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The Application of the Paraglider to Spacecraft Recovery
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English
Abstract
The performance of the Paraglider spacecraft recovery system is described in terms of wing aerodynamic characteristics, glide range, maneuver capabilities, and landing trajectories. Factors that influence the wing-spacecraft rigging design, the flight control scheme, and the wing loading are discussed. With the current state of the art of inflatable wing design, a glide range of the order of 25 miles can be obtained from an initial altitude of 40,000 ft. Wing loadings between 5 and 20 lb/sq ft permit adequate maneuver capabilities and acceptable touchdown sink rates with satisfactory margin on flare initiation altitude.
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Faulders, C. and Minott, G., "The Application of the Paraglider to Spacecraft Recovery," SAE Technical Paper 640039, 1964, https://doi.org/10.4271/640039.Also In
References
- Rogallo F. M. Lowry J. G. Croom D. R. Taylor R. T. “Preliminary Investigation of a Paraglider,” NASA TN D-443 August 1960
- Rogallo F. M. Lowry J. G. “Flexible Re-entry Gliders.” Paper presented at the SAE National Aeronautics Meeting April 4-8 1960
- Unpublished data from wind tunnel tests conducted by the NASA Langley Research Center.
- Polharnus E. C. Naeseth R. L. “Experimental and Theoretical Studies of the Effects of Camber and Twist on the Aerodynamic Characteristics of Parawings Having Nominal Aspect Ratios of 3 and 5,” NASA TN D-972