iqisc_pa-r-os-/ sul)i)lement 2 national aeronautics and space administration apollo .5 mission...
TRANSCRIPT
STI CENTER -GS;53o45/100NASA JOHNSON SF_,,V,'.'_FO!_-i,i'[E=i
210i NS_£;!_,F :,_,.0:.- ,:.EHOUSTON, TX 77058_3696
75-A/7_, 4_'?
NASAIn
Connectionto Aerospace
A Service of:
NationalAeronautics andSpace Administration
USCIENTIFIC &
TECE/NI CAL INEOR.MATION
IQISC_PA-R-OS- /
Sul)i)lement 2
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION
APOLLO .5 MISSION REPORT
i
APOLLO MISSION 5/AS-204/LM-1 TRAJECTORYi RECONSTRUCTION AND POSTFLIGHT ANALYSIS
VOLUME I
.
(NES&-TM-X-721105) APOLLO .5 tlirSSION REPORT° 1t75-72089SUPPLEMENT 2: APOLLO MISSION 51As_ao_irn_IrHAJECTOR_ RECONSTRUCTION AND POSTFLIGI/T
ANALYSIS, VOLUME i (_ASA) 187 p Uncles
!iii!iii !!!ii .............: :-:.:.:.:.:.: /<7,. _:_• • iIlllllllll • - _ ,
• -.'.'.'.'.', i__ _.'>i__..">" ' -',I
:,::: :-:: _
" i:i'i::i;' DISTRIBUTION AND REFERENCING• el• • •
• This poper Is not luitable'for generoI distribulion or referencing. It moy he referenced
• only in other working cotrelpondence and documents by pe,ticipoting organizations.i Q•
._.;_,,4if _ MANNED SPACECRAFT CENTER._._ HOUSTON, TEXAS-: May 1968
• ° ° . • ° • •
• ..... • °
...... ° ,
MSC-PA-R-68-7
Supplement 2
APOLLO 5 MISSION REPORT
Supplement 2
APOLLO MISSION 5/AS-204/LM-1 TRAJECTORY
RECONStrUCTION AND POSTFLIGHT ANALYSIS
VOLUME I
May 13, 1968
Prepared by: TRW Systems Group
Approvedby: __L_ow _ __--t_George M.
Manager
Apollo Spacecraft Program
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION
MANNED SPACECRAFT CENTER
HOUSTON, TEXAS
05952-H484-R0-00
I"RWNOTE NO. 68-FMT-642
PROJECT APOLLO
TASK MSC/TRW A-50
iii i" i
APOLLO MISSION 5/AS-204/LM-1 TRAJECTORYRECONSTRUCTION AND POSTFLIGHT ANALYSIS -
APPENDIXESi n i i [ i i
VOLUME I
22 APRIL 1968
PreparedbyGuidance and Control Department
W. P. GirodT. A. PhythianG. L. Roland
SystemsEvaluation DepartmentJ. M. AlfredE. L. BarnettD. H. CooperJ. B. Moore
PreparedforMISSION PLANNING AND ANALYSIS DIVISION
NATIONAL AERONAUTICS AND SPACEADMINISTRATIONMANNED SPACECRAFTCENTER
HOUSTON, TEXAS
FOREWORD
This report is submitted to the NASA Manned Spacecraft Center in
accordance with Task: MSC/TRW A-50.3 Contract NAS 9-4810. This
report contains the postflight analysis performed in conjunction with the
flight of Apollo Mission 5/AS-204/LM-t, and is issued as a supplement to
Section 3, Trajectory Section, of the Apollo Program Mission Report.
The report is issued in two volumes. Volume I contains details of
the analysis and results obtained, including appendices. Volume II con-
tains a listing of the "45 Day" Best Estimated Trajectory (BET) for the
LM-t mission from S-IVB separation to the occurrence of the gimbal lock
condition in the PRA-V burn sequence. This listing is in the NASA Apollo
Trajectory (NAT) format which is shown below. The listing is not gener-
ally distributed, but is available from NASA/MSC upon request. Requests
should be made to:
NASA/MSC Computations Analysis DivisionCentral Metric Data File
Code ED-5, Bldg. t2, Room 133Houston, Texas 77058
The listing is in three parts which are identified by time span covered and
the corresponding accession number.
Time Span (GET) Accession No.
Part I 00:53:54- 04:06:21 05- 07334
Part II 04:06:00 - 06:17:56 05 - 07335
Part IH 06:13:40 - 07:47:32 05 - 07336
iii
NASA APOLLO TmAJKTOI_Y INOI!x
_qTR GmTC GnT¢ G|TS GIR _TC_C_19$ $ECONO_ l_'ItlRS $ECONO$ SFCONDS _m MIN SEC
_CENTRIC G_nET|C _E_nETIC G_O_TIC INFmT_&L TNERTTAL I_RTIJLLAT|TqI_E LATtTI_nE LON_[TI_n_ ALT|T_nE VELOCITY PATH ANGLE HEIOI_G
_RBIT R_D[U$ _EOCE_IC nELATIVE R_LATIYE R_LATIV_
L_ _CLtN_TION R_l_r_ O_|VATIVE ALTITUDF V_L_CITY PATH ANGLE _EADING_E_S F_T F_T/SEC FEET _ET/SEC _£GREES O£GR£[_
2_ X ECI v _C| Z _CI _n_T _C| VnnT _! _I'_T _C| G SIl__T _F_ _F_T ¢_F115_C _T/$_C _F_T/SEC F_ET/SE_ o_
_ _ F_I_ Y EC?G Z _Ct_ _OT _1_ V_0T EC|G _O_T FCIG C $1J_ YF_T FEFT F_T _F_PS_C _F_T/S_ FF_T/S_C FF_T/S[C _*_
4t _ I_C Y AG_ _ IGC XD_T IGC ¥_T A_¢ ?n_T AGC C $tl_ 7
_? IJ £CF V _CF W FC_ I_0_T ECF V_C_IT _CF _Ol'JclT EC_ OIAtTFF_T F_T F[_T FF_TISFC*_Z _£ET/SEC_*? FE_T/SEC_I2
6_ _C_ _C| V_r)OT EC! ZDf_T EC! _D_IT _CIG Y_DOT _Ct_ ZO_CT _¢IG IEV_LUT_N_T/S_et2 _TF_FC_e2 FE_YtS[CelZ FF_T_E_Qe 2 _¥/_o*_ _Tp_C_I2
_E_T/_C_2 F_ET/S_C_? FEET/_C_2 FFFT F_T N_I N_!
?_ AXIS AXIS FCC_NTRt_ITY _CLINAII_ _O_E° AT_$ P_RIGFE _N_AL_
_ P_RI_ SAT** _R_W_H _lT,e ARI_$ |_LI_I _, _RN'dCH AN_NALY ANOMALv
_MT°LITttS SP_F_ _ N&CH _YNAMIC _V_K_LnS T_TAL
_lPl TC_AL _DV_NtC AFRn_YNA_|C AFP_DYN_IC
t0_ _f_T PIPA YD_T PIP& ZOOT PIPA V[LOC|TY VELOCITY PATH ANGLE HFA_!_
X_T E_F V I_T F_ 70CIT ESF WIkP W|_
iV
CONTENTS
Page
3. APOLLO MISSION 5/AS-Z04/LM-I TRAJECTORYRECONSTRUCTION AND POSTFLIGHT ANALYSIS ....... 3-i
3. i Introduction and Summary .................... 3-I
3. i. I Sequence of Events .................... 3-i
3. i.2 Analysis and Programs ................. 3-I
3.2 Ascent Analysis .......................... 3-7
3. 3 Orbit Analysis ........................... 3-Z4
3.3. I Lunar Module Orbital Reconstruction ....... 3-36
3.3. 2 RTCC Trajectory Comparison ............ 3-38
APPENDIXES
A TRACKER I_.SIDUAI_ PLOTS ................. A-I
B SUPPLEMENTAI_Y DATA .................... B-i
ILLUST RATIONS
Page
3-1 AS-Z04 Mission Timeline and Tracking Periods ........ 3-3
3-2 Uncompensated G&N Minus S-IVB (Boost) - Delta XVelocity ................................. 3-10
3-3 Uncompensated G&N Minus S-IVB (Boost) - Delta YVelocity ................................. 3- 11
3-4 Uncompensated G&N Minus S-IVB (Boost) - Delta ZVelocity ................................. 3 -1Z
3-5 Uncompensated G&N Minus S-IVB (Boost) - Delta XPosition ................................ 3- 13
3-6 Uncompensated G&N Minus S-IVB (Boost) - Delta YPosition ................................ 3- 14
3-7 Uncompensated G&N Minus S-IVB (Boost) - Delta ZPosition ................................ 3-15
3-8 Compensated G&N Minus S-IVB (Boost) - Delta XVelocity ................................. 3 -16
3-9 Compensated C;&N Minus S-IVB (Boost) - Delta YVelocity ................................. 3-17
3-10 Compensated G&N Minus S-IVB(Boost) - Delta ZVelocity .................................. 3-i8
3-1! Compensated G&N Minus S-IVB(Boost) - Delta XPosition .................................. 3- t9
3-1Z Compensated(JAN Minus S-IVB(Boost) - Delta YPosition .................................. 3 -20
3-13 Compensated G&N Minus S-IVB(Boost) - Delta ZPosition .................................. 3 -21
vii
TA BLES
Page
3-1 Summary of Events ........................... 3-Z
3-2 IMU Performance Parameters .................... 3-9
3-3 State Vector Comparison - Compensated LM G&N MinusBET (t = 600. 0 seconds) ........................ 3-Z2
3-4 Timeline of Launch Events ...................... 3-23
3-5 LM Orbital Fit Summary ....................... 3-Z6
3-6 Residual Mean and RMS by Station and Data Type forSegments 1-5 ............................... 3-29
3-7 State Vector Summary ......................... 3-34
3-8 Maneuver Summary ........................... 3-37
3-9 Position and Velocity Comparison - LM-I G&N versusBET/PRA HI ............................... 3-38
3-10 RTCC Summary of Radar Data for AS-Z04/LM-I ........ 3-39
3-Ii RTCC Comparison Summary ..................... 3-44
3-12 RTCC Comparison Summary for Special Vectors ........ 3-45
B-I Radar Data Su_cnrn,_ry .......................... B-2
B-Z C-band Station Locations ........................ B-4
B-3 USBS Station Locations ......................... ]3-6
B-4 Drag Summary .............................. B-7
13-5 Radar Data Weighting .......................... B-7
ix
3. APOLLO MISSION 5/AS-Z04/LM-I TRAJECTORY RECONSTRUCTIONAND POSTFLIGHT ANALYSIS
3. I INTRODUCTION AND SUMMARY
3. i. I Sequence of Events
The Apollo 5 mission was launched from launch complex 37 B at
Cape Kennedy, Florida, on 22 January 1968. Range zero was established
at Z2 hours, 48 minutes, and 8 seconds Greenwich mean time (GMT), with
lift-off securing 0.4 second later. Lunar module/Saturn IVB (LM/S-IVB)
insertion occurred at 10 minutes and 3.3 seconds ground elapsed time
(GET) with subsequent LM/S-IVB separation at 53 minutes and 56 seconds
GET.
After two and a half revolutions, the first descent engine burn was
initiated by the guidance computer. This burn was performed at less than
full tank pressures; consequently, the thrust buildup was not adequate, and
the engine was shutdown by the computer 4 seconds after ignition.
The premature cutoff of this burn required deviations from the
planned mission. A:modified alternate mission was used which combined
mission program sequences HI and V. Mission program sequence III was
comprised of two descent engine burns and two ascent engine burns.
However, the second ascent engine burn in sequence HI was inhibited by
ground command. Mission program sequence V was comprised of an
ascent engine burn that continued until all the fuel aboard was depleted.
Table 3-1 lists the times associated with events pertinent to this trajectory
analysis. A complete mission description may be obtained from the
Apollo 5 Mission Re_rt. Figure 3-1 presents the AS-204 mission time-
lines and tracking l_riods.
3. 1. 2 Analysis and Programs
This section describes the programs that are used in the postflight
trajectory analysis. The programs used to reconstruct the orbital phase
of a mission and associated programs are discussed first, followed by
description of the programs used in the analysis of the guidance system
and the reconstruction of the spacecraft trajectory during thrusting
periods.
3-1
•_.
_.
__
__
_o
_.
_....
....................
o
_d
__
g_
_4
dM
Md
o_
Mm
0_
__
_
_0
•o
'o
<_
_<
_._
o._
__
_0_0
_o_
3-Z
-11 i
"tI! ilL
3 I 2
22 2_4808 22"23:4808 23:0(9:48:08 23014808I I I I 1 I
qw---- DPS ; ULLAGE OJ_
/ i_DPS I FNGIN'_ ISNITION .......
f
II _DOS I _NGINF CCITOFF ......
II
, []
Hail ....
t 1GROUND _LAPSEO rIME (HRI 5
23:0; 48:08 23:03:48:08 2304I I I 1
C_REENWICH MEAN TIMt [DAY:']R MIN:S[CI
I , I_ I' I I
APS ENGINE CUTOFF _I--APS FUEL 0EPLETIOI
i
1I--
--I--
8
48:08 23:05.48:08 23:06:48:08l I I I
Figure 3-I. AS-204 Mission Tim,
line and TrackingPeriods
3-3
Orbit Reconstruction Programs
Low-speed tracking data for a mission are received from MSC on a
magnetic tape. The data tape is input into the Master Tape Generator
(MATAG) Program which reformats the data into a format that is compat-
ible with the TRW orbit determination program (ESPOD) and generates a
time-ordered master data tape. The master data tape is then input into
the ESPOD Data Generator (EDG) Program which edits the master data
tape and outputs the delta in the form of tape or cards.
The ESPOD Program determines the state vector for a spacecraft
at a given epoch and the covariance matrix of uncertainties. This is
accomplished by an iterative process which minimizes the weighted sum
of the squares of the residuals, where the residuals are the difference
between the actual ob_Jervations and the computed observations based
upon a current estimate of the spacecraft trajectory. ESPOD also has
the capability of including in the solution vector such parameters as drag
(CdA/ZM), radar errors, and station location errors.
There exist two versions of ESPOD, both of which have the general
capability described above. The USB ESPOD is distinguished by the fact
that it can process RAER, RxY, and doppler radar tracking data. It does
not, however, have the capability of modeling burns. The IGS ESPOD, in
contrast, can only process RAER radar tracking data even though it does
have two burn models, the LOP burn model and the IGS burn model. The
LOP burn model uses an analytic thrust acceleration model - constant
thrust oriented along the roll axis. Thrust/mass ratio, and orientation of
roll axis are _ome of the parameters that can be included in the solution
vector. The IGS burn model uses an acceleration burn tape based on
telemetered data which is then input into ESPOD. Accelerometer and
gyro errors may be modeled or included in the solution vector.
After a best estimate of the trajectory (BET) is obtained in ESPOD,
a trajectory tape is generated and input into the RTCC Comparison
Program. This program compares the RTCC trajectory and the BET by
means of state vecto:c differences exhibited in various coordinate systems.
The total difference in position and velocity is also listed.
3-5
Guidance and Navigation Programs
The spacecraft trajectory during thrusting periods after S-IVB
separation is reconstructed from inertial measurement data telemetered
from the guidance and navigation system. Before an accurate recon-
struction can be undertaken, it is necessary to determine the systematic
errors present in the guidance system hardware so that appropriate
corrections to the IMU data can be made. This procedure for trajectory
reconstruction may be divided into three general areas.
Data Processing
The three sources of trajectory data used in Apollo IMU evaluation
must be formated so that they are compatible with the trajectory com-
puting programs.
a) The G&N Processor Program is used to edit Apollo
downlink telemetry data and produce a regular
ephemeris of measured position, velocity, andacceleration.
b) The S-IVB Processor Program is used to inter-
polate the S-IVB IU trajectory to the AGC/LGCtime base and rotate the data into appropriatecoordinate frames.
c) The General Data Processor Program is used to
smooth, interpolate, and rotate high-speed
tracking data (GLOTRAC, C-band) to an appro-
priate time base and coordinate frame.
IMU Evaluation
Determination of the systematic errors present in the Apollo guidance
system is based primarily on comparisons of the trajectory (sensed and
total) as measured by the AGC/LGC, with S-IVB and GLOTRAC trajec-
tories. The boost phase of any mission is the most important for this
analysis because of the relatively long lime duration with high acceleration
levels. The two principal tools used in IMU error analysis are discussed
in the following paragraphs.
3-6
a) The Error Analysis Program (EAP) is used to
compute the partial derivatives of sensed
position, velocity, and acceleration
(_Ps/bEk, bVs/_Ek, bAs/_Ek)with respect
to each of the error terms, Ek, in the ApolloIMU error model. The input which drives
the EAP is the edited ephemeris of sensedacceleration obtained from the G&N Processor
Program.
b) The Velocity Comparison Program {VELCOMP)
corrects the Apollo sensed trajectory profile
using the EAP partials and the best estimates
of the IMU errors, E k. It then compares thecorrected trajectory (in both sensed and total
coordinates) with external reference trajectorydata (S-IVB and GLOTRAC). The recoveredset of IMU errors must, of course, be com-
patible with the preflight test history of the
onboard guidance system and with the known
trajectory constraints during later phases ofthe mission.
Trajectory Reconstruction
During thrusting periods for which limited external trajectory data
are available, a different technique for trajectory reconstruction is
employed. This method relies on two external inputs: {l) the set of IMU
hardware errors determined from ascent analysis and (2) an accurate
state vector,. {Po' Vo)' from the ESPOD program to initialize the total
trajectory. The Trajectory Reconstruction Program is driven with the
outputs of the G&N Processor and EAP Programs. At time, t i, the total
corrected velocity is computed from:
= +V -K_ sl Ek +VTi Vo si _Ek VGi
This quantity is integrated to obtain total position, PTi' which is extra-
polated to time, ti+l, for the next computation of velocity due to gravity,
(VGi+ 1)"
3. 2 ASCENT ANALYSIS
Analysis of IMU errors consists of determining the physically
acceptable set of errors which bring the LM G&N trajectory into agree-
3-7
ment with the best estimate of the actual trajectory flown. This "best
estimate" is referred to as the Best Estimate Trajectory (BET). During
the boost phase there were eight trajectories available from which to
chose a standard of comparison, or BET. These eight trajectories were
classed into two independent groups. Five of the trajectories were gen-
erated by MSFC from the S-IVB Instrument Unit (IU) telemetry data. They
represent a five -stage evolution in the processing of that data, from the
raw (quick look) IU output through a final S-IVB BET designated the "Final
S-IVB Observed Mass Point Trajectory (OMPT)". The three remaining
trajectories represent a similar evolution in the processing of GLOTRAC
radar data. The final OMPT and final GLOTRAC trajectories agreed
closely throughout most of the burn. However, the GLOTRAC data BET
became erratic near the endpoints of the burn, and the final trajectory
generated from itwas truncated to exclude data prior to 24 seconds and
subsequent to 552 seconds. Therefore, in order to have a continuous
trajectory available for comparisons with the LM G&N data, and since the
S-IVB data agreed so well with the external source (GLOTRAC), the S-IVB
final OMPT was chosen as the boost phase BET.
The error magnitudes associated with each IMU error model para-
meter were derived from comparisons of the LM G&N trajectory and the
BET. These errors are presented in Table 3-2- together with their pre-
flight estimates and uncertainties. In this table, the great majority of
the derived error magnitudes lie within their associated uncertainty band.
In general, errors satisfying that constraint will not be discussed further
except to reiterate that they were selected because the state vector errors
they produce coincide with observed residuals.
The IMU error set given in Table 3-2 was used to construct a com-
pensated LM G&N trajectory. Plots of the trajectory comparisons are
presented in this section to demonstrate the residuals in velocity and
position which were obtained before and after compensation of the LM
G&N trajectory. Figures 3-2 through 3-7 present the velocity and position
residuals, respectively, which existed between the uncompensated G&N
and BET trajectories. Figures 3-8 through 3-13 present the residuals
remaining after the LM G&N trajectory had been compensated for errors.
3-8
''
_'
''
',
''
_'
,'
_,
,,
,_
,o
N_
_'_.....
_N
_,__
__
00
00
_C
_,_
_0
b'
__
"_:
o.o
o._0
_._
_:
j,,_,_
Qo
o-
--
__
c_
=_
_EF.
;dE
co
_,_
o_
o:
.o_
oo
_,.......
__
.^
___
U_
....o
Oo
_.,_
__
..,.o
oc::
c"o
.,.........
--X:
0
°,_o_
_._,
_o
_°..
c__
o.c_
oo
o_
__-
,__
_-o
_--
_=
l
:_=_E:
°oi
3-9
3-10
iiiii_i
3-11
3-12.
3-13
3-14
3-15
3-16
3-17
3-18
_-t9
3-20
3-21
Table 3-3 presented below summarizes these comparisons at 600 seconds
(approximately 9 seconds after S-IVB cut-off). '_V"denotes velocity in
feet per second. "P" denotes position in feet. The vectors were compared
in the LM G&N coordinate system.
Table 3-3. State Vector Comparison - CompensatedLM G&N Minus BET, It = 600. 0 seconds)
Uncompensated Compensated
VX (G&N)-VX (BET) 131. Z13 -0. 044
VY (G&N)-VY (BET) -260.148 -0.002
VZ (G&N)-VZ (BET) 257. 367 0. 035
PX (G&N)-PX (BET) 34, 954. 651 -8. 390
PY (G&N)-PY (BET) -64, 879. 780 i6. 6t3
PZ (G&N)-PZ (BET) 63,469. 562 -85. 887
The uncompensated residuals were between one and two orders of
magnitude greater in all axes than those experienced on preceding Apollo
flights. This was true for two reasons. First, the LM IMU was skewed
with respect to the traditional "launch inertial" orientation so that both
the "X" and the "Y" axes were out of the horizontal plane and no axis was
oriented directly crossrange. One effect of this orientation was to make
the "X" and "Y" IMU axes susceptible to substantial correlated misalign-
merits arising from gyro drift errors. Assuming that each drift error
varied randomly from the launch load, it can be seen that an extremely
complicated pattern of super-imposed initial IMU misalignments could
and did arise prior to lift-off. Secondly, one of the IMU error sources
(ADIAX) was deliberately biased to an extreme value via the LGC com-
pensation load, thereby producing "built-in" error. This resulted in an
artificially large ADIAX error, which in turn generated enormous IMU
3 -2Z
misalignments (-3377 arc-seconds in "X" and -1951 arc-seconds in "Y")
in addition to those resulting from the other terms.
All events in this section are related to the time base which defines
time zero (t = 0. 0) as the "instant" at which LM guidance reference
release {GRR) occurred. The following table of launch events {Table 3-4)
is included as a guide to the time relationships existing between LM GRR
and other events of significance in the launch process. The times of these
events are given in the Greenwich mean time (GMT) base.
Table 3-4. Timeline of Launch Events
GMT
Event (hr:min:sec)
S-IVB GRR 22:48:03.039
Range Clock Zero 22:48:08.000
Lift-off ZZ:48:08.000
LM GRR 22:48:08.860
LGC Clock Zero 22:48:08.960
PIPTIME 22:48:I0.870
LM GRR was triggered by the LGC upon detection of an average lift-
off acceleration at or above I. Ig over a half-second sample interval.
From Table 3-4 it can be seen that LM GRR occurred O. 860 seconds after
range clock zero. Thus, range time can be calculated from times in the
LM GRR time base by addition of 0. 860 seconds.
The LM-I flight represented a substantial departure from earlier
missions with regard to the amount of data available for postflight IMU
analysis. In preceding missions, independent trajectory measurements
of reasonable quality were available for several high acceleration flight
phases. In general, usable data have been obtained during boost, during
3 -23
several orbital burn sequences, and during reentry. However, the LM-1
mission necessarily precluded an intact reentry and recover. In addition,
revisions made in the flight profile were such that high quality tracking
data were not available during the burns. As a consequence of this,
determination of IMU performance errors depended entirely upon analysis
of boost phase data. A summary of these errors is presented in Table 3-2.
Most of the performance errors lay well within specified i_ limits. Errors
which exceeded these limits were X-accelerometer misalignment about
Z (MXAZ); Y-accelerometer misalignment about Z (MYAZ), X-gyro input
axis acceleration sensitive drift (ADIAX), Z-gyro input axis acceleration
sensitive drift (ADIAZ), and X-gyro spin axis acceleration sensitive drift
(ADSRAX). The ADIAX and ADIAZ results are of particular interest.
The prelaunch calibrations for these parameters were widely dispersed.
Postflight analysis resulted in estimates of these terms quite consistent
with laboratory calibrations. These facts, coupled with prior flight history
cast some doubt on the validity of preflight tests procedures and results.
As indicated earlier, the quality of tracking data during and after
orbital burns was inadequate to obtain an accurate ESPOD trajectory.
However, a comparison was made between the compensated LM-1 G&N
burn trajectory and an ESPOD state vector at completion of the burn. The
results of this comparison appear in Table 3-9. As can be seen from the
table, the agreement is poor. The difference is believed to be largely
attributable to the ESPOD trajectory for the postburn interval, which is
considered unreliable.
3. 3 ORBIT ANALYSIS
3.3. i Lunar Module Orbital Reconstruction
The lunar module (LM) trajectory was reconstructed using low speed
C-band and low speed S-band radar tracking data and the TRW Orbit
Determination Program (ESPOD). The LM orbital Segment of the flight
begins at LM/S-IVB separation and ends at the ascent propulsion system
(APS) fuel depletion burn. For the purpose of reconstructing a best esti-
mate of the trajectory (BET), the LM orbital phase of the flight was
divided into five segments as follows:
Segment I LM/S-IVB separation to first descent
propulsion system burn (DPS- I) cutoff
3 -24
Segment Z DPS- I engine cutoff to the beginning of
program reader assembly III (PRA Ill)
Segment 3 End of PRA IIIto the end of the first
period (5 hours and 9 minutes GMT)
of reaction control system (RCS)
thrusting following PRA Ill
Segment 4 End of the first period of RCS thrustingfollowing PRA III to the beginning of the
second period (5 hours and 59 minutes
GMT) of RCS thrusting following PRAIII
Seglnent 5 The beginning of the second period ofRCS thrusting following PRA III tobeginning of PRA V
Table 3-5 presents a summary of information pertinent to the recon-
struction of each of the above mentioned segments.
Before the reconstruction of each segment is discussed in detail, a
few assumptions concerning these fits should be stated. First, it is
assumed that all stations are in perfect time synchronization with one
another unless otherwise noted. Second, it is assumed that all data are
time tagged on the receive pulse; thus, the light time correction retards
the time tag of the data. Third, it is assumed that a 0. 107-second timing
bias added to all tracking data accounts for the difference between UTI
and UTC for 2Z-Z3 January 1968.
Information which is too detailed to present in the body of this
report, but nevertheless has a significant influence on the resulting BET,
is presented in Appendix B. The information found in Appendix B is listed
below:
• A summary of radar observations for the lunar
module spacecraft with comments on the use of
each pass of data
• A surn/rtary of the station locations used inESPOD
• A sumn, ary of drag parameter (CdA/gm)values for various phases of the mission
• Arable of radar data weights used in ESPODfor C-band and S-band radar data
3-Z5
3-Z6
The free-flight portion of the trajectory for Segment I (see
Table 3-5) was recortstructed using C-band and S-band radar tracking
data; however, not all of the available data were used in the fit. All the
doppler data were weighted out of the fit, although some of the doppler
data were good, Angular information was also weighted out of the fit
when suspicious residual patterns occurred that corresponded to low
elevation passes. Another reason that the data were weighted out was the
need for better data balance between stations in the southern hemisphere
and stations in the northern hemisphere. See Appendix B for comments
on the use of the available data for this segment.
A drag value c,f 0. 2039 feet2/slug was used in the fit which solved
on the state vector _nd X- and Y-angle biases at TEXS01 and TEXSOZ. A
0. 132-degree X-angle bias and 0. 064-degree Y-angle bias were recovered
for TEXS. The DPS I burn was modeled by the IGS burn model and initial
misalignments in the platform and accelerometer biases were fixed at the
values obtained by analyzing the guidance system.
The trajectory which resulted from a fit using only C-band data was
compared with the BET at epoch. The comparison revealed a total differ-
ence in position of 2;68 feet and a total difference in velocity of 0.54 feet/
second. Also a trajectory which resulted from a fit using onlyS-band data
(RXY and doppler), when compared with the BET at epoch, revealed a total
difference in position of 1017 feet and a total difference in velocity of 0. g9
feet/second. These comparisons indicate that the C-band data and the
S-band data were consistent:
The residual mean and RMS by station and data type are listed in
Table 3-6 for Segr_ents I through 5. All quantities are defined as usual,
and N is the number of data points for each observation type. Residual
plots for this segment can be found in Appendix A.
The trajectory for Segment 2 was reconstructed using C-band and
S-band data. In a manner similiar to the Segment t trajectory recon-
struction, the doppler data and angle data corresponding to low elevation
passes were weighted out of the fit.
3 -27
a. C-band data
P_nEe {ft]
S_tton Rev. Sellm_nZ I Rev_ Segment _ Rev_ Segment _ Rev_ S_JLm_t 4 Rev_ S_llment 5 S_IiOn Rev. Sin|merit t77, 0 M_n
ANTC 4 IZ4.0 _MS_J.0 N _.NTC
_0,0 _Z_. D Me=.ASCC 4 _48, 0 $ _4. 0 RMS
2$, 0 8_. 0 N ._SCC
RMS 0.00_8BDOC z.l _.0 N _DQC Z.t O.01Z_
bZ.0 t,_.0I_t.0 -166,_ -17.0 -IqS.0 _4¢=_
CROC t,_ [ZL.0 _ _,_ _ 2O.O _ _7.0 _MS72.O ]8,¢, t0.0 S_.0 _ CROC L.Z 0 00_47Z. 0
GBIC 4 S0,0 RMS}D, I_ N GB]C
HAWC 1,4 14Z.0 _ _00.0 _MS
ML_C L,_ 7t,0 4 4g,,) RMS 0. 00414b. o ss. ) N t_L._C 2, 3 0. o09b4b 0
.Z_.Q Mesn o. oolipAT_ Z _1.o RMS
7 _ N PATC 2 O. OOJ5_,0_. 0 Mean
TANC _ 92. 0 RMS TANC_q. o N
ts_,o SS.0 -91._ Mei_ -o, o0i_WHSC 4 8b,o > _b.0 _ g. 0 RMS WFL_C t o. oo_4
_l.O _1.o _.o N _1.o
b. S- band. data
S¢_t_on Rev_ _.el_me_¢_ IRev_ _,_nt_ R_ff= Segment _ Rev_ SeJ_men: 4 R_ Segment S Stxt,o_ ]_ev. Se_n_rnt i
-_5, o M¢a_ o, o_,>cACN$ _ qZ.0 RMS ACNS Z 0. UI_
]%O N _,0
CNB$ [ i_.0 RMS CNBS I 0.00_I
C_ I.Z _44.0 ],_ Z,_.0 _ 67.O RMS CR(_ _.Z 0.02_444.O _.0 _.0 N _4.0
GLOS _ _7.0 RMS GLDS _ 0, 00_q
GWMS 4 II_.0 _ Z45.0 RMS GWMS
GYMS _ 4 _4.0 _MS _-_S _ 0 014_
t_4,_, _.0 Mean -0 00_
_S,0 41.0 N _S.0
MILS 4 t_.0 S 4_,0 R_S MILSI_.0 11.0 N
-_9,0 [0S. 0 k_ean -0. 000} !
4S.O ZL.0 N 4_.0
E.OLDOUTFRAME /
Aa_uth 4d,g)
Lev_ Selment t Ray. Segment 3 _ev_ SeSrn*nt 4 Rev_ SeJ[ment 5 _lt4ttt_
0. 004B h(_n
0. 008Z I_MS ANTCJ3. 0 N
-0. O045 -0. 003_ M_n0.0_14 S 0. 0073 Rk4S ASCC
Z$.0 81.0 N
M_nRMS BDOCN
-0. 0061 -o. 0056 0. 005_ Me_
.4 0.00_ 5 0.00Z_ 5 O. OO4O RMS CROC3&.0 tO. 0 _.0 N
• 0. 0047 Meln0. OO64 RMS GBIC
ZT. 0 N
MQan
J, • • 4t- _5. o 46. o N ttAwc-o. ool ?, Meino. ooz9 R_s ML.AC
_5.0 N
MeanRMS PATCN
-0.0650 Mean
5 o. OI Z _ Rh,(S TANC]Ol.O N
o hog_, o. ooo_ P,_eano ,._L 4 o. oo_7 RM5 WHSC
X #,nile(de&)
St_l,on _)Rev_ SeRme_ Z _ev_ S_ Rev. S©_me_t 4 R®v. Se&menl
bS. 0 I_
Me_ CNB5RM_N
-O.0478 -0.0001 Mean CI;C60.0184 _ 0. _tT_ RMS
Z0.0 _3.0 N
0.0_Z7 Meln GLDS
18.0 N
-0.0_h -0.0Zg_ _eln CWM54 _. 01_*, 5 0.0_11 RMS
t_.0 10_.0 N
-0. 01_B 0. 00IT Me_, _¥MS_.4 0.0114 4 0. 0ZZl _MS
0. OOO7 Memn KAW5_. 4 0. 017K RMS
_0. 0 N
-0.0_0& Mein I_ L.S0.0_11 R_4S4.O N
* . "*'i 0.0_4_ Mean TLX_• 1 _ 0. 0_04 RMS
t_.0 N
Table 3-6. 1_esidual Mean and R/VISby Station and Data Typefor Segments 1-5.
Elo_tton (do|)
ov_ _*&r_t f JRav_ Sol;m_ _ Z _ $aimont 3 P,ev.._ $mllm_It 4 _ S*lFn_tI*II_n
-0.00_6 Iql_q¢ (I. 00_2 N
_3.0-0.03O7 -0.0ZZ2 _
4 0. OO41 5 0.0t04 RMS25.0 61.0 N
MW0. 006 t lU*_
_ _ 0.0OS6 N
_a. OOO3 0.0o54 -0. oleo o. otq6 Id I_s*t. 2 Q. 00_ _. 4 o. oo7o _ 0. 006_ 5 o. _040 RMS
7_.0 3S. 0 L0.0 $3.0 NM_
0, 0|09 IUM.q4 0. 0050 bl
30.0
.0. O01S 5 0.01_ _)3.4 0.0_4_
55. O 4_.0 NMun
°O. 00B72,3 0. 006_ N
46. O
0. 0028 l_M.q2 0.00_l N
?.0- 0.0ZO _) M_
5 O. O069101.0
-0. 005Z -0. 004_ -0. OZg? aM_n0.0O49 _ 0. O07? 4 0_ OO44 _M_
_.0 tl.0 _.0
?-^allt [d*II)
Seiment I Rev. Seime"c Z Re v. Sellment 3 Rev_ S*l_lnt • F,ev__ Selma_t
0, O007 0 0tZ? M_0.6O68 _ 0.0tt_ _MS
0 _Z2_ RI._
0,0t26 0.0tt_ 0.0_ k4_nt,Z 0 0_ S 0. OO6O _ O.0tq_ BM$
44.0 _L.0 Sl,0 N
0._t61 _. 0L46 _Qs_RM$O. OO77 4 G. 00_3 N
._ 00_0 °0.0q6q Mun4 0. O_ID 5 0.0_._ RMS
16._ _08.0 N
-0.0484 -0.04_ -0. 046_ M_
2t.0 _._ tL0 N
9._ N
l, _ 0. _,i01 4 n. 00_ RM$_. i_.0 N
3 -29
An attempt was made to fit all the data from LM/S-IVB separation to
the beginning of PRA 2II while modeling the DPS 1 burn. However, the
poor data coverage prior to PRA III resulted in an unsatisfactory fit. Now
the Segment 2 trajectory fit the data prior to PRA III better than the com-
bined fit of Segment I and Segment 2. Therefore, in order not to compro-
mise the initialization of the PRA III burn, the Segment 2 trajectory was
chosen as the BET for this phase of the mission.
A drag value of 0. 2039 feet2/slug was used in the Segment 2 fit which
solved on the state vector. TIEXS03 had an X-angle bias of 0. 148 degree
and a Y-angle bias of 0. 075 degree. These results compare favorably
with the values recovered for TEXS in the Segment 1 fit. The Segment 1
trajectory was compared with the Segment 2 trajectory at DPS i engine
cutoff. The comparison revealed a 2000-foot difference in total position
and a 2.42-foot/second difference in total velocity.
The Segment 2 trajectory was also compared with two other trajec-
tories at epoch. The first trajectory resulted from a C-band data fit; the
second trajectory resulted from an S-band data fit (RXY and doppler). The
comparisons indicate that both the C-band trajectory and the S-band tra-
jectory are within 200 feet in total position and 0. 15 foot/second in total
velocity of the BET. This again indicates that the C-band data and the
S-band data are consistent.
The residual mean and RMS by station and data type for Segment 2
are found in Table 3-6. The residuals for this segment are found in
Appendix A,
The trajectory from the end of PRA III to the beginning of PRA V
was divided into three segments (3, 4, 5) because low-ievel RCS thrusting
occurred during this period. Segment 3 covers the period from the end of
PRA III to 5 hours and 9 minutes GMT; RCS thrusting occurred during
this segment. Segment 4 covers the period from 5 hours and 9 minutes
GMT to 5 hours and 59 minutes GMT; this is a free-flight period.
Segment 5 covers the period from 5 hours and 59 minutes GMT to the
beginning of PRA V; RCS thrusting occurred during this segment.
The trajectory for Segment 3 was reconstructed using all available
C-band and S-band data. Since more than half the available data were
3-31
from TEXS, the TEXS data dominated the fit. Also the maximum ele-
vations for the other stations (GYMS, WHSC, and MLAS) were all less
than 8 degrees.
A drag value of 0.4516 feet2/slug was used in the fit that solved on
the state vector. Table 3-5 presents a summary of information for this
fit.
The residual mean and 1RMS by station and data type for Segment 3
are listed in Table 3-6. Residual plots for this segment can be found in
Appendix A.
The trajectory for Segment 4 was reconstructed using all available
C-band and S-band data. The majority of the data, 271 observations of
the total 380 observations, were observations that had elevations below
10 degrees. Available information indicated that no RCS thrusting
occurred during this interval. Therefore, although the data situation is
not the best, confidence can be placed in the reconstructed trajectory.
The solution vector consisted of the state vector with drag modeled
using a value of 0.4516 feet2/stug. The trajectory for Segment 4 was com-
pared with the trajectory for Segment 3 at 5 hours and 9 minutes. The
total difference in position was 1467 feet, and the total difference in
velocity was 2. 17 feet/second. These differences are a measure of the
effect of the RCS thrusting on the Segment 3 trajectory.
The residual mean and RMS by station and data type for Segment 4
can be found in Table 3-6. The residual plots for this segment can be
found in Appendix A.
The trajectory for Segment 5 was reconstructed using all available
C-band and S-band data. As with Segments 3 and 4, the primary data
problem was the lack of tracking data with elevations above 10 degrees.
Only Guam had tracking data above 10 degrees elevation (maximum ele-
vation was 28 degrees for Guam). RCS thrusting occurred for a period
of about 30 minutes; therefore, the accuracy of the reconstructed tra-
jectory is degraded by these conditions. The solution vector for the fit
was the state vector with drag modeled by a value of 0. 4516 feet2/slug.
3 -32.
The resultant residual patterns (see Appendix A for the residual
plots for this segment} were erratic and verify the fact that thrusting
occurred. Also the Segment 4 trajectory was compared with the
Segment 5 trajectory at 5 hours and 59 minutes GMT. The total difference
in position and the total difference in velocity (5500 feet and 8.07 feet/
second, respectively) are a measure of the effects of RCS thrusting on
the Segment 5 trajectory.
Attempts were made to fit Segments 4 and 5 together using limited
telemetered acceleration information from Carnarvon and Hawaii, but the
lack of telemetry information from Guam prevented a good fit of Segment
4 and Segment 5 data.
The residual mean and RMS by station and data type for Segment 5
can be found in Table 3-6. The residual plots for this segment are given
in Appendix A.
Table 3-7 lists state vectors corresponding to specific events. The
quantities tabulated are defined as follows:
Symbol Definitionof Symbols
LAT Geodetic latitude of the vehicle measured posi-
tive north of the equator (degrees)
LON Longitude of the vehicle measured positive eastof the Greenwich meridian (degrees)
BETA Flight-path angle measured positive downwardfrom the local vertical (degrees)
AZ Azimuth of the velocity vector measured posi-tive east of true North {degrees)
R Magnitude of the position vector (feet)
V Magnitude of the velocity vector (feet/second)
3 -33
Q0
_-_
0_
_O
0
NC
_N
_N
O0
P.-
Cr,
N_
CP
"f_
2"
".-:2..:
N_1
NN
N
¢_P
-I_
0_
••
°•
ook_i_1_-
_o
-_
_I
,_t_
0_
L/3
1
_'_
__
<
__._
_
_"_x+-=
o__
3-34
Data Anomalies and Biases
The following data anomalies were observed on the Apollo 5 flight:
ASCC04 The range residuals exhibited a peakedpattern while the azimuth residuals had a0. 06-degree discontinuity at the maximumelevation of the pass (Appendix A).
CLQC The radar site had a wrong fit for theazimuth and elevation angles.
WHSC02 Large angle residuals substantiated the factthat White Sands tracked on a side lobe.
TANC05 A minus 0. 065-degree bias in azimuth wasobserved during this pass.
The following data biases were observed from Table 3-6:
CROC The average azimuth bias for revolutions1-5 was -0.0049 degree.
GYIkdS The average Y-angle bias for revolutions
2-4 was -0.0466 degree.
GWMS The average X-angle bias for revolutions4-5 was -0. 0295 degree.
HAWS The average Y-angle bias for revolutions
2-4 was -0.0231 degree.
TEXS The average X-angle bias for revolutions1-4 was 0. 1262 degree, and the averageY-angle bias for revolutions 1-4 was0. 0684 degree.
Maneuver Azlalysis
It was not possible to reconstruct the PRA III and PRA V maneuvers
using low-speed C°h,and tracking data and telemetered acceleration infor-
mation in the form of an acceleration burn tape, in IGS ESPOD for the
following reasons:
• The lack: of good C-band data
• ']?he thruster activity following PRA ILl
However, DPS 1 was modeled in the Segment I trajectory by using the
burn tape and value.=: for platform errors that were obtained by analyzing
the guidance system.
3-35
In order to give the reader some idea of the magnitude of the burns,
the following information is tabulated. Table 3-8 lists the maneuver, the
time of initiation of the maneuver (GMT), the source of the information,
the duration of the maneuver in seconds (_t),the component AV's in LM
guidance platform coordinates (Z_Vx, &Vy, _Vz), and the total velocity
(AV). The listed velocities have not been corrected for guidance errors.
3.3.2 Orbital Burn Phases
Normally, the Apollo G&N trajectory (total position and velocity)
estimates during all burns are available on downlink at 2-second intervals.
However, after premature termination of the DPS-I burn, the LGC was
placed in idle mode. In this mode, only the accumulated aecelerometer
counts were available. Using these counts and compensating for the IMU
performance errors determined from boost data, the LM- I G&N trajectory
for PRA III was reconstructed. PRA III was the second descent engine
burn (the first successful descent engine burn, under program reader
assembly control).
The LGC PRA IIItrajectory was initialized on (or made to coincide
with) the ESPOD BET at time (t) = 22191.05 seconds for LM GRR immedi-
ately prior to DPS ignition. In this manner perfect agreement (LM G&N
versus BET) was obtained at the beginning of the comparison interval.
However, the ESPOD BET is discontinuous over the burn periods. It con-
sists of two distinct segments, one terminating at ignition and the other
beginning at shutdown. It was not possible to link these end points reliably
with tracking data taken during the burn. Moreover, the BET sequence
obtained after shutdown covers a period of only 5 minutes and is based on
inadequate data (TEX, with twenty-one data points; WHS, with only seven
data points). A better orbit determination during that period was not
possible because of RCS activity during orbit five (for which there was no
telemetry coverage). Consequently, the postburn BET was completely
independent of the preburn trajectory (from which the initialization vector
was taken) and was of uncertain quality. For this reason, the rather
3-36
D'-
"-0
0"
_,°_ u
I
@@
_N
i
._-_
zzz
al"
_o
"r=
_
Ib*_
bo
•_,._
2
il"3-37
large postburn velocity discrepancies (Table 3-9) between reconstructed
LM G_N and BET are not considered significant.
In like manner, the PRA V burn reconstruction was initialized with
the ESPOD BET at t = 27, 639. 05 seconds, and the trajectory w,as recon-
structed using LGC data and the IMU errors determined from ascent
analysis. Since no useable telemetry data were available after occurence
of the gimbal lock condition, the trajectory reconstruction was terminated
at t = 28, 051. 05 seconds.
Table 3-9. Position and Velocity Comparison -LM- I G&N versus BET/PRA HI
(t = ZZ, 419. 05 seconds)
LM IMU Coordinates
VX (G&N)-VX (BET) -0.39
VY (G&N)-VY(BET) 0.52
VZ (G&N)-VZ (BET) -14. I0
PX (G&N)-PX (BET) -612.00
PY (G&N)-PY (BET) -289.00
PZ (G&N)-PZ (BET) -2048.00
3.4 RTCC TRAJECTORY COMPARISON
The state vectors obtained in real time by the RTCC for the Apollo 5
mission were compared with the Task A-50 best estimate of the trajectory
(BET) at RTCC anchor times from LM/S-IVB separation to HAW05 (prior
to PRA V). The purpose of making these comparisons is to aid the RTCC
in evaluating fit procedures for this and subsequent Apollo Missions.
The state vector comparisons are discussed in this section. Also
included in the discussion is a set of special state vectors comparisons of
3-38
Table 3-10. RTCC Summary of Radar Data for AS-204/LM-I
Anchor Time E B_/kX
Code Batch (day:hr :min:sec I N (de_) A/R
BDAC 06 00:22:58:12 21 28 S
BDQC 08 00:Z2:58:12 21 28 A
REDC 02 00:23:00:24 34 25 R
CYIC 05 00:23:07:48 33 30 R
TANC 09 00:23:27:00 23 12 A
CROC I1 00:23:42:18 42 12 A
CROS 13 00:23:42:48 37 13 A
CNBS 12 00:23:50:18 27 8 A
WHSC 14 01:00:19:18 47 17 A
IPATC |6 01:00:24:36 47 20 R
MLAC 17 01:00:24:36 51 23 A
MILS 18 01:00:26:48 24 23 R
BDQC 19 01:00:28:00 54 51 A
REDC 20 01:00:35:00 32 38 R
BDAS 21 01:00:29:54 32 50 A
REDC 20 01:00:35:00 32 38 R
TANC 23 0i:00:58:48 50 26 A
CROC 22 0i:01:15:06 52 20 A
CROS 24 01:01:16:48 35 20 A
HAWS 26 01:01:40:06 37 11 R
GDSS 25 "01:01:50:24 29 15 A
WHSC 27 01:01:53:36 34 60 R
MLAC 29 0I:01:57:48 53 39 A
BDQC 31 01:02:0t:12 47 12 A
BDAS 35 01:02:02:54 30 12 R
ANTC 33 01:02:03:36 39 7 A
REDC 34 01:02:07:54 18 4 R
PREC 37 01:02:28:06 18 16 R
CROC 39 01:02:48:30 50 44 S
CROC 41 01:02:48:30 50 44 S
3 -39
Table 3- 10. RTCC Summary of Radar Data for AS-204/LM-I (Continued)
Anchor Time EMAX
Code Batch (day:hr :min:sec) N (de_) A/R
CROS 42 01:02:48:30 25 43 A
HAWC 44 01:03:12:42 53 24 A
WTNC 43 01:03:18:27 16 39 R
CLQC 48 01:03:22:29 42 13 R
GYMS 46 01:03:24:12 47 24 R
WHSC 47 01:03:25:30 49 42 A
MLAC 50 01:03:3i:i8 47 19 A
GBIC 5l 01:03:31:24 54 25 A
MILS 52 01:03:33:48 22 17 R
ANTC 53 01:03:35:54 55 43 A
ASCC 54 01:03:49:48 54 14 A
CROC 55 01:04:22:54 6 3 R
CROS 56 01:04:22:54 8 3 R
GWMS 57 01:04:33:18 38 22 A
HAWC 58 01:04:47:12 32 6 R
HAWS 60 01:04:47:18 18 6 R
WTNC 59 01:04:51:37 24 42 R
GYMS 61 01:04:57:18 30 51 R
WHSC 56 01:04:58:36 33 10 R
TEXS 66 01:05:01:00 I I 12 R
TEXS 67 "01:05:02:i2 15 15 R
ASCC 68 01:05:22:54 48 10 R
ASCC 70 01:05:22:54 80 10 S
ACNS 69 01:05:25:18 22 9 A
TANC 72 01:05:40:06 80 33 A
TANC 73 01:05:50:18 28 13 A
CROC 74 01:05:58:00 63 5 A
GWMS 75 01:06:10:48 66 29 A
HAWS 77 01:06:27:42 24 8 R
HAWC 79 01:06:27:48 49 8 A
WTNC 78 01:06:32:29 15 18 R
3 -40
prime interest to the RTCC. As previously noted, a time bias was added
to the time tag of the low speed tracking data to account for the difference
between UT! and UTC. The real-time orbit determination program does
not account for the difference between UT1 and UTC. However, when the
comparisons were made, the BET was adjusted so that the BET and the
RTCC trajectory were using the same time scale (UTC).
Table 3-10 lists in detail the data received and processed by the
RTCC. The :enaximul_n elevation of the pass (Emax), the anchor vector
time (GMT), the number of valid points in each batch (N), and an indi-
cation that the data were either accepted or rejected (A/R) is tabulated.
An "S" in the accept/reject column denotes an single station solution. The
batch number is simply a numbering system used by the RTCC and has no
special significance. The MSC memorandum on the RTCC Mission Data
Summary was the source of Table 3-10
RTCC Comparisons
A summary of comparisons is listed in Table 3-tl. The table lists
the data used in the fit to obtain the RTCC vector, the RTCC batch number,
the RTCC anchor time (GMT), the maximum elevation of the pass (Emax),
the BET segment number, the total difference in position (_R), and the
total difference in velocity (AV).
It can be seen from the summary that good comparisons were
obtained for Segments 1 and Z. The exceptions are the CROC 39, the
CROC 41, and the CROS 42 comparisons. The large total velocity differ-
ence for these three comparisons can be explained by the fact that the
RTCC fits occurred !immediately following DPS I engine cutoff and were
essentially single station fits.
The relatively bad comparisons for Segments 4 and 5 are the result
of low level RCS thrusting which occurred from 5 hours, 1 minute, and
36 seconds GMT to 5 hours and 9 minutes GMT and from 5 hours and
59 minutes GMT to 6 hours and 32 minutes GMT on 23 January. Segments
4 and 5 were defined by these periods of RCS thrusting; consequently, the
effects of the thrusting on the trajectory were minimized. The RTCC,
however, was unaware that thrusting was occurring, and consequently, it
3 -41
tried to fit the data from ASCC 70 to HAWC79 which degraded the result-
ing trajectory.
The bad comparison for TANC73 can be explained by the fact that
only 28 observations were used in this fit (80 observations were used in
the TANC72 fit). The maximum elevation of the data in the TANC73 fit
was 13 degrees compared to a maximum elevation of 33 degrees for the
data in the TANCY2 fit.
Special Comparisons
The summary of special comparisons can be found in Table 3-12.
The vectors are time ordered according to anchor time and the total
difference in position and velocity is listed.
The output of the RTCC Compare Program is listed for each vector
appearing in Tables 3-1_ and 3-12.
The results of the comparison program are given in the following
listing. The definitions of the symbols used are as follows.
Symbol Definition of Symbols for RTCC Comparison
X Components of the position and velocity vectorreferenced to a geocentric, inertial, Cartesian,
Y coordinate system. It is a right handed systemZ where the X-axis lies in the true equatorial plane
in the direction of the Greenwich meridian at
X Oh day of launch, the Z-axis is orthogonal to theY true equatorial plane, and the Y-axis completes
the right-handed system. The units are earthZ radii and earth radii/hour.
SEMI-MAJOR Semi-major axis (feet)
ECCEN Eccentricity of the orbit
INCL Inclination of the orbit plane to the equator
measured positive counter clockwise from theequatorial plane to the orbit plane at the ascend-ing node (degrees)
NODE Right ascension of the ascending node (degrees)
3 -42
Symbol Definitionof Symbols for RTCC Comparison
ARG PERIGEE Argument of perigee measured positive in thedirection of motion from the ascending node
(degree s)
TRUE ANOM True anomaly measured positive in the direction
of motion (degrees)
PERIOD Osculating period of the orbit (minutes)
APOGEE Altitude of apogee above a reference sphere
(nautical mile s)
PERIGEE Altitude of perigee above a reference sphere
(nautical miles)
VEL-MAG Magnitude of the inertialvelocity vector (feet/second)
FLT PATH Flight path angle measured positive downwardfrom the local vertical (degrees)
HEADING Azimuth of the velocity vector measured positive
east of true North (degrees)
DECLIN Declination(degrees)
LONG Longitude of the vehicle measured positive east
of the Greenwich meridian (degrees)
HEIGHT Height of the vehicle above a reference sphere(nautical miles )
Difference between the RTCC and TRW components
DELTA U of the position and velocity vector in a vehicle
DELTA V cerltered, coordinate system where the U-axis isDELTA W collinear with the earth-centered inertial radius
DELTA UDOT vector and is directed outward, the V-axis lies
DELTA VDOT in the orbit plane and is orthogonal to the U-axis,
DELTA WDOT and the W-axis completes the right-handed system.
DELTA POS Magnitude of the difference between the RTCCposition vector and the TRW position vector
DELTA VEI_ Magnitude of the difference between the RTCC
velocity vector and the TRW velocity vector
3 -43
Table 3-!I. RTCC Comparison Summary
EAnchor Time max AR &V
Station Batch (da_:hr:min:sec) (deg) BET {ft) (ft/sec1
CROC 11 22:23:42:18 12. 5 l 1126 0. 88
CROS 13 22:23:42:18 12.5 1 1048 0. 89
CNBS 12 22:23:50:18 8. 1 1 552 0.51
W HSC 14 23:00:19:18 17.2 1 346 0.81
MLAC t7 23:00:24:36 22. 5 1 335 0.77
BDQC 19 23:00:28:00 50.6 1 301 0.67
BDAS 21 23:00:29:54 50.5 1 317 0.60
TANC 23 23:00:58:48 26.0 1 546 0.76
CROC 22 23:01:15:06 20.2 1 394 0.55
CROS 24 23:01:16:48 20.3 i 331 0.33
GDSS 25 23:01:50:24 14.7 1 201 0.28
MLAC 29 23:01:57:48 39.2 l 232 0.22
BDQC 31 23:02:01:12 12.3 1 286 0.19
ANTC 33 23:02:03:36 7.4 1 333 0.17
CROC 39 23:02:48:30 43.7 2 724 3.29
CROC 41 23:02:48:30 43.7 2 723 3.29
CROS 42 23:02:48:30 43.4 2 632 3.59
HAWC 44 23:03:12:42 24. 3 2 844 I. 17
WHSC 47 23:03:25:30 42.4 2 276 0.44
MLAC 50 23:03:31:18 19.3 2 310 0.44
GBIC 51 23:03:31:24 24.6 2 284 0.40
ANTC 53 23:03:35:54 42.7 2 316 0.54
ASCC 54 23:03:49:48 14.4 2 121 0.16
GWMS 57 23:04:33:18 22. 1 2 1013 0. 75
ASCC 70 23:05:22:54 9. 5 4 2585 1. 15
ACNS 69 23:05:25:18 9.7 4 1778 4. 0t
TANC 72 23:05:40:06 33.4 4 1266 0.91
TANC 73 23:05:50:18 33.4 4 811t 23. 01
CROC 74 23:05:58:00 5. 0 4 2666 6. 24
GWMS 75 23:06:10:48 28. 5 5 2057 2. 09
HAWC 79 23:06:27:48 8. 5 5 1600 2. 44
3 -44
Table 3..12. RTCC Comparison Summary for Special Vectors
Anchor Time zKR AV
Vector Description (day:hr :min:se c) BET (ft) (ft/sec)
High speed radar vectorfollowing the separat!Lonmaneuver 22:23:44:00 1 661 138. 59
Best RTCC vector priorto DPS t 23:02:03:36 1 333 O.17
High speed vector
following DPS I Z3:02:48:34 2 6, 870 18.47
Best RTCC vector prior
toPRA 3 23:04:33:18 2 I,013 0.75
High speed vector from
WHSC following PRA 3 23:05:02:13. I 3 2, 640 49. 61
Vector used to build
LGC Navigation update
prior to PRA 5* 23:05:09:29 4 27, 918 65. 88
Best RTCC vector p:_iorto PRA 5 23:06:27:48 5 i,600 2.44
High speed vector from WHSC prior to PRA 5 (vector used to build LGCnavigation update )
3 -45
t.)
I,.-k-
I.-.i
II
Jr
IJl_
lJ
U31I-
l_2111
I;
21I'-
LT}
IMO
l:J
I-r_l_
Oum
tO_C
l_j
_.
I_ID
O0
_,,-*
_I"P
-),-
I_0"
F"I
]1.e
Um
llmZ
I_(C
I0"r
L_
O,
(.
_f'l-t_I.L
EE
Lr_1
l_
I_
-C
rrl
(::/
ell¢1_¢_
IC
)_.,
U.,
I_I_.,
t'_4"
rMIM
II
I--
OL
Irll_
_*I%1{I:
l_
il_l
_21
_[•
4_,.-.I
.,.,+,
,l_
p",er,
r_++
:Z:
rrsf,m
-r""
LL
•l_
lJI
I.,II_
<_..+
.,_•
,,.fr_+
.-J'."+
0+f''-
,,'-+,.,-+
+_
3T_..
PMIE
)'Z
':_
t..)Z
,,DoI:
."-{.,..+
w,_<
P,_
;_...
_.I'M
_,3l-..,s
,,N
r_z"
3-46
iI
I
Z_
_
o_
Z
Z_
_
__
O0
_I
_Z
_O_
o__
_;_
_I
li•
3-47
P
'I
II
-,__
_j_
....
__
__
_>
*e
==
,_==
--
,_
_
3-48
!I
I
Z_
__
_I
_N
__
__
__
0_
r.
egJg_gg
oe_I
_
IIU
Z
3-49
II
I
_Z
Z_
_Z
__
C.
0_
0_
_C
__
__.'_
3-50
I.Jal_I_
C[
IX).-
I--I.-
II
II_r_
U4J
_J
I_I
IU
31I--
l.J31t-t.J
3I--
i--P
-N
O_
P"
IM_
(_.L
)-•
rw.IP
.lr_-
,1'I_
i.-i._
<rC
tr.
Ii
_•
•,
:E•
•*
i.u
"r,r_
_-_
cr
X*
,,Z
•*
*_
**
*Z
L_.
t.;.J()'_"
*"4"4¢:)_-4
.-4_,
D.C
..
t_C,
,t,_
%.
.
_.._u
_t--
-_,
w
II)t,_
LU
P
"7)£'.
Z0
0r'_
R'l
N.-I
<DU
'.L
_I--
•
3-51
_.).-ac
*,'c_
i_I--
II
IC
a_JI..)
I.Jt,
t_P-
I__.
_--_
Of.
I--_ix
I--_
c'),,I).4"
t_I--
,,1-u"
_1"e:)
_r_
f_O
.I--
,_r-
r__
=F.c_
0_,-_
f_o
_,,t
e"r_j
_,eeP
,,t"00"
,,1",t"_.
1_o
n_r
-e_.
II
_j
••
:_•
•J
l.u
ZI_
i.,
f,.a
OK
.e'l_
_IX
"(.._
r_OG
_0O
_o
r.,_._,:>*
•
,_1C
'(_
e,"f_J
I_0Z
h-
h-
r..j<1_
u.
-r_
•Z
•*
'c_
••
•zu
a
I,__.a
Ca
(.a
•.a_O
c_r_
,0,-_
h-O
'_c[._1
,,1i--
f_..,1.-
t_r._,,r_CC
O;)r_
_r__0
0_
"-_
UJ
••
•_
l--
_,el"1.r
,41",_1'•
I,_1,1.1_,-_,-._
I_._
CL
__._
I_,_'_1.:_
__'_
3-52
II
I
_{1
QIQ
_•
X
3-53
I
3-54
+U
+0C
+,l_l
tJ+.)
0C
b_.2
LD
qJ_
I.JL
2'-,U
J_"
aeI
I--K_
I"_w
O0"
I;:,
,dled
l_C
_C;)I*-
<DI,-.-+N
0_
31*
lP
'-t'-.
_P
"0
m_JllO
.4",,1
..
,,..,,,.,..
i,,-
•L
,7,,C)
I,I.I(2+
,,..IIO+
_,..I
,',r"f_
l-E
)(.*
I..i....i
IJ._"
_J"N_J
*--_1C
:*,_(.5
(D
75'gg
.....I,-
L-_E
)N
rMO
+.)_
•l[e.i
.,.++._
U.
u_uJ
_'_"x
..+,41"N
I_-0_
_.IP
I,-I.-
I--_1}
_,,+10
_)II_P
,-+-+
[JO
e
)(I'M
l_JU
Je-,_N
O,=J
4E_.e-.4(:3
U_II.
•d'_"
P'
4"_I"
__.=
).4_,,d
DOI"-
l,.-n"+
_'+E
)P"-
P'-
C)
U.+
,_,,,D
O,,m
l,,,.,I
Il
IN
_J{::::
mIP,,I
II
_:O
..';-
'I
P0
C>
_J
-;
_:)Io
¢_ar.-
,.ooD
i._m
IDf.-.
t._m
._lrI_
2'..-+
r_.I
O_
.4".41"
I.IJ_'M
Ic_
ZC
_,-*
C',
Z_l--
_;
i_41_
i***Im.
.•
UJ
•*
*ILl
*•
*Q
__
)--
0.O
¢+
,_
ffol_I
0.0+
+I".-
P"-I
I,,-
(31,,-"J
I,__
I,I.
C)
I;)Z
.JZ
Z1_',,4.'_
Zi._
00
0_--
O_u
OO
o.j
,u
._/(.,
a.5r
LIP
Il_l__
LIJ
•*
•I.
•*
*.._
..
._.)
r_m
_1
¢_e-*
*.*'_r--
u__1
_'_IM
I%I
eo0.**
ua
®,m
+,,..
,_N
oom,,o
'<•
._+_
-"%
_tP_4_
I_linZ
II_'P
"I_
_lr,_1"Q
II_
I_"O
_Z
,..INI=ll,.-
_"l
%C
lI:
,,*,,.4
U.IU.I,-_,-*
O.
_I_
0::)
INN
0t_l
_+"
I_¢[i,.*
_,<D
,O;1.
u'lN
NI10_
Iu
Z¢_4.)
l-I_
**
LL
.I_
L_t*_
4["
??
,,•
3-55
_lPl,-
I-I
II
f_(_
P,.
Or.1=
-_dY
I=-
==
"IK
k..._
Z0"0"
,a=p..l'..O
,U
_",D
...__
_atI
_--•
••
_C•
••
u,a
,=l;l;
u_u
_
•I--P
_P"-
u_r,.:._.._oe,_
_l*_l_
(_N_
l_I_
U_
¢'_(_1_
__
ff'__'_
,.._
•_.
U'_
Uh
_.J
,C
£",.I
2£*
*Z
**
*_
*•
*Z
",
r_¢."
_r_
_DO
,O
_P
,..I_.G
_.._
•c
_L)
V-
•J,)
Z
G.
_•
O'
0I,,-
L,U
**
*G
.*
*•
*.a•
**
I,.__
_'_¢_
¢"j
*•
_J
N_d
O"
O"
I
II
_Z
0
o',
NN
3-56
I..-I.-
)-!
¢I
cC
_1,
I--I1_
t+n_,_
,t_as
,4P,,t
O"
I.-
•t'.+
r+I.I.+I'_
_'___...+
l,_O
__,
(.,.,.,j
II
_*
**
_[_*
*•
t.L+
2;I,-,-+,_
a"0
J-I-,-
*'_,,,IP
I.£.i,4PI"-
l+"J
0"_.+,P..,
r_.+,...+
iJJ_
,=.+
.-4U
,JOD
0t"
__
¢1.,"
).,..:!+
**
O.
_(["
(..._
_I'%
_..J
_¢_
_-_{
__
_(t_
1__
__
UIJ
#"L
'+s('_
P"
+4"I'*,.+
+_,_0
wi"_
+'__
¢I:+¢0<
P',,D
.,-.+Z
..,-+I_
_.+_
.
X_T
,4"U
__0
P'-
C,
..tP-"
P'-
C_,_
"t*
*Z
**
*_
**
•Z
U.
_".-Jo
I_,
+",
IJI_
t-¢C
M
+'+
mm
o'r+
",.-,m
m,,-",'-*c
>
i','+_
I.,_I,I_
I._0',
P_,,,,_
+."+
,*,..+I_t_i
P'-I_
I-.-_._
I.I,J
0'__._
OJ
."+::t"
I"-P'-
._.._I._
I[,*.,,,p,.-
,__.+
0':_
Z'_[
_-,C
i__:_
t%l
14.t_J
'I+-
_Z
C:
•,-+_.
4_P',,.l,fs
P+JI*'+
,,,,,,_*..,,*I,_
,_r_i_.-
UL
)_'_
_J.pLU
C_
•*
*_'-_0
*'_',_e+
ll''+
mr_--"
I.L.
r",
_..4t._
I.I.J*--*t_
I_n
__1"
IJ'+xU
_I_J
**
*L
lUU
'_4r
*o:
_"I*.-
ud
0][I-.-
e__,
*IJ_
L_._._
r--,N
I
3-57
l=J
k,,.1"-+
I,'+
I,_I.)311:
l,,_Ik.-l,._3k'-
1,_llt.llk+
I.,-0_I[I.ll[
1,..I[¢[
4P_l,=
.aO(_
OD
P_-QO
r+l+=.,,(P
+k,-
4Pl_(%
t...+IP,-P,,J,II_
,...,r_D("_
_,,,,-1_t..+
*,..,_+
++e,+
l'4_I,,,-I_+
,0,*_21
++
ZI00_
,II*+..,,.4p,P,,+
l_S.'xl'n.,.,_£
I
lI
_,r,
••
'_•
••
Ul
_+_
_,,,IP
,_(_+
,...+_++
tr"-
'.r..,.,+
k...l'_
l'_I
0+10
el.'r_.
,--I0..
_.+
•l=-
O"
O"
__,0,4',41'
C,
o_oo
_.,*.'+
14.)-).-
_r_
""*_+
+l",l
¢I_(.5
4"+
,,DI%
1,I[
I*"-P"-
n,I_
_p_
Z0"
O"
+_
,at
11"*
•,_+
I'%1,,,-+
_-
,..,,Iu"_l,l"x,
_,,=J
D_
oDo_
¢0¢I"
Ii,IJ
..--up,-._
r-0
_O_C
I_4
k.-
I.--(I
,._0'_
I_,0+
__IP
0u_
__:_
(._C
:<r,,t
,.ta;
_'Z
m,O
,.-+_)
*
Xo
0.i.i.i
.--<rr_
•-*_
,__fJ
.t._
,_pt_
p_l+
"_,_:_t,
'<...)0+;<
_)'=
"I,=
-+
r_C
,,"X,__..,I._
i.r_,..+
U.+
<+'.I+
'+,,._
._+
I.L.
(...,+
._C
'_t,+
J.,,.>
I_(p
_:_
:"
_L_-+
__+_,.+
_,_I"+
I_,.J
_PL
'_C
_C
_+r_
L"_
r,.,-•-
,,-,.-,
:"*"=*I,,.,-P'-
i.l.'
([.
•.v
...+...
_¢t.
_r_
++-
_Z:P
'.P
,.:_
IJ_
__,,m
o.._
_u
oe.-+o+c_o
"_-P
._,,.um
*_
o_
,_*.4
O_
_._Z
P_
f_"_
U-_"+
.4r_
_zf_
f_.
7+_
¢I__
¢I,,,_
._
_.'__
__P
-_•
_.
3-58
t,d,
I,-a_.
_l--ac
re_
QC
I#
I
u,J
__
_3_
__
t-..
(kC
dt'M
t'_C
It,_
tl_I,rt
C,,_
_cr
__'_
17'0'I
u_It
IL,
k...<D
IE,
0".er_
o'_.._
.0t'_
_C"
_._
I_
__
_"'__
__
_I_
Xp
-I_
___.__.i_._
_I_'_'_,-
Q._
_
"r
.,.,
=r
,_,,
r'_,
,,
Zu
_,
I-"_",
I,-_,-_1
_"..,,
__m
_,.4.4r
I_"_
_r.
Ce_
Ua
t,_U
_U
.-
,,_ii
Z
t...-..._
c.t..t.L.u
at.e,t'_.,d
-¢c.._
..tO
""_
_"F
"-tJu
.:
0.0._
_kakl_,,I_'
<p,_
&_,_O'i_.-_m
.-¢
Ck
CO
Ct
t-'_'t
t.,--,T
U.Jk-
•
_.._
_,.
.._,-.,
_•••
_•.•
..,•
••
_..,,",_,-
II
_JZ
C_
UJU._
C,
.•
Um
Le..,_
t'_,,,.¢ce,,,r"'-_
_C_
_Z
"__.
I_"I_"
la.la_
e_tNO
D_
L_.
Z
3-59
I,_31
,ILI,,.-
a.m
,o_
I,-,.I-,.
I,-.I
II
I%1
I_aOO
"+t'_
e"rJCl_
4'%J
I',.+O
pes,_"le
_+
••
1_._
OD
n-e-.+
+...+c"
I--f.-J
,_,.2I,_.JI,P
,('+'+
_fs,JL
,P_P
"-I_
,,,.,J
Z¢_
QC
_
_=ri.L
Ji.i_
d"
0"0_,C
_,'_:u_
,,_.'-'
i.-
t-'._
+,_O_
I.LP
'-O
-"L'+
,,D+._XO
",_,,
l.k)"_'
"_"_
+"
"_Pp"+
<'_(._
",lrP
',Ie+.l<:
elle%
ll'_4_.P
"P"
OZ
_O
_'
''_
I'L-I
I(._
+'-
L_
I._<'"
'_')C
,--+...--1
IPL
n0
N_
O(_+
f_li
C_
t,,I-'-
P"
O"
I'_',_+
_,-._4P
_',4"CC
_t"
_'_
"r•
._
,•
+,
r..+•
.•
_
I--C
L",
I,--P
--+
.),_
o_+
,_,..+_1-(.,
I1".,._,31
t_,-_C
+O"
e+_
4.,.._,.,,I',,,I"t...+m
e,.-'0
eL__t
__"
'_',Z
+,J2
+_.
•_I
,,,0I,P,
_t,+,,,_p
.--+t_"r_l
t'_
I._.._
+-,_
'4++
++
+',D,h.
r,,alJ'_
I-.-+
d+I,_..,_)
_----
+0
tJZ
_
Cl_
0_"
Z("+
I._L_
e_J,.,-+.,,,+I'_
e"_,_1"
I",-_.
_.C
r_
_qr
M_
ZI
i_i_
t"+"+:_4.3
IO
,O
"I_
Z,.I
C,I.-
P-
f'.,lm
__<
'4"'4'
u.J,..-+
',0,aO
L_
_P",'I"+
+.:'
,.,.a_,f
'++1"+
,.)_U
i__,,._
_--4t,,,.)
_IJe,.+_4PsJ
_1:5r
IIP+I_
I_1•
•l
I,I.JI.P.I/_
•O
C_"
t",-_l_
3-60
ItJI,):1+
{K.
I--it
_i_
4,-I.-
1-|
6I
C:
C:;,_O
,_.L__(I_
_'_'_
o-
C-
,q
t--
k-
f_U
"rr_
,,t....
_+.,t
P'-
C_1"
,',"+
,'__.,IO
";_
I'.--,o
_.__,
II
_.,_L)I
{",._
i,-.-
_U
3N
g{,"
Z_
'
I_-I
1[_,(c.
U.)
••
.II.
.%
UU
_!
I_.t.l_
_•
",.J
.._,..i0"{7
O.
3-6_
•it--
Ei
-moc
it-t-;
I--I
t!
_]g
t.--A
..)3
I'-',k,._3
;"-,L
LJ
t,lap
"C
g'Y
tt"'W
_'_"t"-
I:_e,f
C'"
t"-',L
'_If"C
JP
"-_
i,Jr__D,-.,
)r--
_,lr',,I
_c.--_
r",0"
"r,<1.r,...
r,r_rr_
C_
C_
;_O
"u
-_t_
O"
O_,
.,..*<r_,4
C"
r
_P
"f"
",,.
tL
_
,,to
-.1"I_
,.tm
_"
[,-l-
u-,ur..
C'_
(_r._
0C
.0"-
_C
_,.
I--_
0"_0
qf"D
:.P
'-<r
M-.
__"
,J
CL
C.'
u"_('_l
00"L
h.,It
.,fC
')_
re"C
),,_,1_"
G.
_LI:
L_O
_k,-
t,U•
••
@.
*•
•,.J
•*
•t._
_"
_
t_u_
_LiN
-r'_
t.iJ
_,_:_
,r,n_Z
ge--co,
o_
I_o
..oZ
.._r__-,o
3-6Z
++
3
I--0_.
I_t,-.-
Eat+
_-
II
I
•_
,+0I.P
,<
+_.O
tjI"r.Iq
,JC_,
_"_-,
i,.-4
_<
[I_
I_-C
.t,._
PP
,L+
+
•I'--
C3
(.-'U
.,0"
_+_r.,.._
_<._0C
"I"+
__
t'_O
"+
+.,LJ0'+
'_"u"
,,_"I"
,GG
"r_J
U.._
_wIE
s_,
_"I".-
+4PI"-_
,4rL
_O
"+...
I_LP
--f'--
I¢Z
_¢JDI._LL
_t_l
+,t
U"
P__"
31+-.+
,...+1,._
•
•+
++
+_
_I
L-
_,.,+,..,,+
+..+
oo_o...,,__+
-,o-,-+
,.+..
,,,,+
++
,.++
,,.,+_,
+o
._+,+;
C'_,
r,
Z
.__..._
p.-(,_uJ
.,_P_+
f'_P'_I
_I---
++,
ILl-,+
•
I-,4_
12..I
I1.3
ZC
+
ot",
Z.-_
,_r_
,cP
c,_+
_r--
aDI,.-"
>+
+,+
.-,_,.:,.,,.+
.+_...,_+
..,0"_<
,..®+
__
,.,"+_;+
•+
+_-"
oo
_B
•I
!
3-63
ag:I.-
_ee
c[
II
I
e_
_,r•
•_
0_r
,,,-__J
f'-I"-
c',
C_..
C-
r"P
--:_
_.,#_-f"-
I"-F
-
•'2..'.
'i'i,r_
_lI
r-,r.i
t__C
I_)._.
li.I,--
>
C..
-,_
,U..
..11-
..,J_;'_
t._(.._U
'@.N
,'_L
LJ.,,__1"_v"
Q,.
',,ID',,k",,.;"_I.--,0
_.u_I.--•
•._.2-Z
>,(
dZ
c.,J,
_,,
_.9l
.,1"q"
_t"<
_"
_.,.-',14
,,.,__.
Il
L__
ZC.
U')
_L
.LJ
I','-
>
r
c%_.
_x
._D,,o
i.La
__L_.,o
o£
_;er'lk..,
.,_J,,,ID.aD
..,-_u
,,,;cuI
_
3-64
if.li=-
li_'
II
II
I
I_I-I
_II"
_J31"
I_"!
I--
.=i
_,il'xli%i
0P
.,-_I0
I__'-
O"
0O
"_I
•
I_:'i'
I._r...l_p
¢_
I.i.,_lD
_D.
,..l
•K
__
_".C
__
_e-_
i_C
"O
,O
"i.Li
,.O._"
rT_
,q
"jj
='..
I-"rl
Z.
(-"
•-i,-III
M7
qp
qi_"
C_'
_C
)p
-+i_,
)
Z_°;
7._=
.=.=
._"'
CD
'_I_
_4',I,p_
'-,,.I,>
_.'__l
,._I,,.:
i4_I
t.i-l,i.l
.,.41,,.)U
.J,-i*-'i_=
,.iC
f..2itl"
"•
_-:_U'_
•IX
t"_i,l.t
f"_i._.l
I,=-",_.
_,.f_.
I'i+l#'_
ll'_'f'_,i
_..,aOI
3-65
!I
I
I_JL)
3I--
U3
_"_.)
3_"
¢.
i
:(3t--
r,_I_
la.(3
3-66
I--e¢
I!
I
Zo
f)t.,
bk
r.
-I1.
_LI
3_,..T
C_l_,
G"
•-_¢J_t',
_"I_-
:_
I;.a
Z
U3
tJ.._
••
•r'_
__J
__Iur_
_---_
_-_
I%11.r_
_,_
I_1_L
l._m=
l_I_"
__
_T.2
.,a_fL_Dt_
U.I._
I_
,.3
3-67
I,j
1--I,.,,-
I-I
II
"T
I'--0
0I
,,-i_
I
_c_
_._
-.:..
-_
0r-_
r--,'
0g>
p,
r,_I-
_I'u'
rr,r-_..4
.4"g
,.-w
I.I-C_
_r'-
r--L
_C
C..,.,_u
,_'
LL
:_'Il
L-
_,
_M
[;,,4'
r_i_
,%,.3
¢.,.f:..(.
a:
C_
•7
l-u
,I---
Ii,I
**
C._
*•
i.,.J
**
•_
E_
C
L.:
2"_"
_v"i.P
_I-,-
C.
u..,
L.)
1.__L
C*
**
_1._,,.,.,iI.F
,rr
,0,)
I:["_,
I.*.C
_.|
*,"r,
LL"
I.r_,""__
(.rIX
".._
_1:
C._
,X.
L..'_
"_*
E_
•
,.,_
k-if**
--*
LL
U.
L_
-68
I-o
r,.C
I[I,-
I_LC
C_.
II
D
T_
#-r-
•I
,,",
,,_"t"
U,.,U
_
i_U
¢,/|
r
I--_,t
U_,
__._
I__r_
O'
U_
_'*(_"
,-_,--_
_]1_
C"
I..L_'_
,,1".t.._
l_,_D
:"_L
._,4_
,4De'.
_f"-
r.-_'
_--I-.,
,,tL
L'
C_
L_
._
rc_m
_,_O
"L
_ir
IP
l
",Jr,.:)
:-_:It
U._
=:-
,,-,r,'-,_',"_,o
,':).4"_o
__=.
_,,.*.
_,_.
NU
'_"_
)_,-"'),-,
U.I
"--1"-
P'-
*'e"_,t
_f".,_
-.J,O
,O,-'_
UJL
L:
_.._
e.,_•-.4_
IJ,J,,-_0"0"
O_':I'U
*,IL_
L_
•_,
•U
.._'_U'_
•_..____...
t,,"-L._J
3-69
UK_
KE
I!
!
N_
__N
O_
0
----z...
_...z_
ZN
_I
N_O
_Z
_Z
_
m_
O0
•
--_
__0_
_o--
O_
•
__
__
_II
_Z
O_
__
_
3-70
!I
I
0_N
_JJg
JJJ
_0oO
0
__
N_O
_O
__
_
°°
_"'""°"°__ii
_m
oo
Z
0O
o_
_Q
•_
OC
,_
_Z
3-7i
II
I_o
U_
U
0O
_
_N
NO
NN
O
=---
z,,._*.,
z_
0
<----
__o
_o
_o
o
E_
UII
U
O_
Z
_O0
__
Z
II0
_•
3-72
U31
I!
I
•0
_I_
_N
_0_
_
_O
UII
U
C)
OZ
3-73
II
I
O0
_0
_0
_•
II
_I
_I
0
NN
Z
_ZII
•0_
_0
_0_
__
II
_Z
0
3-74
II
I
Z_
O0OC
)_0
__00
0C)
Z_
_I
00_
_Z_mO
_
(3
Z_0
00(3
_
IIU
Z
__N
__
_•
_*
3-75
II
I
OO
_
Z_
O0**
Z***_***
Z_
zm
m*
__o
ZN
@N
Z_
U
Z
II_
Z
3-76
I.;,31
o+
I+,,.'+o+
.O
__.-
II
!
¢+_J
,,.4O
"
.,,,41..4+._
_-4.-+..-I
.=_
cP,..-<
l+J._.
),-,_.,.,,__l,¢_l'+
's,NI.'_,+
.,IC,,,._
L_L
L+IJ._
+"
"_.<
,,+I
r_l`+
..+)
iCl..+
+_+
I=..i..,.
l._l_+
,__+
_¢':
,,,i0P,_
I.i,.,_..,.P+.l
l,,La
_+,t+
_+•
••
+"
••
•2
I.I.+
l,.laP
+,P
-a
II
O_
Zl.J.l
I.I.,._
0r'*I+
'-"",_
"C-+I"+
-O"
N+_
•
•I--.-
_,._.
+'+
_P+
_P'+,_0
l_J
<Z"et"
II''+
+I-"
_JC
."Z
l,i,.,+
_.,3"
I,_0"I_N
,_Ir'.i
,+_
k-,-,,ID
_",_
+_
I._0"
"=.J_"Z
_"P
_P,If'
Zl.=
J["
{'I,_
t.=_Y
_O
__i_
.=_Ip
<_
M.,-4
LL.._i
Or"
++
',,"C
u,...,+
...>
(_t_+
•j
_I"IJ_
I,__
Ipl_i
_iP''*
.,.__+
%,,ii,*
I,=,L,
)
•o,,.+
+,,,-,o
t_,-,o,-.-_
co-_,.._C
-"+
'-'_'+
<
,,,?+
-+
<!
e'_•
3-77
II
I,.._
.__,
_.)
i_,I.,3311"
t.)3
)"_._
3t-"
,,...,<
30'(,._
_<
1"r_
_I
-r.-+
_-_rr,
IO
0
Z__c+
_+
_+
_+
__
>"
••
•_
_f"-
¢_,,JP
'-P
-_.'
,.J
i_:(o
o,,o,
0"I
_,CI-"t_
_•
xf_
r_I_J
c+I',J
,--+._
rslrq
+-.+LI+
+/.
I
••
Z•
•+
r"+
••
Z_.
C+
+-l._
_43r_I.-
r_,-_
P--
+..+,_.:I_p-+
,JI'+
--_]1;a_-
,-_¢0
,0tL
,r,-.
,d:,,_
,,,:,0,
u'_rn
z_.c'
t_Z
It',q
_*I
.--I_ID
U_U
,.U
"_X
'0"
ZO
"a,.
-_
I,
,Z
,L.__,,-
•air
,.,.3L,_
4"_r"
t_<r
J_
u.,
,,.,,_
..jO
__r
t.OU
J-,1"
,4t"_'.L
t._er_,.._,,_.
__
")<
_I.-
<t
U-
t-*
..I_
_")-
,._,-.*
Z_J
C_
r'
C_
;,._;'_tl_
__1"-,t
',.,J
ILt,
...l+J
II
UZ
C:
,..+_...-
LU
*.._r'.-
f"-,'v
_rM
._r_,u.J
,•
•u._
u_u-_
,_e.,
i,.-M
J
U_--
I.-_*
*tL
.14-
,,,o
oG
-*
3-78
I.)=I
llt_l-
cl:01:
_:
__3
4..:+.3
',..3_
+;
I_II+
I_i-
_"_
_-o:
'_I-
I__:
!L_+*IDI._
i('_k-
C+
PPL
_,+
+,._
C+
./"0
I_•
C_.'+
•r,_+
.op
+.iO
ur"
__
U'
U•
"043
O"
P.
u'_a0
_,4I_
£,_O
sO
.C
'++
'n,.C
._I"
I_U
'__
31t+
P'4t_
Z_
0:),_3
"t"l""
(._f"
i_
_i+•
•L
_0
14"X"
IsJ_4_
._I--
++
,.
"r•
•.
uu
k"-P
PP
r".-.,+
.-4i
_3.--_
...lP
_JI'_+
....,-+Z
V>
_C
+
_r+-
P--I
_..o
I_k.
.2"_.
',ltmC
r.-_
mI_
_;r"-
_-_I--
,,0._E
_r'_
.._.,-_
I.,o4',_
2_k-.k-
++
2+"
••
C+
.•
._
LiJ
-+_+
+_+
++
+=+
:__=
o+
_+
L3
3_
)--"
>,.-.
4+
+U
"(_:
LL
,_.
l['P
-+
++_
_tI-
q.-+
_I_C
++
i_I%
+=
e+<
_P+_+
Pm
_u+
+,+
u+_
m+
cZ
<.
=m
+,.J
_P_I
+(_
LUtW
I_L
U+
_+f-
__+
<_
i_e
I_+I
*
==
7+=,
_'_.'-.*+o._.+.+.
+-_._*.
'+***'++
-_+"+
l=.-
u_c)
Zi._
i_-_.
'+P
;0",+
"<
_+P"-
cL'_t--
_.
+_
-+<
,o
++
,_
+_
_+_'=
X:
'.ID
_+.IX
)p-
_+_+
_I.0
I_I_
_0
Ctt
_I_+
.I_
+.3
kU
_LI.I
_[I+
.l*J
_+
+D+
+t+
+:7
I+
+_=
+=
4P.t
--_f
*<<
'_'
+_.
_,_._
Z_J
f',.t_+
I--_.
_t._
•O
+C
_l_lJJ,-+
,,.+_.
aO_
+"3>
I%IP_I
.__
_="
C'+:£
I--P
_,-
•U
-U
.¢._
,,,N
E_.
3-79
¢11._.IQ
,_
O[
1"-1"
1--I
II
,_(.J
_IK#--
,t_3
I","
c'I...-cry.o3
_.4t_
rNl
r__
"r'I,.-
••
•3E
•,,,
•u
.;
....J_
{X"
LI--
k.L_
kL
O'
C£
00_C
,0
_U
"I-_1,...
O'C_
I_'_
0
._-.
__,-_,
_%_.
_.,_..
3-80
U
0_
t_
00C,O
Z•
3-8_
U
II
I_
U_
NNO0
O_N_
_0_
ee__tee
Z__0
O0
e.e*
00
_u
_u_
_1
I
o0
Oo
Z
3-SZ
I,-Ir
k.-t.--
)'-"¢
!!
t._f
!t.J
3)"-
(,.,_J
I...-(.._
3)"
QO
U_
C$,,.-
_..t_
_-.-_tr_.4'
P.-rr
,_I--
C'_
r_.N
.,,t'X
_:r_
e,',0".
O-
C_
,'f"4"
_,,,_0['_,..I"
_-_..,,
U',
,4"k...4-
p-rr.
It"0
"Tt_
h-
-",'_I
t_U
",!
Z_
c_c,
(t_2
u.,u
._
"J_.O
_o
,_x;0
_;O
_en
_-
k-
U-
U.JU
.,
•.
Z•
•*
C::
**
*2"
U_
1.3_
_.r)
t-Z
.Jr-
_0¢_J
{._l-
P-
C)
U.J
_r_
..t"_"
)--r<
talk--•
I-"t_
U_
UJ
_ri_.
_,x
0_U
.i_P
-I"_
Io
_O
_O
_¢;
,..i_O
_t_
i.uu
J.,_
_.,,i,..._
_"_,_
*,._'_
_1i._
_"T
%l0_1
0"__'
IU
,.Z
3-83
APPENDIX A
TRACKER RESIDUAL PLOTS
This appendix contains plots of the range, azimuth, and elevation
residuals to the reconstructed trajectory for the C-band radar data and
plots of the range, X-angle, Y-angle, and doppler residuals to the recon-
structed trajectory for the S-band radar data for the Apollo 5 mission.
The trajectory was reconstructed using low speed C-band and S-band
tracking data.
Each plot is identified by the name of the station, the revolution, the
type of data, and the BET segment which generated the residuals. Near
the bottom of each plo'_ is listed representative spacecraft elevations above
the local, station-centered, horizontal plane. This will help the reader to
visualize the geometry of the pass. The time scale is given in minutes
from 0 hour (GMT) of the day of epoch. The time scale may be correlated
with the elapsed time :[rom range zero by associating the first data point
with the time listed near the top of each plot.
Below each plot comments will be made on such things as geometry
of the pass, data quality, program model errors, etc. , if applicable.
A-!
APPENDIX A
CONTENTS
Page
A-I Revolution I, Carnarvon: RAE (Segment I BET) ....... A-7
A-2 Revolution i, Carnarvon: Doppler (Segment I BET) ..... A-8
A-3 Revolution i, Canberra: IIXY (Segment I BET) ........ A-9
A-4 Revolution I, Canberra: Doppler (Segment i BET) ...... A-10
A-5 Revolution i, White Sands: R.AE (Segment I BET) ...... A-ll
A-6 Revolution I, Texas: RXY (Segment l BET) .......... A-12
A-7 Revolution I, Texas: Doppler (Segment 1 BET) ........ A-13
A-8 Revolution Z, Merritt Island: R.AE (Segment 1 BET) ..... A-14
A-9 Revolution Z, Merritt Island: KXY (Segment I BET) ..... A-15
A-10 Revolution Z, Merritt Island: Doppler (Segment 1 BET) . . A-16
A-11 Revolution Z, Patrick: RJkE (Segment I BET) ......... A-17
A-IZ Revolution Z, Grand Bahama: XY (Segment I BET) ..... A-18
A-13 Revolution Z, Bermuda: RXY (Segment i BET) ........ A-19
A-14 Revolution Z, Bermuda: Doppler (Segment 1 BET) ...... A-Z0
A-15 Revolution Z, Bermuda(Q): RAE (Segment I BET) ...... A-Zl
A-16 Revolution Z, Carnarvon: RJkE (Segment 1 BET) ....... A-ZZ
A-17 Revolution Z, Carnarvon: RXY (Segment 1 BET) ....... A-23
A-18 Revolution _, Carnarvon: Doppler (Segment I BET) ..... A-Z4
A-19 Revolution Z,, Hawaii: R/KY (Segment I BET) .......... A-25
A-Z0 Revolution 2,,Hawaii: Doppler (Segment i BET) ....... A-26
A-Z1 Revolution Z,,Goldstone: R_XY (Segment 1 BET) ........ A-27
A-ZZ Revolution Z, Guaymas: XY (Segment i BET) ......... A-28
A-Z3 l_evolution Z, Guaymas: Doppler (Segment | BET) ...... A-29
A-3
CONTENTS (Continued)
Page
A-Z4 Revolution Z, White Sands: R.AE (Segment 1 BET) ...... A-30
A-Z5 Revolution Z, Texas: l_XY(Segment I BET) .......... A-31
A-Z6 Revolution Z, Texas: Doppler (Segment 1 BET) ........ A-32
A-Z7 Revolution 3, Merritt Island: KAE (Segment t BET) ..... A-33
A-Z8 Revolution 3, Merritt Island, RXY (Segment i BET) .... A-34
A-Z9 Revolution 3, Merritt Island, Doppler (Segment I BET) . . A-35
A-30 Revolution 3, Grand Bahamas: XY (Segment I BET) ..... A-36
A-31 Revolution 3, Bermuda (Q): RJkE (Segment i BET) ...... A-37
A-32 Revolution 3, Bermuda: RXY (Segment I BET) ........ A-38
A-33 Revolution 3, Bermuda: Doppler (Segment I BET) ...... A-39
A-34 Revolution 3, Antigua: RAE (Segment I BET) ......... A-40
A-35 Revolution 3, Ascension: XY (Segment I BET) ........ A-41
A-36 Revolution 3, Ascension: Doppler (Segment I BET) ..... A-4Z
A-37 Revolution 3, Carnarvon: RAE (Segment 2 BET) ....... A-43
A-38 Revolution 3, Carnarvon: R.XY (Segment Z BET) ....... A-44
A-39 Revolution 3, Carnarvon: Doppler (Segment Z BET) ..... A-45
A-40 Revolution 3, Hawaii: ILAE (Segment 2.BET) .......... A-46
A-41 Revolution 3, Hawaii: R.XY (Segment 2.BET) .......... A-47
A-42. Revolution 3, Hawaii: Doppler (Segment Z BET) ....... A-48
A-43 Revolution 3, California: RAE (Segment 2 BET) ....... A-49
A-44 Revolution 3, Guaymas: RXY (Segment Z BET) ........ A-50
A-45 Revolution 3, Guaymas: Doppler (Segment 2.BET) ...... A-51
A-46 Revolution 3, White Sands: ILAE (Segment 2.BET) ...... A-52
A-47 Revolution 3, Texas: RXY (Segment Z BET) .......... A-53
A-4
CONTENTS (Continued)
Page
A-48 Revolution 3, Texas: Doppler (Segment 2 BET) ........ A-54
A-49 Revolution 4, Merritt Island: RAE (Segment Z BET) ..... A-55
A-50 Revolution 4, Merritt Island: KXY (Segment Z BET1 ..... A-56
A-51 Revolution 4, Merritt Island: Doppler (Segment 2 ]BET) . • A-57
A-52 Revolution 4, Grand Bahama: KAE (Segment 2 BET) .... A-58
A-53 Revolution 4, Grand Bahama: XY(Segment Z BET) ..... A-59
A-54 Revolution 4, Antigua: RAE (Segment Z BET) ......... A-60
A-55 Revolution 4, Ascension: RAE (Segment Z BET) ....... A-61
A-56 Revolution 4, Carnarvon: RAE (Segment Z BET) ....... A-6Z
A-57 Revolution 4, Carnarvon: RXY (Segment Z BET) ....... A-63
A-58 Revolution 4, Carnarvon: Doppler ISegment 2 BET) ..... A-64
A-59 Revolution 4, Guam: RXYCSegment Z BET) .......... A-65
A-60 Revolution 4, Guam: Doppler (Segment Z BET) ........ A-66
A-6I Revolution 4, Hawaii: RAE (Segment Z BET) .......... A-67
A-62 Revolution 4, Hawaii: R.XY (Segment 2 BET) .......... A-68
A-63 Revolution 4,, Hawaii: Doppler (Segment Z BET) ....... A-69
A-64 Revolution 4_, Goldstone: XY (Segment Z BET) ......... A-70
A-65 Revolution 4, California: RAW. (Segment Z BET) ....... A-71
A-66 Revolution 4, Guaymas: RXY(Segment Z BET) ........ A-7Z
A-67 Revolution 4, White Sands: R.AE (Segment 3 BET) ...... A-73
A-68 Revolution 4, Texas: RXY(Segment 3 BET) .......... A-74
A-69 Revolution 4, Texas: Doppler (Segment 3 BET) ........ A-75
A-70 Revolution 4, Guaymas: RXY (Segment 3 BET) ........ A-76
A-7t Revolution 5, Merritt Island: RXY (Segment 3 BET) ..... A-77
A-5
CONTENTS (Continued)
Page
A-72 Revolution 5, Merritt Island: Doppler (Segment 3 BET) . . A-78
A-73 Revolution 5, Ascension: RAE (Segment 4 BET) ....... A-79
A-74 Revolution 5, Ascension: R_XY (Segment 4 BET) ....... A-80
A-75 Revolution 5, Ascension: Doppler (Segment 4 BET) ..... A-Si
A-76 Revolution 5, Tananarive: R.AIE (Segment 4 BET) ....... A-82
A-77 Revohtion 5, Carnarvon: RAE (Segment 4 BET) ....... A-83
A-78 Revolution 5, Carnarvon: R.XY (Segment 4 BET) ....... A-84
A-79 Revolution 5, Carnarvon: Doppler (Segment 4 BET) ..... A-85
A-8O Revolution 5, Guam: RXY (Segment 5 BET) .......... A-86
A-8I Revolution 5, Guam: Doppler (Segment 5 BET) ........ A-87
A-8Z Revolution 5, Hawaii: RAI_. (Segment 5 BET) .......... A-88
A-83 Revolution 5, Hawaii: R.XY (Segment 5 BET) .......... A-89
A-84 Revolution 5, Hawaii: Doppler (Segment 5 BET) ....... A-90
A-6
A-7
A-8
AI::I
o--
(D
--i
_i
":
,-_.....:_!..........
_
if,i.....
_,I_•
..
.'
i"]
.............
_,I,
'__If::
°_!
'iil:
..2_
',
......[
,
_"
;_.I_/"
IJ
_'
,:!......
Fj
t.......;
'....
1_I-
_?
'F'-
"tf-!i",r,
:'l'l"
_s'
't
:5=!
!"
:....i-
_:_-
if
I_,,|:
t!!
t,.-:-_-;!I
.__.ti_,i
|--',.ki-¢
__IIcTIIliI!i_-,(._i
I!_:i,_f
:_;li:_
't-J
_I:,_I|111_1
_iit.i_!
°',t_:
t!:"
1!
-I-!I_!_I.
,_-....._'-_
,_:_•
-a.-9
A-iO
A-I1
++.:p+
_]i:!:G
!r
_!_-
•.
:-!
•1"i
I_
t+F
+r_!"l
'i
!i!_
l_1
i
....._+
,._,+
,,_+"_+,_,_+.+
+ril......i!+
_,I_
++....,
,,
'_
+r7-_%
_:f!ti
;t_I....
["
[........
I,
;.i
....t
03_
E_
tI
i[;
[I:
--_
_!
i_
i;....
!!1,!
o_+
:+
+'
i.+
+.
I
'"+
+i+
I......
:,
'i
,.'
I.,..+
_i
++
._;
'm+
r+--.:
:o
i_'
I".........
<,,,m
,,_++
i:
,Z
i,.
ri.
/i
r-,'.,!
_!-._.....
i.<_---
+i_,,+
_+,+
..+
++
,
++
I+
++
__•
+.
.+
___0
A-12
A-13
A-i4
A-15
0
A-16
A-17
;Jo
A-18
:_,_i
iti:¸
•_.
_"•
-_-_l"---
_'
IiI
I_
'_
i!
I'
-1-_
.
--'iii:
...._!_J_;i_i
'l!
I,I::m
u
-_-i_i-li_-}!!!L/ii-']_i!il;il
_iii!iill_
i!iT
_+
_o°
I_--_!,
"--
-_i
,,I1_i--
I.i.
I;
_o
__
_'ti
!/
//
:I
:......_it""
i'
.!
tl;/
!'
""_
oN
1!!l
|I:
i:t:--;-.-t
-_t..!I.
iI
/I
i:......
.rll-
_I
II
<.,,_>
t,-,,,_+
r,_.
-+-
i_,
ll,
I.l
/_
/[I
t_--I-
..-r--i-I.
._'ill
t,,_......
<"
•1
._C__l.
L_L
f_,..'gi
i<
i_t'i
•!
II
'_
iL
JIL
iI
i
0Z
A-i9
A-20
A-21
A-ZZ
A-23
A-24
A-Z5
A-Z
6
A-27
A-28
o
A-29
A-30
L'
iE
....I-'_
,_--
,'
*_-,
I:
i_
iI
ii
,i
|
I•
ii
"n
,I
i•
_.-_--_
ii
ii
'|--"
!|
i!
•._-]t
....!
i
'i
i'
I.i
iI
ii'
I|
_/
I.1_
L_
Ii
'l
'_'
//
•I:t
-H-_--------i--_--......_-_...._--I--:--
__
-i_-I
:'-H÷-__
_....
r-i--
!!
|i
'I
'I
I-
_/)
i'
'i
!I
i/
!;
I
,i,_I
-LI._L
•,i_,
i,,/
ti
.::!_
oi
,_i
',l
:_...'
._,_
•-__
t...._,
''
-_-
_i-i
'','
'"--
,i
'.
i*
i_
__
_:
......-?-
'•
-4
'!
!:
I,,_
;.i
,_
_,L__L_L__L
@
A-31
oZ
A-3Z
A-33
A-34
A-35
0z
A-36
A-37
A-38
oZ
A-39
A-40
A-41
oZ
A-42
A-43
A-44
A-45
A-46
A-47
0Z
A-48
A-49
A-50
A-51
A-5Z
A-53
A-54
A-55
A-56
A-57
A-58
A-59
A-60
A-6
1
A-62
A-63
A-64
A-65
,,i-I0
A-66
A-67
A-68
A-69
0
A-70
A-71
A-72
A-73
A-74
A-75
A-76
A-77
r!I-_i_ii_!_i!__
i_̧i
t,
ir
i
_'
'i
,-FIi_
'_
-_
iI.....
...;_
ii
'i
_i
_!__
i_,
_I_
.....il.......l_-
1.."_
°
iI:
i_
ii
ii
_......
0Z
A-78
A-79
A-80
A-81
A-82
A-83
A-84
A-8
5
ii
iii
:.4.
.i..i
.._ii
].",L
!l:Ji_.=,_],
]_._]
_"_
1-%
-iL
./
.i_ll
'I
:/
>,
'...._l_hl1,;i:I'lttl
Jlt-_:°
-!_
IT]-i--B
t'-...._,,t.J-t,
........._-.-it_I].:,t-._;.t
_[_
o=
]_L:C:
t:_-!!ttL
$"
i:
_i]i,
/:
://._
-
''
-"!
i_"it
iiiF
1"_
_v-,
....i
7:,i
"
<4,_il._
_:__
.,,._
:.i,
_i.
.'i
:'
I<
"ItI1
t::°
°_ii
i--7.-'.-!I:
1',l_f#7k!til:t
ti"
o_"_
:i
t:i:
.-.:17....:
p:!<
_,_
o_
_[
_:_.[_ItLt,',-Plt!t
ti:
7'J=
3t-L]lLZ
'-,-I_"::!"......bi_t:til:-ITL'1_-
_'o.o
r>2li
!.l_._:.I
I:C:_,I:t7Iil
t:::!:1.:_..Ti
_::i
".......
-.__
o_
<a
_"-_....
_/
ll!tit_;
!_
._,
iI
::i..
i._
l
<.
;,.
l!....
::......:
;:;;i.....
!,
"_
,,,........
_,......_.....I;
I,I
lJ_,_,,4
,__:
[--,m;_._
!t
I_11'L
t_:__+
II•
•i
'T:.L_
''
i!::
i,i
,;
Ii
!
A-86
A-87
A-88
A-89
Ii
J.I
II
,-
,-,
lr
.-
_.....
,--4...._-.-
ji
IJ
....'
!
•_
.............I
I_
..
.-;
,,,i._._
,;
....,
I.I1
.tJ
II:i
/t/,I
=_.
..:
T....
,.-_
i=
......:....
l
"t'l
m--_-t
,,"!"-_=
_'/:
,I.It
]l_l
i,
_-,t
....!_--.J/,.
i_/I,
:kt
i.l._I_
._.,
_....
_...........
"_
_._]
...._
j.__:.?o
./,
!'/1.....
"k'J_%-
._=
'_'_
i"--'
'_....t--,'--_
"""_
I,
I"l
I',-t
_-=_Jo
A-90
APPENDIX B
SUPP LEMENTAI_Y DATA
Information which is too detailed for the body of the report is pre-
sented in this appendix. This information includes a summary of radar
observations, a summary of station locations, a summary of drag values
for various phases of the missionp and a summary of the radar data
weights used in ESPOD.
Table B-I, a sunnmary of data observations, lists the time of the
first valid data point with an elevation above 3 degrees (rise time) and the
elevation of this data point (rise elevation), the maximum elevation of the
pass, the time of the last valid data point with an elevation above 3 degrees
(set time) and the elevation of this data point (set elevation), and the num-
ber of valid data points by station and revolution. Also included is a com-
ment regarding the use of each pass of data.
Table B-2 lists the C-band station locations used in ESPOD. These
locations are referenced to the Fischer Ellipsoid of 1960.
Table B-3 lists the S-band station locations used in ESPOD. These
locations are referenced to the Fischer Ellipsoid of 1960.
Table B-4, the drag summary, lists the vehicle configuration, the
time interval for which the listed drag value is valid, vehicle weight for
this time interval, vehicle cross sectional area, and the value of the drag
parameter.
Table B-5 lists the values used by ESPOD to weight the radar track-
ing data from each station as a function of data type and radar type.
B-i
•,
.UJ
_,.
.,
.J
!!_i_
i°°
__
_""_
JD>
_.z_°
C_
eqN
Ne_
C_•
__t
_I............................
¢;
"__
NN
No
oN
oo
_o
oN
e-"2
22
22
22
22
2_
__
__
__
__
__a
oo
oo
oo
c_
oo
oo
oo
oo
oo
c_
oo
o¢_o
oo
_o
oo
Ngg;gggggNgNNgg;gggN
g;g;
g;gNggg
g
__,___.
__
_i._
A
z0
_o
_o
oo
oo
oo
oo
o_
_o
oo
_o
oo
oo
oo
o_
oo
1
'_-
__
-
.__
NN
N_
N_
NN
N_
N_
gN
gN
N_
gg
NN
_g
NN
__
__
u
B-3
•°l
I_o.ol._o.lto
____0_
-,00
-,00
O0
_r---
o_
,o'-",.o
0'_o'-,
C0m
o_o
,.0
-.0
",0
O0
_.0
_D
,,0
,,0
t-i
B-4
B-5
<
__
u_
_0
__0
e_l
_0_
u_
N_0
_-_
eJ
_0
o_
e_
0_
[_
_,_
_-
[_
e_
e_
O0
e_
_0
O_
_0_
__
__
CO
__"
0_
[__0
'_
_0
_'_
__
__
__
0_
_'_
__
oo
o,_
0_.
"__
0O
_on
I__
0_
e__
_0",
_'_'_
Ln
"-0,._
uN
g_
M_
M4_
__
_16_
_o
0_
_i
o'_t_]
e__
_N
_N
eq',_
__
0
0m._,
L_Z
<_
m0
__
__:
,..IN
.._
NI
o
_m
onm
oom
ooon
onm
moo
onm
¢;¢.;II;
_'Z,
.oo
_,-,_
o_
_m
_=
"'__
_"0
__
"_
_=
•,_
_,_
o_,
_=
_'_
_o_
<
B-6
B-?