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  • 1
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    Solar-electric geocentric transfer (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Time-optimal or nearly-time-optimal trajectory computer program developed for solar-electric geocentric transfer considers yaw motion only, yaw and roll only, and unconstrained motion configurations.
    Keywords: MECHANICS
    Type: LEW-12939 , NASA Tech Briefs (ISSN 0145-319X); 3; 3; P. 419
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    A users manual for a computer program which calculates time optical geocentric transfers using solar or nuclear electric and high thrust propulsion (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: This manual is a guide for using a computer program which calculates time optimal trajectories for high-and low-thrust geocentric transfers. Either SEP or NEP may be assumed and a one or two impulse, fixed total delta V, initial high thrust phase may be included. Also a single impulse of specified delta V may be included after the low thrust state. The low thrust phase utilizes equinoctial orbital elements to avoid the classical singularities and Kryloff-Boguliuboff averaging to help insure more rapid computation time. The program is written in FORTRAN 4 in double precision for use on an IBM 360 computer. The manual includes a description of the problem treated, input/output information, examples of runs, and source code listings.
    Keywords: SPACE SCIENCES
    Type: NASA-CR-139038 , R-827
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Solar electric geocentric transfer with attitude constraints: Analysis (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A time optimal or nearly time optimal trajectory program was developed for solar electric geocentric transfer with or without attitude constraints and with an optional initial high thrust stage. The method of averaging reduces computation time. A nonsingular set of orbital elements is used. The constraints, which are those of one of the SERT-C designs, introduce complexities into the analysis and the solution yields possible discontinuous changes in thrust direction. The power degradation due to VanAllen radiation is modeled analytically. A wide range of solar cell characteristics is assumed. Effects such as oblateness and shadowing are included. The analysis and the results of many example runs are included.
    Keywords: ASTRODYNAMICS
    Type: NASA-CR-134927 , CSDL-R-901
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Optimal solar sail planetocentric trajectories (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The analysis of solar sail planetocentric optimal trajectory problem is described. A computer program was produced to calculate optimal trajectories for a limited performance analysis. A square sail model is included and some consideration is given to a heliogyro sail model. Orbit to a subescape point and orbit to orbit transfer are considered. Trajectories about the four inner planets can be calculated and shadowing, oblateness, and solar motion may be included. Equinoctial orbital elements are used to avoid the classical singularities, and the method of averaging is applied to increase computational speed. Solution of the two-point boundary value problem which arises from the application of optimization theory is accomplished with a Newton procedure. Time optimal trajectories are emphasized, but a penalty function has been considered to prevent trajectories which intersect a planet's surface.
    Keywords: ASTRODYNAMICS
    Type: NASA-CR-157130 , R-1113
    Format: application/pdf
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  • 5
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    SUNSPOT: A computer program for producing optimal solar sail planetocentric trajectories (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The input, output and subroutines, including listings, for the SUNSPOT code are described. SUNSPOT can calculate time optimal planetocentric trajectories including orbit-to-orbit transfer and orbit to a subescape point. Trajectories about the the four inner planets can be calculated, and shadowing, oblateness, and solar motion may be included. A penalty function may be included to prevent trajectories which intersect the planet's surface.
    Keywords: ASTRODYNAMICS
    Type: NASA-CR-157129 , C-4947
    Format: application/pdf
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  • 6
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    Stability of the Shuttle on-orbit flight control system for a class of flexible payloads (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The stability of the Space Shuttle on-orbit flight control system is determined for a class of payloads for which the payload is tilted out of the orbiter bay and the bending can be modeled as localized at a pivot. Examples are the Inertial Upper Stage or the Centaur with attached spacecraft during deployment. The many inertial, geometric, and jet option parameters are reduced to a smaller set which allows the determination of stability or instability as a function of bending frequency and the other elements of the set. The resulting stability charts, which are presented, can be used by payload designers and misssion planners to predict possible instability without elaborate analysis or simulation.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 83-2178 , Guidance and Control Conference; Aug 15, 1983 - Aug 17, 1983; Gatlinburg, TN
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Optimal solar sail spiral to escape (1977)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: A solar sail is being considered for various solar system missions, such as a comet rendezvous and a planetary sample return. Such missions might include a planetocentric escape or capture trajectory segment. This paper considers a method for calculating time optimal planetocentric solar sail spiral trajectories to near escape and orbit to orbit transfers. A number of examples illustrate trajectories generated with a computer program, SUNSPOT, based on this analysis.
    Keywords: ASTRODYNAMICS
    Type: Astrodynamics Specialist Conference; Sept. 7-9, 1977; Jackson Hole, WY; US
    Format: text
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  • 8
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    Comparison of two sensors for outer planet mission onboard navigation. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Onboard instruments have been shown to be an effective aid to navigation on missions to the outer planets. The relationship of two possible candidate navigation instruments, an image tube (television) and a scanning photometer, with other systems such as data processing and attitude control is discussed. Certain key problem areas relating to the design of each sensor are considered, and the scientific uses of each sensor are examined. The navigational efficacy of both instruments is illustrated by some selected results from a navigation and guidance simulation of outer planet missions. It is concluded that both devices are viable alternatives for onboard outer planet navigation.
    Keywords: NAVIGATION
    Type: The growth and maturity of navigation in space; National Space Meeting; Mar 15, 1972 - Mar 16, 1972; Orlando, FL
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Optimal high- and low-thrust geocentric transfer (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A computer code which rapidly calculates time optimal combined high- and low-thrust transfers between two geocentric orbits in the presence of a strong gravitational field has been developed as a mission analysis tool. The low-thrust portion of the transfer can be between any two arbitrary ellipses. There is an option for including the effect of two initial high-thrust impulses which would raise the spacecraft from a low, initially circular orbit to the initial orbit for the low-thrust portion of the transfer. In addition, the effect of a single final impulse after the low-thrust portion of the transfer may be included. The total Delta V for the initial two impulses must be specified as well as the Delta V for the final impulse. Either solar electric or nuclear electric propulsion can be assumed for the low-thrust phase of the transfer.
    Keywords: SPACE SCIENCES
    Type: AIAA PAPER 74-801 , Mechanics and Control of Flight Conference; Aug 05, 1974 - Aug 09, 1974; Anaheim, CA
    Format: text
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  • 10
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    Optimal low thrust geocentric transfer (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A computer code which will rapidly calculate time-optimal low thrust transfers is being developed as a mission analysis tool. The final program will apply to NEP or SEP missions and will include a variety of environmental effects. The current program assumes constant acceleration. The oblateness effect and shadowing may be included. Detailed state and costate equations are given for the thrust effect, oblateness effect, and shadowing. A simple but adequate model yields analytical formulas for power degradation due to the Van Allen radiation belts for SEP missions. The program avoids the classical singularities by the use of equinoctial orbital elements. Kryloff-Bogoliuboff averaging is used to facilitate rapid calculation. Results for selected cases using the current program are given.
    Keywords: PROPULSION SYSTEMS
    Type: AIAA PAPER 73-1074 , Electric Propulsion Conference; Oct 31, 1973 - Nov 02, 1973; Lake Tahoe, NV
    Format: text
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