Title:
Supersonic Propulsive Divert Maneuvers for Future Robotic
and Human Mars Missions
Supersonic Propulsive Divert Maneuvers for Future Robotic
and Human Mars Missions
Author(s)
Mandalia, Amit B.
Advisor(s)
Braun, Robert D.
Editor(s)
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Abstract
Future robotic and human missions to Mars require improved landed precision and
increased payload mass. Two architectures that seek to meet these requirements using
supersonic propulsive diverts are proposed in this paper: one utilizing a high-altitude
propulsive divert and another with thrust vectoring during supersonic retropropulsion. Low
ballistic coefficient entry vehicles decelerate high in the thin Mars atmosphere and may be
used to deliver higher-mass payloads to the surface. A high-altitude supersonic propulsive
divert maneuver is proposed as a means of precision landing for low ballistic coefficient
entry vehicles that decelerate to supersonic speeds at altitudes of 20-60 km. This divert
maneuver compares favorably to traditional precision landing architectures with up to
100% improvement in range capability while saving over 30% in propellant mass.
Architectures which utilize hypersonic vehicles with ballistic coefficients of 10 kg/m2 were
found to land within 500 m of a target with this maneuver alone. This high-altitude divert
range capability is sensitive to altitude and flight-path angle variations at maneuver
initiation and relatively insensitive to velocity at initiation. Propellant mass fraction is
relatively invariant to the initial conditions and correlates directly with the divert distance.
Supersonic retropropulsion has also been proposed as a means to deliver higher-mass
payloads to the surface, and thrust vectoring during supersonic retropropulsion can save a
substantial amount of fuel in a precision landing scenario. Propellant mass savings greater
than 30% are possible if thrust vectoring is unconstrained during the supersonic phase of
flight. Propellant mass fraction is found to be sensitive to the divert direction and also the
altitude and flight-path angle, favoring low altitudes and shallow flight-path angles.
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Date Issued
2013-12-13
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Resource Type
Text
Resource Subtype
Masters Project
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