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O R B I T A L F L I G H T TEST P R O G R A M . F L I G H T TEST
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REAL WORLD FULL SCALE T H E R M A L /V A C U U M C O N D I T I O N
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RENDEZVOUS
SA F E T Y ENVIRONMENT
STUDIES
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FLIGHT PATH ET FLIGHT PATH
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STS-2
STS-3
STS-4
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40,3°
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150 MM
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165 NM
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650 PSF
580 PSF
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660 PSF
720 PSF
765 PSF
790 PSF
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60 MM
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55 NM
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0
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VEHICLE
ASCENT FLIGHT TESTS POST
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0
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TANK-ORBITER OFVBITF.R
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0
SRB TO ET LOADS
0
ET TO
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T A N K OR8ITEN UHWAHU ATTACHMENT
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ORBITER INTERNAL LOADS STRUT LOADS DISS IPATION WING LOADING TAIL LOADING PAYLOADS
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FEEOLINE
DYNAMICS) WHIC
INSTABILITY
TURN
CAUSE
ENG INE PERFORMANCE,
PRESSURIZATION
F L I G H T TEST V E R I F I E S
DESIGKOF
ORBITER/ET PROP ELLANT FLOW SYSTEM POGO SUPPRESSORS
HAVE WID E PERFORMANCE
MARGINS
P O GO S U S C E P T I B I L I T Y ,
TERMS
FILl/ORAfM DISCONNECT
L0
FIll/DR/MN DISCONNECT
O R 8 I T E R / E X T TANK L0 DISCONNECT
OR8ITER/EX T TAN DISCONNECT
W-/0
ORBITAL FLIGHT TEST PROGRAM
ENVIRONM ENT
C H A R A C T ER I Z A T I O
WHAT
MEASURED
OSTA, DPI.
ACOUSTICS
MICROPHONES
VEHICLE FLEXING
S T R A I N G A G E S/ V I S U A L
FREE
P H O T O - STERO
PARTICULATES
OUTGASSING
ORBITER
ORBITER
IECM
Q U A R T Z C R Y ST A L M I C R O B A L A N C E S SAMPLES
IECM
IECM
MASS SPECTOSCOPY
SAMPLE ARRAY
IECM IECM
THERMAL
TEMPERAT URE MEASUREMENTS
VIBRATION
ACCF.LEROMETERS
OSTA, DFI, ORBITER
SHOCK/ DYNAMICS
ACCELEROMETERS
OSTA, DFI, ORBITER
WHY - DEFINE
R E A L P A Y L OA D
FOR THE DESIGN
ENVIRONMENT FOR THE ANALYSIS
ORBITER
PAYLOADS
RESPONSES
FUTURE PAYLOADS,
W-ll
ON-ORBIT F L I G H T TESTS
DATA COLLECTION
POST if
T H E R M A L CONTROL SYSTEMS POGO STAB ILI TY ELECTRICAL POWE
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SYSTEM
CONTAMINATION MONITORING •1
P A YL OA D B A Y E N V I R O N M E N T ENVIRONMENTAL CONTROL SYSTEMS
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X
COMMUNICATIONS
TRACKING
X
GUIDANCE/NAVIGATION PERFORMANCE
SYSTEMS FLIGHT CONTROL/HYDRAULICS A C T I V I T Y TFSTS
SUMMARIZED ON FOLLOWING CHARTS
W-12
ON-UNbl I r-Lium THERMAL
CONTROL SYSTEMS
STS-1
STS-2
+ZLV, X-POP TAIL
+ZLV, 88 HRS
STS-4
10 HRS
PTC, 10 HRS
5/3/6/3,
TO SUN
6/10,
SI, W HRS
34 HRS
B E N I G N CONDITIONS BASELI NE
DATA
SI, 80 HRS
POST B E T A , +Y SI ATTITUDES,(EQUIP AVAILABLE
SI,
80
RS
PTC, 10 HRS
OFT, LACK
SI,
26
RS
+Z SI/ 20 HRS
TIME)
TEST
BENI GN CONDITI ONS
-THERMAL STABILIZ
- T H E R M A L S T A B I L I Z - Q MS P R O P L I N E S
(ATTITUDE TO
- CO LD B O N D L I N E
- C OL OL D F R C S , M L G
SUPPORT OSTA-1)
C O N S T R A I N T , DEEP SPACE V I E W I N G ,
STARTRACKER
-QMS HTRS, HYD
& MLG
SYSTEM
HYDAULICS
- K U - B A N D SYSTEM
COLD PAYLOAD
-WARM BOTTOM
-COLD BONDLINE
ATTACHMENTS
STRUCTURAL
CONSTRAINTS
-COLD MID + AFT
RECOVERY
-PAYLOAD BAY
CONDITIONS
FUSELAGE, QMS,
- F R C S S OA K B A C K
HYDRAULICS AND
-ARCS SOAKBACK
-RCS SOAKBACKS
-POTABLE AND
-AIRLOCK
-QMS DUTY CYCLE
WASTE WATER
- P A Y L OA OA D B A Y K I T
-ARCS SOAKBACK
LINES
-LONG
-STARTRACKER
- F L A SH E V A P A N
FLASH EVAP AND
WATER FEEDLINE
WATER FEEDLIN E HO
COLD
DURATION BURN W-13
TO E A R T H
(*Z
LV)
PASSIVE THERMAL CONTROL
(PTC)
TAIL TO SUN BOTTOM
EARTH
T O S U N ( + 1 SI SI )
O R Q I T A L R A T E (6/3, £/3, 6/10)
'SUN
TAIL TO SUN (+X SI)
B O T T O M T O SU N ( - Z S I )
SUN
NOSE TO SUN (-X SI)
SUN
TOP TO SUN (+Z SI)
SUN (-Z SI) BETA
> 73° BETA
TAIL TO SUM
>'73° B E T A
U
SI)
SIDE SUN (+Y SI) BETA
NOSE TO SUN {-X SI) BETA
EARTH ORBITAL RATE BOTTOM (6/3, 6/3, 6/10) > 73* B TA
SIDE SUN (*Y SI) ROLLED RIGHT BETA
W-16
ORBITAL FLI GHT TE
PROGRAM
ON-ORB1T TESTS Y L O / \ n P»
DOOR T E S T S
STS-1
Latch tests Opening closing test R a d i a t o r deploy I'LOD cycle test after 12 hrs of or +Z LV Radiator stowing/ door closing
'AYLOAD DEPLOYMENT
STS-1
ItMS
STS-2 » Latch tests PLOD cycle after 80 hrs +Z LV
STS-3
PLOD cycle after
6/3,6/3,6/10
PLBD cycle after 00 hrs -X SI PLOD cycle after 26 hrs +2 SI
STS-4 PLOD cycle after 00 hrs +X SI PLOD cycle after 40 hrs -Z SI
POST OFT PLDD cycle after 40 hrs +Y SI
R E T R I E V A L SYSTEM
STS-2 Unloaded tests Cycle MPM.MRL - RMS direct,backup, single,manual, auto and op erator commanded auto modes
STS-3 Loaded tests with PFTA Rete ntion mech - Cxtract1on/stow1hy - Manual,a uto,opr cmd,direct,backup, s i n g l e modes' with PTTA - RMS envl r. tes Capture dynamics t R MS use w i t h JI.CM (contain, monl
STS-4 9 RMS use with IECM ( p l um e I m p i n g e ment)
POST
OR
Deploy R e t r i e v e P/ o M a x W e i g h t 'P/L 9 M a x Vol.
ORBITAL FLIGHT TEST PROGRAM PAYLOAD
GANGED LATCHES TYPICAL
D O O R C E N T E R L I N E LATCH MANUA L
SYSTEM
D I S C ON N E C T
POINTS
THRU
BELOW
,/
PASSIVE ROLLER ACTIVE LATCH
PASSIVE SHEAR FITTING
LEF T DOO
ACTUATOR (2) M O T O R S
D R I V E DETENT
VERIFICATION'OF DOOR OPERATIONS UNDER VARIED THERMAL CONDITIONS
W-18
ORBITAL
F L I G H T TEST P R O G R A M
O R B I T E R M E C H A N I C A L SUBSYSTEMS RUDDER/SPEED DRAKE HYDRO-MECHANICAL ACTUATION MANIPULATOR (OPTIONAL)
AFT ET S E P A R A T I O N
OR M E C H A N I S M S V E N T D O OR (BOTH SIDES)
S T R UC UC T U R E D I S C O N N E C
•SYSTEMS DISCONNECT o S E P A R A T I O N SYSTEM
CLOSEOUT OOOR
PAYLOAD RETENTION
PAYLOAD AY ACTUATION
DOOR LATCHING
MANIPULATOR BODY
FLAP
HYDRO-
CREW TRANSFER TUNNEL
MECHANICAL ACTUATION
EMERGENCY
IT
EGRESS
HATCH M E C H A N I S M S ELEVON SERVO SURFACE ACTUATORS
CREW INGRESS/EGRESS HATCH MECHANISM SIDE) STARTRACKER
DOOR
YAW AND BRAKE CONTROL PEDALS
SOFTWARE/HARDWARE P E R F , BRAKING MAIN
MANIPULATOR^ DEPLOY JETTISON
GEAR
WHEELS ND BRAKES ANTISKID
TIRES
I PAYLOAD/ARM DYNAMICS I DEPLOY/RETRIEVE A G I L I T Y
RENDEZVOUS SENSOR DEPLOYMENT FORWARD ET SEPARATION'
n F P i n v M F N T A f jnj n R F T
FVAI
DEPLOYABLE DATA S E N S O R (BOTH
SIDES)
PROX IMITY OPERATIONS OPERATIONS NOSE CEAR
.WHEELS
TIRES
STEERING/DAMPING
SYST SYSTEMS EMS OPE RA TION
O N - O R B I T F L I G H T TESTS ENVIRONMENTAL/TEMPERATURE/POWER
STS-1 R A D I A T OR I . W E A T S I N K CAPABILITY, ON-ORBIT
SYSTEMS
STS-2
STS-3
R A D I A T O R HEAT SINK CAPABILITY DURING ENTRY
RADIATOR HEA SINK CAPABILITY ON-ORBIT, COL CASE
PRSD PERF HIGH LOAD'ON PC'S FULL, HALF AND MIN QUANTITY, WITH 'STIRRING' (EFFECTS
STRATIFICATION)
STS-1 ECLSS TEST-
CABIN HEAT LOAD
24 HRS
+X SI
POST OFT
RADIATOR HEA SINK CAPABILITY WITH LARGE PAYLOAD
ATCS TESTS IN
VARIOUS ATTITUDES
FLASH EVAP, HIGH DUCT STEAM F L O W TESTS -X SI CRYO TANK HEAT LEAK DEMO -X SI, COLD
PERIOD tY SI, W A R M PERIOD
W-20
O R B I T A L F L IG H T T E S T P R O G R A M ORB1TER ELECTRICAL POWER SUBSYSTEM B A S EL I N E C O N F I G U R A T I O N
FCP SUBSYSTEM 14-KW
27.5
CONTINUOUS/24-KW P E A K
TO 3 2 . 5
VOC
REACTANT STORAGE
1530-KWH MISSION ENERGY 264-KWH ABORT/SURVIVAL ENERGY LB 02 FOR ECLSS TOTAL LOADED • 92 LB HZ/TANK QUANTITY • 781LB /TANK
OXYGEN DEWARS HYDROGEN DEWARS PRODUCT WATER VALVE MODULE
PRELAUNCH UMBILICAL (DISCONNECTED AT T-4 HOURS)
CP/ECLSS HEAT EXCHANGER
VENT
KAIN DISTRIBUTION ASSEMB LIES - TYPICAL PLACES
COOLANT LOOP SERVICE PANEL FUEL
ZERO
CELL
STRATIFICATION/ HIGH
COWER
PLANTS
(3)
LOAD, HEAT LEAK, ETC, TESTING
W-21
O R B I T A L F L I G H T TEST P R O G R A M ORBITER ENVIR ONMENTAL CONTROL
f
C A B I N T E M P C O N T R OL
A T M O S P H ER E R E V I T A L I Z A T 1 0 N U N I T
DUCTING
ECLSS C O N T R O L P A N E L
, F O OD OD M A N A G E M E N T , S PA C E R A D I A T O R P A N E L S
DUCTING
AVIONICS
L I F E S U P PO R T SUBSYSTEM
DEPLOYED
AVIONICS FANS/HEAT EXCHANGER
HYDRAULIC HEATERS
WASTE MANA GEMENT STORAGE FUEL CELL HEAT EXCHA NGER
STORAGE AVIONICS AIR/FAN COOLING
SPACE RADIATOR
HEAT SHIELD POSITION AHEAD OF WING
THERMAL/VACUUM,. ZERO
PANELS RADIATE FROM COTII SIDES
FLIGHT DYNAMICS,
'AMMONIA BOIL ER (ATMOSPHERE H E A T
R E A L T H E R M A L LOADS EFFECTS
TANKS SINKS)
SYSTEM P E R F O R M A N C E
W-22
O R B I T A L F L I G H T T ES T P R O G R A r.OMMHNir.ATIQNS
TRACKING
STS-1
STS-2
S-BAND PM AND FM TE T
0 U H F O N - O R B I T TEST
POST
ANTENNA SWITCHING TEST
CCTV
CCTV
DATA ONLY OTHER SYSTEMS
CCTV
DATA ONLY
S -B A N D T D R S TEST KU-BAND TESTS RENDEZVOUS RADAR"TESTS PAYLOAD COMM 0 AIR FORCE COMM
GUIDANCE/NAVIGATION TESTS
0 0 0 0
ACCEL IMU DRIFT AFT,COAS VERIF ALIGN VERIF AFT COAS ST IMU ALIGN VERIF SUN, EARTH HORI
TEST 0 ST IMU A L I G N W H I L E
ROLLING
0 AFT COAS 0 AFT COAS
V E R I F 0 AFT COAS
0 FWD COAS 0 FWD COAS
VERIF VERIF A L I G N 0 FWD COAS
0 FWD COAS 0 FWD COAS
ALIGN VERIF
PARTICLE INTERFERENCE 0 N A V BASE STAB +X SI
GLOBAL POSITION SATELLITE TESTS RENDEZVOUS SYSTEMS TESTS
0 NAV BASE STAB +Z SI
0 ST IMU ALIGN VERIF
WITHIN
10°20° OF H O R I Z 0 ST TO IMU ALIGN 0 I MO TO IMU A L I G
0
ALIGN VERIF
VERIF
0
POST
STS-3
STS-2
N W-23
1 R B I T A L M A N E U V E R I N G S YS TE M T F S T S •.
O R B I T A L F L I G H T TEST P R O G R A M FLIGHT, BURN TIME, ENGINE STS-1 L.ENG R.ENG
STS-2
L.ENG
K.FNG
STS-3
.FNG
R.FNG
STS-4
:FNfi
R.FNf,
POST
.FHR
R FMK
-X SI C R O S S F E E D , L ; E N G ; 200 SEC ENGINE,
CROSSFEED, 200 SEC
200
SIMULATED ENG INE FAILURE, AUTO CROSSFEED
10
200
40
-SIMULATED ENGIN E FAILURE, MTV
10
HO
ENGINES BACKUP FLIGHT SYSTEM, BACKUP FLIGHT SYSTEM, ENGINE, COMBINED WITH TEMP, RESTART E N G I N E RESTART HRS, -X SI THERMAL C O N D I T I O N I N G PULSE MODE L . P O D T O R , E N G I N E C R O SS F E ED ,
MTVC
R . P O D T O L , E N G I N E C R O S SF E E D , A U T O TOTAL
ORBIT
TEST T I M E
PROP ELLAN T R EQ UI RE D
LB/SEC)
1152
QMS TO RCS INTERCONNECT TEST,
TOTAL
TEST PROPELLANT,
134/1
1920
11,520
1920
12.120
1000 1152
2W\
„ „.
ORBITAL FLIGHT TEST PROGRAM F L I G H T C Q NNTT R Q I . /R /R C S
TESTS
STS-?
STS-1
RCS/GN&C
JESTS
ATTITUDE .. .
RCS/GN&C TRANLATIONAL TEST F L I G H T C O N T RO L W A R TEST HYDRAULIC CIRC , PUMP TEST
STS-3 B A C K - UP F L I G H T CONTROL SYSTEM
STS-4 DATA
POST ONLY
TEST ROTATION T R A N S L A T IO N MANEUVER
C R EW A C C O M M O D A T I O N S
STS-1 NOI SE LEVE TEST CABIN SAMPLING
STS-2 TEST NOISE LEVE CABIN SAMPLING
0 AI
LOCK/ENU P R E P , D EM O
STS-3 DATA ONLY CABIN SAMPLING
STS-<4
DATA ONLY CABIN SAMPLING
P O ST O F T NOI SE LEVE CABIN SAMPLING 0 EVA DEMO 0 MMU EVAL 0 PRS F.VAL
TEST
PROXIMITY OPERATIONS STS-1
STS-2
POST OFT STATION KEEPING PASSIVE APPR OACH A C T I V E A P P R OA C H
W-25
E N T R Y F L I G H T TESTS DATA COLLECTION
POST
T H E R M A L C O N T RO L S Y S T E M S AERODYNAMICS/FLIGHT CONTROL ENTRY HEATING LOADS
STRESS
FLUTTER 0
(AERO THERMAL
x
DYNAMICS
TPS)
(STRUCTURES)
BUFFET
TPSVERIFICATION
CONTAMINATION MONITORING ENVIRONMENTAL CONTROL ELECTRICAL POWER G U I D A N C E / N A V I G A T I O N P E R F O RM A N C E COMMUNICATIONS 0
TRACKING
AIR DATA SYSTEM
AUTOLAND MSBLS
TACANS PAYLOAD
ENVIRONMENT
A C T I V I T Y TESTS SUMMARIZED
FOLLOWING CHARTS
W-26
ENTRY FLIGHT TEST AERODYNAMIC TESTS
DURING SELECTED C R I T I C A L E N T R Y P E R I OD S E F F EC T I V E N ES S, ,A N D DATA AND REMOVAL OF
STABILITY MANEUVERS
(PTI'S)
E V A L U A T E A E R O D Y N A M I C E L A ST I C I T Y , C O N T RO L S Y S T E M
FLIGH T PERFORMANC E PARA METERS,
VER IF IC AT ION OF WI ND TUNNE
I N T E R I M PLACARDS, C O N T R OL CONSIST
DERIVATIVES REQ UI RE MANEUVERS AER O STICK
I N P U T S ( A SI SI )
OBTAIN
PROGRAMMED TEST INPUTS
S H OR T D U R A T I O N P I T C H , Y A W , A ND / OR R O L L D O U B L E T S , ( I N V O L V I N G
B OT H A E R O S U R F A C E S A N D R C S S E T S ) ,
PUSH OVER PULL
(POPU'S)
F A I R L Y L O N G D U R A T I O N , B O D Y F L A P P U L SE SE S B Y M A N U A L O P E R A T I O N , S C H ED U L ES
0
PROGR AM MED
MID C.G.'S D U R I N G ELEVON BASICALLY
USEABLE DATA,
E L EV O N
I-LOADS, FLIGHTS
BODY FLAP DEFLECTION
EFFECTS
A E R O D Y N A M I C C H A R A C T E R I ST I C S
INDEP ENDENT
T H E R EF O R E, A E R O D Y N A M I C C H A R A C T E R I S T I C U S I N G D I F F E R EN T C O M B I N A T I O N S R A N G E O F D E F LE C TI O NS
ELEVON
CAN BE DETERM INED WITH MID-C,G,' BODY FLAP DEFLECTIONS
(SAFE)
T H A T SPAN
FOR OPERATIONAL C ,G, RA NG E,
EXTREME C.G.'S TO PE (EVALUATED POST W-27
AERODYNAMIC DATA REQUI REMENTS HYPERSONIC LATERAL/DIRECTIONAL HYPERSONIC VISCOUS
STABILITY
REAL
P I T C H I N G M OM OM E N T
SUPERSONIC LATERAL/DIRECTIONAL STABILITY VEHICLE
TRIM CHARACTERISTICS H I N G E MOMENTS
TRANSONIC
T R A N S O N I C . L A T ER ER A L / D I R E C T I O N A L M A C H 3,0 TO <|,5 L A T E R A L MACH
RUDDER
STABILITY
TRIM CAPABILITY
EFFECTIV ENES
P U S H OV E R -P U L L U P P E R F O R M A N C E , H E A T I N G
T R I M CHARACTERISTICS
HtAIIW, VISCOUS «W MUMMIT
ms roHini oo r*auu osci • uuv oc$i« uquiiocin
OH
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t f $ . t S T s - t iti-j $ r s - 4 oroft o/or O/OB oroi 0210 EX PAN SION
P LA H
aiCHT/VTO
EXPANSI ON PLAH
W-28
10
Tl* (UCJJ
o BOLL
Tl
II
Tl
TIKI (SUJ)
u
ti VdOCITT
0*
fj Al
PUSHOVER
COMMANDS
P U L L U P S C H E D U L E ( T Y P I CA L )
(OR ASI'S)
W-29
ELEVON
HINGE MOMENTS
SCHEDULES
LATERAL DIRECTIONAL CONTROL
TRANSITION FROM HEATING
HEATING DATA
5
ELEVON TRIM
0
-5 -•
-10
•
P O S T OF
4 5 6 MACH
| 8 910'
20
W-30
STS-2
STS-3
STS-4
ASI/PTIi
PUSH OVER-PULL BODY FLAP
16.
•
24
•MINUTES fROM
A E R O D Y N A M I C TESTS
l
W-31
POST OFT
0202
0203
0204
0205
PUSH OVER-PULL PODY FLAP
UJ
100--
50 -•
24
32
MINUTF S FRO
POST OFT AERODYNAMIC
TESTS
W-32
ENTRY FLIGHT TESTS AEROTHERHQDYNAMICS SHAPING
GROUNDRULES:
SHAPE TRAJECTORY
S U R F A C E T EM P E R A T U R E L I M I T S W H I C
TPS MATERIAL CAPABILITY AND T H ER M A L
o
CRI TERI
EE D S I N G L E M I S S I O N D O N O T E X C EE
M I N I M I Z E P E AK B O N D L I N E T EM P E R A T U R E ,
NOM IN AL TRAJECTORY
E S T A B LI S H ED
FROM:
T P S M A T E R I A L C A P A B I L I T Y / D E SI G N L I M I T S U R F A C E T ER H P E R A T U R E C A P A B I L I T B O N D L I N E / S T R U C T U R A L T EM P STRUCTURAL
DESIGN
LIMIT
TEMP GRA DIEN T
(T RA J
IW/lO)
U N C E R T A I N T Y A N A L Y S I S /M A R G I N R E Q U I R E M E N T AERO HEATIN
TPS'RESPONSE T R A J E CT O R Y D I S P E R S I O N S SURFACE TEMP
W I T H T H ER M A L U N C E R T A I N T Y
M A R G I N D U E T O H E A T I N G R A T E D I S P E R S I ON S
B O N D L I N E T EM P M A R G I N D U E T O H E A T L O A D D I S P E R S I O N S W-33
2950
W I N G L E A D I N G E DG E F O RW A R D C H I N
2850 STS-2 STS-i|
2750 SURFACE TEMP, °F
STS-3
STS-1
2650 STS-2
2550
STS-; STS-1
2450
t 0 BONDLIN E TEMPERATURE MAK GIN
-10
''OFT
O'RBiTER ISOTHERMS
TRAJECTORY 14414.1 2300F.
2575F
2000F LOWER SURFACE VI EW
2000F 23GOF
ENTRY/ASCENT
700F / 750F 850F /
800 F GOOF UPPER
SURFACE V I E W
800F
'DENOTES A C C E N T T E M P E R A T U R E S ( M A X I M U M Y A W 8 DEC)
1200F
750F 830F
900F
'1000F *2100F *2150F
*2220F
*1000F
2565F 1BOOF
SIDE
SURFACE VIfW
W-35
DATA SYSTEM STS-1 DATA ONLY
ENTRY FLIGHT TESTS
SJS-3
_SIS-2 DEPLOY
PROBE
A T M = 5,0*
DATA ONLY
N=5,0*
STS-3
STS-U
POST
AUTOLAND THRU
AUTOLAND
AUTOLAND
MANUAL LAND,
ROLLOUT,
RHTU ROLL-
F L A R E, M A N U A
LAKEBED
LAKEBED
O UT , R U N W A
LAND,
AUTOLAND
LAKEBED
0 DAC PHOTOS
PROBES
STS-9
MAN UA L APPROAC "IT
DEPLOY BOTH
* UNDER REV IEW
AUTQLAND
STS-1
POST
FLARE,
0 DAC PHOTOS
0 DAC PHOTOS
0 DAC P H O T O S
AUTOLAND
THRU
ROLLOUT,
0
D A C PHOTOS
CREK ACCOMMODATIONS STS-1
NOI SE LEVEL DATA
STS-2 NOI SE LEVEL DATA
STS-3 NOI SE LEVEL DATA
STS-il
POST OFT
NOISE
N O I S E L EV E L
LEVEL
DATA
DATA
A N I T - G SU I T EVALUATION
ORBITAL F L I G H T TEST P R O G R A M
P O S T " OF OF T " 0
P ERI OD
IT HAS-BEEN RECOGNIZED THAT THE TRANSITION FROM DDT&E T H A T S OM E T E S T I N G M U S T
0
FOR THAT REASON WILL HAVE
CONDUCTED
OPERATIONS
GRADUAL
IN THE OPERATIONAL PERI OD,
OV-102 ORBITER WILL R E M A I N
I N S T R U M E N T E D B E Y ON D O F T A N D O V - 0 9 9
M U C H S M A L L ER B U T H A D E Q U A T E I N S T R U M E N T A T I O N
ET
EACH CASE
LARGE
P E R C E N T A G E O F T H E D A T A P R O C E S S I N G " B L A C K B O X " C O M P O N E N T S C A N B E R E M OV E D F O R W E I G H CRITICAL FLIGHTS,
0
THE COMPLETION
V E R I F I C A T I O N TESTING OR THE TESTING OF NEW CAPABILITIES
THUS
C O N D U C T E D O N A G E N ER A L L Y N O N - I N T E R F E R E N C E B A S I S W I T H P A Y L O A D ,
W-37
S T S - 1 F L I G H T P R O F IL IL E
KEYSER
K-l
OVERVIFVI NOMINAL ASCENT
ASCENT ABORT ONORBIT
DESCENT
STS-1 F L I G H T
OVERVIEW
TS 1
ONORBIT
OV ERV IEW
PROFILE:
ORBIT ALTITUDE
150/150
INCLINATION:
10.3
LAUNCH DATE:
MARCH
G M T O F L A U N C H ( F R O M KSC):
12:23:00
EST OF LAUNCH:
7:23 A..M,
DEGREES
1981
HOURS
LAUNCH WINDOW DURA TION:
MILES
MINUTES
EARUEST:
L A U N C H L I G H T I N G R E Q U I R E M EN T
LATEST
SUN-RU NWA Y
MISSION DURATION:
PST OF
L A N D I N G (AT EAFB):
A Z I M U T H / EL E V A T I O N
54,5
: 53 53
HOURS
A ,M
C ON S T R A I N T
STS-1
FLIGHT ASCENT
G R O U N D T K A C K AND POST-MECO COMMUNICATION COVERAGE
STS-1 ASCENT
90'W
60*W
30'W
30°E
lonyItude
80'E
90'E
120*E
150*E
S T S- 1 A S C E N
MAJOR EVENTS
RANGE
LIFTOFF THROTTLE FOR DYN MAX,
"
PRESSURE
SRB SEPARATION MECO
(ET SEP)
PRESSURE
(MIN iSEC)
( N .M I . )
:00
0,
:31
,1
:5
1.
:12 :3
ALTITUDE/ORBIT (N.MI.)
21,
710,
13/80
OMS-1 I G N I T I O N
OMS-1 C U T O F F
57/150
OMS-2 IGNITION OMS-2
CUTOFF
150/150
STS-1
IMPACT FOOTPRINT
Impact constraint
[ C o m p o s i te SR
i m p a c t footprint
Nominal staging
SI-
79
WEST LONGITUDE,
78'
77'
6"
>-i Nuruw/u. ci 80
100
11
•130
20 O)
30
Incnnation .T
<1(7.3
30
impact Latitude
30.95
Longitude = 93.22°
40
ND1AN
70
80
OCHAN
90
100
E a s t longilutle, (leg
K-ll
TS 1
FLI GHT ASCU NT
ABORTS
K-12
ASCENT ABORTS
INTACT ABORT CAPABILITY PROVIDES ORBITER,
AND
INTACT
PAYLOAD TO
A PLANNE D
ABORT CAPABILITY
S I N G L E SPACE SHUTTLE M A I N
SYSTEM
(QMS)
S A F E R E T U R N O F T H E CREW,
ROUTE
LAN DIN G SITE,
IS TO
ThlE
PRIMARY
PRO VID E PROTECTION
E N G I N E (SSME)
R
S I N G LE LE
REQUIREMENT
AGAINST
ORBITAL
TH
LOSS
MANEUV ERIN
ENGINE,
K-13
INTACT ABORT MODES
RETURN PRESS
LAUNCH SITE
(RTLS)
M A I N E N G I N E C U T O F F MECO) ABORT ONCE AROU ND (AOA) ABORT
ORBIT
(ATO)
K-
TYPES
INTACT ABORTS
ADORT-TO-ORBIT TRAJECTORY
(ATO)
CIRCULARIZATION
ENTRY INTERFACE
LAUNCH RETURN S I T E (RTLS) DURATION «
ABORTONCE-AROUNO
STAGING
DURATION
S O L ID R O C K E T B O O S T E R S (SRB) MAIN ENGINE C U T O F F (MECO)
LAUNCH
SR
I M P A C T [TANK I M P A C T
TANK
IMPACT
K-15
« 107 MIN
STS-1 A S C EN T A B O R T C A P A B I L I T Y
NOMINAL MECO
EARLIEST '1:23
ABORT MODE
8:32
PRESS TO MECO (AOA ATO)
RTLS
LATEST
GET =-
T I M E A F T E R L I F T - OF F , M 1 N
K-16
RTLS
POWERED RETU RN L A U N C H S I T E (PRTLS) SSME's A R E B U R N I N G GLIDE RETURN L A U N C H S I T E (GRTLS) Q R B I T E R GLIDES TO L A N D I N G AT KSC
PORTION PORTION
WHICH
RTLS
RTLS
WHICH
P R E S S TO MECO (ADA
A TO )
REQUIRED FOR S I N G L E SSME F A I L U R E P R I O R
T I M E C R I T I C A L F A I L U R E S THAT R E Q U I R E I M M E D I A T E RE T U R N
CAPA BILI TY
LAUNCH SITE
K-17
TYPICAL^RTLS PROFILE RTLS al)0rt flight phases (J
PrOpellant-dissipation
(2)
PWD FIT guidance
(3)
P o w e r e d | ) i tc tc ! u lo lo w n ( P P
Load relief (?) T A f l M g u i d a n c e
AiiloUnu!
O R B / E T mated coast Orbiler r e c o v e r y
•Pitcharound
"Nominal launch trajectory
T3
3g's
Nominal entry trajectory
ET Irajectory
Landing Range to landing silo, R, n. mi,
K-18
ABORT ONCE
A D E Q U A T E E N E R G Y (SSME ' A ND T H E N D E O R B I T LAND
ARO UND
( AO A
QMS) O R B I T F R TO ELY AT LEAST ONE R E V O L U T I O N N O R T H R U P S T R I P, N , M ,
2 QMS M A NE UVE R S
O MS -1
( O PT I MI Z ES O R B I T A L C O N D I T I O N
OMS-2 ( D EO R BI T M A N E U V E R
OMS-2)
P R O V I D E S D E S I R E D ENTRY CONDIT IONS)
REQUIRED S I N G L E SSME F A I L U R E P R I O R ACCEPTABLE ORBIT CAPABILI TY T I M E C R I T I C A L F A I L U R E S R E Q U I R I N G I M M E D I A T E R E T U R N (AFTER RTLS C A P A B I L I T Y ENDS)
K-19
STS-1 POST-MECO GEOMETR
OMS-l
PERIGEE \' (62 N.. M l . )
QMS-2 ENTRY INTERFACE
(400,000 FT)
K-20
ABORT
O R B I T (ATO)
OMS) N . M I ,CIRCULAR ORBITER ACHIEVE A D E Q U A T E E N E R G Y (SSME QMS) , , O R B I T (AND D E O R B I T ) B U I N S U F F I C I E N T E N E R G Y (SSME ACHIEVE NOMINAL N.MI, CIRCULAR ORBIT,
SIMILAR
NOMINAL MISSION OMS-1:
R A I S E S APOGEE TO 105 N . M I ,
OMS-2:
C I R C U L A R I Z E S O R B I T TO 105 N . M I ,
R E Q U I R E D W H E N S I N G L E SSME F A I L U R E P R I O R 0 N CIRCULAR)
CAPABILITY
ACHIEVE NOMINAL ORBIT
K-21
STS-1 POST-MECO GEOMETRY
CIRCULAR ORBIT (105 MI,)
PERIGEE
MI.K7
APOGEE (105 MI,)
K-22
CONTINGENCY ABORT MOOES
EJECTION DITCHING
K-23
TS 1
FLI GHT
ON ORB IT
SIS-1 ONORBIT TIMELINE
OMS-l
MEAL OMS-2
I,
STATUS
COMPUTERS
CONFIG
CHECK OUT DOORS
,OPEN
(TV)
S L E EP A C T I V I T I E S
IMU ALIGN
SLEEP
CONFIG ORBITER O R B I T A L OP S
TESTS (FTO'S) (STAR TRACKER, ATTITUDE HOLD) MEAL 1ECK
ALIGN (FTO'S);
EDWARD AFB, CALIF NORTHRUP STRIP, N ME KENNEDY SPACE CEN, HICKAM FIELD, HAWAII KADENA, OKINAWA ROTA, SPAIN
SET UP
STATUS REPORT
DEORBIT © O P P O R T U N I T I EE SS ® i
!•
cE
oE
e e i
SITES
LANDING
• D
»
•
•
i
i
6
oD
8
10
GROUND ELAPSED TIME, HOURS
1
12
I
i
1
i
16
1 18
K-25
STS-1 ONORBIT TIMELINE (CONTINUED) RECONF
SLEEP
COMPUTERS
OMS-3 . M A N E U V E R
SNACK
P O S T S L EE P A C T I V I T I E S
OMS-4 M A N E U V E R
CLOSE PAYL OAO DOORS
ALIGN MEAL
R E C O N F COMPUTERS
TEST O B J E C T I V E S
ALIGN
CONFIG FLT CONTROL SYS
S EA T
[BEGIN DEORBIT REHEA RSAL
MANEUVER
RECONF COMPUTERS CABIN
MEAL
ING RESS
IMU ALIGN
DEORBIT REHEARSAL]
[END
V
(MIDDECK)
PREP
SEAT E G R E S S
OPEN PAYLOAD BAY
CONTROL CHECK OUT
RECONF
D O OR S
COMPUTERS
RECONF COMPUTERS
S U IT D O F F I N G DEACTIVATE
S Y ST E M
ACT IVAT ION
SUIT DONNING
DEORBIT f"« O P P O R T U N I T IE S » R
i
oE
oE
oE
OK oN
1
i
1
i
ON
18 GROUND ELAPSED TIME, HOURS
i 30
oD
ON
o OH i
32
1
OH i
34
1 36
K.-26
STS-1
ONORBIT TIMELINE (CONCLUDED)
SLEEP
SNACK
DOORS
CLOSE PAYLOAD
SLEEP
ALIGN
POST SLEEP ALIGN
SEAT
RCS TEST
INGRESS
MANEUVER PREP
(FTO)
53:31)
IDEORBIT
MEAL RECONF
COMPUTER
[LANDING
FLT CONT CHECK RECONF
COMPUTER
CREW SYS DEACTIVATION S U IT D O N N I N RECONF
DEORBIT OPPORTUNITIES i
36
eR
I
!
38
40
42
GROUND
44
ELAPSE
t
• K'
l 46
i
T I M E , HOURS
COMPUTE
•
o E
o
•
• N
e
•
K
•
I
48
52
.
5'
54:31]
STS-1 F L I G H T D E S C E N T
K-28
DESCENT DEORBIT ENTRY T E R M I N A L A R F A EN E R G Y M A N A G E M E N T APPROACH
(TAEM)
LANDING
K-29
120 120
140 140
LONGITUDE,
160 160
EAST
180
WEST
16
120
100
TS 1
;•::f • • :- • rt
:
-|
• i •
\':.\
i
•
'
ENTRY I NTERFACE THROUG H LANDIN G GROUNDTRA CK
'
:l'
K-31
STS-1 •i'lo
i
-
r
UI'IO'
i ——• ——•i
APPROACH
LANDING GROUNDTRACK
1
111*0'
''fit
nxwltwlt
K-32
National National Aeron autics an Space Administration
ashing ashington. ton. D C. 2 0 546 AC 20 755-8370 For Release.
SPACE SHUTTLE STATUS REPORT
Wednesday,
November
5,
1980
O r b i te powered
orbiter
power
nd a y m o r n i n g . u p o n M o nd
u n i t s I, 2 and 3 h a v e b e e n r e i n s t a l l e d
All
underway. system
pods
torqued bottom
lt ts att achi ng each 12 bol
retesting
The exter nal
of the wing have been
is now
of the orbital maneuvering
t o t h e o r b i t e r s t r u c t u r e h a v e b e en e n i n s ta t a l l ed ed
for fli ght .
testing.
Auxiliary
and
rs t a n k a f t u m b i l i c a l d o o rs
on the
installed..and._are...now u n d e r g o i n g
P r e p a r a t i o n s a r e u n d e r w a y t o r e i n s t a l l th t h e Space
Shuttle ma in engine
November
8-9.
Tiles:
T he he vehicle number
w i t h 58
thermal pr ot ec ti on sys st t em em
30,116 w i t h
of
November 4 03 03 .
number of
bonds
2, 476
cavities
to completion
Du ri ng that week, accepted
remaining.
i s 1,269.
tiles were bonded
t i l e s n o w on on t h e
and 11 rejected.
-more-
estimated
D u r i n g t he h e w ee ee k e n d i n g
a n d 7 3 removed
t i l e proof
Th
for a net gain
t ests were
conducted
-2
Tank/Solid Rocket
External
M a t i n g of ters
Boosters;
the e x t e r n a l
on a mob ile
launcher
platf orm
Assembly Building began
Monday
e a r l y T u e s d a y aft erno on. attachment tank when lished
struts
Se
i t i s l o a de de d
t r i a l s of
pretensioning of the
tests
propellant s will be
accomp-
operations.
mating
the UTC L i b e r t y , f i r s t of sol li id
Complex
39, Pad At
over
3 of the V e h i c l e
Operations:
b e g i n W e d n e sd sd a y
rocket booster
sched-
ret rie val
pod covers for the hea at ted pod
o n t h e r o t a t i n g s e r v i c e s t r u c t u r e w e re re d e l i v e r e d t o
on Frid ay and weekend.
Prooftestin g
two s p e c i a l l y b u i l t
afte rnoo n, Nove mber
o r b i t a l m a n e u v e r i n g s ys y s te te m
sys st tem
the.pad
boos-
and was v i r t u a l l y complete
wi h supercold
uled
purge
i n H i g h Bay
completion
vessels d e s i g n e d
The
Pull
the t w i n solid rocket
compensate for the sh rin kag e of the external
t
following
Recovery
t a n k and
of
i n s t a l l e d , o n t h e r o t a t i n g s e r vi vi c e
Installation
t h e p ay a y lo l o ad ad
the r ot at in g service
completed
Monday.
ground han dli ng mechanism
s t r u c t u r e is is s c h e d u l e d
-more-
structure
(PGHM)
to begin on
Thursday.
3-
Payloads;
O f f i c e o f S p a c e a n d T e r r e s t r i a l A p p l i c at at i o n
payload, scheduled
flight
Apollo Telescope Mount
(ATM)
Checkout
B u i l d i n g H i g h Bay
I n t e g r a t i o n Test E q u i p m e n t ) integrated with
Five other
STS-2, i s t o b e moved
Clean Room
and
worksta nd.
n
CITE (Cargo
Experiments
beginnin g abou
experiments
mounted
is to b e g i n M a r c h
-end-
2.
will
November
o n t h e pallet;
two r i d e i n t h e o r b i t e r ' s c a b i n . I n t e g r a t e d
OSTA-1 payload
from
in the Operations
installed
OSTA-1 p a l l e t
OSTA-1's s e v e n
(OSTA)-l
CITE t e s t i n g
of
