Five accelerometers mounted near the adapter base of the Titan 3-C launch vehicle and three on the hub of the ATS-F spacecraft provided (1) data for verifying basic spacecraft mode shapes and frequencies during powered flight while attached to the launch vehicle; (2) failure mode detection and diagnostic information on in-flight anomalies; and (3) data to be used in the design of future spacecraft to be flown on the Titan 3-C. Because data from the instruments mounted on the spacecraft hub passed through an in-flight disconnect at the separation plane between the transtage and ATS-F, the moment this connector was broken, the signal to the telemetry system showed a step function change. By monitoring these telemetry traces on the ground at appropriate times during flight sequences, a positive indication of spacecraft separation was obtained. Flight data showing dynamic response at spacecraft launch vehicle interface and at the top of ATS spacecraft during significant launch events are presented in tables

Honeycutt, G.

Lindner, F.

Mattson, R.

English

NASA Technical Reports Server

General Disclaimer 
One or more of the Following Statements may affect this Document 
 
 This document has been reproduced from the best copy furnished by the 
organizational source. It is being released in the interest of making available as 
much information as possible. 
 
 This document may contain data, which exceeds the sheet parameters. It was 
furnished in this condition by the organizational source and is the best copy 
available. 
 
 This document may contain tone-on-tone or color graphs, charts and/or pictures, 
which have been reproduced in black and white. 
 
 This document is paginated as submitted by the original source. 
 
 Portions of this document are not fully legible due to the historical nature of some 
of the material. However, it is the best reproduction available from the original 
submission. 
 
 
 
 
 
 
 
Produced by the NASA Center for Aerospace Information (CASI) 
https://ntrs.nasa.gov/search.jsp?R=19780025153 2020-03-22T02:04:52+00:00Z
iATS-6 FLIGHT ACCELEROMETERS
Roger Mattson, George Honeycutt, and Fred Lindner
NASA Goddard Space Flight Center
HISTORY AND OBJECTIVES
At the inception of the Applications Technology Satellite (ATS)
program, two flight spacecraft, ATS-F and ATS-G were scheduled to be
launched on two Titan III-C launch vehicles. This was the first time
a NASA unmanned spacecraft was to be launched on this vehicle and it was
deemed necessary to acquire flight data regarding payload environment.
A study of the types of instrumentation that would be applicable
was performed by the ATS Project Office. The review consisted of
defining the type of instrumentation such as accelerometers, strain
gages, and acoustic microphones, and the mode for using such
instrumentation as well as methods of transmitting the acquired data
to the ground stations. The purpose for flying the instrumentation
was as follows;
1. Provide data for verifying basic spacecraft mode shapes
and frequencies during powered flight while attached
to the Titan III-C vehicle. Data was to be used to update
and revise the structural analytic model of the ATS-F
and -G spacecraft,
2. Provide failure mode detection and diagnostic information
on in-flight ^tiomalies.
3. Provide data that could be used in the design of f Lit,r^e,
spacecraft flying on the Titan III-C.^	
,.>
(x l 11 1, 13C Al)--/M y A01	 C SC L 01D	 t
it	 iY
1e
1
i
I	 I
I
j;
:t
r
^-	 ----
^ft'4 '=NeiI j	 't	 i
As a result of the ATS-F project study, the accelerometer system
	
^I
shown in Figures 1 and 2 was baselined and selected for the
ATS-F spacecraft. Basically the NASA Project Office was responsible
for providing the accelerometers to be mounted on the spacecraft
as well as one accelerometer mounted on the transtage interface
ring at the adapter interface with the spacecraft. The launch
vehicle contractor provided the necessary interface wiring between
these instrumentation points, the signal conditioning equipment and
a means for telemetering the data through the vehicle telemetry
system to the ground stations.
As the program progressed and ATS-F operational requirements were
reviewed, it became apparent that the accelerometers mounted to
the spacecraft hub would provide a valuable source of data for
indicating when the spacecraft had been separated from the
transtage. Since the data from these instruments was passed
through an in-flight disconnect at the separation plane between
I	
the transtage and ATS-F, the moment this connector was broken
the signal to the telemetry system would show a step function
i
{	 change. By monitoring these telemetry traces on the ground at
the appropriate times during flight sequences, a positive indication
of spacecraft separation could be provided. Since the ATS-F had
no other positive (direct) means for indicating separation, this
i
particular data source was extremely valuable for subsequent
operational plans.
' 1
j
i
i`
1	
'.
'I
•	 .,
-2-
ORIGINAI, PAGE, I:
' P( h ►N Qj TALITY
HUB
— A C--ELERO',%oIETE RS
STN 77179
ACCELEROMETERS
wj	 1:_-	 ^	 .	 r'.-.^	 ^ ^ _rte ^^	
^^ ^
7
 _"^.'7.^ "7Rr^'^-rFgN^-^^^w.^s
z
xY
sIC AXES
ADAPTER
9
STRINGER
s
S/C x
LV -Y
STN 77M
LOOKING AFT
	 \
kTRINGER `29
OF P	
till Al.l'^`^
TAR E-T
S/c	 Lv
+Y	 Z
F i;;U ,-e 2. A-Ws Definition :uui .Accelerometer Location
^	 t	 N1	 t
a
1
s\ s vI-:'M 1 1 ESCI%IP H( IN
\t't','It`l', t tlit ` 1t`t' I ) , • ^,'1'littit til : Intl 1.00;1titlll
V ivo ;il't't'It`l',1lllt`lt'1': : \\'t'I't` 111Ulllttt`tl t,ll 1!1, 1 l:ltlllt'll \ t'!llt'It' 110:11' 'It' ,t,l;lillt'I'
;1111 Illrl't' on lilt` ,il;l,'t`t'l':Ilt 11111).	 t';1111t' I Il,t:	 t!lt' ; It' t't`lt'I't`II It , lt`t'ti \\TIII
1!WiV kik'Sk . HO ion ;Illll ('imiI't' f .illtl \1'. lllt'il' 1't`l:lll\'t' to :Itioll:.
Data .\t'tllli-,ititl,l ^  •tt'In
t'll,` :;t:','lal^ !1'l t Rl llit'^:t` ll;lil::,lilt'c`l'ti \\'t't't` t't ,!ltlillt`at`tI all,l tl' ;ul:;llilltt'tl \ 1;;
tilt' l'It:ul 1:111t1t'll \ • t`lllt'lt' s -h:llltl I,' It I IIlt`11'\' :4)'stt`III.	 This tl:lla \\':1`, I't't't t ll10tI I,\
I - i:It0	 l'tli.tltl ,a;: t t MIS 'l';tI ll"	 'lt 	 l'lilt' t'tt, t 't`, .'t`11f to
t ll,;llt l'c`lilt`l' (li^l 'l').	 1'Ilt'st` \\'t`i't' lllc`;1 tIt't'ttlllilllllatt`tl lU :I f^tl'lll;lt t'ltllllt;ISlftlt'
\\'lt!1 lilt'l' an:ll^::i:: t`tlUli'lilc`llt, 	 flit` tl;lta \\';ls rt`tl11L. vtI to tiItt`t't`ll tl;t illt,,;lal,ll
tinll' Ili: tJl'Io	 I. :ltl;ll\ :iti,
1''I,ltII1l' H, VSI , I I'*-
Intoll:it't` i):lt:l
Hit` (lt,;llt k ;:l:: \\;1:: ;ill :ll\.'t`tI It , t t l t l:tltl i't`^ih^ll^t` :Il till` llllt'1'I:tt't` alltl ;It lllc`
Ittit ttl tilt' s 11 : W t`,'1.1t1 tl lilt I). 	 f';II I I;'	 Itl'(':;, ' IIt:; :1	 ;tlIII Ill ;li'\ - 0f lilt` \ • tt 1 1- :11i(Ill i'l•c;httllst`
tl:lt:! lt,l' sit;llltlt';IIII I;!llll,'ll t`\Till: : :II 111 ' . liltt`l'f:It',' 1 1 01\\'t't`ll tilt` A VS - t •'	 i nct't't';lft
;ltttl tht` ' I ' il:ln 111	 l • \ t'llit' It , .	 N,tlt' lll;ll till:	 i:; Ilk` \' it , 1 - :11it'll 1'0:;	 till.	 \\'i l!1
Ilk :;tt`:Itl\	 :;tat)' . 1 , .'t'It'I . :Ittt; t. 	 VIli -; 1 1,:1t :I \\:IN 1,:11,t • II fl't t llI ,'' ,'tilt) ;l':liIII 1't`,'tl'kIN
lilt l lilt' tltlll ill :Ili t I1't',111t'lit'\' IiMod !z; :lltill't\i Ill :1tt'.	 I IIt`: t'	 ,'_ ; lltl:	 ,IV	 ;I\'t'1'.1,',t',i
1't`::iAril:;t':: tl I14' ;lt't',`10VOilll'tt'I' It rt ' .'II ' I! :II :<I:ltloll^
,
r.
1	 1
I
ti-, in
I	 ^
7	 C4	 O
(y^	 F I	 G^1	 CV	 N
ORIGINAL PAGE IS
---	 OF PU()h QUALITY
1
O	 O
A	 `
O
O u
J acs
;4
r - 	 - ------	 _
C^'
r-r
'^ O v ,V, U' V ,^ ^ ^
U
^"
c G7 W
t-
J
.gyp
ti '7o N C N
+'
r ,
U
o e^
t
'^
[
o-4 ^ r
`*,
c:
-- 1 r a O rM4
..
	 v
O 4
u
C ^^
U p
U
C
U r^ a
.^
U
U U
'UU
o v rn ^^ cn rn n Encn cfl nQ
C)
u
U U U U
o0 !7 N ^ ^, o0 CA I :i	 c yI ^ N -ao
N N
p
O
O c1
3 O 3 O ^' U
Q ,
w^ U
^	 I
UN CV
U F+ 
N ^.^+ ;24 
v
L i r;r
CD
O pN O r
t p
i^ C)
C)
p
s.
j
N
^
C1.1^
o
N
^J / C`1 N N M OD
U
N C\1
N N Cl
^. U
1
c
1	 3
1
I
l^l!
% II?:
'Cale ,
Dominant Dyivainic Response («0 llz)
at S^mcecraft-\'chicle Interface for
Silnific • :iut T„iunc^'t l-'vents
Event Accel
	 Froq. Accel. F rec,1 ^Aceel, Frei .	 II(Hz) (Ilz) (Ilz)
Lift-off 0.l 45 1. :30 0.7 .15I
2.3 70
Stake i 0.1 10 0.-1 20
Sh utdo\% ri 0.4 30 0.5 30
1.0 70 0.5 I	 50
Sta,e II 0.0 10
^
0.4 -10 0.2 20
Shutdown
I
0.6 70 0.4 40
Stai;c III 0.2 20
Second Start 0. 0.3 i0
Sta;c 1II 0.4 10 0.1 20
Second Shutdown 0.5 70 0.5 — 40 11 (l — 10
7
rl^'
Simcceraft Data
	 >
1
'.rabic 0- is a summary of the response measured at tile top of the spacecraft
Ot' lull) area fUl'l!-llitle:mt launch events. This data has been filtered through n
narrowb.md filter 	 shown at the lmttom of the table. The frequencies listed 	 ^! r
.ire the lateral fundamental nodes of the Spacecraft (S. 5 Hz) and the first
	 ?
lougitud evil node (36 llz). Also shown on this Lable is the maximum steady-state
acceleration reached for each event.
Predicted Versus Jleasured Data
Table 4 is a presenLation of the max imuall measured spaccer^lft respo• 1se	 ^ E
uonipared with the mean +2 sigina calculated values. 'These measured numbers
f
t'
are simple peals picket] off the oscillograpli shots without ally filtering ;uld the
!a
predicted data came front the alight loads analysis. Note ttl:lt in general the
predicted was higher then pleasured, as expected, since it is mem +2 sigma.
The exception to this is the 7_.-axis, stage III, second start, showing that measured
-.1:lta ewceded predict( d. The predictions for this even had less statistical
base of flight, data, thus perhaps has more error. Also the stage III on this
tli-lit could have been more rough th.m previous. Note that there were no
predictions for liftoff or stage III second shutcloan. 'These were omitted from
the program because it was believed, based on previous Tit,-Li IQ-C flights,
that these events were less severs: th-in the others, culd b01:011SC of costs consLr'aints
on the ATS-F program. As it tit rtied out the liftoff eve tit ma-, the most severe for
lateral Y-axis respons(, , This was definitely une\I)ected aal the reasons
for it ;ire not fully understood.
8
	
I	 j
i
	
1	 '
1	
j
-	 h
1I
i
i
f	 r.
I
I
t	 t
' 	1
I
I
^	 I
i
r	 `
a	 1	 ^
Pe.slx ► nsu ;It Top of A't';- . G Spnec • raft During
Si^^;niCi^ • ;ult l.:IUncil l^:t'c^nis
Vt•onl
ATS-G
Axif-
F re q,
(llz)
\'illr;Iti()II
Ilc`spolise
(^ l'^^at: c>
Stk•;Id,v	 11atc•
Accelk'rati	 II 
0.2 -0. S
I,i ftoff Y 5.5 2., 4
T :36,0 I..l
Stai;c I .l" ^..^ l,.	 1
^illltdOtt'tl Y 0„ 1
Stage II ^ S.	 , ► ().:l)
Shutdown I g.5 0.2Z :36. 0 1.	 1 •^? 3
Stage 111 8.5 ().	 1
Second St;l rt 1 8.5 o.2
'L. :1(;^0 0.5 -l.:,
tit:I^'C III X 8.5 0.:3
tircondtihutdot\ n Y 8.5 0. 2
-. ---	 7. —3(1.0 I	 0.8----- ------^.,0
* 35 - •15 Ilr Filter for Z
0 - I'2. 5 11! 1'• lllet• foI• X ;I nil Y.
ll
ii
i
1
t
I
^ ! - ! : '. k ,
	III
M.
Axis
010-111 42 siglra)
tital;'c` 11
it)
t	 '	
i	
1	 ^	 i	 t	 +
n r 	1---	 T
,d
J
dFTi.
I1;1I . :Itio!I I)at,!
; .1 PO:iltiVO illdiC:1ti0a Of SlYlCCC • 1•atl ,ii`ll:wntioll from tliv l;ltvioh velliC'll' \1•tls
•	 v.`l-i'lled hN. eun:,ultill" 1 •.`:11-tilue tli-lit ;lU-cotcrunieter data. Shurtl^ :,ftl'i the,
Solmratioll, p y rowchilic dex'iCVS M-Crc aCtll;lt.'kl ;111d th.' Sc`paratiull SllringS C' :!u.ccl
relative movemeat h tv.veu the
	 and l;tt!uc.h vehicle. This tool. tip
Sl:lcl: in tlu! tr:ulSlhiccr Cal)lc :uul sc!vrrctl the fl1'- :l^\a^ c^mu., t!)r. R'lu'n t;lis
.`velit Occurred there wns :ui in mediate .lata 1lropoul 1 •runl the spneveraft
accelerometers an.i thus au indic:ltioll of separation.
CONCi.U3Ic)NS
The prima 01)4'Cti\ • OS juStif1 • ing th.` nl`L`ci for ill Sh'nnic`ntill" . the :H'I'S-1' flight
were realized. Ulk)ii r.`ccipt of the lli;;ht data :uid its subsequent :ula1 y sis, the
fullowiug results wore attahled:
1. Sp; l.'CCraft'lauuuil VChi. • C Sep:lr:ltiun	 intli.'at.'kl
2. VCl'i11Cat1011 that the Ill;lth0111at1.':tl t 1,`C'11111C1ll1;S 11: C`d ill ihC` 10 ;1CIN
t
aualvsis were adekluate ill lW.!.li. • tilig prC.kunill:ult i'r.`(turn.'iCS an.i
t	 .Issoc'i:itvd Illaoilitlides
3. Valuably dat:l for the desi;,11 of futlive Spaeecr.ift. to ho l:uul.010d by
Titan IlI-C weve ac•quirr.i•
11
r..
n


ATS-6 flight accelerometers

Abstract

Similar works

Full text

Available Versions

NASA Technical Reports Server