A predictor-corrector guidance algorithm for use in high-energy aerobraking system studies

Details A predictor-corrector guidance algorithm for use in high-energy aerobraking system studies A predictor-corrector guidance algorithm for use in high-energy aerobraking system studies

Jan 1991

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1991aiaa.meets....b&link_type=abstract

AIAA, Aerospace Sciences Meeting, 29th, Reno, NV, Jan. 7-10, 1991. 13 p.

Computer Science

Performance

Aerobraking, Aerocapture, Aerodynamic Characteristics, Atmospheric Density, Manned Mars Missions, Predictor-Corrector Methods, Algorithms, Degrees Of Freedom

Scientific paper

A three-degree-of-freedom predictor-corrector guidance algorithm has been developed specifically for use in high-energy aerobraking performance evaluations. The present study reports on both the development and capabilities of this guidance algorithm to the design of manned Mars aero-braking vehicles. Atmospheric simulations are performed to demonstrate the applicability of this algorithm and to evaluate the effect of atmospheric uncertainties upon the mission requirements. The off-nominal conditions simulated result from atmospheric density and aerodynamic characteristic mispredictions. The guidance algorithm is also used to provide relief from the high deceleration levels typically encountered in a high-energy aerobraking mission profile. Through this analysis, bank-angle modulation is shown to be an effective means of providing deceleration relief. Furthermore, the capability of the guidance algorithm to manage off-nominal vehicle aerodynamic and atmospheric density variations is demonstrated.

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