Experimental investigation of packaging and deployment characteristics of an inflatable toroidal-space-station configuration
Folding, packaging, and deployment of inflatable toroidal space station model
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Folding, packaging, and deployment of inflatable toroidal space station model
Solar cell array deployment systems applied to spinning satellites based on flexible substrates and chemical rigidization
Impact acceleration and landing system characteristics of Apollo spacecraft command module configurations with deployed heat shield
Roller drum, actuation system, support structure, electrical provisions, and substrate design concepts for deployable large area solar array structure
Motion equations for clamshell heat shield deployed from parent vehicle in atmosphere
Deployment dynamics analysis of large surface in orbit and on test stand
Prototype deployable large area solar array structure design
Sensor systems for initiating parachute deployment for Mars entry vehicle
Motion of spinning satellite during deployment of n asymmetrical appendages, noting Pioneer spacecraft
Calculating method for parachute opening forces, system velocity, cloth pressure loading and filling time for horizontal and vertical deployment conditions
Motion of spinning satellite during deployment of n asymmetrical appendages, noting Pioneer spacecraft
Flight test of 31.2-foot-diameter modified ringsail parachute deployed at Mach 1.39 and dynamic pressure of 11 pounds per square foot
Simulation of deployment dynamics of spinning spacecraft
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
Development, fabrication, and testing of deployable solar cell array for spin-oriented spacecraft applications
Experimental design of deployable tension cone decelerator with inflatable toroids for compression resistant structures in base of cone
Structural and librational dynamics of satellite deploying flexible booms or antennas
Sensing techniques for initiating parachute deployment on Mars lander vehicle