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DISCOVERER 1.•

LAt7NCIN REPO NIT

Agena 1110 /Thor 322

4.AUGU ST 1961

DOWNGRADED AT 3 YEAR INTER

VALS; DECLASSIFIED AFTER

12 YEARS

DOD DIR 5200.10

;AI

Satellite Systems Division

vri'Mfrfl; 6565th Test Wing

- Vandenberg Air Force Base

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LOCKHEED AIRCRAFT CORPORATION

11•111116SHEEl

EMSC 445936-10 /61-70

Copy No.

Sheets

DISCOVERER

LAUNCh REPORT

Agena 1110./Thor 322

DOWNGRADED AT 3 'fan is .

SIOAINNED AM 12 WM

IMO MOM 5200.10.

66m ST WING

VANDENBEE3 AIR FORCE BASE

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MISSILES rod SPACE DIVISION
145936-W61-7o

PREFACE

Discoverer Launch Report 1110/322 presents the launch evaluation,

analysis, and documentation of the launching of the twenty-seventh

Discoverer system flight tested frms Vandenberg Air Force Base. The report

is prepared by the Flight Test Evaluation Staff for the Satellite Systems

Division of the 6565th Teat Wing (Development)(ANC) at Vandenberg Air lbrce

Base. Contributions to Section IV', Thor Systems Analysis, and Appendix C,

Thor 322 Preparation History, were made by base operations of Douglas Aircraft Company: Agena documentation in the appendix vas contributed by base

operations of Lockheed Missiles and Space Company, who also provide reproduction and distribution of the report.

Launch data for the analysis was furnished, by the following organizations:

Lockheed Missiles and Space Company (LMSC) -- primary tracking and

telemetry data and blockhouse landline recordings.

Douglas Aircraft Company (DAC) -- analog records of first stage

telemetry.

Pell Telephone Laboratories (BM) command guidance radar plotboard

chart, tabulated command guidance events and values.

Pacific Missile Range (PO) -- metric optic and FPS-16 radar tabular

position data, missile flight safety plotboard charts, first

stage telemetry, and radiation interference monitoring record.

1st Strategic Aerospace Division, USAF .-immatAhar data and engineering

surveillance and documentary photography.

ii

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TABLE OF CONTENTS •

Page

LAUNCH SUMMAR7f 1

REMEDIAL ACTION 3

LAUNCH EVALUATION 4

Agena Performance

Countdown and Thor Performance

IV. THOR SYSTEMS ANALYSIS 17

Guidance and Control 17

Propulsion System 19

C. Electrical Power System. 19

D. Hydraulic System 20

E. Instrumentation 20

F. Ground Support Equipment 20

V. RANGE SUPPORT 21

A. Metric Optics 21

B. Metric Radar 22

C. PMR Telemetry.. 22

D. Missile Flight Safety 22

E. Radiation Interference Control 23

F. Meteorology 23

Engineering Sequential Photography 24

Documentary Photography 24

APPENDIX

A. Glossary of Technical Terms 25

B. Discoverer 1110/322 Weight Breakdown 27

• C. Thor 322 Preparation History 26

D. Agana 1110 Preparation History 30

E. Pad Countdown and Flight System Check 31

F. Discoverer Launch Data Digest 33

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11413C 4593640/61-70

LIST OF TARIM;

Table

1 Discoverer XXVII Coimtdown Criteria and Performance

Evaluation 6

2 Thor 322 Criteria and Performance gvaluation 13

LIST OF naernaroNs

• Figure Page

1 Discoverer XVII velocity and Trajectory 16

2 Simplified Schematic Diagram of Thor Pitch Attitude

and Bate Loops 18

iv

LOCKHEED AIRCRAFT CORPORATION SPACE DIVISION
MC 445936-106140

DISCOVERER LURCH REPORT

AMNIA 1110/THOR 322

I. LAMM EREIMARC

Discomm7OOMI (Agena 1110/Thor 322), ommposed of an Agensea

.satellite (Model 6205) and a Thor booster (Model DK.21) was launched

from Complex 77-3, Pad 4, Vandenberg APB at 1535:00.46 PDT on 21 Jay

1961. The primary launch objective -- to place the Agena, equipped

with a recoverable Advanced Engineering Test (AZT) capsule, into near

polar orbit -- was not achieved: the vehicle destroyed itself after

approximately 60 sec of flight as a result of a Thor control malfunction

which caused divergent pitch oscillations to develop, exceeding the

structurel‘limits of the vehicle. The cause of the malAniction is

attributed to an open in the Thor flight controller pitch-rate loop.

The events leading up to the destruction of the vehicle and postdestruct phenomena are tabulated below.

TIME FROM

pirrarr (sec) EVENT

0 Liftoff. 1535:00.46 PDT. Vehicle pitch oscillation

started.

30 Agena normal acceleration due to pitch oscillations

reached peak levels of +0.3 g.

40 Agena normal acceleration peak levels decreased to

+0.1 g.

48 Agena normal acceleration predominately negative with

peak levels between -0.8 g and -0.25 g.

57.5 Magnitude of Agena normal acceleration started. increasing rapidly.

59.2 Magnitude of Agena normal acceleration reached g

and continued increasing beyond. the accelerometer

calibration. Photographs show first flash at vehicle

forward section.

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Imsc 1459364)3/61-7o 111111144

TDCE FRQ4

LUTON' sec) EVTINT

59.6 Second flash seen on photographs.

59.61 Agena telemetry signal lost.

59.7 Fire in forward section of vehicle apparent in photographs.

59.71 MECO (Thor main engine cutoff) indicated on Thor

sequential events channel.

59485 Thor main engine flame shortens in photographs in-

, dicating MECO.

59.88 Thor MECO (70% of stable chamber pressure).

59.9 Some Thor data (guidance) lost fran telemetry carrier.

6o Agena acquisition beacon signal lost.

60.6 Photographs show vehicle enveloped in flame.

62 Optical trackers reported vehicle break-yap.

65 Range Safety MPS-19 radars reported. loss of track on

Agena beacOn.

68.6 Range Safety destruct transmitter switched from lox

power to high power.

78.7 Photographs show explosion in vehicle.

79.5 Remaining data lost from Thor telemetry carrier.

93.6 Range Safety transmitted DESTRUCT ARM signal.

94. 9 Range Safety transmitted DESTRUCT signal.

185 Vandenberg Tracking Station MART radar lost track

on Agena beacon. Tracking data indicate Agena impact.

312 Thor telemetry carrier lost by Vandenberg Tracking

Station TIM-18.

The debris resulting from the vehicle's disintegration fell in the

ocean about 4300 yd from the pad. Search and salvage operations were

conducted from 22 July through 28 July in an attempt to recover components

which might show the type and cause of the vehicle falure. The impact

area was searched by MR divers using self-contained underwater breathing

equipment and by a Navy minesweeper using SONAR equipment. Portions of

the Thor engine section and fuel tank were located and identified but no

salvage was attempted. No Agena components were located in this operation,

however, the nitrogen and helium pressure spheres were washed. on to the

beach.

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-2- 1111111111
UM 44593640/6140

II. RADIAL ACTION

As a result of this launch the following action has been

taken tgrIbuglas Aircraft Company to increase the reliability

of the Thor flight controller:

Simplification of the design of the shaping network

to provide a more reliable checkout. (Page 17)

Encapsulation of the network boards to preclude

vibration damage. (Page 17)

Implementation of a more reliable checkout procedure

for verification of total loop response of the RIG

and. rate gyros. (Page 17)

LOCKHEED AIRCRAFT CORPORATION
IMSC X45936-10/61,-70

EMI

III. LAUNCH EVALUATION

ACESA. PERFORMANCE

Tor the most pert the flight termination during boost did. not permit the

Agana subsystems to perform their normal roles and thus an extensive evaluation

is not possible. The following evaluation applies to observations prior to

T+60 sec.

The space airframe (SS/A) appeared to remain intact under abnormal environment until excessive stress due to aerodynamic loading (high dynamic pressure,

adverse angle of attack) probably caused structural failure.

The Agena propulsion systems (SSA) was not active. However, telmmetered

data indicated it was in a satisfactory standby condition.

The auxiliary per supply aystaa (SS/C) appeared to provide normal voltages from all batteries, inverters, and regulators until loss of the Agena

telemetry signal, at T+59.61 sec.

The guidance and control system (SOD) with the exception of the rwmtimer

was on a normal standby status. The rate gyros, caged attitude gyros, and

roll accelerometer responded properly to the dynamic disturbances preceding

flight termination. The Dmtimer monitor indicated that the timer brake was

released by 3-900 umbilical pullavay at approximately T+1.0 sec.

Telemetry and commmications system (SOH) performed satisfactorily until

T+59.614 after which the telemetry signal vas no longer received. Return from

the radar Sand beacon was observed until 14-185 sec. During countdown some

difficulty was experienced in setting the secondary programer period. This

difficulty, apparently due to the ground monitor loading the programmer's

timing oscillator, was resolved prior to launch.

COUNTDOWN AND THOR PERFORMANCE

The evaluation of the countdown and MrparfOrmance is prarldedtgrtvo

time-event tables which compare . the actual launch performance to pre-launch

criteria established to define the conditions and functions which most be met

to achieve primary launch objectives.

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LOCKHEED AIRCRAFT CORPORATION

41110111°1

MISSILES and SPACE DIVISION
Table 1 evaluates the countdown tros its initiation through liftoff. In

doing this it does not attempt to describe all activities connecteivith the

countdown, but defines the technical points vhose specifications must be met,

or vbose banction must be verified. The specifications and tolerances are

given in the criteria column "Test and Function"; the values measured or events

verified are given in the "Performanoe'Evaluation" column.

Table 2 evaluates the performance of the Thor vehicle by coagering the

functional results in flight to. the criteria. In the table, the columns

"Time from Liftoff" and "System and Function" repeat the criteria. The column

"Performance Evaluation" correlates the actual flight perfOrmance of the

vehicle to the criteria.

At the and of the section, trajectory and velocity information derived.

from WHIM and PM FPS-16 radar tracking data is illustrated in Figure 1.

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LOCKHEED.AIRCRAFT CORPORATION MISSILES sod SP
LMSC 445936-10/61-70

IV. THOR SYSTEMS ANALYSIS

A. GUIDANCE AND CONTROL

Command Guidance System

No malfunction was detected in the command guidance system performance.

Functional operation of the equipment was normal until the missile-borne

guidance equipment was damaged by vehicle break-up at T+59.70 sec. The nominal

time for the earliest command guidance missile control function was T+90 sec.

Control System

Diverging rigid body. oscillations (0.3 cps) in pitch begin at liftoff

and continued until T+60 sec. They exceeded telemetry calibration levels at

T+10 sec. The pitch rate gyro bottomed at T+]6 sec.

Attitude loop gains, as measured in the first 10 sec of flight, were

approximately 20 per cent higher than expected. Cross-coupled oscillations

in yaw and roll reached maximum peak-to-peak amplitudes at T+30 sec. At that

time gyro rates of 1.1 deg/sec in yaw and 1.4 deg/sec in roll and attitude

errors of 0.8 deg in yaw and 0.6 deg in roll were recorded.

Calculations indicate an open circuit in the pitch rate loop. The

gain and phase of the pitch rate signal out of the demodulator were proper;

however, the signal was not present at the main engine pitch d-c amplifier.

The loss of the damping signal caused the booster control system to become

unstable at its rigid-body frequency.

For future flights, the series-connected 8-mfd capacitor in the rate

shaping network and the 16-mfd capacitor/4.5-megohm resistor parallel combination in the engine feedback shaping network (Figure 2) will be removed.

Their removal will simplify the circuitry and facilitate a more reliable

checkout of the system. In addition, the shaping network boards will be

modified and encapsulated to preclude malfunctions produced by vibration. A

new procedure has been generated for verification of total loop response of

the RIG and rate gyros.

. amit

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WIC 445936-10/61-70

To Telemetry

sAAr11.••••••/

To Main Engine Valve

Main

Engine

Position

Fig. 2. Simplified. Schematic

Diagram of Thor Pitch Attitude and Bate Loops

•

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All auxiliary shaping network assemblies at the.Vandedberg Field

Station (DAC) have been inspected for possible open or short circuits. The

leads-on several of the 8-mfd capacitors were of questionable reliability;

one lead was cracked half-way through at the solder bend next to the capacitor.

PROPULSION S/STEDI

Propulsion system performance was normal during start, flight, and

cutoff.

The 2.4min hold at the beginning of Phase V of the terminal countdown

succeeded in producing a normal buildup of vernier engine chamber pressure

and, consequerntly, a normal start sequence. Direct observations, confirmed

by photographic data, indicate that the amount of =bleed for vernier

engine No. 2 was marginal despite the hold. The hold was not intended.as a

permanent procedure. In order to achieve optimum bleed. rate in future launches,

the LC-fill-flow rate trill be reduced. This reduction will provide a longer

period during Phases IV and V for vernier-engine chilldovn.

At T+59.71 sec, the engines were cut off by a vernier cutoff signal.

Measurements of vernier engine chamber pressure confirm that VECO, which

automatically commands MECO, was the initial event. Apparently the VECO wiring shorted to aB v. Wiring from the VECO circuit to sequence of events

telemetry apparently failed at the same time, since the VECO command was not

indicated on the telemetry channel. A MECO command signal, of approximately

1/3 sec duration, was evident an the sequence channel. Transients in all

propulsion system fUnctions are typical of a ' command cutoff.

Measurements of fUel pump inlet pressure at cutoff indicate that the

fuel. tank was ruptured at VECO 4.0.3 sec.

ELECTRICAL POWER SYSTEM

The electrical power system functioned. properly. The timing and rates

of commands generated in the progromervere correct. Inverter phase4. voltage, actuator potentiometer positive and balance voltages, and guidance supply

voltages were maintained at proper levels throughout the flight.

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LOCKHEED AIRCRAFT CORPORATION MISSILES and SPACE DIVISION
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D. • HYDRAULIC SYSTEM

Hydraulic pressures were maintained at satisfactory levels throughout

the powered portion of the flight; hydraulic return pressure was slightly

lover than. normal, but it remained within tolerance until after'angine shutdown. Oscillations in hydraulic return pressure paralleled engine movements

during the period of powered flight. Data indicate no evidence of hydraulic

fluid depletion.

Hydraulic return pressure decayed abnormally after T+62 sec. The

significance of the behavior cannot be determined because of the unknown

extent of vehicle breakup.

L. INSTRINIENTATION

Instrumentation equipment operated satisfactarilyttroughout the

flight; data were returned for all guidance and control functions until

T+59.9 sec. Propulsion and hydraulic system data continued until T+79.5

sec •

F. GROUND SUPPORT EQUIPMENT

The ground support equipment operated satisfactorily in the preps-

:

ration and launch of the vehicle.

Fuel Computer

During phase IV of the terminal countdown, the fuel computer failed

to order fine load at 97 per cent due to a high-speed computing relay malfunction.

Pad Damage

Pad damage was normal. Refurbishment can be accomplished within the

normal turnaround schedule.

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V . RANGE SUPPORT

A. METRIC OPTICS

Film prints were received from MOTU cameras located at Vandenberg APB and

Pt. Arguello and from an ME-16 camera located on Tranquillon Peak, Pt. Arguello.

The MOTU coverage was limited to several seconds after liftoff because of a

low overcast. The ME-16 coverage extends from the time that the vehicle breaks

through the overcast until T+131 sec.

Events of possible significance and their times (+0.02 sec) taken from the

ME-16 film print include (1) two bright flashes of light at T459.15 sec and at

T+59.58 sec, which appear to be sun glints off the Agana nose section area;

(2) a fire, first visible at T459.69 sec, apparently located near the Agena

forward equipment rack but possibly in the Agena adapter section; (3) a visual

indication of TharldSCO at T459.85 see, based on shortening of the flame;

(4) flames that envelop the vehicle at appradam3t*.lyT460.6 sec; (5) an explosive-appearing fire cloud which first starts to develop at T+78.67 sec;

and (6) two large objects emerging frau the explosive fire cloud at T+79.35

sec. The above Observed events appear to correlate closely with vehicle events

seen on telemetry, namely: (1) loss of Agena telemetry at 7459.61 sec;

(2) MECO indications (T459.71 sec fran sequential events and T459.88 sec from

70 per cent wain engine chamber pressure); (3) loss of first stage guidance

and control telemetry data at T+59.9 sec; and (4) complete loss of first stage

telemetry signals at T+79.5 sec. JUst prior to the Agena fire indication at

T459.69 sec, the film indicated that the vehicle was yawing at a considerable

angle. This observed attitude correlates with the Aiwa normal accelerometer

readiMg.of -3.0 g at T+59.2 sec, and subsequent increase beyond telemetry

bandwidth.

Tabular data in tangent plane coordinates were provided every 1/4 sec

fran T+3.3 sec to T411.3 sec on the booster space position, velocity, velocity

components, acceleration, and acceleration components. Tabular data on pitch

and yaw were given every 1/4sec fran T+3.5 sec to T+8.5 sec and roll tabular

data: emery 1/4 sec from T+2.0 sec to 1+1L.5 sec. The short duration of metric

• optical coverage was caused. by a low overcast.

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METRIC RADAR

Tabular data in tangent plane coordinates on the booster space position,

velocity, velocity•components, acceleration, and acceleration components

vere provided every 1/4 sec from T+27 sec to T+59.5 sec, based on trajectory

data froa FPS-16 radars on Tranquillon Peak, Pt. Arguello. Also provided 'were

smoothed original tabular polar data for the Tranquillon Peak FPS-16 radar

and polar tabular data transformed tram the PPS 3.6 radar site to the Vandenberg Tracking Station MGM radar site.

Graphical plots of the optic-radar data were satisfactory.

PMR TELEMETRI

PMR tracking and recording of the first stage telemetry were generally

satisfactory. Frequent data dropouts and noise . of 1-sec or less duration

occurred from T+36 sec until final loss of telemetry signal at T+79.5 sec.

At T+59.6 sec, PAM telemetry traces of guidance parameters and command guidance

functions went- to zero 'while propulsion. and hydraulic system parameters went

to mid-band or stayed at their normal level until T+78.6 sec, dropping to zero

level before T+79.5 sec. MECO vas.indicated at T+59.7 sec by the sequential

events trace and at T+59.9 sec by 70 per cent chamber pressure criterion.

Pitch oscillations drove the peak of the pitch rate signal out of band after

T+10 sec.

D. MISSILE FLIGHT SAFE=

Tracking data were provided to Missile Plight Safety by comp ITS-16

radar, MPS.19 radar, and by the PPM-33 electronic skyscreens. The optical

skyscreens were operational but their coverage vas limited by the low (700 ft

to 1000 ft) cloud cover.

Operators of the optical trackers on Tranquillon Peak vho were above the

overcast reported that the vehicle vas breaking up at T+62 sec. At T465 sec

the MPS-19 radar lost track on the Mina radar beacon. Because the vehicle

was obviously out of control, the range safity officer transmitted the destruct

system ARM command at T+93.6 sec and the vehicle DESTRUCT command at T+54.9 sec.

-22-

LOCKHEED AIRCRAFT CORPORATION MISSILES and SPACE DIVISION
wac 145936-10/61-70

MEM

Available data indicate that the destruct charge may have been actuated at

T+18.7 sec as a result of structural failure of the vehicle. No evidence of

an erplosion at the time of the destruct command was noted.

B. RADIATION INTERFEREME CONTROL

The flight test radiation frequency bends were monitored for interfering

radiation by PMR ground stations and airborne stations. The ground stations

are located at Pt. Mugu, San Nicolas Island, and Pt. Arguello. The airborne

stations were in two aircraft flying various flight paths between Paso Robles,

Bakersfield, Palmdale, George APB, Oceanside, Catalina Island, and Pt. Mugu

at an altitude of approximately 15,000 ft. The monitoring reports for launch

time were as follows:

PLIGHT TEST DSE 

Beacon Response

BTL Ground Transmitter

BTL Airborne Transmitter

Te.lemetering

ITUDaiRINCT BAND (Ws)

414 to 418

2835 to 2865

2910 to 2930

8525 to 8535

9564 to 9575

227.2 to 247.3

MONITORING REPORT 

Clear

Clear. Nearest adjacent

signals were at 2630 Mcis

and at 2875 Mc/s.

Clear

Clear

Clear

Clear

• Destruct Transmitter

Beacon Interrogation

F. METEOROLOGY

The surface weather conditions in the launch pad area at launch time were

as follows:

Visibility 7 miles

Temperature 59 F

Relative Humidity 86%

Wind Direction 270 deg

Wind Speed. 9 knots

Barometric Pressure 29.681 in. Hg (NSL)

Sky Cover 10/10. Broken along layer

at 700 ft and overcast at

1000 ft.

LOCKHEED AIRCRAFT CORPORATION MISSILES and SPACE DIVISION
IMSC 44593610/6140

Rawinsonde soundings were made before the launch and immediately after

launch to determine the weather conditions at altitude. The post-Imundh

sounding shows a maximum wind shear of 27.3 fps per 1000 ft at an altitude of

7500 ft and with a length of approximately 1000 ft.

ENGINEERING sommumpsrmompar

Engineering sequential photographic coverage was satisfactory. Tracking

cameras had short coverage because of a low overcast, however, first stage

pitch oscillations were evident. Timing was missing on six cameras (Items 11.44 •

11.12, 11.14, 11.15, 11.17, and 11.20). Items 11.11 to 11.13 (first stage

engine ignition cameras) had a late start which was attributed to an abbreviated T-5 sec warning. Special project camera items were two airborne tracking

cameras mounted in a C-47 circling at 6000 ft. Track:was erratic and coverage

of one camera very short but the films included the vehicle fire and self. .

destruct, supplementing the photographic record of the PMR ME-16 camera on

Tranquillon Peak.

DOCUMENTARY PHOTOGRAPHY

Documentary photographic coverage was satisfactory. Tracking cameras had

short track because of a low overcast.

LOCKHEED AIRCRAFT CORPORATION MISSILES cad SPACE DIVISION
LMSC 445936-10/61..70

APPENDIX A

GLOSSARY

or

TECHNICAL MINIS

Thor thrust attainment - The point in time at which the Thor main

engine chamber pressure first reaches 90 per cent of its steady-state level.

Liftoff - The time at which the 1000 cycle liftoff tone is first

shown on the data records. The liftoff tone is triggered. by a microswitch

on the launcher which is actuated fran 3/4 to 1,1/4 inch vertical movement

of the Thor booster.

Thor main engine cutoff (1000) - The time at which the Thor main

engine chenber pressure has dropped to 70 per cent of its steady-state level.

Thor mein engine operating time - The elapsed time between Thor

thrust attainment and Thor main engine cutoff.

Thor vernier engine cutoff (VECO) - The time at which the vernier

engine chamber pressure has dropped to 70 per cent of its steady-state level.

Start of separation sequence - The time at which the monitor records indicate reception of the separation command 83. The separation

sequence includes thereafter the firing of the separation squibs and the

retrorockets, and the indication of relative motion by the separation

monitor.

End of separation - The time at which the separation monitor record

assumes its new steady-state level.

Orbital stage engine ignition • The time at which the mein power

relay closes.

Orbital stage thrust attainment - The time at Which the orbital

stage engine chamber pressure first reaches 90 per cent of its steady-state

level.

Orbital stage engine cutoff - The time at Which the orbital stage

engine chamber pressure drops to 70 per cent of its steady-state level

during the engine shutdown sequence.

1111111.1

LOCKHEED AIRCRAFT COUORATION

41110

MISSILES and SPACE DIVISION
LMSC 445936-10/61-70

APPENDIX A (Continued)

Orbital stags engine operating time - The elapsed time between

orbital stags engine ignition and orbital stage engine cutoff.

Orbital stage thrust duration - The elepsed time between orbital

stage thrust attainment and orbital stage engine cutoff.

(13) Beacon countdown - Failure of beacon to send a reply for each

interrogation pulse code train transmitted.

(I4) Agana velocity correction - The adjustment of the Agena velocity

integrator setting accomplished through the guidance system command. The

magnitude of the . in-flight correction is derived. from the recorded duration

of the discrete command D1 and the correction scale factor.

Timer hold command - The adjustment of the Mena timer braking

time accomplished through the guidance system command for the purpose of

delaying Agana engine ignition. The magnitude of the in-flight correction

is the combined duration of discrete commands D1 and D2.

NALreference velocity - The missile velocity relative to the

launching pad coordinate system.

(17) Inertial velocity - The missile velocity relative to non-rotating

coordinates at the earth's center.

(ay Plight path elevation angle - The angle between the missile inertial velocity vector and a plane pexpehdicular to a line between the

missile and the center of the earth.

(19) Sensible velocity gain - The time integral of longitudinal acceleration as. senselby an errorless accelerometer-integrator co-locatedyith

the longitudinal accelerometer.

.26.

LOCKHEED AIRCRAFT CORPORATION MISSILES cod SPACE DIVISION
IMSC 11.1159364061-70

APPENDIX B

ORM

DISCOVERER 1110/322 WEIGHT BREAKDOWN

First Stage (Thor 322)

Liftoff

Weight (1b)

Booster Dry Weight 6,573

Pressurization Gas

Trapped Propellants 395

Vernier Propellants 85

LW), Oil 127

Foal in Main Tank 32,044

Lax in Main Tank 67,673

Orbital Stage Adapter 258

Retro-rockets and Attachments 10

Destruct Package /1

TOTAL FIRST STAGE WEIGHT (INCLUDE% ADAPTER) 107,270

Orbital Stage (Agena 1110)

Agena Dry Weight 2,265

Pyrotechnics 1

Control Gas (Nitrogen-Freon) 138

Helium 3

Fuel (UM) 3,762

acid-tzar (MIA) 9,522

TOTAL ORBITAL STAGE WEIGHT 15,718

TOTAL DISCOVERER LIFTOFF ItELEGEE 122,988

27

LOCKHEED AIRCRAFT CORPORATION MISSILES and SPACE DIVISION
DSC 445936-10/6140

APPENDIX

Maw

MOB 322 PREPARATION HISTORY

DATE EVENT

4,13,61 Received. booster 322.

4-211-61 Began receiving inspection.

5-6-61 Completed receiving inspection. Began modifications.

5,12,61 Began pneumatic leak checks.

5-18,61 Began continuity checks.

5-30,61 Completed leak checks. Began control system checks. (Problems

with flight controller and the tolerator:rpm:knee required troubleshooting.)

6-8-61 Began instrumentation checks.

6-13-61 Accomplished final acceptance test. Completed control system

checks.

6-20.61 Delivered booster to launch emplacement 4. Began indexing.

641-61 Completed. mating.

6-22-61 Installed Bncketdyne kits. Began GSE simulator checks.

6-29-61 Completed GSE simulator checks. Began launcher checks. Checked

azimuth and vertical alignment.

6-30-61 Completed launcher checks. Began missile leak checks.

7-3-61 Replaced. the fuel start tank pressure switch. Began calibration

of inflight transducers.

7-5-61 Removed and sent the flight controller to the electrical laboratory

for trajectory change.

7,6-61 Completed. calibration of the waveguide.

7-7,61 Begin hydraulics checks.

7-11-61 Returned the flight controller from the electrical laboratory.

Began electrical checks after the flight controller was installed.

Completed leak cheCis and, calibrations of inflight transducers.

7-12-61 Accomplished the all-systems tests completing electrical checkouts.

7-13-61 Completed guidance phasing and polarity checks. Completed a dry

countdown. Discovered a malfUnction in the fuel computer during

a second day count; replaced the computer- but it remained inaccurate.

Began troubleshooting. 111111111111111

LOCKHEED AIRCRAFT CORPORATION MISSILES and SPACE DIVISION
IJ4SC 445936-10/61-7O

APPEND] C (Continued)

DATE EVENT

7.14.61 Repaired the fuel computer. Installed the telemetry package from

booster 323 in place of the original package because of intermittent dropouts apparent in the all-systems test.

7.] 5-61 Completed successful Lax and simultaneous flow exercises. (In

unloading from the simultaneous exercise approximately:Woo gal

of LOX ware spilled into the LO pit, the complex pit, and on

adjacent-areas. The No. 2 relief valve in the LOX main line froze

open. Only superficial dameg, resulted.)

7,17.61 Completed R-4 preflight procedures.

7,18.61 Completed R-3 preflight procedures except for the dry countdown

which was re-scheduLed for R-2 day.

7-19-61 Completed the R-3 dry countdoi ► and R-2 preflight procedures.

7-20.61 Completed R-1 day preflight procedures.

7-21-61 Launched the vehicle on the first attempt.

LOCKHEED AIRCRAFT CORPORATION MISSILES sod SPACE DIVISION
LM8C 44593640/61-70

AP'PERMX D

AGENA 1110 PREPARATION =STORY

DATE EVENT

6-28-61 Received vehicle 1110 at LMSC/VAFB Missile Assembly Building.

PerfOrmed receiving inspection.

6-29-61 Performed SS/D validation checks.

6-30-61 Completed SOD validation checks. Performed SS/B leak checks.

7-1-61 Performed SOB leak checks.

7-2-61 No nark scheduled.

7-3-61 Cleared. SOB leaks. Performed Mt calibrations.

74-61 No work scheduled.

7-5-61 Changed. diplaxer. Performed MR checks.

74-61 Performed TIM calibration. Re-ran VSWR checks due to multiplexer

replacement.

7-7-61 Performed destruct checks.

7-8-61 Performed payload fit checks..

7-9-61 No work scheduled.

7-10-61 Transferred vehicle 1110 to complex 75-3, pad 4. Performed

electrical compatibilities.

7-11-61 Performed SSA checks. Performed Countdown and Flight System

Check preparations.

7,12-61 Performed successfully Countdown and Flight System Check.

7-13-61 Performed umbilical drop tests.

7-14• 1 Perfomed SOB leak checks. Performed modifications.

7-15-61 Performed dual flows on the Thor booster (DAC).

7-16-61 No work scheduled..

717-61 Performed R-4 Day activities.

7-18-61 Performed R-3 Day activities.

7-19-61 Performed R-2 Day activities.

7-20-61 Performed. R-1 Day activities.

7-21-61 Launched Discoverer 1110/322 from complex /5-3, pad 4 at

1535:00.46.

-30-

LOCKHEED AIRCRAFT CORPORATION MISSILES and SPACE DIVISION
LMSC 445936-10/61-70

APPENDIX E 11111.1111%

PAD COUNTDOWN AID FLIGHT SYSTEM cam

The first and final countdown and flight systems check on Awns 1110

was performed. on 12 Jay 1961.

Prior to the start of the countdown and flight systems check l the complex

chief was notified that the payload. would not be available until later in the

day. In order to accelerate the completion of the check, a coordinated decision

was made between SSD/VAPB, LVISC/Bunnyva3.e,and. LMSC/VAPB that Phase II would

be performed first and the simulator substituted in place of the payload. Due

to this decision, Test Procedure 1412358, dated 10 July 1961, was performed.

with the following deletions and deviations for this portion of the check:

Task 2A, Payload Mating -- All payload items deleted.

Task 4A, Pr Checkout -- Items 28, 30, 31, 32, 33, 34, 37, and 40

deleted.

Task 12A, Payload Checkout -- Task deleted.

Task 19A, Terminal Count -- Task deleted.

Phase I -- Deleted.

Preparation for Phase II -- Deleted.

The check was initiated at 1100 and proceeded. normally through tasks 1A,

2A, 11A, 4A, 16A, 19A, and Phase II. This portion of the check was completed

satisfactorily at 1327.

Post-test items 2, 5, 6, 8, 9, 10, 11, 12, 13, 14, and 15 were performed

in order to return the vehicle to the proper configuration to perform Phase-I

checkout.

Upon the arrival of the payload to the pad, the necessary payload preparations were made and the countdown and flight systems check was initiated at

1605.

The test procedure was perforaml as written for a Phase-I checkout except

the following deletions:

1111111111111t

LOCKHEED AIRCRAFT CORPORATION MISSILES and SPACE DIVISION
DAM W936-1061-70

APPENDIX B (Continued.)

Task 4A, Er Checkout — Items 12 through 28, 4 .2 through 72, and 76

through 87 were deleted.

Task 19A, Terminal Count -- Items 17, 18, and 23 were deleted.

Tasks . 1A., 2A, 114 liA, 12A, 19A, and Phase I were completed. at 2326 with

only minor problems arising.

Upon satisfactory ccerpletion of the post-teat items, a successful countdown and flight systems check had. been performed. on Vehicle 1110.

LOCKHEED AIRCRAFT CORPORATION MISSILES Gad SPACE DIVISION
"111,11111! -•

' •

•

APPENDIX F

DISCOVERER LAUNCH DATA DIGEST

Adisoots alUtelso 1xla aa Mee sonatat 1.5,mo fp,

isslimulifu itAr

Aslsolu 112.0° UtItelle 165 Veleeitm 04000 tee

Aslosotto 177.3•

(11 • ass.) Uttados *102 am Vol•oltys 2500 As

•

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it 220012 ma Metro

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re

15 120116 •

rut HMI

IMSC 1459364.063.:To

• 11110101 UN= 113100111111 MNMS= MOM ND OMB AM isms. J9•. MI& eaummor MIMI MOMS noomamo FL= 0111MOIMOU 

011111:011. MGM UM

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eeu Morted.

2021/16) &O&M Probable ikladatel 01$1114111 NNW mmit• amle - 1.76,

' 1314116 Ospsoto osorated Sr.. ymetedsiee Z etieli strariletable br untie .alined) (Ilesomay sired% Iskeelie eratrel at amass sot prossionS) ls.ttdaa. w telowetry or railer erldtal easteeta Omollemble radio asi radar mataate spirted. •

12012/1TO k = Yoe Illeradleel 11111 teal laomparetrd. Prembare APINS MOM MAIO. Ilmearob Mates swam *Abe Salm dem by monsvi .... seine (!•0) ewer berets Men, arid enkese. bet Wesel reurele. Sr setae Altered te tastes me. Sem tram • min peer relay Orel Motet. erl twitter Orbit esMirred. bat Solverteet Mill meet aneeed mood Iwo et au- mery tietag. Owl& jeetea, ettb mostly mu.

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bet 'WW1 1/a/ea i undi 2111250

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lamemed to Maki 41131106101 orbit awl War MM.

Mat morel tram we up area t• loom muds thorn& shissoborbilss.

lg

•

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bitsgratar eel,* lea. Mo. ust MUM latm yreponeet astrastlos. Iroutosts dubs sopsnottss. Use s0/1 ita gnu sot for lasorrost = koosbig. ft•d• alerbod bat

sot voroon lossoory so. imam sods Wined Not aossoplolea.

ratisarti sulderre Atter km 03 dast Alp=

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.tostator. Mews - aalmatet peter 6* mel mateet by ISM* Otatlea. • Ouse le meld art be ejected.

Adam, 160.2.. slUbsts sla

=m15.6" t" ItesestatatOrr

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ktisieb 916.65 sta. torles•o let •

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emmer eltb dropir isresatem roils (a..) to War better embed at loesta. MOW opode, r

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ablorbattielemi eel tiormstat for batteries. Iwo yealtium !attestor devise ad tsetse aurtation gym imteLlell to medal !attitude data.

sx=UM)

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orrery.

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la .sit OM* 'sea Mriumeom Asalyele Owl (M) MM.

LOCKHEED AIRCRAFT CORPORATION MISSILES ma SPACE DIVISION
("Vtallgeded)

Astrolabe Me Altitudes 1.10.* es • Valseitm 16,116es baUsatiew It. Iheratriettd 0. aliases 91.96111, Pgalsom 119.1 as

Vides 30T.3 in

,asmii, Jae Altibpats 191.4 s

Voloodp 86,00 fpe

boifstlaae 011:91° Porte& 91.1 aka Parapet 131.5 go

toseson 519.7

•

Agisudi 172° Malted: 106.7 se Velegitm WAY flu laellgatiose 60.3r Iseastrisity: 0.091 Perla& 9d ?gripes 106.0 Apogee: 339.3 am

Asturatis 17140 Altitude (ss): M.? au Aldiuds'(10)s 101.1 s

butts Andes -7-

Adman 174° Altitudes 160.1 et

Yawata: DA% fpt lealleatLau61.0r leeestrialts: .03X6 Pariah 953 min haste: 07. ga Wester 4)6.17

 um

AVM .allar-10/61-70

F (continued)

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awed the Awns to mortar e Mpg to mortar the rassephere. War beset eoneulat for is rated* eel attitude. /106 150 10 1611 see 211-p aratUratate

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poem 1 tad X. Isi.Wie

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LOCKHEED AIRCRAFT CORPORATION MISSILES sad SPACE D
Asisothe 1100 taittales 156.9 se Validity shwa leatisstlent 81.49° Asseeetrielty: 0.0307 wiled: 93.67 Ma

mum: ,151.6 20 1909“: *374 ma

Asiesd►: 1786 Altitlls: 154.8 mu Velocity's 10.8,0 fag !..Beata: (134-

imiotrifttys IMO/

Pastels 98.9 ole Shrives 153.5 se Apepses 100.5 a

DSC 445936 4.061 -70

laws mom Disoovem custorneas goeum di OM Ad ORM%

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rs

ra 1306/sge I

is36323.

0-17.41 PAR 18118108 Mt Aires 1 rah 8096 dudes Is (teal Mort not sell Sea sleek mese (i65,002 tbrett)IlsOpee loop test of DS Oukleoess Ilysteu.Oeh•deled I day active orbital. iris.

lam* as rind attempt. Litton esd dor basil seal. Amer odlitede leediturisal eseillatieue (3.5 a time .1t8 preview addable. All Areas fenetiuse eriertet. Orbit close to tilt desired. Arid .spools memory after 48

Man (three daye).lbe lees. eet time is orbit before is. ,it/allog recovery.

lords to seed attempt. Liftoff sad that Wald sail. All Awes fusetiese 'Motet. Oddta1 beset eatiefeedeep to Male °atrial Motes. Attl- Vale gestalt Met alter mull lopeetlas bemuse it Amplirldoe of centre/ am, uppereettr ass I. a oalfseetiss is the ps••• •

valve sestrol eddifter.

Woo& co waved attempt. Liftoff, Thor toad, wed Ogees boost esdishetery to attain orbit but Aiwa issidesee drift. addles daring beset sot later. *Meet is odd*. !bar 17-81 ere Isegriestird searilatis et Slot 1.5 A's Fier Orbital Wow suritsetiess se less 31 pail'' renewer;

.rtes pt.

Levosbod

Aftwetes rne A/titides 803.5 Velocity: 115,690 fr lisellastise: to.% Seseettleitys 0.0366 feted: 93.1 ma Perigee: 186 a

Peery XII as

Amos a vital 0096 muds*

l

Weld start—set soot as Ude aid.) Sher smiles (16:4000 lb tined) used far first tire with. Discoverer.

Ades Apses I MAR 6151 geese Mit:otter liver arils Dleek.1 seam Ill.1

liesvreseverdde Coeds

Xri

M tta= 1108/161 5 1.18.451 Ter

145700•/

Noweeavera►le Ayes 3 eitb 0096 ••81118 rerilester pains& let pus for first did/ alert.

an first aumme. Lift. Aslrodu 171.60 off sad beast phase nail al.

Altitudes Uri.) a thee. oseillattets tee sated wiassty: 06,0? l7.! is useelereseter ass Mester Deallastieesilo. atter Alma mos ., yrepariert pressure doles. dead 110.1° after sewed phase ad orbital. stair aunt bare , Plows 4011141 wort tor' =efts ddestrisitys .0503 attar rirat veleaty W. Orbit period bare ' end odentriarip lore Pep as mre after • a resale' tie W. Sojeetlea road leas velosity. Woe roars* end Period: 03.0 id... after first

operatten ter 1 see aria. first tern

pis we seeeftftehea. 97.11 ids. after

Mufti buns Periapes 339 a after seem* Yeas *own 670 el atter wood burg

LOCKHEED AIRCRAFT CORPORATION MISSILES aid SPACE DIVISION
11111100E-1.0/61-70

VAMP NNO

MILMELEMagent VAINUSEM. 011D1121. PANAMA •

cora elta

(aid stoat lot toittrelie vita Ulu* It swim out 991.

ottloaut

tonna on firet •e4tompt. Lift.

offend lhor heart mortal.

toldsout uttaUtly mot Ito the ilemt tfmn, ottotootolio

uttouolual tesommittod liter

ebtorimg mud sogmemee um000do

nd dieereteo fee Agent enemy

start am& volonitv onio.

Milt is6•411114666 duo to* • eantrol welds oalitinettem — 1mao of hydeatato peateenre

otoradostolo JD nee prier to

Iodise shotiomm. lbealtIND

lone of eitltmde esataol farmed

erec000me otleaty motor ma possibly low tomato taloato am to pm.

mature .line dattatova.

Ashentht 171 deg

Similar to Jettf

stellar to eell

Usemett en rirnt tuttolot.

!Aft" Thar twat, mad Alone

orbital injection were morme1.

Added imetvmenstationAndielatoo

that stn.. Agape for 10.epa

Thar oectltAtimee is Wee some

Yon atottopoly ooloclotot.

.:dear run 6 end tree 7 the

hortaan eetooter failed; Wham

Inge 9 end Ines Wastrel:gen

vac eaddeoly loot. Caputo reentry mon ant errectvt doe 50

vehicle Meddler.

Woo* on first *time/. Nara Coutotat 17*

torootoot voltage OM/00 Alt

prior to liftoff, almoriNg with

ortiutut JACO raletoe. ohm

west em sollonee someal.

Deft boost, Apo• att otatlao

restatered atettoain hooting

eta:Nang at Vett see, indiont.

lag won flaw volla. tun.

slant dropeat enearrol toot

rm., too w *te7.3 old Tan eon to MIA secs at WPM

telmotry am loot. Wiwi"

or Imo eleetrteel poise mt.,

trotoala os resell of W.,

oratootot actual hoottooloo of

Ape wkaystar, preolmillog

orbital iklestion.

tonna en tint salon* end lease* from Cs 71.1,

recently modified to Dienevoter

eantlgoration. Taaimimal hold

-. MAD min. Unser areal.

Thor earecalod largest roll program to dates 61030'.• error

is Thor first stop or pit* program ~rested by engem'

mildew. After etaertes env.

mends initiated. All Agin*

otoottoo operated Proltorle to establish a Nor neednal orbit.

c.pmetn .denture oft 33 /au.

'Wroth' 17e deg Altitude' lid 1,n.

Velocity: 21,641 foe

loollastiems 8161 deg

Noematatailyt 0.014

muds 9047 old revive, 140 p.m.

Amain Z,6 GAN

•

•

Apes e. Thoc.Anal vita elect 11 maim Onatime,

Katt 1 vernier modimmt.

Animate: 17e deg

Altibmart 109.11 a.m.

%Malty* 13.660 its Inolinellent 69.3 deg

Itomentricityt 6.06

Pariedi 14.1

twinge: 107.1 eat.

Apoemai 436.6....

•

•

tadVoiMit lacitoonoi

NUENEL.—Aa.... 0110

2313/ 1

%mote

901XAS

EMIL

•MD

Mt

Mutat

DAWN AMP

nos

• 011101112. OWN= 1716

mosvoma 4--1ILSWg

Lttaria

1103h00 4 3-3041

3,131,143

No A611

1 mu

r/a=

tXtr fed tto936026

1106/107

11c6/301

:

4

t-1.1+1.

11.21407

Tee

No Are 1316:00

Xtv

IX w936.07 1 6.16-61 leo ASR heeds Tee--eon

recovery

•

not

144593‘99 1 7-7-61 Tee ACT

Tee-vatr

recovery

stalls' to Jon tome* on tint attar*. Door

thrust greater then prodieted

eller sloe eagles start es-

/Nonce. Noon eampLheg JP-100

utrotott to Selig topes the

vehicle at embilicel ralneen:

with occreevoidlogeop pm

tottary-bme end regolmted ftliw

pavan. nreator Amos ego:stet.

city and DMUS period Win -

tested to Wooster grew.

Wad* 171 dad Altitudes 146.6 ear.

Veloeityt MAW rpe

Inelliattoet 81.96 deg

Neeentrieihrt 0.05$

fwical1 . 9) Nip Porigeet 146.8.e.m.

1111.1111111

LOCKHEED AIRCRAFT COR ►ORATION MISSILES and SPACE DIVISION
immois

APPERDIX 1P (0i;atinued. '

_ftdoureaale amon WNW; UP= . g@ aavA Na PAW AM • 01111TAL COMM few

341"4444

mr-eaugmu , auL . MEL OIL IMMO 1211211M *Man • /1111111mmitaandst BiaLIESsma memo An

tuntss t n.Til re Atit MAW he WI

LOCKHEED AIRCRAFT CORPORATION

-37-

alb

111.1111

ERIBUSEagg.

MISSILES and SPACE DIVISION

tanan ea neat arei. stets attar Ilftert. a aathestle•

MWMa Mar Altatetlet esuesn the "Well eallar late Alversset pltek arealerattem. Al 7vis.• •

ass, a ..3 aftspot Web teetiess4 twos/ ILAN sue

aseatrall W •tteisiaa asselanneter,

startles Anstrpotlat ar His tablet&

At MA ass, the valet. was as. *elope.' Ile new. +WI at Is10.7 ewe We esItlete ewledal. the seem er his salrasselta le Mist. WWI la an Im its Thor rUght renuvuor pluemet. /asp.