Extension of Traditional Entry, Descent, and Landing Technologies for Human Mars Exploration

Christian, John A.; Wells, Grant William; Lafleur, Jarret M.; Verges, Amanda; Braun, Robert D.

doi:10.2514/1.31929

Cited by 52 publications

(40 citation statements)

References 26 publications

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“…The MSL vehicle diameter is 4.5 m. For this study, the MSL heatshield shape was used but the diameter was scaled-up to 15 m to account for the larger size and payload that will be required for human-class high-mass Mars missions. High-mass Mars versions of 70-degree sphere cone geometries were previously studied by Braun and Manning [1], Steinfeldt et al [5], and Christian et al [6]. Nominal entry mass values of 100 and 160 metric tons were considered.…”

Section: Geometriesmentioning

confidence: 99%

“…Nominal entry mass values of 100 and 160 metric tons were considered. The estimated payload mass fractions for a 15 m diameter 70-degree sphere cone with nominal lift-over-drag ratio (L/D) of 0.3 is 0.25 [6] meaning that a 15 m vehicle could land payloads of 25 to 40 metric tons on the surface of Mars. The second vehicle geometry considered in this study was a slender, mid-L/D vehicle also known as the Ellipsled.…”

Section: Geometriesmentioning

confidence: 99%

“…In recent years, a number of studies have been performed to determine the vehicle and mission requirements that would enable the human exploration of Mars [1][2][3][4][5][6][7][8]. The vehicle geometries of these proposed high-mass Mars vehicles were based on 70-degree sphere cones, Apollo-type capsules, or a slender, mid lift-over-drag ratio (L/D) vehicle referred to as an Ellipsled.…”

Section: Introductionmentioning

confidence: 99%

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Coupled Fluids-Radiation Analysis of a High-Mass Mars Entry Vehicle

Palmer

Allen

Tang

et al. 2011

42nd AIAA Thermophysics Conference

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The NEQAIR line-by-line radiation code has been incorporated into the DPLR Navier-Stokes flow solver such that the NEQAIR subroutines are now callable functions of DPLR. The coupled DPLR-NEQAIR code was applied to compute the convective and radiative heating rates over high-mass Mars entry vehicles. Two vehicle geometries were considered -a 15 m diameter 70-degree sphere cone configuration and a slender, mid-L/D vehicle with a diameter of 5 m called an Ellipsled. The entry masses ranged from 100 to 165 metric tons. Solutions were generated for entry velocities ranging from 6.5 to 9.1 km/s. The coupled fluids-radiation solutions were performed at the peak heating location along trajectories generated by the Traj trajectory analysis code. The impact of fluids-radiation coupling is a function of the level of radiative heating and the freestream density and velocity. For the high-mass Mars vehicles examined in this study, coupling effects were greatest for entry velocities above 8.5 km/s where the surface radiative heating was reduced by up 17%. Generally speaking, the Ellipsled geometry experiences a lower peak radiative heating rate but a higher peak turbulent convective heating rate than the MSL-based vehicle.

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Section: Geometriesmentioning

confidence: 99%

Section: Geometriesmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Coupled Fluids-Radiation Analysis of a High-Mass Mars Entry Vehicle

Palmer

Allen

Tang

et al. 2011

42nd AIAA Thermophysics Conference

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“…Human Mars architecture studies [10], [11], [12], [13] predict payload masses on the order of 20 to 100 t. The EDL requirements of these high-mass, high ballistic coefficient systems extend well beyond the capabilities of many Viking-heritage EDL technologies. Supersonic deceleration is possibly the most critical deficiency in extending these heritage technologies.…”

Section: Retropropulsion Systems Studiesmentioning

confidence: 99%

“…Alternatively, Christian, et al [12] replaced the traditional parachute system with a purely propulsive descent, initiated at supersonic velocities. Because these studies are for human class missions, with payload masses ranging from 20 to 100 t, significantly larger propulsion systems are required than have been flown previously.…”

Section: Retropropulsion Systems Studiesmentioning

confidence: 99%

A Survey of Supersonic Retropropulsion Technology for Mars Entry, Descent, and Landing

Korzun¹,

Cruz²,

Braun³

2008

2008 IEEE Aerospace Conference

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This paper presents a literature survey on supersonic retropropulsion technology as it applies to Mars entry, descent, and landing (EDL). The relevance of this technology to the feasibility of Mars EDL is shown to increase with ballistic coefficient to the point that it is likely required for human Mars exploration. The use of retropropulsion to decelerate an entry vehicle from hypersonic or supersonic conditions to a subsonic velocity is the primary focus of this review. Discussed are systemslevel studies, general flowfield characteristics, static aerodynamics, vehicle and flowfield stability considerations, and aerothermodynamics.The experimental and computational approaches used to develop retropropulsion technology are also reviewed. Finally, the applicability and limitations of the existing literature and current state-of-theart computational tools to future missions are discussed in the context of human and robotic Mars exploration.

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Attitude tracking control for Mars entry vehicle via T-S model with time-varying input delay

Lei

Xiao-li

et al. 2016

Nonlinear Dyn

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Extension of Traditional Entry, Descent, and Landing Technologies for Human Mars Exploration

Cited by 52 publications

References 26 publications

Coupled Fluids-Radiation Analysis of a High-Mass Mars Entry Vehicle

Coupled Fluids-Radiation Analysis of a High-Mass Mars Entry Vehicle

A Survey of Supersonic Retropropulsion Technology for Mars Entry, Descent, and Landing

Attitude tracking control for Mars entry vehicle via T-S model with time-varying input delay

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