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  • 1
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    Study of the seismic waves SKS and SKKS (1954)
    In:  Bull. Seism. Soc. Am., Tokyo, Railway Tech. Res. Inst., vol. 44, no. 4, pp. 39-56, pp. L06615, (ISSN: 1340-4202)
    Details
    Publication Date: 1954
    Keywords: Waves ; Seismology ; earth Core ; Travel time ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 2
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    Ascent air data system results from the space shuttle flight test program (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The ascent air data system of the Space Shuttle consists of a simple biconic spike probe on the nose of the external tank. Pressure measurements were calibrated in a wind tunnel to obtain vehicle attitude and speed (relative to the air) and dynamic pressure. The wind tunnel test data analysis and the calibration are discussed in terms of test problems and calibration parameter formulation. The flight pressures are traced from telemetry data to final air data products. Analysis of the flight results showed that static pressure could not be accurately determined at the higher Mach numbers (above approx. 2.0). By replacing static pressure with data from a postflight estimated trajectory the ascent air data system performance met the user requirements. Lessons learned are enumerated, the most important being the need for a thorough systems integration effort.
    Keywords: SPACE TRANSPORTATION
    Type: NASA. Langley Research Center Shuttle Performance: Lessons Learned, Part 1; p 187-231
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Optimal aeroassisted orbital transfer with plane change using collocation and nonlinear programming (1990)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The fuel optimal control problem arising in the non-planar orbital transfer employing aeroassisted technology is addressed. The mission involves the transfer from high energy orbit (HEO) to low energy orbit (LEO) with orbital plane change. The basic strategy here is to employ a combination of propulsive maneuvers in space and aerodynamic maneuvers in the atmosphere. The basic sequence of events for the aeroassisted HEO to LEO transfer consists of three phases. In the first phase, the orbital transfer begins with a deorbit impulse at HEO which injects the vehicle into an elliptic transfer orbit with perigee inside the atmosphere. In the second phase, the vehicle is optimally controlled by lift and bank angle modulations to perform the desired orbital plane change and to satisfy heating constraints. Because of the energy loss during the turn, an impulse is required to initiate the third phase to boost the vehicle back to the desired LEO orbital altitude. The third impulse is then used to circularize the orbit at LEO. The problem is solved by a direct optimization technique which uses piecewise polynomial representation for the state and control variables and collocation to satisfy the differential equations. This technique converts the optimal control problem into a nonlinear programming problem which is solved numerically. Solutions were obtained for cases with and without heat constraints and for cases of different orbital inclination changes. The method appears to be more powerful and robust than other optimization methods. In addition, the method can handle complex dynamical constraints.
    Keywords: ASTRODYNAMICS
    Type: NASA, Goddard Space Flight Center, Flight Mechanics(Estimation Theory Symposium, 1990; p 471-490
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Prediction of flow-induced failures of braided flexible hoses and bellows (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Analytical techniques were developed to evaluate braided hoses and bellows for possibility of flow induced resonance. These techniques determine likelihood of high cycle fatigue failure when such resonance exists.
    Keywords: MECHANICS
    Type: MFS-19004
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    A New Concept for Controlled Lifting Entry Flight Experiments (1967)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Feasibility of trajectory guidance and control concept for lifting configuration with roll modulation
    Keywords: SPACE VEHICLES
    Type: NASA-CR-66718 , LMSC-677802
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Postflight analysis of the Space Shuttle ascent air data system (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An analysis of measurements recorded by the ascent air data system (AADS) located on the nose of the external tank of the Shuttle during the first flight is presented. The 30/10 deg biconic spike has five pressure ports for tracking yaw and pitch attitude, total pressure, and static pressure; comparison of AADS data with wind tunnel data allowed determination of angle of attack, angle of sideslip, Mach number, and dynamic pressure. Program goals for AADS development are reviewed, and specific design features are described. Wind tunnel test data were compared with best estimates simulations and initial flight data where possible; only wind tunnel derived Mach number predictions for time intervals 90 sec after launch are noted to deviate significantly from actual flight data.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 81-2457 , Flight Testing Conference; Nov 11, 1981 - Nov 13, 1981; Las Vegas, NV
    Format: text
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    NASA TECHNICAL REPORTS
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