Aeroassist vehicle requirements for a Mars Rover/Sample Return Mission

Meyerson, Robert E.; Cerimele, Christopher J.

doi:10.2514/6.1988-303

Cited by 6 publications

(1 citation statement)

References 4 publications

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“…The fourth, discovery-class mission, Sample return missions for Mars have been studied periodically for the past 30 years [4][5][6] . The Earth entry phase envisioned by previous studies involved either 1) an orbit insertion at Earth with Space Shuttle or Space Station rendezvous for recovering the samples or 2) direct entry with an Apollo-style entry vehicle utilizing parachutes, air-snatch, or water recovery.…”

Section: Introductionmentioning

confidence: 99%

A passive Earth-entry capsule for Mars Sample Return

Mitcheltree

Kellas

Dorsey

et al. 1998

7th AIAA/ASME Joint Thermophysics and Heat Transfer Conference

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A combination of aerodynamic analysis and testing, aerothermodynamic analysis, structural analysis and testing, impact analysis and testing, thermal analysis, ground characterization tests, configuration packaging, and trajectory simulation are employed to determine the feasibility of an entirely passive Earth entry capsule for the Mars Sample Return mission. The design circumvents the potential failure modes of a parachute terminal descent system by replacing that system with passive energy absorbing material to cushion the Mars samples during ground impact. The suggested design utilizes a spherically blunted 45-degree half-angle cone forebody with an ablative heat shield. The primary structure is a hemispherical, composite sandwich enclosing carbon foam energy absorbing material. Though no demonstration test of the entire system is included, results of the tests and analysis presented indicate that the design is a viable option for the Mars Sample Return Mission.

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Section: Introductionmentioning

confidence: 99%