Path: LunarMissions/DynamicalModels
% Returns thrust and exhaust velocity for a rocket engine.
Outputs thrust aligned with the specified vector. The thrust is set to
zero once the fuel mass is at or below zero.
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Form:
[thrust, uE] = FThrustLander( massFuel, d )
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Inputs
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massFuel (1,1) Mass of fuel (kg)
d (.) Data structure
.thrust (1,1) Thrust magnitude (N)
.uE (1,1) Exhaust velocity (m/s)
.uThrust (3,1) Thrust unit vector
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Outputs
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thrust (3,1) Thrust vector (N)
uE (1,1) Exhaust velocity (m/s)
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