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The Aerodynamic Deployable Decelerator Performance-Evaluation Program (ADDPEP) aims to advance the state of the art by developing the most effective analytical and empirical techniques for designing aerodynamic deployable decelerators and for evaluating these engineering techniques through wind-tunnel and free-flight tests. During ADDPEP Phase 2, two types of decelerators were investigated: large reefed supersonic parachutes and raminflated balloon-type BALLUTEs. The areas investigated included analytical and engineering design, material capabilities, fabrication techniques, and wind-tunnel and free-flight tests. Free-flight tests were performed on a hemisflo parachute having a nominal 16-ft-diameter canopy, a 10-percent extended skirt, and a 14-percent porosity. This design was tested for 200,000-lb opening loads, deployment Mach numbers were 1.50, 1.63, and 1.84 at altitudes of 13,700, 15,500, and 10,500 ft, respectively. The results confirmed that this parachute has excellent aerodynamic characteristics and adequate strength. Five-foot-diameter BALLUTEs, both textile and metal, were fabricated. These were designed for a broad spectrum of deployment conditions ranging from Mach 2.7 at 73,000 ft to Mach 10 at 225,000 ft. The textile BALLUTEs were wind-tunnel and free-flight tested; the metal BALLUTEs were wind-tunnel tested only. Flight tests were limited to Mach 9.7, and wind-tunnel tests to Mach 3. The flight test data supported wind-tunnel data, which indicated that excellent stability and structurally adequate designs can be attained with five-foot-diameter BALLUTEs.
The Aerodynamic Deployable Decelerator Performance-Evaluation Program (ADDPEP) aims to advance the state of the art by developing the most effective analytical and empirical techniques for designing aerodynamic deployable decelerators and for evaluating these engineering techniques through wind-tunnel and free-flight tests. During ADDPEP Phase 2, two types of decelerators were investigated: large reefed supersonic parachutes and raminflated balloon-type BALLUTEs. The areas investigated included analytical and engineering design, material capabilities, fabrication techniques, and wind-tunnel and free-flight tests. Free-flight tests were performed on a hemisflo parachute having a nominal 16-ft-diameter canopy, a 10-percent extended skirt, and a 14-percent porosity. This design was tested for 200,000-lb opening loads, deployment Mach numbers were 1.50, 1.63, and 1.84 at altitudes of 13,700, 15,500, and 10,500 ft, respectively. The results confirmed that this parachute has excellent aerodynamic characteristics and adequate strength. Five-foot-diameter BALLUTEs, both textile and metal, were fabricated. These were designed for a broad spectrum of deployment conditions ranging from Mach 2.7 at 73,000 ft to Mach 10 at 225,000 ft. The textile BALLUTEs were wind-tunnel and free-flight tested; the metal BALLUTEs were wind-tunnel tested only. Flight tests were limited to Mach 9.7, and wind-tunnel tests to Mach 3. The flight test data supported wind-tunnel data, which indicated that excellent stability and structurally adequate designs can be attained with five-foot-diameter BALLUTEs.
The objective of this program is to advance the state of the art by using analytical and engineering techniques for designing aerodynamic deployable decelerators. Three classes of decelerators - small supersonic parachutes, ram- air-inflated BALLUTEs, and large high-dynamic-pressure parachutes were investigated. Free-flight tests using a newly developed GAC missile system and wind-tunnel tests in the full-scale propulsion wind-tunnel facility at Arnold Research Center were conducted. The results indicated that the engineering techniques that were developed led to improved decelerators and that an improved free-flight test capability was established.
The Aerodynamic Deployable Decelerator Performance-Evaluation Program (ADDPEP) has aimed to advance the state of the art by developing the most effective analytical and empirical techniques for designing aerodynamic deployable decelerators and for evaluating these engineering techniques through wind-tunnel and free-flight tests. During the third and concluding phase of ADDPEP, two types of decelerators were investigated: large reefed supersonic parachutes and small supersonic parachutes. The areas investigated by tests included analytical and engineering design methods, material capabilities, and fabrication techniques. Three large parachutes were built that had the same basic configuration: hemisflo, 16-ft-diameter canopy, 10-percent extended skirt, 10-percent porosity. These parachutes were designed for 200,000-lb opening loads. Free-flight tests were performed at deployment Mach numbers of 2.22, 1.20, and 2.70; at altitudes of 18,050, 9370, and 19,700 ft; and at dynamic pressures of 3697, 1514, and 5155 psf, respectively. The tests confirmed the predicted drag area. However, reefing line loads were underestimated; improved analytical methods are needed to predict this hoop-type load under dynamic conditions at the higher Mach numbers. Three small parachutes were built that had the same basic configuration, designated PARASONIC: 4-ft-diameter, 5-percent total porosity. Wind-tunnel tests confirmed that this PARASONIC design, when constructed of materials that are compatible with the flight environments investigated, has better stability than a HYPERFLO design that was also investigated in both Phases I and III.
The present state-of-the-art, technology, and theory applicable to deployable aerodynamic decelerators, especially textile parachute canopies, are presented. Major types of decelerators are described, and their aerodynamic and operational characteristics, as well as applications, are discussed. Detailed coverage is given to decelerator materials, design and construction, hardware, test methods and vehicles, and test instrumentation. Decelerator design procedures and performance prediction techniques are demonstrated by sample calculations.
The analysis, design, test, and application of a first-stage decelerator and stabilization balloon system (ballute) for recovery of payloads up to Mach 10 between altitudes of 120,000 and 200,000 ft, down to Mach 4 at 70,000 ft are discussed. Techniques of analysis, construction, development, and inflation are described, along with development of high-temperature materials, fabrication techniques, and results of wind tunnel, functional, environmental and missile tests. A present GAC-RTD prime program called ADDPEP (Aerodynamic Deployable Decelerator Performance Evaluation Program) is summarized. This program covers the design, construction, testing, evaluation, and modification of newly developed deployable decelerators (parachute and balloon types). The test techniques being used during this program to provide the necessary data for such advanced deceleration systems are discussed. Also presented are some applications of the ballute system, including the Gemini capsule where is will be an emergency escape system for the astronaut, augmenting his stability in case of highaltitude abort during ascent or decent of the boost vehicle. Tests have substantiated the feasibility of expandable structures for positeve deceleration and stabilization. (Author).
This document serves as the third revision of the USAF Parachute Handbook which was first published in 1951. The data and information represent the current state of the art relative to recovery system design and development. The initial chapters describe representative recovery applications, components, subsystems, material, manufacture and testing. The final chapters provide empirical data and analytical methods useful for predicting performance and presenting a definitive design of selected components into a reliable recovery system.