| FAILURE VERIFICATION - GROVE REGULATOR P/N 1601302-7, |
11 MAY 1962 |
|
| Authors:
J. W. Abramoski; LOCKHEED MISSILES AND SPACE CO INC SUNNYVALE CA
|
|
| ZERO-G REPORT LIQUID BEHAVIOR SCALING, |
07 MAY 1962 |
|
| Authors:
J. L. Hansen; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
|
 | The simple vibrating systems described by the equations in the report bear little direct relation to the complex shapes and surfaces which are usually seen in zero gravity, or to those which will probably exist in the Centaur fuel tank. The simple systems do, however, have the feature in common with the complex ones that their response to a disturbance is controlled by density viscosity, and surface tension. The analytical ... |
|
| PNEUMATIC AND PROPULSION CONSOLE. PART NO. 1513399-501. MODEL NO. 205-145. PNEUMATIC AND PROPELLANTS CONSOLE. PART NO. 1518773-501. MODEL NO. 205-601. OPERATION AND SERVICE MANUAL. |
04 MAY 1962 |
|
| Authors:
LOCKHEED MISSILES AND SPACE CO INC SUNNYVALE CA
|
|
| COMMUNICATION CONSOLE ASSEMBLY PART NO. 1599531. OPERATION AND SERVICE MANUAL. |
04 MAY 1962 |
|
| Authors:
LOCKHEED MISSILES AND SPACE CO INC SUNNYVALE CA
|
| This manual contains operation and service instructions for the Communication Console Assembly. The console, located in the Launch Operations Building, provides prelaunch missile checkout and checkout indication and record capabilities for programmer 400-cycle frequency check, auxiliary time command check and record, beacon signal and transponder power levels, and telemetry voltage indications. |
|
| Development Program for the Centaur Intermediate Bulkhead. |
28 APR 1962 |
|
| Authors:
GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
|
| This report outlines the approach to be taken in the development of a new Centaur integral bulkhead. It prescribes the over-all plan for design development and test programs for an improved bulkhead configuration for flight vehicles. Detailed test plans will be prepared for each test article to fulfill the general requirements stipulated in this report. (Author) |
|
| PRELIMINARY UTILITY OPERATION AND MAINTENANCE MANUAL. Z(MIDAS,)ZNASA, ADVENT SYSTEMS. DATA CONTROL AND COMPARISON PANEL, PART NO. 283-10000 (ELECTRADA), 1460077-1 (LOCKHEED). |
27 APR 1962 |
|
| Authors:
LOCKHEED MISSILES AND SPACE CO INC SUNNYVALE CA
|
|
| PAYLOAD CONSOLE, PART NO. 1513400-501, MODEL NO. 205-146; PART NO. 1513400-701, MODEL NO. 205-146; PART NO. 1518779-501, MODEL NO. 205-644. OPERATION AND SERVICE MANUAL. |
20 APR 1962 |
|
| Authors:
LOCKHEED MISSILES AND SPACE CO INC SUNNYVALE CA
|
| This manual contains operation and service instructions for the Payload Console, Part No. 1513400-501 and 1513400-701, Model No. 205-146, and Part No. 1518779-501, Model No. 205-644. This manual is concerned primarily with descriptions and functional details of equipment. |
|
| RECORDER CONSOLE PART NO. 1517461-501. MODEL NO. 205-113. OPERATION AND SERVICE MANUAL. |
20 APR 1962 |
|
| Authors:
LOCKHEED MISSILES AND SPACE CO INC SUNNYVALE CA
|
| This manual contains operation and service data for Recorder Console, Part No. 1517461-501, Model 205-113 for use in the Launch Operations Building (LOB) of Complex 75-3 for Project 102. This manual is concerned primarily with descriptions and functional details of equipment manufactured by LMSC. Major components furnished by vendors are described only to the extent necessary to explain their function as part of this console. This recorder console, consisting of ... |
|
| Design and Analysis of Centaur Intermediate Bulkhead Improvements, |
20 APR 1962 |
|
| Authors:
F. G. Rosacker; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
|
| The report outlines the design and analysis approach in a program to improve the Centaur intermediate bulkhead. (Author) |
|
| Z(PROGRAM 201)ZRELIABILITY TEST OF PROPELLANT SHUTOFF VALVES P/N 1062804-1. |
16 APR 1962 |
|
| Authors:
LOCKHEED MISSILES AND SPACE CO INC SUNNYVALE CA
|
| This report describes a reliability test program that was applied to IRFNA and UDMH propellant shutoff valves. |
|
| PERSONNEL PLANNING INFORMATION FOR POINT ARGUELLO LAUNCH COMPLEX 2. |
15 APR 1962 |
|
| Authors:
LOCKHEED MISSILES AND SPACE CO INC PALO ALTO CA
|
|
| Atlas Space Booster Flight Test Plan for Booster No. 179D, Atlas-Agena B-Mariner R-Program AT AMR. |
15-Apr-1962 |
|
| Authors:
GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
|
| This report describes the test plan for the second Atlas booster vehicle to be utilized in the flight operation of the Mariner R-Agena B program at AMR. The primary purpose of the second Mariner R flight is a Venus fly-by of an instrument package launched with the composite Atlas-Agena B-Mariner R/Spacecraft vehicle system, and secondary, to obtain scientific data on space media. The planned Atlas portion of this launch is ... |
|
| NOSE FAIRING SUPPORT TEST, |
09 APR 1962 |
|
| Authors:
L. Lewton; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
|
| The object of the test was to determine if the structural integrity of the EID 7512 tank would be maintained while filled with liquid nitrogen and subjected to angular loads. (Author) |
|
| Design Proof Test Report for Centaur Fill and Drain Valve Assembly GD/A Part No. 57-23209, Spec. No. 57-23209, Vendor-GD/Astronautics, Vendor P/N, |
09 APR 1962 |
|
| Authors:
D. E. Lawrence; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
|
| The report covers the design proof testing performed on the Centaur fill and drain valve assembly. (Author) |
|
| MIDAS PMR AEROSPACE GROUND EQUIPMENT ENGINEERING ANALYSIS REPORT. VOLUME I. GROUND HANDLING AND SERVICE EQUIPMENT. |
06 APR 1962 |
|
| Authors:
LOCKHEED MISSILES AND SPACE CO INC SUNNYVALE CA
|
|
| Mercury Test Summary for Major Critical Components Airborne Equipment, |
01 APR 1962 |
|
| Authors:
D. W. Heagy III; H. L. Newman; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
|
| This report presents the qualification or approval status of major critical components on the Mercury portion of WS107A-1. All components are operating, non-standard, airborne CFE components. (Author) |
|
| GROUND HANDLING AND SERVICING EQUIPMENT. AGENA B MODEL NO. 5205 THROUGH 16205. OPERATION AND SERVICE MANUAL |
30 MAR 1962 |
110 pages |
| Authors:
LOCKHEED MISSILES AND SPACE CO INC SUNNYVALE CA
|
 | The ground handling equipment covered in this manual is used for handling and supporting Agena B vehicles while they are being assembled, disassembled, transported, transferred, stored, lifted, tested, alined, and mated with their companion booster adapter and booster on the launch pad. Other equipment covered in this manual is used for handling and supporting the booster adapter. For convenience, the ground handling equipment is divided into the following four categories: ... |
|
| NASA AMR AEROSPACE GROUND EQUIPMENT ENGINEERING ANALYSIS REPORT. REVISION B, VOLUME III. LAUNCH CONTROL SYSTEMS. |
30 MAR 1962 |
|
| Authors:
LOCKHEED MISSILES AND SPACE CO INC SUNNYVALE CA
|
| This report covers AGE for LCS equipment and operations for the NASA Ranger Program at the AMR, Air Force Missile Test Center, Launch Complex No. 12, Cape Canaveral, Florida. LCS provides equipment for monitoring and controlling the Agena vehicle supplies equipment for distribution of electrical power used in monitoring and controlling the launch pad and countdown operations. The LSC equipment also initiates and monitors simulated flight conditions of the Agena ... |
|
| Atlas/Agena Flight Test Directive for Atlas 110D, |
27 MAR 1962 |
|
| Authors:
D. E. Cole; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
|
| The purpose of the GD/A FTD is to provide a working document to define objectives and to set forth evaluation criteria, preparations and support requirements for the pre-launch and launch portion of the Atlas Booster for each Atlas Agena flight test. (Author) |
|
| Atlas/Agena Flight Test Directive Atlas Missile 118D, |
23 MAR 1962 |
|
| Authors:
W. E. Schmitt; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
|
| The purpose of this report is to present a combined pre-flight check-out plan for Atlas 118D as well as preliminary flight performance data. (Author) |
|
| DIGITAL AND ANALOG PAYLOAD GROUND HANDLING EQUIPMENT AGENA MODEL NO. 11205 AND 16205. OPERATION INSTRUCTIONS. |
16 MAR 1962 |
|
| Authors:
LOCKHEED MISSILES AND SPACE CO INC SUNNYVALE CA
|
|
| Evaluation Test of Centaur Rate Group Operation in High Altitude Chamber. Drawing No. 55-40001, |
13 MAR 1962 |
|
| Authors:
D. D. Blanchard; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
|
| A typical mission of the Centaur vehicle calls for operation of the autopilot during high altitude environmental conditions. It is important that the rate group package and other autopilot packages reach a stabilized operating temperature at which the operating characteristics of the autopilot are not adversely affected. This test, therefore, was performed to test the rate group package under simulated high altitude conditions, consisting of the low absolute pressure of ... |
|
| Mercury Test Summary for Major Critical Components Airborne Equipment, |
01 MAR 1962 |
|
| Authors:
D. W. Heagy III; H. L. Newman; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
|
| The report presents the qualification or approval status of major critical components on the Mercury portion of WS107A-1. All components are operating, non-standard, airborne contractor furnished equipment components. (Author) |
|
| Centaur Propellant Utilization Ratio Error Detector Assembly. Vibration Test Procedure. |
28 FEB 1962 |
|
| Authors:
B. A. Lanterman; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
|
| The purpose was to specify requirements and procedures for testing and checkout of the Centaur ratio error detector assembly during vibration. (Author) |
|
| HORIZON SENSOR TARGET. PART NO. 1460264. OPERATION AND SERVICE MANUAL. |
23 FEB 1962 |
|
| Authors:
LOCKHEED MISSILES AND SPACE CO INC SUNNYVALE CA
|
| The horizon sensor target simulates altitude, roll attitudes, and pitch attitudes of an Agena vehicle in flight for checkout of the horizon sensors. The target is placed over the horizon sensor window lens. A lens focuses radiation from the circular earth heater into the window. Between the target lens and the heater are two circular shutters which control the amount and direction of radiation exposed to the sensor. Each shutter ... |
|
| SPACECRAFT CONDITIONING (S-27 COMPOSITE GROUND COOLING TEST), |
16 FEB 1962 |
|
| Authors:
F. D. D'Alo; LOCKHEED MISSILES AND SPACE CO INC SUNNYVALE CA
|
| The objectives of this test were to evaluate the Douglas Nose Cone, to determine the quantity of air supplied to the Agena Vehicle while pressurizing the cone with a Type 15 Air Conditioner, and to obtain performance data on the Type 15 Air Conditioner, S/N 08. The Douglas Nose Cone was identified as Fairing, Space Vehicle Assembly, Part Number 5873805. |
|
| Centaur Liquid Hydrogen Transfer Line Flex Elbow Load Test, |
14 FEB 1962 |
|
| Authors:
M. Klassen; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
|
| The object of the test was to measure the force imposed by the transfer line flex elbow at its connect point with the airborne centaur tank under simulated propellant loading conditions. (Author) |
|
| Centaur C-T Vehicle Thermal Protection Criteria, |
09 FEB 1962 |
|
| Authors:
P. L. Sutton; W. R. Ginsky; R. O. Barkdoll; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
|
| Several components of the Centaur need special thermal protection in the Tullahoma Test to achieve the test objectives. The method of heat addition, the insulation requirements, and the purge requirements for the critical areas are given herein. (Author) |
|
| PAYLOAD AND CAPSULE TEST PLUG CHECKOUT CONSOLE PART NO. 1595985, MODEL NO.205-1005-1. OPERATION AND SERVICE MANUAL. |
01 FEB 1962 |
|
| Authors:
LOCKHEED MISSILES AND SPACE CO INC SUNNYVALE CA
|
|
| PREVENTIVE MAINTENANCE TECHNICAL MANUAL: TRAILER, DRAWING 55-09001, PALLET, DRAWING 55-91106, UPPER STAGE, MISSILE. |
01 FEB 1962 |
|
| Authors:
W. A. Carle; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
|
| This manual contains preventive maintenance instructions for the TRAILER AND PALLET, UPPER STAGE, MISSILE. GD/Astronautics Drawing NOs. 55-09001 and 55-91106. (Author) |
|
| Mercury Test Summary for Major Critical Components Airborne Equipment, |
01 FEB 1962 |
|
| Authors:
D. W. Heagy III; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
|
| The report presents the qualification or approval status of major critical components on the Mercury portion of WS107A-1. All components are operating, non-standard, airborne contractor furnished equipment components. (Author) |
|
| Z(MIDAS)ZRELIABLITY QUARTERLY REVIEW (1 NOVEMBER THROUGH 31 JANUARY 1962). |
FEB 1962 |
|
| Authors:
LOCKHEED MISSILES AND SPACE CO INC SUNNYVALE CA
|
|
| Validation Procedure Centaur Propellant Utilization Error Ratio Detector Exerciser, SM-1026. |
31 JAN 1962 |
|
| Authors:
D. A. Lanterman; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
|
| The procedure constitutes validation of the Centaur propellant utilization ratio error detector test equipment. (Author) |
|
| Centaur Booster Static Inverter Evaluation Test, Specification No. 55-06142, |
24 JAN 1962 |
|
| Authors:
J. K. Gilbert; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
|
| The static inverter was subjected to the temperature-altitude-humidity, and acceleration tests. (Author) |
|
| Z(MIDAS AND NASA SYSTEMS.)ZPORTABLE HYDRAULIC POWER UNIT. PART NO. 1062331-1. SERIAL NO. 205-256-7, 205-256-8. OPERATION AND SERVICE MANUAL. |
19 JAN 1962 |
|
| Authors:
LOCKHEED MISSILES AND SPACE CO INC SUNNYVALE CA
|
|
| ADVENT SYSTEM. PAYLOAD GROUND HANDLING EQUIPMENT. AGENA MODEL NO. 8205. OPERATION INSTRUCTIONS. |
12 JAN 1962 |
|
| Authors:
LOCKHEED MISSILES AND SPACE CO INC SUNNYVALE CA
|
|
| NASA SYSTEM. GROUND HANDLING EQUIPMENT FOR AGENA SATELLITE MODEL NO. 10205. OPERATION INSTRUCTIONS. |
12 JAN 1962 |
|
| Authors:
LOCKHEED MISSILES AND SPACE CO INC SUNNYVALE CA
|
|
| AMR Tanking History on Atlas 104D/Centaur C-2. |
10 JAN 1962 |
|
| Authors:
GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
|
| This report incompasses all facility and missile checkout tankings, performed on the Atlas 104D and Centaur No. 2, beginning with an Atlas fuel tanking 27 April 1961 and culminating with a dual Centaur tanking 19 September 1961. The primary purpose of this report is to present significant information leading to the determination of propellant weights, tanking control capability and tanking monitor system performance. (Author) |
|
| Range Safety Trajectory and Dispersion Information for the Atlas-Centaur Vehicle No. 1, |
02 JAN 1962 |
|
| Authors:
L. Bleitz; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
|
| This report is an addendum to AE61-1219, RANGE SAFETY TRAJECTORY AND DISPERSION INFORMATION FOR THE ATLAS CENTAUR VEHICLE NO. 1., 8 December 1961. Since that date, certain flight parameters have been changed. Although the new trajectory remains within the bounds of the 30 dispersions, it was deemed prudent to rerun at least the nominal trajectory with the standard range safety data tabulations including premature cut-off data. (Author) |
|
| Centaur Nose Fairing Jettison Test, |
28 DEC 1961 |
|
| Authors:
J. H. Derango; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
|
| The object of the test was to evaluate the Centaur Nose Fairing Fuel Vent Duct Seal and disconnect mechanism and to determine the effect of the vent duct disconnect loads on the trajectory of the fairing during jettisoning. (Author) |
|
| Centaur Hydraulic Power Package Pump Shaft Seal Evaluation Test Report. Drawing No. 55-08500-803 (Spec No.) 55-08600, |
21 DEC 1961 |
|
| Authors:
Earl M. Walker; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
|
| The purposes of these tests were: to isolate the cause for recent seal failures, to evaluate the sealing capabilities of two pump shaft seal configurations, to determine the spring pre-load that is most compatible with seal wear, and to determine the torque required to turn the pump shaft. (Author) |
|
| Pre-Production Test Report for Agena Booster Boiloff/Valve Revision GD/A Part No. 27-80750-851 Vendor - GD/Astronautics, |
20 DEC 1961 |
|
| Authors:
William Graham; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
|
| Pre-production testing was performed on a boiloff valve to provide a basis of qualification. |
|
| RELIABILITY ANALYSIS OF CRITICAL AND MAJOR AGE Z(FOR PROGRAM 201.)Z |
15 DEC 1961 |
|
| Authors:
D. C. Swisher; LOCKHEED MISSILES AND SPACE CO INC SUNNYVALE CA
|
|
| Study of Ramjet Fuel in Atlas for the Atlas/Centaur/Advent Program, |
15 DEC 1961 |
|
| Authors:
P. F. Fernald; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
|
| The purpose of the study was to evaluate the payload improvement potential available if rocket propellant (RP-1) fuel were replaced with Ramjet (RJ-1) fuel in the first stage of Atlas/Centaur for the Advent Program. (Author) |
|
| Evaluation Test of Agena Booster Boiloff Valve Revision DWG. No. (Sensor) 27-81448, DWG. No. (Boiloff Valve) 27-80750, |
13 DEC 1961 |
|
| Authors:
William C. Graham; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
|
| The purpose of the test was to evaluate the design of the boiloff valve and sensor controller for a modulation band of 5.1 psig and 5.4 psig and to prove-out the aforementioned design improvement changes. The strain characteristics of the boiloff valve and sensor controller bellows were to be found under conditions of cycling and vibration. Also the ability of the boiloff valve to withstand greater tank pressures was to ... |
|
| Centaur Fill and Drain Valve Flow and Pressure Drop Tests, |
12 DEC 1961 |
|
| Authors:
J. E. Frink; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
|
| This report defines tests performed to determine flow rate versus pressure drop across the Centaur liquid oxygen and liquid hydrogen fill and drain Valves 57-23209 while simulating missile environmental conditions. (Author) |
|
| FLIGHT DYNAMIC LOAD ANALYSIS OF THE ATLAS/CENTAUR BETA CONFIGURATION, |
08 DEC 1961 |
|
| Authors:
C. P. Kelly Jr; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
|
| This report presents the results of an analytical investigation of the lengthened (beta) Atlas/Centaur primary airframe structural integrity. The scope of the presentation includes: (1) description of the analysis and control performance of the booster phase load relief autopilot, (2) description of the design criteria and resulting design loads, (3) a stress analysis demonstrating the ability of the lengthened Centaur and the Atlas airframe to support the design loads. (Author) ... |
|
| Range Safety Trajectory and Dispersion Information for the Atlas-Centaur Vehicle No. 1, |
08 DEC 1961 |
|
| Authors:
L. Bleitz; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
|
| The range safety section of the Atlantic Missile Range at Cape Canaveral, Florida requires certain data for each flight in order to establish range safety criteria. The required data include the following: Reference, fast, slow, and nose right dispersion trajectories; Impact areas for the booster package and sustainer tank sections; Impact areas and remaining time of flight for premature cutoff times; Maximum turning rate of the missile velocity vector in ... |
|
| Mercury/Atlas MA-5 (Atlas Missile 93D). |
06 DEC 1961 |
|
| Authors:
GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
|
| This report has been prepared to present preliminary information relative to the flight of Mercury/Atlas MA-5 93D. The information presented is based on visual observation and data evaluation to the extent permitted by time limitations. It should be considered as preliminary only and the final reports on this flight referenced for further information. (Author) |
|
| Systems Test of DPF Type Servo Valves, |
04 DEC 1961 |
|
| Authors:
J. B. Cross; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
|
| Testing was conducted to determine the system dynamic load frequency response characteristics of the differential pressure feedback servo valve. (Author) |
|
Ground Support Sys & Facil for Space Vehicles
