| Mercury Booster Working Group Flight Test Report Mercury/Atlas MA-3 (Atlas 100D) 25 April 1961. |
08 MAY 1961 |
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| Authors:
GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
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 | The report describes the launch and flight parameters of an unmanned spacecraft. |
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| Factory Acceptance Testing of Missile 47E. |
08 MAY 1961 |
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| Authors:
GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
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| The report presents the results of composite test of missile 48E. (Author) |
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| Factory Acceptance Testing of Missile 32E. |
05 MAY 1961 |
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| Authors:
GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
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| The report presents the results of composite test and post-composite testing of missile 32E. |
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| Factory Acceptance Testing of Missile 35E. |
05 MAY 1961 |
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| Authors:
GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
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| The report presents the results of composite test and post-composite testing of Missile 35E. (Author) |
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| Frequency Response Tests of the Autopilot System With or without Accumulators 'Data Only,' |
05 MAY 1961 |
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| Authors:
W. H. Neal; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
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| The objective of the test was to determine the effect of the sustainer-accumulator and booster accumulators on the frequency response of the autopilot system. (Author) |
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| Factory Acceptance Testing of Missile 46E. |
02 MAY 1961 |
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| Authors:
GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
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| The report presents the results of composite test of missile 46E. Pertinent system level testing is also included. |
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| Special Missile Lift System Tests at OSTF-2, Category I. |
30 APR 1961 |
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| Authors:
GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
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| The missile lift system special tests conducted during the period of 14 August to 20 December 1961 were conducted to check out the operation of the system under a variety of load conditions. A total of thirty-nine cycles of the lift system was completed. (Author) |
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| Boeing Optical Beacon Battery Radio Interference Test Report. Appendix 'B', |
28 APR 1961 |
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| Authors:
B. Hoerl; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
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| The purpose of the test was to determine if the Optical Beacon Battery conformed to the requirements of Military Specification MIL-I-26600. (Author) |
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| Evaluation Test of Liquid Oxygen Topping Line System Convair Drawing No. 27-21516, |
27 APR 1961 |
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| Authors:
C. A. Palosaari; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
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| This report describes tests performed on topping lines. The object of this was to determine if the re-designed liquid oxygen topping line would meet missile requirements. The topping line assembly was subjected to the Proof Pressure, Vibration, and Burst Tests as outlined in the procedure. The operation satisfied all design requirements. (Author) |
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| Factory Acceptance Testing of Missile 30E. |
20 APR 1961 |
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| Authors:
GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
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| The report presents the results of composite test and post-composite testing of missile 30E. |
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| Factory Acceptance Testing of Missile 26E. |
14 APR 1961 |
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| Authors:
GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
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| The report contains the results of composite testing performed on a guided missile and missile components. |
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| Factory Acceptance Testing of Missile 25E. |
14 APR 1961 |
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| Authors:
GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
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| The report presents the results of composite test and post-composite testing of missile 25E. |
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| Atlas/Agena B Missile Structural Capabilities for Ranger Program, |
13 APR 1961 |
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| Authors:
R. A. Jankowski; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
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| The Atlas Agena B missile configuration is examined in this report for loadings resulting from a Ranger Payload. (Author) |
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| Evaluation of Wheaton AC Voltage Sensing Relay Model E 1020, |
13 APR 1961 |
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| Authors:
S. A. Schwartz; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
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| The objective of the test was to evaluate the voltage sensing relay and to determine if it can meet the specifications required for operation in launch control equipment. (Author) |
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| Factory Acceptance Testing of Missile 112D. |
12 APR 1961 |
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| Authors:
GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
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| The report presents the results of composite test and post-composite testing of missile 112D. |
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| Acceleration and Control Maneuvers Test on Centaur Attitude Control System, |
12 APR 1961 |
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| Authors:
P. A. HOUSE; C. Finn; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
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| The objectives to the tests performed were the following: to verify that Centaur accelerations in space have been duplicated on the coast phase test stand; to determine the engine decay impulses to give the differences between actual and engine commanded changes in velocity; and to define the autopilot switching lines from the recovery maneuvers. Records were also taken of the test stand operating conditions, pressures, temperatures, and propellant consumption. (Author) ... |
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| MOBILE APCHE AND LAUNCH CONTROL PARAMETERS FOR 'E' SERIES MISSILES (HORIZONTAL CONCEPT). |
10 APR 1961 |
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| Authors:
GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
|
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| Systems Test of Hydraulic Servo Actuators 'Data Only' Report, |
07 APR 1961 |
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| Authors:
J. B. Cross; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
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| This report documents the test data from the finished portion of the actuator test program. The data herein include frequency response plots of the actuator specimens as tested on the 'E' Series Autopilot Tail Section Test Stand Number 3. (Author) |
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| G. E. MOD III Instrumentation Waveguide. |
06 APR 1961 |
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| Authors:
B. E. Hoffman; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
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| The purpose of this test was to evaluate an instrumentation Waveguide to determine if the waveguide could be a contributing cause to poor flight performance of the instrumentation system. |
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| Design Proofing Test Report for CV-A Boiloff Valve and Solenoid Sensor First Stage Centaur, Dwg. No. 55-80209-801. |
06 APR 1961 |
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| Authors:
S. G. Sproles; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
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| The purpose of this report is to describe the test equipment and procedure required for the design proofing of a boiloff valve. (Author) |
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| Reliability Test Report for Control Unit Power and Signal, RSC. Part No. 27-36236-5, S/N 006-0014 and 006-0015, |
06 APR 1961 |
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| Authors:
F. J. Denny; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
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| The purpose of this test was a search for critical weaknesses. (Author) |
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| Flight Test Report Atlas Missile 16E, 24 March 1961. |
06 APR 1961 |
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| Authors:
GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
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| The primary purpose of the flight was to evaluate E series missile system performance at maximum R and D range. Other first order objectives included evaluation of Inertial Guidance System performance and accuracy, determination of warhead performance, arming and fuzing system performance, and missile system maximum range capability. (Author) |
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| Factory Acceptance Testing of Missile 39E. |
03 APR 1961 |
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| Authors:
GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
|
| The report presents the results of composite test and post-composite testing of Missile 39E. (Author) |
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| Factory Acceptance Testing of Missile 41E. |
03 APR 1961 |
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| Authors:
GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
|
| The report presents the results of composite test and post-composite testing of Missile 41E. |
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| Factory Acceptance Testing of Missile 3F. |
03 APR 1961 |
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| Authors:
GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
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| The report presents the results of composite testing of Missile 3F. |
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| Control of Chilldown and Pressure Rise in SF-1 Cruiser Tank and Transfer Line. |
03 APR 1961 |
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| Authors:
S. Tengan; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
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| The objective of this test is to establish an optimum chilldown procedure for the SF-1 Transfer Line and Cruiser Tank, utilizing a minimum amount of SF-1 and the minimum time without exceeding the safe missile fuel tank operating pressure (11 psig) and boiloff valve capability. (Author) |
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| 3 AND 4E Hydraulic Staging Line Investigation, |
31 MAR 1961 |
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| Authors:
S. R. Harrison; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
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| The objective of the test was to conduct additional testing of the 3E and 4E configuration of staging disconnects and associated hydraulic lines, under simulated flight loads, to verify the hydraulic installation. (Author) |
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| Flight Proofing Test Report for Abort Sensing and Control Unit Drawing No. 27-11111-821, |
30 MAR 1961 |
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| Authors:
R. N. Galloway; F. J. Denneny; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
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| The purpose of the report is to describe the test equipment and procedure required for the flight proofing of components of a 'square canister' containing six rate gyro output detectors, thirteen pressure switch output detectors and associated circuitry needed to supply two 'ready-abort' outputs as well as seventeen telemetry outputs. (Author) |
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| Evaluation of Kinetics Voltage Sensing Relay Model M485-1. |
30 MAR 1961 |
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| Authors:
L. W. Keith; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
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| The objective was to evaluate the voltage sensing relay to determine if it can meet specifications required for operation in launch control equipment. (Author) |
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| Design Proof Test Report for Antenna: 'C' Band Beacon CVA P/N 55-13602-1, |
30 MAR 1961 |
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| Authors:
E. Thiede; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
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| This report contains the design proof test procedures, test data, and a summary of the test results obtained in testing the C-Band Beacon Antenna. (Author) |
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| Design Proofing Test Report on Centaur Propellant Utilization Manometer Heater Control Assembly, |
29 MAR 1961 |
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| Authors:
G. J. Kaleta; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
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| The objective of the test was to subject the Centaur propellant utilization manometer heater control assembly to all environmental and functional tests necessary for determining if the heater control assembly shall meet design proofing test requirements. (Author) |
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| Range Safety Trajectory and Dispersion Information for the Mercury/Atlas 100-D Flight Test Vehicle. |
28 MAR 1961 |
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| Authors:
J. Libidinsky; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
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| A summary of trajectory data required by the Range Safety Division, AMR, for the establishment of range safety criteria for the flight of the XSM-65-100-D flight test vehicle is presented in this report. (Author) |
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| Reliability Test of Valve Safety Relief Hydraulic Sustainer Part No. 27-08569-1 Search for Critical Weakness, |
28 MAR 1961 |
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| Authors:
J. C. Easton; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
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| Tests were made to determine the operational characteristics (fluid leakage rates) of the test units while being subjected to three temperature vibration levels and the changes in test unit performance as a result of these tests. |
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| Control-Rate of Turn, Autopilot CVA Part No. 27-04574-1. |
27 MAR 1961 |
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| Authors:
P. Fernald; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
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| The purpose of the report is to describe the test equipment, test procedure, and results of the evaluation testing of an angular rate gyro. |
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| Factory Acceptance Testing of Missile 38E. |
24 MAR 1961 |
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| Authors:
GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
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| The report presents the results of composite test and post-composite testing of Missile 38E. (Author) |
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| Adjustment and Preload Procedure for Interstage Separation Latch, Atlas/Centaur Missile (Model 55). |
24 MAR 1961 |
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| Authors:
E. L. Manor; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
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| This report provides adjustment and preload instructions for the Interstage Separation System Latch. (Author) |
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| Restrictor - Fluid Zero 'G' Manometer CVA P/N 57-43032-7. |
24 MAR 1961 |
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| Authors:
R. L. Johnson; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
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| The object of the test was to determine the capability of the restrictor to prohibit passing of the manometer fluids under pressurization surge conditions. (Author) |
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| Initial Acceptance Test Report for Regulator Assembly, 'E' Series Helium Pressure (Fuel Tank) Dwg. No. 27-80400 (Convair Stratos), |
23 MAR 1961 |
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| Authors:
H. P. Ryan; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
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| The purpose of this report is to describe the test equipment and procedure required for the initial acceptance testing of a fuel tank pressure regulator in a simulated missile propellant tank flow set-up. (Author) |
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| Maximum Range Capability of 'D' and 'E' Series Atlas with and without Propellant Utilization Control, |
21 MAR 1961 |
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| Authors:
R. Rose; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
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| The purpose of this report is to indicate the range capability for D and E series Atlas missiles, with and without PU control, as determined from a Monte Carlo statistical study. (Author) |
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| Evaluation Test of Filter - Orifice Pneumatic Check-Out, CVA P/N: 27-11903-1. |
21 MAR 1961 |
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| Authors:
B. Augustus; T. L. Lamoureux Jr; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
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| The object of this test was to determine the attenuation and phase shift characteristics of three small orifices in a helium pneumatic system. (Author) |
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| Design Proof Test Report for Autopilot Servo Amplifier-Centaur-Dwg. No. 55-40002. |
21 MAR 1961 |
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| Authors:
H. D. Andrews; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
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| The report contains a summary of the test results, the test procedure used, and the data obtained while design proofing the Centaur servoamplifier. (Author) |
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| Flight Proofing Test Report for CV-A Boiloff Valve and Solenoid Sensor, Dwg. No. 27-80750-837. |
20 MAR 1961 |
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| Authors:
R. Tuttobene; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
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| Flight Proof Testing was performed on CV-A Boiloff Valve and Solenoid Sensor, CVA P/N 27-80750-813; -837. The purpose of this test was to flight proof the valve and sensor combination for use on the Extra Heavy Agena Booster, and by similarity, for use on the 'F' series Atlas missile. (Author) |
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| Reliability Test of Valve, Check - Hydraulic Pressure Part No. 27-08560-1 Search for Critical Weakness. |
20 MAR 1961 |
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| Authors:
Jack C. Easton; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
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| The purpose of this test was to determine the operational characteristics (external leakage rates) of the Valves, Check-Hydraulic Pressure, while being subjected to three (3) temperature-vibration levels, and the changes in test unit performance and body outside diameter as a result of these tests. (Author) |
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| The Centaur Type Propellant Utilization System, |
17 MAR 1961 |
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| Authors:
J. W. Mildice; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
|
| The report describes the centaur type propellant utilization system together with its pressure sensing system. It touches on sensor construction and electrical characteristics, on the computer comparator and system tolerances and parameters. |
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| Factory Acceptance Testing of Missile 108D. |
15 MAR 1961 |
|
| Authors:
GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
|
| The report presents the results of composite test and post-composite testing of Missile 108D. |
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| Evaluation of B-2 Liquid Oxygen Line, P/N 27-23518-1 'E' Series. |
14 MAR 1961 |
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| Authors:
R. E. Jumont; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
|
| The object of this test was to evaluate the B-2 liquid oxygen duct assembly by investigating the ability of the duct to withstand the flight requirements. The requirements consisted of pressurization, static load, vibration, flex and burst tests. (Author) |
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| Flight Proofing Test Report for the Airborne Optical Beacon Battery (Light Weight Version) Dwg. No. 27-04526 (BAC) Part No. 10-20411-2. |
14 MAR 1961 |
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| Authors:
J. K. Gilbert; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
|
| The report describes the flight proof testing of airborne optical beacon batteries. (Author) |
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| Evaluation Test Report for Light Weight TLM Battery CVA P/N 27-06348-1. |
14 MAR 1961 |
|
| Authors:
L. P. Hamblen; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
|
| The test specimen covered by this procedure consists of primary silver-zinc cells with interconnecting lugs, stainless steel container, thermostatically controlled heater, power receptacle, pressure relief valve and pressurizing valve. (Author) |
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| Factory Acceptance Testing of Missile 37E. |
13 MAR 1961 |
|
| Authors:
GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
|
| The report presents the results of composite test of missile 37E. (Author) |
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| Pre-Production Test Report for Solenoid Sensor, Dwg. No. 27-81448-807, and -813. |
08 MAR 1961 |
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| Authors:
S. G. Sproles; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
|
| Pre-production testing was performed on two solenoid sensor assemblies. The prime function of the solenoid sensor is to regulate and maintain the liquid oxygen boiloff valve (P/N 27-80750) crack and reseat pressures at values higher than those presently required for the 'D' and 'E' series Atlas program. The solenoid sensor is to be used on the 'F' series Atlas, extra heavy agena booster, and the Atlas - Centaur booster. When ... |
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Reports by Corporate Author
