Tracking System Data Analysis Report Ranger 4 Final Report

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iI Technical Report No. 32-523

Tracking System Data Analysis Report

~ Ranger 4 Final Report

W. R. Wollenhaupf

OTS PRiCE

1 XEROX 5 / HtCROFlW $

ET PROPULSION LABORATORY CALIFORNIA INSTITUTE OF TECHNOLOGY PASAD EN A, CALIFOR N I A

March 1, 1964 Technical Report No. 32-523

Tracking System Data Analysis Report Ranger 4 Final Report

W. R. Wollenhaupf

N. A: Renzetti, Chief 0 Communications Engineering and Operations Section

JET PROPULSION LABORATORY CALIFORNIA INSTITUTE OF TECHNOLOGY PASADENA, CALIFORNIA March 1, 1964 Copyright 0 1964 Jet Propulsion Laboratory California Institute of Technology

Prepared Under Contract No. NAS 7-100 National Aeronautics & Space Administration ~ ~ ~~~ .. ~

JPL TECHNICAL REPORT NO. 32-523

CONTENTS

1. Introduction ...... 1 A . History of Mission ...... 1 B. System Configuration ...... 2 1. Ground Station Modes ...... 2 2. Spacecraft Modes ...... 2 C . Data Evaluation Techniques ...... 3

II . Performance Analysis ...... 4 A' Pr'eilight Calibrations ...... 4 1. DSIF 1 (Mobile Tracking Station. South Africa) ...... 4 2 . DSIF 2 (Pioneer Site. Goldstone) ...... 4 3. DSIF 3 (Echo Site. Goldstone) ...... 4 4 . DSIF 4 (Woomera) ...... 4 5. DSIF 5 (Johannesburg) ...... 5 B . Postflight Analysis of Station Performance During Mission .... 5 1. DSIF 1 (MobileTracking Station. South Africa) ...... 5 2 . DSIF 2 (Pioneer Site. Goldstone) ...... 6 3. DSIF 3 (Echo Site. Goldstone) ...... 6 4. DSIF 4 (Woomera) ...... 7 5. DSIF 5 (Johannesburg) ...... 7

111. Final Orbit ...... 9

Appendixes A . DSIF and Spacecraft Characteristics ...... 11 B . Equations Used in Data Evaluation ...... 17 C . Resultsof Ranger4 Preflight Calibration Tests ...... 19 D . Hourly Trajectory Listing from Injection to Impact ...... 23 E . History of Ground Modes and Transmitter VCO Frequencies ...74 F . Final Orbit Residual Listing ...... 76

References ...... 108 JPL TECHNICAL REPORT NO. 32-523

TABLES

1 . Nominal view periods vs actual tracking periods ...... 2 2 . Commands sent to Ranger 4 spacecraft by DSlF 5 ...... 8 3 . Summary of data used in orbit determination ...... 9 4 . Tracking data noise statistics ...... 9 5 . Errors in position and velocity vectors at injection based on tracking data noise statistics only ...... 9 A.1 . DSlF characteristics for Ranger 4 ...... 11 A.2 . Doppler reference frequencies used at the DSlF stations .....11 C.1 . Coefficients for optical pointing error ...... 19 C.2 . Coefficients for optical star tracks and postflight analysis ....19 C.3 . Ranger 4 preflight boresight-vs-polarization-angle test .....20 E.1 . Ranger 4 DSIF tracking history ...... 74 E.2 . Transmitter VCO frequencies ...... 75 .

JPL TECHNICAL REPORT NO. 32-523

A.1 . Mobile tracking station (DSIF 11 ...... 12 A.2 . Goldstone Pioneer Site (DSIF 21 ...... 12 A.3 . Goldstone Echo Site (DSIF 31 ...... 13 A.4 . Woomera tracking station (DSIF41 ...... 14 A.5 . Johannesburg tracking station (DSIF 51 ...... 15 A.6 . Spacecraftcommunicationssystem ...... 16 C.1 . Preflight star track results, April 10. 1962 (DSIF 41 ...... 21 C.2 . Prefiight star track results. April 3. 1962 (DSIF 5) ...... 21 C.3 . Preflight star track results. April 12. 1952 (DSIF 5) ...... 22 D-1 . C-2 doppler residuals (DSIF 11 ...... 23 D.2 . C-2 doppler truncation (DSIF 21 ...... 23 D.3 . RF boresight shift (DSIF 2) ...... 23 D.4 . C-1 doppler residuals (DSIF 21 ...... 24 D.5 . 30-Mc bias OSC frequency (DSIF 21 ...... 24 D.6 . C-1 doppler residuals (DSIF 31 ...... 24 D.7 . Angular residuals vs hour angle (DSlF 41 ...... 25 D.8 . Angular residuals vs hour angle (DSIF 51 ...... 25 D.9 . Angular residuals vs hour angle (DSIF 51 ...... 26 D- 10. C-2 doppler residuals (DSIF 51 ...... 243 D- 11 . Pseudo two-way doppler residuals (DSIF 5) ...... 27

V JPL TECHNICAL REPORT NO. 32-523

ABSTRACT ;13520 The analysis of the Deep Space Instrumentation Facility (DSIF) spacecraft tracking performance during the Ranger 4 mission is sum- marized. Included are ground system configurations, station view periods, and a discussion by station and view period of all tracking data; i.e., angular and doppler, taken by the tracking stations. Also presented is a summary of the tracking data which were actually used in determining the spacecraft orbit and the noise statistics of these data. /4-

1. INTRODUCTION

This report summarizes the analysis of the Deep Space (CC&S). This conclusion was based on the following: Instrumentation Facility (DSIF) tracking performance (1) all telemetry channels were in lock at DSIF 1 but no during the Ranger 4 mission. It supercedes all previous telemetry commutation was occurring and (2) no blips Tracking Data Analysis reports for this mission. were observed on Channel B-2 at the scheduled time of solar panel extension nor at any of the times when the subsequent CC&S commands were to be given. Because of the malfunctions it was not possible to command the A. History of Mission spacecraft and a midcourse maneuver did not occur. The Ranger 4 spacecraft, using the Atlas D-Agena B booster, was launched from the Atlantic Missile Range The DSIF continuously tracked the transponder signal (AMR) on April 23, 1962 at 20 hr, 50 min, 15 sec from initial acquisition until battery depletion at 0722 (20:50:15) Greenwich Mean Time (GMT). Based on AMR GMT on April 24, 1962. For the remainder of the mission tracking data, Atlas-Agena separation appeared normal, the DSIF stations tracked the capsule beacon signal, and at Agena B first engine cutoff the spacecraft was in a except for short periods during which unsuccessful circular parking orbit at an altitude of 185 km and a searches were made for the transponder signal. Because space fixed velocity of 7.800 km/sec (see Ref. 1). The of the spacecraft malfunction, a terminal maneuver was parking orbit was terminated 254 sec later by Agena B not attempted. Lunar occultation, as determined by loss second engine ignition. Agenu B second engine cutoff of received signal at Goldstone Pioneer Site (DSIF 2) (at 21:04:15 GMT) concluded all powered flight for the and Echo Site (DSIF 3), occurred at 12:47:46 GMT on Ranger 4 spacecraft and represented the time of injec- April 26, 1962. DSIF 2 and DSIF 3 continued to listen tion into a lunar intercept trajectory. During this launch for the beacon signal until approximately 13:30 GMT. to injectioZ-pethe spacecraft was tracked by AMR No signals were detected; therefore, it was concluded stations. that the spacecraft impacted the moon and tracking operations ceased. Based on the orbit determined from the Initial acquisition of the spacecraft transponder by the transponder data, lunar impact occurred (on the dark DSIF was made by the Mobile Tracking Station (MTS, side of the moon) at 12:SO:OO GMT. The total flight time DSIF 1) at 21:13:12 GMT. Prior to acquisition by this from injection to lunar impact was 63.76 hr (Ref. 1). station, a malfunction had occurred in the spacecraft Table 1 summarizes the nominal station view periods vs which afFected the Central Computer and Sequencer the actual tracking periods.

1 JPL TECHNICAL REPORT NO. 32-523

Table 1. Nominal view periods vs actual tracking periods

Nominar I Actual DSIF Dato Station Riso, Set, Viow Acquisition, End of track, Tracking GMT GMT poriod GMT GMT poriod

April 1 2 1 :13:45 08:39:19 1 1' 27 21 :13:19 08:35:20 1 1' 22" 23-24 5 2 1 :13 :45 08:39:19 11'27' 21 :14:37 08:43:20 11'29' 4 22:29:19 23:49:19 1' 20' 22 :2 2:oo 00:06:00 1' 44'

April 2 08:34:19 16:58:54 8' 25" 08:32:40 17:05:35 8' 33" 24-25 3 08:28:45 16:58:54 8' 3w 09:00:4ob 17:07:20 8' OF 4 13:59:19 01 :54:19 11'55' 13:52:44 01 :58:59 12' 06' 1 Not scheduled to track 5 21 :24:49 09:20:13 11'55' 21 :21:35 09:25:11 1 2' 04'

April 2 08 :56:00 12:47:46 9' 52" 08:47:30 17:48:20 9'01" 25-26 3 Not scheduled to track 4 14:16:19 02:12:19 11'56' I 14:23:00 02:13:06 11'50" 1 Not scheduled to track 5 2 1 :4 2:19 09:28:19 11'46' 21 :40:13 09:32:00 1 1' 51'

April 2 08:56:19 12:47:46' 3' 51" 08 :46:00 12:47:46 4' 02" 26 3 08 :46:54 12:47:46' 4' 01' 08:33:00 12:47:46 4' 15"

*Bored on 5-deg elevation angle constraint for AZ/EL stations and 90-270 deg hour angle constraint for HA/DEC stations. bStation searched far transponder from 07:48:50 to o9:OO:OO GMT. =Spacecraft accultd by moon.

B. System Configuration mode, taking both angular and C-1 data. This mode is possible at all DSIF stations. The detailed characteristics of the DSIF stations and the spacecraft are given in Appendix A. 2. Spacecraft Modes 1. Ground Station Modes The spacecraft modes are defined according to the For the Ranger 4 mission there were four possible telemetry system mode for that portion of the mission. modes of operation of the DSIF. They are identified as They are as follows: Ground Modes and are defined as follows: GM-1. Ground receiver tracks the transponder signal TM-I. From launch to start of midcourse maneuver, (ssO.05 Mc) in the two-way doppler mode, approximately 16 hr. taking both angular and C-2 data. This mode is possible at DSIF 1, 3, and 5 (Johannesburg TM-11. Midcourse maneuver, approximately 28 min. DSIF Station).

GM-2. Ground receiver tracks the transponder signal TM-111. Post-midcourse maneuver to end of terminal (960.05 Mc) in the one-way doppler mode, maneuver, approximately 48 hr. taking both angular and C-1 data. This mode is possible at all DSIF stations. TM-IV. End of terminal maneuver to bus impact, ap- GM-3. Ground receiver tracks the transponder signal proximately 40 min. (960.05 Mc) in the pseudo-two-way doppler mode, taking both angular and C-3 data. This mode is possible with the combination DSIF 1, TM-V. Capsule impact to end of mission, 60 day 4 (Woomera Station), 5, (noncoherent) or nominally. DSIF 2,3 (coherent).

GM-4. Ground receiver tracks the capsule beacon Because of the spacecraft malfunction, the spacecraft signal (960.15 Mc) in the one-way doppler stayed in the TM-I mode for the entire mission.

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C. Data Evaluation Techniques goal of isolating and removing systematic errors, and The Orbit Determination Program (ODP) will deter- determining the characteristics of tracking data noise mine a spacecraft orbit by converging on the set of statistics; i.e., the RMS and mean values of the residuals initial conditions at injection epoch, which causes the (observed minus computed). The pertinent equations weighted sum of the squares of the differences between used are given in Appendix B. There are essentially two the actual observed values and the computed observed phases in the mission tracking evaluation: in-flight and values to be minimized. The computational method is a postflight. modsed weighted least-squares method. In this method, independent data weighting values are determined from In the in-flight phase, station reports are analyzed to the measured effective variances. Whereas in the usual detect any unusual occurrences. Also, transmitter VCO least-squares method, the data points are weighted, in- drift statistics are compiled, frequency changes are noted dependently, inversely proportionally to their measured and brought to the attention of the ODP group, and variances. When determining the effective variance for changes in transmitter assignment are evaluated. After each data type at each station, consideration is given to the orbit is reasonably well known, observed values are the correlation width of all recognized noise sources, the checked against predicted values to determine validity of sampling rates, counting times, elevation angles, and the tracking data and to detect blunder points before range to the spacecraft. they influence the orbit. Certain parameters such as the doppler system figure of merit (g') are computed and Prior to being put on the ODP input tape, the incom- used to evaluate the quality of the incoming doppler ing data goes through a tracking data editing program data. Once the ODP listings are available, the residuals (TDEP) which rejects gross blunder points, points that and rejected points are analyzed to detect systematic are outside of the antenna mechanical constraints, and error sources. The Test Director is informed of all un- points with bad teletypewriter format. No attempt is usual occurrences, and if applicable, corrective action is made to unscramble or correct bad format points. Hence, recommended. by sacrificing the possibility of utilizing the maximum number of data points there will be a reduction in the The postflight evaluation phase consists of analyzing all sensitivity to blunder points and possible error points available data pertaining to the DSIF tracking that might otherwise have a significant effect on the performance. Complete analysis of all residuals, by data type, is orbit. made to detect equipment biases, periodic noise which The current policy for weighting data is to assign an might be attributed to station equipment, and any other initial weight for each data type based on the sample systematic errors. The validity of the noise model is rate, count time, and expected data quality. These weights checked by least-square fitting the tracking data. All may be changed (on option) when the sample rate and observations are evaluated and compared with preilight count time changes or when the residuals indicate periods calibrations and past performance. All indications of of extremely good or relatively poor tracking data. equipment problems and nonstandard occurrences are investigated and recommendations made to the appro- Data evaluation techniques, consistent with the ODP priate agencies. New data analysis techniques are investi- computational methods, have been developed with the gated and implemented if applicable.

3 JPL TECHNICAL REPORT NO. 32-523

II. PERFORMANCE ANALYSIS

A. Preflight Calibrations lar residuals (that is, the difference between the ODP In order to improve the quality of the primary angular computed values and the OPE corrected values) of DSIF data going into the Orbit Determination Program (ODP), 4 and 5 for both RA 3 and 4. The coefficients of this it is first corrected for the antenna optical pointing error polynomial were combined with the OPE coefficients. (OPE). For the angle data stations, DSIF 4 and 5, this Results of the study show that the total angular error has error was determined from a series of independent, been reduced to approximately 2 0.02 degrees in both horizon-to-horizon, star tracks conducted in 1961-1962. hour angle and declination. These new coefficients are A polynomial curve fit was made to the differences be- shown in Appendix C. Use of this method for future tween the refraction corrected ephemeris values and the missions is being studied. observed values read from the angle encoders. The OPE is then represented by the coefficients of the resulting The following preflight calibration tests were made by polynomials. In general, the preflight calibration star the DSIF stations for Ranger 4. Numerical results and tracks are required for two purposes: (1) to detect gross star track plots may be seen in Appendix C. system errors and (2) to test the validity of the correction polynomial. The coefficients used for the RA 4 in- 1. DSIF 1 (Mobile TrackingStation, South Africa) flight computations may be seen in Appendix C. A boresight-vs-polarization-angletest was conducted on April 9, 1962. Results compared favorably with those Experience gained in Ranger 3 has shown that the of Ranger 3. OPE coefficients do not remove all systematic pointing errors. This is reasonable since the RF and optical axis 2. DSIF 2 (Pioneer Site, Goldstone) of the antenna are not necessarily the same. That is, the A star track of Alpha Virginis (Spica) was conducted RF axis is a function of the position of the quadripod on April 18, 1962. Hour angle residuals compared favor- feed, whereas the optical axis is not. Thus, if there is a ably with previous star tracks. No comment can be made quadripod deflection (due to thermal effect and/or gravi- on the declination residuals since the antenna appeared tational loading) at some given instant of time, the optical to be locked in declination. A new test was not requested error and the RF error would not be the same. Further, since DSIF-2 is not a primary angle station. the optical refraction and the RF refraction are not the same due to the difference in respective wavelengths. In 3. DSIF 3 (Echo Site, Goldstone) addition to these effects, the RF pointing error is also a Nine short term star tracks were conducted on April function of feed alignment, received signal-to-noise ratio, 13, 1962. The stars tracked were Alpha Aquilae (Altair), and received polarization angle (since the antenna null Alpha Lyrae (Vega), Beta Herculis (Antares), Alpha pattern does not have the same slope at all polarization Bootis (Arturus), Alpha Virginis (Spica), Epsilon Ursae angles). The RF boresight-vs-polarization-angle test was Majoris (Alioth), Alpha Leonis (Regulus), Lambda Scor- an attempt to study the RF errors. The test was designed pii (Shaula), and Sigma Sagittarii (Nunki). Results com- to correlate the optical and RF errors observed at the pared very well with the previous star tracks. In addition, collimation tower over a range of signal levels and polar- a boresight-vs-polarization-angletest was also conducted ization angles. Experience has shown that the results of on April 13, 1962. Results of this test compared favorably the test cannot be applied to the in-flight data in a mean- with those of Ranger 3. ingful manner. Hence, for the purpose of describing the RF pointing error the test is inadequate, and a new 4. DSIF 4 (Woomera) method for determining the RF antenna calibration is A horizon-to-horizon star track of Alpha Virginis required. However, the tests are required to add to the (Spica) was conducted on April 10, 1962. Based on the composite statistical data, and they are an excellent indi- results of this track, it was decided to change the declin- cation of RF system status and autotrack capabilities. ation coefficients of the correction polynomial used for Ranger 3. The hour angle coefficients were not changed. After the completion of the mission, a study was made On April 14, 1962 a boresight-vs-polarization-angle test to improve the coefficientsof the correction polynomial. was conducted. Results compared favorably with those of A polynomial curve fit was made to the first pass angu- Ranger 3.

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5. DSIF 5 (Johannesburg) 1. DSIF 5 had indicated good telemetry after acquisi- A horizon-to-horizon star track of Beta Corvi was tion at 21:14:37. This made it appear that DSIF 1 conducted on April 3, 1962. Hour angle residuals did not had either equipment problems or that they were agree with those seen on previous star tracks from this on a side lobe. Hence, time was lost in making addi- station; therefore another track was requested. This track tional searches for the main carrier. (of Alpha Virginis) was conducted on April 12, 1962, and 2. The telemetry channels in lock were very noisy results compared very well with previous star tracks. In which again made it appear that the station was on addition, a boresight-vs-polarization-angletest was also a side lobe. conducted on April 12, 1962. Results compared favorably 3. When two-way acquisition was attempted, the sta- with those of Ranger 3. tion two-way doppler indicator did not show good two-way lock. The indicator referred to is the station internal 10-cps oscillator, the output of which is B. Postflight Analysis of Station Performance phase modulated in the ground transmitter and sent During Mission to the spacecraft. It is retransmitted from the spacecraft and appears at the ground receiver in the As a result of the spacecraft malfunction, the space- output of a phase detector circuit where a maximum craft continued to tumble throughout the entire mission positive voltage was considered to indicate a good with a periodicity of approximately four minutes. This two-way lock. Subsequent investigation revealed could be seen in both the angular and doppler residuals. that the output of the phase detector is range de- Further verification was given by the periodic variation pendent. Further, the voltage associated with a good in AGC signal strength levels. In general, the AGC levels two-way condition could be either positive or nega- were lower than would be expected for a normal mission tive depending on range. At the time in question since it was impossible to change to the spacecraft high- the sign of the detector output voltage was negative. gain antenna. These lower signal levels caused some Hence, it appeared as though the indicator was not difficulty in maintaining lock during later passes. functioning properly.

The following is a station-by-station postflight analysis The transmitter was turned off at 23:05:00 with DSIF of DSIF tracking performance during the mission. It is 5 acquiring two-way lock at 23:07:00. At 23:38:00 the based on all available data such as real time tracking transmitter was again turned on and two-way lock was data, in-flight station reports, station logs, calibration completed at 23:40:00. The transmitter was then turned books, etc. All times listed refer to Greenwich Mean Time off at 00:06:00 and pseudo two-way lock was completed (GMT). Residual plots of all data used in the orbit de- at 00:07:34. Tracking was continued in this mode until termination, and plots of subsequent data which are of the transponder signal was lost due to battery depletion particular interest, are shown in Appendix D. Also in- at 07:22. Unsuccessful searches were made for the cap- cluded in this appendix is an hourly trajectory listing, by sule beacon signal until 08:35:20. This concluded the station, from injection to impact. Pertinent equations used first pass. The station was not scheduled to track during in the data analysis are shown in Appendix B. Appendix subsequent passes. E contains a mission history of ground station mode Angular residuals are large, particularly in azimuth versus time and pass, and a history of transmitter VCO where the error at times is one degree. Also, there still frequency during the transponder tracking period. appears to be a hitching problem. However, DSIF 1 angular data is not used in the ODP, hence, these large 1. DSIF 1 (Mobile Tracking Station, South Africa) errors do not affect the computed orbit. A total of 881 The transponder signal was first heard at 21:13:12 on C-2 doppler data points were received from this station April 23, 1962, and one-way acquisition was completed during the mission. Of this number, 703 data points 21:13:19. At this time all telemetry channels, except were used in the orbit determination. The remainder channel 1, were in lock but there was no telemetry com- were rejected because of bad data condition, bad tele- mutation. Two-way lock was not established until typewriter format, or they were blunder points. A least- 21:28:48 with the first good data being transmitted at squares technique was used to determine the quality of 21:30:11. This delay in two-way acquisition was caused the raw C-2 doppler data, i.e., the doppler data from the by the following: incoming data tape. The standard deviation of the data

5 JPL TECHNICAL REPORT NO. 32-523

taken during the transponder tracking period was de- On the second view period, April 25, the beacon signal l termined to be 0.602 cps. For this same period, the ODP was acquired at 08:47:30. There was a malfunction of computed standard deviation (using a different method) the Coordinate Converter computer and as a result the was 0.639 cps. The difference between the two values is servo system was operated in the “aided track” mode. most probably caused by using slightly different rejection Three unsuccessful, 30-min searches for the transponder criteria. Quality of the two-way doppler data taken dur- signal were conducted at 09:30, and 13:00, and 17:30. ing this mission compares very well with the data taken The receiver dropped lock a total of 39 times during the during the Ranger 3 mission (standard deviation = 0.677 tracking period because of low signal strength. AGC cps). The waveform appearing in the C-2 doppler resid- readings ranged from -142 dbm to threshold. Tracking uals of Fig. D-2 of Appendix D is a result of doppler period was terminated at 17:48:20. counter truncation error caused by the round-off mecha- nism of the doppler counter. Transmitter VCO drift was The third view period acquisition occurred at 08:46:00 I within the specification of 1part in IO8 per 15 min during on April 26, 1962. One unsuccessful, 5 min search for the entire pass. The VCO frequencies during the two- the transponder was made at 09:42:00.Tracking con- way doppler tracking period may be seen in Table E-2 tinued normally with the exception of short periods when of Appendix E. AGC signal strength readings ranged the receiver dropped lock due to low signal strength. between - 118 dbm and - 146 dbm. The one-way doppler data taken during this period was not required for computing the orbit; but it was critically 2. DSIF 2 (Pioneer Site, Goldstone) needed to verify the orbit which had been computed The transponder battery was depleted approximately from the transponder data, and to verify lunar impact. 1 hr and 10 min before the first RA-4 spacecraft view In the equation for determining the doppler shift from period for this station. Hence, DSIF 2 was confined to C-1 data there are two unknowns, namely, the true cap- tracking the capsule beacon in ground mode GM-4 dur- sule beacon frequency and the 30 mc bias oscillator ing all passes. frequency. Therefore, it is imperative that an accurate record of the bias oscillator frequency be maintained, Initial acquisition of the beacon signal occurred at particularly during critical periods. During this pass, 08:32:40 on April 24, 1962. At 10:04:49, a comparison analysis showed that the bias oscillator drift exceeded of the receiver VCO frequencies between this station and the 1 part in 106 per hour specification and was varying DSIF 3 revealed that both stations had been tracking on somewhat periodically (Fig. D-5). This drift should have I a side lobe rather than the main carrier. That is, there been noted in the in-flight station reports, and the bias was a difference of 38 cycles between the receiver VCO oscillator frequency should have been monitored at more frequencies at DSIF 2 and DSIF 3 which could be ac- frequent intervals. As a result of these omissions, the C-1 counted for by the receivers being locked on opposite data was not usable (a plot of this data may be seen sidebands. The VCO frequency was adjusted and the in Fig. D-4). The capsule beacon signal was lost at I main carrier was in lock at 10:07:23. Tracking continued 12:47:46.8 when the spacecraft was occulted by the normally with the exception of short periods during moon. This time was determined from the station Mid- which the receiver dropped out of lock because of the western analog recording. DSIF 2 continued to search low signal level (AGC readings ranged from -147 dbm for the capsule signal until 13:30:00. No signal was de- to threshold during the pass). At 15:50:00 it was dis- tected; therefore, it was concluded that the spacecraft covered that the precision bias doppler loop had been impacted the moon. This terminated the tracking period out of lock since 14:20:00. Also of interest during the first and the mission. tracking period was an abrupt boresight shift of approximately -0.01 deg in declination (Fig. D-3). The time of 3. DSIF 3 (Echo Site, Goldstone)

I the shift corresponds roughly with the time of local The transponder battery was depleted approximately sunrise and could be accounted for by a feed quadripod 1 hr and 10 min before the first RA-4 spacecraft view deflection due to a thermal effect. This same phenomenon period for this station. Therefore, tracking was confined had been observed at DSIF 5 during Ranger 3, and sub- to ground mode GM-4 during all passes. sequent tests conducted at Johannesburg (see Ref. 2), verify this conclusion. DSIF 2 data, taken during this and From 07:48:50 to 09:OO:OO on April 24, 1962, an un- subsequent passes, were not used in the orbit computa- successful search was made for the transponder signal. tion. The tracking period was terminated at 17:03:13 Initial acquisition of the capsule beacon signal occurred when the spacecraft went below the station horizon. at 09:00:40. As previously noted in the DSIF 2 analysis,

6 JPL TECHNICAL REPORT NO. 32-523 it was discovered that the station had been tracking on data points were received at the Jet Propulsion Labora- a side lobe prior to 10:08:48. Two additional and unsuc- tory (JPL) (C-3 doppler data from DSIF 4 were not used cessful, 30-min searches were made for the transponder in the ODP since more accurate C-2 data was available signal at 12:30:00 and 15:30:00. During the pass the from either DSIF 1 or DSIF 5). Of this number, 35 points receiver was periodically dropping lock due to low signal were used in determining the RA-4 spacecraft orbit. The strength. AGC signal strength ranged from -141 dbm remainder were rejected because of bad teletypewriter to threshold. Data taken during this and subsequent format, bad data condition code, or they were blunder passes were not used for computing the spacecraft orbit. points. The high percentage of rejection (59.8%) is a The tracking period ended at 17:04:52 when the space- result of tracking through the spacecraft “turn around” craft went below the station horizon. period during which the spacecraft rate is rapidly chang- ing. Angular residuals show the spacecraft tumble; but DSIF 3 was not scheduled to track during the second otherwise they appear normal. Transponder AGC signal Goldstone view period. strength levels ranged between - 113 dbm and - 123 dbm with a periodic variation of four minutes. On the third view period, initial acquisition of the beacon signal occurred at 08:33:00 on April 26, 1962. Prior to the second view period, the transponder bat- One unsuccessful attempt was made to acquire the trans- tery was depleted. Hence, subsequent tracking was con- ponder signal at 09:52:00. The same general comments fined to the capsule beacon signal with the exception of made for the C-1 beacon doppler data in the DSIF 2 short periods when unsuccessful searches were made for analysis are applicable for DSIF 3. Again it must be the transponder signal. Initial acquisition of the beacon noted that the 30-mc bias oscillator frequency was not signal on the second pass occurred at 21:21:35 on monitored often enough. At 11:55:00, automatic record- April 24, 1962. Tracking continued normally except for ing of the bias oscillator frequency ceased. Some man- short periods when receiver lock was dropped because ually recorded frequencies were submitted after 11:55, of low signal strength. AGC readings during the tracking but they did not agree with the previous frequencies. period ranged between - 139 dbm and threshold. Angu- lar residuals showed a relatively large error (as great as That is, the slope of the manually recorded frequencies k.08 degrees), and excessive scatter due to low signal was entirely different from that of the automatically strength. These data were not used in the ODP therefore recorded frequencies. In the ODP, frequencies were the errors did not affect the computed orbit. The track- obtained between 11 :55 and occultation by extrapolation ing period was terminated at 01:58:59 on April %, 1962. based on the slope of the automatically recorded frequencies. After this was done, the C-1 data was usable On the third view period, the beacon signal was ac- for verifying lunar impact. These results are discussed quired at 14:23:00 on April 25, 1962. During the pass, in Sec. 111. Using DSIF 3 data, the capsule beacon fre- three unsuccessful 30-min searches were made for the quency drift was estimated to be 1.65 cycles/min during transponder. The receiver was periodically going out of the period 11:25-11:55. Lunar occultation, determined lock because of low signal strength. AGC readings from the analog recording of the receiver functions, ranged between -149 dbm and threshold. The tracking occurred at 12:47:46.9. DSIF 3 continued to search for period ended at 02:13:06 April 26, 1962. This concluded the capsule signal until 13:30:00. No signals were de- DSIF 4 participation in the Ranger 4 mission. tected; therefore it was concluded that the spacecraft impacted the moon. This terminated the tracking period 5. DSIF 5 (Johannesburg) and the mission. The transponder signal was acquired in ground mode GM-3 at 21:14:37 on April 23, 1962. Tracking continued 4. DSIF 4 (Woomera) in this mode until the MTS transmitter was turned off The transponder signal was initially acquired in ground at 23:05:43. DSIF 5 transmitter was turned on at mode GM-3 at 22:22:00 on April 23, 1962. At 22:43:00 23:07:00 and two-way lock was completed at 23:07:55. DSIF 4 acquired the capsule beacon signal and tracked During the period 23:39:54 to 00:06:00,DSIF 1 again it until 23: 00:00. Psuedo two-way transponder tracking assumed the transmitting assignment with this station was reestablished at 23:OO:10. Tracking continued nor- tracking in the GM-3 mode. At 00:07:00the transmitter mally in this mode until the spacecraft went below the was again turned on and two-way lock was completed station horizon at 00:06:00on April 24, 1962. During this at 00:07:54. Two-way lock was lost at 07:21:50 when first view period a total of 87 hour angle and declination the transponder battery was depleted. During the trans-

7 JPL TECHNICAL REPORT NO. 32-523 ponder tracking period, DSIF 5 transmitted a total of that the doppler portion of the ODP was not properly 18 commands in an unsuccessful attempt to obtain a updating the transmitter VCO frequency. A plot of the response from the spacecraft. These commands, and the psuedo two-way doppler residuals may be seen in Fig. time that they were sent may be seen in Table 2. The D-11. Psuedo two-way doppler are not used in the ODP capsule beacon signal was acquired at 08:14:30 and since more accurate two-way doppler data are available. tracked until the spacecraft went below the station horizon at 08:43:20 GMT. Ranger 4 was the first mission for which DSIF 5 had two-way doppler capabilities; hence, the following comments are of particular interest. A least-squares tech- Table 2. Commands sent to Ranger 4 spacecraft nique was used to determine the quality of the raw C-2 by DSIF 5 doppler data, i.e., the doppler data from the incoming data tape. Results of the analysis showed that the quality Verifiedb, GMT Command” I Initiated, GMT of data, taken during the transponder tracking period, RTC-0 01 :52:20 01 :53:02 was excellent with a standard deviation of 0.067 cps. RTC-0 01 :53:23 01:54:02 This compared very well with the standard deviation sc-1 01 :57:00 01 :57:42 of 0.078 cps computed by a different method in the RTC-0 02:l 1:50 02:12:20 ODP. The difference between these two values is most RTC-0 02:12:49 02:13:27 probably caused by handling the data in hourly blocks sc-1 02:15:00 02:15:40 (in the least-squares method), and by using slightly dif- RTC-5 02:22:00 02:22:40 ferent rejection criteria. A study of the first pass trans- RTC-5 02:27:00 02:27:40 RTC-5 02:33:00 02:33:40 mitter VCO frequency history revealed that the oscillator RTC-5 02:43:00 02:43:40 was very stable; i.e., the frequency drift was well within RTC-5 02:40:00 02:40:40 the specification of 1 part in los per 15 min. The VCO RTC-0 03:15:00 03:15:41 frequencies during two-way tracking period may be seen RTC-3 03:16:01 03:16:40 in Table E-2. RTC-0 05051 0 05:05:50 RTC-0 05:06:1 1 05:06:50 On the second view period, the beacon signal was RTC-3 051 2:OO 0512:40 acquired at 21:21:35 on April 24, 1962. During the pass, RTC-0 05:50:00 05:50:40 the receiver was periodically dropping out of lock be- RTC-2 05:52:00 05:52:40 cause of low signal level. AGC level ranged between aComplete list of spacecraft ground commands may be found in Ref. 4. - Definitions of commands used herein are: 141 dbm and threshold. An unsuccessful search for RTC-0: clear command the transponder signal was made between 06:20:00 and RTC-2: antenna hinge angle override RTC-3: antenna switchover 06:50:00 on April 25. The tracking period terminated RTC-5: telemetry mode change SC-I: midcourse maneuver roll duration when the spacecraft went below the station horizon bverification by the station read-write-verify (RWV) system. Note: Above data taken from mission station reports. at 09:24:11. Angular residuals for the pass were relatively large (as great as k.08 degrees) and some scatter, due to low signal strength, was observed. Data taken For the period 23/21:14:37 to 24/07:22:00 a total of during this, and the subsequent pass, were not used in 428 C-2 doppler data points, and 960 hour angle/ the ODP; therefore the large errors did not affect the declination data points were received at JPL. Of this computed orbit. number 377 doppler and 719 hour angle/declination points were used in computing the spacecraft orbit. The The beacon signal was acquired on the third view remainder were rejected because of bad teletypewriter period at 21:40:13 on April 25, 1962. Three unsuccess- format, bad data condition code, or they were blunder ful, 30-min searches for the transponder were made at points. Angular residuals seen in Appendix D show the ef- 23:08:00, 03:03:00, and 07:00:30. Throughout the pass, fect of the new angular correction coefficients. The point- the receiver was periodically dropping out of lock being error in both hour angle and declination has been cause of low signal strength. AGC readings ranged from reduced to approximately k0.02 deg. Two-way doppler -147 dbm to threshold. Tracking was terminated at residuals during the period 24/02:08 to 24/05:04 origi- 09:32:08 on April 26, 1962. This concluded DSIF 5 par- nally showed a negative bias of approximately -0.2 ticipation in the Ranger 4 mission. Using C-1 doppler cycles/sec which could not be accounted for. In a subse- data taken during this pass, the capsule beacon frequent discussion with T. W. Hamilton, it was discovered quency drift was estimated to be 1.54 cycles/min.

8 JPL TECHNICAL REPORT NO. 32-523

111. FINAL ORBIT

Table 3. Summary of data used in orbit determination (see Ref. 1)

Station Data types

DSlF 1 2-way MOBILE TRACKING STATION doppler

Hour Angle, DSlF 4 WOOMERA Declinotion

2-way

DSlF 5 doppler JO'BURG I Declination

The final orbit of the Ranger 4 spacecraft was deter- vectors at injection epoch which minimized the sum of mined from the DSIF transponder data only. Data types the squares of the residuals (observed values minus com- included two-way doppler, and angular tracking data puted values). Hence, the accuracy of the determined taken in either Ghl-1, GM-2, or GM-3. Prior to use in orbit will depend on the statistics of the tracking noise, the ODP, the angular data was corrected for the known and the statistics of all other error sources such as errors antenna pointing error which was determined from op- in the physical constants and/or station locations. The tical star tracks and inflight data taken during Ranger 3. possible errors in the spacefixed Cartesian coordinates at Coefficients describing the error may be seen in Appen- reference epoch due to tracking data noise are given in dix C. A summary of the data used in the final orbit Table 5. These errors or uncertainties were then mapped determination, by station and type, is given in Table 3. into the target area using the miss vector B. Conclusions Both the computed root-mean-squared noise (RMS) and were that the final orbit was accurate to within a 22-km the mean of the residuals for each station is given in 1-sigma circle in the B plane and 33 sec in linearized Table 4. time of flight (see Ref. 1).The final orbit was verified by

The JPL Ranger orbit determination program was designed to find, or converge on, the position and velocity

Table 4. Tracking data noise statistics (see Ref. 11 Vector Component Error

Fation I Data types Position X 0.290 km Y 0.384 km 0.676 km DSlF 1 2-way doppler 703 0.639 cpr -0.005 cps 2

DSlF 4 Hour angle 35 0.009 dcg -0.001 deg Declination 35 0.007 deg -0.002 deg Velocity X 0.648 m/rec

0 DSlF 5 2-woy doppler 377 0.078 cpr -0.002 cpr Y 1.242 m/rec

Hour angle 71 9 0.020 deg -0.002 dag 0 Declination 71 9 0.01 2 deg -0.002 deg 2 2.225 m/rec

9 JPL TECHNICAL REPORT NO. 32-523 using the C-1 data taken by DSIF 3 during the occulta- found in Ref. 1. Appendix F contains a listing of the tion pass. residuals (observed minus computed) upon which the above statistics were based. The converged injection con- A complete discussion of the uncertainties due to errors ditions from the final orbit determination may be seen in in the physical constants and the miss parameters may be the trajectory listing in Appendix D. JPL TECHNICAL REPORT NO. 32-523

APPENDIX A

DSIF and Spacecraft Characteristics

Table A-1 . DSlF characteristics for Ranger 4

DSlF 1 DUF 2 DSlF 3 DUF 4 DUF 5 (Mobile hacking Pionm Sh, (Echo sib, stotion) Goldstone) Goldstono) (Woome-) (Johonnosburg)

1. Antenna type Az-EL HA-DEC Az-EL HA-DEC HA-DEC 2. Antenna diameter ion 85 55 ft 85 fi 85 n 3. Maximum angular rate 40 deg/sec 1 deg/secHA 2 deg/sec 1 deg/recHA 1 deg/secHA 0.8 deg/rec DEC 0.8 deg/sec DK 0.8 deg/sec Mc 4. Antenna gain (960 ME) 22.2 db 43.5 db 43.5 db 43.5 db 43.5 db 5. Receiver noise figure 6.3 db 0.6 db 1.8 db 1.8 db 1.8 db 6. Transmitter power 25 w -- 200 w -- 200 w 7. Command capability no no Yes no Yes 8. Nominal receiver frequency 960.05 Mc 960.05 Mc 960.05 Mc 960.05 Mc 960.05 Mc 9. Loop noise bandwidth 20 cps 20 cps 20 cpr 20 cps 20 cpr at threshold 10. Threshold -1 55 dbm -1 62 dbm -162 dbm -1 62 dbm -1 62 dbm 1 1. Modmum input signal level -45 dbm -65 dbm -65 dbm -65 dbm -65 dbm 12. Doppler resolution a. Two-way 0.17 m/sec 0.1 7 m/sec b. Pseudo two-way -- -- c One-way 0.34 m/sec 0.34 m/sec 13. Data transmission a. Angles-doppler real time real time real time real time real tima b. Engineering telemetry near real time none near real time none near real time 14. Recorded telemetry Yes Yes Yes yes Yes

Table A-2. Doppler reference frequencies used at the DSlF stations

DSlF Reference froquency I don 1 One-way operation: 31.0050 MC Two-woy operotion: see footnote b 2 31.0100Mcc 3 One-way operation: 31.0050 MC Two-way operation: see footnote b 4 31.0100 McC 5 One-woy operation: 31.0050 Mc’ Two-woy operation: see footnote b

aObtained in th receiver using 31.oooO Me from the Gertsch frequency multiplier and the 5.0 kc bias fn- quency. bThe referen- frequency is obtained from the transmitter VCO and the 3.33 kc bias frequency. CObtained from the Gertsch frequency muhipliar.

11 JPL TECHNICAL REPORT NO. 32-523

r ------I TAPE 960-MC TRACKING

L -_--____-I IO-ft AZEL I I I I I TO DATA 25-w I HANDLING TRANSMITTER I I ! TELEMETRY I I vco I I I I DISCRIMINATORS (9 CHANNELS)

ENCODERS RECEIVER TELEMETRY ACQUISITION I DECOMMUTATOR 1 PANEL I aow 3-DIGIT ACQ UlSlTlON J-g, PRINTOUT I DATA I

RECEIVER ANALOG (PRECISION) 1 TIME

Fig. A-1. Mobile tracking station (DSIF 1)

I I W a > V La w WIDEBAND -I= * RECORDERS W 960.05 Mc OSCILLATOR TELEMETRY I-

TO TELEMETRY, DISCRIMINATORS DECOMMUTATOR, AND ENCODERS AT THE ECHO SITE VIA MICRO- WAVE LINK

Fig. A-2. Goldstone Pioneer Site (DSIF 2)

12 JPL TECHNICAL REPORT NO. 32-523

85-11 AZ-EL 960-~~ DATA HANDLING ------TRACKING ANTENNA ANGLES PRECISION PARAMETRIC PRECIS ION RECEIVER DIPLEXER b&i 1-1 DOPPLER DOPPLER AMPLIFIER ITIME GENERATORI L---T7---I I U A !U j I I I ------,s AZ ANGLE -- ENCODERS v vc 0 960.15-MC BIAS W IDEBAND 200-w 960.05 Mc OSCILLATOR TELEMETRY TRANSMITTER

RECEIVER 2 -WAY t ACOUlSlTlON DOPPLER vco AND PANEL FREOUENCY - 890.046 Mc - CONTROL # TAPE TO SPECIAL TRANSMITTER TELEMETRY VIDEO RECORDERS SCIENTIFIC OISCR IMINATORS DEMOD ACOUlSlT ION (2) EOUIPMENT TELEMETRY

ANALOG RECEIVER RECORDIN G TELETYPE TELEMETRY

RWV + COMMAND - I UNIT

Fig. A-3. Goldstone Echo Site (DSIF 3)

13 JPL TECHNICAL KkYUKI NU. YZ-3ZY

85-ft HA-DEC ANTENNA

960-MC TRACKING

AMPL I FI E R I FEED I

TAPE I WI DEBAND I RECORDERS 4 (2) TELEMETRY I I TELEMETRY I I TEST -1 I TAPE I I t I I TELEMETRY I DISCRIMINATORS I I I 960.15-Mc BIAS I OSCl LLATOR I I I I ACOUlSlTlON I RECORD PANEL I I I I I I DATA HANDLING 4 DOPPLER I SYSTEM I ANGLES I I DOPPLER HA TIME 4 ANGLE GENERATOR ENCODERS

Fia A-4. Woomera tracking station (DSIF 4) JPL TECHNICAL REPORT NO. 32-523

85-ft HA DEC 960-MC r------i TRACKING PARAMETRIC DATA HANDLING DIPLEXER ANTENNA ANGLES - AMPLIFIER - PRECISION I DOPPLER A I I I I TIME GENERATOR L------J I A HOUR ANGLE ANGLE DECLINATION ANGLE ENCODERS

960.1 5-M c

RANSMITTER RECEIVER

PANEL DOPPLER AND e vco FREOUENCY 890.046Mc I, i CONTROL p=qDISCRIMINATORS I ACOUISITION 1 PANEL 1

ENGINEERING ANALOG DATA 1 (36RECORDING CHANNEL) ~~~~~~I~RY TELETYPE 3-DIGIT ENCODER PRINTOUT S6E AND I TELETYPE I AGC DISPLAY] I I RWV 1 4 I TELETYPE

Fig. A-5. Johannesburg tracking station (DSIF 51

15 JPL TECHNICAL REPORT NO. 32-523

QUASI OMNl dc-dc dc BATTERY REGULATOR DIRECTIONAL ANTENNA CONVERTER +0.5 db GAIN

~~ DETECTOR I I

COMMAND PHASE IF MIXER a su Bc A R R IE R S- DETECTOR * AMPLIFIER a

960.05Mc FREQUENCY TRANSPONDER, MULTIPLIER RECEIVER AND TRANSMITTER RF t AMPLIFIER

I I RF +34.8 i .DRIVER 'xbrn RF PHASE FREQUENCY SWITCH OSCILLATOR SWITCH M0 DUL AT0 R MULTIPLIER HIGH-GAIN +34.8 4 dbm ANTENNA EXCITATION TRANSFER TELEMETERING SIGNAL SUBCARRIERS 3w ------_ - _ - _ _ r------j COAXIAL CABLE j RF RG 87A/W AMPLIFIER POWER MONITOR I ; LENGTH2 1/2in. I LENGTH 2 1/4in. LOSS 0.2 I LOSS 0.3db I LOSS 0.2 I

Fig. A-6. Spacecraft communications system

16 JPL TECHNICAL REPORT NO. 32-523

APPENDIX B

Equations Used in Data Evaluation

TIK. following equations, by T. W. Hamilton, are used Definition of symbols in-flight c.valnation of the two-way doppler data: fRC = received frequency

,P (.’-\v;iy doppler) = (0.40)? ft = spacecraft transmitted frequency

u = radial velocity component. ul spacecraft to DSIF station. u2 DSIF station to spacecraft

\\-11crc c = speed of light

fi? = doppler system figure of merit ( 1 A :) = doppler term, spacecraft to DSIF station R = slant range of spacecraft in km T,. = doppler averaging time ( 1 & -:) = doppler term, DSIF station to spacecraft T,*= sample interval fL. = receiver 31 mc VCO frequency

The first term on the right is an estimate of the variance fK = transmitter 29.66 mc VCO frequency due to gaining or losing a cycle in either the ground rcIcei\,er or the spacecraft receiver in a random fashion fl = 30.5565 mc bias oscillator frequency due to noise, and noise on the signal due to the trans-

mission medium. The second term is an estimate of the f2 = 455 kc oscillator frequency (0.455 Mc) variance due to doppler counter round-off, and the third term is the variance due to transmitter reference oscilla- F~ DSIF 1 tor drift. The equation used to compute g’ is given by: One-way transponder tracking at 960.05 Mc:

B* = 1.4 X 10-ls sec-’ 01 30 :. f,( 14 T) = 3ofv + - 292/3 fR f7= transmitter VCO frequency

Ttot= time interval over which E( Afr)’is Two-way transponder tracking at 960.05 Mc: I determined 30 30fv + -29 2/3 fR The following equations relate the received frequency, the frequency transmitted from the spacecraft, the doppler shift, and the receiver VCO frequencies. 29 2/3

17 JPL TECHNICAL REPORT NO. 32-523

assume v, = u2,then For DSIF 3 and DSIF 5.

One-way transponder tracking at 960.05 llc:

and

fl, = fll[29 2/3 31 - 32 (+)I Two-way transponder tracking at 960.05 Mc:

Pseudo two-way transponder tracking at 960.05 Mc with DSIF 3 or DSIF 5 transmitting: 32 30 f, = -3ofR 1 -+ fK(' = ft (1 * +) = 3% + fK1 29 2/3 ( +) f, = 30f/i, ( 1 +) 32 assume o, = u, then,

where

fl(, = the transmitter VCO frequency of and r DSIF 3 or DSIF 5, then, 1 32 29 2/3 C C 29 2/3 For DSIF 2 and DSlF 4 One-way capsule tracking at 960.25 Mc:

V One-way transponder tracking at 960.05 hlc: ~RC= ft (1 t --) = 30fY + fnl

fwl = fl - f2 then, Pseudo two-way transponder tracking at 960.05 Mc:

The following form of the autocorrelation function is used to determine whether the tracking data noise is of a 32 random nature. ft = -29 2/3 N-k Then, 32 32 29 2/3 C C - xfv where where ri = the ith residual fR2 = DSIF station transmitter VCO frequency N = the total number of data points used

One-way capsule tracking at 960.25 Mc: (2/3 N) = the largest integer in 2/3 N

K = a dummy index related to time; Le.,

th: = (to+ k At), where At is the sample interval

then, p(k) = the autocorrelation coefficient of the kth

fR(' = 3ofv + fl - f2 order

18 JPL TECHNICAL REPORT NO. 32-523

APPENDIX C

Results of Ranger 4 Preflight Calibration Tests

Table C-1 presents coefficients of polynomial repre- Table C-2 presents coefficients of polynomial. repre- senting optical pointing error-used to correct angular senting both optical star tracks and postflight analysis of data for in-flight orbit computations. Ranger 3 and 4. These coefficients were used for Ranger 4 postjlight orbit computations.

Table C-2. Coefficients for optical star tracks and Table C-1. Coefficients for optical pointing error postflight analysis

~~ ~ ~~ Hour angle coefficients Declination coefficienh 1 Hour angle coefficients Declination coefficients

DSlF 4 DSlF 4 I _____~

A00 = 8.5500i 840-03 Boo = i 343091 00-02 = 4.mm87m2 800 = 5.C.5083350-02 A01 = 5.45209422-04 801 = 1.34214922-04 Aoi = 5.45289422-04 801 = 1.34214922-04 Aoz = 2.40249580-06 802 = -1.41100901-05 Aoz = 2.40249500-06 802 = -1 A1 100901 -05 A03 = 2.24566914-07 803 = 0.0 A03 = 2.24566941-07 803 = 0.0 A10 4.271 32078-04 810 = -4.31028233-04 Ai0 = 2.99712960-04 810 -3.23836803-04 All = 8.69504098-06 811 = 3.34771543-06 A11 = 0.69584090-06 811 = 3.34771543-06 Alz = -6.52073317-07 812 = 1.01895206-07 A12 = -6.52074417-07 812 = 1.01895206-07 A13 = -1.59490382-08 813 = 0.0 A13 = -1.59490382-08 813 = 0.0 Azo = 2.5326800246 020 = -9.56363999-06 Azo = -3.541 87980-07 820 = -1 32446178-05 A21 = -7.0951 1508-00 821 = 4.53942058-09 A21 = -7.0951 1500-08 821 = 4.53942050-09 Azz = -7.041 16079-09 822 = 2.09578021-09 Azz = -7.041 16079-09 822 = 2.09578021-09 A23 = -1.23595449-10 823 = 0.0 A23 = -1.23595449-1 0 823 = 0.0 A30 = -0.30262704-08 830 = 0.0 A30 = -1.70066062-07 830 = 0.0 A31 = 1.9051 3740-09 831 = 0.0 A31 = 1.90513748-09 031 = 0.0 A32 = 3.9524031 9-1 0 832 = 0.0 A32 = 3.95248319-10 832 = 0.0 A33 = 9,57751200-12 833 = 0.0 A33 = 9.57751208-12 833 = 0.0

The useful range of these functions is The useful range of these functions is -OoO 5 ff 5 +so9 -35O s 6 s +350 -00O 5 u 5 +00q -35O 5 6 5 +35"

DSlF 5 DSIF 5

A00 = 9.14070200-03 BOO = 2.9860570-02 Aoo = 5.66230510-02 800 = 9.05199500-03 A01 = 1.50520433-04 801 = 1.04434590-04 Aoi = 1.50520433-04 801 = 1.04434590-04 AQ~= 6.24530962-06 802 = -3.64955790-06 A02 = 6.24530962-06 802 = -3.64955790-06 A03 = 3.43042729-07 803 = 2.01030020-07 A03 = 3.43842729-07 803 = 2.01833020-07 A10 = 3.9500951 1-04 810 = 7.39376711-05 A10 4.36034641 -04 8x0 = -6.901 3041 0-05 A11 = 9.36369950-06 811 = 4.55037975-06 All 9.36369950-06 811 = 4.55037975-06 A12 = -3.41 91 3970-07 812 -9.45727640-08 A12 = -3.41 91 3970-07 812 = -9.4572764048 Ai3 = -3.76659061 -09 813 = -7.1 2650861 -09 A13 = -3.76659061 -09 813 = -7.1 2650061 -09 A20 = 4.31922333-06 020 = -9.21 91 0567-06 Azo = 1.03365993-06 820 = -1.071 24020-05 A21 = -1.03537453-00 821 = 5.89778738-08 A21 = -1.03537453-00 821 = 5.09773730-00 Azz = -3.041 87273-09 822 = 3.62001044-09 Am = -3.041 07273-09 822 = 3.62001 044-09 A23 = -1.52368370-1 1 823 = -5.1 6572902-1 1 A23 = -1 252360379-1 1 823 = -5.1 6572982-1 1 A30 = 4.02603978-00 830 = 0.0 A30 = -1 S0618567-07 830 = 0.0 A31 = 6.22459846-10 831 = 0.0 A31 = 6.22450046-10 831 = 0.0 A32 = 1.79924034-10 832 = 0.0 A32 = 1.79924034-1 0 832 = 0.0 A33 = 3.31402952-12 833 = 0.0 A33 = 3.31 402952-1 2 833 = 0.0

The useful range of these functions is The useful range of these functions is

-00" 5 ff 5 800, -35O I65 +35" -00O 5 a s+004 -39 s Q S+35"

19 JPL TECHNICAL REPORT NO. 32-523

Results of the Ranger 4 preflight boresight-vs-polarization-angle test are presented in Table C-3.

Table C-3. Ranger 4 preflight boresight-vs-polarization-angle test

Mean values Standard Mean value Standard Signal DSlF of residuals deviation of of residuals deviation of level, station in AZ/HA, residuals in in EL/DEC, residuals in dbm deg AZ/HA. deg deg EL/DEC, dag

~ 100 --0.013 0.068 -0.007 0.057 110 -0.014 0.069 -0.008 0.056 120 -0.013 0.069 -0.004 0.058 130 0.005 0.066 0.009 0.065

120 0.004 0.003 0.016 0.002 125 0.006 0.002 0.01 5 0.003 130 0.005 0.002 0.015 0.004 135 0.005 0.003 0.016 0.003 140 0.008 0.004 0.016 0.007 145 0.008 0.007 0.01 5 0.009 150 0.017 0.006 0.01 8 0.007

120 0.033 0.01 1 0.048 0.004 125 - 0.020 0.000 -0.056 0.000 130 -0.029 -0.031 -0.053 0.01 6 135 -0.020 0.000 -0.056 0.000 140 -0.01 8 -0.006 -0.016 0.065 145 -0.020 0.000 -0.056 0.000 150 -0.019 -0.003 -0.017 0.065

120 -0.01 7 0.01 1 -0.010 0.015 125 -0.019 0.01 2 -0.007 0.005 130 -0.014 0.01 8 -0.005 0.008 135 -0.010 0.025 -0.008 0.01 7 140 -0.013 0.037 -0.007 0.022 145 -0.016 0.050 -0.006 0.03 1 150 -0.030 0.083 -0.003 0.052

Note: Residuals are defined as the difference between the optical values and the RF boresight values.

20 JPL TECHNICAL REPORT NO. 32-523

HA. deg Fig. C-1. Preflight star track results, April 10, 1962 (DSIF 4)

0.08 SOURCE BETA CORVl .. .** 0.04 ' ** *****..o** ** ****:**"****-* 4 "*a 2****d,***m* *e ** (,* *** *' IJ (1 **.***" *,E*. . ** 00 D .

-0.04

HA, deg

Fig. C-2. Preflight star track results, April 3, 1962 (DSIF 5)

21 JPL TECHNICAL REPORT NO. 32-523

HA,deg

Fig. C-3. Preflight star track results, April 12, 1952 (DSIF 5)

22 JPL TECHNICAL REPORT NO. 32-523

APPENDIX D

Hourly Trajectory Listing From Injection to Impact

Appendix D consists of an hourly trajectory listing from injection to impact. Figures D-1 through D-11 pre- sent doppler and angular residuals.

4.0 2 1)

De m -- u) 2.0 1.0 D - *-a -. G u. a+ 2.' - .t :- > 0 --/r .'C 0 --a (r V h=?%-*-I, z *. *-* *: 11--, w 0 1. =- I ., , $0 a- 3 t - ,, 3 ':8 am-' &a e .*** .-• 8 (L [L LL # ':--.. -a- -1.0 = + La. -2.0 - .- a- .- 1.

- 4.0 -2.0

0.08

I In 004 l a >- 0 ~ I

I> ~ $0O W [L LL -0.04 D I

-008

23 JPL TECHNICAL REPORT NO. 32-523

TIME (GMT)

Fig. D-4. C-1 dcippler residuals (DSIF 2)

TIME (GMT)

Fig. D-5. 30-Mc bias OSC frequency (DSIF 2)

24 JPL TECHNICAL REPORT NO. 32-523

0.08

0.04 0 d 0 &: &: ngo cc n 8 -0.04.

1 -0.08

iiA, deg

Fig. D-7. Angular residuals vs hour angle (DSIF 4)

HA. deg

Fig. D-8. Angular residuals vs hour angle (DSIF 5)

25 JPL TECHNICAL REPORT NO. 32-523

0.08

0.04 -

m U0 4 do I J 0

-0.04.

-0.08 0.08

0.04

0 u d 0 W n n

-0.04

-0.08 290 300 310 320 330 340 350 0 IO 20 30 40 50 60 70 80 70 100 HA, deg Fig. D-9. Angular residuals vs hour angle (DSIF 5)

1.00 . . 0.80 . .

0.60

I I I I v) 0.40 n 0

-0.6 01 I I I I 00:00:51 01:00:51 02:00:51 03:00:51 0400:51 05 TIME (GMT)

Fig. D-10. C-2 doppler residuals (DSIF 5) JPL TECHNICAL REPORT NO. 32-523

TIME (GMT)

Fig. D-11. Pseudo two-way doppler residuals (DSIF 5)

27 JPL TECHNICAL RtPWRl

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29 JPL TECHNICAL REPORT NO. 32-523

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31 JPL TECHNICAL REPORT NO. 32-523

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32 JPL TECHNICAL REPORT NO. 32-523

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33 JPL TECHNICAL REPORT NO. 32-523

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35 JPL TECHNICAL REPORT NO. 32-523

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37 JPL TECHNICAL REPORT NO. 32-523

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39 JPL TECHNICAL REPORT NO. 32-523

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41 JPL TECHNICAL REPORT NO

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43 JPL TECHNICAL REPORT NO. 32-523

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JPL TECHNICAL REPORT NO. 32-523

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47 JPL TECHNICAL REPORT NO. 32-523

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49 JPL TECHNICAL REPORT NO. 32-523

0 0 0 v) om 0 w ow . e .I- 6 d ma 4 -z dZ 4 - 0 40 0 ez 0 00:u In 0 90 0 u ou mNNqtv m -I 00000 0 d N -.I r- 9 ez 0, m 0 9 d I- 9 . a 9u In In 3 In3 0 N c3 NU- m w w N -I ...... w I e! a. 4

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51 JPL TECHNICAL REPORT NO. 32-523

m 0 ON~-INN~~N N 0 v) OOOOOOOOQ w I1 9 I- NU*Y~~~*NOD 6 a Od..IOInlnd** d z ..I~,~~.c~NIcN n m;+oornrnr;iniri * 0 0 lY 0 0 0 0 u mcuwrnm m rnNNmN m -I m 00000 0 00000 0 4 0 I I N - N In@+OOD U 9 Lz .* 0 drnr-rn0 * a m N momNm f d I- 6 *e400 9 L a rn rn001m9 * M 3 N I-OhOW 0 N a 0 mmmor- 6 W N NddNN N A ...... n I Lz n 4 4 4 a Lz n n

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53 JPL TECHNICAL REPORT NO. 32-523

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54 JPL TECHNICAL REPORT NO. 32-523

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55 JPL TECHNICAL REPORT

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57 JPL TECHNICAL REPORT NO. 32-523

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JPL TECHNICAL REPORT NO. 32-523

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59 JPL TECHNICAL REPORT NO. 32-523

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61 JPL TECHNICAL REPORT NO. 32-523

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9 0 ONclldrlrldNN m 0 v) 000000000 0 Ly . c ?) a rl z w 0 0 (z 0 rl 0 0 u mrlNmN m ~d~mmm -1 mrlNmN rn 00000 00000 0 a 00000 0 I I N U I nmm+m m mer-crm d 9 (z mslcmo 0 mmmsc m d 0, 0 lce~clm0 N m d C olcmmm 0 m t- c 4 er-mmc 0 m 0 9 2 amumm -? m !n N GI au9Nc -7 QQOOU m UOInOlc m (Y ammom 41 NQNN- N @lcdNd N d NS~N~N ...... - ..... e I I rz I n a a 4 a a a2 n n a.

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63 JPL TECHNICAL REPORT NO. 32-523

I- 0 o~rn44-1~~~ m 0 000000000 0 e. 4 * 0 N 0 m m4NmLw m NrtNmm m 0 00000 0 00000 0 N e 9 U r- 0 e VI N e rl W ln W .. IC In m 9 a0 * N $ U 0- o, * N d N fu I ..e.. . ac I a a a 4 a rr d Y a n. a.

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v)> 4 a n 'AI N I/) Q L) JPL TECHNICAL REPORT NO. 32-523

m 0 Ohlmdddd" a m 0 v) 000300000 0 v) 0 W 0 w c I L m a m 4 d 2 -I X U " J n J 0 0 cr: 0 a 0 0 m 0 J 0 0 U 0 V -I *.I Nrld*!n m -1 4 0 00000 0 4 N Y N 3 9 P I- 9 5 m 0 + 6 0 rr c OD 4 c . 4 d . 4 9 3 9 9 3 ON-INOO~~N N 3 m N z1 o3oooooco w e W -I N -I 3 ...... c1 o! I cz a a 4 4 a z n

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65 JPL TECHNICAL REPORT NO. 32-523

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v) v) 1 2 I I m m U .n: v)- tcz tY d uc d a+ 02 oz w w w NU NU v) 0 0 4 w Lu JPL TECHNICAL REPORT NO. 32-523

U I w mNY100OQ u 7 NI-~~ODON U c a o r-~r-rnr-om '-. a ez o a~uo*om z 0 c m.nummo~ 0 0 maN+.nom u z u1 o 011+mdr-00 e u ONdmNdNOd I a 00.. 0 ..... v)

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67 JPL TECHNICAL REPORT NO. 32-523

I I

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m 9 b OI OI h r- m. 0 Llrn-!arn4 fl m ~tnwanu~ UJ I- o~nnov)mu * b z X U m 0 a~mud~0.aU -IN~VIO~O.O 2 0000000 N 0000000 V I Y UO.inUlOOQ W 7 ooo-lmoin I- a a ~mmr~a.~s~d a D c 000000000 0 muoGm6m z 9 Lu o n.+mr+.i+ao 4 .+ V o~~maa~ocr I m a 00...... 2 0 3 IA 8m' 7 =om -.. Oi mod 04 om mm~cwon~ suYorXu4 ~mnunocczu am vl cd I- m m N 9 N 0- d A .mm~.o~om z 0 0 0 0 0 00 I0000000 I 1 I a m h N 0 0 00 o*.(-(m000 n d N m m u 04 QNN~~QNQ~w dno~uoin m N 9 VI VI 00 003000000 IC OI~~+-YIOV\ 2 9 u In u 9 om 3 mtur(mao* c N 0 9 I- d O* u inu.+m~~mmoI-cmo.odr(04 c.l N U r- O 4 OVI Lu ur-*OImd0uI c cz) m 4 9 In OVI v) Iao'md9-YIOln Q N N U m m 94 e ~~l+mmod c . . . e . .. 0 0 IA ...... I 0 U I 0 -z 0 N

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69 JPL TECHNICAL REPORT NO. 32-523

m 0 0 u 0 0 0. 0 6 O1 d d .t u 3 0 - 0 o ~fi~mmm.+~.% d d u ...... d I I mrl~mrn m 00000 0 N I N 9 "+NO u 9 6 6 d d L L 9 9 N N

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70 JPL TECHNICAL REPORT NO. 32-523

In omm4444m~ o -I rn J .n 000030000 VI 003 II W II ~wmmc~m~om c 0.04. 4 oom z 066 CI OIc\r- a osm cz ON4 0 OWVI 0 om4 V e.. moNmm m -1 00000 0 a hlwa I CI b.EO mmesr- m cf z ~mmw9m 0 r-mowm N c Odrnr-w m a N\+L~V\C m 2 OOf 0 30r w W I 466 6om oom Icsm mmm mnm Q14-L 9JN .....we. 1 I crm~mm99 uo3>>>>0 mooom003 anaacf CI5 0 I aatx 0

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I- I (3 cz 3 L) c1 U cf LL..... 4 1 I- 01 II LY z W Lu !& W u m z 0 4 4 0 W U d 0 I3 JPL TECHNICAL REPORT NO. 32-523

9 of-m N V\U~~~OONC)OHU m U 003 0 VI NO00303300 0 0 Lu m 4.00 9 c U d mr-w U a + 0 tnUU 0 z ?) 0 l-4.4 r- w N 9 om4 d 0 OD W md9 U LL N m mtnl- m 0 0 In mNN m 0 m N 0.. . u . . I 2 NNCf 0 4 N u aaN v) CI x t Q a LL w 0 I- a dNN d 3 m 4 005 0 3 3 0 I u ~r-m0 l- m dmcr m (c 9 ~m-rU d N l-Ud m U 0 tnbN m U N +l-l- 0 m r- mm* m l- N clmm l- m N 40 ... . UO Ill I tnO 40 >XP n d v) v\O 9l-c n I c no w e0$8 4.0 mo m m 00 0 0 90 N N 0 U N 0 0 0 U U ul 0 9 9 l- In N Q 9 U + 4 VI . m Lu 9 w U rz 0 W m 0 a t 0 t m Lu 9 V u V mmmdmm c.l lno 000000 2 IO c 0 tno V r-m Lu U 2; a 9 n N .n 4 U X 0 ...... 9 I I

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c N e( V U 0 I tn a Y * U 3 z- ln .? u LL ...... U d I U 01 IIIII I II U cz 0 'c 4J z W 0 W 5 VI z 4 9 a Q w V P VI

73 JPL TECHNICAL REPORT NO. 32-523

APPENDIX E

History of Ground Modes and Transmitter VCO Frequencies

Table E-1 consists of a history of Ranger 4 DSIF tracking by station, date, and ground mode.

Table E-1. Ranger 4 DSlF 4 tracking

Station Date Ground Mode From, GMT To, GMT Station Date Ground Mode From, GMT To, GMT

DSIF 1 23/24 April GM-1 21 :25:52 23:05:00 DSlF 2 25 April GM-4 08 :47:30 09:30:00 GM-3 23 :07:00 23:36:00 Searched for 09:31 :20 1o:oo:oo GM- 1 23:40:00 00:06:00 transponder GM-3 00:07:34 07:23:00 GM-4 10:00:09 13:OO:OO Searched for 13:00:17 13:30:00 DSlF 5 GM-3 21 :14:37 23:05:43 transponder GM- 1 23:07:55 23:36:00 GM-4 13:31 :39 17:30:17 GM-3 23:39:54 00:06:00 Searched for 17:30:18 17:48:20 GM- 1 00:07:54 02:40:00 transponder GM-2 02:40:55 02:41 :32 14:23:00 15:03:00 GM-1 02:42:00 07:2 1 :50 DSlF 4 25 126 April GM-4 15:03:32 GM-4 08:14:30 08:43:20 Searched for 15:33:37 transpander DSlF 4 GM-3 22 :2 2 :oo 22:40:00 GM-4 15:35:08 19:56:42 GM-4 22:43:00 23:OO:OO DSIF 4 25 126 April Searched far 19:59:26 20:30:00 GM-3 23:OO:lO 23:35:00 transponder GM-2 23:36:04 23:37:00 GM-4 20:30:35 01 :27:55 GM-3 23:38:36 00:06:00 Searched far 01 :30:00 02:OO:DO transponder DSlF 2 24 April GM-4 08:32:40 17:03:13 GM-4 02:Ol :50 02 :13 :06 DSlF 3 GM-4 09:00:40 12:28:57 DSlF 5 GM-4 21:40:13 23 :07:00 Searched for 12:30:05 13:04:00 Searched for 23:08 :00 23 :3 8 :00 transponder transponder GM-4 13:05:00 15:25:00 GM-4 23 :3 8 :00 03 :OO:OO 16:OO:OO Searched for 15:30:00 Searched for 03 :03 :00 03:32:00 transpander transponder GM-4 03:33:00 07:OO:OO DSIF 3 24 April GM-4 16:04:00 17:04:40 Searched for 07:00:30 07:30:00 transponder DSIF 4 24 125 April GM-4 13:52:44 15:00:00 07:30:00 09:32:08 Searched far 15:OO:OO 15:31:55 GM-4 transponder DSlF 3 26 April GM-4 08:33:00 09:52:00 GM-4 1538 :47 18:23:00 Searched far 09:52:00 10:25:00 Searched for 20:00:00 2 0:3 0 :00 transponder transponder GM-4 10:25:00 12:47:54’ GM-4 20:31 :21 01 :oo:oo Searched far 1 2 :47:54 13:31 :00 Searched for 01 :20:00 01 :30:00 capsule transponder GM-4 01 :3 1 :00 01 3839 DSlF 2 GM-4 08 :46:00 09:40:50 Searched for 09:4 2 :00 09:47:42 DSIF 5 GM-4 21:21:35 06:20:00 transponder Searched far 06:20:00 06:50:00 GM-4 09 :48 :40 12:47:47‘ transpander Searched for 12:47:47 13:32:10 GM-4 06:50:00 09:25:1 1 capsule

‘Loss ai signal at lunar occuhation.

74 ~

JPL TECHNICAL REPORT NO. 32-523

Table E-2 consists of a history of the transmitter VCO frequency during the transponder tracking period.

Table E-2. Transmitter VCO frequencies

Station lime, VCO frequency, Station lime, VCO frequency, Date transmitting GMT cPs transmitting Date GMT CPS

~ DSlF 1 23 April 21 :30:00 29660226.0 01 :10:00 29660599.0 21 :35:00 29660227.0 01 :20:00 29660590.0 21 :40:00 29660227.0 01 :30:00 29660597.0 21 :45:00 29660227.0 01 :40:00 29660596.0 21 :50:00 29660226.0 01 :50:00 29660601.4 21 :55:00 29660226.0 02:00:00 2966061 3.1 22:oo:oo 29660226.0 02:10:00 2966001 2.0 22 :05:00 29660226.0 02:20:00 29668017.0 22:lO:OO 29660225.0 02:30:00 2966001 8.0 22 :1 5 :00 29660225.0 02:40:00 29660056.0 22:20:00 29660225.0 02:50:00 29660056.0 22::s:oo 29460225.0 03 :OO:OO 29660060.0 2 2 :30:00 29660225.0 03:lO:OO 29660861 .O 2 2:35:00 29660226.0 03:20:00 2966801 1 .O 22:40:00 29660225.0 03:30:00 2966001 1 .O 22:45:00 29660226.0 03 :40 :00 2966801 2.0 22:50:00 29660220.0 22:55:00 29660220.0 DSlF 5 24 April 03:50:00 2966001 2.0 23 :OO:OO 29668228.0 04:OO:OO 2966801 1 .O 23:OS:OO 29660220.0 04 :1 0:OO 2966801 1 .O 04:20:00 2966001 2.0 DSlF 5 23:20:00 29660224.0 04:30:00 2966001 2.0 23:25;00 29660224.0 04:40:00 2966801 1 .o 23:30:00 29668224.0 29660264.2 23:35:00 29660225.0 05:10:00 05:20:00 29660264.1 DSlF 1 23 :40:00 29660203.0 05 :30:OO 29660264.0 23 :45 :00 29660203.0 05:40:00 29660264.0 23:50:00 29668203.0 05:50:00 29660263.0 23 :55:00 29660204.0 06:OO:OO 29660263.0 24 April oo:oo:oo 29660 203 .O 0.51 0:OO 29660263.7 29660204.0 00:05:00 06 :20:OO 29660263.7 DSlF 5 00:10:00 29660590.0 06:30:00 29660263.5 00:20:00 29660600.0 06:40:00 29660263.6 00:30:00 29660601 .O 06:50:00 29660263.3 00:40:00 2 966 0 600.0 07:OO:OO 29660263.3 00:50:00 29660600.0 07:lO:OO 29660263.3 01 :oo:oo 29660599.0 07:20:00 29660263.3

75 JPL TECHNICAL REPORT NO. 32-523

APPENDIX F

Final Orbit Residual listing

This Appendix consists of a listing of final orbit residuals.

76 JPL TECHNICAL REPORT NO. 32-523

00 0;o0 040 010 0 0 0;o 00 010 0 0 010 010 0 0 0:o 00 0'0 0 0 ok 010 0 0 010 09 0lo000~00:o 0 0 010 .f. 0;. .I . .!. .. . I 1 I I ,I I I ,I I I I ! I 00 o~oooopoio 00 010 0 0 ob 0'0 00 om 0 0 PI0 010 i I 00 olo oio OJ: 00 010 o*o0 0 00 of0 ooao00 IO0 010 !OO 010 00 0 00 010 io0 010 00&j2J .93 010.I . I -9 rule Od Nlr- om *IO 919 *Id.I .. I& I jl ! I i I ! "" r.J" "1" dlrl ;e9 9'9 .oo oio 414 PO m mm .or. I'N 10- ob PI* "1" .9 9 rclr- #om 01o Pdc(.. dld.I I 00 olo 0 0 olo 00 010 0 0 019 010000'0 00 0'00 0 0'0010 000l0 00 O!OO:O0 0 0:oOb 0 0 O!O .j. Si? ...... I .. I 'I' *:-* ! #/ I i f I j ! I OooOoOOOoIO0,0OOOOO00oO~oOmOOOpw0000pOOOOO~0i 4 i 010 ojo .io.. 01 0 010 0 0 oio 010 0 0 0'0OoO'OOOOO0:0OOOOOOOOOO010OO0~0O 00000 oooooto 01 0 0;oof0 0;o 010 010 0:o0 0 0'00 0 0 0 010 0 0 0 0 0 0 0 0 0 0 olo 0 0 0 0 OE om00 ob00 0 b O!O c------'--uu---'------XOOOOOOOOO~OOOOOOOOOOOOOOOOOOOOOOOOOOOOOOQOOO~O~OOO~~~~~~~0 0 00100 0000 00 0 0 00 00100 0 0 0 00 0 0 00 0'0000'00 omow 0 ~00090'00000000~000000000000l0000000000000000b07°ovool 00000 000D00 ry 0'00 0 0'000 010000/00 0 0 0 00 0 00 0 0 0080 0 0 0 0 0 0 0 0 010 00 0 0 0 ouomu 010 0 00'0 Y 010 0'0010 oto 010 0'0 010 0 0 0 0 0 0 0 0 0 0 010 0 0 0 0 0 0 0 0 0 0 0 0 00 op 0 0 k 0 0 OF3 0 0 0 b 010 . .I...... ,e...... I/ I i 0 0 0100 0 0 0 0 0 0 0 0 0 0~000 0 0 0 0 0 0 0 0 0 K 00 00 0 0 'ppdoolo 0;o 0:oO~o oiooo 0:o 010 OB D 0010 000 0 OiO 0100 0 0 0 0 0 o

JPL TECHNICAL REPORT NO. 32-523

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79 JPL TECHNICAL REPORT NO. 32-523

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81 JPL TECHNICAL REPORT NO. 32-523

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82 JPL TECHNICAL REPORT NO. 32-523

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83 JPL TECHNICAL REPORT NO. 32-523

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JPL TECHNICAL REPORT NO. 32-523

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85 JPL TECHNICAL REPORT NO. 32-523

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87 JPL TECHNICAL REPORT NO. 32-523

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89 JPL TECHNICAL REPORT NO. 32-523

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90 JPL TECHNICAL REPORT NO. 32-523

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91 JPL TECHNICAL REPORT NO. 32-523

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93 JPL TECHNICAL REPORT NO. 32-523

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95 JPL TECHNICAL REPORT NO. 32-523

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97 JPL TECHNICAL REPORT NO. 32-523

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99 JPL TECHNICAL REPORT NO. 32-523

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101 JPL TECHNICAL REPORT NO. 32-523

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103 JPL TECHNICAL REPORT NO. 32-523

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JPL TECHNICAL REPORT NO. 32-523

1. Hamilton, T. W., W. L. Sjogren, W. E. Kirhofer, J. P. Fearey, D. L. Cain, The Ranger 4 Flight Path and Its Determination From Tracking Data, Technical Report No. 32-345, Jet Propulsion Laboratory, Pasadena, September 15, 1962.

2. Stoller, Floyd W., Investigation of the DSlF 85-Foot Antenna Strudural Deflec- tions Caused By Deadload and Thermal Inputs, Technical Memorandum No. 33-94, Jet Propulsion Laboratory, Pasadena, August 7, 1962.

3. Ranger 4 Tracking Information Memorandum 332-14, EPD-63, Jet Propulsion Laboratory, Pasadena, March 26, 1963. 4. Space Flight Operation Plan, Ranger 4, EPD-74, Jet Propulsion Laboratory, Pasa- dena, March 12, 1962.

5. Ranger 4 Tracking Operations Memorandurn 332-1 I, EPD-137, Jet Propulsion Laboratory, Pasadena, March 8, 1963.

6. Space Flight Operations Memorandum, Ranger IV, EPD-91, Jet Propulsion Lab- oratory, Pasadena, July 5, 1962.

107