saturn v launch vehicle flight evaluation report-as-511 apollo 16 mmion

315 Pages·2002·38.06 MB·English

MPR-SAT-FE-72-l JUNE 19, 1972
‘535) SbTURU 5 LAUNCH w3-33823
!T EWALUATICN EEPJRT-AS-511
;SIOI (UAS A) 327 p AC
CSCL 22c Urclas
G3/30 1sa4fJ
SATURN V LAUNCH VEHICLE
FLIGHT EVALUATION
REPORT-AS-511
APOLLO 16 MMION
PREPARED 6Y
SATURN FLIGHT EVALUATION
WORKING GROUP
GEORGE C. MARSHALL SPACE FLIGHT CENTER
MPR-SAT-FE-72-1 JUNE 19, 1972
SATURN V LAUNCH VEHICLE
FLIGHT EVALUATION
REPORT-AS-511
APOLLO 16 MISSION
PREPARED BY
SATURN FLIGHT EVALUATION
WORKING GROUP

MPR-SAT-FE-72-l
SATURN V LAUNCH VEHICLE FLIGHT EVALUATION REPORT - AS-511
APOLLO 16 MISSION
BY
Saturn Flight Evaluation Working Group
George C. Marshall Space Flight Center
ABSTRACT
Saturn V AS-511 (Apollo 16 Mission) was launched at 12:54:00 Eastern
Standard Time (EST) on 16, 1972, from Kennedy Space Center,
Complex 39, Pad A. The vehicle lifted off on a launch azimuth of
90 degrees east of north and rolled to a flight azimuth of 72.034
aegrees east of north. The launch vehicle successfully placed the
manned spacecraft in the planned translunar coast mode. The S-IVB/
IU impacted the lunar surface within the planned target area.
This was thes econd Apollo Mission to employ the lunar Roving Vehicle
(LRV) during Extravehicular Activity (EVA). The performance of the
LRV was satisfactory and as on Apollo 15 Mission resulted in a signi-
ficant increase in lunar exploration capability. The total distance
traveled on the lunar surface with the LRV on this Mission was 27
kilometers (17 miles).
All launch vehicle Mandatory and Desirable Objectives were accomplished
except the precise determination of the lunar impact point and time.
No failures or anomalies occurred that seriously affected the
mission.
Any questions or rmnts pertaining to the information contained in
this report are invited and should be directed to:
Director, George C. Marshall Space Flight Center
Huntsville, Alabama 35812
Attention: Chairman, Saturn Flight Evaluation Working
Group, S&E-CSE-LA (Phone [phone])
TABLE OF CONTENTS
Page Page
TABLE CF CONTENTS iii 4.2.2 Parking Orbit Phase 4-7
LIST OF ILLUSTRATIONS vii 4.2.3 Injection Phase 4-9
4.2.4 Early Translunar Otiit Phase a-10
LIST OF TABLES xi
SECTION 5 - S-IC PROPULSIOlY
ACKNOYLEDGEMENT xiii
5.1 Sumnary 5-l
ABBREVlATILW xiv
5.2 S-IC Ignition Transient
WISSION PLAN rviii
Perfomance 5-l
FLIGHT SIRWARY xxi
5.3 S-1C Mainstage Perfomiance 5-3
MISSION OBJECTlVES ACCOMPLISHMENT xxviii
5.4 S-IC Engine Shutdown Transient
FAlLURtS AiU ANOMALIES xrvix Performance 5-5
5.5 S-IC Stage Prupellant
SECTION 1 - INTRODUCTION
Ranagemm t 5-6
1.1 Purpose l-l
5.6 S-IC Pressurization Systems 5-7
1.2 Scope l-l 5.6.1 S-IC Fuel Pressurization
system 5-7
SECTIOn 2 - EVENT T!sS 5.6.2 WC CCK Pmsurizatiun
system s-9
2.1 SumaryofEvents 2-l
2.2 Variable Time and Comanded 5.7 S-IC Pnewtic cuntro1
Pressurp Systulm S-10
S*itch Selector Events 2-l
5.8 S-IC Purge Systems S-10
PCTICW 3 - LAWY OPERATiWS
S-It KNKJ Suppression
s-v
3.1 3-l SF- S-10
Prelamct llilestones 5.10 S-It Hydraulic Systecn S-10
:::.1 S-IC stage Pm:aunch Problenu ::;
3.2.2 S-II Staq Prelaunch P~ublems 3-l SECTIOIY 6 - S-11 PRWULSIoll
3.2.3 S-IVB Pmlaunch Problems 3-3
3.2.4 IU Stage PrPlawtch Prablenis 3-3 6.1 f-w 6-l
3.3 Terminal Culntbun 3-4 6.2 S-11 Chilldcnm ad Eluild~
lransimt Performa 6-2
3.4 Prapcllant loading 3-4
3.4.1 W-1 Luading 3-4 6.3 S-11 Mainstagr, Performance 6-7
3.4.2 LOX Luading 3-4 6.4 s-11 shutdow Transient
3.4.3 En2 Loading 3-5 Perfuuna 6-9
Ground Support Equipwit 3-6 6.5 S-II Stapc Propllant
:-: 1 Gruwid/khiclt I&wface 3-6 lmagwnt 6-11
3:5:2 ClSFC Furnished Gnnmd
Stqxport Equipmt 3-7 6.6 S-I! Pressurization Systm 6-13
6.6.1 S-II Fuel Pnxsurizatiun
SXTIDN 4 -TRAJECTORY system 6-13
6.6.2 S-II LOX Pwwssurizatian
4.1 S-Y 4-l system 6-15
4.2 Trajectory Evaluation 4-l 6.7 s-11 Pnewtic cuntro1
4.2.1 Ascent Phase 4-l Pressurr Sys'rn 6-19
iii
TABLE OF CONTENTS (CONTINUED)
Pege Page
8.2.2 Benaing tints 8-3
6.8 S-11 t+ellm Injection
sfi- 6-19 8.2.3 Vehicle Dynamic Chrrscterlstics 8-3
8.2.3.1 longitudinrl Dynnfc
6.9 Paa suppression systen 6-20 Characteristics 8-3
6.10 S-11 HydrrulIc System 6-20 0.2.4 Vibration n-5
8.3 S-11 POGO limiting Backup
SEClIOI( 7 - s-IVn PnoPlnsIoI Cutoff system 8-7
7.1 S--V 7-l
SECTION 9 - CUIWCE AND NAVICATIO)I
7.2 s-IV6 Chlllddn end Buildw
Transient Pcrfomancc for 9.1 S-Y 9-:
First Bum 7-2 9.2 Gufdsncc tarprrisons 9-1
7.3 S-In Mainstsgc Pcrfomdnce 9.3 Nwlgrtion end Guidance
for First Bum 7-5 Schrr Evaluation 9-10
7.4 S-IVB Shutdown Transient 9.4 Navigation and Guidance
performance for First Bum 7-7 System Caqonents 9-22
7.5 S-IVB Pwking Orbit Coast 9.4.1 ST-124M Strbilired Plrtfom
Phase Conditlmlng 7-7 w- 9-24
9.4.2 LVOC and LVM 9-24
7.6 S-IVB Chilldowm and Builds
Transient Perforunce for SECTIW IO - C;oIITROl AND SEPARATIOW
Second Bum 7-7 7-13
7.7 S-M *Instage Perfomance 7-1s 10.1 S-Y 10-l
For Second Bum 10.2 s-IC Control systn
7.7.1, kinstage Pmdiction Technique 7-17 Evrluatlon 10-l
10.2.1 liftoff Clearances 10-l
7.0 SiIVB Shutdarn Transient 10.2.2 Inflight Dynirics 10-l
Perfomnce for Second Bum 7-17
s-11 Control sysm
7.9 S-WE ftegt Pmpellrnt 7-18 Evrlurtion 10-e
I(mrgemnt
I-10 10.4 s-IUD Control systcll
7.10 S-IV0 Pmsurirrtlal systcll 10-9
7.10.1 S-IV6 Fuel Pmsurir4tlon 7-20 10.4.1 Control System EwltMlon
sfi- &wing First Bum 10-9
7.10.2 s-IVI) LDX Pmsurlzrtim
10.4.2 Control Systea EwluetIon
Sfltn 7-24
Ourhg Parking Orbit IO-14
7.11 j-IV8 PlUElvtlC Contml 10.4.3 Control Systcl Evelwtlon
Pmsum sysbm 7-24 Chwlng SecendBum IO-15
7-24 10.4.4 Control Systa Evelwtlon
7.12 s-IVB Aurlliry Propulsion 7-24 After S-IVII Second Bum 10-18
sysr-n
7-29
7.12.1 APSl4odulc~PerfolmMec 7-31 10.5 1nstn-mt wtContm1
7.12.1.1 Propellent Sysm Colponcnts Lvrlurtlon lo-24
7.12.1.2 Hcl!u Pmssurlutim system 7-31
10.6 separat1al IO-24
7.12.1.3 &InSvlJeltSa tlgetlcn Of Frllurr 7?--3?1! 1100..66..12 SS--K1/1S -II Second sepwPelatn1eo n Separation
7.12.1.4 MS Extenul Lerkege Cormctfve 7-31 Ev4luet:o 10-a .* ;.
ktln 10.6.3 s-1 l/S- *9 seplratiom IO-26
7.12.1.5 Thnnt SySocll ::; 10.6.4 S-IvB/CW Separation IO-26
7.12.2 APS lbdule 2 PorFom-
7.12.2.1 Pmpellmt Qstcll. SECTION ll- ELECTRICAL WE- w1D EMERGENCY
7.12.2.2 lk!iu Pmsurization Sysm ::g DETECTION CYSTEM
7.12.2.3 ~S$""l LuLspc Comctive
11.1 s-v 11-l
7.12.2.4 Thrust Sysa :z
11.2 S-IC Staqe Electric41
7-41
7.13 S-IVB Orbital kflng Operations 7-41 G-S- 11-l
7.13.1 Fml Tank Wing
7-41 11.3 S-11 Steg+ Electrlul
7.13.2 LOX T&L G@ng end Srfing
SYSti 11-l
7.13.3 Cold lcliu m 7-43 11.3.1 S-II 1gntt1on system
7.13.4 Mtmt lkllu oup 743 Electrical Netuort Armly II-2
7.13.5 stat Pneurtic Caltrol
sp)rcm %ffnO 7-44 11.4 S-IVB Stage Electrical
7.13.6 Engine Start Tank Srflng 7-r4 srs- II-3
7.13.7 Engine Control spkcfe Lfin9 11.4.1 f-v 11-3
11.4.2 S-IVB Fotwrd B4ttery No. 2
7.14 Nydmulic systa
Brthcy Perforunce 11-3
8-l
SECT1ale - STWCTIRS 11.5 lnstrumt Uit Electric41
SF- 11-9
8.1 s-v 11.5.1 S-V II-9
::1'
8.2 total Vehicle StnictumS 11.5.2 Batteq kulysir 11-14
Evelutlon
8.2.1 LoegltudinrlLoed4
iv
TAME 0F CONTENTS (CONTINUED)
Page
Page
11.6 ?,dtUrn v bWqenCy bteCtim SECTION 18 - SPACECRAFT SLWARY 18-l
11-1s
System !EOS)
SECTlOW 19 - APOLLO 16 INFLICiHT
SECTION 12 - VEHICLE PRESSURE EIIVIRCU4MEHT OEIWSTRATION 19-l
12.1 h""dl-y 12-l SECTION 20 - LWAR ROVING VEHICLE
12.2 Base Pressures 12-I 20.1 SWaf-y 20-l
12.2 1 s-IC Base Pressures 12-1
12.2.1 s-11 Base Pressures 12-1 20.2 Deployment 20-3
20.3 LRV to Stewed Payload
SECTION 13 - VEHICLE THEPJW ENVIRONMENT Interface 20-3
13.1 SmdV 13-l 20.4 Lunar Trafficability
13.2 S-IC Base Heating 13-I Envirommt 20-3
13.3 S-II Base Heating 13-I to.5 Heel Soil Interaction 20-6
13.4 Vehicle kroheating Thennal 20.6 Locmtion Performance 20-6
Envitlnment 13-6 20.7 Mechanical Systems 20-6
13.5 S-[C/S-II Separation Thermal 20.7.1 Harmonic Drive
Environrent 13-7 20.7.2 Iheels and Suspension 2:
20.7.3 Brakes
SECTIUU 14 - EPVIROM(EWTAL CONTROL SYSTEMS 20.7.4 Stability z:
20.7.5 Hand Controller 20-B
14.1 S-V 14-1 20.7.6 LO&S 20-D
14.2 S-IC Envirommtal Control 14-l Electrical Systems 20-8
14.3 S-11 Enviromental Control 14-2 ii-x 1 Batteries 20-B
2U:a:2 Traction Drive System
14.4 ILL Lnviroomntal Control 14-2 20.8.3 Distribution System ii:
14.4.1 The~l Conditioning Systeu 20.6.4 Steering
UCS) 14-2 20.6.5 kp-Hour Integrator g:;
14.4.2 ST-124M 6as Derring Systm
(=f) 14-7 20.9 Control and Display Console 20-10
20.10 Navigation Systeu 20-10
SECTIDN 15 - MTA SYSTEMS
20.11 Craw Station 20-15
15.1 S-f-Y 15-1
15.2 Vehicle Measummnt Evaluation 15-i 2200..1122 -l TShueRfuuaryl 2200--1166
15.3 Atttwm WF Tclenetty Systca 20.12.2 Transportrtion Phase 20-16
Evaluatton 15-l 20.12.3 Evtrawhicular Activity
Periods 20-16
15.4 C-Emd Radar SystemEvaluattou IS-4
20.13 Structural 20-19
15.5 Secure bra- Safety Comand
System Evaluation 15-7 20.14 Lunar Roving Vehicle
Configuration 20-19
15.6 Comand and Commiution
Systeu Evaluation IS-7 RPfNDIX A - ATHOSPHEL
15.6.1 Cownd -ication Systeu
S-V 15-7 A.1 -ry A-l
15.6.2 CCS Perfocwnce 15-I A.2 Grnaral Ampheric Conditions
15.6.3 ccs S1qlal LOSS 15-10 at hutch Time A-l
15.7 Growl Engineering bras 15-12 A.3 Surface Observations at
1amch Time A-l
A.4 llpper Air Measuramts A-l
16-l A.4.1 Yindfpccd A-l
16-l A.4.2 Mind Direction A-2
A.4.3 Pitch Mind bqa*nt YYiandw Colponcnt A-2
A.4.4 torponntuind Shears A-2
A.4.5 Extra Ylnd Data in thAe -2 lilgh
17-l
A.4.6 WC fwm
17-l A-2
17-5 A.5 ~~'c Data
A.5.1 AtPsphcric Rwsfty :::
17-5 A.5.2 Optical IdI! of kfraction
17-9 A.5.3 ;:;
V
SEcna 16 - IMSS CHAMCTERlSflCS
16.1 f-v
16.2 ass Evalvltion
SECflDlI 17 - LINAR 119ACT
17.1 5-v
11.2 TranslmarCoestkrmven
17.3 Trajectory Evalwtion
17.4 Lwr 1-t CoM .ionS
17.5 Tracking Dlta
TABLE OF CONTENTS (CONTINUED)
A.6 coqwlson of Selected
A~spherlc olta for Srturn V
Lmmches A-3
APPENDIX 6 - AS-511 S16111FIWT 0011FIGlWlIOW
CnmeES
6.1 Intmductlon B-1
vi
LIST OF ILLUSTRATIONS
Fipw Page
figure ’ age 6-9 1-11 fuel Pwp Inlet b-16
Ccmditions
2-l Ground Station Time to 6-10 S-II LOY Tdnk Llllage
Vehicle lime Conversion z-2 PtT5SUI-P 6-17
4.1 Ascent Trajectory Positian 6-11 s-11 LOX Pump Inlet
collpan son 4-2 Conditions 6-18
4-2 Ascent Trajectory Space- 6-12 S-II Center Engine LOX
fixed Velocity and flight feedline Accuntulator Bleed
Path Angle Comparisons 4-2 System Performance 6-21
4-3 Ascent Trajectory Acceleration 6-13 S-11 Center Engine LOX
Convarison 4-3 feedline Accwwlator fill
b-b Dynamic Pressure and Mac3 Transient 6-21
hmher Comparison 4-7 6-14 S-II Center Engine LOK
b-5 Launch Vehicle Groundtrack 4-0 feedline Acclnlulator Helium
Supply System Performance 6-22
b-6 Injection Phase Space-
flxed Velocity and Flight 7-l S-IVB Start Box and Run
Path Angle iolrperisons 4-9 Requirements - first Burn 7-3
4-7 Injection Phase Acceleration 7-2 S-IVB Thrust Buildup Transient
Comparison 4-10 for First Bum 7-4
5-l S-!C LOX Start Bcx 7-3 S-IVB Steady State Performance
Requirements 5-2 - First Bum 7-6
S-2 S-IC Engines Thrust Buildup 5-3 7-4 S-1VB Thrust Decay 7-a
5-3 S-IC Stage Propulsion 7-5 S-IV8 CVS Perfomance -
Performance 5-4 Coast Phase 7-9
S-4 f-l Engine Thrust Decay 5-6 7-6 S-IVB Ullage Conditions
Durrng Repressurization
5-5 S-IC Thrust Decay 5-7 'sing 02/Q Currier 7-10
5-6 S-IC Fuel Tank Ul'age 7-7 S-IVB 02/H2 Burner Thrust
Pressure 5-8 and Pressurant Flwrate 7-l 1
5-7 S-It LOX Tank Ullage Pressure 5-9
7-0 S-IV6 Start Box and Run
6-l S-11 Engine Start Tank Requirements - Second Sum 7-12
Performance 6-3
7-9 S-IYB Steady State
6-2 S-II Engine Helium Tank Perfomance - Seand Bum 7-11
Presswes 6-4
7-10 S-IVB Engine Steady State
6-3 S-11 J-Z Engine Schematic 6-5 Perfornuncc During Sbge
Acceptance Test 7-16
6-h J-2 Engine Configuration
Changes 6-8 7-11 S-IVB LH2 Ullage Pressure -
First Bum and Paming Omit 7-19
6-4 S-11 Engine Punp Inlet
Start RequireRnts 6-8 7-12 S-IN LH2 Ullagc Pressure -
Second Bum and Translunar
6-5 S-11 Single Engine Thrust Coast 7-19
Buildup Characteristics 6-9
7-13 S-IV6 Fuel Plnp Inlet
6-6 S-11 Propulsion Performance 6-10 Conditions - First Bum 7-21
6-7 S-11 J-Z 0utbw-d Engine 7-14 S-IVB Fuel Pulp Inlet
Thrust Decay 6-12 Conditions - Second Bum 7-22
6-8 S-11 Fuel Tart Ullage
PrnPrSUre 6-15
vii
LIST OF ILLUSTRATIONS (C~~TUNJED)
r1gure rdw
7-15 .-ibb Staw r~hrntrcn
L"".loprs d-Y
7-:3 b-lfl S-IV6 vrbratlon Spectral
7-16 A!L3l?.SlS 8-9
7-25 9-l Trajectory and ST-124M
7-17 s-la LCI pu* Inlet Flatfom Velocity Com-
Conaltlons - Second Gum i-26 parisons. Boost-to4PO
(1raJectov-y Minus LVDCl 9-2
7-18 I-IVR Cold Helium Supply
History 7-27 9-2 Trajectory and ST-124M
Platform Velocity Com-
l-19 APS Module 1 Helium ~upoly parisons. Boost-to-TLl
Pressure 7-28 (Trajectory Minus LVM! 9-2
7-m S-lb% APS Accumulated Helium 9-3 Cmrparison of LVOC and post-
Leakage for Modules 1 dna 2 7-30 flight Trajectory During fp0.
7-21 APS Degulatcr Outlet X Position and Velocity 9-b
PITSSUIT T-32 9-d ConQarison of LVDC and Post-
7-22 S-IVB Anblent nellurn Inter- flight Trajector) Dur;ng EPO.
connect Spheres Schenlatlc 7-33 \ Posltion and Velocity 9-7
7-23 APS Module 2 Supply Pressure 7-35 9-5 Comparison of LVDC and Post-
flight Trajectory Dwing [PO,
7-20 APS Heltum Bottle/Regulator 2 Posi?ion and Velocity 9-8
Discharge Transducer Hountlng 7-36
9-6 Cmperiron of LVLK and Dost-
7-25 APS neltun Pressure flight Trajectory During EPO.
Regulator 1854601 7-36 Radius and Velocity 9-9
7-26 APS lieliun Regulator Outlet 9-7 Comdrison of CVGC and Post-
Pressure During Pressurization 7-37 flight Trajectoy During
7-27 APS Module 2 Regulator Boost to TLI. I Position end
Outlet Pressurn 7-38 Velocity 9-11
7-28 APS neliw Bottle/Regulator 9-8 Cqarison of LVLK and Post-
rDbuisncthinagrg e (PTrrodnpSodusCeedr Redesign) i-39 fBliogohst t toT rajTeLctIo. ry V PosDitiounri ng and
Velocity 9-12
7-29 S-IVB LOX Drnp and Ortrital
Safing Sequnce 7 -40 9-Y Comparison of LVOC and Post-
flight Trajectory During
7-30 S-IVB LOX m Parameter Boost to TLI. 2 Positiw and
Histories 7-12 Velocity 9-13
7-31 S-Iv9 LOX Tart u11age 9-10 Cmrisons of LVDC and Post-
Cce~sure - kcs~d Bum and flight Trajectory Dwifq
TrrczJ8Jr.r coils. 743 Boost to TLI, Radius and
8-l LonT;tudinal Acceleraton at Velocity 9-14
Ill and 01 During Thrust 9-11 Continuous Vent Systa, (CVS)
Buildw and Launch 8-2 Th-ust and kceleration
8-Z Longitudinal Load at Tim During EW 9-15
of kxinn Bending Ibrent. 9-12 AS-511 P:tch Attltudc Anp?e,
CECO and IXCO 8-2 FirSt Bum 9-18
El-3 Bending Moment and Load g-13 G-511 Yaw Attitude An9lc.
Factor Distribution dt Tim First Bum 9-19
of krimm Bending r)amt a-3
9-14 AS-511 Roll Attitude Angle.
8-4 Ill AcceleroRtcr Five Hertz First Gum 9-20
Rrsponse During S-It Bum
(Lowgittiinrl) 8-4 9-15 ;ztn$ and Actual Pitch
- Second Bum 3-23
B-5 IU and m Longitudinal
kcelcration After S-IC DECO 8-5 9-16 Comsmded and ktual Tn
Attitude - 5econd Bum 9-23
8-6 IU and C% Longitudinal
Acceleration After S-1' DECO 84 9-17 lnplitude of Cross-&balysis 9-25
0-Y AS-Sll/AS-510 kaleration and 10-l AS-511 Liftoff Vim Ranauver 10-2
Pressure Dscillatims [kring 10-Z a-511 Reconstructed
S-11 Bum (8 to 20 tls Filter) E-8 Liftoff Trajectory 10-3
0-8 AS-511 Pm Inlet Prersurr 10-3 Pitch Plane Dynamics During
and Thrust Pad kaltrrticm S-IC Bum 10-4
Oscillations During kcw-
lrtor Fill Transient (1 to 10-4 Va Plane Dynaics Ourin
110 Hz Filter) 8-8 S-IC Bum 10-S
10-S Pitch ard Yaw Platte Fme
St- Angle qf Attack
thing S-IC Bum 10-6
viii