Computer Science – Performance
Scientific paper
Jan 1988
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1988aiaa.meetx....m&link_type=abstract
AIAA, Aerospace Sciences Meeting, 26th, Reno, NV, Jan. 11-14, 1988. 17 p.
Computer Science
Performance
Aeroassist, Mars Sample Return Missions, Mars Surface Samples, Roving Vehicles, Algorithms, Computerized Simulation, Lift Drag Ratio, Shells (Structural Forms), Trajectory Analysis
Scientific paper
A three degree-of-freedom computer simulation has been developed to perform Martian aeroassist trajectories using the HYPAS guidance algorithm. This simulator was used to perform a parametric study at the Johnson Space Center of various low L/D vehicles and their performance with the inclusion of vehicle and atmospheric dispersions. The ultimate goal is to define an extreme (minimum L/D) aeroassist configuration for the Mars Rover/Sample Return Mission to compare with the previously defined biconic aeroshell. The study shows that a raked cone vehicle with L/D betweeen 0.3 and 0.6 will perform adequately in the Martian environment in the presence of dispersions. Average apoapsis error for the 0.6 L/D vehicle was 11.9 km (6.4 nm) above the 2000 km target which compares fairly well with an error of 3.5 km (1.9 nm) for the 1.5 L/D biconic vehicle. The study concluded that the low L/D raked configuration warrants further study which could include stability analysis as well as the inclusion of density shears and dynamic atmospheric variations.
Cerimele Christopher J.
Meyerson Robert E.
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