Guidance Trades for High Ballistic Coefficient Mars Lander Trajectories
Author(s)
Anderson, Tyler R.
Braun, Robert D.
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Abstract
Large ballistic coefficient entry vehicles are required to achieve more ambitious
exploration goals at Mars. These trajectories exhibit several characteristics that
make successful landings difficult including low altitude deceleration and inability
to decelerate under parachute. One promising mission architecture involving
propulsive supersonic descent and landing is proposed as a candidate for future
high ballistic-coefficient vehicles. This paper will investigate guidance options
for precision landing using hypersonic bank-angle steering and thrust vector controlled
propulsive descent. First, a numerical predictor-corrector guidance algorithm
is applied to examine the benefits and trade-offs of range targeting during
the hypersonic regime. This is compared against the state-of-the-art Apollo Final
Phase guidance algorithm. Next, a modification is included to increase guidance
performance. Finally, a propulsive divert algorithm is assessed for its impact on
landing accuracy and propellant usage.
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Date
2017-02
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