Mars Observer mission designThe spacecraft for the Mars Observer mission is described, and an interplanetary trajectory design maximizing the spacecraft dry mass delivered into its mapping orbit is presented, along with an orbit insertion strategy minimizing spacecraft propulsive requirements. Emphasis is placed on the mapping orbit designed to meet the science requirements for a low-altitude near-circular near-polar orbit which is sun-synchronous with the dayside equatorial crossing at 2 PM local mean solar time. Additional requirements on the design are that the mapping orbit have a repeating groundtrack of no more than 7 sols and comply with the NASA Planetary Protection requirements. It is planned to operate the spacecraft and instruments in a repetitive fashion to minimize mission operation complexity and cost.
Document ID
19900056470
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Beerer, Joseph G. (Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Horvat, Glen M. (Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Roncoli, Ralph B. (JPL Pasadena, CA, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1989
Subject Category
Astrodynamics
Report/Patent Number
AAS PAPER 89-196
Meeting Information
Meeting: AAS/NASA Intl. Symposium on Orbital Mechanics and Mission Design