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  • 1
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    Selection of orbits for the CRRES dual mission satellite (1986)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: The Combined Release and Radiation Effects Satellite (CRRES) is somewhat unusual, in that it performs related scientific experiments in two very different orbits. The selection of the Low Earth Orbit and Geosynchronous Transfer Orbit requires a number of scientific and engineering trade-offs. Issues in this design process discussed here are launch and insertion capabilities, altitude regimes of scientific interest and orbit stability, ground track and lighting considerations, lifetime of both missions, and the transfer between the two orbits.
    Keywords: ASTRODYNAMICS
    Type: Journal of the Astronautical Sciences (ISSN 0021-9142); 34; 315-329
    Format: text
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  • 2
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    Orbit/deorbit analysis for a Mars rover and sample return mission (1990)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: ASTRODYNAMICS
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 27; 425-432
    Format: text
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  • 3
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    Aerobraking for capture into Martian orbit (1990)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: A summary is given of several studies into problems associated with aerobraking a manned vehicle into a Martian capture orbit. The problems investigated are the establishment of entry flight path angle windows that allow aerocapture; the determination of the sensitivity of the entry trajectory to initial flight path angle; the determination of the effect on aerocapture of the assumed Martian atmosphere model; and the determination of the effect of random atmosphere disturbances on adaptive guidance systems that may be used for aerocapture. As a result of investigating the above problem areas, entry windows were established for three different vehicle configurations. Sensitivities to changes in initial flight path angle were also obtained for these three configurations. One configuration was chosen to determine the effect of Martian atmospheric model changes and random variations of density within a specific atmospheric model. Of particular interest was the effect of random density variations on adaptive guidance techniques. The effect of entry velocity on the size of the entry window was also examined.
    Keywords: ASTRODYNAMICS
    Type: NASA, Goddard Space Flight Center, Flight Mechanics(Estimation Theory Symposium, 1990; p 491-510
    Format: application/pdf
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  • 4
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    An automated method of tuning an attitude estimator (1995)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Attitude determination is a major element of the operation and maintenance of a spacecraft. There are several existing methods of determining the attitude of a spacecraft. One of the most commonly used methods utilizes the Kalman filter to estimate the attitude of the spacecraft. Given an accurate model of a system and adequate observations, a Kalman filter can produce accurate estimates of the attitude. If the system model, filter parameters, or observations are inaccurate, the attitude estimates may be degraded. Therefore, it is advantageous to develop a method of automatically tuning the Kalman filter to produce the accurate estimates. In this paper, a three-axis attitude determination Kalman filter, which uses only magnetometer measurements, is developed and tested using real data. The appropriate filter parameters are found via the Process Noise Covariance Estimator (PNCE). The PNCE provides an optimal criterion for determining the best filter parameters.
    Keywords: ASTRODYNAMICS
    Type: NASA. Goddard Space Flight Center, Flight Mechanics(Estimation Theory Symposium 1995; p 127-135
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  • 5
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    Evaluation of a stall-flutter spring-damper pushrod in the rotating control system of a CH-54B helicopter (1974)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Results of a design and flight test program conducted to define the effect of rotating pushrod damping on stall-flutter induced control loads are presented. The CH-54B helicopter was chosen as the test aircraft because it exhibited stall induced control loads. Damping was introduced into the CH-54B control system by replacing the standard pushrod with spring-damper assemblies. Design features of the spring-damper are described and the results of a dynamic analysis are shown which define the pushrod stiffness and damping requirements. Flight test measurements taken at 47,000 lb gross weight with and without the damper are presented. The results indicate that the spring-damper pushrods reduced high frequency, stall-induced rotating control loads by almost 50%. Fixed system control loads were reduced by 40%. Handling qualities in stall were unchanged, as expected.
    Keywords: AIRCRAFT
    Type: NASA. Ames Res. Center Rotorcraft Dyn.; p 223-232
    Format: application/pdf
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  • 6
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    The MSFC UNIVAC 1108 EXEC 8 simulation model (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A model is presented which simulates the MSFC Univac 1108 multiprocessor system. The hardware/operating system is described to enable a good statistical measurement of the system behavior. The performance of the 1108 is evaluated by performing twenty-four different experiments designed to locate system bottlenecks and also to test the sensitivity of system throughput with respect to perturbation of the various Exec 8 scheduling algorithms. The model is implemented in the general purpose system simulation language and the techniques described can be used to assist in the design, development, and evaluation of multiprocessor systems.
    Keywords: COMPUTERS
    Type: NASA-CR-61379
    Format: application/pdf
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  • 7
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    A study of Mariner 10 flight experiences and some flight piece part failure rate computations (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The problems and failures encountered in Mariner flight are discussed and the data available through a quantitative accounting of all electronic piece parts on the spacecraft are summarized. It also shows computed failure rates for electronic piece parts. It is intended that these computed data be used in the continued updating of the failure rate base used for trade-off studies and predictions for future JPL space missions.
    Keywords: ASTRODYNAMICS
    Type: NASA-CR-145933 , JPL-TM-33-759
    Format: application/pdf
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  • 8
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    LLV - Lunar Logistic Vehicle Final report (1969)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Evaluation of systems design training institute for engineering faculty
    Keywords: SPACE VEHICLES
    Type: NASA-CR-107445
    Format: application/pdf
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  • 9
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    The mission control center biomedical data analysis and display system. (1968)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Biomedical data analysis and display system at Mission Control Center, tracing information from sensors to consoles
    Keywords: BIOTECHNOLOGY
    Type: NTC 68, NATIONAL TELEMETERING CONFERENCE; Apr 08, 1968 - Apr 11, 1968; HOUSTON, TX
    Format: text
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  • 10
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    Discrete approximations to optimal trajectories using direct transcription and nonlinear programming (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A recently developed method for solving optimal trajectory problems uses a piecewise-polynomial representation of the state and control variables, enforces the equations of motion via a collocation procedure, and thus approximates the original calculus-of-variations problem with a nonlinear-programming problem, which is solved numerically. This paper identifies this method as a direct transcription method and proceeds to investigate the relationship between the original optimal-control problem and the nonlinear-programming problem. The discretized adjoint equation of the collocation method is found to have deficient accuracy, and an alternate scheme which discretizes the equations of motion using an explicit Runge-Kutta parallel-shooting approach is developed. Both methods are applied to finite-thrust spacecraft trajectory problems, including a low-thrust escape spiral, a three-burn rendezvous, and a low-thrust transfer to the moon.
    Keywords: ASTRODYNAMICS
    Type: AIAA PAPER 90-2963 , AIAA/AAS Astrodynamics Conference; Aug 20, 1990 - Aug 22, 1990; Portland, OR; United States
    Format: text
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