Aerocapture and aeromaneuvering at MarsThis paper presents the results of a guidance analysis study for aerocapture and aeromaneuvering at Mars. A 4-state, near-optimal, hybrid guidance algorithm is derived for applications throughout the paper. It is based on the critical assumption that Loh's function remains constant between successive guidance updates. Besides the guidance algorithm, the paper presents a performance evaluation of guidance derived from estimated or 'navigated' spacecraft state, provided by an onboard navigation subsystem for real-time applications on Mars. For the performance evaluation, the spacecraft state is augmented by such parameters as the reference atmospheric density and scale-height, the banking angle and angle of attack for spacecraft control and the accelerometer measurement model errors. Finally, the paper examines also, the influence of random uncertainties in atmospheric density on aeroassisted maneuvers, by a Monte Carlo type of simulation.
Document ID
19930029295
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Vijayaraghavan, A. (JPL Pasadena, CA, United States)
Date Acquired
August 15, 2013
Publication Date
August 1, 1992
Subject Category
Space Communications, Spacecraft Communications, Command And Tracking