Performance of a 26-meter-diameter ringsail parachute in a simulated Martian environment
NASA, 1967 - 72 pages
Inflation, drag, and stability characteristics of an 85.3-foot (26 meter) nominal diameter ringsail parachute deployed at a Mach number of 1.15 and at an altitude of 132,600 feet (40.42 kilometers) were obtained from the first flight test of the Planetary Entry Parachute Program. After deployment, the parachute inflated to the reefed condition. However, the canopy was unstable and produced low drag in the reefed condition. [remainder of summary illegible].
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3-percent density error accelerometer data accelerometer error accelerometer oscillation aeroshell drag coefficient aeroshell-payload separation angle of attack apogee approximately 4 seconds average axis system ballast release balloon canopy configuration canopy mouth Center Langley Station center of gravity center-of-gravity data period Deceleration Systems diameter ringsail parachute dynamic pressure Entry Parachute Program ENVIRONMENT By Charles feet Figure 13 Figure 17 film supplement L-946 flight test fluctuation frames per second free-stream full-inflation condition gores indicate inertia inflation process inflation sequence kilograms kilometers Langley Research Center Longitudinal acceleration longitudinal axis Mach number meter Mortar fire nominal diameter ringsail obtained Onboard camera parachute and payload parachute inflated parachute system payload separation Photogrammetry pitching and yawing Planetary Entry Parachute radians reefed condition reefed parachute Research Center Langley riser lines Rolling motion shown in figure slug-ft2 small amplitude spacecraft stability characteristics suspension lines trajectory values Variation of altitude vertical wind shear