Sensing techniques for initiating parachute deployment on a Mars lander vehicle.
Sensing techniques for initiating parachute deployment on Mars lander vehicle
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Sensing techniques for initiating parachute deployment on Mars lander vehicle
Calculating method for parachute opening forces, system velocity, cloth pressure loading and filling time for horizontal and vertical deployment conditions
High altitude parachute systems test techniques for analysis of inflation, stability variations porosity, effects at low dynamic pressure, etc
The development of the parachute is presented as well as the future possibilities.
The "Bulletin Technique", of March, 1919, gave the results of tests and studies made up to that date in connection with airplane parachutes. This work has been continued.
In the Mars Exploration Rover (MER) Mission, NASA returns to the red planet, following the extremely successful Mars Pathfinder in 1997. The mission will send two lander-rovers to the surface of Mars with separate launches in May and June, 2003. This paper describes the Parachute Decelerator System for the entry vehicle.
This paper describes one method by which an Earth qualification test program for Mars parachute can be conducted.
US Army MC-4/5 ram-air parachutes were tested in the 80- by 120-Ft test section of the National Full-Scale Aerodynamics Complex. Arrays of targets on the upper and lower surfaces of the central cell of the canopies were measured by stereo photogrammetry, and the target positions were used to estimate both the shape of the cell and angle of attack of the canopy. Forces and moments were measured by a six-axis load cell. Based on the photogrammetry and load-cell measurements, the relationships between lift, drag, and angle of attack were determined over a range of trailing-edge flap deflections, front riser lengths, and free-stream airspeeds. This paper describes the test, with an emphasis on the photogrammetry measurements, and presents a summary of results.
Nylon shock absorbers reduce the canopy-opening shock of a parachute to a level that protects the wearer from injury. A shock absorber is mounted on each of the four risers between the shroud lines and the harness. Because of their size and location, they pose no problem in repacking the chute and harness after a jump.
Subsonic parachute-borne blunt probes for charged particle measurement in ionosphere
Improved control system power unit drives the control surfaces of very large controllable parachutes. The design features subassemblies for determining control surface position and cable loading, and protection of the load sensor against the possibility of damage during manipulation.
Subsonic parachute-borne blunt probes for charged particle measurement in ionosphere
Flight tests of ringsail parachute with 15 percent porosity, for planetary entry
Flight test of conical spacecraft simulating parachute deployment in Mars atmosphere
Inflation, and drag characteristics of disk gap band parachute in simulated low density Mars atmosphere
Inflation, drag, and stability characteristics of ringsail parachute deployed in simulated Mars atmosphere
Structural design and performance tests on disk gap-band parachute for supersonic planetary entry
Material strength, shock loading, and stress analyses for planetary entry parachute design