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2016 Mars Insight Mission Design and NavigationScheduled for a launch in the 2016 Earth to Mars opportunity, the Interior Exploration using Seismic Investigations, Geodesy, and Heat Transport (InSight) Mission will arrive to Mars in late September 2016 with the primary objective of placing a science lander on the surface of the Red Planet followed by the deployment of two science instruments to investigate the fundamental processes of terrestrial planet formation and evolution. In order to achieve a successful landing, the InSight Project has selected a launch/arrival strategy that satisfies the following key and driving requirements: (1) Deliver a total launch mass of 727 kg, (2) target a nominal landing site with a cumulative Delta V99 less than 30 m/s, and (3) approach EDL with a V-infinity upper limit of 3.941 km/s and (4) an entry flight-path angle (EFPA) of -12.5 +/- 0.26 deg, 3-sigma; the InSight trajectories have been designed such that they (5) provide UHF-band communications via Direct-To-Earth and MRO from Entry through landing plus 60 s, (6) with injection aimpoints biased away from Mars such that the probability of the launch vehicle upper stage impacting Mars is less than 1.0 X 10(exp 4) for fifty years after launch, and (7) non-nominal impact probabilities due to failure during the Cruise phase less than 1.0 X 10(exp 2).
Document ID
20150016876
Document Type
Conference Paper
External Source(s)
Authors
Abilleira, Fernando (Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Frauenholz, Ray (Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Fujii, Ken (Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Wallace, Mark (Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
You, Tung-Han (Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Date Acquired
September 1, 2015
Publication Date
January 26, 2014
Subject Category
Lunar and Planetary Science and Exploration
Space Transportation and Safety
Report/Patent Number
AAS 14-363
Meeting Information
AAS/AIAA Space Flight Mechanics Meeting(Santa Fe, NM)
Distribution Limits
Public
Copyright
Other
Keywords
Landers
Trajectory Optimization