| A Review of Communications Satellites and Related Spacecraft for Factors Influencing Mission Success. Volume II. Appendices A, B, C. |
17 NOV 1975 |
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| Authors:
F. W. Buehl; R. E. Hammerand; AEROSPACE CORP EL SEGUNDO CA SATELLITE SYSTEMS DIV
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 | Volume II of a three volume review of communications satellite and related spacecraft programs to identify factors influencing mission success. Includes a summary of military and commercial programs to date evaluating factors which contributed to success or failure of each. (Author) |
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| Manufacturing Methods for a 2-kW Traveling Wave Tube. |
NOV 1969 |
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| Authors:
M. M. Seldon; VARIAN ASSOCIATES INC PALO ALTO CA TWT DIV
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| The objective of the program is the design and realization of manufacturing methods, processes, techniques, and special equipment for fabricating a 2-kW pulse space power amplifier in production quantities. (Author) |
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| FRACTURE DATA ON PROSPECTIVE ALLOYS FOR DEEP SUBMERGENCE AND SPACE APPLICATIONS. |
NOV 1968 |
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| Authors:
Fred R. Stonesifer; Herschel L. Smith; NAVAL RESEARCH LAB WASHINGTON D C
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| Explorations into the ocean and space demand structural materials of higher fracture toughness and strength-to-weight ratio. Nickel-steels and titanium alloys appear promising for such applications. This report presents fracture toughness data obtained through nearly 600 tests performed on specimens from 134 plates of materials in these two classes. (Author) |
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| ON A HEAT AND MASS TRANSFER PROBLEM WITH TWO MOVING BOUNDARIES, |
SEP 1968 |
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| Authors:
J. C. Y. Koh; J. F. Price; R. Colony; BOEING SCIENTIFIC RESEARCH LABS SEATTLE WASH MATHEMATICS RESEARCH LAB
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| The heat and mass transfer problem in a passive transpiration cooling system involving two moving boundaries is formulated. A numerical calculation scheme and computer program are developed to solve the problem. Computations are performed for the case of porous tungsten infiltrated with copper exposed to an environment of high pressure and high heat flux. The effects of porosities and the radius of curvature on the thermal response and infiltrant recession ... |
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| STABLE EQUILIBRIUM ORIENTATION OF A SPACECRAFT WHICH CONTAINS A MOMENTUM WHEEL. |
10 MAY 1968 |
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| Authors:
John U. Beusch; MASSACHUSETTS INST OF TECH LEXINGTON LINCOLN LAB
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| The orientation of a spacecraft when it is in a stable equilibrium state is studied. The spacecraft contains a single momentum wheel which stores angular momentum. The axis of the wheel is not necessarily parallel to a principal axis of the spacecraft. For an arbitrary but fixed speed of the wheel relative to the spacecraft body, it is shown that there may be one, two, or three stable equilibrium points. ... |
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| TECHNOLOGY FEASIBILITY SPACECRAFT (TFS) TECHNOLOGY REPORT. VOLUME IV. STERILIZATION AND BIOASSAY. |
FEB 1968 |
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| Authors:
R. Mckinney; MARTIN MARIETTA CORP DENVER COLO DENVER DIV
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| The purpose of this portion of the Technology Feasibility Spacecraft (TFS) Program was to gain experience in the conduct of bioassays to be used in accurately estimating the incremental and total microbial burden occurring during the assembly and test of a full-scale spacecraft. (Author) |
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| EFFECT OF INTERNAL RADIATION ON THE TEMPERATURE DISTRIBUTION OF A SPHERICAL SHELL. |
JAN 1968 |
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| Authors:
Donald C. Todd; Jan A. van der Bliek; Han M. Hsia; ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AIR FORCE STATION TENN
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| The report is a continuation of a study of the effects of internal heat transfer on the temperature of hollow spacecraft and the requirements for thermal modeling. Considered is the effect of internal heat transfer by radiation on the temperature distribution. The equation governing the heat transfer of a spherical shell exposed to parallel radiation is derived; conduction and radiation are considered. The general equation is simplified by assuming steady ... |
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| A TECHNIQUE FOR ESTIMATING SPACE POWER SYSTEM COSTS. |
OCT 1967 |
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| Authors:
J. G. Fish; AEROSPACE CORP EL SEGUNDO CALIF EL SEGUNDO TECHNICAL OPERATIONS
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| A technique is presented for estimating development and procurement costs for space power subsystems. The data employed in deriving the costing relationships primarily stem from the 1966 DOD Space Power Study and the Aerospace Corporation's experience and data sources. These sources represent the most current and extensive survey of both costs and technologies of the space power field that exist today. Energy sources and power conversion schemes are analyzed separately ... |
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| THE ABC OF OUTER-SPACE PILOTING, |
28 JUL 1967 |
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| Authors:
I. Merkulov; FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO
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| Spacecraft guidance, control, stabilization, correction, deceleration, and landing systems are discussed. It is noted that the exhaust velocity of a spacecraft is 2000 - 4000 m/sec and that a parachute-landing engine system was employed in the soft landing of the 'Voskhod' spacecraft. The engine was switched on when the spacecraft was close to the Earth's surface so that it decelerated the drop of the parachute reducing the velocity to a ... |
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| INFLUENCE OF STRUCTURAL ELASTICITY ON ATTITUDE, STABILITY AND DRIFT OF SPACECRAFT. |
01 JUL 1967 |
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| Authors:
Felix Buckens; Raymond Gorez; Pierre Yves Willems; LOUVAIN UNIV (BELGIUM) INSTITUT DE MECANIQUE APPLIQUEE
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| The effect of the spin on the behavior of an elastic satellite has been investigated in different cases of external alternating torques. A solution on analog computer was further obtained for the equations of vibration of the elastic parts of a spin stabilized spacecraft. The effect of the magnetic field on the motion of a spin stabilized satellite has been treated in a first approximation as for a rigid body ... |
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| THE 'MAGNETIC WALLS' OF A COSMIC SHIP, |
31 MAR 1967 |
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| Authors:
a. petrov; FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO
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| The popular-science article deals with the protection of spaceships and their crews from ionizing radiation and charged particles through magnetic fields created by superconducting alloys. |
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| STABLE EQUILIBRIUM ORIENTATION OF A SPACECRAFT WHICH CONTAINS A MOMENTUM WHEEL. |
20 FEB 1967 |
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| Authors:
J. U. Beusch; MASSACHUSETTS INST OF TECH LEXINGTON LINCOLN LAB
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| The orientation of a spacecraft when it is in a stable equilibrium state is studied. The spacecraft contains a single momentum wheel which stores angular momentum. The axis of the wheel is not necessarily parallel to a principal axis of the spacecraft. For an arbitrary but fixed speed of the wheel relative to the spacecraft body, it is shown that there may be one, two, or three stable equilibrium points. ... |
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| SUPPORT FACILITIES AND EQUIPMENT FOR MISSILE AND SPACE SYSTEMS, |
20 FEB 1967 |
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| Authors:
Victor Klein; LIBRARY OF CONGRESS WASHINGTON D C AEROSPACE TECHNOLOGY DIV
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| The compilation of abstracts is the 21st report in a series (formerly titled 'Protective Structures and Components') on support facilities and equipment for missiles and space systems. The report includes data on techniques for Arctic and permafrost areas, road construction methods, new construction of main and branch railroad lines, railroad construction techniques, construction materials, description of a floating harbor crane, and transportation of containerized goods by tractor trailer trains. Appended ... |
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| A SPACEFLIGHT EXPERIMENT TO ASSESS RADIATION SHIELDING CALCULATIONS. |
APR 1966 |
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| Authors:
William H. Coop; Mac C. Chapman; NORTHROP SPACE LABS HAWTHORNE CALIF
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| The design, development, and testing of a spaceflight experiment to provide data for the assessment of mathematical shielding study models was investigated. The experiment was to provide data for assessment of mathematical shielding study models for comparison with the results obtained by a computer program. This experiment measured proton depth-dose distribution, bremsstrahlung production, and the effects of radiation anisotropy, energy spectrum, and vehicle heterogeneity under known (measured) conditions of radiation ... |
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| A SIMPLE NUMERICAL SOLUTION FOR HEAT CONDUCTION IN A SOLID WITH A RECEDING SURFACE, |
20 AUG 1964 |
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| Authors:
J. J. Brogan; LOCKHEED MISSILES AND SPACE CO SUNNYVALE CALIF
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| Recent interest in use of sublimation for cooling infrared detectors to cryogenic temperatures, and continued use of the ablation concept for thermal protection of re-entry vehicles, requires an accurate yet simple method of solution to problems of heat conduction in solids with a receding surface. General analytical solutions are not available and exact solutions are known only for the special cases. A simple numerical method of solution is described, and ... |
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| Microencapsulated Sealant and Self-Sealant Components. |
AUG 1964 |
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| Authors:
John F. Hanny; NATIONAL CASH REGISTER CO DAYTON OH
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| The purpose of this research program was to encapsulate potential sealant and self-sealant components. The microcapsules formed were to be chemically and environmentally resistant, yet possess the capability of being ruptured by such forces as pressure, shock and shear. Two mixtures of triethylene tetramine and Quadrol (1,1,1',1'-ethylenedinitrilo tetra-2-propanol) have been encapsulated by interfacial polycondensation and formulated into single package capsular self-sealant systems. Evaluations have indicated that both of these systems ... |
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| AUXILIARY POWER SYSTEMS FOR SPACECRAFT. AN ANNOTATED BIBLIOGRAPHY, |
MAY 1963 |
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| Authors:
Peter R. Stromer; LOCKHEED MISSILES AND SPACE CO SUNNYVALE CALIF
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| One hundred and thirty-five references have been selected from the 1962-1963 literature reporting research and development in auxiliary power systems for spacecraft. Emphasis has been placed on solar and nuclear auxiliary power sources with only a representative sampling of other concepts such as magnetohydrodynamics, biochemical and hydrox fuel cells, batteries, etc. Subject and corporate source indexes are provided. The facilities of the Lockheed Missiles and Space Company, Technical Information Center ... |
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| AEROSPACE GROUND EQUIPMENT ENGINEERING ANALYSIS REPORT VOLUME III. LAUNCH CONTROL SYSTEMS. |
31 DEC 1962 |
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| Authors:
LOCKHEED MISSILES AND SPACE CO INC SUNNYVALE CA
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| This report consists of: (1) a general description of Launch Control Systems (LCS) operations, functions, and equipment at both Complexes 75-3 and 75-1; (2) diagrams illustrating equipment locations; and (3) a technical analysis of all Launch Control Systems equipment used at Launch Complexes 75-3 and 75-1, describing the design functions, and location. To avoid duplication of information, reference is made to the equipment of Launch Complex 75-1 only as it ... |
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| RELIABILITY ANALYSIS OF CRITICAL AND MAJOR AGE Z(FOR PROGRAM 201.)Z |
15 DEC 1961 |
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| Authors:
D. C. Swisher; LOCKHEED MISSILES AND SPACE CO INC SUNNYVALE CA
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