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  • 1
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    The aerodynamic challenges of SRB recovery (1985)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Recovery and reuse of the Space Shuttle solid rocket boosters was baselined to support the primary goal to develop a low cost space transportation system. The recovery system required for the 170,000-lb boosters was for the largest and heaviest object yet to be retrieved from exoatmospheric conditions. State-of-the-art design procedures were ground-ruled and development testing minimized to produce both a reliable and cost effective system. The ability to utilize the inherent drag of the boosters during the initial phase of reentry was a key factor in minimizing the parachute loads, size and weight. A wind tunnel test program was devised to enable the accurate prediction of booster aerodynamic characteristics. Concurrently, wind tunnel, rocket sled and air drop tests were performed to develop and verify the performance of the parachute decelerator subsystem. Aerodynamic problems encountered during the overall recovery system development and the respective solutions are emphasized.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Johnson Space Center Space Shuttle Tech. Conf., Pt. 1; p 189-208
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Balloon launched Viking decelerator test program (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Four BLDT flights were conducted during the summer of 1972. The purpose of these tests was to qualify the Viking parachute system behind the full-scale Viking entry vehicle over the maximum range of entry conditions anticipated in the Viking '75 soft landing on Mars. A summary of the test series is presented. Test conditions ranged from a Mach number of 2.0 to 0.5 and dynamic pressure from 11.7 to 4.4 psf. This range of conditions covers the uncertainty in entry conditions at Mars due to atmospheric and entry performance uncertainties. Emphasis is placed on parachute performance and simulated Mars entry vehicle motions as influenced by the parachute performance. Conclusions are presented regarding the ability of the parachute to perform within the operational parameters required for a successful soft Martian landing. A list of references which covers all reports in the qualification test program is included.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-112288 , TR-3720359
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Video guidance, landing, and imaging systems (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The adaptive potential of video guidance technology for earth orbital and interplanetary missions was explored. The application of video acquisition, pointing, tracking, and navigation technology was considered to three primary missions: planetary landing, earth resources satellite, and spacecraft rendezvous and docking. It was found that an imaging system can be mechanized to provide a spacecraft or satellite with a considerable amount of adaptability with respect to its environment. It also provides a level of autonomy essential to many future missions and enhances their data gathering ability. The feasibility of an autonomous video guidance system capable of observing a planetary surface during terminal descent and selecting the most acceptable landing site was successfully demonstrated in the laboratory. The techniques developed for acquisition, pointing, and tracking show promise for recognizing and tracking coastlines, rivers, and other constituents of interest. Routines were written and checked for rendezvous, docking, and station-keeping functions.
    Keywords: ASTRODYNAMICS
    Type: NASA-CR-132746
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    136-foot main parachute for recovery of Space Shuttle Solid Rocket Boosters (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A 136-ft-D(0) main parachute system has been developed to replace the present 115-ft-D(0) main parachutes currently flown on the Space Shuttle Solid Rocket Boosters (SRB's) for the purpose of reducing the velocity at water impact. This cluster of three larger main parachutes will decelerate the 170,000-pound SRB to a terminal nominal impact velocity of 75 feet per second (ft/s) as compared to the present velocity of 88 ft/s. The paper discusses the design, development, and manufacturing of this 136-ft parachute.
    Keywords: SPACE TRANSPORTATION
    Type: AIAA PAPER 84-0804
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Terminal descent simulation study Final report (1969)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Simulation program for parachute and terminal descent phases of Mars soft lander
    Keywords: SPACE VEHICLES
    Type: NASA-CR-66811
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Balloon launched decelerator test program: Post-flight test report, BLDT vehicle AV-3, Viking 1975 project (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The pertinent events concerned with the launch, float, and flight of balloon launched decelerator test vehicle AV-3 are discussed. The performance of the decelerator system is analyzed. Data on the flight trajectory and decelerator test points at the time of decelerator deployment are provided. A description of the time history of vehicle events and anaomalies encounters during the mission is included.
    Keywords: AIRCRAFT
    Type: NASA-CR-112178 , TR-3720293
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Balloon launched decelerator test program: Post-flight test report, BLDT vehicle AV-2, Viking 1975 project (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The pertinent events concerned with the launch, float, and flight of balloon launched decelerator test vehicle AV-2 are discussed. The performance of the decelerator system is analyzed. Data on the flight trajectory and decelerator test points at the time of decelerator deployment are provided. A description of the time history of vehicle events and anomalies encounters during the mission is included.
    Keywords: AIRCRAFT
    Type: NASA-CR-112177 , TR-3720291
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Balloon launched decelerator test program: Post-test test report (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Balloon Launched Decelerator Test (BLDT) flights were conducted during the summer of 1972 over the White Sands Missile Range. The purpose of these tests was to qualify the Viking disk-gap band parachute system behind a full-scale simulator of the Viking Entry Vehicle over the maximum range of entry conditions anticipated in the Viking '75 soft landing on Mars. Test concerns centered on the ability of a minimum weight parachute system to operate without structural damage in the turbulent wake of the blunt-body entry vehicle (140 deg, 11.5 diameter cone). This is the first known instance of parachute operation at supersonic speeds in the wake of such a large blunt body. The flight tests utilized the largest successful balloon-payload weight combination known to get to high altitude (120kft) where rocket engines were employed to boost the test vehicle to supersonic speeds and dynamic pressures simulating the range of conditions on Mars.
    Keywords: AIRCRAFT
    Type: NASA-CR-112176 , TR-3720289
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Qualification flight tests of the Viking decelerator system. (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The Balloon Launched Decelerator Test (BLDT) series conducted at White Sands Missile Range (WSMR) during July and August of 1972 flight qualified the NASA Viking '75 decelerator system at conditions bracketing those expected for Mars. This paper discusses the decelerator system design requiremnts, compares the test results with prior work, and discusses significant considerations leading to successful qualification in earth's atmosphere. The Viking decelerator system consists of a single-stage mortar-deployed 53-foot nominal diameter disk-gap-band parachute. Full-scale parachutes were deployed behind a full-scale simulated Viking vehicle at Mach numbers from 0.47 to 2.18 and dynamic pressures from 6.9 to 14.6 psf. Analyses show that the system is qualified with sufficient margin to perform successfully for the Viking mission.
    Keywords: AIRCRAFT
    Type: AIAA PAPER 73-457 , Aerodynamic Deceleration Systems Conference; May 21, 1973 - May 23, 1973; Palm Springs, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Mars lander vehicle/parachute dynamics. (1968)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Mars lander vehicle/parachute dynamics, discussing sensibility to wind gusts in Martian atmosphere
    Keywords: SPACE VEHICLES
    Type: SPACE CONGRESS; Mar 11, 1968 - Mar 14, 1968; COCOA BEACH, FL
    Format: text
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    NASA TECHNICAL REPORTS
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