Vibroacoustic and thermal environment data gathered from the first three flights of the space shuttle are presented. The characterization of the particulate, gaseous, and electromagnetic emissions associated with the shuttle flight is emphasized. Measurements of vehicle glow light emissions and material effects (mass loss) due to the low Earth environment interactions with the shuttle vehicle are presented

Leger, L. J.

Miller, E. R.

English

NASA Technical Reports Server

INTRODUCTQRY COMMENTS 
L, LEGER 
E. MILLER 
The f i r s t  two days of t h e  workshop w i l l  c o n s i s t  of d a t a  gathered from the  f i r s t  
t h r e e  f l i g h t s  of t h e  Space Shu t t l e .  I n  order  t o  l i m i t  the  scope of the  
meeting, on ly  summary d a t a  w i l l  be presented i n  two areas; the  v ib roacous t i c  
and thermal environments. 
are being planned f o r  t h e  near  fu tu re .  The emphasis of the  meeting w i l l  be the  
c h a r a c t e r i z a t i o n  of t he  p a r t i c u l a t e ,  gaseous, and electromagnet ic  emissions 
a s soc ia t ed  wi th  t h e  S h u t t l e  f l i g h t .  Data as generated through t h e  use of t h e  
Induced Environment Contamination Monitor (IECM) p re sen t s  the  l a r g e s t  base 
s i n c e  it was c o l l e c t e d  on STS-2, STS-3, and STS-4 f l i g h t s  and the re fo re ,  a 
l a r g e  po r t ion  of t i m e  has been a l l o c a t e d  f o r  these  presenta t ions .  A s  an a i d  i n  
i n t e r p e t i n g  o the r  r e s u l t s ,  a s h o r t  summary of measurements of "vehic le  glow" 
l i g h t  emissions and material e f f e c t s  (mass l o s s )  due t o  the  low e a r t h  
environment i n t e r a c t i o n s  wi th  t h e  S h u t t l e  v e h i c l e  w i l l  be presented.  
An important cons ide ra t ion  i n  planning the  workshop was t o  schedule it  as soon 
as p o s s i b l e  a f t e r  f l i g h t  t o  a l low as much t i m e  as poss ib l e  f o r  f u t u r e  payload 
planning. A s  a r e s u l t ,  t h e  p re sen ta t ions  are i n  viewgraph form. Also,  be 
aware t h a t  a l a r g e  po r t ion  of t h e  da t a  to  be presented is pre l iminary  s i n c e  a 
cons iderable  amount of d a t a  a n a l y s i s  remains t o  be completed. 
More ex tens ive  p re sen ta t ions  of d a t a  i n  these  areas 
1 Preceding page blanK 
A-7 
https://ntrs.nasa.gov/search.jsp?R=19830014023 2020-03-21T03:44:45+00:00Z
MEETING DEFINITIQN 
a OBIECTIVE-PRESENTATION OF DATA W I C H  RELATE TO D f f  IN IT ION OF ENVIRONMENT ASSO- 
0 EMPHASIS 
CIATED WITH SHUllLE FLIGHT AS DERIVED FROMFOUR SHUTCE FLIGHTS 
* M J O R I T Y  OF DATA PRESENTED WILL ADDRESS THE OPTICAL E N V I R ~ ~ E ~  (IVUXECULAR 
@SUMMARY OF V I  BROACOUSTIC, ELECTROMAGNETIC INTEREFERENCE AND THERMAL 
8 PAYLOAD MEASUREMENTS OF SOME THERMAL AND ELECTROMAGNETIC ~ I R O ~ E ~  
AND PARTICULATE) 
MEASUREMENTS MADE US I NG DEVELOPMENT FLIGHT I N S T R U M E ~ A T I O N ~  
0 BRIEF DESCRIPTION OF AMBIENT OXYGEN EFFECTS PRESENCED AS A I D  IN INTERPRE- 
TATION OF OTHER MEASUREMENTS 
HELD EARLY NEXT YEAR 
* NOTE: SUMMARY OF ALL ENVlRONNlENTAL DATA TO BE ADDRESSfD AT MEEVf NG TO 8E 
In the 1974 timeframe, a set of contamination requirements/goals were developed 
for the Shuttle by two working groups; the Particles and Gases Contamination 
Panel and the Contamination Requirements DeFinition Group. These two charts 
summarize the requirements that were developed. 
discussed i n  detail here but are presented as a reference and to point out that 
considerable planning was conducted t o  ensure that the Shuttle would provide an 
acceptable measurement platform for a large majority of payloads. 
The requirements will not be 
A-8 
SUMMARY OF CONTAMINATION ZILCIFICATIONS AND MUJURLMENTS REOWIREMLNT8 
?RELAUNCH THROUGH ASCENT 
I cD1 I I I 
I 1 I 
((ow-VOLAIILI I l S l O W  
INVU OEIOII11o* 
W I G E  G U  C I O W C I  LESS THAN le4 
e e - 2  comofwsimLts ow SURFLXCI I I CDI 
c a s  
0 1  
I 
SUMMARY OF CONTAMINATION YLClFlCATlOIl 
A N 0  MEASUREMENT REOWIREMENTL 
ON ORBIT 
I I 1 
I c* 
W L E C U L A I I E T U O N F L U X  
YOLECULAI OECOI111ON ON AN 
fiMBILN1 SWlFACL 
MOLECULAR OEMSITION OM AM 
MOLECULAR OEPOSITIONON 4 
AMBIf W l  L U I F  ACE 
C)IIOGEWIC SURFACE 
ofanaowiow or WKIL wamcss 
C. DS 
C1.C 
C.0.E 
CD.t 
A-9 
E s s e n t i a l l y ,  a l l  d a t a  i n t e r p r e t a t i o n s  t o  be presented i n  the workshop are 
dependent upon miss ion/vehic le  parameters. This  c h a r t  suinmarizes the major 
parameters f o r  t h e  STS-1 through STS-4 f l i g h t s .  
fo l lows:  -ZLV, -Z-axis of v e h i c l e  pointed t o  t h e  earth (payload bay t o  the  
earth);  Y-POP, y-axis perpendicular  t o  the  o r b i t a l  plane;  -XSI, -x-axis s o l a r  
i n e r t i a l ;  PTC, pass ive  thermal c o n t r o l  a t t i t u d e  (veh ic l e  r o t a t i n g  about %-axis 
a t  4 RPH). 
Acronymn d e f i n i t i o n s  are as 
STS MISSION DESCRIPTION 
STS-1 STS-2 I 
MAJOR -ZLV. Y-POP 
ATTITUDEW PAY LOAD -2LV. Y-POP 
BAYTOEARTH 
DEVELOPM~ZNT 
FLIGHT OSTA-1, 
PAvLoAo's' INSTRUMENTATION IECM + DFI 
I I tDF1) I 
STS-3 
3-22-82 
192 
3p'*360 TO -230 
241 (130) 
TAIL TO SUN -X SI 
NOSE TO SUN 3 AXIS SI  
BAY TO SUN 3 AXIS SI 
PASSIVE THERMAL CONTROL 
PTC 
W 1 ,  IECM AND DFI 
STS-4 
6.27-82 
168 
306 I1661 
TAIL TO SUN 3 AXIS SI 
BOTTOM TO SUN 3 AXIS SI 
TOP TO SUN 3 AXIS SI 
PTC 
GRAVITY GRADIENT 
-ZLV 
W D  82-1. IECM AND DFI 
A-10 
This c h a r t  con ta ins  p i c t o r i a l  d e s c r i p t i o n s  of the major a t t i t u d e s  used dur ing  
STS-1 through STS-4. This  c h a r t  a long with the  mission d e s c r i p t i o n  and STS 
f l i g h t  mission t ime l ine  c h a r t s  are to  be used as references  f o r  t he  o the r  
p re sen ta t ions  during the  workshop. 
ORBITER ATTITUDES 
TOP LV, p = 30° 
(-ZLV, t x S ,  . 
SUN 
NOSE SUN, Q = O o  
(+ x SI, Y POP) 
PTC, p = Uo 
(X  ROLL, X INERTIAL) 
c 
SUN 
TOP SI, p = 60' 
(-z SI) 
SUN 
TAIL SUN, 1 REVIORB. 
- X  SOLAR, -2 SPACE 
p =45* 
L 
0. 
c 
SUN 
TAIL SI, p = Oo 
(-x SI, 2 POP) 
Addit ional  d e t a i l  of v e h i c l e  a t t i t u d e  is  presented i n  t h i s  cha r t .  E s s e n t i a l l y ,  
a l l  of t he  a t t i t u d e s  f o r  STS-1 through STS-4 were se l ec t ed  f o r  system 
performance assessment r a t h e r  t h a t  payload pecu l i a r  measurements. As such, 
t hese  a t t i t u d e s  and o t h e r  ope ra t iona l  condi t ions  do not r ep resen t  the  best 
condi t ions  ( l o w  contaminat ion)  poss ib le .  
A-11 
STS FLIGHTS MISSION TIMELINE 
SUMMARY 
MET lHRSl 
0 15 30 45 60 75 90 105 120 135 150 165 19 
I I I I I I I I I I I I I 
I 
lSTS. 1 
-2LV YPOP -2LV YPOP I I 
TOP SUN 
I 1 TAIL S U N A  k- 
I 
ISTS. 2 
1 
[--'-pxq PTC I NOSE SUN I TOP SUN 
-2LV NOSE 
I TAIL S U N 2  L TOP SUN 
I 
ISTS.3 
I 
I '  
r 
STS MISSION DESCRIPTION 
STS-1 
ALTITU'E 240.278 (130*160) 
km(N. N I.) 
MAJOR .ZLV. v-POP 
ATTITUOE[S) PAY LOAD 
8AY TO EARTH 
TAIL TO SUN 3 AXIS !3 
BOTTOM TO SUN 3 AXIS SI 
TOP TO SUN 3 AXIS SI 
TAIL TO SUN *X S I  
NOSE TO SUN 3 AXIS SI 
BAY TO SUN 3 AXtS s1 .zLv. Y-PoP 
PASSIVE THERMAL CONTROL ___ Z i V  I 
r ib  
GRAVITY GRADIENT WC I I DO0 82-1. lECM AND DFI I -1, fECM AND DFI I OSTA-1. IECM + DFI 
A-12 


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