ParachuteDesign Parameters
Typical relationships between various parachute-design parameters and aerodynamic-performance characteristics are illustrated schematically in figure 2. Although wind-tunnel tests have been used to determine force and moment coefficients for some types of parachutes, the preponderance of aerodynamic data available for design is from aerial-drop tests. Consequently, there is a notable lack of data on tangent C-ji. normal lt t. and moment 1 force coefficients and their derivative for some of the...
State Of The Art
The technology of deployable aerodynamic deceleration systems advanced rapidly during the 1960's because of the impetus of intensive development programs carried out concurrently with spacecraft design, construction, and testing. Heretofore, all operational spacecraft landing and recovery systems have been ballistic i.e., drag-surface decelerator systems. For the most part, these systems employ a drogue initial stage and a main descent-parachute final stage e.g., the Mercury, Gemini, Apollo,...
References
1. Murray, H. L. Parachute Subsystem Apollo Block II Increased Capability Earth Landing System Final Report of the Series 85 Qualification Drop Tests. Vols. I and II, Rept. NVR-6070, Northrop Corp., Aug. 1968. 2. Buhler, W. C, Installation, Operation and Maintenance Project Mercury Landing System and Post Landing Equipment. Rept. RP-2201B, Northrop Corp., Aug. 1960. 3. Ewing, E. G. and Vickers, J. R. Feasibility Study of a Universal Aerial Recovery System. Vol. I, AFSSD-TR-66-47, Northrop...