Embed Size (px)
Citation preview
MISSION PLANNING AND ANALYSIS DIVISION
N74-70678
Unclas00/99 16319
April 9,1969
MANNED SPACECRAFT CENTERHOUSTON,TEXAS
AERONAUTICS AND SPACE ADMINISTRATION
APOllO 10 (MISSION F)
SPACECRAFT OPERATIONAL
ALTERNATE MISSION PLANS
MSC INTERNAL NOTE NO. 69-FM-85
VOLUME III
lUNAR ALTERNATE RENDEZVOUS
::::::::::::::;::: -(N ASA-TM-x-69816) APOLLC 10 (MISSION F)::::::::::::::::::SfACECBAFT OPERATIONAL ALTEBNAT EMISSION:::::::::::::::::: PLANS. VOLUME 3: LUN AR ALT ERN AT E::::::::::::::::::BENDEZVOUS (NASA) 35 P..................
·- I~:.:.:.:.:.:.:.:.:.:.:.:90:::::::::::::::::::::::
•~t~~ttt~~.~~~ fJ'~ :~:.~{:::::::t} ,~ {', -•. ,'\ NATIONAL
~ f ..; ::::~:~~.:.:.:.:.:.:.:.:.:.:.:.
~~~~j:j:j[j:j:j:~:j:j:j:.......................:::::::::;:::::::::::::::::::::::::::::::::::::.:.:.:.:.:.:.:.:.:.:..::::::::::::::::::::::::.:.:.:.:.:.:.:.:.:.:.:.:..:.:.:.;.:.: ..:.:.:.:.:........................:::::::::::::::::::::::..:.:.:.: ..:.:.:.:.:.:.:.:::::::::::::::::::::::::::::::::::::::::::::::.:..:.:.:.:.:.:.:.:.:.::::::::::::::::::::::::........................'"..........~ :::::::::::::::::::::::..................................................:.:.:.:.:.:.:.:.:.:.:.:.:.:.:.:.:.:.:.:.:.:.::::::::::::::::::::::::.:.:.:.:.:.:.:.:.:.:.:.:::::::::::::::::::::::;.;.:.:.:.:.:.:.:.:.:.:::::::::::::::::::::::::::::::::::::::::::::::. . .• :::::::::::::::::::::::.:.:.:.:.:-:-:.:.:.;.:.:.:.:.:.:.:.:.:.:.:.:.:::::::::::::::::::::::::::::::::::::::::::::::........................:.:.:.:.:.:.:.:..:.:.:.:.:.:.:.:.:.:.:.:.:.:.:::::::::::::::::::::::::=:::::::::::::::::::::.:.:.:.:.:.:.:.;.:.:.:.::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::=:.:.:.:.:.;.:.:.:.:.:.::::::::::::::::::::::::.......................
)ifIWtW.:.:.:.:.:.:.:.:.:.:.:.:::::::::::::::::::::::.:.:.:.:.:-:.:.:.:.:.:.:.:.:.:.:.:.:.:-:.:.:.:::::::::.:.:.:.::::::::
••
•
•
MSC INTERNAL NOTE NO. 69-FM-85
PROJECT APOLLO
APOLLO 10 (MISSION F) SPACECRAFT OPERATIONALALTERNATE MISSION PLANS
VOLUME III - LUNAR ALTERNATE RENDEZVOUS
By Ronny H. MooreOrbital Mission Analysis Branch
April 9, 1969
MISSION PLANNING AND ANALYSIS DIVISION
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION
MANNED SPACECRAFT CENTER
HOUSTON, TEXAS
APproved:~co...J C~Edgar C. Lineberry, ChiefOrbita' 'ssion Anal sis Branch
Approved: ,in., J.,-o..,..h....n~.:...:r-a-lyr-'-,~C""'·:""::e~"""""-""":;;....a",-----r -Mission Planning and Analysis Division
••
•
••
Section
1.0
2.0
3.0
4.0
5.0
6.0
7.0
CONTENTS
SUMMARY
INTRODUCTION
SYMBOLS AND DEFINITIONS
INPUT DATA, GUIDELINES, AND ASSUMPTIONS
BASIC RENDEZVOUS TECllliIQUES . . . . . .
ALTERNATE RENDEZVOUS PLANS AND PROCEDURES FORVARIOUS SITUATIONS . . . .
6.1 Alt.ernate la, DPS Unstaged .
6.2 P~ternate lb, APS Inoperative
6.3 Alternate 2, APS Rendezvous
6.4 Alternate 3, Modified Football
CONCLUSION
REFERENCES
iii
Page
1
1
2
5
6
6
7
8
9
10
30
TABLES
Table
I MANEUVER SUMMARY FOR OPERATIONAL APOLLO 10(MISSION F) RENDEZVOUS . . .
II MANEUVER SUMMARY FOR ALTERNATE la, DPS UNSTAGED
•Page
11 •12
III
IV
V
VI
MANEUVER SUMMARY FOR ALTERNATE lb, APSINOPERATIVE .
MANEUVER SUMMARY FOR ALTERNATE RENDEZVOUS 2,APS ONLY .
MANEUVER SUMMARY FOR ALTERNATE RENDEZVOUS 3,MODIFIED FOOTBALL
TEST OBJECTIVE SUMMARY
iv
113
14
15
16
•
••
FIGURES
Figure Page•
1
2
3
4
5
6
Relative motion nominal rendezvous and alternatesla and lb .. ... . ..
Relative motion alternate 2, APS only
Relative motion alternate 3, modified football
Relative motion of descent stage with respect tothe ascent stage for alternatelb ....
Relative motion of descent stage with respect toCSM for alternate 2 " .... .
Relative motion of descent stage with respect tothe CSM for alternate 3 . .
19
20
21
22
7 MSFN coverage and daylight/darkness summary foralternate la, DPS unstaged
(a) 98:00 to 103:~0
(b) 103:00 to 106:20(c) 108:00 to 109:40
8 MSFN coverage and daylight/darkness summary foralternate lb, APS inoperative
(a) 98:00 to 103:00(b) 103:00 to 108:00
232425
2627
•9
10
MSFN coverage and daylight/darkness summary foralternate rendezvous 2, APS only .
MSFN coverage and daylight/darkness summary foralternate rendezvous 3, modified football
v
28
29
••
••
•
••
APOLLO 10 (MISSION F) SPACECRAFT OPERATIONAL.
ALTERNATE MISSION PLANS
VOLUME III - LUNAR ALTERNATE RENDEZVOUS
By Ronny H. Moore
1.0 SUMMARY
This document, which is VolUIlle III of the operational alternatemission plan for Apollo 10 (Mission F), presents the operational lunarorbital alternate rendezvous plans. Four 1M-active alternate rendezvousplans and procedures which fulfill mission test objectives are presented. With the exception of the LM-active modified football alternate, the alternate plans are based on various postulated nonnominalsituat~ons in wh~ch the basic coelliptic rendezvous s~que~ce is used.
Although the operational plans were generated for the May 17 missionlaunch date, they are generally applicable to ar"y launch date a.nd time.Based on formulated ground rules and known constraints, the operationalplans are feasible from a trajectory standpoint; that is, the plans donot impose unique maneuvers or procedures, additional crew training,or new software requirements for the onboard or the ground supportcapabilities. The plans update those published in the pr-eliminaryalternate mission plan (ref. 1).
2.0 INTRODUCTION
The total mission planning effort for Apollo 10 (Mission F)includes alternate mission plans for both the earth orbital and thelunar orbital mission phases. The preflight planning effort is significantbecause certain mission test objectives can be accomplished if properpreparations are made for development of the operational alternatemission plans, techniques, procedures, and mission rules. Therefore,the purpose of this document is to present four operational alternateplans which are feasible based on certain ground rules and knownconstraints.
The ground rules and rendezvous techniques and the operationallunar orbital alternate rendezvous plans are presented for the followingnonnominal situations.
2
1. Inflbility (or nondesire) to jettison the descent stage
2. Loss of useful APS only,
3. Loss of useful DPS only
4. Loss of both APS and DPS
Maneuver summaries, relative motion plots, daylight/darkness histories,and MSFN tracking summaries are presented for all the alternate rendezvousplans.
3.0 SYMBOLS AND DEFINITIONS
AGS abort guidance system
••
APS ascent propulsion system
CDR constant differential height
CES control electronics system •CSI coelliptic sequence initiation
CSM command and service modules
~h differential altitude between active and inactive vehicle orbits
~v total change in velocity caused by thrusting
DOl descent orbit insertion
DPS descent propulsion system
F.T. full throttle
G.m.t.
g.e.t.
Greenwich mean time
ground elapsed time from earth lift-off •h apocynthion altitude referenced to the landing site
a
h pericynthion altitude referenced to the landing sitep
•
••
•
••
lMU
1M
LPO
MSFN
PDl
PGNCS
RCS
RTCC
SM
SPS
TEl
TM
TPl
TPF
VHF
alternate rendezvous
APS rendezvous
coelliptic sequence
DPS rendezvous
---------------
3
inertial measurement unit
lunar module
lunar parking orbit
Manned-Space Flight Network
powered descent initiation
primary guidance and navigation control subsystem
reaction control system
Real-Time Computer Complex
service module
service propulsion system
transearth injection
telemetry
terminal phase initiation
terminal phase finalization
very high frequency
any deviation from the nominal rendezvous toaccomplish mission objectives
any rendezvous during which the APS is theprimary propulsion system and no DPS isavailable
a rendezvous technique to establish, prior toTPl and at a different altitude, an activevehicle (chaser) orbit and to establish adesired relative condition at a selectedtime forTPl
any rendezvous during which the DPS is theprimary propulsion system and no APS is required
football rendezvous
4
a relative condition between the CSM and LMinitiated by a radial separation which placesthe vehicles in equiperiod orbits such thatrendezvous occurs one orbit later
••
4.0 INPUT DATA, GUIDELINES, AND ASSUMPTIONS
The following guidelines and assumptions were used to design thealternate rendezvous plans.
1. LM test objectives will have first priority.
2. Alternate rendezvous time lines will not exceed the nominalrendezvous time line.
3. No additional crew training will be required for alternates.
4. No additional RTCC or onboard processors will be necessary .
5. Alternate plans will be consistent with current spacecraft,crew, and operational constraints.
6. The CSM will be nominal in all alternates.
7. The sequence of events will contain no more maneuvers thanthe nominal rendezvous.
8. The CSI-CDH coelliptic sequence will be used whenever possible.
9. RCS backup capability will be maintained on any APS-onlyrendezvous.
Sources of input data used to design the alternate rendezvousare summarized as follows. 1M test objectives are discussed in detailin the mission requirements document (ref. 2), while the LM operationalconstraints were obtained from the Apollo Operations Handbook (ref. 3).The spacecraft operational trajectory (ref. 4) presented the operationalrendezvous time line and the initial vectors used to generate thealternate plans. Weights and engine performance parameters were obtainedfrom the Spacecraft Operational Data Books (refs. 5, 6, and 7) andfrom reference 8. The MSFN tracking was generated based on requirementsdefined by Flight Control Division (ref. 9) and by use of MSFN stationsdefined by Goddard in reference 10.
•
••
• 5
•
•
••
5.0 BASIC RENDEZVOUS TECHNIQUES
Except for the modified football rendezvous, the basic rendezvoustechnique that is used for the alternate rendezvous plans is the CSl-CDRcoelliptic sequence. The objective of the pre-CSl logic is to applya maneuver (CSl) which will result in the desired TPl conditions beingobtained by the active vehicle at a selected TPl time after a coellipticmaneuver (CDR) has been performed at a selected time after CSI. Thistechnique is used in the Apollo 10 (Mission F) rendezvous. A maneuversummary of the Apollo 10 (Mission F) rendezvous is presented in table I.Although the CSI-CDR technique is used, two preceding maneuvers(phasing and insertion) are required to establish the proper conditionsso that the coelliptic sequence of the Apollo 10 (Mission F) rendezvouswill be nearly identical to the planned lunar landing mission sequence.A similar scheme is used in the alternate plans when advisable; however,a CSl-CDR rendezvous sequence may be arranged with only one maneuver(phasing) so that rendezvous can occur one revolution earlier. Thissingle pre-CSl maneuver technique is used in the APS-only alternaterendezvous to conserve APS power and time. The DOl is a maneuverdesigned to enable the 1M to brake out of the LPO and to descend overa specific landing site. Although it is not designed specifically asa rendezvous maneuver, it may be altered to arrange for more favorableconditions for some alternates. The phasing maneuver and, wheredesirable, insertion are planned so that certain conditions are obtainedduring the rendezvous sequence. The conditions are as follows.
1. The TPI maneuver will occur at the midpoint of darkness on aLM-to-CSM elevation angle of 26.6°.
2. Coelliptic ~h will be 15 n. mi. with the 1M below the CSM.
3. The CSI maneuver wil~ occur at the first apocynthion afterinsertion or' after phasing on the shortened rendezvous sequence.
4. The CDR will occur one-half period after CSI.
All of these conditions exist during the nominal Apollo 10 (Mission F)rendezvous.
The other rendezvous technique considered is the modified football,which is initiated by a radial separation maneuver. Rendezvous couldbe accomplishea exactly one revolution after the radial separationmaneuver if an identical radial maneuver is performed in the oppositedirection along with terminal line-of-sight br~~ing. However, the ~V
requirement for braking is reduced if a standard TPI is performed atthe chaser pericynthion to increase the travel angle during terminalphase from 90° to 130°. The football technique is suggested as an
6
alternate exercise if neither main LM propulsion system is usableor if a complete rendezvous is not allowed for some other reason.
6.0 ALTERNATE RENDEZVOUS PlANS ANDPROCEDURES FOR VARIOUS SITUATIOfS
The alternate rendezvous plans are designed for situations duringthe Apollo 10 (Mission F) lunar orbit when the nominal 'rendezvous cannotbe attempted.
6.1 Alternate la, DPS Unstaged
A DPS rendezvous alternate la may be flown if it is apparent thatthe descent stage cannot be staged, either because of a failure of thestaging mechanism or because of a desire to retain the DPS for laterdocked maneuvers (i.e., a docked DPS TEl). The sequence of events forthis alternate rendezvous is presented in table II.
The alternate la sequence is exactly the same as the nominalrendezvous sequence presented in table I except that descent staging,which occurs nominally 10 minutes prior to insertion" is not performed.All maneuvers prior to insertion are performed as in the operationalsequence. Insertion, CSI, and TPI are performed with DPS. The CDHis performed with the 1M RCS because it will normally be a smallmaneuver. However, if the required 1M RCS burn time is greater thanor equal to 10.0 seconds (~V ~ 4 fps), the maneuver will be performedwith the DPS at 10 percent thrust to avoid approaching the four-jet+X RCS impingement limit of 15-seconds for burn duration.
Because the unstaged LM is somewhat difficult and inefficient tomaneuver during the braking phase, the CSM will perform the brakingmaneuvers and docking. Thus, after this rendezvous, the orbit will beapproximately 43 n. mi. by 62 n. mi. If it is not desirable to performTEl in this orbit, a docked circularization maneuver would be performedat apogee approximately one revolution later. The posigrade SPS burnof 26.1 fps will be approximately 2.2 seconds in duration in the dockedconfiguration. The 1M might not be jettisoned prior to circularizationbecause it may be desirable to perform TEl with the DPS. All the rendezvousalternate la parameters and relative motion will be the same as for thenominal rendezvous. The only differences in profiles are the burn timesof insertion and subsequent maneuvers caused by use of different propulsion systems and a heavier vehicle. A maneuver smnmary foralternate la is presented in table II, and the relative motion is presented in figure 1. The MSFN coverage and the daylight/darkness history
••
•
••
••
•
••
7
are showni~ figure 7. Note that TPI, nominally performed with the RCS,will be executed with the DPS at 10 percent full thrust to avoid a lengthyRCS burn. As a result, radar lock-on must be broken to perform TPI.However, the current nominal plan is to execute TPI with the +X RCS;with open interconnect, which also requires momentary loss of radarlock-on.
6.2 Alternate Ib, APS Inoperative
The DPS rendezvous alternate Ib, maybe flown if the APS enginecannot be used or if ascent battery power is limited. The latter situation would make it desirable to remain on descent power as long aspossible. The sequence of events is identical to a DPS rendezvousalternate la except that descent staging can occur when the descentstage is no longer needed. Staging is planned to occur after CDR so thatTPI and braking (TPF) can be performed with the LM RCS and, therefore, anominal terminal phase can be accomplished.
The recommended staging sequence is as follows.
1. Perform a 2-fps retrograde maneuver with 1M RCS -x jets ata convenient time after the CDR maneuver.
2. Stage.
3. Perform a 2-fps posigrade maneuver with the +X thrusters.
The staging sequence will place the descent stage below both the 1Mand the CSM and will prevent any recontact problem. The 2-fps retrogrademaneuver places the 1M on a slightly different ellipse, and by stagingand performing a 2-fps posigrade maneuver with the ascent stage,'_taeascent stage will return to the original ellipse. The relative motionof the descent stage with respect to the ascent stage is shown infigure 4. The staging sequence is performed at a convenient time afterthe CDH maneuver such that tracking and pre-TPI procedures between CDHand TPI are not disturbed. The DPS stage is retained until after theCDH maneuver to conserve APS power. The maneuver summary for alternate Ibis presented in table III, and the relative motion, which is the same asthat for DPS rendezvous alternate la, is shown in figure 1. The MSFNcoverage summary and the daylight/darkness history are presented infigure 8.
8
6.3 Alternate 2, APS Rendezvous
An APS rendezvous may be flown when the DPS cannot be used. Thesequence of events for this rendezvous is presented in table IV.
To provide adequate separation distance at DOl, theCSM performsthe minifootball maneuver as in the nominal sequence. The stagingsequence recommended during +-he mini football is the following.
1. Approximately 15 minutes prior to DOl, perform a 2-fps posigrade maneuver with the LM RCS (-X jets).
2. Stage the DPS.
3. Perform a 2-fps retrograde maneuver (+X jets).
The sequence of maneuvers will place the descent stage behind and aboveboth the CSM and 1M and will prevent any recontact problems. The relative motion of the descent stage with respect +-0 th,= CSM is shownin fig"L'.re 5. By comparison of this figure with figure 2, it isapparent that no recontact problems should occur. To conserve APSpower, the DPS stage is retained 1.lIltil just prior to DOl. Because DOl,which is performed with the APS, is targeted to achieve a 40-n. mi.pericynthion altitude, any slight perturbations in the 1M traj ectory"caused by the staging sequence will not be significant.
Approximately 195° prior to the landing site, the APS performsDOl to approximately a 40-n. mi. pericynthion altitude. The choice ofpericynthion altitude is based on the 1M RCS impingement limit for theascent stage (a continuous burn of approximately 55 sec). If the APSis lost, any backup RCS burns must be less tha.n this limit. With a40-n. mi. pericynthion altitude, the largest possible RCS burn (CDR)is approximately 50.4 seconds in duration. At pericynthion after DOl,the APS performs a phasing maneuver targeted to set up relative conditions so that the coelliptic rendezvous sequence to place TPI at themidpoint of darkness will result in a ~R of 15 n. mi. when CSI and CDRare performed on the next. apsis crossings. Phasing raises LM apocynthionaltitude to approximately 102 n. mi., at which point CSI is performed.The CDR maneuver is performed one-half period later at pericynthion.The CSI maneuver raises pericynthion altitude to approximately 46 n. mi.so that the retrograde APS CDR can place the 1M in a coelliptic orbit15 n. mi. below the CSM. The CSI and CDR maneuvers could be performedby use of the RCS thrusters with the APS interconnect because sufficientAPS propellant will still be available. The TPI maneuver occursapproximately 35 minutes after CDR on a 1M-to-CSM elevation angle of26.6°. Terminal phase occurs as in the nominal rendezvous profile,although one revolution sooner. Alternate 2 contains one less maneuver
••
•
••
••
•
••
9
(insertion} than the operational sequence to permit rendezvous onerevolution earlier, which conserves the APS power supply. A similarsequence is planned as part of the nominal PDI abort procedure forboth the F and G missions; therefore, no new crew training or uniqueprocedures are introduced here. For alternate 2, the maneuver summaryis shown in table IV, the relative motion in figure 2, the MSFNcoverage and the daylight/darkness history in figure 9.
6.4 Alternate 3, Modified Football
In all rendezvous plans, the sequence is begun with a separationmaneuver. The maneuver is a small radial maneuver that places the CSMand LM in equiperiod orbits to enable the vehicles to arrive at thesame position one orbit later. The relative motion caused by themaneuver is termed minifootball. A 2.5-fps radially-down maneuverperformed by the eSM will place the eSM approximately 1.9 n. mi. aheadof the 1M at DOI. The DOI maneuver normally is performed 180° afterthe separation maneuver or halfway through the minifootb~ll. Likewise,a 2.5-fps radially-up maneuver will place the CSM approximately 1.9 n. mi.behind the .LM at DOI. If no other type of rendezvous is possible becauseof unusable DPS and APS engines or for some other reason, a modifiedfootball could be performed to check out the rendezvous radar and theVHF ranging. If the radial separation is 80 fps instead of 2.5 fps,the maximum range obtained is approximately 61 n. mi. .Close approachwould occur one orbit later if no maneuvers were performed. A nearnominal terminal phase can be accomplished by performing TPI on anelevation angle of 26.6° and at the midpoint of darkness but with a~h at TPI of approximately 14.6 n. mi. instead of the nominal 15.0 n. mi.Performance of the standard 1300 transfer from TPI rendezvous lengthensthe transfer time by approximately 15 minutes but lessens the ~V required. An 80-fps radial maneuver was chosen so that the maximum rangepossible would be obtained without violation of the 1M ReS impingementlimit on the APS (55-sec burn duration). The 80-fps separation maneuver is 51.9 seconds in duration. Descent staging occurs 15 minutesprior to the 80-fps separation maneuver. The recommended sequence isas follows.
1. Perform 2-fps retrograde maneuver (eSM +X jets).
2. Stage.
3. Perform 2-fps posigrade maneuver (eSM -X jets).
Performance of this sequence will place the'descent stage below and infront of the eSM as shown by the relative motion in figure 6.
10
Because the separation maneuver will place the ascent stage ahead andabove the CSM, no recontact problems exist. The relative motion isshown in figure 4; the maneuver summary, in table V; MSFN tracking anddaylight/darkness history, in figure 10.
7.0 CONCLUSION
The data and procedures presented in this document represent theoperational lunar orbital alternate rendezvous plans for Apollo 10(Mission F). The purpose of the document was to propose alternatesthat are feasible from a trajectory standpoint. The RTCC and RTACFprocedures and processors will be used to compute the maneuvers inreal time, and real-time maneuver targeting rather than preflightgenerated data will be relied upon for the alternate missions. Theprocedures and' data do not vary significantly within the launch windowwith the exception of the g.e.t. of the maneuvers and the MSFN coverage.The plans were generated based on a launch date of May 17,1969, and a
lift-off time of l6h
33m
49.37ls G.m.t.; however, the plans are basicallyapplicable to any launch date and time. These plans were designed tosatisfy certain test objectives. A summary of test objectives relatedto the nominal rendezvous are presented in table VI, along with theauthor's estimated accomplishment of each test objective during eachalternate rendezvous.
••
•
••
••
•TA
BLE
I.~
MAN
EUVE
RSU
MM
ARY
FOR
OPE
RATI
ON
AL
APO
LLO
10(M
ISSI
ON
F)
REN
DEZ
VO
US
••
Tim
esi
nce
Ull
age
Th
rust
Resu
ltan
to
rbit
C,
Tim
e,p
rev
iou
sf::
,V,
man
euve
rM
ain
eng
ine
dir
ecti
on
bP
rop
uls
ion
h/h
,M
aneu
ver
day
:hr:
min
:sec
,fp
sf::
,ta,
f::,t,
,sy
stem
ap
g.e
.t.
man
euv
er,
sec
deg
mi.
min
:sec
n.
sec
Min
ifo
otb
all
4:0
2:5
5:4
0.0
--2
.5--
7.2
27
0.0
-xRC
S6
1.2
/57
.8(C
SM)
(fo
ur-
jet)
DO
l4
:03
:54
:12
.058
:32
.07
2.8
8.0
15
.0(1
0%)
18
0.0
DPS
58
.2/8
.21
1.5
(40%
)
Ph
asin
g4
:05
:06
:35
.07
2:2
3.0
19
3.5
8.0
26
.0(1
0%)
26
.0D
PS1
94
.4/9
.81
5.0
(F.T
.P.
)
Des
cen
t4
:06
:53
:29
.01
06
:54
.0--
----
----
--
stag
ing
In
serti
on
4:0
7:0
3:2
9.0
10
:00
.02
13
.34
.01
4.4
15
2.6
AP
S4
3.6
/9.8
CSI
4:0
7:5
4:4
0.0
51
:11
.05
0.5
--3
2.1
0.0
+xRC
S4
5.9
/43
.1(f
ou
r-je
t)
CDR
4:0
8:5
2:4
1.0
58
:01
.05
.8--
3.7
27
0.0
-xRC
S4
6.2
/42
.8(f
ou
r-je
t)
TPI
4:0
9:2
9:1
6.0
36
:35
.02
4.9
--1
5.8
27
.1+X
RCS
62
.3/4
3.0
(fo
ur-
jet)
TPF
4:1
0:1
1:4
1.0
42
:25
.031
.5--
39
.83
05
.3-Z
RCS
61
.2/5
7.8
(tw
o-j
et)
aln
clu
des
0.5
-sec
on
du
llag
eo
ver
lap
.
bMea
sure
dco
un
terc
lock
wis
efr
omd
irecti
on
of
mo
tio
n.
cMea
sure
dab
ove
lan
din
gsit
era
diu
s(0
.8n
.m
i.be
low
mea
nra
diu
s).
TABL
EII
.-M
ANEU
VER
SUM
MAR
YFO
RA
LTER
NA
TEla
,D
PSU
NST
AG
ED
Tim
esi
nce
Ull
age
Th
rust
Resu
ltan
to
rbit
C,
Tim
e,p
rev
iou
s6V
,m
aneu
ver
Mai
nen
gin
ed
irecti
on
bP
rop
uls
ion
h/h
Man
euve
rd
ay
:hr:
min
:sec,
fps
nta
,6
t,,
syst
ema
p'
g.e
.t.
man
euv
er,
sec
deg
mi.
min
:sec
n.
sec
Min
ifo
otb
all
4:0
2:5
5:4
0.6
--2
.5--
7.1
27
0.0
-xRC
S6
1.2
/57
.8(C
SM)
(fo
ur-
jet)
DO
l4
:03
:54
:11
.658
:31
.07
2.7
8.0
15
.0(1
0%)
18
0.0
DPS
58
.2/8
.21
2.5
(40%
)
Ph
asin
g4
:05
:06
:34
.47
2:2
2.8
19
3.5
8.0
26
.0(1
0%)
26
.0D
PS1
94
.7/9
.61
5.9
(F.T
.P.)
Inse
rtio
n4
:07
:03
:02
.31
16
:27
.92
13
.28
.01
5.0
(10%
)1
51
.1D
PS4
3.6
/9.9
42
.9(4
0%)
CSI
4:0
7:5
5:2
1.2
52
:18
.95
0.3
8.0
42
.3(1
0%)
0.0
DPS
43
.8/4
3.6
CDH
d4
:08
:53
:22
.35
8:0
1.1
6.1
8.0
3.7
(10%
)2
70
.0D
PS4
6.2
/42
.8
TP
I4
:09
:29
:15
.63
5:5
3.3
24
.88
.01
6.8
(10%
)2
7.1
DPS
62
.3/4
2.9
TPF
(CSM
)4
:10
:11
:26
.64
2:1
1.0
31
.6--
90
.01
26
.3+X
RCS
62
.3/4
2.9
(fo
ur-
jet)
Cir
cu
lar-
4:1
2:2
3:0
3.1
13
1:3
6.5
26
.12
0.0
2.2
0.0
SPS
62
.3/6
2.2
izati
on
(CSM
)
aln
clu
des
0.5
-sec
on
du
llag
eo
verl
ap
.
bMea
sure
dco
un
terc
lock
wis
efr
omd
irecti
on
of
mo
tio
n.
cA
ltit
ud
em
easu
red
abov
ela
nd
ing
sit
era
diu
s(0
.8n
.m
i.b
elo
wm
ean
rad
ius)
.
dlf
6V<
4.0
sec,
the
bu
rnw
ill
be
done
wit
h-X
fou
r-je
tR
CS.
••
••
•
••
•TA
BLE
nI.
-M
ANEU
VER
SUM
MAR
YFO
RA
LTER
NA
TE1
b,
APS
INO
PER
ATI
VE
••
Tim
esi
nce
Ull
age
Th
rust
Resu
ltan
to
rbit
C,
Tim
e,p
rev
iou
sf::
,V,
man
euve
rM
ain
eng
ine
dir
ecti
on
bP
rop
uls
ion
h/h
,M
aneu
ver
day
:hr
:min
:sec,
man
euv
er,
fps
f::,ta
,f::
,t,se
c,
syst
ema
pg
.e.t
.de
gn
.m
i.m
in:s
ecse
c
Min
ifo
otb
all
4:0
2:5
5:4
0.6
--
2.5
--
7.1
27
0.0
-xRC
S6
1.2
/57
.8(C
SM)
(fo
ur-
jet)
DO
l4
:03
:54
:11
.65
8:3
1.0
72
.78
.01
5.0
(10%
)1
80
.0D
PS5
8.2
/8.2
12
.5(4
0%)
Ph
asin
g4
:05
:06
:34
.47
2:2
2.8
19
3.5
8.0
26
.0(1
0%)
26
.0D
PS1
94
.7/9
.61
5.9
(F.T
.P.)
Inse
rtio
n4
:07
:03
:02
.31
16
:27
.92
13
.28
.01
5.0
(10%
)1
51
.1D
PS4
3.6
/9.9
42
.9(4
0%)
CSI
4:0
7:5
5:2
1.2
52
:18
.95
0.3
8.0
21
.8(1
0%)
0.0
DPS
45
.8/4
3.6
CDH
d4
:08
:53
:22
.35
8:0
1.1
6.1
8.0
3.7
(lO
%)
27
0.0
DPS
46
.2/4
2.8
Des
cen
t4
:09
:08
:22
.3l5
:00
.0--
----
----
--st
ag
ing
e
TP
I4
:09
:29
:l8
.02
0:5
5.7
24
.8--
l6.1
27
.l+X
RC
S6
2.3
/43
.0(f
ou
r-je
t)
TPF
4:1
0:1
1:4
3.4
42
:25
.43
1.6
--4
1.0
30
5.3
-zRC
S6
1.2
/57
.8(t
wo
-jet)
aln
clu
des
0.5
-sec
on
du
llag
eo
verl
ap
.
bMea
sure
dco
un
terc
lock
wis
efr
omd
irecti
on
of
mo
tio
n.
CA
ltit
ud
em
easu
red
abov
ela
nd
ing
sit
era
diu
s(0
.8n
.m
i.b
elo
wm
ean
rad
ius)
.
dIf
f::,V
<4
.0fp
s,th
eb
urn
wil
lb
edo
new
ith
+Xfo
ur-
jet
RC
S.
eSee
secti
on
6.2
for
stag
ing
pro
ced
ure
s.
TAB
LEIV
.-M
AN
ElN
ERSU
MM
ARY
FOR
ALT
ERN
ATE
REN
DEZ
VO
US
2,
APS
ONLY
Tim
esi
nce
Ull
age
Th
rust
Resu
ltan
to
rbit
C,
Tim
e,p
rev
iou
s6V
,m
aneu
ver
Mai
nen
gin
e,
dir
ecti
on
bP
rop
uls
ion
h/h
,M
aneu
ver
day
:hr:
min
:sec,
6ta
,m
an
euv
er,
fps
6t,
sec
,sy
stem
ap
g.e
.t.
deg
n.
mi.
min
:sec
sec
Min
ifo
otb
all
4:0
2:5
5:4
0.6
--
2.5
--
7.1
270.
0-x
RCS
61
.2/5
7.8
(CSM
)(f
ou
r-je
t)
Des
cen
td
4:0
3:3
9:2
8.7
43
:48
.1--
--
--
--
--
--
stag
ing
DO
l4
:03
:54
:28
.71
5:0
0.0
28
.24
.01
.91
80
.0A
PS5
8.2
/40
.0
Ph
asin
g4
:04
:53
:56
.05
9:2
7.3
57
.74
.04
.00
.0A
PS1
02
.2/4
0.0
CSI
4:0
5:5
4:2
4.2
60
:28
.27
.7--
5.0
0.0
+XR
CS
10
2.2
/45
.7(f
ou
r-je
t)
CDH
4:0
6:5
5:0
1.9
60
:37
.87
8.3
4.0
5.5
4.4
APS
46
.1/4
2.8
TP
I4
:07
:30
:10
.93
5:0
9.0
24
.9--
15
.92
7.2
+XR
CS
62
.2/4
2.9
(fo
ur-
jet)
TPF
4:0
8:1
2.3
6.4
42
:25
.53
1.8
--
40.5
305.
3-Z
RC
S6
1.2
/57
.8(t
wo
-jet)
aln
clu
des
0.5
seco
nd
ull
ag
eo
verl
ap
.
bM
easu
red
cou
nte
rclo
ckw
ise
from
dir
ecti
on
of
mo
tio
n.
CA
ltit
ud
esm
easu
red
abov
ela
nd
ing
sit
era
diu
s(0
.8n
.m
i.b
elo
wm
ean
rad
ius)
.
dS
eese
cti
on
6.3
for
stag
ing
pro
ced
ure
s.
••
••
•
••
••
TABL
EV
.-M
AN
EtN
ERSU
MM
ARY
FOR
ALT
ERN
ATE
REN
DEZ
VO
US
3,
MO
DIF
IED
FOO
TBA
LL
•
Tim
e,T
ime
sin
ce
Ull
age
Th
rust
Resu
ltan
to
rbit
b,
pre
vio
us
6V,
man
euve
ra
Pro
pu
lsio
nh
/h,
Man
euve
rd
ay
:hr:
min
:sec,
fps
6t,
dir
ecti
on
,sy
stem
ap
g.e
.t.
ma
neu
ver
,d
egn
.m
i.m
in:s
ecse
c
Des
cen
t4
:03
:44
:03
.7--
--
--
--
--
--
stag
ing
c
Sep
arat
ion
4:0
3:5
9:0
3.7
15
:00
.08
0.0
51.9
88
.7+X
Res
75
.6/4
3.9
(fo
ur-
jet)
TP
I4
:05
:31
:18
.392
:14.
61
8.5
11
.917
5.2
+XRC
S6
1.8
/43
.9(f
ou
r-je
t)
TPF
4:0
6:1
3:4
4.3
42
:26
.030
.839
.630
5.1
-ZRC
S6
0.9
/58
.1(t
wo
-jet)
~easured
cou
nte
rclo
ckw
ise
from
dir
ecti
on
of
mo
tio
n.
bA
ltit
ud
es
mea
sure
dab
ove
lan
din
gsit
era
diu
s(0
.8n
.m
i.b
elo
wm
ean
rad
ius)
.
c See
secti
on
6.4
for
stag
ing
pro
ced
ure
s.
f-J VI
TABL
EV
I.-
TEST
OB
JEC
TIV
ESU
MM
ARY
Est
imat
edp
erc
en
tac
com
pli
shed
Deta
iled
test
ob
jecti
ve
Mo
dif
ied
DPS
APS
foo
tball
lalb
23
l.L
M-a
ctiv
ere
nd
ezv
ou
s70
9555
20
2.
PGN
CSu
nd
ock
edp
erfo
rman
ce1
00
10
0--
--
3.
LM/C
SM/M
SFN
VO
ICE/
TM1
00
10
01
00
10
0
4.
Lu
nar
orb
itv
isib
ilit
y1
00
10
040
40
5.
Ren
dezv
ous
rad
ar
per
form
ance
10
01
00
251
5
6.L
and
ing
rad
ar
test
10
01
00
----
7.
1Msu
perc
riti
cal
hel
ium
10
01
00
----
8.
AG
S/C
ESatt
itu
de/t
ran
sla
tio
nco
ntr
ol
75
10
01
00
10
0
9.
1M/A
GS
ren
dez
vo
us
ev
alu
ati
on
10
01
00
9520
10
.PG
NC
S/A
GS
mo
nit
ori
ng
10
01
00
8530
ll.
VH
Fra
ng
ing
10
01
00
10
01
00
12
.G
roun
dsu
pp
ort
lun
ar
dis
tan
ce
10
01
00
10
01
00
13
.1M
IMU
per
form
ance
10
01
00
10
01
00
14
.A
GS
per
form
ance
10
01
00
5050
••
••
•.\
••
••
•...
......
uDar
knes
s
t--~
r-- r
--- !'...
. ..........
.
"'\ 1\ t
I--'
----:]
II1/
CSI1
J""
("'1
,V
~I"I
I.....
. ...-I-
'"
"'-
I'-In
sert
ion
_f..---Ii J
DOl
1.6
2.0
•••
.. ::
",,'1
",'"
.... .... ....
- _0E
:,.._
_,-..~I.l1JU.U
••u.t
,......
c·4
1--'...
.
-N~
MilifO
O~ball
-.
o.4
.81.
2-
X,n.
mi.
I--P
hasi
ngm
aneu
ver
"'"_
/TP
I......I
I"CD
H/'
f---t--+--f-O"!b"".t;o-+--+-t---+---+-+--+--:::;;j,...-""~=+-----l~-+--+--+--+-+
;.,...
...,-"
--1-
+--
-1--
+--
-1--
--
200
160
120
'E C80
"E Q.) E
40Q
.) u '"Q
.)
"i5.
> 0V
>.c
:c«
'"0
u t;;: 0
Q.)
Q.)
>co
40 80 120
360
320
280
240
200
160
120
8080
120
160
200
240
140
'----'-
---'-
---J'-
---'-
---'-
---'_
-'-
-..
....
L..
---l.
_-'-
---'-
----'-
_'-
----L
---'-
_'-
--'-
---'-
---'_
-'-
-..
....
L..
---l.
_-'-
---'-
---'-
_'-
---'-
------'-
_'-
--'-
---..
....
L..
--1
280
Hor
izon
tald
ispl
acem
ent.
n.m
i.
Figu
re1.
-R
elat
ive
mot
ion
nom
inal
rend
ezvo
usan
dal
tern
ates
laan
dlb
.
'")\--
'O
J
/.-
"
"......
CDH
2.0
\/0
01
1.6
TP
F""
",,/
f-D0
1
.81.
2X,
n.m
i.o
.4
N-
o60I--
I40
,,+.~"
~"~"~~
~I"~"~
"~'t'~
"~"~"+
'=~~~;
=F=:::
:::::t
--~:::
::::-+
--~-J-
-~----
t--L-l
-l-J
1--+
--+
---t-
-I---+
.-••-.
.-••....j
. iPb..·
..·-
~CS
I.....
.••--~
f--+
--+
--+
-:o
>.'·
...···i-
-r--
i-t-
-t--
t---
-lr-
--l'-
----
t--+
--4-
-+--
+I -~---+!---...-:::
:::"
,.J-
--+-
-+--
-+--
-!--
-L-J
"~I
20i-1
-7i"c-
"-"-"'
t-t-i-
ir--t-
-t--t-
---Jf-
--t--t
--+---
-J--+-
-+--I-
----l"
'--=:~
~+---l
-----1
--L-J
" ..' ..' l :
I--
0E...
......
.Dar
knes
s
80I--
C.4
I---
+-~.
~"...
ttI
....
....
...
....
....
....
...
".~-
'....~-----j--t---t---+----1--t--+--+--i--t----1---J---I-----I
,I"~
••.••
,••.""
..........
~#,.,.
, '.
°E c .... c w E w u co Ci.
V1 :c
w >c;
;0 .c
u«
:e w >
4011
1-t-
--t-
t-t-
+-+
----
-f-+
-++
-+-f
-+-+
---I
---J
--+
----
1---
-l--
--L
-J--
---J 14
012
010
080
60~...L--~----L-~~L..---;;---.L~---..l-~--l----!.:---l~~~--L---.L--l-LL---L--l-----l--.-J
100
8060
4020
Ahea
d0
Beh
ind
2040
60
Hor
izon
tald
ispl
acem
ent
n.m
i.
Figu
re2.
-R
elat
ive
mot
ion
alte
rnat
e2,
APS
only
.
••
••
•
••
••
•3
0
20
E s::: ..1
0..... s::: .Q
) E Q)
Q)
u>
lI:l
00
....
0
VI
<X:
-0 lI:
l0
u t Q)
s:>
0 Q)
OJ 1
0
...U
IIU
Dar
knes
s
..--- -
r---
~r---
......
./
~V
........
~/
Via
dia
,se
para
tion
, ,I
,I
TP
Fj
~;
/~'
"....~
~"'-
......~
~
'-.""
lrTP
1~'
~,.....
''''',...
......
...,
IIIII
••·.....1
••••
••••
11••
··'~"""
20 1
0A
head
oB
ehin
d1
02
03
040
50
60
70
Hor
izon
tal
disp
lace
men
t,n
.m
i.
Fig
ure
3.-
Rel
ativ
em
otio
nal
tern
ate
3,
mod
ified
foo
tba
ll.
1
E
..T
ime
tick
sev
ery
20
min
with
resp
ect
tode
scen
tst
agin
g
..D
esce
ntst
agin
gJ
1~
\.
~~
V/
...""
'--~
I--"
-----~
-
2 o13 2
Q) >
~0
~.0
a:;<
!E Q
)
U I1l
a. '" -0
:;; oI1
lQ
)U
OJ
~ W >
76
54
32
1A
head
oB
ehin
d1
Hor
izon
tal
disp
'lace
men
t,n
.m
i.
Fig
ure
4.-
Rel
ativ
em
otio
no
fde
scen
tst
age
with
resp
ect
toth
eas
cent
stag
efo
ral
tern
ate
lb.
••
••
•
••
••
• f\)
I-'
•T
ime
tick
sev
ery
20
min
wit
hre
spec
tto
des
cen
tst
agin
g,
y19
'
.-
----r-
--~
Des
cent
sta
gin
g7y~
~.....
......
/"- r«
v.
I
'-M
inif
oo
tball
23
s:::E
:;: o QJ co
4
, =QJ E ~1
a.
III
-Q
J-0
>-
0~
..0
~eu
Q; >
20
Beh
ind
12
34
56
78
Hor
izon
tal
disp
lace
men
t,n
.m
i.
Fig
ure
5.-
Rel
ativ
em
otio
nof
des
cen
tst
age
wit
hre
spec
tto
CSM
for
alte
rnat
e2
.
o 23
I•
Tim
eti
cks
ever
y2
0m
inw
ith
2re
spec
tto
desc
ent
stag
ing
1
~ JD
esce
ntst
agin
gJ
12~
~V
-'"
~I-
-.~
~
r-- t
--
--1.-
--•
1
E
76
54
32
1A
head
0B
ehin
d1
Hor
izon
tal
disp
lace
men
t,n
.m
i.
Fig
ure
6.-
Rel
ativ
em
otio
no
fde
scen
tst
age
with
resp
ect
toth
eC
SM
for
alte
rnat
e3
.
••
••
•
••
Min
ifoot
ball
•00
1
••
Hr
AC
NC
YI
M"n
MIL
ANG
BO
A
TEX
GY
MG
DS
DA
YLI
GH
TD
AR
KN
ES
SD
AY
liGH
T
98:0
098
:10
98:2
098
:30
98:4
098
:50
99:0
099
:10
99:2
099
:30
99:4
099
:50
100:
0010
0:10
100:
2010
0:30
Pha
sing
Gro
und
elap
sed
time,
hr:m
in
AC
N
CY
IC
YI
MA
DA
NG
ANG
MA
D
BOA
BOA
MIL
TEX
TEX
M
GYM
GY
M
GD
SG
DS
HAW
-H
AW
DA
YliG
HT
DA
RK
NE
SS
DA
YLI
GH
T
l\)
\.)j
100:
3010
0:40
100:
5010
1:00
101:
1010
1:20
101:
3010
1:40
101:
5010
2:00
102:
1010
2:20
102:
3010
2:40
102:
5010
3:00
Gro
und
elap
sed
time,
hr:m
in
(a)
98:0
0to
103:
00.
Figu
re7.
-M
SFN
cove
rage
and
dayl
ight
/dar
knes
ssu
mm
ary
for
alte
rnat
ela
,D
PSun
stag
ed.
TPI
CSI
COH
CY
I
IAN
GI
ANG
MAD
BOA
BOA
:TE
X
TEX
GY
M
MIL
GD
S
GYM
MIL
GO
SI
HAW
IH
AW
OARKNES~
GW
M
DA
YLI
GH
TD
AY
LIG
HT
DA
RK
NE
SS
_
Inse
rtio
n
103:
0010
3:10
103:
2010
3:30
103:
4010
3:50
104:
0010
4:10
104:
2010
4:30
104:
4010
4:50
105:
0010
5:10
105:
2010
5:30
Gro
und
elap
sed
tim
e,hr
:min
I\)
+""
.--
eRO
.•
TPF
-,
ANG
ANG
TEX
IB
DA
BD
A
TEX
GYM
GY
MG
DS
GD
SM
IL
MIL
HAW
HAW
HSK
GW
MG
WM
DA
RK
NE
S_
DA
YLI
GH
TD
AR
KN
ES
SD
AY
LIG
HT
105:
3010
5:40
105:
5010
6:00
106:
1010
6:20
106:
3010
6:40
106:
5010
7:00
107:
1010
7:20
107:
3010
7:40
107:5
010
8:00
Gro
und
elap
sed
time,
hr:m
in
ltl}10
3:00
to10
6:20
.
Figu
re7.
-C
ontin
ued.
••
••
•
••
Cir
cula
riza
tio
n
••
•
TEX
1GY
MGD
SHA
WHS
KGW
MCR
ODA
YLIG
HTDA
RKNE
SSI\
)V
l
108:
0010
8:10
108:
2010
8:30
108:
4010
8:50
109:
0010
9:10
109:
2010
9:30
109:
40
Gro
und
elap
sed
time,
hr:m
in
(c)
108:
00to
109:
40.
Figu
re7.
-C
oncl
uded
.
Min
ifo
otb
all
001
HaW
ACN
CYI
MAD
MIL
ANG
BOA
TEX
GYM
GDS
DAYL
IGHT
DARK
NESS
DAYL
IGHT
II
II
II
II
II
II
II
III
II
II
II
II
II
II
II
II
II
JI
JI
JJ
II
II
JI
II
JJ
JJ
II
II
JI
JI
IIII
II
II
II
II
I98
:00
98:1
098
:20
98:3
098
:40
98:5
099
:00
99:1
099
:20
99:3
099
:40
99:5
010
0:00
100:
1010
0:20
100:
30
Gro
und
elap
sed
time,
hr:m
in
Pha
sing
I\)
0'\
AN
CYI
CYI
MAD
ANG
ANG
MAD
BOA
BOA
MIL
EXEX
Mil
GYM
MGD
SGD
SHA
WHA
W
100:
3010
0:40
100:
5010
1:00
101:
1010
1:20
101:
3010
1:40
101:
5010
2:00
102:
1010
2:20
102:
3010
2:40
102:
5010
3:00
Gro
und
elap
sed
time,
hr:m
in
(a)98
:00
to10
3:00
.
Figu
re8.
-M
SFN
cove
rage
and
dayl
ight
ldar
knes
ssu
mm
ary
for
alte
rnat
eIb
,A
PSin
qler
ativ
e.
••
••
•
••
••
•C
SI
Inse
rtio
nC
DH
Des
cen
tst
agin
gTP
I
CY
I
ANG
ANG
"AB
DA
BD
ATE
X
TEX
GYM
MIL
GD
SG
YMM
ILG
DS
HA
WH
AWG
WM
_D
AY
LIG
HT
DA
RK
NE
SS
DA
YLI
GH
TD
AR
KN
ES
SI
II
II
II
III~I
II
II
II
II
II
II
II
IIIlfflll
IIT
IT
II
II
II
II
II
II
II
II
II
II
II
II
II
103:
0010
3:10
103:
2010
3:30
103:
4010
3:50
104:
0010
4:10
104:
2010
4:30
104:
4010
4:50
105:
0010
5:10
105:
2010
5:30
Gro
und
elap
sed
time,
hr:m
in
TPF
ANG
BD
A
TEX
GYM
GD
S
MIL
HAW
GW
M
105:
3010
5:40
105:
5010
6:00
106:
1010
6:20
Gro
und
elap
sed
time,
hr:m
in
(bl
103:
00to
108:
oo.
Figu
re8.
-C
oncl
uded
.
Min
ifco
tbal
lD
esce
ntst
agin
gDO
l
IHA
WAC
NCY
IM
ADM
ILAN
GBD
ATE
XGY
MGD
SDA
YLIG
HTDA
RKNE
SSDA
YLIG
HT
98:0
098
:10
98:2
098
:30
98:4
098
:50
99:0
099
:10
99:2
099
:30
99:4
099
:50
100:
0010
0:10
100:
2010
0:30
Pha
sing
Gro
und
elap
sed
time,
hr:m
in
CSI
CDH
ACN
CYI
CYI
MAD
ANG
MIL
MAD
ANG
BOA
BDA
TEX
TEX
MIL
GYM
GYM
GDS
GDS
HAW
HAW
DAYL
IGHT
DARK
NESS
DAYL
IGHT
.f\
)C
P
100:
3010
0:40
100:
5010
1:00
10U
O10
1:20
101:
3010
1:40
101:
5010
2:00
102:
1010
2:20
102:
3010
2:40
102:
5010
3:00
TPI
Gro
und
elap
sed
time,
hr:m
in
TPF
CYI
1AN
G-.
"An
1BD
ATE
XM
ILGY
Mf:D
C;HA
WDARKNES~
DAYL
IGHT
103:
0010
3:10
103:
2010
3:30
103:
4010
3:50
104:
0010
4:10
104:
20
••G
roun
del
apse
dtim
e,hr
:min
Figu
re9.
-M
SFN
cove
rage
and
dayl
ight
/dar
knes
ssu
mm
ary
for
alte
rnat
ere
ndez
vous
2,AP
Son
ly.
••
•
••
•D
esce
nt
stag
ing
Sep
arat
ion
••
nHA
WAC
NCY
IM
ADM
ILAN
GBO
ATE
XGY
MGD
SDA
YLIG
HTDA
RKNE
SDA
YLIG
HTI
II
II
II
II
II
II
II
II
II
II
II
II
II
II
II
II
II
II
II
II
II
ITT
TT
TT
II
II
III
II
II
II
II
II
II
II
98:0
098
:10
98:2
098
:30
98:4
098
:50
99:0
099
:10
99:2
099
:30
99:4
099
:50
100:
0010
0:10
100:
2010
0:30
Gro
und
elap
sed
time,
hr:m
in
TI
TPF
ACN
CYI
MAD
MIL
ANG
BDA
TEX
GYM
GDS
HAW
DAYL
IGHT
DARK
NESS
DAYL
IGHT
II
II
II
II
II
II
II
II
II
II
II
II
II
II
II
II
II
II
II
II
II
II
II
II
II
II
II
I\)
\0
100:
3010
0:40
100:
5010
1:00
101:
1010
1:20
101:
3010
1:40
101:
5010
2:00
102:
1010
2:20
Gro
und
elap
sed
time,
hr:m
in
Figu
re10
.-M
SFN
cove
rage
and
dayl
ight
/dar
knes
ssu
mm
ary
for
alte
rnat
ere
ndez
vous
3,m
odifi
edfo
otba
ll.
30
REFERENCES
1. Moore, R. H.; and Miller, S. L.: Preliminary Alternate MissionPlan for Apollo Mission F, Volume III - Lunar AlternateRendezvous. MSC IN 69-FM-38, March 4, 1969.
2. TRW: Mission Requirements SA-505/CSM-106/LM-4 F Type MissionLunar Orbit. SPS9-R-037, February 11,1969.
3. Grumman Aircraft Engineering Corporation: Apollo OperationsHandbook, Lunar Module 4, Volume I - Subsystems Data.NAS-9-1100, June 15, 1968.
4. OMAB; LMAB; and LAB: Spacecraft Operational Trajectory for ApolloMission F, Volume II - Operational Mission Profile TrajectoryParameters Launched May 17, 1969. MSC IN 69-~1-66, March 10,1969.
5. CSM/LM Operational Data Book, Volume I - CSM Data Book.SNA-8-D-027, May 1968.
6. CSM/LM Spacecraft Operational Data Book, Volume II - LM Data Book.SNA-8-D-027, May 1968.
7. CSM/LM Spacecraft Operational Data Book, Volume III - MassProperties. SNA-8-D-027, March 1968.
8. Peterson, D. G.: Monthly Propellant Status Report for MainPropulsion SUbsystems (SPS, DPS, APS). MSC memo 69-FM74-90,February 26, 1969.
9. Flight Control Division: Flight Control Network SupportRequirements, Missions F and G, Ref. A. FC031, January 15,1969.
10. Goddard Space Flight Center: Goddard Directory of TrackingStation Locations.· July 1, 1964.
••
•
••
