(LAUNCH VEHICLES - Storming Media

LDEF Mission Update: Composites in Space.

MAY 1991

Authors: R. C. Tennyson; G. E. Mabson; W. D. Morison; J. Kleiman

The full text of this report is not available and therefore is not for sale. This information is provided for reference purposes only.

Green Light to Plastic Engine Parts.

MAY 1991

Authors: D. F. Baxter

Tuning Up the Metals in Auto Engines.

MAY 1991

Authors: S. R. Lampman

FMS Control Goes Back to Basics.

MAY 1991

Authors: T. Baer

Reliability of Space Systems,

07 NOV 1969

Authors: A. Marks; FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OH

A general discussion is presented on space vehicles. Sources and causes of malfunctions are discussed, and emergency preventive methods are outlined. The types and frequency of occurrence of malfunction in various space vehicles are given in tabulated form. It is pointed out that the actual reliability is lower than the theoretical one. (Author)

Determination of the Effects of Acceleration-Induced Loads on a Propellant System Bladder.

MAY 1969

Authors: John Denker; AIR FORCE ROCKET PROPULSION LAB EDWARDS AFB CA

Four sections of propellant system bladders were evaluated during five tests on the 1-15 Test Area Centrifuge. Two specimens were accelerated to 25 g applied laterally to the test item and two specimens were accelerated to 20 g applied longitudinally. (Author)

Evaluation of a Mariner Propellant System Bladder Using Centrifuge Facility 1-15.

MAR 1969

Authors: John Denker; AIR FORCE ROCKET PROPULSION LAB EDWARDS AFB CA

Twelve evaluations of a propellant system bladder design intended for use on Mariner space vehicles were completed using the AFRPL centrifuge to impose acceleration-induced loads of ten, twenty, and thirty times the force of gravity. The AFRPL Centrifuge Facility and RPRO (Operations) personnel successfully produced the requested test conditions in a routine manner. (Author)

Operation and Service Manual for Gemini B/MOL/L/V Electrical Interface Substitute 58E040504.

26 SEP 1968

Authors: MCDONNELL DOUGLAS CORP ST LOUIS MO

The purpose of the report is to familiarize personnel with the operation and service of the Gemini B/MOL/L/V Electrical Interface Substitute, 58E040504. The report describes the console, associated panels and their functions. The console is used to electrically simulate the Gemini B Spacecraft when performing functional tests on the Gemini B/MOL Launch Vehicle. (Author)

Gemini B Procedures Simulator. Performance/Design Requirements.

01 JUN 1968

Authors: MCDONNELL ASTRONAUTICS CO ST LOUIS MO

The Gemini B Procedures Simulator (GBPS) will be used for training and precedures development for the Gemini B segment of the Manned Orbiting Laboratory (MOL) program. Set forth in this document are the performance and design requirements for the GBPS. (Author)

WIND TUNNEL INVESTIGATION TO DETERMINE AERODYNAMIC CHARACTERISTICS OF A 0.03-SCALE MODEL OF THE TITAN III/MOL LAUNCH CONFIGURATION DURING THE ABORT SEQUENCE AT MACH NUMBERS FROM 0.60 TO 3.00.

AUG 1967

Authors: M. L. Homan; D. A. MacLanahan Jr; ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFS TN

A 0.03-scale model of the Titan III/Manned Orbiting Laboratory (MOL) launch vehicle was tested in Tunnels 16T and 16S of the Propulsion Wind Tunnel Facility at Mach numbers from 0.6 to 3.0 to obtain aerodynamic force and moment data on the airborne vehicle during the abort sequence. Test results show that there was a reduction in magnitude of the pitching-moment and normal-force coefficients at all angles of attack as jet ...

DEVELOPMENT OF AN ALIGNMENT AND MEASURING SYSTEM FOR LARGE AEROSPACE VEHICLES. VOLUME I.

AUG 1967

Authors: Mark Steinhacker; KOLLSMAN INSTRUMENT CORP ELMHURST NY

DEVELOPMENT OF AN ALIGNMENT AND MEASURING SYSTEM FOR LARGE AEROSPACE VEHICLES. VOLUME II.

AUG 1967

Authors: Mark Steinhacker; KOLLSMAN INSTRUMENT CORP ELMHURST NY

WIND TUNNEL INVESTIGATION TO DETERMINE PRESSURE DISTRIBUTION CHARACTERISTICS OF A 0.03-SCALE MODEL OF THE TITAN III/MOL LAUNCH CONFIGURATION DURING THE ABORT SEQUENCE AT MACH NUMBERS FROM 0.60 TO 3.00.

JUL 1967

Authors: D. A. MacLanahan Jr.; M. L. Homan; ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFS TN

A 0.03-scale model of the Titan III/Manned Orbiting Laboratory (MOL) launch vehicle was tested in Tunnels 16T and 16S of the Propulsion Wind Tunnel Facility at Mach numbers from 0.6 to 3.0 to determine pressure distributions on the airborne vehicle during the abort sequence. Test results show that the jet, simulating thrust termination, forces the solid-propellant motor induced normal shock forward. Disturbances caused by the jet produce an increase in ...

GENERAL-UTILITY SPACECRAFT AND MULTIPLE-ORBIT/PAYLOAD LAUNCH APPLICATIONS IN SPACE RESEARCH AND DEVELOPMENT,

JUL 1967

Authors: Donald F. Adamski; AEROSPACE CORP EL SEGUNDO CA LABS DIV

Costs for the majority of near-earth unmanned, space research and advanced development missions of the late 1960's and early 1970's can be significantly reduced by using multiple-orbit/payload launches involving general-utility spacecraft and orbital buses. This concept has evolved through the implementation of the new DOD Space Experiments and Flight Support Program (SEFSP). The modification and combination of previously developed spacecraft with other off-the-shelf space flight proven hardware to synthesize in ...

BUFFET RESPONSE OF AEROELASTICALLY SCALED TITAN III MISSILE CONFIGURATIONS AT TRANSONIC MACH NUMBERS.

MAR 1967

Authors: J. E. Robertson; T. R. Brice; ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFS TN

A wind tunnel investigation was conducted to obtain the structural response of 0.07-scaled aeroelastic models of Titan III missile configurations to buffet airloads at transonic Mach numbers. Test results in the form of bending-moment response in the pitch and yaw planes were obtained for various payload, upper stage, and booster combinations. The tests were conducted in the Mach number range from 0.6 to 1.4 and at angles of attack ranging ...

SSLV-5 NO. 9 POST FIRING FLIGHT TEST REPORT (FINAL EVALUATION REPORT) AND MOL-EFT FINAL FLIGHT TEST REPORT.

DEC 1966

Authors: MARTIN CO DENVER COLO

Program 624A, Standard Space Launch Vehicle C-9 (MOL/HSQ) was launched from Complex 40 at the Eastern Test Range on 3 November 1966 at 13:50:42.20 GMT (08:50:42.20 EST). This vehicle was the sixth test of the Titan 3C configuration and the tenth test of 624A program. The flight test was conducted according to Flight Plan VI. The payload consisted of a MOL simulated laboratory containing 11 experiments and the MOL configuration ...

FULL-SCALE SIMULATED ALTITUDE INVESTIGATION OF THE CENTAUR-PAYLOAD SURFACE AND FUNCTIONAL DEGRADATION RESULTING FROM THE SATURN S-IVB RETRO ROCKET EXHAUST CONTAMINANTS,

APR 1966

Authors: W. W. Muse; ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFS TN

Five tests were conducted to determine the surface contamination of the Centaur vehicle and its payload resulting from the deposition of retro exhaust particles during separation from the spent S-4B stage. The test article consisted of a full-scale model, 120-deg segment of the S-4B interstage adapter-Centaur-Payload sections of the Saturn 1B-Centaur vehicle. An S4B retro motor was mounted in the adapter section at either a 0- or 11.5-deg angle upward ...

AERODYNAMIC PERFORMANCE ANALYSIS PROGRAM 7100.

25 MAR 1966

Authors: H. H. Dempster; GENERAL DYNAMICS SAN DIEGO CA CONVAIR DIV

This document contains the open-loop design reference trajectory data used to analyze the capability of the SLV-3 to perform its role for Program 7100. This information is required by the various design groups for computation of aerodynamic heating and of structural, dynamic, and aerodynamic loads. The principal trajectory design data presented include: Mission profile and SLV-3 mission requirements; Launch vehicle description; Aerodynamics, Propulsion, weights, and environmental data; Trajectory design constraints; ...

DETAIL SPECIFICATION FOR ATLAS STANDARD LAUNCH VEHICLE SLV-3 GD/C MODEL 69,

15 JAN 1966

Authors: G. H. Wolfe; GENERAL DYNAMICS SAN DIEGO CA CONVAIR DIV

This specification covers the following launch vehicle: United States Air Force Model SLV-3 GD/C Model 69; and the Atlas Standard Launch Vehicle Utilizing a MA-5 Rocket Engine System. The Atlas Standard Launch Vehicle consists of a basic launch vehicle and mission peculiar kits. The Launch vehicle shall be used as a standard Launch Vehicle (SLV-3) to boost an upper stage and payload into a predetermined trajectory as required by the ...

X-Y PLOTTER CONSOLE. PART NO. 1589232. MODEL NO. 205-852. OPERATION AND SERVICE MANUAL.

29 JUN 1962

Authors: LOCKHEED MISSILES AND SPACE CO INC SUNNYVALE CA

This manual contains operation and service instructions for the X-Y Plotter Console. The X-Y Plotter Console is used as support equipment in the checkout and calibration of the Agena jet reaction gas valve system during subsystem test. The console generates ac step-ramp and dc triangular wave actuating signals and applies them to the flight control electronic unit and gas valves, simultaneously plotting a Cartesian coordinate graph of the generated signal ...

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)

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)

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)

Liquid Hydrogen Pressure Loss Phase II,

22 MAY 1961

Authors: P. R. LaBerge; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA

The pressure loss in the Centaur fuel system is a factor in the determination of the net positive suction head available to the turbopumps. The magnitude of the pressure loss is also required in order that the operation of the boost pump in the propellant system may be evaluated. This report describes the method of determining the pressure loss at various flow rates. (Author)

FLIGHT TEST REPORT, MERCURY/ATLAS MA-1 (ATLAS 50D), 29 Jul 60. AMR RANGE TEST 1505. CONVAIR TEST P4-501-00-50. Z(WS 107A-1)ZFLIGHT TEST WORKING GROUP,

22 AUG 1960

Authors: R. E. Payne; K. E. Newton; R. W. Taylor; F. R. Radcliff; W. H. Caldwell; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA

The primary objective for this flight was to determine the integrity of the Mercury Capsule. Other first order objectives for NASA included evaluation of the capsule structure and afterbody shingles, afterbody heating, flight dynamic characteristics, capsule re-entry system and recovery procedures. (Author)

EVALUATION OF HYDROGEN VAPORIZER,

10 AUG 1960

Authors: R. B. Murphy; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA

This report is a performance evaluation of a hydrogen vaporizer used in pressurized liquid transfer during propellant tank loading.

VEGA MODEL VORTEXING INVESTIGATION,

04 AUG 1960

Authors: I. N. Gere; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA

This report describes configurations tested to control fluid flow at tank outlet. The object of this test was to determine if vortexing would occur at the propellant tank outlet, and to develop and to test anti-vortexing devices if vortexing occurred. (Author)

GEYSERING STUDY LOX TRANSFER SYSTEM (HIGH TOWER) MODEL 55 - CENTAUR,

23 JUN 1960

Authors: I. N. Gere; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA

This report is aimed at studying the causes and effects of geysering into the missile tank, and investigating the minimum flow required to prevent geysering and top off the missile. (Author)

EXPLOSIVE RELEASE DEVICE TEST -- CENTAUR,

05 MAY 1960

Authors: J. D. Orr; C. K. Perkins; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA

A quick-acting device is required to release the Centaur upper-stage jettisonable insulation. The report presents the results of an investigation of the characteristics of different types of explosive release devices -- explosive nuts and the explosive bolt. The quantities to be measured included the peak recoil force generated by the explosion, the firing delay time, the energy of the major fragment, and the extent of damaging fragmentation. The test procedures, ...

10D COUNTDOWN OPERATIONS MERCURY HS 36-1.

27 AUG 1959

Authors: GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA

This report contains the operational countdown checklist (from T-180 minutes to liftoff) for readiness and launch procedures for the 10D Mercury launch vehicle and associated support equipment. The countup procedures for securing the launch area and related equipment are also reported.

TEST EQUIPMENT PROGRAM FOR ABORT SENSING AND IMPLEMENTATION SYSTEM FOR MERCURY ATLAS FLIGHTS,

17 JUL 1959

Authors: M. Penberg; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA

The report supplies detailed information on each phase of the test equipment program for checkout of the Mercury abort sensing and implementation system; included is detailed information on test set design and use during performance of the various component, subsystem and system level checks. (Author)

INSTRUMENTATION SUMMARY PG1A AGENA ATLAS SPACE BOOSTER AT PMR,

19 JUN 1959

Authors: T. M. Wooster; GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA

This report describes the instrumentation planned to support flight testing of the PG-1A missiles utilized in conjunction with the Space program at PMR. The second stage vehicle measurements are transmitted by the second stage vehicle telemetry, and can be found in the Flight Test Directives published prior to each flight. The instrumentation configuration for this program has been established as a result of the test objectives and systems analyses. Details ...