Add to ORKGThe design criteria and characteristics of parachutes for recovery of the solid rocket boosters used with the space shuttle launch are presented. A computer program for analyzing the requirements of the parachute decelerators is described. The computer inputs for both the drogue and main parachute decelerators are; (1) parachute size, (2) deployment conditions, (3) inflation times, (4) reefing times, (5) mass properties, (6) spring properties, and (7) aerodynamic coefficients. Graphs of the parachute performance are included
Parachutes used for Mars landing missions are only certified for deployment at Mars behind blunt bod...
During the first Supersonic Flight Dynamics Test (SFDT-1) for NASA's Low Density Supersonic Decelera...
A technique is developed to optimize the shuttle solid rocket booster (SRB) design for water impact ...
Preliminary parametric studies were performed to establish size, weight and packaging arrangements f...
Recovery and reuse of the Space Shuttle solid rocket boosters was baselined to support the primary g...
The performance requirements, preliminary designs, and development program plans for an airborne rec...
Criteria and recommended practices for design, selection, analysis, and testing of deployable aerody...
Material strength, shock loading, and stress analyses for planetary entry parachute desig
The nonlinear differential equations of motion for a general parachute-riser-payload system are deve...
This research has developed a viable drogue parachute release system sufficient for recovering level...
Deployment and performance characteristics of 5-Foot diameter (1.5m) Attached Inflatable Decelerator...
The recovery of the Solid Rocket Boosters presented a major challenge. The SRB represents the larges...
The drag parachute system was added to the Space Shuttle Orbiter's landing deceleration subsystem be...
A 55 foot diameter disk-gap-band parachute was deployed behind an expandable 15 foot diameter, 120 d...
Balloon Launched Decelerator Test (BLDT) flights were conducted during the summer of 1972 over the W...
Parachutes used for Mars landing missions are only certified for deployment at Mars behind blunt bod...
During the first Supersonic Flight Dynamics Test (SFDT-1) for NASA's Low Density Supersonic Decelera...
A technique is developed to optimize the shuttle solid rocket booster (SRB) design for water impact ...
Preliminary parametric studies were performed to establish size, weight and packaging arrangements f...
Recovery and reuse of the Space Shuttle solid rocket boosters was baselined to support the primary g...
The performance requirements, preliminary designs, and development program plans for an airborne rec...
Criteria and recommended practices for design, selection, analysis, and testing of deployable aerody...
Material strength, shock loading, and stress analyses for planetary entry parachute desig
The nonlinear differential equations of motion for a general parachute-riser-payload system are deve...
This research has developed a viable drogue parachute release system sufficient for recovering level...
Deployment and performance characteristics of 5-Foot diameter (1.5m) Attached Inflatable Decelerator...
The recovery of the Solid Rocket Boosters presented a major challenge. The SRB represents the larges...
The drag parachute system was added to the Space Shuttle Orbiter's landing deceleration subsystem be...
A 55 foot diameter disk-gap-band parachute was deployed behind an expandable 15 foot diameter, 120 d...
Balloon Launched Decelerator Test (BLDT) flights were conducted during the summer of 1972 over the W...
Parachutes used for Mars landing missions are only certified for deployment at Mars behind blunt bod...
During the first Supersonic Flight Dynamics Test (SFDT-1) for NASA's Low Density Supersonic Decelera...
A technique is developed to optimize the shuttle solid rocket booster (SRB) design for water impact ...