Entry Configurations and Performance Comparisons for the Mars Smart Lander

Lockwood, Mary Kae; Powell, Richard W.; Sutton, Kenneth; Prabhu, Ramadas K.; Graves, Claude; Epp, Chirold; Carman, Gilbert

doi:10.2514/1.20677

Cited by 29 publications

(10 citation statements)

References 11 publications

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“…• • A fully internal actuator preserves the integrity of the aero-shell with no external aerodynamic tabs, thruster nozzles, etc., that would be found on other actuator concepts [6].…”

Section: Enables the Ballast Mass Actuators To Be Designed So As To Ementioning

confidence: 62%

Sherpa Moving Mass Entry Descent Landing System

Balaram

2005

Volume 6: 5th International Conference on Multibody Systems, Nonlinear Dynamics, and Control, Parts A, B, and C

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We describe Sherpa — a Strap-on High-altitude Entry Reconnaissance & Precision Aeromaneuver system that utilizes a moving mass system within an entry capsule to land a spacecraft precisely onto the surface of Mars. Sherpa uses two sets of “strap-on” assemblies, one for high-altitude sensing using a terrain imager, and another for agile hypersonic flight using a moving-mass steering device. In this paper we focus on the moving mass system — a steering device that provides an agile trajectory control capability that is mechanically simple, completely internal to the vehicle, has high control authority, and is robust to mechanism failure. The Sherpa system takes a small fraction (5–10%) of the total system mass, and is capable of delivering payloads to within the proximity (~5 km) of a wide variety of landing sites including those at high-altitude (2.5+ km above the reference geoid).

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“…• • A fully internal actuator preserves the integrity of the aero-shell with no external aerodynamic tabs, thruster nozzles, etc., that would be found on other actuator concepts [6].…”

Section: Enables the Ballast Mass Actuators To Be Designed So As To Ementioning

confidence: 62%

Sherpa Moving Mass Entry Descent Landing System

Balaram

2005

Volume 6: 5th International Conference on Multibody Systems, Nonlinear Dynamics, and Control, Parts A, B, and C

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“…Lockwood et al discuss entry issues for the Mars Smart Lander [now the Mars Science Laboratory (MSL)] [99]. MSL is to be a 70-deg sphere-cone forebody with a biconic afterbody [100].…”

Section: Mars Science Laboratorymentioning

confidence: 99%

Laminar-Turbulent Transition on Reentry Capsules and Planetary Probes

Schneider

2006

Journal of Spacecraft and Rockets

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“…Novel structural and control concepts that enable the decelerator to undergo variation in geometry are the subject of this paper. It should be noted that other alternatives that have been proposed for the aerodynamic control problem make use of aerodynamic surfaces such as tabs or flaps 3 . They are either fixed in configuration or single-shot deployable, which limits them to only a few discrete configurations.…”

Section: Introductionmentioning

confidence: 99%

Structural and Control Concepts for Variable Geometry Planetary Entry Systems

Quadrelli

Boussalis

Davis

et al. 2009

50th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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The results presented in this paper apply to a generic vehicle entering a planetary atmosphere which makes use of a variable geometry change to modulate the heat, drag, and acceleration loads. Two structural concepts for implementing the cone angle variation, namely a segmented shell and a corrugated shell, are presented. A structural analysis of these proposed structural configuration shows that the stress levels are tolerable during entry. The analytic expressions of the longitudinal aerodynamic coefficients are also derived, and guidance laws that track reference heat flux, drag, and aerodynamic acceleration loads are also proposed. These guidance laws have been tested in an integrated simulation environment, and the results indicate that use of variable geometry is feasible to track specific profiles of dynamic load conditions during reentry.

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Entry Configurations and Performance Comparisons for the Mars Smart Lander

Cited by 29 publications

References 11 publications

Sherpa Moving Mass Entry Descent Landing System

Sherpa Moving Mass Entry Descent Landing System

Laminar-Turbulent Transition on Reentry Capsules and Planetary Probes

Structural and Control Concepts for Variable Geometry Planetary Entry Systems

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