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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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Release mechanism for actuation of automatic device operates on system of restrained energy force, which is automatically released by electrical charge that may be applied by manual switch or, in remote application, by RF impulse, received by conventional electronic circuitry.
Description of scan actuator geared servomechanism for Mariner Mars 1969 spacecraft
Design and testing of squib-actuated valve
Patent data on gas actuated bolt disconnect assembly
Actuator using compressed gas as driving force to control valve handling large liquid flows
Study, design, fabrication, and evaluation of thermally actuated valves for spacecraft instrumentation requiring small zero leakage
Actuator disk theory and flow field calculations for propeller induced flow with nonuniform circulation distribution
High temperature polyimide actuator rod seals for aircraft hydraulic systems
Mariner 4 scan platform structure and actuator design, development and performance
Scan platform servomechanical actuator for Mariner Mars 1969 spacecraft, emphasizing gear arrangement and train dynamics
Nonmagnetic explosive actuated indexing device permitting precise 180 deg rotation of magnetometer sensor on Pioneer 6 spacecraft
Explosively actuated /pyromechanical/, devices for spacecraft, discussing guidelines for design, testing, application and cost efficiency
Nonmagnetic lightweight oscillating actuator for multiple indexing of spacecraft magnetometer
Fluid thermal actuator for temperature control of ITOS /Improved Tiros Operational System/ meteorological satellite, discussing design and performance
Surveyor camera double acting rotary solenoid actuated focal plane shutter utilizing two blades in parallelogram linkage
Mariner Mars 1971 gimbal actuator design and life test for autopilot system using hypergolic bipropellant rocket engine
Two types of polyimide seals are developed for hydraulic actuator rod in low pressure second stage of two-stage configuration. Each seal melts test objectives of twenty million cycles of operation at 534 K. Analytical and experimental study results are discussed. Potential applications are given.