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:::::::::::::::::::::::
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NATIONAL
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AERONAUTICS
AND
SPACE ADMINISTRATION
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FINAL
::::::::!_iiii!i! A P0 LL0 11 i:_:_:i:_:i:i:i:i:_:_:i FLIG H T PLA N
:::::::::::::::::::::::
i:i:i:i:!:i:i:i:!:!:!:i
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PREPA RED BY FLIGHT __ PLANNING BRANCH FLIG HT C REW SUPPO RT D IV IS IO N
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MANNED
SPACECRAFT
HOUSTON,TEXAS
CENTER
r
°.o=o
:::::::::::::::::::::::: _,._T_,
°'°°oO.'o'o'oOoO° ,
9_A_;'_.,',_ L_
.-t:.:.-.-.l.:.'.:.'.-.
APOLLO II APOLLO AS-506/CSM-IO7/LM-5 FINAL FLIGHT PLAN
JULY l,
1969
Flight
Planning
Branch
G. M. Col ton Flight Planning
Branch
?. A. Guil!ory Flight Planning
Branch
Aoproved
by:
/- y ,'--/ / W. J. A#rth Chief, Flight
<_:.-_-Crew Support Division
Donald_K. Director
Slayton of Flight Crev_lOperations
Concurrence:
__'_Low Manager,
_
_ ADollo • S _T//
_-'0_IJ'---@_-7"7 Spacecraft Pro.qram
, _ _ 7 /
,/,
,
2
Christo_hj_f _ C. Kraft,-d?._'" Director of Fligh_ Operations
Any con_ents or questions on this document should be forwarded to T. A. Guillory, Flight Planning Branch, mail code CF34, extensio_q 427l.
ACKNOWLEDGMENTS Acknowledgment is made to Spencer Gardner for their Apollo II Flight Plan. Messrs. technical Richard Rogers, William Killian support in the preparation of shown in the Flight the CM and LM During Plan were the Flight and the
Views of the earth and the P52 stars taken from the document, Views from of Apollo II (Mission G). The CSM and LM attitude information Lunar Orbit Attitude Sequence for
was taken Mission G.
from
the
document,
TABLE OF CONTENTS
Abbreviations Introduction
iii xi
SECTION I - GENERAL I. 2. 3. 4. 5. 6. 7. 8. 9. Mission Description SummaryFlight Summary Flight Plan (TLC-TEC) Plan (Lunar Orbit) l-l I-5 I-6 I-7 I-8 I-9 Data Data l-lO l-lO 1-13
LM Power Descent
Profile
CSM Burn Schedule LM Burn Schedule Lunar Landing Site
Landmark Tracking Flight Plan Notes
SECTION II I. 2. 3. Update Forms Table CSM Maneuver LM Maneuver
- UPDATE FORMS 2-I 2-2 2-27
Update Pads Update Pads - DETAILED TIMELINE
SECTION III I. 2. 3. Launch Phase TLI-T&D Translunar a. b. c. 4. Lunar a. b. Cislunar
3-I 3-3, 3-4
Coast Activities Navigation 3-7, 3-35 3-47 3-17
LM Familiarization Lunar Orbit Orbit Insertion
Activities 3-53 3-63
Second LM Ingress LM Activation and C/O
SECTION III c. Undocking d. Touchdown e. EVA f. g. h. LM Liftoff LMActive Docking LM Jettison
CONT'D 3-67 3-69 3-77 3-90 3-94 3-97 3-101 3-135
5. TEI-TEC 6. Entry SECTION IV DETAILED TEST OBJECTIVES I. 2. 3. Detailed Test Objectives Test Objective/Mission Test Objectives SECTION V - CONSUMABLES I. 3. 5. RCSPropellant Usage Activity Cross Reference
4-I 4-2 4-6
5-2 5-3 5-22 5-23 5-25 5-31 5-32 5-36 5-41 5-45 5-50
2. SM RCS Budget CM RCS Budget LM RCS Budget 4. SPS Budget 6. DPS Budget 7. APS Budget 8. 9. I0. II. CSM Budget EPS LM EPS Budget LM ECS Budget PLSS Budget SECTION VI - SUMMARYFLIGHT PLAN Summary Flight Plan
6-I
ii
ABBREVIATIONS ACCEL Accelerometer ACN Ascension ACT Activation ACQ Acquisition AEA Abort Electronics Assembly AGS Abort Guidance Subsystem AH AmpereHours ALSCC Apollo Lunar Surface Close-up Camera ALT Altitude AMPor amp Ampere ANG Antigua ANT Antenna AOH Apollo Operations Handbook AOS Acquisition of Signal or Acquisition of Site AOT Alignment Optical Telescope APS Ascent Propulsion Subsystem ARS Atmosphere Revitalization System ATT Attitude AUX Auxiliary AZ Azimuth BAT BDA Bio BP BT BU BW BRKT CAP COM CAL _ CAM CB CDH CDR CDU CEX CIN CIRC CK CM CMC CMD CMP CNTL C/O COAS COMM CONFIG Battery Bermuda Bio-Medical Data on Voice Downlink Barber Pole Burn Time Backup Black & White Bracket Capsule Communicator Calibration Angle Camera Circuit Breaker Constant Delta Altitude Commander Coupling Data Unit Color External Color Internal Circularization Check Command odule M Command Module Computer Command Command Module Pilot Control Check out Crew Optical Alignment Sight Communications Configuration
iii
CONT CP CRO CRYO CSC CSI CSM C&WS CYI DAP DB DCA DEDA DEGS DEPL DET DIFF DOI DPS DS DSE DSKY DTO DUA DWN E EASEP ECS ED EDT EFH El EL EMS EMU ENH EPO EPS EQUIP EST EVA EVAP EVT E×T f FC FDAI
Continue Control Point Carnarvon, Australia Cryogenic Contingency Sample Collection Coelliptic Sequence Initiation Command Service Module Caution and Warning System Grand Canary Island Digital Auto Pilot Deadband Digital CommandAssembly Data Entry and Display Assembly Degrees Depletion Digital Event Timer Difference Descent Orbit Insertion Descent Propulsion System Documented Sample Data Storage Equipment Display and Keyboard Detailed Test Objective Digital Uplink Assembly Down Erasable or Enter Early Apollo Scientific Experiment Environmental Control System Explosive Device Eastern Daylight Time Earth Far Horizon Earth (atmosphere) Interface Elevation or Electric Entry Monitor System Extravehicular Mobility Unit Earth Near Horizon Earth Parking Orbit Electrical Power Subsystem Equipment Eastern Standard Time Extravehicular Activity Evaporator Extravehicular Transfer External F Stop Fuel Cell Flight Director
Package
Attitude
Indicator
iv
FLT _I FOV fps or FPS FT or ft FTO FTP GBI GBM GDC GDS GET GETI GLY GMT G&N GNCS GNM GYM H2 HA HAW HBR HD HGA HI Hp HSK HTR HTV ICDU ID IGA IGN IMU INIT INT IP ISA IU IVC IVT JETT KM kwh
Flight Frequency Modulated Field of View Feet per second Feet Flight Test Objective Full Throttle Position Grand Bahama Islands Grand Bahama (MSFN) Gyro Display Coupler Goldstone, California Ground Elapsed Time Ground Elapsed Time of Ignition Glycol Greenwich Mean Time Guidance and Navigation Guidance Navigation Control System Guam Guaymas, Mexico Hydrogen Apogee Altitude Hawaii High Bit Rate (TLM) Highly Desirable High Gain Antenna High Perigee Altitude Honeysuckle (Canberra, Heater USNSHuntsville
Australia)
Inertial Coupling Data Unit Identification Inner Gimbal Angle Ignition Inertial Measurement Unit Initialization Intervalometer Initial Point Interim Storage Assembly Instrumentation Unit Intervehicular Communications Intravehicular Transfer Jettison Kilometer Kilowatt Hour
LA LAT LBR LBS or Ibs LCG LDG LDMK LEB LEC LFH LGC LH L/H LHEB LHFEB LHSSC LiOH LLM LLOS LM LMP LNH LOI LONG LOS LPO LR LRRR or LR3 LS LT LTG LV L/V LVPD M MAD MAN MAX MAXQ MCC MCC-H or MCC MDC MEAS MER MESA MET
Launch Azimuth Latitude Low Bit Rate (TLM) Pounds Liquid Cooled Garment Landing Landmark Lower Equipment Bay Lunar Equipment Conveyor Lunar Far Horizon LM Guidance Computer Left-hand Local Horizontal Left-hand Equipment Bay Left-hand Forward Equipment Bay Left Hand Side Storage Container Lithium Hydroxide Lunar Landing Mission Landmark Line of Sight Lunar. Module Lunar Module Pilot Lunar Near Horizon Lunar Orbit Insertion Longitude Loss of Signal or Loss of Site Lunar Parking Orbit Landing Radar Laser Ranging Retro-Reflector Landing Site Light Lighting Launch Vehicle Local Vertical Launch Vehicle Pressure Display Mandatory Madrid, Spain Manual Maximum MaximumDynamic Pressure Midcourse Correction Mission Control Center - Houston Main Display Console Measurement USNS Mercury Modularized Equipment Mission Event Timer
Stowage Assembly
vi
MGA M/I MIN MLA MNVR MPS MSFN MTVC N2 NAV NM NOM NXX 02 OBS O/F OGA OMNI OPS ORB ORDEAL ORIENT OVHD P PAD PCM PC PDI PGA PGNCS PIPA PLSS PM POL PRE PREF PREP PRESS PRIM PROP PSE PT PU PUGS
Middle Gimbal Angle Minimum Impulse Minimum Merrit Island, Florida Maneuver Main Propulsion System Manned Space Flight Network Manual Thrust Vector Control Nitrogen Navigation Nautical Miles Nominal NounXX Oxygen Observation Oxidizer to Fuel Ratio Outer Gimbal Angle Omnidirectional Antenna Oxygen Purge System Orbital Orbit Rate Display Earth Orientation Overhead
and Lunar
Pitch or Program Voice Update Pulse Code Modulation Plane Change Powered Descent Initiation Pressure Garment Assembly Primary Guidance Navigation Control Section Pulse Integrating Pendulous Accelerometer Personal Life Support Systems Phase Modulated Polarity or Polarizing Pretoria, South Africa Preferred Preparation Pressure Primary Proportional Passive Seismic Experiment Point Propellant Utilization Propellant Utilization and Gaging System
vii
PTC PWR PX× Qty R R&B RAD RCDR RCS RCU RCV RED REFSMMAT REG REQD RH RING RLS RNDZ RR RSI RT RTC RXX SA S/C SCE SCS SCT SEC SECO SECS SEP SEQ S-IVB SLA SLOS SM SPOT SPS SR SRC SRX SS STX
Passive Thermal Power Program XX Quantity
Control
Roll or Range Red & Blue Radiator Recorder Reaction Control System Remote Control Unit Receiver USNSRedstone Reference Stable Member Matrix Regulator Required Right-hand Ringsite Radius of Landing Site Rendezvous Rendezvous Radar Roll Stability Indicator Real Time Real Time Command Routine XX Shaft Angle Spacecraft Signal Conditioning Equipment Stabilization Control System Scanning Telescope Secondary S-IVB Engine Cut-off Sequential Events Control System Separate Sequence Saturn IV B(Third Stage) Service Module LM Adapter Star Line-of-Sight Service Module Spot Meter Service Propulsion System Sunrise Sample Return Container S-Band Receiver Mode No. X Sunset S-Band Transmit Mode No. X
viii
S.V. SWC Sw SXT T EPHEM TA TAN TB TCA TD&E TEC TEl TEMP TERM TEX TGT TIG TLC TLI TLM or TM TPF TPI TPM T/R TRANS TV TVC TWR US V VAN VHF VLV VI VOX VXX W/O WRT WTN XFER XMIT XPONDER Y
State Vector Solar Wind Composition Switch Sextant Time of Ephemeris Update Trunnion Angle Tananarive, Madagascar Time Base Time of Closest Approach Transposition Docking & LM Ejection Trans Earth Coast Transearth Insertion Temperature Terminate Corpus Christi, Texas Target Time of Ignition Trans Lunar Coast Translunar Insertion Telemetry Terminal Phase Final Terminal Phase Initiation Terminal Phase Midcourse Transmitter/Receiver Translation Television Thrust Vector Control Tower United States Velocity USNS Vanguard Very High Frequency Valve Inertial Velocity Voice Keying Verb XX Without With Respect to USNSWatertown Transfer Transmit or Transmitter Transponder Yaw
ix
aV _VC _R 8-balls
Velocity Velocity Position Flight
Change (Differential) Change at Engine Cutoff Change (Differential) Director Attitude Indicator (FDAI)
CAMERA NOMENCLATURE EL/250/BW-BRKT Electric Hasselblad/250mm Black & White film-Camera Intervalometer (f-stop 5.6, shutterspeed=250 Infinity) Lens/ Bracket 1 sec,
INT _f5.6,250,INF)
16mm/18/CEX-BRKT MIR (fS,250,INF) 6fps
16mm Camera/18mm Lens/Color Film External-Camera Bracket Mirror (f-stop 8, shutterspeed 1 = _-5_O-sec, Infinity) 6 frames per sec
SYMBOL NOMENCLATURE LUNAR PENUMBRA(OCCURS PRE LOll)
SPACECRAFT SUNSET -HONEYSUCKLE 85FT D_SH COVERAGE -DARKNESS (UMBRA) -MSFN LOS -SPACECRAFT SUNRISE .LUNAR P,ENUMBRA(OCCURS PRE LOll) JLUNAR SURFACE
/
EARTH (ALWAYS) _ DOWN \(5-_
WINDOW
S-BAND HGA
_----_" _/_ "7 i\_'_../j_ 7
X
I
,
OPTICS --S-BAND STEERABLE SUBSOLAR POINT MSFN AOS 'MADRID 85FT DISH COVERAGE
I I I
.GOLDSTONE D!S_ COVERAGE 85FT
LUNAR TERMINATOR SPACECRAFT SUNSET
DARKNESS
MSFN LOS SPACECRAFT SUNRISE LUNAR TERMINATOR
xi
INTRODUCTION This Flight Plan has been prepared by the Flight Planning Branch, Crew Support Division, with technical support by TRW Systems. This document schedules the AS-506/CSM-IO7/LM-5 to fulfill, when possible, the test objectives quirements, G Type Mission Lunar Landing. operations defined in Flight
and crew activities the Mission Re-
The trajectory parameters used in this Flight Plan launch, with a 72° launch azimuth and were supplied Analysis Division as defined by the Apollo Mission Trajectory.
are for July 16, 1969 by Mission Planning and G Spacecraft Operational
The Apollo II Flight Plan is under the configuration control of the Crew Procedures Control Board (CPCB). All proposed changes to this document that fall in the following categories should be submitted to the CPCB via a Crew Procedures Change Request: I. 2. 3. 4. Items Items Items that that that impose additional impact result result Flight require the in crew training or impact test crew procedures. objectives. change. activity
accomplishment a significant major
of detailed RCS or activities
EPS budget
Items that day in the Items that
in moving Plan. a change
to a different
5.
to the
flight
data
file. what proposed changes
The Chief, Flight fall in the above
Planning Branch categories.
(FCSD) will
determine
Mr. T. A. Guillory will act the Apollo II Flight Plan.
as co-ordinator
for
all
proposed
changes
to
Any requests for additional copies or changes to the distribution this document must be made in writing to Mr. W. J. North, Chief, Support Division, MSC, Houston, Texas.
lists Flight
of Crew
xii
SECTION I - GENERAL
MISSION
DESCRIPTION
I.
Launch and EPO (a) Nominal window (b) Earth 43 sec. (c) (d)
(Duration time of
2:44) is 9:32
LIFT OFF - 2:44 EDT, July 16,
GET 1969, with a launch
launch duration orbit after
4 hrs. into
24 rain. a I00 nm circular orbit at II rain.
insertion lift-off
CSH systems Optional night
C/O in earth
orbit to the pad REFSrIHAT during the first
IHU realign
(P52)
period occurs at 2:44:26 GET over (See Table the I-I Pacific for burn Ocean during data). the
(e)
TLI
second
revolution.
2.
Translunar After tory, (a) TLI, the
Coast which following
(Duration places major docking the
73:10) spacecraft
2:44
- 75:54
GET lunar LOI: SIVB photoreturn trajec-
in a free prior to
events
occur
Transposition, graphy
and LH ejection,
including
(b) (c) (d)
Separation
fror.1 SIVB and a CSH evasive venting of propellants navigation sets at 06:00
maneuver (slingshot) sightings, GET and five star/earth sets hori-
SIVB propulsive Two series zon, GET
of P23 cislunar of five
consisting
at 24:30
(e)
Four midcourse
corrections
which with
take
place
at TLI + 9, TLI + 24, zero (See Table I-I).
LOI - 22 and LOI - 5 hours
AV nominally
I-I
(f)
Passive
thermal
control
(PTC) will do not require
be conducted different
during attitudes.
all
periods
when other (g) (h) LM inspection
activities
and housekeeping at 75:54:28 GET, ends the TLC phase.
LOI l , performed
3.
Lunar
Orbit
(Duration
59:30) 69:00
75:54
- 135:24
GET
LOI Day (a) (b) (c) (d) LOIl
(Duration
25:00)
- 94:00
Photos LOI2
of targets
of opportunity
Post LOI 2 LM entry tests will
and inspection.
S-Band/VHF
B Voice
be conducted. tracking (one set of sightings)
(e)
Post
LOI 2 Pseudo landmark I-4) of 9 hours
(See Table (f) Rest period
DOI and EVA Day (a) (b)
(Duration
28:00)
94:00
- 122:00 GET
Docked LM activation Docked landing (See Table I-3) site
and checkout landmark sighting (one set of sightings)
(c) (d) (e) (f) (g) (h)
Undocking DOI thru LM post Rest
and separation landing touchdown (See Figure and simulated 4 hours I-3 Powered Descent) liftoff
period
(LM) of change
CSM plane Rest period
(CSM) of 4 hours
I-2
(i) (j) (k) (1) (m)
EVA prep EVA for 2 hours 40 minutes
Post EVA Rest period Rest period (LM) 4 hours 40 minutes
(CSM) 4 hours 50 minutes
Ascent (a) (b)
and TEl Day LM Lift-Off LM active CSl PC CDH TPI Braking
(Duration
25:00)
122:00
- 147:00
GET
and Insertion rendezvous
(c) (d) (e) (f)
Docking LI.I jettison TEl Rest Period
4.
Lunar (a) (b) (c)
Orbit
Particulars start duration period
(Average
Values
for
a 60 x 60 nm orbit)
Revolutions Revolution S/C niqht
at 180 ° longitude - l hr. 58.2 rain. ;.i;
#
duration
-
- 47 rain. 72 rain. July 16,
(d) MSFN coverage per rev. (e) Orbit inclination
/
._ /
- 1.25 ° for
1969 launch
I-3
-_
(f) (g) (h)
S/C orbital Lighting Horizon lunar
rate change
- 3°/min. at fixed
(.05°/sec) ground point - l°West/Rev. angle on the
visibility surface degree
+ 20 ° selenocentric
(i) (j) (k)
One lunar Site 2 will
on lunar
surface
is
16.35 at
nm
be visible point
(3 ° sun angle) to horizon
REV. 7
S/C subvehicle
327 nm.
5.
Transearth Transearth the (a) following Three
Coast coast
and Entry begins with
(Duration TEl at
59:39) 135:24:34
131:52
- 195:03
GET of
GET and consists
major midcourse
events: corrections with takes GET. occur in the Pacific GET. local This time. Ocean at a longitude will occur of are scheduled zero. GET and Entry Interface at TEl + 15, El - 23
and E1 - 3 hours (b) CM/SM separation occurs (c) at 195:03 will
AV nominally place
at 194:51
Splashdown about
172.4 ° West at prior to
195:17 sunrise
approximately
25 minutes
I-4
_'
o
l
1-5
1-6
/
.
i /
I
_
8
/
°
I!
1-8
TABLE I-3
LUNAR LANDING SITE DATA
DAY
SITE DESIG
LATITUDE
LONGITUDE
ILAUNCH AZIMUTH/ SUN ELEVATION 72°/10.5 °
2LAUNCH AZIMUTH/' SUN ELEVATION 108c/13.5 °
JULY 16 2(IIP6) 0932 EDT
00°42'50"N 00.71388889°N (00.6914°N)
23°42'28"E 23.70777778°E (23.7169°E) 3
JULY i8 3(lIPS) I132 EDT JULY 21 5(IIPi3) 1409 EDT
O0°21'lO"N 00.35277778°N O!°40'41"N 01.67805556°N
01°17'57"W 01.29916667°W 41"_53'57"W 41.89916667°W Landing
89.295°/II
°
I08°/13
°
94.6775/9.7
°
I08°/II.7
°
Data From TJ memo, Accuracy May 12, 1969, TJ-69-499o i L o 3
"r T im!o
Estimates,
Site
Landmarks,
Sun Elevation
Angles
Are
For Approximately
27 Hours
After
LOI,
Ist
Opportunity
Includes 2nd Opportunity TLI Data From MPAD memo, landing June 12, 1969, 69-FM41-181. TABLE I-4
site
coordinates
for
G,
LANDMARK TRACKING DATA July 16 Launch LONGITUDE DELTA ALTITUDESUNEL (nm) 000.00 43°
LANDMARK DESIG.
LATITUDE
A1(Pseudo)
2°N 2.000°N l °53'N l .885°N 01°15'56"N 01.26555556°N (Ol .24307°N)
65 30' ° 60.500°E 28o42 'E 28.726°E 23o40'44 '' 23.67888889°E l (23.6880°E) 24°53'20°E 24.88888889°E 23°44' 37"E 23.74361111°E 23°30' 55"E 23.51527778°E site 2 position, l-lO
IP(130)
000.00
130(Prime LDG SITE 2)
-OOl .68
8.5 °
123 (Alternate LDG SITE 2) 129 (Alternate LDG SITE 2) 133 (Alternate LDG SITE 2) l Data June
00°30'I 9"N 00.50527778°N Ol °17'06"N 01.28500000°N D0°,17' 14"N 00.78722222°N
-001.71
-OOl .76
-OOl .68
from HPAD memo, landing 20: 1969, 69-FM41-199.
TABLE I-4
LANDMARK TRACKING DATA (CONT'D) July 18 Launch DELTA ALTITUDESUN EL (nm)
LANDMARK DESIG.
LATITUDE
LONGITUDE
IP(GI)
O°I6'N 0.267°N 01°17'06"N 01.28500000°N O0°I8'N O0.300°N 00°36'51"N 00.61416667°N 00°16'59"N 00.28305556°N 00°03'42"N 00.06166667°N
32°19'E 32.317°E 23°44'37"E 23.74361111°E 3°23'E 3.383°E 01°04'39"W 01.07750000°W 01°25'43"W 01.42861111°W 01°16'36"W 01.27666667°W -O01.Ol 9° -001.97 26°
GI(129)
IP(143)
143(Prime LDG SITE 3) 150(Alternate LDG SITE 3) 147(Alternate LDG SITE 3)
-001.01
-
-000.99
-
I-II
TABLE I-4
LANDMARKTRACKING DATA (CONT'D) July 21 Launch DELTA ALTITUDESUN EL (nm)
LANDMARK DESIG.
LATITUDE
LONGITUDE
IP(GI)
O°30'S O.5OO°S I°42'N 1.696°N 0°36'N 0.608°N 01°30'37"N 01.51027778°N 01°20'04"N 01.33444444°N 01°45'33"N 01.75916667°N 02°03'I0"N 02.05277778°N
26°33'W 26.550°W 32°I0'W 32.162°W 36°34'W 36.567°W 41°49'05"W 41.81805556°W 40°47'34"W 40.79277778°W 41°34'12"W 41.57000000°W 42°13'41"W 42.22805556°W -001.77 8°
Gl
IP(180)
_
180(PRIME LDG SITE 5) 171(Alternate LDG SITE 5) 178(Alternate LDG SITE 5) 184(Alternate LDG SITE 5)
-001.25
8.9 °
-001.29
-001.22
-
-001.23
1-12
FLIGHT PLAN NOTES
A.
Crew I. Crew designations are as follows: Designation Co_nander (CDR) Command Module Pilot (CMP) Lunar Module Pilot (LMP) 2. Crew positions during Left Launch thru TLI CDR T&D thru Entry CMP MannedM L CMP 3. the mission CSM Center LMP CDR
Prime Armstrong Collins Aldrin are as follows: Right CMP LMP
Backup Lovell Anders Haise LM Left Riqht
CDR
LMP
The crew will eat and sleep simultaneously throughout the mission. Eat periods will be normally l-hour duration, with additional activities held to a minimum during this time frame. Sleep periods will normally be 8 to lO hour duration with two 4 to 5 hour sleep periods while the LM is on the lunar surface. Activity Launch to insertion Insertion to TLI TLI to evasive mnvr TLC & LOI l&2 LM activation & checkout PGAConfiguration PGA's with helmet & gloves (H&G) PGA's without H&G PGA's with H&G Constant wear garments PGAwithout H&G (CMP H&G donned for latch cocking & CDR/LMP H&G donned for pressure integrity check and cabin reg check) PGA's with H&G except CMP without H&G after DOI PGA's without H&G except for CDR/LMP simulated countdown & EVA PGA's with H&G (except H&G off after docking) Constant wear garmets
4.
Undocking Touchdown
through through
touchdown pre lift-off
Liftoff
through
LM jettison splashdown
LM jettison
through
1-13
5.
Two crew status reports via air-to-ground commmunications will be made by the flight crew during each activity day. The first report will be given after the first meal of the day and will concern the sleep obtained during the previous sleep period. The second report will be given following the final meal of the day and will concern the radiation dose received during the previous 24 hours and medication taken if any. The following information should be logged: a. Food Consumption b. Exercise c. Used fecal bags marked as to crewman and GET Negative checklist. Continuous ground. reporting will be used in reporting completion of each
6.
7.
CSM biomedical
data
are automatically
transmitted
to the
8.
LM biomedical ing to docking
switching is as scheduled
performed manually in the timeline.
by the
LMP from
undock-
9.
All onboard gage readings and will not be corrected
will be read directly from the by the appropriate calibration
gages. factors,
B.
Photograph i Photographic requirements were derived a. Lunar Surface Operations Plan b. Photographic Operations Plan
from
the
following:
Co
Procedures I. CSM Crew procedures called out in the flight plan may be found following documents: ,{_ 1 a. Apollo Operations Handbook - CSM-I07 (AOH), Volume 2 b. Crew Checklist c. CSM Rendezvous Procedure d. Abort Summary Document e. Apollo Entry Summary Document f. Photographic Operations Plan g. Descent Procedures Document h. Ascent Procedures Document i. Lunar Landmark Tracking Attitude Studies j. Lunar Orbit Attitude Sequence for Mission G k. Data Priority Documents
in
the
l -14
2.
LM Crew procedures called out in the flight plan may be found following documents: VC_,_ L a. Apollo Operations Handbook LM-5 Volume 2 b. Crew Checklist c. LM Rendezvous Procedures d. LM Descent/Ascent Summary Document e. Lunar Landing Phase Photographic Operations Plan f. Data Priority Documents g. EVA Procedures h. Apollo Lunar Surface Operations Plan
in
the
D.
Communications I. General a. CSM and LM HBR data transmissions in lunar orbit will normally require the use of the high gain or steerable antennas b. During communications, the spacecraft will be referred to by name (Apollo II) and MCC-H will be referred to as Houston. c. The preferred S-Band communications are: Tl) CSM TaT Uplink Mode 6 (Voice, PRN, and Updata) (b) Downlink Mode 2 (Voice, PRN, TLM-HBR) (2) LM Ta) Uplink Mode 7 (Voice, Updata) (b) Downlink Mode l (Voice, TLM-HBR) d. LM voice recorder has a maximum utilization of lO hours. This recorder will be used during LM operations to record all LM voice data during undocked operations (27 hours 42 minutes). This recorder will be operated in the VOX mode. e. A small portable voice recorder will be carried in the CM to be used at the discretion of the crew as a voice recorder backup. This recorder will not be transferred to the LM for use during undocked operations. f. The S-band"squelch" will be on during the sleep periods in order to prevent MSFN fade-out noise from disturbing the crew. 2. DSE Operation a. The DSE will normally be operated via ground command except for special cases where the operation is time limited. In these cases the crew may be asked to rewind the tape. b. During the earth orbit period when the CSM is not over a MSFN station, CSMTLM-LBR data will be recorded on the DSE and will be dumped during the pass over the US and over CRO prior to TLI if possible. c. DSE will be used for CSM HBR and voice recording during all CSM engine burns. d. DSE data and voice recordings will be made in CSM LBR mode whenver possible in order to minimize the DSE dump time.
1-15
e.
f.
g. 3.
During PTC using the HGA REACQ communications mode the DSE will be used to record LBR data when the HGA is not in the MSFN field of view. During lunar orbit LM operations, the DSE will be used to record LM-TLM-LBR data during all docked LM activites that occur on the lunar farside. For undocked LM activites only DOI will be recorded as VHF ranging is required. DSE will be used to record all H_BRentry data during the blackout region.
Launch - Earth Orbit Phase a. OMNI B and VHF LEFT will be selected for lift off. OMNI D will be selected by the crew during boost phase if the launch azimuth is less than 96 ° or OMNI C if the launch azimuth is greater than 96 ° . OMNI D will probably be the best antenna for earth orbit. b. VHF Duplex B will be used for launch, and Simplex A for earth orbit operations. c. VHF Simplex A will be used for entry to be compatible with recovery forces communications. Translunar and Transearth Coast Phase The translunar and transearth sleep communications mode will be as follows. The CSM x-axis will be placed normal to the ecliptic plane. The CSM will be rolled at a rate of approximately three revolution per hour. During the near earth sleep periods prior to 30 hours GET (range less than 120Knm) omni antennas B and D will be used. During the other sleep periods (beyond 120Knm) the high gain antenna may be required (in the REACQ mode). The REACQ configuration will provide approximately 210 degrees of HGA coverage per CSM/LM revolution or 35 minutes of MSFN coverage per hour. The REACQ configuration will also allow MCC-H to use real time control to select TLM HBR or LBR and to dump the DSE during each spacecraft revolution. Lunar Exploration Phase a. Normal CSM communications between MSFN/LM will be by S-Band during the lunar exploration period. b. If additional communications capability is required the S-Band erectable antenna will be deployed by the EVA crewman and will be utilized for all LM/MSFN/CSM communications. c. During periods when both crewmen are EVA, the "AR" position (Relay Mode) will be the normal communication mode on each of the Extravehicular Communication System (EVCS). The CDR will relay the LMP VHF voice and data to the LM which in turn will relay to MCC-H via S-Band.
4.
5.
1-16
E.
CSMNotes I. Electrical Power System and Water Management a. Spacecraft lift-off switch positions are listed in the Apollo Operations Handbook (Volume 2) for CSM 107. b. The CSM will remain fully powered up throughout the mission (CMC, IMU and SCS in the "operate" configuration and optics power-up as required). c. Fuel cell H2 and 02 purging is scheduled as follows H2 approximately every 48 hours and 02 approximately every 12 hours. d. The hydrogen and oxygen VAC ION pumps will be inactive throughout the mission. e. Potable water will be chlorinated once a day before each sleep period, starting with the First sleep period (GET 13:30). The POT H20 inlet valve will be opened prelaunch. f. FC purges and waste water dumps will not be scheduled within one hour prior to optical sightings. g. Waste H20 dumpin9 will be managed to allow: -(T)---Maximum QTY:85-90% (2) Minimum QTY:25% (3) At LOI:QTY : 75% (4) At CM-SMSEP:QTY = 90% to 100% (5) No dumping after MCC3 until after LOI (6) Dumps will be performed (if required) within 2 hours preceding MCC maneuvers (7) In lunar orbit if dumping is required, dumps will be performed immediately prior to sleep periods (8) The water dump will not be operated in the automatic mode at anytime during the mission h. The cryogenic heaters will be in AUTO during the mission and the fans will be operated manually. The fans will be cycled for one minute before and after each sleep cycle. i. The batteries will be charged according to the following schedule: Time Battery 5:20:00 B 12:20:00 A 48:10:00 B 80:25:00 A 103:30:00 B 148:00:00 A 154:00:00 B 2. Environmental Control System and Cabin Pressurization a. One C02 odor absorber filter (LiOH canister) is changed approximately every 12 hours or if C02 partial pressure is greater than 7.6mm Hg. There are 20 filters (2 in the canisters onboard and 18 stowed).
1-17
b.
A Pre TLI/LOI ECS redundant component check including the secondary evaporator operation, is performed prior to TLI and LOI. The secondary evaporator water control valves will be turned "OFF" after the check. The evaporator operation will be as follows: (I) Launch - primary loop operation (2) Earth Orbit - primary loop operation and secondary loop test plus redundant operation test prior to TLI. (3) Post TLI - deactivate both evaporators (4) Pre LOI-ECS pre TLI/LOI redundant component check and primary evaporator activation (5) Post TEl - deactivate primary evaporator (6) Entry interface minus 1 hour - activate primary and secondary evaporator.
c.
3.
Guidanceand Navigation ,_ a. During lunar orbit, the CSM and LM will utilize the same landing site REFSMMAT such that the gimbal angles would be 0,0,0 at landing with the LM sitting face forward on landing _ site number two and the CSM over the landing site pitched up 90 ° from local horizontal "heads up". b. During PTC the CSM/LM x-axis is Ditched up 90° (Nor for TLC and down 90° (South) for TEC with the Y-Z axes in the plane of the ecliptic. This change in x-axis pointing is to enable simultaneous viewing of the earth and moon through the side windows while maintaining a favorable high gain antenna position. c. The CSM tracking light will be on continuously from undocking to landing and from LM lift-off to docking. Landmark Tracking The following ground rules were used for landmark tracking. a. IMU to be realigned on the dark side preceding each tracking period. b. MSFN is reacquired after each tracking period. The tracking data will be acquired by MSFN after all the marks have been made and while N49 (AR,AV) is displayed. MSFN will give a GO when data acquisition has been verified. c. The pseudo landmark tracking (AI) will be used to determine the altitude of an area in which the LM will be making altitude checks after DOI. The data will be processed during the sleep period after the trackings and relayed to the LM prior to undocking.
4.
1 -18
o
d.
In the docked configuration the CSM/LM _'_ _r_/_{_ approaches the landmark in an inertial hold attitude. This inertial attitude places the spacecraft 2° below the local horizontal at the 35 ° elevation angle point. At 35 ° elevation angle a pitch down of O.3°/sec is initiated. Five marks are then taken with the time between marks a minimum of 25 In the seconds. undocked tracking (See configuration profile) the CSM approaches the landmark in ORB RATE and pitched down 22° from the local horizon -/ tal. At 35° elevation angle five marks are taken with the time between marks a minimum of 25 seconds. ORB RATE is continued throughout the marking period. will approach the LM in ORBRATE heads In and pitched tracking the CSM up the undocked COAS ° from the local down 40 horizontal. When the LM is centered in the COAS the CSM will initiate a variable pitch rate to keep the LM centered in the COAS. /_r_. _22 _ /_ _ir_/_'--_ 0 \ _o_,,_ _'.\\\ " \ 40° ..... \ \\_ °
e.
f.
5.
CSM/LM and CSM attitude maneuvers will normally be at a rate of O.2°/sec or O.5°/sec. unless other rates are required. NOTE: At 0.2°/sec,15 minutes is required to maneuver 180 ° . At O.5°/sec, 6 minutes is required to maneuver 180 ° . Passive thermal control mode will be initiated after MCCl or as soon as MCCI is scrubbed and maintained throughout the mission (except in lunar orbit) until at least three hours before entry except for interruptions for midcourse corrections, communications orientation (maximum interruption of three hours). PTC will not be initiated before approximately 7:00 GET. Service Propulsion on Bank A except System All SPS burns will LOll which will be initiated be initiated on Bank B.
6.
7. F.
LM Notes I. Entries into the LM a. Three entries into the LM are scheduled in the at 56:30, 81:30 and 95:52 GET respectively.
timeline
1-19
2.
The first entry (56:30 GET) will be for LM familiarization and will be performed by the CDR and LMP in the constant wear garments. During this period there will be approximately 5 minutes of VHF-B LBR data which will be recorded by the DSE in the CSM. The LM will remain on CSM power during the crew familiarization period. c. The second entry (81:30 GET) will be for LM housekeeping and will be performed by the LMP in constant wear ga_lents. During this period the LM will go to internal power for the S-Band/VHF B voice activation. d. The third entry into the LM (95:52 GET) will be performed by the LMP in LCG's to prepare the LM for undocking and descent to the lunar surface. During this period the LMP and CDR initially transfer to the LM in LCG's then return to the CSM for PGA donning. Environmental Control System and Cabin Pressurization a. The LM cabin will contain ambient air at lift off and will bleed down to zero pressure psi during the launch. b. The LM will be pressurized for transposition and docking after which it will be isolated and the pressure periodically monitored. c. The LM will be pressurized prior to the first entry (LM familiarization) after which it will be isolated again for the remainder of the TLC period. Prior to the second entry (LM housekeeping) it will be pressurized again and will remain pressurized.
b.
d.
3.
Guidance and Navigation a. Two LGC erasable memory dumps and MCC-H verifications will be accomplished prior to DOI. If a significant number of errors are found, memory correction and re-verification will be performed before DOI. b. The LM IMU will be manually aligned to the CSM IMU during the DOI Day LM activation and checkout. P52/AOT alignments will be performed as close to DOI as possible. c. All translations during the undocked manned LM operations will be under PGNCS control. d. The capability for MCC-H to update the LGC via uplink will normally be blocked by the LMP UP-DATA LINK switch (panel 12).
1 -20
4.
RCS Operation and Interface Constraints a. During CSM/LMdocked checkout operations, the LM steerable and/or RR antennas will not be powered down once they have been activated. The SM B3 and C4 thrusters will be deactivated before the LM steerable and/or RR antennas have been unstowed in order to prevent SM-RCS impingement on these antennas. b. The CSMroll jets and LM yaw jets will be disabled when the probe is preloaded (docking latches are cocked} and the tunnel is pressurized prior to undocking. The jets will be activated after tunnel venting. c. LM RCS two jet ullaqe (System B) will be used for unstaged ullage maneuvers in order to prevent asymetrical RCS thrust caused by impingement on the descent stage. d. The RCS interconnect will be used during the APS lift-off and ascent, but will not be used during the rendezvous maneuvers. Rendezvous a. The rendezvous radar will be pointed away from the sun and will be turned off when no functional use is required to prevent overheating of the antenna. b. The LM tracking light will be on continuously between separation and touchdown and between launch and docking except during PGNCS/AOT alignments. During PGNCS/AOT alignments (LM P52), the tracking light would interfere with the alignments. (dark adaption)
5.
1-21
1-22
Z I.L
-23
SECTION II
- UPDATE FORMS
UPDATE FORMS This Flight I. 2. 3. 4. 5. 6. 7. 8. 9. TLI section Data contains File are the update the pads which are in the
onboard
spacecraft.
The CSM forms
as follows:
Maneuver Data
P37 Block P27 Update
P30 Maneuver P76 CSM Rendezvous Lunar Earth Earth Entry Orbit Orbit are:
(External
_V)
Rescue
Entry Block Data
The LM forms !. 2. 3, 4. 5, 6. 7. 8. 9. I0. II.
P27 Update AGS State Phasing Vector Update
P30 LM Maneuver
P30 LM Maneuver DOI Data PDI Data Lunar Surface
LM Ascent CSI Data CDH Data TPI Data
2-I
TLI
--I r-" .._1
X X X X X X X X X X X X X + X X X X X X X X X X X X
X X X X X X X _X X X X X X + X X X X X X X X X X X X X X X X X X
TB6p R P Y BT _VC' VI R p Y R P Y SEP TLI
_-
EXTRACTION
O', ',O O_
.-I FI
2-2
TLI
PAD X:XX:XX (HR:MIN:SEC) PREDICTED TIME OF BEGINNINGF O S-IVB RESTARTPREPARATION FOR TLI (TB6 = TLI IGN -578.6 SEC) PREDICTED SPACECRAFT IMU GIMBAL ANGLES ATTLI IGNITION DURATION OFTLI BURN NOMINAL TLI _V SETINTO EMS AV COUNTER NOMINAL INERTIAL VELOCITY DISPLAYED ON DSKY AT TLI CUTOFF PREDICTED SPACECRAFT IMU GIMBAL ANGLEST COMPLETION A OF S-IVB MNVRTO CSM/S-IVB SEP ATTITUDE PREDICTED SPACECRAFT IMU GIMBAL NGLES A ATTIME OF CSM EXTRACTION OF LM FROM S-IVB
TB 6p
R p y BT _VC
XXX(DEG) XXX (DEG) XXX (DEG) X:XX (MIN:SEC) XXXX.X (FPS)
VI
+XXXXX (FPS)
R SEP P SEP Y SEP
XXX(DEG) XXX(DEG) XXX (DEG)
R EXT P EXT Y EXT
XXX(DEG) XXX(DEG) XXX (DEG)
2-3
P37 BLOCK DATA
' I.
X l X
[
!
X X t ' _VT LONG GET400K GETI _VT LONG GET400K GETI
O T,
il _
!
X X X X
X X GET400K GETI X X I
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X X LONG
AVT
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X X GET400K GETI LONG
AVT
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X X X LONG
X AVT
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_O O _.
GETI X X X X AVT LONG GET400K GETI X X X X AVT LONG GET400K
-<1:
2-4
P37 BLOCK DATA GETI XXX:XX (HR:MIN) XXXX (FPS) +XXX(DEG) XXX:XX (HR:MIN) DESIRED TIME OFIGNITION
ZVT LONG GET400K
TOTAL VELOCITY MNVR OF LONGITUDE OFTHELANDING POINT FOR ENTRY GUIDANCE TIMEOF ENTRY INTERFACE
2-5
P27 UPDATE PURP GF T V • INDEX INDEX V VI
n
304 .)1 INDEX O2 O3 O4 O5 O6
bo
"_
07
11 12 13 14 15 16 17 2O 21
O'_ O_
22 23 24 N34 HRS X X X MIN X X X X X X 0 X X X X X X X i X X 0 [
I
. • _
NAV CHECK SEC N43 LAT
LONG ALT + 0 i + 0_
2-6
P27 UPDATE - CSM PURP XXX TYPE OFDATA TOBE RECEIVED (SUCH AS: CMC TIME) TYPE OFCOMMAND LOAD (70-71-72-73) TIMEDATA RECORDED
V
XX(VERB)
GET
XXX:XX:XX (HR:MIN:SEC) XX (OCTAL)
304 Ol
INDEX NO. OFCOMMAND WORDS IN LOAD CORRECTION IDENTIFIERS TIME FORCONFIRMATION OF GROUNDRACK T
02-24 N34 NAVCHECK
XX (OCTAL) XXX:XX:XX.XX (HR:MIN:SEC)
N43 LAT XX.XX(DEG) LATITUDE FOR GROUND TRACK CONFIRMATION LONGITUDE GROUND FOR TRACK CONFIRMATION ALTITUDE FOR GROUND TRACK CONFIRMATION
LONG
XXX.XX(DEG)
ALT
XXX.X(DEG)
2-7
P30 MANEUVER PURPOSE SET STARS + RALIG N "o co PALl GN o YALIGN__ + + + ULLAGE. 0 0 0 0 0 0 0 0 0 0 I Ip PROP/GUID WT N47
PTRIM N48 YTRIM o e0 HRS GETI " MIN SEC z_V X AVy Z_V7 N81 N33
X
X X
R P Y H A Hp Z_VT N42
X X X X X X + + X HORIZO N/M/INDOW X X + +
0"-
X X
BT _VC
X X X
SXTS 0 SFT I0
I
0 TRN BSS SPA SXP LAT LONG N61
-o o,. ._
p./
X X X X X X X X OTHER + + 0
__:
RTGO EMS VIO GET 0. 050
2-8
P30 MANEUVER PURPOSE PROP/GUID XXXXX XXX/XXX TYPE OF MNVR BE PERFORMED TO PROPULSION SYSTEM (SPS/RCS)/ GUIDANCE (SCS/G&N) PREMANEUVER VEHICLE WEIGHT SPSPITCHGIMBAL OFFSET O T PLACE THRUSTHROUGH T THECG SPSYAW GIMBAL OFFSETO T PLACE THRUST THROUGH THE CG TIME OFMNVR IGNITION
WT P TRIM
+XXXXX (!bs) +X.XX (DEG) +X.XX (DEG) XX:XX:XX.XX (HRS:MIN:SEC) +XXXX.X (FPS) TXXXX.X(FPS) TXXXX.X (FPS) XXX (DEG) XXX (DEG) XXX (BEG) XXXX.X(NM)
Y TRIM
GETI
aVX _V¥ _VZ R p y HA
P30 VELOCITYO BE GAINED T COMPONENTS IN LOCAL VERTICAL COORDINATES IMU GIMBAL ANGLES OF MANEUVER ATTITUDE
PREDICTED APOGEE ALTITUDE AFTER MANEUVER PREDICTED PERIGEE LTITUDE A AFTER MANEUVER TOTAL VELOCITY F MANEUVER O MANEUVER DUPJ_TION PREMANEUVER &V SETTING IN EMS &V COUNTER SEXTANT STAR FOR MANEUVER ATTITUDE CK SEXTANT SHAFT SETTING FOR MANEUVER ATTITUDE CK SEXTANT TRUNNION SETTING FOR MANEUVER ATTITUDE CK BORESIGHT STAR FOR MANEUVER ATTITUDE CK USING THE COAS
HP
+XXXX.X (NM)
&VT BT &VC
+XXXX.X (FPS) X:XX (MIN:SEC) XXXX.X (FPS)
SXTS
XX (OCTAL)
SFT
+XXX.X(DEG)
TRN
+XX.X (DEG)
BSS
XX (OCTAL)
2-9
SPA
+XX.X (DEG)
BSSPITCH ANGLE NCOAS O FOR MANEUVER ATTITUDE CK BSS POSITION X ONCOAS FOR MANEUVER ATTITUDE CK LATITUDE ANDLONGITUDE OFTHE LANDING POINT FOR ENTRY GUIDANCE RANGE TOGO FOR EMS INITIALIZATION INERTIALVELOCITY T .05G FOR A EMS INITIALIZATION TIME OF .05G
SXP
+X.X (DEG)
LAT LONG
+XX.XX(DEG) YXXX.XX (DEG)
RTGO
+XXXX.X (NM)
VIO
+XXXXX (FPS)
GET(.05G)
XXX:XX:XX.XX (HRS:MIN:SEC) XX (OCTAL) XX (OCTAL) XXX(BEG) XXX(DEG) XXX(DEG) X (jETS) XX.X (SEC) XX.X (DEG)
SETSTARS
STARS FORBACKUP DC G ALIGN
R, P, Y (ALIGN)
ATTITUDE TOBESETIN ATTITUDE ETTWFOR S BACKUP GDC ALIGN NO.OFSMRCS JETSUSED AND LENGTH TIME OF ULLAGE OF WINDOWMARKING AT WHICH HORIZON IS PLACED AT A SPECIFIED TIG (ATT CK) ADDITIONAL REMARKS VOICED UP BY MCC-H
ULLAGE
HORIZON/WINDOW
OTHER
2-10
THIS PAGE INTENTIONALLY
LEFT BLANK.
P76 UPDATE PAD PURPOSE + + + 0 0 0 0 j 0 0 j
i
+ 0 0 +1 0 0 0 + 0
HR MIN SEC AVX AVY AVZ
N33 TIG
_,
[
N84
i
o,.
PURPOSE + + 0 0' 0 [ 0 + 0 0 HR 0 MtI'4 SEC AVX AVY N84 N33 TIG 0 + 0 + 0 0
-o
i'_
o_
+ 0
, j
I
I
!
,
,
',
i + + 0 0 0 0 0
I
i
_
/
AVZ PURPOSE + 0 + 0 + 0 0 0 0 HR MIN SEC AVX AVY AVZ PURPOSE N84 N33 TIG
+ 0 o.
.o
o. ._ _: + + 0 0 0 0 0
!
i
I I + 0 + 0 + 0 0 0 0
HR MIN SEC AVX AVY AVZ
N33 TIG
+ 0
N 84
2-11
P76 UPDATE PAD PURPOSE N33 TIG XXXXX XX:XX:XX.XX (HR:MIN:SEC) PURPOSE OFMANEUVER TIMEOF IGNITION
N84 &VX _VY _VZ XXXX.X (FPS) XXXX.X (FPS) XXXX.X (FPS) COMPONENTS OF &V APPLIED LONG A LOCALVERTICAL AXIS AT TIG (LM)
2-12
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(x a
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+
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2-13
_-_ "_
_ _- __
v
CSM SEP PAD 33 GETI XXX:XX:XX. XX (HRS:MIN:SEC) +XXXX.X(FPS) +XXXX.X (FPS) +XXXX.X(FPS) XXX(DEG) XXX(BEG) XXX (BEG) GET OF CSM/LM SEPARATION BURN LOCAL VERTICAL VELOCITYCOMPONENTS OF SEPBURN SEPARATION BURN INERTIAL GINBAL ANGLES
81
DELTAVX DELTAVY DELTAVZ R P Y
22
DOI PAD 84 DELTA VX DELTAVY DELTA VZ GETI XXXX.X(FPS) XXXX.X (FPS) XXXX,X(FPS) XXX:XX:XX.XX (HRS:MIN:SEC) LM LOCAL VERTICAL VELOCITYCOMPONENTS FORDOI BURN GETOFDOI BURN
33
PDI + 12 ABORT PAD 84 DELTAVX DELTAVY DELTAVZ XXXX. (FPS) X XXXX.X (FPS) XXXX.X(FPS) LM LOCALVERTICAL VELOCITY COMPONENTS FORFIRST OPPORTUNITY PDI PLUS 12 MIN ABORT GET OF PDI + 12 MIN ABORTBURN
33
GETI
XXX:XX:XX.XX (HRS:MIN:SEC)
"CSM RESCUE" PAD PHAS 33 GETI XXX:XX:XX.XX (HRS:MIN:SEC) XXX:XX:XX. XX (HRS:MIN:SEC) GET OF CSM ABORTPHASINGBURN GETOF TPI FOR LMABORTSETWEEN B PDI AND PDI + lO MIN GETOF TPI FOR LMABORTS AFTER PDI + lO MIN
TPI (PDI
37 lO)
GETI
TPI (PDI
37 lO)
GETI
XXX:XX:XX.XX (HRS:MIN:SEC)
"CSM RESCUE UPDATE" PAD PHAS 33 GETI XXX:XX:XX.XX (HRS:MIN:SEC) GETOF CSM ABORTPHASINGBURN FOR 2ND OPPORTUNITY (l REV DELAY)
2-14
TPI (PDI
14.5) 37
GETI
XXX:XX:XX.XX (HRS:MIN:SEC)
GETOF TPI FOR LM ABORTS BETWEEN PDI AND PDI + 14.5 MIN FOR 2ND OPPORTUNITY GETOF PREFERRED LMLIFTOFF TIME
TPI (T2) 37 RESCUE TWO PAD 47 WT
GETI
XXX:XX:XX.XX (HRS:MIN:SEC)
XXXX.X (Ibs)
PREMANEUVER CSM WEIGHT SPSPITCH YAW & GIMBAL OFFSET TO PLACE THRUST THROUGH THE CG GETOFRESCUE BURN LOCAL VERTICAL VELOCITYCOMPONENTS OF RESCUE URN B RESCUE BURN GIMBAL ANGLES
48
P TRIM Y TRIM
X.XX(DEG) X.XX (DEG)
33
GETI
XXX:XX:XX. XX (HRS:MIN:SEC) XXXX, (FPS) X XXXX,X (FPS) XXXX.X (FPS) XXX (DEG) XXX(DEG) XXX (BEG) XX.X (FPS)
81
DELTA VX DELTAVY DELTA VZ R P Y _Vc
22
_Vc
VELOCITY TOBE SET IN EMS COUNTER FOR RESCUE BURN GET OF CSI BURNBASEDON RESCUE BURN GET OFTPI BURNBASEDON RESCUE BURN THE FUTURE APSIDAL CROSSING (APOLUNE OR PERILUNE) OF THE ACTIVE VEHICLE AT WHICH CDH SHOULD OCCUR
II
GETI
XXX:XX:XX. XX (HRS:MIN:SEC)
37
GETI
XXX:XX:XX.XX (HRS:MIN:SEC)
N
X
2-15
CSI ONE II GETI XXX:XX:XX.X (HRS:MIN:SEC) XXXX.X(FPS) XXXX.X (FPS) XXXX.X(FPS) X GET OF CSI OnE BURN LOCAL VERTICAL VELOCITYCOMPONENTS OF CSI ONE BURN THE FUTURE APSIDAL CROSSING (APOLUNE OR PERILUNE) OF THE ACTIVE VEHICLE AT WHICH CDH SHOULD OCCUR
81
DELTA VX DELTAVY DELTA VZ
N
CSI TWO, THREE, FOUR SAME AS ABOVE EXCEPT CSI TWO, THREE, FOUR CDH 13 GETI XXX:XX:XX.X (HRS:MIN:SEC XXXX. (FPS) X XXXX.X (FPS) XXXX.X(FPS) GET OFCDH BURN LOCAL VERTICAL VELOCITY COMPONENTS OF CDH BURN
81
DELTA VX DELTAVY DELTA VZ
TPI 37 XXX:XX:XX.X (HRS:MIN:SEC DELTA VX DELTA VY DELTA VZ _V (LOS) XXX(FPS XXX (FPS XXX(FPS XXX(FPS GET OFLMTPI BURN LOCAL VERTICAL VELOCITY COMPONENTS OF TPI BURN VELOCITYOMPONENTS C ALONG THE LINE OF SIGHT TO TARGET BURN DURATION ALONG THE LINE OF SIGHT
81
59
LOSBT
X:XX MIN:SEC
P22 PAD T1 XXX:XX:XX.XX (HRS:MIN:SEC) GET WHICH AT LANDMARK APPEARS ON HORIZON
2-16
T2
XXX:XX:XX.XX (HR:MIN:SEC)
GET AT WHICH LANDMARKLOS IS 35° ABOVE LOCAL HORIZONTAL DISTANCE OF LANDMARK NORTH OR SOUTH OF ORBITAL TRACK LATITUDE LANDMARK OF LONGITUDE LANDMARK OF ALTITUDE LANDMARK OF ABOVE OR BELOW MEAN LUNAR RADIUS
NM (NORS)
XX.X (NM)
89
LAT LONG ALT
+XX.X (DEG) 7XX (DEG)
NOMINAL LM IGNITION TIMES CSI II PC33 GETI GETI XXX:XX:XX.X (HRS:MIN:SEC) XXX:XX:XX.XX (HRS:MIN:SEC) XXX:XX:XX.XX (HRS:MIN:SEC) NOMINAL GET OF LM CSI BURN NOMINAL GET OF LM PLANECHANGE BURN NOMINAL GETOFLM TPI BURN
TPI 37
GETI
2-17
THIS
PAGE INTENTIONALLY
LEFT BLANK.
LUNAR ENTRY AREA X X X X X X X X X X X X X X X X X X R 0.05G P 0.05G Y 0.05G GET X X X 0 ' X X X 0 P LAT LONG X + 0 0 + + X X X + + + 0 0 X X MAX G V400K RTGO VIO RRT X X + ZC mrZ 0 0 X X + 0 0 0 RET 0.05G DL MAXN69 DLMIN VLMAX _:"Z _zDZ N60 EMS HOR CK N61
¥400K
-- 0 0 + + --
+ 0 +
+
._X_ X X X X X X
o,, ,4D
+
X X X X X X X X X X X X X X X 0 0 0 + + X X X X X X X X X X X X
vL MIN
D O RET VCIRC RETBBO RETEBO RETDRO SXTS 0 SFT 0 0 TRN BSS SPA SXP LIFTVECTOR
X X X X X X X X
o.
-<:
_ + X X X X X X X X X X X X
2-18
LUNAR ENTRY PAD AREA XXXXX SPLASHDOWN DEFINEDY AREA B TARGET LINE SPACECRAFT GIMBAL IMU ANGLES REQUIRED AERODYNAMIC FOR TRIM AT .05G TIMEOF ENTRY ATTITUDE HORIZCHECK E! -17 MIN. AT PITCH ATTITUDEOR F HORIZON CHECK ATEl -17 MIN. LATITUDE OFTARGETOINT P LONGITUDE OFTARGET OINT P PREDICTED MAXIMUM REENTRY ACCELER_,TION INERTIALVELOCITY ENTRY AT INTERFACE INERTIALFLIGHT PATH ANGLE AT ENTRY INTERFACE RANGEO GOFROM T .05G TOTARGET FOR EMS INITIALIZATION INERTIAL VELOCITYT ,05G A FOR EMS INITIALIZATION REENTRY REFERENCE BASED TIME ON GET OF PREDICTED400K (BET START) TIMEOF .05G FROM 400K(RRT)
R .05G P .05G Y .05G GET (HOR CK) P (HOR CK) LAT LONG MAX G
XXX(DEG) XXX(DEG) XXX (DEG) XXX:XX:XX (HRS:MIN:SEC) XXX (DEG)
+XX.XX(DEG) +XXX.XX (DEG) XX.X (G's)
V4OOK
+XXXXX (FPS)
400K
-X.XX (DEG)
RTGO
+XXXX.X (NM)
VIO RRT
+XXXXX (fps) XXX:XX:XX (HRS:MIN:SEC)
RET.05G
XX:XX (MIN:SEC) +X.XX (G's)
DL MAX
MAXIMUM ACCEPTABLE VALUE OF PREDICTED DRAG LEVEL (FROM CMC) MINIMUM ACCEPTABLE VALUE OF PREDICTED DP, AG LEVEL (FROM CMC) MAXIMUM ACCEPTABLE VALUE OF EXIT VELOCITY (FROM CMC)
DL MIN
+X.XX (G's)
VL MAX
+XXXXX (FPS)
2-19
VL MIN DO RET VCIRC RETBBO RETEBO RETDRO SXTS SFT TRN BSS SPA SXP LIFT VECTOR
+XXXXX(FPS) X.XX(G's) XX:XX (MIN:SEC) XX:XX (MIN:SEC) XX:XX (MIN:SEC) XX:XX (MIN:SEC) XX (OCTAL) +XXX. (DEG) X +XX.X(DEG) XXX (OCTAL) +XX.X(DEG) +X.X (DEG) XX (UP/DN)
MINIMUM ACCEPTABLE VALUE OF EXIT VELOCITY (FROM CMC) PLANNED LEVEL DRAG DURING CONSTANT G TIME FROM THAT S/C VELOCITY El BECOMES CIRCULAR TIMEFROM TOTHEBEGINNING El OF BLACKOUT TIME FROM TOTHE El END OF BLACKOUT TIMEFROM TO DROGUE El DEPLOY SEXTANT STAR FOR ENTRYTTITUDE A CHECK SEXTANT SHAFT SETTING FOR ENTRY ATTITUDE CHECK SEXTANT TRUNNION SETTING FOR ENTRY ATTITUDE CHECK BORESIGHT FOR STAR ENTRY ATTITUDE CHECK USING THE COAS BSS PITCH ANGLE NCOASOR O F ENTRY ATTITUDE CHECK BSS POSITION X ONCOASOR F ENTRY ATTITUDE CHECK LIFT VECTOR DESIREDAT .05G's BASED ON ENTRY CORRIDOR
2-20
THIS
PAGE INTENTIONALLY
LEFT BLANK.
EARTH ORBIT ENTRY UPDATE X X X X X X X X X X + I X X I I I [ I X X X X X + + X X 0 ! i I I I j ' /
/
Z
AREA _V TO R 0.05G P 0.05G Y 0.05G RTGO I VlO RET0.05G LAT LONG N61 EMS EMS
X X
X X
X X X
+1 X ,IX 0 X X
o',,
X X
•
RET 0.2G DRE f55 ) ° N66
o-,'° -•,o" R R j X X _: < X X X X X X X X X X X
R R, X X X X X X X X X X X X
/
BANK AN RET B R RETBBQ RETEBO RETDRQG (90°/fps) DRE (90°) CHART UPDATE
X POST BURN X
X X + + X X X
r'n
X
X X + + X X X X
P 0.05G RTGO VIO RET 0.05G RET 0.2G
. _.
EMS
X _]
Z _ _O R
DRE ::kl00 nmN66 /' R R // BANK AN RETRB RETBBO RETEBO SEC RETDROGTO MAIN
O __ Z
R[
X Xi X X X X X X
X X X X X X X X
2-21
EARTH ORBIT ENTRY UPDATE AREA XX×-X RECOVERY - FIRST AREA 3 DIGITS DENOTES REV IN WHICH LANDING OCCURS. LAST DIGIT DENOTES RECOVERY AREA AND SUPPORT CAPABILITIES AVDUE TOENGINE TAILOFF
AVTO EMS R O,05G P O.05G Y O.05G
XX.X (FPS)
XXX(DEG) XXX(DEG) XXX(DEG)
SPACECRAFT IMU GIMBAL ANGLES REQUIRED FOR AERODYNAMIC TRIM AT 0.05G.
EMS RTGO XXXX.X (NM) RANGE TOGO FROM .05G TO TARGET INERTIAL VELOCITY AT .05G FOR EMS INITIALIZATION TIME FROM RETROFIRE TO .05G
VIO
XXXXX (FPS)
RETO.05G N61 LAT
XX:XX (MIN:SEC)
+XX.XX(DEG)
LATITUDE IMPACT OF LANDING POINT LONGITUDE IMPACT OF LANDING POINT
LONG
+XXX.XX(DEG)
N66 RET .2G DRE(55° ) XX:XX(MIN:SEC) TIME FROM RETROFIRE TO .2G DOWNRANGE ERROR AT .2G BACKUP BANK ANGLE FOR SCS ENTRY: ROLL RIGHT/ROLL LEFT
+XXXX.X (NM)
BANK AN
XX/XX (DEG/DEG)
2-22
RETRB
XX:XX (MIN:SEC)
TIME FROM RETROFIRE TO REVERSE BACKUP BANK ANGLE TIME FROM RETROFIRE TO BEGINNING OF COMMUNICATIONS BLACKOUT TIME FROM RETROFIREO END T OF COMMUNICATIONS BLACKOUT TIME FROM RETROFIREO T DROGUE CHUTE DEPLOYMENT
RETBBO
XX:XX (MIN:SEC)
RETEBO
XX:XX (MIN:SEC)
RETDROG CHART UPDATE 90°/FPS DRE ° ) (90
XX:XX (MIN:SEC)
÷XX _XXX
VALUES USED TO RE-PLOT BACKUP ENTRY HART C _V AND DOWNRANGE ERROR (DRE) @ 90° BANK ANGLE
POST BURN P O.05G EMS RTGO +XXXX,X (NM) RANGE GOFROM TO O.05G TO TARGET FOR EMS COUNTER INERTIAL VELOCITY @O.05G TIME FROM RETROFIRE O.5G TO TIME FROM RETROFIREO O.2G T DOWNANGE R ERROR BACKUP BANK ANGLE FOR SCS ENTRY: ROLL RIGHT/ROLL LEFT TIME FROM RETROFIRE TO REVERSE BACKUP BANK ANGLE XXX(DEG) PITCH ANGLE @ENTRY INTERFACE
VIO RETO.05G RET 02G DRE BANK AN
+XXXXX (FPS) XX:XX (MIN:SEC) XX:XX (MIN:SEC) +XXXX.X (NM) XX/XX (DEG/DEG)
RETRB
XX:XX (MIN:SEC)
2-23
RETBBO
XX:XX(MIN:SEC
TIME FROM RETROFIRE TO BEGINNING OF COMMUNICATIONS BLACKOUT TIME FROM RETROFIRE TOEND OF COMMUNICATIONS BLACKOUT TIME FROM RETROFIRE TO DROGUE CHUTE DEPLOYMENT
RETEBO RETDROG
XX:XX(MIN:SEC XX:XX(MIN:SEC
2-24
EARTH ORBIT BLOCK DATA X X X X X X X * X X X I [ _ !
I
B
X X
'
AREA
I
X X X _,
|
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L o _ . , ! I ! I i
LAT LONG GETI
X X X
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xix I
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X X X REM AR KS:
X X X
2-25
EARTH ORBIT BLOCK DATA AREA XXX-X RECOVERY AREA FIRST 3 DIGITS LANDING REVOLUTION LAST DIGIT RECOVERY AREA AND SUPPORTCAPABILITIES COORDINATES OFTHE DESIREDANDING L AREA DEORBIT IGNITIONTIME FORTHE DESIRED LANDING AREA DEORBIT MANEUVER &V TO BE LOADED INTO THE EMS COUNTER.
LAT LONG GETI
+XX.XX (DEG) TXXX.X(DEG) XXX:XX:XX.XX (HR:MIN:SEC)
&VC
XXX. (FPS) X
2-26
LM
P27 UPDATE
PO,_ GET
• ' 1174 01 O2
"_4
• INDEX
',1 I •
• INDEX
,' • I
• INDEX
"1 I •
a-
03 O4 O5 O6 O7 10 11 12 13 14 15 16 17
o. •,O
O--
20 21 22 23 24 N34 HR MIN X X X X X X X X X X X X X 0 + 0 II II X X X
"_ "_
a_
•,<
NAVCHECK SEC X X N43 LAT LONG 0
ALT + 0
li
2-27
P27 UPDATE-LM PURP XXX TYPE OFDATA TOBE RECEIVED (SUCH AS: LDG TIME) TYPE OFCOMMAND LOAD (70-7]-72-73) TIME DATA RECORDED INDEX NO.OFCOMMAND WORDSIN LOAD CORRECTION WORD IDENTIFIERS TIME FORCONFIRMATION OF GROUND TRACK
V GET I174 Ol 02-24 N34 NAVCHECK TIME N43 LAT LONG ALT
XX(VERB) XXX:XX:XX (HR:MIN:SEC) XX(OCTAL) XX(OCTAL) XXX:XX:XX.XX (HR:MIN:SEC)
XX.XX (DEG) XXX.XX (DEG) XXX.X (NM)
LATITUDE GROUND FOR TRACK CONFIRMATION LONGITUDE GROUND FOR TRACK CONFIRMATION ALTITUDE GROUND FOR TRACK CONFIRMATION
2-28
AGS STATE VECTOR UPDATE
PURP 240 241 242 260 261 262 + + 254 244 245 246 264 265 266 o. ',,0
o-
+ REMARKS:
+
272
-J
2-29
AGS STATE VECTOR UPDATE PURP PURPOSE AGS FOR STATE VECTOR UPDATE +XXXXX I00 FT) +XXXXX lO0 FT) +XXXXX lO0 FT) LM STATE VECTOR-POSITION COMPONENTS
240
241 242
260
+XXXX.X FPS) +XXXX.X FPS) +XXXX.X FPS)
LMSTATE VECTOR-VELOCITY COMPONENTS
261 262
254
+XXXX.X (MIN)
LMTIMEFOR WHICH THE STATE VECTOR IS ACCURATE
244
+XX×XX (I00 FT)
CSM STATE VECTOR-POSITION COMPONENTS
245 246
+XXXXX (I00 FT) +XXXXX (I00 FT)
264
+XXXX.×(FPS) +XXXX,X (FPS) +XXXX.X (FPS)
CSM STATE VECTOR-VELOCITY COMPONENTS
265 266
272
+XXXX.X (MIN)
CSM TIMEFOR WHICH THE STATE VECTOR IS ACCURATE
2-30
O7
_.J
0 .,_1 (D + + + +j + X X X X X X
0
_
X
X
X
X
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2-31
PHASING N33 PHASING TIG XXX:XX:XX.XX (HR:MIN:SEC) IGNITION TIME OF LM MANEUVER
N81 LOCAL VERTICAL AV AVX AVY AVZ N42 ORBITAL HA PARAMETERS +XXXX.X(NM) PREDICTED APOGEE ESULTING R FROM MANEUVER PREDICTED PERIGEE RESULTING FROM MANEUVER TOTAL REQUIRED AV FOR THE MANEUVER DURATION FTHEMANEUVER O +XXXX.X(FPS) +XXXX.X (FPS) +XXXX.X (FPS) LOCAL VERTICAL AVCOMPONENTS OFTHE MANEUVER
HP
+XXXX.X(NM)
AVR
+XXXX.X (FPS)
BT FDAI R
X:XX (MIN:SEC
XXX(DEG)
INERTIAL FDAIANGLES AT THE BURN ATTITUDE
P AGS AV AVXAGS AVYAGS AVZAGS
XXX (BEG)
+XXXX.X (FPS +"-XXXX.X (FPS _XXXX.X(FPS XX (OCTAL)
LOCAL VERTICAL AV COMPONENTSTHE OF MANEUVER TARGET TO THE AGS BSS STAR FOR MANEUVER ATTITUDE CHECK BSS PITCH ANGLE ON COAS, BSSX POSITION & ON COAS FOR MANEUVER ATTITUDE CHECK
BSS
SPA SXP
+XX.X (DEG) TXX.X (DEG)
2-32
13 LO
P30 LM MANEUVER !PURPOSE + 0 0 + 0 0 + 0 0 0 + 0 HR MIN SEC AVX AVY + + X X X X X X X X X + + X X X X X X X X X AVZ Ha HD AVR BT R P AVX AVY AVZ X X X X X X X: X PEMARKS: X X X X X X X X: BSS SPA SXP AGS AGS AGS FDAI INER N86 N81 LOCAL VERT N42 TIG N33 + 0 0 0 + 0
0 eq
o
a_
2-33
P30 LM MANEUVER PURPOSE XXXXX PURPOSE MANEUVER OF (SUCH AS DOI TARGETING) IGNITION TIME FORTHE MANEUVER
N33 TIG OF MANEUVER
XXX:XX:XX.XX (HR:MIN:SEC)
N81 LOCAL VERTICAL AV AVX AVY AVZ N42 ORBITAL HA HP AVR PARAMETERS +XXXX.X (NM) +XXXX.X (NM) +XXXX.X (FPS) PREDICTED APOGEE AND PERIGEE RESULTING FROM THEMANEUVER TOTAL AV REQUIRED THE FOR MANEUVER DURATION OFTHEMANEUVER +XXXX.X (FPS) +XXXX.X (FPS) +XXXX.X (FPS) LOCAL VERTICAL V A COMPONENTS OFTHE MANEUVER
BT FDAI R P N86 AGS AV AVXAGS AVYAGS AVZAGS BSS
X:XX(MIN:SEC)
XXX(DEG) XXX (DEG)
INERTIAL FDAIANGLES AT THE BURNTTITUDE A
+XXXX.X(FPS) -+XXXX.X (FPS) +XXXX.X (FPS) XX (OCTAL)
LOCAL VERTICAL V A COMPONENTS THE OF MANEUVER TO USED TARGET AGS THE
BSS STAR FOR BURN ATTITUDE CHECK BSS PITCH ANGLE N O COAS, & BSS X POSITION ONCOAS FOR MANEUVER ATTITUDE CHECK
SPA SXP
+XX.X(DEG) +XX.X(DEG)
2-34
-QO
Q-
0
0
X
+i + ,i+
'
+
li+ × "
2-35
DOI DATA CARD N33 DOI TIG XXX:XX:XX.XX (HR:MIN:SEC) IGNITIONTIME OF LM MANEUVER LOCAL VERTICALAV COMPONENTS OF THE MANEUVER +XXXX.X (FPS) +XXXX.X (FPS) +XXXX.X (FPS) PARAMETERS +XXXX°X (NM) PREDICTED APOGEE ESULTING R FROM MANEUVER PREDICTED PERIGEE RESULTING FROM MANEUVER TOTAL REQUIRED AV FOR THE MANEUVER DURATION FTHEMANEUVER O
N81 LOCAL VERTICALAV
AVX AVY AVZ N42 ORBITAL HA
HP
+XXXX.X (NM)
AVR
+XXXX.X (FPS)
BT FDAI R P N86 AGS AV AVXAGS AVY AGS AVZ AGS
X:XX (MIN:SEC)
XXX (DEG) XXX (BEG)
INERTIAL FDAIANGLES AT THE BURN ATTITUDE
+XXXXoX (FPS) +-XXXX.X (FPS) +--XXXX.X (FPS)
LOCAL VERTICAL AV COMPONENTS THE OF MANEUVERTO TARGET THE AGS BSS STAR FOR MANEUVER ATTITUDE CHECK BSS PITCH ANGLE ON COAS, BSSX POSITION & ONCOAS FOR MANEUVER ATTITUDE CHECK
BSS
XXX (OCTAL)
SPA SXP
+XX.X(DEG) TXX.X (DEG) --
2-36
L !_
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2-37
PDI DATA CARD PDI PAD TIG PDI XXX:XX:XX°XX (HR:MIN:SEC) XX:XX(MIN:SEC) +XXXX.X(NM) PDI IGNITIONTIME
TGO CROSS RANGE
TIMETO HIGHGATE OUT-OF-PLANE ISTANCE D BETWEEN THE INITIAL LM ORBITAL PLANE AND THE LANDING SITE (POSITIVE INDICATES LANDING SITE IS NORTH OF ORBITAL PLANE)
FDAI AT TIG R P Y DEDA 231 (IF REQ'D) XXX(DEG) XXX (DEG) XXX (BEG) XXXXX (I00 FT) INERTIAL DAIANGLES F ATIGNITION
LUNAR RADIUS THE AT LANDING SITE
PDI ABORT
lO MIN PHASING TIG XXX:XX:XX,XX (HR:MIN:SEC) XXX:XX:XX,XX (HR:MIN:SEC) TIME OF IGNITIONOF LM PHASINGMANEUVER TPI IGNITIONTIME
TPI TIG
2-38
NO PDI +12 ABORT N33 ABORT TIG XXX:XX:XX.XX (HR:MIN:SEC) AV +XXXX.X (FPS) +XXXX.X (FPS) +XXXX.X (FPS) PARAMETERS +XXXX.X (NM) PREDICTED APOGEE RESULTING FROM HANEUVER PREDICTED PERIGEE RESULTING FROM MANEUVER TOTAL REQUIRED AV FOR THE MANEUVER DURATION MANEUVER OF LOCAL VERTICAL V A COMPONENTS OF THE PHASING ANEUVER M IGNITION TIME FOR ABORT BURN
N81 LOCAL VERTICAL AVX AVY AVZ N42 ORBITAL HA
HP
+XXXX.X (NM)
AVR
XXXX.X (FPS)
BT FDAI R P N86 AGS AV AVXAGS AVYAGS AVZAGS Nil CSl TIG
X:XX (MIN:SEC)
XXX(DEG) XXX (DEG)
INERTIAL DAIANGLES F AT THE BURN ATTITUDE
+XXXX.X(FPS) +XXXX.X(FPS) +XXXX.X (FPS) XXX:XX:XX.XX (HR:MIN:SEC) XXX:XX:XX.XX (HR:MIN:SEC)
LOCAL VERTICAL AV COMPONENTS OF THE MANEUVER TARGET TO THE AGS
TIME OF IGNITION FORCSI BURN TIME OF IGNITION FORTPI BURN
N37 TPI TIG
2-39
THIS
PAGE INTENTIONALLY
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2-40
LUNAR SURFACE DATA CARD T2 ABORT T2 TIG XXX:XX:XX.XX (HR:MIN:SEC) LIFTOFF TIMESECOND PREFERRED TIME AFTER TOUCHDOWN(_T.D. +12 MIN.) TIME OF IGNITION FORPHASINGBURN TIME OF IGNITION FORCSI BURN TIME OF IGNITION FORTPI BURN
N33 PHASING TIG
XXX:XX:XX.XX (HR:MIN:SEC) XXX:XX:XX.XX (HR:MIN:SEC) XXX:XX:XX,XX (HR:MIN:SEC)
Nil
CSI TIG
N37 TPI TIG
T3 ABORT T3 TIG XXX:XX:XX,XX (HR:MIN:SEC) XXX:XX:XX.XX (HR:MIN:SEC) XXX:XX:XX.XX (HR:MIN:SEC) LIFT OFFTIME AFTER FIRST CSM REVOLUTION CSMORBITALPERIOD
CSMPERIOD
P + AT
CSM PERIOD PLUS THE TIME INTERVAL BETWEEN CLOSEST APPROACH AND LIFTOFF TIMES TIME OF IGNITION FOR CSI BURN TIME OF IGNITION FOR TPI BURN
Nil
CSI TIG
XXX:XX:XX.XX (HR:MIN:SEC) XXX:XX:XX°XX (HR:MIN:SEC)
N37 TPI TIG
2-41
LM ASCENT PAD + 0 0 + 0 0 0 + 0 + + 0
L
+ 0 0 i + 0 0 0 + 0 + + 0
HRS MIN SEC V (NOR) V (VERT) N76 *CROSSRANGE DEDA 047 DEDA 053 DEDA225/226 j DEDA 231 TIG
I I _
2-42
LM ASCENT PAD ASCENT TIG N76 INSERTION TARGET V(HOR) V(VERT) CROSSRANGE DEDA 047 DEDA 053 DEDA225 DEDA 226 DEDA 231 XXXX.X (FPS XXXX.X (FPS +XXX.X(NM) XXXXXX (OCTAL) XXXXXX (OCTAL) XXXXXX(I00 FT) HORIZONTAL VELOCITY AT ORBIT INSERTION VERTICALELOCITYT V A ORBIT INSERTION CROSSRANGE DISTANCE AT ORBITAL INSERTION SINEOFLANDING AZIMUTH ANGLE COSINE FLANDING O AZIMUTH ANGLE LOWER LIMIT OF _ AT ORBIT INSERTION UPPERIMIT OFG_ L AT ORBIT INSERTION RADIAL DISTANCE OF LAUNCH SITE FROM CENTER OF MOON XXX:XX:XX.XX (HR:MIN:SEC TIME OF APS IGNITION FOR LM ASCENT
XXXXXX (lO0 FT) XXXXXX (lO0 FT)
2-43
2-44
CSI DATA CARD (P32 LM MANEUVER) N!l CSI TIG XXX:XX:XX.XX (HR:MIN:SEC) CSl IGNITIONTIME
N37 TPI TIG
XXX:XX:XX.XX (HR:MIN:SEC)
TPI IGNITION TIME
N81 AVX AVY FDAI PITCH XXX.X(FPS XXX.X(FPS XXX(DEG) LOCAL VERTICALV A COMPONENTS OF THE CSl MANEUVER FDAI INERTIAL PITCH ANGLE AT THE CSl BURN ATTITUDE AGSIGNITION TIME OF NEXT MANEUVER DESIRED TPI TIG (FOR CSl CALCULATION ONLY)
DEDA 373
XXXX.X(MIN)
DEDA 275 N86 AGS AV AVXAGS AVYAGS AVZAGS
XXXX.X (MIN)
XX°XX(FPS) XX.XX(FPS) XX.XX(FPS)
LOCAL VERTICAL AV COMPONENTSOF CSl USED TOTARGETGS A EXTAV
2-45
2-46
CDH DATA CARD NI3 CDH TIG XXX:XX:XX.XX (HR:MIN:SEC) IGNITIONTIME FOR CDHMANEUVER
N81 LOCAL VERTICAL AV AVX AVY AVZ PLM FDAI +XXX.X (FPS) TXXX.X (FPS) TXXX.X (FPS) XXX(DEG) LOCAL VERTICAL AV COMPONENTS OFCDH MANEUVER FDAIINERTIAL PITCH ANGLE AT CDH BURN ATTITUDE AGSIGNITION TIME OF NEXT MANEUVER
DEDA 373
XXXX.X(MIN)
N86 AGS AV AVXAGS _VYAGS &VZAGS +XXX.X(FPS) _XXX.X(FPS) TXXX.X(FPS) LOCAL VERTICAL V A COMPONENTS OF CDH USED TOTARGETGS A EXT AV
2-47
2-48
TPI DATA CARD N37 TPI TIG XXX:XX:XX,XX (HR:MIFI:SEC) IGNITIONTIME FOR THE TPI HANEUVER
NSi LOCAL VERTICAL _V _VX Z4Y _'/Z N42_VR RLM PLM +XX.X(FPS ¥>',X.X (FPS TXX.X (FPS +XX.X (FPS XXX (DEG) XXX (DEG) LOCAL VERTICAL £V COMPONENTS F THE O TPI MANEUVER TOTAL REQUIRED &V FOR THE MANEUVER ROLL AND PITCH FDAIANGLES ATTPI BURN ATTITUDE
N54 TIG-5 R TPI TPI N59 A V LOS F/A R/L D/U BT +XX.X (FPS) YXX.X (FPS) TXX.X (FPS) XX:XX (MIN:SEC LINE-OF-SIGHT &V COMPONENTS THE OF TPI MANEUVER DURATION F THEMANEUVER O XX.XX(FT) +XXX.X(FPS) RANGE TPI TIG - B MIN AT RANGE ATE TP! TIG - 5 MIN R AT
2-49
SECTION Ill
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SECTION IV - DETAILED TEST OBJECTIVES
SECTION 4 DETAILED OBJECTIVE ACTIVITIES
This section contains the activity summaries which reflect the test objectives for Mission G as described in "Mission Requirements G Type Mission", SPD9-R-038, Change A dated May l, 1969. These activity summaries are presented the approximate sequence in which they are planned to occur during the mission. Each activity A. summary provides the following information: Functional to the Test
in
TEST OBJECTIVES. This is the listing of the Objectives (complete or partial) which relate particular activity;
B.
TEST REQUIREMENTS. Here the special test prerequisites (and mission phase if necessary) are presented in addition to brief statements of the requirements for performing the activity; TEST PROCEDURES/CHECKLISTS. These are the procedural references for the performance of the activity as far the test objectives are concerned; and
C.
as
D.
DATA REQUIREMENTS. This part of the summary identifies the gross data which are needed for evaluation of test results in terms of flight crew and ground support requirements. for relating Detailed and relating activities part of this section. rules and Functional to Functional Test Objectives with Test Objectives, are
Cross references the activity summaries provided as the initial The following A.
ground
are to be used in implementing should
data not
requirements:
The collection the timeline
of highly desirable (HD) data of the crew _rocedures.
constrain
B.
Post-flight debriefing requirements which are fulfilled transmission of data per the DATA REQUIREMENTS sections from the post-flight debriefing.
by real time may be deleted
All of the Test Requirements have not been totally implemented into the mission timeline. These items are identified in this section as "Not Implemented" or with the conditions by which they will be implemented.
4-I
TABLE 4-I MISSION ACTIVITY AND TEST OBJECTIVE CROSS REFERENCE
ACTIVITY LMDescent Lunar Surface Navigation EVA Preparation Surface External and Egress
FTO D-l, G-l, G-3, H-l, M-I G-l, B-l, A-l, J-4, and Photography and Photography D-l, E-l, M-3 S-031, B-l, I-l, G-2, G-3, L-4, M-2 B-2, E-l, M-3 D-2, E-2, C-l, F-l, D-3, E-3, C-2, F-2, D-4, H-2, C-3, I-3, L-2, J-5, L-l J-2, M-3 L-3, L-4, J-3,
Sample Collection LM Observations Observations
Lunar Surface
Experiment
Deployment/Conduct
S-078, C-l, I-2 C-2
S-080
Post EVA Operations Contamination Prevention
4-2
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4-5
LM DESCENT A. Test D-l G-l G-3 H-l M-l B. Test I. Objective LM Landing Gear Performance Under Landing Conditions Location of the Landed LM from LM Data Capability of Locating the Landed LM in Real Time from LM/CSM/MSFN Data Data on Landing Aids and Final Approach Visibility Photograph Lunar Surface During LM Descent Requirements Determine of landing landing site visibility, site landmarks. [H] extent of washout and visibility
2. 3.
Photograph the landing site during the approach through window with the data acquisition camera. [G, H, M] Evaluate graphs. landing [G, H] aids, i.e., Landing Point Designator,
the maps,
LM pilot's photo-
4.
Assess visual phenomena from expected. [H] Voice
during
LM landing
which
are
significantly
different
5.
[m]
anotate
location
and identity
of
features
during
final
descent.
6. 7. C.
Determine landing location features during descent. Assess LM landing conditions
in [G]
real on the
time lunar
by description surface. [D]
of
terrain
Procedures/Checklist I. 2. Photographic Descent and Television Document. Operations Plan.
Procedures
D.
Data Requirements I. Flight a. Crew Reports/Logs/Photographs
LM crew comments on landing site visibility during final approach and landing phases and on effectiveness of the Landing Point Designator and landing site recognition aids. [H] (M) GET at start of final approach. data [H] acquisition (M) camera photographs during LM
b.
c. d.
Voice track regarding observations descent phase. [G] (M) Photographs of features taken
of surface
features
during
the
the landing site and surrounding lunar surface through a LM window during descent. [G, M] (M) 4-6
e.
Data Acquisition Camera photographs of the high gate to touchdown. [H, M] (M) Photographs of features taken
landing
site
from
f.
the landing site and surrounding lunar surface through a LM window during descent. [G, M] (N) observed during the final approach, and vehicle stability after touchdown.
g.
Comments on any lunar dust the severity of the landing [D] (M) Support [D, G, H] (I,1)
2.
Ground a. b. c, d.
LM TM HBR. LM TM LBR.
[D, G] (M) touchdown. [G, H] (M) of signal through
LM BET from DOi through
MSFN tracking data of LM from touchdown. [G] (F4)
acquisition
4-7
LUNAR SURFACE NAVIGATION A. Test G-I G-2 G-3 L-4 M-2 B. Test I. 2. Objectives Determine the Location of the Landed LM from LM Data Determine the Location of the Landed LM from CSM Data Determine Capability of Locating the Landed LM in Real Time from LM/CSM/MSFNData Panoramic Coverage of Distant Terrain Features Photograph Lunar Surface Post Touchdown/Pre EVA Requirements Correlate photomaps Photograph [G, M] Obtain Provide lunar surface features surrounding and mark the LM location. [G, L, terrain features thru the M] landing site with LM location.
the LM window to correlate
3. 4. 5.
two sets
of
LM IMU alignments of prominent
after
landing features.
[G] [G, L]
TV coverage
terrain
Track the landed LM from the CSM during two orbital passes. Mark on a landmark near the landed LM. [G] - (Only one pass is implemented.) Track the CSM with LM RR during of the [G] the one pass. landed [G] - (Not Implemented.) sur-
6. 7.
Obtain 70 MM photographs rounding lunar features. Assist MCCH in determining
LM or its
shadow and the
8. C.
landing
LM location
in
real
time.
[G,
L]
Procedures/Checklist I. 2. 3. 4. Photographic and Television Surface Operations Align Plan. (P57)". (P22)"
LM AOH, "PGNCS Lunar LM AOH, "Lunar CSM AOH, "Orbital Requirements Flight a. Surface
Program Program
Navigation
Navigation
(P22)".
D.
Data I.
Crew Reports/Logs/Photographs of the landed LM location on lunar photomaps. [G] (M)
Estimate
4-8
b.
Comments by LM crew regarding any difficulties estimating the location of the LM with respect features. [G] (HD) Comments by LM crewman on location of landed to prominent terrain features. [G] (M) Obtain high resolution CSM. [G] (M) Photographs of features taken photographs of the
encountered in to lunar surface
c.
LM with
respect
d.
landing
area
from
the
e. f.
the landing site and surrounding lunar surface through a LM window after landing. [G, M] (M) of the lunar surface as viewed from the LM.
Provide TV coverage [G, L] (M)
2.
Ground Support a. b. c. d. e. LM TLM HBR. [G] (M) LM TLM LBR. [G] (M) BET of CSM during BET of LM from the lunar surface touchdown. area obtained phase. [G] (M)
DOI through
[G] (M) during previous lunar
Photographs of the landing missions. [G] (M) Post-scan Estimate Reflectivity illumination. conversion solar video
f. g. h.
tape
of all
TV coverage. by mission contributing
[L]
(M) [L] (M)
illumination and geometry [L] (HD)
established of surfaces
geometry. to indirect
4-9
EVA PREPARATION AND EGRESS A. Test B-l B-2 C-l C-2 C-3 L-I B. Test I. 2. Objectives Demonstrate Egress-to/Ingress-from the Lunar Surface Evaluate Crew Lunar Surface EVA Capability EMU Capability to Provide a Habitable Environment EMU Effects on Crew Mobility/Dexterity/Comfort Data/Voice Communications Capability During EVA TV Coverage of an Astronaut Descending to the Lunar Surface Requirements Perform EVA preparations. [C] pre-mounted TV camera and turn the lunar surface. [L] [B, C] TV coverage of the lunar surface camera
Release the MESA pallet with power on prior to descent to Egress to the lunar surface.
3. 4.
Deploy and set EVA. [L] During relay. Two-way
the TV camera to provide
5.
EVA, communicate [C] voice
with
MSFN via
the EVA-LM-MSFN two way voice
6. 7,
[c]
communications
to
be performed
between
two EVA crewmen.
EMU and biomedical data transmitted to MSFN via
from two EVA crewmen will EVA-LM-MSFN one-way relay,
be simultaneously [C]
C.
Procedures/Checklist I. 2. EVA Procedures Lunar Surface Document. Operations Plan.
D.
Data I.
Requirements Flight a. Crew Reports/Logs/Photographs MSFN of the initial and final positions of the PLSS water valve, primary oxygen shutoff valve and water shutoff/ valve each time they are changed. [C] (M) flow, unit (M) low feed status
Notify diverter relief
b.
Notify MSFN when PLSS; High 02 flowrate, low vent water pressure or PGA pressure low remote control indicators and audible warning tone come on, [C]
4-10
c
Record
EMU radiation
dosimeter
readings
just
prior
to
the EVA.
[c](M)
d Notify MSFN if noxious odors occur or any condensation on the visor assembly. [C] (HD) Comment on the adequacy of procedures and difficulties during donning of EMU equipment. [C] (HD) encountered
e
f
Comment on time required and adequacy of the EMU checkout procedures. [C] (MD) Comment on the adequacy of EMU thermal from a sunlit area to shadow and vice Comment on estimated energy expenditure to simulation experience. [C] (HD) environment versa. [C] and comfort when walking (_) as compared
g
h
i j.
Provide data on the adequacy of hardware and procedures, and the time required to perform the egress from the LM. [B] (M) Comment on voice [C] (M) Provide quality for EVA-EVA and EVA-LM-MSFN communications.
k.
(M)
l)
sequence
camera
coverage
and TV camera
coverage
of:
[B,
M]
A crew member descending A crew member walking A crew member performing Support EB, C] (M) TV signals. (HD) video
to
the
lunar
surface.
2) 3) 2. Ground a. b. c. d. e. f. g.
on the lunar
lunar
surface. EVA operations.
surface
LM TM FM.
Ground recorded LM TM LBR. Post-scan Record [k]
[B]
(HD)
conversion
tape
of all during
TV coverage. video
ILl
(M) ILl (HD)
of S-band
signal
strength
transmission. [L]
GET at beginning Time period, simultaneously if
and end of TV transmission. any, when LBR TM (in lieu with TV data. [L] (M)
of HBR TM) transmitted
4-1i
h.
Identity of ground from LM. [L] (M) Time period, if any, TV data. [L] (M) Estimate LM position MSFN recording of incident on lunar
station(s)
used to
record
video
transmission
i.
when erectable
antenna
used to
transmit
j k. I.
illumination. surface. [H]
[L] (HD)
(M)
of EVA-LM-MSFN voice.
[C]
(M)
4-12
SURFACE SAMPLE COLLECTION A. Test A-I E-I F-I F-2 I-3 J-2 J-3 J-4 M-3 B. Test I. Objectives Provide a Contingency Lunar Surface Sample Behavior and Characteristics of the Lunar Surface Collect Rock Samples and Fine Grained Material Photograph Collection Area of Samples Obtain a Lunar Sample for Quarantine Testing Obtain a Core Sample of the Lunar Surface Collect Lunar Geologic Samples Collect a Lunar Environment Sample Obtain Photographs of Geologic Inspection & Sampling Requirements Contingency
[A]
Sample
- Obtain
upon first
descending
to the
lunar
surface.
2.
Bulk Material loose samples.
- Obtain [F]
30 pounds consisting
of I/3
fragmentary
and 2/3
3. 4.
Core Sample - Obtain
with
the drive using tools
tube. stowed
[I, in
J] the MESA. Photograph
Geologic Samples - Obtain sample areas. [J, M] Lunar Environment Sample
5. C.
- Seal
in
gas analysis
container.
[J]
Procedures/Checklist I. 2. 3. Lunar Lunar Landing Surface Mission Operations and Television Flight Plan. Operations Plan. Plan.
Photographic
D.
Data Requirements I. Flight a. b. c. d. Crew Reports/Logs/Photographs relation lunar to LM where samples were collected. [A, F, J] (M) [E] Sample. (M)
Record areas in [A, F, a] (M) Record unusual
surface
observations. collection collection
Comment on soil Comment on soil [E] (HD)
behavior behavior
during during
of Bulk of
Sample.
Documented
e.
Estimates of volume of fine grained bag of the Documented Sample. [E] 4-13
material (HD)
collected
in one
f. g. 2.
Take photographs Photograph defined in the the
during
sample
collection.
[A,
F] (HD) as
lunar surface Photographic
sample areas and of the samples Operations Plan. [J] (M)
Ground Support a. b. LM position on lunar of all surface. [J] (M) conferences. [J] (M)
MSFN recordings
MSFN/EVA voice
4-14
EXTERNAL LM OBSERVATIONS AND PHOTOGRAPHY A. Test D-I D-2 D-3 D-4 L-2 M-3 B. Test I. 2. 3. 4. 5. C. Objectives Effects of Landing on LM Landing Gear Effects of Landing on LM Structure and Components Descent Engine Skirt Damage and Clearance After Landing Effects of RCS Plume Impingement on LM Structure and Components TV Coverage of External Landed LM Obtain Photographs of Landed LM Requirements Operate the TV camera to provide any observed descent engine of LM external skirt ground an external structural clearance. impingement collected view of the LM. [D, M] [D, M] [D, M] M] [L]
Photograph Determine Photograph Obtain
damage. [D,
any effects
RCS plume
observed.
photographs
of any lunar
material
on the LM.
Procedures/Checklist I. Mission G Photographic and Television Operations Plan.
D.
Data I.
Requirements Flight a. Crew Reports/Logs/Photographs include any visible [D] (M) dis-
Comment on any LM component damage to coloration or lunar soil accumulation. Comments describing of any skirt ground any descent clearance.
b.
engine skirt [D] (M)
damage and estimate
c.
If the landing gear strut assembly estimate the amount of stroking of assembly. [D] (M)
photographs each primary
cannot be obtained, and secondary strut
d.
Photograph the landing gear to show the stroking secondary strut assemblies. [D, M] (M) Photograph the LM exterior showing any structural along
of the
primary
and
e. f.
damage.
[D,
M] (M)
Photograph each landing Y axis. [D, M] (HD)
gear assembly
the Z axis
and the
4-15
g. h. i. j. k.
Photograph Photograph
the the
descent
engine
skirt.
[D, [D,
M] (HD) M] (HD) antenna, [D, M] (HD) lunar material RCS jets,
LM base heat shield.
Photograph the LM exterior, windows and foot pads. [D, Photograph soil accumulation
i.e., structure M] (HD) on the LM.
Photographs by the close adhering to LM surfaces. Support (M), [L] of gravity
up stereo camera of [M] (HD)
2.
Ground a. b.
kM TM HBR. [D] LM Mass, [E] (M) center
(HD) and mass moment of inertia calculations.
c. d. e. f. g.
Video tape Record GET at
of all
TV coverage. signal strength
[L]
(M) TV coverage. ILl (HD)
of S-band beginning
during
and end of
TV operations. LBR TM and TV transmission. [L] (M)
Time period Identification [L] (M)
of simultaneous of ground
station(s)
used to record
video
transmission.
h.
Time period when erectable surface. [L] (M)
antenna
was used to
transmit
from
lunar
4-16
LUNAR SURFACE OBSERVATIONS AND PHOTOGRAPHY A. Test E-I E-2 E-3 H-2 J-5 L-3 [o-4 L-5 M-3 B. Test I. Objectives Behavior and Characteristics of the Lunar Surface Erosion of Lunar Surface by DPS Plume Impingement Effect of Any DPS Venting on the Lunar Surface Crew Performance of Visual Tasks on the Lunar Surface Study and Description of Lunar Topography Features TV Coverage of Lunar Surface Near LM TV Panoramic Coverage of Distant Terrain Features Coverage of Astronaut Activities on the Lunar Surface Obtain Photographs During EVA Requirements Provide TV coverage of the lunar surface in the vicinity of LM and panoramic scenes of distant terrain features. [L] the
2.
Photograph the lunar terrain at various azimuths with respect to the sun including 9, 90 and 180 degrees. Comment on ability to see terrain features in these areas. LH, M] Estimate of view the distance of photographs to prominent terrain taken. [H] features within the field
3.
4.
Observe lunar compressibility,
surface characteristics including texture, consistency, cohesiveness, adhesiveness, density and color. [E]
5.
Study and photograph the mechanical behavior of the lunar surface from interactions of astronauts boots and equipment with the lunar soil, erosion by DPS plume impingement and DPS venting. [E, M] Describe and photograph field relationships range, pattern of alignment or distribution of lunar topographic features. [J,M] Photograph state. [M] the structure of lunar surface such as shape, size, of all accessible types
6.
7.
material
in its
natural
C.
Procedures/Checklist I. Mission G Photographic and Television Operations Plan.
D.
Data I.
Requirements Flight a. Crew Report/Logs/Photographs
Report condition of the temperature indicator viewing ports on the TV camera at the beginning and the end of the TV operations. [L] (M)
4-17
b.
Position of the TV camera scan rate operation. [L] (M) Comments describing lunar surface while the interaction walking. [E]
switch
at start
of TV
c.
between (M)
astronaut
boots
and
d.
Comments on slope and roughness terrain to include descriptions ments or other obstacles. [E] Comments on the color mechanically disturbed Comments on lunar any discoloration.
characteristics of craters, (M)
of the depressions,
landing embank-
e.
and texture of both areas of the lunar adjacent
undisturbed surface. to
and [E] (M) to include
f.
soil conditions [E] (M)
DPS vents
g.
Comments describing the lunar surface penetration by the Solar Wind Composition Staff and core sample tool under their own weight and the estimated force. [E] (Mandatory for either the staff or the core sample tool: highly desirable for the other.) Comments on lunar soil erosion pingement during landing. [E] Record vent Photograph effects. valves opened. as caused (M) (M) DPS plume to impingement if soil erosive discoloraby the DPS plume im-
h. i. j. k.
[E]
the lunar surface [E, M] (M)
showing
Photograph the lunar surface adjacent tion is observed. [E, M] (M) Photograph astronaut an astronaut footprint boots and lunar surface.
DPS vents
I.
showing interaction [E, M] (M)
between
m.
Photograph the Solar Wind Composition Experiment Staff and core sampling tool after being inserted to their maximum depth as penetrometers. [E, M] (HD) Photograph the in the vicinity Photograph from [E, M] (HD) natural slopes, of the landing the CSM of the crater site. lunar walls [E,M] surface and embankments (M) surrounding the LM. of tasks
n.
o. p.
Comments on the visibility of the lunar terrain as a function the sun/viewing angle and on their ability to perform visual while on the lunar surface. [H] (M)
4-18
q. r. s.
Comments on color/contrast Comments on and significant Estimate the field
perception. unexpected
[H] visual
(M) phenomena. [H] (M) within
of distance to at least one prominent terrain of view of the photographs in item t below.
feature [HI (M) to include
t.
Photograph the lunar terrain at various sun azimuths degrees, 90 degrees and 180 degrees. [H, M] (M) Photograph any unexpected visual phenomena. [H,
0
u. v.
M] (HD)
Photograph a representative depression caused by use of the scoop in collecting fine grained fragmental material. [E, M] (M) Photograph one of the one scoop of fine grained fragmental pre-numbered bags. [E, M] (HD) material placed in
w.
x.
Photograph of each LM foot pad and surrounding evidence of LM foot pad-lunar soil interaction.
lunar soil [M] (HD)
exhibiting
2.
Ground Support a. b. c. d. e. f. LM TM HBR. Estimate Video Record of [m, L] (HD) incident illumination. TV coverage. signal strength [L] [D] (M) TV transmission. [L] (M) with TV. [L] (M) (M)
tape of all of S-band
during
GET at beginning Time period ILl (m) Identity mission.
and end of TV transmission.
when LBR TM was transmitted
simultaneously
g.
of ground [L] (M)
station(s)
used to record
LM video
trans-
h.
Time period when erectable lunar surface. [L] (M)
antenna
was used to transmit
from
the
4-19
EXPERIMENT DEPLOYMENT/CONDUCT A. Test S-031 S-078 S-080 B. Test I. Objectives Deploy the Passive Seismic Experiment Package Deploy the Laser Ranging Retro-Reflector Experiment Conduct the Solar Wind Composition Experiment Requirements Emplace, (PSEP). [S-031 ] Photograph level and orient Deploy the solar the Passive Seismic Experiment panels and aim the antenna at Package the earth.
2. 3.
the
deployed
PSEP and deployment
area.
[S-031] the descent
Remove the Laser Ranging Retro-Reflector (LRRR) from stage and carry it to the deployment site. [S-078] Emp-lace, level to she landing and orient the site. [S-078] LRRR to the alignment
4.
marks
corresponding
5.
Remove the Solar Wind Composition deploy it on the lunar surface.
Experiment [S-080]
from
the LM MESA and
6.
After one hour operation, disassemble the Solar Experiment, place the reel and foil in a teflon sample return container. [S-080]
Wind Composition bag and store in a
C.
Procedures/Checklist None
D.
Data Requirements I. Flight a. b. c. Crew Reports/Logs/Photographs of experiment. area. [S-031, [S-031] S-078, (M) S-080] (HD)
Comment on deployment Photograph deployment
Comment on location of deployed experiment LM, attitude of deployed foil with respect time foil was deployed. [S-080] (M) Retrieve IS-080] reel (M) and foil from the Solar
with respect to the to the sun and total
d.
Wind Composition
Experiment.
e. 2.
Comments on orientation [S-078] (HD) SuDport
and elevation
setting
used
for
deployment.
Ground a.
Experiment
TLM Data [S-031]
(M)
4-20
POST EVA OPERATIONS A. Test B-l C-l C-2 B. Test I. 2. C. Objectives Demonstrate Egress-to/Ingress-from the Lunar Surface EMU Capability to Provide a Habitable Environment EMU Effects on Crew Mobility, Dexterity/Comfort Requirements Perform Perform post EVA preparations [C] and ingress. [B]
PLSS shutdown.
Procedures/Checklist I. EVA Procedures Document.
D.
Data Requirements I. Flight a. Crew Reports/Logs/Photographs
Notify MSFNof the initial and final positions of the PLSS water diverter valve, primary oxygen shutoff valve and water shutoff/ relief valve each time they are changed. [C] (M) Notify MSFNwhen PLSS; High 07 flowrate, low vent water pressure or PGA pressur_ low remote control indicators and audible warning tone come on. [C] flow, low feed unit status (M)
b.
c.
Provide data on the adequacy of hardware and procedures, and the time required to perform the ingress to the LM. [B] (M) Comment on the adequacy of procedures during doffing of EMUequipment. [C] Record quantity [C] (M) of water drained and difficulties (HD) encountered
d.
e.
from PLSS at end of EVA period.
f.
Record EMU radiation [C] (M) Provide sequence member ascending
dosimeter
readings
after
completion
of
the
EVA.
g.
camera coverage the LM ladder.
and TV camera [B] (M)
coverage
of
a crew
4-21
Contamination A. Test I-l I-2 B. Test I. Objectives
Prevention
Prevent Earth Contamination by Lunar Exposed Materials Minimize Crew/CM Contamination by Lunar Exposed Materials Requirements All contamination related operations from the initial astronaut egress to the lunar surface until postflight crew/cm quarantine will be completed per procedures contained in _he documents listed below. [I]
C.
Procedures/Checklist I. 2. 3. Lunar Surface Operations Document Plan
EVA Procedures Quarantine
Procedures
D.
Data Requirements I. Flight a. Crew Reports/Logs/Photographs
Crew comments on the adequacy of Biological Isolation Garment, sample return containers, Mobile Quarantine Facility and related equipment and procedures used to prevent back contamination. [I] Photograph particles. Support Facility to the Lunar boots, clothing [I, M] (HD) and equipment showing adhesion of
(M)
b. 2.
Ground a. b.
Deliver samples, CM and Mobile Quarantine Receiving Laboratory. [I] (M)
Comment on ground procedures and hardware used for retrieval, biological isolation and CM transfer to the Lunar Receiving Laboratory. If] (M) Report on the existence of contamination of the crew on CM. [I] (M)
c.
4-22
SECTION V - CONSUMABLESANALYSIS
NOTE Acknowledgement is made to the Mission Planning and Analysis preparation of the consumable Systems Division for the PLSS Consumables Analysis Section (CAS) of the Division (MPAD) for their work in the analysis presented herein and to the Crew Consumables.
5-i
CSM-IO7/LM5
PROPELLANT BUDGET Budget Analysis are summarized in the
The results of the Propellant following Tables and Figures: TABLE 5-I TABLE 5-2 TABLE 5-3 TABLE 5-4 TABLE 5-5 TABLE 5-6 TABLE 5-7 TABLE 5-8 TABLE 5-9 TABLE 5-10 TABLE 5-11 FIGURE 5-I FIGURE 5-2 FIGURE 5-3 FIGURE 5-4 FIGURE 5-5 FIGURE 5-6 SM RCS Propellant SM RCS Budget CM RCS Propellant SPS Propellant SPS Assumptions LM RCS Propellant LM RCS Budget DPS Propellant DPS Assumptions APS Propellant APS Assumptions Total
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And Usage Summary
Summary Summary
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And Usage Summary
Summary
Summary
SM RCS Propellant
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Quad A SM RCS Propellant Quad B SM RCS Propellant Quad C SM RCS Propellant Quad D SM RCS Propellant Total LM RCS Propellant
5-I
S<-RCS
}UDOET and ASS_Z;PTiONS and dccking pkase of tke mission includes
_';ROU}_D P!ff,E8 I. am SPS 2. executed }. c:_ast. £. an
_'he transposition evasive maneuver. an_
_qke first
_hird with
milccurse C_ird is
eorrectiors kCC fol!owei durin.-
(trans!Rnar by an _qS R_-'Cor
_ are
as SP8 burns To SY RCS
the
tri,L. orTit
propellant
req_ired
lunar
%}le sixL__i
:Rideotlrse
c_rre_'tiou
(transeart})
is
execute_l
as
RCS %urn p. Qle
cf 5 fps. individual is ouad determined plots are %2," the included flijkt for reference dur!n en!// S
as she
ouart
mana;emer_t
controllers
mission. TABLE .$Y RC$ PPOPEL!A'rT 5-1 AND ,,rSANE SL%KARY 1}42._ lb due to loaded mixture ra¢io 15.6 _6.4 $0.4
LOADIN3
Kominal loadel Initial outage Total trapped ,_'-_=_,a_'ir=_ --*o this budget are _oresented in table 5-5. AV were coordinated with I2,1&B in MPAD.
It should be noted that the mission flexibility allowance c!' _,CC fps n_s used in ......... t Pe fast return. _-'d:_it'_nto _Tn real time however, it is higkly that a slower earth return _ou:u be perfornted in the missicn flexibiliLy
l r,,
beeK '" _,±ke _/ ,%;
had already been =sed ,,e,g., for _r,_rescu<). Table 5-h shows 3906 ibs of propellant re!,;¢i£in:_ ne.Ttlr_al!y and a total propellant t__ar_in (accounting _:.
from Apollo
All orientation All orientation
5-25
TABLE !/,4 RCS Propellant Loade_ Trapped !ominaldelivera%!e Gaging Inaccuracy an_ loading
5-6 and Usage Stur=_mry
Loading
6_3.0 40.6 _92.4 tolerance 39.5 17.0 _ 35.9 252.7 25_.2
_Ciztureratio uncertainty Usable Uominal mission requiremen_ i_ominalemaining r
5-26
TABLE 5-7
I_
J
-
RCS
PRhPFI TTTI F
[ ANT
_HI}GPT a q/C WT !M RCS (L3S)
PA_F IM b RCS (LBS) 633,0 628.0 628,0 626.1
I IM RCS (%) i00-0 99.2 99.2 98.9 98.6 98.3 98,2 97.9 97.3
i
TIfF HKS _
FV;I_I
b
(LBS)
O 99 I00 i00 i00 I00 • 00 I00 I00 101 I01 xO1 lO1 ZOl i01 I01 101 101 i01 lOl 101
u OGTPUI _5 _ Iv RCS hOT
PROPELLANT FIRE
LOADINGS
33714. 53709, 53709,
.0 5,0 ,0 1.9
Ui_DOCKiN_ uNCOCKI_G FOR FOR FOR VELOCITY I_SPECTION INSPECTIOI_ INSPECTION YA_ PITCH YAW
ISINuLL _0 20 25 _ bO
35707. 53705. 33703. 53702. 35690. 33687.
LNi N_h_h LN LM MhV;i MNV_
1.7!624.@ 2,0 ,8 2.0 5.6 3.6 622,@ 621,6 619.6 616.0 612,q
FOEMAIION Rk LOCK Oh
FLYING _N_R STAR STAR SIAR BURN I 2 3 AITIIUOE
O [MU C u 52 02 _b _ o_ a6 _b _o W2 IMb I_!u _NVR
REALIGN RLALIGN REALIGN TO DOI NOLD ULLAGE
33683. _680. 33676, 33672. 53672. 35667, 3_W19,
96,7 96,2 95,6 95,0 95.0 9W,I 9W,I 93,3 92,1 92,1 91.9 91,3 91.3 91,2 91.0 90.4 actual weight
_.6i608.8 5,6 5.6 .1 5.9 ,0 5,0 7.6 .3 1.0 3.6 ,6 ,6 1.2 3.6 reflect 605,2 601.6 601.5 595.6 595.8 590,6 583,0 582,8 581,8 578.2 577,6 577,0 575,8 572.2 the
ATTITb_E 2 _ET
_GI
BUrN CONTROL DCI BURN
_OI, EI_T TEI_
33W14. 55W07. 33W07. 33W06.
hGRIZONTAL hOLD L:OWN ON NNVR
RESIDUAL
ATTIToOE PITCH RR
LOCK
_3602, 33W01. 33W01,
i01 =51PITCH DOWN
lOl 102 102
a
55 0 IU
YA_
LEFT CHECK 01_ MNVR analysis only loaded and
ALIGNNENT Rlt LOCK
33400. 33396. do not
b
These _fter
wezghts were used for consumables loadin_. remaining
RCS propellant
of total
5-27
TABLE 5-7
(CONT'D) _%UI C-F'[ • _1 ,. [q/C ,_]_ I N (LBS) RCS P_(_F. LM RCS D 2
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MISSION G PLSS CONSUMABLEANALYSIS
THE RESULTS OF THE PLSS BATTERY, OXYGEN, WATER AND LiOH CONSUMABLE ANALYSIS ARE SUMMARIZED IN THE FOLLOWING FIGURES:
FIGURE 5-18
LMP ANDCDR PLSS BATTERY PROFILE CDROXYGENROFILE P LMPOXYGENROFILE P CDR H20 PROFILE LMPH20 PROFILE LMPANDCDR LiOH CO 2 PROFILE
FIGURE 5-19 FIGURE 5-20 FIGURE 5-21 FIGURE 5-22 FIGURE 5-23
5-50
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