Guided entry performance of low ballistic coefficient vehicles at Mars

Supersonic Propulsive Divert Maneuvers for Future Robotic and Human Mars Missions

“…An MSL-like entry state 9 was used unless otherwise stated. This allowed for parity to compare results and also make sure realistic dispersions were used.…”

“…Vehicles with hypersonic ballistic coefficients of 1 kg/m 2 , 5 kg/m 2 , 10 kg/m 2 , 20 kg/m 2 , 50 kg/m 2 , which enter ballistically, were simulated as part of this study, where ballistic coefficient is defined as m entry / (C D A). The hypersonic trajectories are based on the work of Meginnis et al 9 The ballistic coefficients are varied with the addition of a HIAD to the system, whose mass is estimated using relationships from the literature. 15 The total entry mass is the mass of the HIAD plus 3300 kg.…”

“…Low ballistic coefficient vehicles, such as those that use hypersonic IADs (HIADs), have been shown to decelerate much higher in the atmosphere at Mars, between 20 and 60 km. 9 This allows for more time of flight between the end of hypersonic flight and the point of parachute deployment at 6-10 km. For the first part of this study, it is postulated that performing propulsive maneuvers during this high-altitude portion of flight to target a landing site will lead to an overall reduced propellant usage and a precision landing capability.…”