Evaluation of a semi-active gravity gradient system. Volume I - Technical summary
Semi-active gravity gradient system for attitude control of earth oriented spacecraft
GRAVITY GRADIENT SATELLITE↗
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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Space Programs Summary No. 37-40, Volume IV for the Period June 1, 1966 to July 31, 1966. Supporting Research and Advanced Development
Space program research and advanced development in guidance and control, engineering mechanics, environmental simulation, propulsion, space sciences, and telecommunications
ENGINEERING DEVELOPMENT↗
Fundamental research in solid state energy conversion processes Semiannual technical summary report no. 6, 1 Dec. 1965 - 1 Jul. 1966
Fundamental processes in optical behavior of solids and associated with photovoltaic energy conversion
ENERGY CONVERSION↗
Study of expandable, terminal decelerators for Mars atmosphere entry Interim summary report, Dec. 1965 - Jun. 1966
Design of expandable terminal decelerators for Mars atmosphere entry by Mars-lander capsule
MARS SPACECRAFT↗
Synthesis of atactic and stereoregular vinylaromatic polymers and a study of their reactions with alkali metals, part IA SUMMARY report
Synthesis and characterization of vinylaromatic polymers
SYNTHESIS↗
Optical technology Apollo extension system, part I. Executive summary report
Evaluation and recommended experiments for Apollo Optical Technology Extension System
APOLLO PROJECT↗
Mass loading effects on localized vibratory environments of rocket vehicles Technical summary report, 30 Jun. 1965 - 31 Jul. 1966
Mass loading effects on localized vibratory environments of rocket vehicles
VIBRATORY LOADING↗
Research Summary on Fracture of Swollen Rubber
Crack propagation and critical strain in swollen rubber
CRACK PROPAGATION↗
Steady-state and dynamic operating characteristics of a simulated three-loop space Rankine-cycle powerplant Summary report, 15 May 1964 - 1 May 1965
Steady state operating and dynamic response characteristics of simulated three-loop Rankine cycle space power conversion system of SNAP-8 TYPE
POWER CONVERSION↗
Program of Research on the Management of Research and Development Annual Report, 1965 - 1966 and Program Summary, 1960 - 1966
Research program on management of research and development
MANAGEMENT↗
Summary, study of pump discharge pressure oscillations
Analytical data on pump-generated pressure, flow, blade wake, cavitation, and stall oscillations for application to turbopump design
BLADE↗
Thermal scale modeling in a simulated space environment Technical summary report, Jun. 1, 1964 - Apr. 30, 1966
Thermal scale modeling in simulated space environment
THERMAL ENVIRONMENT↗
High pressure large flow rate flexible connector system Final summary report
Design study, material selection, and stress analysis of high-pressure large flow rate flexible connector system
CONNECTOR↗
A theoretical study of the aerodynamic characteristics of lifting-body entry vehicles Summary report, Mar. 1965 - Mar. 1966
Aerodynamic characteristics of lifting-body entry vehicles
AERODYNAMIC CHARACTERISTICS↗
Separator development for a heat sterilizable battery Quarterly summary progress report no. 1, 1 May - 31 Aug. 1966
Ligand-containing vinyl polymer systems for evaluation as separator materials in Ag-Zn batteries
SEPARATOR↗
Space Programs Summary No. 37-41, Volume III FOR the Period July 1, 1966 to August 31, 1966. the Deep Space Network
Deep Space Network - tracking and navigational accuracy analysis, communications research, development, and engineering, and Deep Space Station engineering and operations
DEEP SPACE NETWORK /DSN/↗
Heat exchanger test experimental apparatus. Section I - Helium heater. Section II - Helium circulator Summary report
Molybdenum heater tube for heating helium to operating temperature of high temperature heat exchanger facility - performance of helium circulator
CLOSED LOOP SYSTEM↗
260-in.-dia motor feasibility demonstration program Final program summary report, Jun. 1963 - Apr. 1966
Static test firing of 260 inch diameter solid rocket motors for demonstrating feasibility
SOLID PROPELLANT ROCKET ENGINE↗