Download or read book Performance of and Design Criteria for Deployable Aerodynamic Decelerators written by George Chernowitz and published by . This book was released on 1964 with total page 492 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Download or read book Performance of and Design Criteria for Deployable Aerodynamic Decelerators written by and published by . This book was released on 1964 with total page 535 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Performance of and Design Criteria for Deployable Aerodynamic Decelerators written by and published by . This book was released on 1964 with total page 530 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aerodynamic Deployable Decelerator Performance Evaluation Program written by E. Bloetscher and published by . This book was released on 1967 with total page 220 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Download or read book Aerodynamic Deployable Decelerator Performance evaluation Program Phase 2 written by Frederick Bloetscher and published by . This book was released on 1967 with total page 219 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Download or read book Performance of Trailing Aerodynamic Decelerators at High Dynamic Pressures written by B. A. Engstrom and published by . This book was released on 1962 with total page 108 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aerodynamic Deployable Decelerator Performance evaluation Program written by Frederick Bloetscher and published by . This book was released on 1967 with total page 119 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Download or read book Aerodynamic Deployable Decelerator Performance evaluation Program written by Frederick Bloetscher and published by . This book was released on 1967 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Download or read book Study and Exploratory Free flight Investigation of Deployable Aerodynamic Decelerators Operating at High Altitudes and at High Mach Numbers written by W. E. Nickel and published by . This book was released on 1964 with total page 155 pages. Available in PDF, EPUB and Kindle. Book excerpt: Thirteen parachute decelerator tests were performed at the Gulf Test Range of the Air Proving Ground Center at Eglin Air Force Base, Florida. These tests were accomplished through the use ofof multistage rockekket boosters. The Cree payyload vehicle was used as the test platform and data gathering system. These tests were conducted using both Hyperflo and Hemisflo parachutes which were deployed at predetermined Mach numberaltitude regimes. Tests were accomplished over a Mach number range of 0.2 to 4.4 and an altitude range of 45, 000 to 190,000 feet. The data presented includes drag coefficients versus Mach number, dynamic pressure, Reynolds number and velocity, canopy angles of oscillation, canopy temperatures and general design considerations. From this parachute decelerator test program, it may be concluded that Perlon mesh roof Hyperflo parachutes perform satisfactorily through Mach 2.1, that Nomex ribbon Hyperflo parachutes perform satisfactorily through Mach 4.0 and that Nomex Hemisflo parachutes perform satisfactorily through Mach 3.4.
Download or read book Theoretical Investigations of Deployable Aerodynamic Decelerators written by H. G. Heinrich and published by . This book was released on 1963 with total page 108 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Computerized Data Catalog and Retrieval System for Deployable Aerodynamic Decelerators written by Thomas J. Hogan (Jr.) and published by . This book was released on 1967 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: In the development of a computerized data catalog and data retrieval system for deployable aerodynamic decelerators, the results were twofold: (1) a list of parameters which completely define the information pertinent to these decelerators; and (2) a data base (the structure to arrange the data elements making up a unit of information) and the computer programs to manipulate the data base. The combination of these results constitutes a system to store and retrieve by computer techniques all data related to deployable aerodynamic decelerators.
Download or read book Deployable Aerodynamic Decelerators written by H. G. Heinrich and published by . This book was released on 1964 with total page 82 pages. Available in PDF, EPUB and Kindle. Book excerpt: This is the twenty-ninth quarterly report, covering the time from 1 March 1964 to 31 May 1964 on the study program of basic information of Aerodynamic Deceleration.
Download or read book Sample Calculation for a Deployable Aerodynamic Deceleration System written by Rudi J. Berndt and published by . This book was released on 1963 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt: A step-by-step procedure is presented as part of a sample calculation by means of which the selection of a deployable aerodynamic deceleration system may be made, the trajectory and related operational characteristics of individual decelerators may be calculated, and design and construction details of the aerodynamic decelerators may be established.
Download or read book Deployable Aerodynamic Decelerators Report Bibliography written by Air Force Flight Dynamics Laboratory (U.S.) and published by . This book was released on 1968 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Proceedings of Retardation and Recovery Symposium written by and published by . This book was released on 1963 with total page 496 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Download or read book A Structural Merit Function for Aerodynamic Decelerators written by Melvin S. Anderson and published by . This book was released on 1969 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: Structural merit function for aerodynamic decelerators.
Download or read book Aerodynamic Deployable Decelerator Performance Evaluation Program written by F. R. Nebiker and published by . This book was released on 1965 with total page 330 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
