Precision Landing at Mars Using Discrete-Event Drag Modulation
Author(s)
Putnam, Zachary R.
Braun, Robert D.
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Abstract
An entry, descent, and landing architecture capable of achieving Mars Science
Laboratory class landed accuracy (with 10 km of target) while delivering a Mars
Exploration Rover class payload to the surface of Mars is presented. The architecture
consists of a Mars Exploration Rover class aeroshell with a rigid, annular drag
skirt. Maximum vehicle diameter is limited to be compatible with current launch
vehicle fairings. A single drag skirt jettison event is used to control range during
entry. Three-degree-of-freedom trajectory simulation is used in conjunction with
Monte Carlo techniques to assess the flight performance of the proposed architecture.
Results indicate landed accuracy is competitive with pre-flight Mars Science
Laboratory estimates, and peak heat rate and integrated heat load are significantly
reduced relative to the Mars Exploration Rover entry system. Modeling parachute
descent within the onboard guidance algorithm is found to remove range error
bias present at touchdown; the addition of a range-based parachute deploy trigger
is found to significantly improve landed accuracy.
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Date
2013-02
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Text
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Paper
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