n ow ro u te d thr ou @h th e Retr o Ro ck e t F ir e Re lays t o th e

6 - I 0


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__NIki SED R 104

]_tr o Roc ke t s i n t_ .. firi ng first th e Lef t ( No . I) Roc k et, af t er a

".) second time de lay the Bo ttom (No. 2) Rocke t an _ 5 _conds late r +:h,___

1_Ig h t (No. 3 ) Roc k et . _ o u gh the Retr o S i gn al Latc h Re lay : a circuit

_ill be c_l e t e d t o e ne rgize t h e Retro F ire Sig n al Di s e ng a g e 23 sec on _

!_ u n e De lay Rel a y. _ - e power t o th e c o il of t h e Retr o F ire S i gnal Dis-

,engage Rela y allows the c irctt lt to be completed to the ASCS Cal ibrator

res ult i ng i n h i gh- t o r que RCS o p er a ti o n. _ -_ s h i gh -t o r q ue o p er at io n

w_1 _ l a st f o r 23 s eco n ds, w h ic h is 3 seco_ Is mo r e t h a n t h e a u ration o f

to tal retr o r o c ke t firi ng . Be h i gh - to r qu e mode ho l ds th e spacecraf t

i n the 3 4 attit ude wh ile the r o ck et s ar e f iri n g. At th e en _ of 23

se c on ds , t h e Re tro Fire S ign a l Di s e ng a ge 23 Seco n _ Ti me De la y Re lay wi l l

ene rgize remo_ power fr on the Re tro F ire Si gnal Relay and thus re mov-

ing t he h _ h - t o r q ue s i gn a l . Wi t h t he At t it u d e Switch i n t h e " AUTO"

p ositlon_ the a stro n aut ma y p re ss t h e Re tr o FA r e S witch e ner g i z _ t he

No. i _r g e n cy Re t r o F ire Rela y AI lowi ng Iso la t e d Bus p ow e r to e n ergize

th e N o. 2 E mergen cy Retr o Re lay, f iri ng the Retr o Roc k ets w h e n T _ s p ace-

c r af t a ss ,_e T_ e p r op er a t tit ud e . Wi th th e Ret ro Att itu d e Switch i n t h e

"BY-P ASS" pos i t ion, - ha p ressi n g t he Re tro F ir e S wit ch w hi ch ene rgi zes

t he Attitu de Pe rm_ s si o _ By -P a ss Re lay, t he Retr o Ro c k e ts wil l be fired.

re g ar dl e s s o f the attit u de o f the spac e craf t. Wh e n th e Ret r o S i gn a l Latc h

i s en er g i zed _ Mai n Squib Bu s p ow e r i s s u pp li ed, t o ene rgi ze th e Retr o Ro c ke t

Asse mbl y J etti s on 6 0 Seco nd T_ __ De l a y R e la y a nd t h e Re tro F ir e War_

Light 15 _econd _-- Delay Relay . After the 1_ second t ime de lay has

r un ont_ the red FI RE RETRO Telelt _ht is ill,_t -=ted. A fter the + _ee

_ - 12


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__NNEIkA. SEDR 104

Retro Fire Mon itor Relays are energized _ the red FIRE 1 _I_0 Te leltgh t

goes ou t and the green l igh t is $11,m_n_ted. A t _he en _ of l_e 60 sec-

ond time _elay, the Re tro Rocke t Ass_ l_ Je ttison 60 Second _-_ De lay

Re lay a_ovs pover to energ ize t_e Retro Rocke t Ass_m_ l_ Jett tsou Rela _

end the Jettison Retro Warnl _ L_ht 2 Second Time De lay Relay. As _he 2

sectmd t :lme de _ Is exp _-_d , the red _ 1_'_0 TelelXght is 111, -,_na _l.

_he Re tro Rocke t Assem _]7 Jett ison Re lay direc ts Main and I solated Bus

power to the two squ _s of the Retr c Rocke t Ass_z_ly Jet tison Bolt.

be bol t r ill t_ac ture and the package _r l_ drop free of the space cra ft_

heine a ssisted by a co il spring Instal led be _een the hea t shleld and

Retro Package Assembl y. _e dropping of the Retro Package Assembly from

the spacecra ft _J.l a _ov the three Retro Rocke t Assemb ly _s rs ttou Sen-

sor e (stn _e po le l_mtt svl tches) to return _o their normal posl ttou

energtz in8 the Re tro Rocke t Assembl _ Separa tlou Re _. _hls v11_

the Re tro Rocke t Aseemb _ UmbilXcal Separa tion Re lay to energtze _ firing

the six squlbs of +h_ _2_ree Retro Rocke t Packaee _tllca la and _etttsc _

the elactr ieal ,_tltesl pl_s _1_ ]_oe ec_ls a fter dropptn8 of the _tro

Package . When the Retro Rocke t Assemb_ Umb ilical Separ ation Rela _ Is

act iva ted , it re moves po wer from th e red JETT 1 _0 Teleltgh t and i_ _, _-

nares the green li ght. When the Re tro Rocke t Assembl _ Separ ation Rela _

is energ ized , it a ctivates th e Accelercme ter Arm _ Second Time Dela _

Re lay. At the end of the 5 second t_ae _elay_ th e relay func tions sup-

plying a ground for Ma in Btts power which opera tes th e .05g Relay. _he

energtz ing o f the No. 1 and No. 2 .05g Retro Sequence Dr op_ .05g Jetti-

son Asse _ly Sequence Drop , and .O5g Retro Te leltgh t Power Dr op t_rouEh

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__NNgLL SEDR 104.

th e co n t a ct s o f the . 05g Relay re moves p ower fro m the v a ri ou s rel ay s

a nd switche s i n volve d i n t h e r e tro s e q ue n ce as well as exti n guishi ng

the retro teleli g hts.

6-ll. ES CAPE

6-Le. GmmRAnE SCZ: XX= ' ION

The e scape syst e m pr 1 - _rily c on sists o f a t o wer assembly desig n ed

to p rovi d e a saf e mea n s of ab ort b etw e e n pre - lau n c h a n d st a gi n g . B y

uti l i z i n g the Posi_r ade Roc ke t Syste m, e s c a pes ma y s t_ . l] be i n iti a te d

after b ooster s taging a nd throu g ho u t sustai n er operatio n u n til or b it.

The tower asse mbly co ns is t s of a i 0 foot, tubul a r steel struct u re with a

4 foot Escape Roc k et mo u n te d %o its tapere d e nd , A s e_e n te d c ls _ p ri n g

with 3 explosives _olts s e cure s the ba se of the tower to the recovery

c omp art me n t u p per fla n ge. Attache d t o the Escape Roc k et Nozzle Adapter

P late is a J etti s o n Roc Eet which is us ed to Jettiso n the tower asse mbly

after the Escape Roc k et h a s b ee n fire d for a n a b ort; howe v er, u n der n or-

re al la u n ch co nd itio n s the Esca pe Roc k et is fire d to a cc o mp l i s h tower

se p aratio n at ti me of b oost e r en gi ne separatio n .

6-1 3 . E SCAPE _ _ORE LI F_0 FF BEFORE _ILICAL DISCONNECT

0 n l y o n e gro -n d co n trol l e d si gnal wil l en ergi ze t h e May d ay Relays .

This sig n al is a direct hard _ li n e f ro m the b loc E ho ll se Abort Switch to

the MaydAy Rel a ys. The s e q ue n ce ( Ref. F ig u re 6 -5) to e n ergize the May-

day Rel a ys is as follows: Th e A b ort Switch is activ a ted en ergizi n g the

5 0 Micro -S ec on d Ti me Dela y Rela y. 2 8 volts is a p plie d thro u gh the 50

6-14


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I1CDONNELL SEDR 10 4

z_N

u >" _. ,__Z

v-

_ >_

_ z_ _._ _8o u_8: _

__"_

FMI 8-149

Figu re 6 -5 Escape Before L iftoff Before U mbi lical Disconne ct

6-15


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NNiiLL SEDR 104 _

M icro-Second T_-_ Delay Rel ay con tacts and through tb_ m_ssi le to the

Mayday Relays. In the event the spacecra ft mus t be aborted on the

launch p ad and the m_ssi le is unable to tran _tt the hardl ine abort

signal, there is one o ther me thod wh ich may be selected. U mbilica l

Pins _ and 45 are a bor t wired and transm it 28 V power fro m the block

house to the spacecra i_' s Gro und C o.w-nd Abor t Signal L atch ing Relay

ene rgizing a na lock ing in the relay . _rough this energ ized re lay space-

craf t 28 V Squ ib Ar m Bus powe r is tr ansmitted to the p ole of the Ground

Te st Umbilical Re lay ; however , power w ill no t con tinue throu gh this relay

until the relay is de-ener gized. _e only way the relay may be de-

ener gized is by ejecting the ,m_ilical. _herefore , if this abort

me thod is requ ired to be used , it woul a be necess ary for the block

house condu cter to select th e Abo rt Switch (power to p ins _ and _5)

an d within m i_l_seco_ds thereaf ter the ,w_ilical i s ejected. After the

Mayday Relays are ener gized , the escape sequence is the same as expla ined

in paragraph 6-16.

6-1_. ESCAPE BEFO RE T_TVTOFFAFTER _3ILICAL DISCONNECT

Du r ing co u n t do wn j th e r e will b e a ppr n_4mat e _ 50 t o 9 0 s econ ds b e tw een

tim e o f s pa cec r afts u n billcal eject a nd ti me z e ro , w h ic h is t wo i n ches

lift o ff. Dur i n g t h is p e r i od , the t h ree available method s o f ab o rt ar e :

(1) _-e block ho use to m issile hardl ine abor t signal as explain ed in the

previous paragr aph ; (2) Ground c_.!_nd receiver abort signal; (3) Astr onau t's

Abor t Handl e. _hese three me thods all result in energiz ing the Mayd ay Relays.

6 -1 6


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_PN_fl ./. SEDR 104

After lif toff, (Time Zero ), there ere three methods by whic h an a bort

may be _-_tia ted _ _ey a re: (1) Ground c_n_d re ceiver abor t signal

a n _ ( 2 ) A st _ =. _ - ,,t bo r t H a ndle , bot h of w h ic h we re poss i b l e me tho d s i n

the pre vl ov _ _a ph , ( 3 ) T h e Boo s t e r Cata s tr oph ic Fail u re De tecti on

System . _s +.bt_ method has been n oneffective in the two pre vious p ara-

graph s du e t o t he _i TA me Z e ro Relay be i ng de -e n er g i ze _ . H ow e ver, _ _i

Zer o Re la y is ene r g i z ed two i n ches af t er lif t off a nd co mp l e te s a

circuit t o t h e Nayd ay Relays if t h e Catastro ph ic Failure Det e cti on Relay

is ae-e n er g lz e cl by lo ss o f p ower fron the mis s i l e.

6 - 1 6 .

When the Mayday Relay s are energized , the abort sequ ence (See Figure 6 -6)

will occur as follows: The a bo rt L igh t on the left hand console wi ll _33,--_ -

mate, the Spacecra ft Separ ation Bo lts Power Rela y is energized and the Space-

craft Separ ation Warning L ight Ti me Delay Relay i s energize d. _e Abo rt

Relay in the MA_--_ n Altitud e Sensor is energizes after Spacecraft A dapter

separation. _e M-_--_ Altitu de Senso r com_u tes the time d elay re qu ired for

the spa cecraft to reach a safe d_m-4c pressure bef ore _ettis on ing the Escape

Tower. Th e Spac ecraft Separation Bolts Squibs will be fired , releasi ng the

Spacecr aft- /_=pter _ R ing and allowing the three _4_4t switche s to re-

turn to the ir n _nal pos itions energizing the E mergen cy Escape Rocke t

F i r e Rela y , t h e Esca pe Roe _ * t F ire Relay an_ t h e Spac e cr a f t Adap ter Dis -

c o n n ect Sq u i b F ir e Rel ay , f iri ng th e Esca p e Ro c k et and t h e fo u r Spac e craf t

Ad a pter Explo wi ve Disc o n ne ct Squ ib s. _ e Es c ape R oc ke t' s 5 6 ,00 0 p o u nds

o f _ will _e p arate t h e spac e c r af t fr c _ t he m issile an_ carr y i t away

fr _n the susta iner at a mall a ngle. The Spa cecra ft Separa tion Sensor

6-18


188/365

MODONNELL SEDR104

T_tm_t Switc hes also ener gize Spa cecra ft Separ aticm Sen sor Relays, which

turn s on the g reen _ CAPSULE Te leli@ht 3 a nd also ener gizes the To wer

Sep a r ati on Ab o rt In t e rl o c k L atc h i n g Re lay. The A bo rt I n t e rl o ck Re l a y

e n ergize s the Retr o Ro cket A ss embl y J e ttisca Relay a nd fire s th e tw o

s q u ibs of th e Re tr o Ro c k et Assembly Jetti s ca B o lt. The b o lt will

fract u r e a n d the pac k ag e will drop free of the s p ac e c r aft, bei n g

assiste d by a c o il spri n g i n stalle d b e twe en th e H eat _i e l d a nd Re tr o

Package Asse mbly f o r t h is p u r po se. Whe n t he spacecraft r e ac h e s a maxi-

altitu de , contacts i n th e Maxi mum Altitu d e Se ns or will close an d

energize t h e Tower Se p arati on Bolts Power Relay firi n g t h e b o lt s . A s

t h e three tow er b o lts are fractured, +_e segmen ted Tower Clam p

se p arate s all o wing th e * . _e e T ower Ri n g Li mit Switch es t o r e t u r n t o

th e ir no rma l po sitio n e n ergi z i n g t h e Eme rge n cy Jettison a nd Jetti son

Rocket Fi re Rel ays. _ o u@h t h e se relays a nd th e ir p arall el co n t a ct s

Mai n a nd I so lated Bus power will fire th e s q u ib s o f _b_ J e ttiso n Ro ck e t .

Th e to we r will b e J e ttis o ne d clear o f th e spac e craft r es u lti n g i n se p a -

rati n g th e tw o T ower t o Sp ac e c ra ft El e ctrical Disco n -ects . _e sep ara -

tio n o f e ither d isco nn ect will de-energize the T o we r Se p arati on Se n s o r

Relay s e nergi z i n g th e Ab o rt Rate Dam p i n g Rel ay _r o , ; _hth e c o ntacts o f

the T o we r Separati on Abort I n terl o c k R elay. _n l s relay will s e nd a sig-

n al to the A SCS c - remandi n grat e d a mping u n til ti me o f Mai n Chu te d eploy-

men t. De-energizi ng the To wer Sep ar a tion Re lays will al so stert tw o 2

seco nd ti me rs in th e r e c o very sequen c e. Th e first tim e r will a rm th e

21 ,000 Fo o t Baroswitch es a nd two se co nd s l at e r t h e s e c ond ti me r a rms t he

10,600 Ft. Baroswitches .

6- .19


189/365

6-20


190/365

_O_O_Bg.L SEDR104

6 - 1 7 . ESO : 'E A TZON

The methods o f initia ting an abo rt after staging are iden tica l to

the methods named for the escape a fter l iftoff and are: ( 1) Ground

cc e ma a ndre c e iv er abort s i gn a l ; (2) As t ron a ut Abort H an d l e; ( 3 ) Boos t er

Ca ta str o phi c Failure Dete ct i o n Sys t e m. An Y o f t h e t h ree me thods _ "1]

energi ze the Ma_l_y Rela ys. The s equen ce wh ich occurs by the ene rgizing

-of these r elays is de scr ibed in the following paragraph.

6,.1 8. OPE TZON

The signal which ener gizes _ Mayday Relays als o is tr ansmitted

to the missile tO shu t down the sus tainer engine (Se e Figure 6-7).

_w0t_h contacts of the ener gized M ayday Relays_ a power cir cuit is can-

pla ted to the ABORT L ight on the m ain instrumen t panel and the .20g

conta cts of the _h_us_ Cuto ff Senso r are armed. As thrust de cays to .20g,

the con tacts close and ene rgize the Spa cecraf t Separation Bolts Po wer

Relay f ir ing five Spacecra ft Separation Bolts squ ibs and zeparating the

Spacecra ft Adap ter Cl amp R ing. The s equen ce following clamp r ing sepa-

ration is the s_ as the nor mal sequ ence (Refer to Pa ragr aph 6-7). Re-

en try may be accompl ished by any of the emergen cy pr ocedures (i.e. , as tro -

nau t or gro und i n itiate d) . Re fer als o t o Par a graph 6 -9. If the ab o rt is

initiated b efore the spa cecr aft ha s ob tained the corre ct velocity fc_

orbital fl ight and it is not desired to fire the Re tro R ockets , the Re tro

Pac k age must be Jetti s oned ma nu a l l y , i t sh_, !d be n o t e d that e ve n i f the

spacecra f t d o e s n ot attain o rb ital vel o cit y , the qu ic k est way f or r e-

en try is by _a_rgen cy firing of Retro Rocke ts.

6-21


191/365

S ECTION

SEQUENCE SYSTEM, LANDINGT H RO UG H RECO V ER

TABLE OF CONTENTS

TITLE PA

Automatic Sequence Description ..............

Automatic Sequence Operation ...............

Emergenc y Sequence Description .............

Emergenc y Sequence Operation ..............

System Components ................................

7-1


192/365


193/365

JWOOO _NmLL SEDR104

vi i . s imcESYS TmLAmmi n Gm0UGHm c o vm z

. 7-m. AOm U T ICSEQUm CE sc oN

_e _a-_4 _ end re covery sequen ce syste m prov ides au tomatic electr ical

and mechan ical sequen cing to land the specec rat_t safely after an a b_ or

norm al re-entr y_ and to Initiate locating aids for ass istance in the su b-

sequen t recove ry. _e pr_mmry (c ompletely aut _matic) system inco rpora tes

e d rogue p arachu te, used initially to dece lera te and sta bilize the space -

craft in the inttisl ph ase of recove ry and a main parachu te for fu rthe r

dece lera tion. Redund an t cir cuits ha ve been inco rpora ted to eliminate the

poss ibility of stng_e-po int fai lures. The land ing Is accomplished u tiltz-

Lu g a 6 3 -foot -d lsm e t er pa r achu t e wh ic h i s depl o yed a t 10 ,6 00 feet. In t he

even t of a mai n ch u t e fai l u r e, a 6 3 -foot -d ia me te r rese rv e ch u te may be de-

pl oy ed b y t h e astro n a u t's m. anu a l se l e c tio n . Bot h mai n and reserv e chu te s

ar e re e fe d t O 1_m_t s_ o c k lo a ds at i n it i a l open i n g . _he r ee fing li ne i s

sev e re d a u tcuatically after a p rad e te r mi n e_ tim e delay a nd t h e ch u te will

ope n f u l_, l ow e ri ng the sp acecraft at the p r e scribe d l - ri d i n gs peed . A

s o u n a f_ a nd ran g i ng (S OFAR) b _ is attache d t o the mai n ch u te r isers

and is rel e aser as a f un cti on o f mai n chute d e ploym e n t. Whe n t h e risers

I_,_I ta u t, f_ e b _._ i s e j ec ted a nd fal ls to th e o c e an a he ad of th e s pa ce -

craft. Whe n t h e b_._ re ache s a d e p th of 2,_00 fe et be lo w se a level, it is

det on a t e d th u s pr o vla_ -g a m e a n s f or d eter_ - _n g the a pp ro_ m- te location of

t he spac e c r af t _n_ , g area b y soun _ fixi ng a n _ ra ng i ng s t a tions. After

mai n ch u te d e p l o y me n t, the la nd i ng i mpa c t ba g is ex t e nd e d , p r o vi d i ng a

c u shi on i ng effect f o r the lan d i ng im p act. After i mpact, th e ma_n ch u te

is a u t c _aticall_ d isc o n n ecte d f o ll o wed by reserv e ch u te ejecti o n; h o w-

ever, ch u te d isc onne ct is del ayed as a fu n cti on o f the Resc u e Ai d s Switch:

i n a u t c _atlc (Ab vfO ),a 1 0 - mi nu te delay i s acco mpl is hed ; i n ma nu al (MAN), a

cu e-sec ond dela y i s accc_ p ll s he d . _eref o re, if the astrona u t d esires7 - _


194/365

m_DO_N/B._. $EDR I04

t_medat _ chute meparat ion a t 4.Tact _ he mus t pos iti_ the Rescue A ids

Switch to the "M AN"pos ition at impact to by-pass the 1 D-minu te delay (at

any port io= of the lO-_,_te _elay r_.4._._ after :Impact). _e astro-

naut will _ egress no _a]__y taking w ith h im the sur vival kl t which

c onta i n s a 1_ ee r a f t a nd o ther s ur viva l ai d s.

7 -2. A_TIC ._ , OP _

On ro ver sep arat ion, pow er is rem oved from the Tow er Sep ar ation Re lays

_ h e Mai n Chu t e Sy ltem Arm 2-Sec oz _l _J.neDe lay Re lay s t O be ene r -

gize d (Se e FA_ n- e 7 - i ) . Aft e r t h e 2- s econdt i me del ay h as run ou t p o v e r

_ ic ws throu g h t h e clos e d ec u t a_ t s e n e r gi z i ng t h e Mai n Chut e2 - Sec ond

Ti me Dela y Rela y s , a nd a_ t e r a 2 -se cond _e la y a rm s t h e No . 1 1 0, 6 00 f t .

Bar osw lt chth r o u sh +h . 1 0, 60 0 ft. A r m Relay cc _tacts . 5 _e No . 1 a nd N o. 2

Baro seitches are _ired in se r i e s t h e r e by requi r ing bo th swatches to be clos ed

befo re normal m-tn chute deploymen t can be accc _lishe_, q_e No. 2 21,000

f t . Ba ro s wlt oh is a r me_ +_ o u sh th e clo se d c o ntactsof th e Mai n _ ut e S y s -

te a Arm 2-S e cond T i me Dela y Rela y s . Upo _ de s c e n t t o 21 ,000 ft. , bo th t h e

No . 1 a nd No . 2 21 ,000 f oo t Bar o nl tch e s , wh ic h a r e wi r e d i n s e r ies, clo s e

_hereby energ izing the D _o_e Deploy Re ls_, _ t he Drogue Chu te M_Gar ,

deploy i ngth e I _ Pa rach u t e. _ h e Drogue Chut e sta bi li z e san _ d e cel er a tes

th e s p ace cr a ft . A t sppr - -4 :_ t e_ 71 0, 6 00 ft ., th e 1 0, 6 00 ft . Ba r omr At_h e s

actuate th e _,4. D eploy Rel ays resutti ng in the r _ova l of the squ ib ground

cix-euits and _ o_ all four squ ibs of th e Antenn a Fa ir ing E _ect_ r . Also,

th e Main Dep loy W ar ai_ L igh t 2-Seconcl _ ,,,_ Dela _ Relay is ae_uate _, a_

at the end of 2-seoc_ l del _ the ze(1 Main De p l o _ Te l e l lg htis l_ --4--t e_ .

_he An tenna F air ing Sepe awt ic_ Sensor ArmRe la_ are ener gized _ the

74


195/365

__NN MLL SEDR 104

closed cc_ta_ts o f the M _n Dep loy Re lays ar ming t he t wo Antenn a Fa ir i_

Separatin_ S ensor Swi_ es.

_e fir ing of _A four Antenna Fa ir ing EJectc_ Squ ibs causes the

Antenna F air ing to separa te from the spacecr aft. A la_L rd _ co_nec ted

fro m the Aute- -a Fa ir ing to the Main Chute _ extracts the Main Chu te fro m

the chu te c_ax_nt. The Main Chu te opens _.I t l a _ i n the reefed co n -

dition to limit shock loads. Four seco nds after the chute is dep loyed , the

ree fing 1t_e is severed by a py rotechn ic c_ge in the ree fing lane cut ters

alAowing the pa ra_,_te to open _y.

_he sep ara tic_ of the fa ir ing from the spacecra ft o!lows the Antenna

Fairi ng S e par atl o _ Se n s or S wit ch e s 1;o functl c n. _ ] _c oush th e sw i tch e s ,

power is ro uted to ener gize the Main E jector Re lay fir ing the Main Ejector

Bag Squ ibs. _ _ squ ibs fire _ _hey gener ate a gas_ filli ng the E_ec-

tot Bag at the bo ttom of the Main Chu te compartmen t aiding the e_ectto n of

the chu te. At _he same time the An tenna F airin_ Separ ation Signal Re lays

are e ner _I ze _ i 1? , -- _, a tl n8 t he _ re e n Mai n Dep l oy Te l e li gh t a nd r e _ o vi_

po wer fr o m the re_ telelig h t. P o wer I s als o d ir e cte d thr ou g h t he Au t enn a

Fai r i n g Se p a r ati c _ S en s ors t o ener giz e t he Mai n I n e r tia S_ r l t chAr m 1 2 -

Seeo _l Time De lay Re lays . After the 12-seco_ time _elay h as run out, the

ener gized con tacts allow power to be supp lied to ener gize the ___ding Ba_

Ex tend and L and ing Bag Nam ing L igh t 2,-Secon_ Tt_ Delay Relays as well as

to t he Ine rtla Switc he s. _ he cl os e d c on ta c ts o f La nd l n _ Bag Extend Re lay

f i re t he s qu i bs of t he L a nd i_ Ba_ Valv e releas i n _ t he hea t sh iel_ 1 a nd

ex t e nd i ng th e i mpa c t la nd i n g ba g. As _ 2- s econ _ tim e d ela y runs o _t,

7- 5


196/365

_ONN i_LL SEDR104 @

th e La nd i n g _ Ws_ Light Re l a y il l mmi na tes th e re d T _ndi D_ Reg

Telelig_ht. Upo n hea t shi e l d se p ar a tl on, th e I a nd i ng _g Un loc k S i g-

na l T,_m_tS witc h es a r e act ua t ed a nd t h r o u gh it s cl o se d co n t a ct_ p ower

fr o m the Auto I _ Bag Fu se is d irected t o e n ergize the T_ ,_

Bag E xt end Si gna l Relay ill_ti_ the green Ta.A_n_ Bag Te l eli g ht

a nd ex t i n g u ishi ng the red light. _ h e f o rce o f im pa ct on la_i_

o perates the T- ertia Switches which pr o vide p o wer t o the c o ils o f the

I mpac t Relays. Thr o ugh the cl os e d c on tacts o f the Yzpact Relays, po wer

is s up plie d t o e n ergize the P o st Tal,w14._ _Sr_ Re. B _,_h th e

activ a te d c o nt a cts o f t he Po s t T_ ,A_,_ S y st em Re l ay s , po wer i s tr_- - -

mitre d to energize the Imp act S i gna l Rela y . A l s o thr o u gh t h e cl o se d

c on t a cts of the Post T_I n_ S y ste m Relays, the F l ash i ng Rec o very

Light circ u it is c c mp l e te d sett_ n _ t he lig h t i n op erati on . _ en the

Im p act S ig n a l Relay is e n ergiz ed , t h e gr e e n M_i n De pl oy a n d T_nd_,=

Bag T e lel ights a re ext tns ulshed and t he re d Resc ue Ai d e Te lel ig h t

is ill - m4 - _te d . With t he Rescue Ai d s Switch i n " MAN", at t h e e nd

of t h e l- s eco Dd ti me d el a y, the Spacecr a ft S t ab iliz a tio n Rel a y is activate d

a ll o wi n g the Main Disco nn ect a nd Reserv e Disco nn ect Relays to b e e n ergize d ;

with t h e switch i n "A UTO", this a cti on is delayed I 0 mi n utes . _o u g h the

ene rgized con tacts of Main Disconnec t Relays_ th e Main Chute Disca nne ct

Sq ui bs a r e f ired , rel ea si n g the ma i n ch u te fr o m th e s p ac ec raf t . _e Re-

serve Disconnect Rela ys fire the Rese r ve Chute Disconne ct Squibs releaetDg

th e Re ser v e Chu te a n _ ene rg iz i n g th e Reserv e Deplo y Rel ays . The Reser v e

De pl oy Re lay s fi re th e Reserve Ch u te E_ e ct o r Bag Squi bs . Th e Rese rve

7 - 6


197/365

"_M_DONNffLL SEDR 104

Chute E jector I_g Squ ibs ac tiva te the _s generator which has a one-

second de lay in ignition time be fore inflating the ejector ba g ex-

pe lling the Reser ve Chu te and the dye _rker. When the Rescue Aids

switch is p laced in the " MA_" posi tion or s_ter the 10-m inu te de lay

with the s_tch in "AU_0"_ the Rescue Aids Sw itch Signal Relay and the

Pos t Land l_ System Power D rop Hold Re lay are ener gize4, q_e ener gized

Rescue Aids Switch Signal Re lay removes po wer from the red Rescue Aids

Tele light and tll,_nates the green l ight. _e Post-I _ADg STs tem

Powe r Dro p Hold Re la y ene r g iz es the Post -T a -d l n _ S y s t e m Power D z o p 3 0-

Second T ime Delay Relay. At the end o f the 30-second t_._ d elay th e Whip

Antenna Ex tend Relay is ene rgized fir ing the W hip Autemm Ext end Squibs

activating the gas cartridge exteDd l_ the active element o f antenn a to

its full length. _hen the Pos t-EandAn g System Re _ys are ener gize_ on

iml_t and , depend ing on the pos ition o f the Rescue A ids Switch, powe r is

appl ied t -_4a te_ or a fter a 10-m inute time del ay to the coil of the

Post Land ing System Po wer Drop Hol d I _ .,_-I o t he P o st I _ d _ Sy st e m

Drop _0-Second Ti me l_e3a_r . After the S0-sec_n_ delay , the Post I and _n_

Sys t em Po wer Drop Rela y i s e _ r _iz e _ w h ic h re mo ve s po we r flwm t he r e-

mai n i n g cmqnents excep t the Wh ipAntenn a Extend a elay.

7-3.

_ h e e me rg en cy pr o v i si o ns of t he _ s y stem b as le- _ ly c on si s t o f

- _ . u ally -o perated back- up systems i n iti a t ed by t h e astronaut . _e appro -

pr l ate bu t t o n , pu 11- r i n _ and sw i tche s are lo c a t ed on th e Le f t Hand C o n -

7- 7


198/365

_ONItlELL SEDR 104

\'\

-ANTENNA FAIRING

I "S OFAR BOMB

HF WHIP ANTEN NAi

' P ILOT CHUTE LANYA RD/ i

IE CHUTE RISER

/

:HUTE

HUTE

"" "_ PILOT CHU TE RISER

DEPLO YM ENT G UN

/ RESERVECH UTE TO ANTENNA FAIRINGEJ ECTOR SAG

PILOT CH UTE lANYARDTO DEPLOYMENT

DYE

RESERVEPARACH UTE

PILOT CHUTE RI SE R

FM18-65

Figure %2 Main and Reserv e Parachute System (Sheet 1 of 2 )

7-8


199/365

_rMCDONNELL SEDI{ 104,

CHUTE

ANTENNA

FAIRING _

SOFA R N3_ /

DYE_RKER

FM18-65

Figure 7-2 Mai n an d Reserve Parachute S ystem ( Sheet 2 of 2)

7-9


200/365

__Nm_t. SEDR 104

sole. The e mergency system con tro ls manusJ_ _-tnitta ted _ep loymen t of

the Drogue , Ma in an d Reser ve Chu tes, extension o f the Lsn dJ_g Bag , and

initiation o f rescue a ids.

7-4- . msms OPZaA TIm

On desc end ing to 21,000 f t., if Drog ue Chute failure is de tected b y

lack o f opent _ shock and _y a v isual cheek th rough the windo w, the as tro-

nau t wi ll depre s s t he I _og ue bu tto n (See Figure 7 -3). De p ressi ng he butt o n

allows the E mer gency Dr ogue Deplo y Relay to be ene rgized and the Dr o@_e

Chute Mor t a r Squ i b s t o _ e f i red depl oyi ng t he Dr o gue Chu t e . If the gr een

Mai n Depl oy Telel l_t fai l s to t"!] ,,, .t--,t_, fa i l u re of t he _ n t Ch u t e to

deploy may be de tected by a la ck of op en i ng shock, a v isual che ck and n o

decrease in rate of des cent. Upon de termining that the Ma in Chu te has

not deployed , the astronaut will place the Recovery Ar m Switch on the Con-

tro l I _ I to t he .mmml po s itio n. I f Mai n Chu t e Depl oy is stl ] _ n o t

s e nsed , o pe r a ti ng the Ma i n Depl oy Pu ll R i ng energ i zes t he E mer gen c y Main

De pl oy Relay , f i r i ng the A n te nna Fa iri ng E j e cto r Squ i b s , ejecti ng t h e

Antenna F air l_ and deploy ing the Ma in Chute through the nor - _1 au t_-_tic

sequence. When the green _4_ Deploy Telel ight is i ll-m_-ated and the

r a te o f de sc en t i s g rea ter th an 32- f e et- p er - seco nd , t h e c hu t e is vls, m_l y

checked for damage . If the chute is da maged or did not depl oy, actuating

the Re se rve De pl oy _,1 1 Ring w_11 energize the l_serve De pl oy Re lays .

_ y ug h th e en e r gize d c on tacts o f th e Re ser ve De plo y Re l ay s , po wer is

appl i e d to th e F,_t. Ch u te l _sc onne ct fi _ t he s q uibs d i s c onne ct_ _ _ the

c hut e fr c _ the s pa cecr a f t . At t he sa me t i me, t he Reserve Ch u te E_ector

Bag Squibs are f ired _nerati_ a gas af ter a 1-second d elay and _n_4 a ti_

the e jector bag which a ids in deployiu _ the Rese rve Chu te.

7-10


201/365

MCDONNELL SEDR 10 4

EMERGE NCy _ DROGUE CHUTE

DRO GUE DEP LOY MORTA R DRO GUERELAy SQ UIBS CHUTE

DROGUE CH UTE _41 _L_iL_T_" o_ -L

EMER GENCY MAIN ANTENNA FAIRING J _DEPLOY EJ ECTO R

RELAy SQUIBS

MAIN CHUTE DEP LOYED BYTHE AUTOMATIC SEQUENCE

MAIN CHUTEFALLST O DEP LOY

RESER VEC kfLITEDEPLOY GUN

SQUIBS

PILO T C HUT E

RESER VE MAIN CHUTEDEPLOY DISCONNECTRELAYS SQU IBS

RESERVE CHUTE

EJ ECTO R

MAIN CHUTE FAILS _IAG SQUIBS

TO DEPLOY O R IS E JECTO R BAGDAMAGED

ELECTRICAL SLGNAL Ill

!_ MECHANICALI MOVEMENTGAS INITIATEDEMERGENCY EMERGENCY

LANDING BAG LANDING BAGEXTEND RE LAY VALVE SQUIBS

LANDING BAG

MAIN CHUTE

DISCONNECT ILANDING BAG SQU IBS

FAILS

RESERV ECHUTEDISCONN ECT

RESER VE CH UTEDEPLOY GU N

SQU IBS

PILOT CHUTE

I 0 M IN. T.D. _ RES ERVECHUTEEJECTO R BAGSQ UIBS

NOTE: RES CUEAIDS SWITCH IPC SI TtO NE D TO "M ANUAL" TO RESCUE AIDS I 30 SE CJ .D. EJE CTOR BAG

BY-PASS "AUTO" 10 -MINUTE DELAy. (10 MIN , T.D. RELAy) WHIP A NTENNASQUIBS

WHIP ANTENNA FMI8-66A

Figure 7 -3 Landing and Recovery Emergency Syst em

7-11


202/365

ml_OONNBZ.L SED R 104

Twe lve second s s__er the Main Ch _ is _p_j_ the gr een

Bag _llgh t should be t_.md _a1 _1. If the l ight d.oesn ot cm_ on, p l_ethe L and ing Ba g S_Ltch in the "MAW"posi tions enm'S lzi_ the Euer gene T"

Land ing _ Extend Relay , f_rJ:S the l_-rg oncy Land _S BsS Val ve Squibs ,

re leas_ the bea t sh lel_ end _ the impact _ bag. Ten

u_nrtes after _ the Res cue kLds Swt ch By-Pass Relay is ener _Lzed.

_lhon ae tlva'. _ the rela y by-passes t he Rescue A _ds Swt ch and en ar_zes th e

rel _m vh ch mq _l_- po_r to f ire the Math Chu te Dsco_-et 8qulbs as yel l.

as "th e squ ibs for th e Reserve , Dseonne etj Deploy Gun , _ the _ector B ag

In the mine a_ner as if the mr i tchwe r e place _l in the " MAN"pos itio n.

mo m

_e 6rc _w par achu te ass,. _l.y (See F igur e 7-5) eo_ s l s t s of a eon_e a_

r i bb o_1 - t_ _o gue e_ n o p _ v itb _1%'ser , dro g ue _ pl o_ beg _

_r o_e mortar , sabot, aria &rogu e mortar cover. _e dro gue p arachu te cano-

py 18 a conical r ibb on p arachu te hav i_ 8 gore s of 2-1n ch wlde _ l_O-lb.

tensi le str ength r ibbons on_ 8 tubular n _lon suspens ion l ines o f 1,(XX) -lb.

tensile stren gth ea ch. _ para _-te i s cons truc te_ to a d l_eter of 6 . 85

fee t e nd p e r,m-en tr y reefe _ (re s t ri cted)t o a n efTect tve d_ a _ e te r of 6 . 0

feet by ,.e--,_ of pocke t bands . The ccn st.w_te_ total poros ity is 27.9%a nd the e ffe ct i ve pc _ o e l t y (_ hro _ r ee_ ) I s 3 6 .3 _ . _ h e 3 0- f t.

I nt eg ralr ise r i s made fr c w th ree l a y e r s of 3 ,000- 1b .te n si l e s t r e n g th

low-elev ation h ot-st re tched Daero _ webbing. _he drogue p arachute s tabtli-

7-12


203/365

,MCDO NNELL SEDR 104

1 ANTENNA FAIRING EJECT ORGU N 9 SHA RKREPELLANT2 PARACH UTEDISCONNECTS(2) 10 D RO GUEMORTAR3 RE COVERyLIGHT 11 WHIPANTE NNA4 ANTE NNA LANYARD 12 PI LOTC HUTEDEPLOYMENTGUN5 BAR DSWITC HES4) 13 PILO TCHUTE6 MAIN CHUTEAND SAG i4 RESER VEHUTEAND BAG

15 SEAMARKER7 E JECTIONBAGS{2) 16 IN ERTIASWITCH8 GASGENE RATORS2) 17' SOFAR BOMB.

J NOTEVII_V LOOKING INBOARD

LEFTHAND SIDE

FM18-67

Figure 7-4 Landing an d R ecover y System Installa tion

7-13


204/365

_

_ONglELI- SEDR 104

FMI8-68

Figure 7 -5 Drogue Parachute

7-14


205/365


206/365

__ma .a. SE DR 104

zes and decelerates the spaeeera_ . _ canopy weighs 2..9 Ibs. wlthout

riser and 5.9 ibs. ine_ the 30-ft. Daero _ r _ser. The _c_e pars-

chute depl oyaent b ag serves a _ua l func tion of ( i) pr otect _ the drogue

parachute _ eJe_ a_ (2) _ means_or order: _ dep 1oymnt

of the &ro6 ue p ar achu te. _he b q is _A__eac tlxred of c otton sa racen fab-

r ic re infor ee_l vith _1_ vebbin g aria co vered at the upper en_ vAt h a

heat i n s u l ato _ of g l ass cl oth . _ h e bag is wei ght e4 a t th e upper e nd

v l th a 0 .5 lb . le a_ &is c _ h l ch assi sts i n s tr i pp i n g th e b ag f r_ th e c a nopy

at th e c _._ _ le t i cnf 14.A a nd r ise r s tr e tchou t. Ins i de th e b ag a re

cotton ta pes to v_4_h the r iser is secured _ur ing pack ing in order to pro-

vide ord er ly r iser dep loyment. _he mouth of the b ag is closed v ith a

light cott _ cord.

7 - 7 . modus_ _o _ _r DS_SO_

_he _ par achu te e_ectio_ mort ar is a device for pos itive Ae-ploy _nt of the dro gue p ar achute _rAth suff icient en er _ to overe _ l_al

pre ssure gr adAe_ts an_ _avita ticnal f orces . _he 4roL _e parachute is

pack e_ in a protect ive bag an_ stove_ in _he mo lar tube o_.top of a

_ASht _t sabot (See _ 7 -6). :he sabot _me_ns as a p _s_onto

e_ect th e parachu te pack , when pres sure _ i_ below by gases &_nera _

frc _ a pyrote -_-_c charge . _ae prope llant ch ar ge is _-tt ial_ fir e_ into

a br eech eh. .-_er of mall volv_e, to produc e high pressur e _nlch is sub -

sequent _,7 vented throu gh a small or ifice sad into the m ain ,_-._er at rel-

attve_,7 lover pressure s. In th is M--e_, r eact ion loads ar e kept to a

.4.4,_._ s ince the pres sure ener gy is no t e_enAed inst an_aneousl _. _he

7-16


207/365

" _MO_NNE_. SE DR 10 4

pres sure se:! 4-u qual ity of the sabo t is der ived f rom an "O" r ing, in-

stalled in a _ve ne ar the base. Two mall ho les are locat ed in _he "O"

x_ groov e to ve_t a ir _r a_ped in the mor tar tube u _er _a_h _ sabot c_

insta lAaticn. F or proper operation _ the "On r ing and the inner w all of

_ m_ar tub e_ w h ic h I s al wa ys i n con ta c t wit h th e " 0 " r i n g, ar e _.-

brica_e_ before ins tallatic_. Be dro _w parachu te pa ck is r etaine_ in

i t s e t _ pos ltlc Dv At h i a _ h e m ort a r _e b y a _ met a l " Rene-_ l "c o ve r

which is atta ched to the upper surf ace of _e antenn a houa i_, q_wee cut-

out sectic_s_ prov ide_ i n the sides of the cover , per mit rou ting of the

steel c ab le riser s in to the dro gue chute c an. m_o c over is des igned to

constra in the chu te in its c o mp _t a_t negative deceler ations and

also to requ ir e m_-_m -I for ces to br eak loose fr om its attaohm,n ts at the

time of deploy_nt.. Pre ssure of _he chute pa ck cau ses _he cover " to de f lect

i n su ch a ma _r tha t att e #_ t ta b s i_,11o _ t fro m _d er a ttachi n g s e rev

hea ds th _ a s lotte A ho le desig n e df or thi s purpos e. _ h e e n e r _ requ ire d

t o ex p el th e Ar o _ u e c hut e from it s com p a rtm e n tis pro vide d f r o mh ig h p res sur e

ga s e s , _e n e ra _e dby i_ n ltl on of a pyr ote- h -_cch ar ge. _ h e ca rt r i d ge i s

1Oe_ 0___Ath 66 gr ains of powd er , con tained in a prop ellan t can att ached

to a steel bo_ _nich hooses t he lgni_lon w _J _ anA ter mina tes in an

elee trl c alconn ect or . B e i_ n lt l c_ ci r c u i try eoms la ts of two s e p a ra te a nd

I nd l v I Aua l br i d g es , e i th e r of wh ic h i s ca p able of ig n iti n g th e pow e r c har geupo _ app lica tic_ of th e prop er c urr e nt .

7_. MA INPARA_

_e main p ara chu te assembl_ consists of: main p arachut e canopy ,

riser, dep loymen t be_, and p arachut e disconnect . _he main pa rachut e

7-17


208/365

_ONNE LI- SEDR 104

Figure 7-8 Main Parachute and Packing Box

I , STRUCTURE 5. SHEAR PI N i

SHORTI NG WIRE 6. PISTO N3] SQULBCA_RIDGE 7. LEADBUFFER4. BUSHING 8. ARM

FMI8-71

Figure 7-9 Main and Reserve Para chute Disconnect

7-18


209/365

At'ICDONNEL L SEDR 104

I 1. FIRING MECHANISM 4. SHE AR PiN II

Ii

I. BODY 5. ELECTRICALCARTRIDGE3. PROJECTILE 6. MA!NCARTRIDGEFigure 7-10 Pilot Chute Deployment Gun

FMI8-73

Figure %11 Parachute Ejector Bag

7-19


210/365

_N_m .L SEDR 104

canopy ls a 63-foot D RY4" -1 dt meter rlngsstl t ype. _he rlz _sal l para-

chu te ls fabrtcate _ fro m 2,25- and 1.1-ounce per sT, _e yar4 n ylnn para-

chute cloth into _8 go res with _8 suspension l _s o: _:_-poun _ tenslle

s tr e n g th. _ he : -_- p a r a chut eis p a_ k e 4 i n a deploym nt bag -. _h:J.ehpro-

vtaem a 1_ sna_ forc e ari a order ly aep lo_en_ (See FA_n_ 7_). _e

bag is : a nuf a_ tur _ lfro: cotton sa t ee n fa bric , r el nfcre e 4v l th _ Icn

vebbi ng an _ eovere _ a_ the upper end vlth _:erao1ex enA glmme cloth

i n s ul ati on . _4 de th e be _, : i 4 n_ al o n g i ts le n g th , i s a p ai r of t ra ns-

ve rs e l o c k i n g fl a p s. _ h elr funet l cn Is to s e pa ra t e th e canop y fabr le

fr_ poss i b le _t v_Lth the l_-As and to eause full 11he stretch-

cu tb e fo r eca nopyd e plo y.

7-9. P_ D Zsc_

Both m ain and re ser ve par achu tes are att _rh_d to the spac ecr a_ by

a device des igne _ to sust ain the p arachu te loads dur ing descent and to

disc_-_ct _he pe _achu te. _e chute is disconnected 10 -_w_es (+ 3. see-

c_) a_ter _act _Ath _ Rescue Aids S_ltch in "_TO " o_ _ 8ecc_ af ter

position ing the Rescue Aids S_A teh to "MA_ " ( a_ter l_pact) . _- ass_l_

con sis t s of _ s e p a r a t e det ails i nst _1_ l i n a mount i n g _ u re vh l ch i s

an i n tegral pa r t o f t he spac e_ r a_ t . _ e pa ra c hu t erise r i s _ a round

th e am _ h l ch tr a nsal _s th e l o a d t o the st ructurethrcushth e p ls tc _. Th e

shear p in res tr ains the piston frc _ a_ _ion te_a4_ _o dAsplace tt .

_ h e n t h e chu te _ i s cc _ n e e t s ig n al Is ec _l e _) a squib c a rtr i 4g e is f i r e d

an_ _ resu l_ e_pand _ gas fc_ces _- pisS;on fca _ard into the arm

recess_ cuttlng _he shear pin :In the proc ess. F.11 d. lsp laee_e_ t of

7-20


211/365

'_._Hmg .i SEDR 104,

pstc_ rem oves par _;;_e load. tran m_ssc_ to s_unture _ a_ the

am to ro _e around, t_e pvot pin. _he loop of _he par achute riser

slips off the ar m end the d isconne _ func to_ i8 ca_l e te. _e lea&

buffer serves to absorb e _-_gy of moving gst _ en_ preven ts rebom _

of _ p_tc_ back into the _ pos _v_.

_e reserve parachute assesb_y consists of: the pl lot chute deplo y-

gun and _s p1 _t para _ute I reserve para chute canopy _ reserveparachute deployment bag _ en_ reserve p arachute d _sconnect. _ reserve

parachute depl oyment bag ls s4u_lA_ to the main pare _h_,te deploy men_ bag

with the addition of flaps st the upper ena of the bag to contain the

_ p1ot chu' r,e, q_e reserve parachute d_ sccnnect is Identical v'J.' _

_et used to dlsccanect the m_n parachu _. _he reserve parachute cauop _"

is _entleal wth "the main pa _-_ute eau op_.

7 - 11 . PILO_ PARACS U_

_e pilot parachute is a fl_ ; eircular type_ 7 2 inches in dXe _er

wth a 30 _. bridle. It is --.ufaetured at 3. _-o.nce per square yaw l

febrlo In th e cauoP7 and 2.2_-ounc e fabrlc :in the vanes.

7-12. cruz OTto

step :In T _ae seque__n_e of re sez_e p_n 'a_hut e deplo_zent. Ei% her gas presst _e

or ma elec 'brtcal tzqp,_,,e _ cause the gun to fire, thus extmL li_ a 12-

ot_ee ]pz'o _e_.-t_ile Idlt31 is at_ aclze _ tO _Aze msez _e parachut e pilot; chttte.

% 21


212/365

__i1" _ ' SEDR 104

_ h e pil ot c hut e I n fla t es a nd i n t urn _,I I. out th e: res e r ve

c hut e, ccm p le t l n g th e s e qu en c e . Wh e th e r f i red e lec tr lea_ or pneu-

ma t l ca_, a c_e -s ecc_ d time de l a y i s pro vid ed b e t we e n r ece ipt of th e

end de tonat ic_ of t h e mal n c h a r g e , q_S de lay pe r mit s t he ma4n

parachu te (if dep loyed and dam aged) to sepa rate frmt the spa cecr a__ to

avot_L ent anglmnen t vA th the reserve p ara chu te to be d e p l oyed . _ g u n

i s ba si c all_ a t u b - l a_ bod y _ n l ch cc nt al n s th e mai n f i r i ng eart rid ge

and the pro _ect ile as sm bl_. _e pro ject ile as e_a_l y is he ld in place

by a p i n wh ic h is a he a r e4 _ h e n th e pro jec t ile Is expelled . _ e ma i n cart -

r l d ge, wh ic h _ner ate8 the gas pr es s u r e t o ej e ct the proj e cti l e, is f i r e d

as f o l l mm: ( i ) Ga s pr es sure , thr o u g h +-_ ,. gas f ir ing :ec _antm (s_ ppl le_

wh en RESER VE P ULL-R I _ is op e r a t e4 ) , d rives a f i_ p i n i nto th e pr im er

ca p at t h e base of t he ,.a_ cartr i d g e , 4n4 t la t i n g a t im e del a y tr ai n ,

causin g a subs equent det onation of the char ge. A m_,_ m of 750 psi gas

pressu re i s r e qu i red f u r pne mmat l c ope rat l cn. (2) An el e ct r ic i_ulse

is receiv ed at th e tim e _ el a_ ig n i t e r I n s t a ll _ t hro u gh th e si_e o f the

gun . A_ t e r a c_ e - s ecc_ d d ela y , th e ig n ite r f i res t h r o u g h t he wa ll of th e

mai n car t ri d ge a nd _e tc _ate s i t i n s t a n ta neo u sl y . F i_ c h a r ac t e r ist i cs

o f the ig n i t e r ce rtr i d _e a r e a s f o ll ows: A ll F i r e Curr e n t 2._ sto p s p e r

bridge, A]] Fail C_+_nt 0.5 a_ps per br td_e, q_ i_nttton elr cutt con -

si st s of t wo i nd Avi_ u a l br i dg es t er mdna ti n _ i n a _- p l n r ec ep t a c le . _,_ z _e

v elocity o f t he pr o_ ec tl le is 2 5 0- 3 00 ft / se c.

7 - 1 3 . P .mm'm mmm,- _ : " ; ._ z _ = = _ = -

" Figure 12 -12. Bea con System Data Fl ow

' 12-22


289/365

WC I_ON_mLL SEDR 104

Before _n_il leal drop , _h . tele metry tranmttter and its power

suppl y receive 04 VO ltS d-c t _on the Ymtn PTe-mpact bus throt _h the

e_er81zed Ground Te st Umbilical Relay t nczmaZ _ open co ntacts. _h_ S

r e]J _'s soZenold ts energzed +_,_h- 'Ott _the ,__l]_cal unt il the ,m_i14caZ

To sl lence _he _4 tra _4tter , the astronaut may pla ce _he te lemet ry

svlteh In the OFF posi tion whleh w1 11 preven t 2It V d-c power from reachln8

the transmitter. PZaclng the telemetry m r ltch in the ground c _and

posltlc m enables a signal fro m the 8round to energtze the telem etr y

o.,_;_-_, ,d relay vb.l.e.h will app.1_ "power to the tranm_ tter. _he elgna l

ls pro gra mmed to la_t _ mlnu tes an _ then it is rem oved shuttt _ off the

telemetry _ans _tter. The tr _4tter wlZ 1 r _ , In o ff u ntil c_=mnded

ag aln b y _ ro u nd c.-._-. -_ ._ - e CONT posl _ c _1 Of _ e _ .w _ 3 _ / s witch

appZies a_t tnuo _s pow er _o the _ +_-_-_ter.

Code_ Ins _ taticn Inf _ raatl o n is m _ p l iea fro: the lns_w*utati _

P s_ mSe _ " , aua usea t o frequency _; : _ ,te _ he tr _ tter. (See _ he

_ u _ a _ 1oa Se _ tlon XIV of thls : _ usl).

BY po wer output Is re 4 to the _ :nl%Iplezer where I t is r o u ted

throush the entm _- svlteh to +_-_e_ -In "oiccme or _Y re covery ant enn a.

32-17. C-B _ BF_C_

he C-Bsn _ beaccm is a transponder _tt cc _lstln8 of 8 receiver and

tr a-_4_ter operatu8 on a frequen cy of epprcnclaa _e3_ 5_00 to _900 MC.

_he beaccet ls _mbZe p ,,l_ed and ls comp ectlble wlth modlfled FPS-1 6 r _ a: -.

Upc= gr ound c _ad _ thr oush th e eo_an _ r eceiver , or by astronaut select ion

1_23


290/365

_O_NffLL SEDR 104

of the CO NTpositiou of the C-Ban _ beacc _ switch , the beacc _ receiver i s

en er g ise d . I nt err og ation b y ground ra da r will t h e n r e s u lt i n a e ode a

re p l_ fr on th e b ea cc _ t ra n s mitt e r . Xnput p o wer is f ro m th e mai n p re-

i_ac t 2 4 v o lt d -c bus through the be ac on rela y conl;ro].l-- _l by th e

comm=_d re c e iv er , or , f o r c on ti nuott s ope ration_ t h r ot _ _ C-Band

b eacon swlt ch . A n OFF po siti on o f the C- Ba n _ b eacon s wi t c h is al so

prov ided. (S ee Figu re 3 2-3.2).

_e C-Band be acon a ntenna connec tion is %b roa c h th e C-Band po wer

divider to the _ C- and S-B an_ Beacon antenna s. A phase sh ifter

is used be tween the C-Ban _ Power Divider and one C-Bend Antenna %o

pre ven t nu lls in the raala t ion p atter n .

12-18. S-_:._BN-_C05

_ h e S- Ba n _ be a co n Is a t ra n s po r t er , m_t co _ s lstl n g of a rec e iver

a ml t rans mitter. (_:= Figure ]2- ]2 ). _ h e un i t operates on a frequenc y

of approxtma te_V 27 00 to 2900 MC and Is double _,_l ,,,ed t o reduos pos si -

b iliti es o f u nau t hor i zed I n te r r o g a ti on . _ h i s unit i s os p ati ble with

gro und based Ver lo_t R adar s and oper ates at a positive accept ance

to le rate o f + 0. 5 mlc ro -se cond _ s n _ a pos itive r e_ e ctl on %o ler mac e of

+_ 1 . 8 _ t or o- mcon d s.

Power @ rcu te, interrogation and repl_ are the s_e as the C -Ben_

kacon , e =p hBe a c on a nt e nn a con ne cti on is thro _h the S-Band Powe r D ivi der to

thr ee " C" and "S" Ba n _ Beacon a nt e nn as.

12-24


291/365

_IIICDONNELL SEDR 104.

_z z_

12 - 25


292/365

_MCDONI tlELL SEDR 104

m, /m,TWo recovery beacon s are eomb ,-_t ln to o_e uni t. One beaco n operates

c_ hlsh freq uency , whlle the other operates c _ ul tra high frequency. Both

are energized t o provlde radlo signals for recovery direct ion flnder equip-

Be HF recover y beac on opera tes on a frequency of appr n_m -tely 8 MC

wlth a tone modula ted ou tput. It is powered by t he 12 volt standby b us

thro ush the t:pac t relay end 18 energized upon landi s . The RF power out -

put ls fed thro ugh the re scue dtple xer _o the elevate4 HF Recovery Antenna.

Be _ recovery beac on opera tes on a frequen cy of approxl mate _7 243 MC

wl_h pulse mod ulation. I t ls powere a by _ 6 volt isolated b us t_lTC.,dh t _e

antenna lettin g separa tion re lay. _ht8 c ircuit is energtze _ when _ an tenna

fatrtn8 ls Je_ttsc _. _he RF power outp ut ls fed thro ush the aDten-a multl-

ple=er an _ the anT_ m-n s witch tO the UgF rescue ant enna.

12-20. _In_.T_ RES_JE

_he Aux. Rescue Be acon opers tes on a frequency of appr -_m-_el_ _4 3 MC

with pulse mo _ bala t l on . I t I s p o wered by th e 6 v olt standby bu s thr o u sh the

An t _ --- Fa ir l _ Sepa ra tl on Re lay. _ he se c ir eu lte are ener _ zed a t ante nna

fairing separa tion . _he RF power is radlated frnm the Aux. Rescue Beac on

_. (See ns _ 2-12).

12 -2L AWTmNAS

12-26


293/365

WOOO NNILL $EDR 104

A b ico_ea l an tenn8 28 used for pre-launch_ launch; orbit a _ 4n_tie2

re-entry phases of "the________nte nna f airing and is loc ated o ve r "the open end of tim r ec overy syste m

cc e_a rtm emt of ' the c _lind_cel sp acec ra_ a _e terbody . _ bico_cal

8ntenna serves 'the HF n,_ UHFvot oe rece iver- transmt _ter8 s the c.--_,n _

receivers , anti the telemetry trsns _Ltter8. _ ac_lve elemnt o f the

bioc _ca l antenna f _s the upper port ion o _ the antemm fa _r _ag _htle

the lo ver p_c_ of the f air ing a _l the spacecra _ bod _ fm the groun _

plane for "the en te_nA , (See _ 12-13).

A _ _ 28 used fca" the _ _Ae e of re-entry; land ing

rescue. It; 2s a compact a ntenna loc ated, cm the open eu:r tace of

meovez7 syateus c_m _-_ent. The antenna 8 fo lded _en the m _;emm

fS_T_ '_ B :l.nfft._11*iL _ 8eCOolld8 8 _ th _ f_ t8 ,_0'i _tt8C8 _

the UHF r ec o ve ry a n te nna i s e r e ct e d a n _ serv es t h e t _ F v o i c e r e c eive r.

t r a- m._t_e rs ,t h e UHF por ti on of th e re c o v eryb ea co n, t h e _: - -an d r e-

c eive r s, a nd th e tele_ e t r _t ran smi t te r . (S e e F i gur e 12 -6 ) .

1 2_._. MA IN BICCffEBF D_I_OLBAHD _ F RECOV_ _ F_

_ h e va r i ous r a d i o sy sta_ a re e c _ to th e b l c _ n e a nt e nn a, th e

_ F d i po le or th e U_ F r ec o ve r y a nt e--a i n th e fo l lo _ ru nn e r : (See

12-27


294/365

_MCDONNIILL SEDR104

(I) 'me HF voi ce rece iver-tr _--m_tter antenna l eads are ccmnected

to the HF _ S BLECT _ coax ial switch which _nen p laced

in the fo3.3.o_ __-_ positions feeds the antenna systems as fo!_s:

(a) _ posit ion , HF recovery ante --- thro _h the reco ver y di-

p]_xer.

(b) BICUNE posit ion , the bico ne antenna throu gh the main m_l ti-

p le_er and the antenna sw_ t c h .

(c) DIPOL E (ORBIT O _LY) posit ion_ o _ HF d ipole ant _ma on

the recto pa ckage.

(2) _ O_ r ecelve r - tr e n _ qtt e r an ten n a le a d i s c onn ec t e d _ th e

mai n w, 1 _I pl e_ er , _ o th e a nt e nn a nl t c h who se outputs f eed s th e

b lce ne a nt e n n a un %il a n %4 _m_ sep a r a t lm . Aft er a ntenna sep a-

ra tio n th e d e s ce n t ant e Dna i s f _ l .

( 3 ) _e c_ l r eceive r a nt en na le a d i s eca n ec t e d t o th e a nt e nn a

mult Ip le _e r .

(_) _ Lo v fr e qu e n t 7 t e l _ . _ r y tr a ns mi tt e r feed s d _ r ecltT t o th e

antenna mt ltip]_er.

m

_he ant _" - _,_tiple_er enables aimc ltaneous or i_I:Lv_Aua l operat ion

of the ra&to syst em- using one antenna . EfTect ive_y th is is a ra alo f_e-

_Cy _un ction b ox v_tch a llows severa l re ceivers an _ tr --_tters o

oper ate s lm u l tan e ously _ hout I n t erfer e n c e wi th each othe r .

cc_ n ectl on o the antenna i s e_ h 1;he e nte-n a sw _tc h to el th e_ _ a e

12-28


295/365

W_i I.L SEDR104

_ic on lc a l a n ten na , or th e t _ F r esc u e an $_-_na. _e an t e nna s wi_ .h i s

o p e ra te d b y th e a nt e nna fairi ng s e p a ra ti on r elay to c aus e th e au tnmatlc

_ht_t t _Cm _ mai n am_ezm s to the U _ res cqze ant emm t _c_ an te mm

J ett l sm Fig ur e

An ant e m_ I s provldml to p ermit _ r adAo tra_e s lcn and r ec ept l o _

a1_er ] _z_. q_, a nd_nna t8 a teles coping _ip a n_zm a vhloh is auto-

mat el a l_ e xt e nd e d by a pyrot e_ c a ft e r _mpa ct . On ce e xt e n de d , th e

a n ten n a i s u ses fo r t_e HF v o ic e rece l ve r -t r a_m_tter a nd t h e HF po rt ion

o f t h e r ec o ve r y b eacon.

_ h e HF rec o very b eacc_ fee_s th r ou g h the rec o ve r y d lpl e xer. _e HF

v oic e rec e iver-transmitte r is fe d t hro u g h _ po siti on o f t he m a_ ANT

and then into the zeeovery diplexer to the HF _aip ante---. _ h e

dAple_r _ e_,,ltaneou s or in_tvid ,m_: operation over a sing le lea d

12_._. C AND S B_D A_Z_AS

m_ee C- a_l S-Bau_ antenn a uni ts are installed i n _he spacecraft

str u ct u re f_r +_e C - a_ S- Ba_ beacons. _ he_e ,,,_tsare e qu al_ s p aced

abou t t_e ctrcm _erenee o f th e ec_ lcal sect tc_. _ach a z_enna un it con -

sists o f on e h elix as a _- Ba n _ a n te nn a a_4 _ he_Y as an S..Bm _ _te nn a.

_te nn a lea_s f rom the C- Ba n _ m_ S - Ban_ b eac_ are _ ou te_ t h r oug h

_ i_vid_el pca_r d ivi d er s tO the t h ree ass o c l ate_ h e 1 _- onte--as. ( See

12-29


296/365

_ONNBCA. SEDR104,

An HF Dipo le a nt e nn a is u se d wh ile i n an o r b it cond itl o n. _ h e

d i po le ant e- -- c o ns ists of tw o u n itsj on e attac h e d t o eit h er side o f

t h e r e tr o p ac k age. _ h e activ e e _ts c o _ Is lst o f t ubular ber y11' h,,_.

c opp er ri bb o n s. _e rib b on s are r o lle d i n a flat c o n d iti on p ri o r t o

o rbit. Upo n reachi n g o r b it, a sq ui b i s fire_ on the di po le a n t enn as

aasa_lies, t o release th e active el e men ts a nd allow t h e m t o un r o ll a nd

bec o me tubu lar in a n e xt e nd e d c c _Ition (See F ig u re 1 2-13).

12 - z9 .

12 - 3 o .A i o

_e a u di o ce n ter pro vi d e s tra ns i s t or iz ed a ud i o s_ p liflers, a v o ic e

op erate d rela_ ( VOX), a n a u di o filter, ta p e rec ord er c ont r o l circ,xlt r y

a n d trans mitter c ont rol circ u itry. (See F ig u r e 12-7 ) . Al l c o mponent s

are contained in a ligh t weigh t, foem en capm , l_ted --_t .

Two fi xed gain heads e t _ pl i f ie r s ar e u s ed to b ri ng aud io s ig n a l s

ep t o he ads e t l e v el a nd f e e d the he a ds ets s ep ar a te l y. Two f i xe d gain

smpl ifier s are p rovide_l to increase the dy, =_c m icrophone outpu ts to

a leve l s uita b le t o be used w ith t he vari ous tran s mitt e r s .

A l o w p a ss f i l tar, with a c u toff f_ f r e qu e n cie s abov e 3 000 c p s,

fi l ters t he aud io suppl ied fr _ the c_ rec e iv e rs. Ou tpu ts fro m

t h e fi l t e r is fe d t o a v ariab l e ga in_ com ma nd au d i o a mpl i f ier.

_ e " v o ice opera t ed relay " is a translst u r I z e d s_ p ll f i e r wit h se p arat e

a_usta b le t h res ho l_ l ev el and re l ea se ti me contr ols . _e a mpl ifi er

12-30


297/365

_,mqC J _NNEI, ,L SEDR 104

owrates a rel ay to pr ovide a gro und ing c irc uit for tran m-ttter ke ying.

_his --tt p ar allels the extern al PTT switch.

_he au aio cen ter fur __a_s a circu it to app l7 the key ing grom _

po ten tial to _e tr ansm itters. Each c ir cuit i s pro tecte_ from the

res t by a diode .

A rela y is insta lle_ in the aud io cen ter for supp ling pover an_

audo signa ls to the tape recorder. In the de-ener gized conditl_, the

re lay cl oses s c ir cuit to the tape recorder inpu t, thu s aud io r eceived

by the sp acecraft is r ecor ded when ever _nRtr umen tation pro _cmas tape

recorder opera tion.

When the m icrophone sv itch or VOX is opera ted , the tape r ecorder

rela y is energi sed if VOX operation o f tape recorde r is se lected . One

set of closed relay con tacts nov c __ple_s the recorder po wer circ uit

indepen _en t of instrumen tat ion l_c_r aw_nS, _nile a second set of

conta cts rou tes signal fro m the microphone a mpli fiers to the recorder

The cir cuits in the audio center opera te d irec tl_ from the spa ce-

craf t 24 VOlt d-c i_pu ts with no furthe r re_ tlatton or voltage incre ase.

The audio con tro l panel pruv des contro ls and circu its for the aud io

signals of the var iotts spa cecraft receivers (see F i_tre 12- 7).

The HF and I _Y ci rcu its are rou ted through ind ividu al T-pads to

vol_ne control s. _e _F circuit has a s ingle vol_ne con tro l, the stone

is true o f the _F c ircu it, _htle sepa rate vol,m- contro l is pro vided

1 2 - 3 1


298/365

_NItI|LL SEDR 104

for the cm--_ a,_ o circu it. Fxed l _uts are used for the alarm

tone and groun _ tnterphone circuits.

_he panel also conta ins a m r l_ch override f _ the impact ke Tlng

feature used with the _HF tram _tters , mzt _TInK butt _ on th e pane l

to _nt _,_ ___e tel_etr y B+ s,ppl_ to provide ezer

NASA Mercury Spacecraft Flight Manual

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