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A series of multistage rocket test vehicles was launched which deployed aerodynamic decelerators at predetermined altitude and velocities. Tests were conducted using extended hemispherical shaped parachutes. Exploratory test were accomplished and data collected over a test regime extending up to Mach 3.0 at 70,000 ft. In addition, data was presented on one test of a FIST ribbon parachute deployed at an altitude of 162,990 ft. and a Mach number of 1,022. Data was also presented on 2 tests conducted involving balloon type decelerators. Useful test data was presented for each parameter investigated. It was concluded that self inflatable aerodynamic decelerators perform satisfactorily up to a Mach number of approximately 2.0. At higher Mach numbers the flow conditions and shock wave interactions caused erratic performance which resulted in canopy damage of considerable magnitude. (Author).
THE MAJOR RESULTS OF THE TEST PROGRAM ARE SUMMARIZED. SOLID METAL CANOPIES WITHOUT SUSPENSION LINES WHICH WERE PROPERLY VENTED EXHIBITED STABLE FLOW AT ALL TIMES REGARDLESS OF CHANGES IN POROSITY, MACH NUMBER, DYNAMIC PRESSURE, AND VARIOUS OTHER PARAMETERS. THE ADDITION OF SUSPENSION LINES TO THE SOLID CANOPIES CAUSED UNSTABLE FLOW TO EXIST AT ALL TIMES. REDUCING THE NUMBER OF SUSPENSION LINES OR ADDING FLOW STABILIZERS DID NOT IMPROVE FLOW PATTERNS. FABRIC CANOPIES BEHAVED POORLY IN GENERAL AND APPEARED TO BE SOMEWHAT DEPENDENT UPON THE LOCATION OF A CONICAL INTERLINE SHOCK WAVE. A DEFINITE IMPROVEMENT WAS NOTED WHEN THE NUMBER OF GORES WAS INCREASED. AVERAGE DRAG COEFFICIENT WAS A FUNCTION OF AVERAGE INFLATED AREA RATIO. SHAPED GORES IMPROVED BEHAVIOR SOMEWHAT, THE 45 DEG CONICAL RIBBON GIVING THE MOST STABLE PERFORMANCE OF ALL FABRIC CONFIGURATIONS TESTED.
This report contains the proceedings of the Retardation and Recovery Symposium sponsored by the Aeronautical Systems Division on 13 and 14 November 1962. The Introductory Session was opened with the Keynote Address which reviewed the use and applications of deployable aerodynamic decelerators throughout the past fifty (50) years and noted the areas in which additional work had to be accomplished. The four Technical Sessions deal with the latest significant developments in the retardation and recovery area. The Technical Sessions begin with presentations and discussions of investigations in the hypersonic and supersonic flight regimes followed by a technical analysis of transonic and supersonic flow phenomena. In addition, new aerodynamic decelerator designs and discussion of the wind tunnel tests pertaining to these designs, as well as overall reliability of recovery systems, are presented. The final Technical Session concludes with a discussion of the military, scientific, and general objectives for decelerators intended for future use.
This bibliography was prepared by the Defense Documentation Center (DDC) for use at a symposium on Parachute Technology. Citations included for documents cataloged by DDC from 1953 through 1963 are restricted to unclassified unlimited references. Entries are arranged in alphabetical sequence by subject areas pertaining to aerial delivery, canopies, materials, parachutes (types), recovery systems, physical effects, and testing. These subject areas are subdivided further into more specific topics.
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.