In 1994, the Deep Space Program Science Experiment (DSPSE) spacecraft will become the first spacecraft to perform, in succession, both a lunar orbiting mission and a deep-space asteroid encounter mission. The primary mission objective is to perform a long-duration flight-test of various new-technology lightweight components, such as sensors, in a deep-space environment. The mission has two secondary science objectives: to provide high-resolution imaging of the entire lunar surface for mapping purposes and flyby imaging of the asteroid 1620 Geographos. The DSPSE mission is sponsored by the Strategic Defense Initiative Organization (SDIO). As prime contractor, the Naval Research Laboratory (NRL) is building the spacecraft and will conduct mission operations. The Goddard Space Flight Center's (GSFC) Flight Dynamics Division is supporting NRL in the areas of The Deep Space Network (DSN) will provide tracking support. The DSPSE mission will begin with a launch from the Western Test Range in late January 1994. Following a minimum 1.5-day stay in a low-Earth parking orbit, a solid kick motor burn will boost DSPSE into an 18-day, 2.5-revolution phasing orbit transfer trajectory to the Moon. Two burns to insert DSPSE into a lunar polar orbit suitable for the mapping mission will be followed by mapping orbit maintenance and adjustment operations over a period of 2 sidereal months. In May 1994, a lunar orbit departure maneuver, in conjunction with a lunar swingby 26 days later, will propel DSPSE onto a heliocentric transfer that will intercept Geographos on September 1, 1994. This paper presents the characteristics, deterministic delta-Vs, and design details of each trajectory phase of this unique mission, together with the requirements, constraints, and design considerations to which each phase is subject. Numerous trajectory plots and tables of significant trajectory events are included. Following a discussion of the results of a preliminary launch window analysis, a summary of the deterministic impulsive delta-V budget required to establish the baseline mission trajectory design is presented.


    Access

    Access via TIB

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Trajectory design for the Deep Space Program Science Experiment (DSPSE) mission


    Contributors:
    Carrington, D. (author) / Carrico, J. (author) / Jen, J. (author) / Roberts, C. (author) / Seacord, A. (author) / Sharer, P. (author) / Newman, L. (author) / Richon, K. (author) / Kaufman, B. (author) / Middour, J. (author)


    Publication date :

    1993-01-01



    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :


    Trajectory Design for the Deep Space Program Science Experiment (DSPSE) Mission (AAS 93-260)

    Carrington, D. / Carrico, J. / Jen, J. et al. | British Library Conference Proceedings | 1993



    Flight Dynamics Support for the Clementine Deep Space Program Science Experiment (DSPSE) Mission

    Richon, K. V. / Kraft Newman, L. / American Astronautical Society| American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 1996



    An overview of the astrodynamics for the Deep Space Program Science Experiment mission (DSPSE)

    Kaufman, B. / Middour, J. / Dasenbrock, R. et al. | British Library Conference Proceedings | 1994