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Trajectory design for the Deep Space Program Science Experiment (DSPSE) missionIn 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.
Document ID
19950054128
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Carrington, D.
(Computer Sciences Corp. Lanham-Seabrook, MD, US, United States)
Carrico, J.
(Computer Sciences Corp. Lanham-Seabrook, MD, US, United States)
Jen, J.
(Computer Sciences Corp. Lanham-Seabrook, MD, US, United States)
Roberts, C.
(Computer Sciences Corp. Lanham-Seabrook, MD, US, United States)
Seacord, A.
(Computer Sciences Corp. Lanham-Seabrook, MD, US, United States)
Sharer, P.
(Computer Sciences Corp. Lanham-Seabrook, MD, US, United States)
Newman, L.
(NASA Goddard Space Flight Center Greenbelt, MD, US, United States)
Richon, K.
(NASA Goddard Space Flight Center Greenbelt, MD, US, United States)
Kaufman, B.
(U.S. Naval Research Lab. Washington, DC, US, United States)
Middour, J.
(U.S. Naval Research Lab. Washington, DC, US, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1993
Publication Information
Publication: In: Spaceflight dynamics 1993; AAS(NASA International Symposium, 8th, Greenbelt, MD, Apr. 26-30, 1993, Parts 1 & 2 . A95-85716
Publisher: American Astronautical Society (Advances in the Astronautical Sciences, Vol. 84, Pts. 1 & 2)
ISSN: 0065-3438
Subject Category
Astrodynamics
Accession Number
95A85727
Funding Number(s)
CONTRACT_GRANT: NAS5-31500
Distribution Limits
Public
Copyright
Other

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