Motion of a spinning satellite during the deployment of n asymmetrical appendages.
Motion of spinning satellite during deployment of n asymmetrical appendages, noting Pioneer spacecraft
SPIN STABILIZATION↗
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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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A method for calculating parachute opening forces for general deployment conditions.
Calculating method for parachute opening forces, system velocity, cloth pressure loading and filling time for horizontal and vertical deployment conditions
PARACHUTE FABRIC↗
Motion of a spinning satellite during the deployment of asymmetrical appendages.
Motion of spinning satellite during deployment of n asymmetrical appendages, noting Pioneer spacecraft
PIONEER SPACE PROBE↗
Flight test of a 31.2-foot-diameter modified ringsail parachute deployed at a Mach number of 1.39 and a dynamic pressure of 11.0 pounds per square foot
Flight test of 31.2-foot-diameter modified ringsail parachute deployed at Mach 1.39 and dynamic pressure of 11 pounds per square foot
FLIGHT TEST↗
Simulation of deployment dynamics of spinning spacecraft
Simulation of deployment dynamics of spinning spacecraft
SPACECRAFT DESIGN↗
Flight test of a 30-foot nominal diameter disk-gap-band parachute deployed at a Mach number of 1.56 and a dynamic pressure of 11.4 pounds per square foot
Flight test of disk-gap band parachute deployed at low supersonic speed and low dynamic pressure to obtain performance data on planetary entry parachute configurations
SUPERSONIC SPEED↗
Deployable solar array
Development, fabrication, and testing of deployable solar cell array for spin-oriented spacecraft applications
SPACECRAFT↗
Deployment mechanics for an inflatable tension-cone decelerator
Experimental design of deployable tension cone decelerator with inflatable toroids for compression resistant structures in base of cone
INFLATABLE STRUCTURE↗
The structural and librational dynamics of a satellite deploying flexible booms or antennas.
Structural and librational dynamics of satellite deploying flexible booms or antennas
LIBRATIONAL MOTION↗
Sensing techniques for initiating parachute deployment on a Mars lander vehicle.
Sensing techniques for initiating parachute deployment on Mars lander vehicle
MARS SPACECRAFT↗
Simulation of deployment dynamics of spinning spacecraft.
Simulation of deployment dynamics of spinning spacecraft, discussing test methods emphasizing gravity compensating techniques
DYNAMICS↗
A method for calculating parachute opening forces for general deployment conditions.
Calculating method for parachute opening forces, system velocity, cloth pressure loading and filling time for horizontal and vertical deployment conditions
NUMERICAL INTEGRATION↗
Deployable lattice column
Lattice column, made up of many individually collapsible sections connected in tandem, rapidly raises measuring instruments to a level appreciably above that where data is to be recorded and evaluated. The column may be collapsed by collapsing each section in sequence and is deployed by extending each section in sequence.
Mauch, H. R.↗
Flight test of a 15-foot-diameter /4.6-meter/ 120 deg conical spacecraft simulating parachute deployment in a Mars atmosphere
Flight test of conical spacecraft simulating parachute deployment in Mars atmosphere
Darnell, W. L.↗
Water pressure and accelerations during landing of a dynamic model of the Apollo spacecraft with a deployed-heat-shield impact-attenuation system
Impact water pressures, accelerations, and landing dynamics of scale model Apollo command module with deployed heat shield impact attenuation system
Stubbs, S. M.↗
Deployable large area solar cell array testing Quarterly report
Detail design, acceleration and vacuum tests, and support fixtures for deployable solar array
Source record↗
Flight test of a 40-foot nominal diameter disk gap band parachute deployed at a Mach number of 1.91 and a dynamic pressure of 11.6 pounds per square foot
Flight test of l0-foot nominal-diameter disk-gap band parachute to determine deployment and inflation, opening shock loads, drag efficiency, and stability characteristics
Eckstrom, C. V.↗
Feasibility development of a self-deploying electromagnetic energy focusing reflector for space or transportable ground based applications
Feasibility development of self-deploying electromagnetic energy focusing reflector for space or transportable ground based operations
Bahiman, H.↗