A rocket engine for Mars sample return using in situ propellants | Zendy

Diane Linne | Zendy

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A rocket engine for Mars sample return using in situ propellants

Author(s) -

Diane Linne

Publication year - 1997

Publication title -

38th aerospace sciences meeting and exhibit

Language(s) - English

Resource type - Conference proceedings

DOI - 10.2514/6.1997-893

Subject(s) - propellant , mars exploration program , aerospace engineering , in situ , rocket engine , rocket (weapon) , sample (material) , liquid propellant rocket , astrobiology , rocket propellant , exploration of mars , aeronautics , environmental science , materials science , engineering , physics , meteorology , thermodynamics

Recent studies for the planned Mars sample return mission were reviewed and modified to utilize carbon monoxide and oxygen as potential in situ propellants. Based on these studies a representative full scale engine thrust of 2225 N (500 lbf) was selected as appropriate to demonstrate performance, and the design for that engine is presented. Previous experimental results combined with parametric analyses were used to define the geometry for the engine which operates on liquid carbon monoxide and liquid oxygen. The engine was constructed using a combination of high-temperature alloys and lightweight ceramics. The materials selected were hafnium oxide, iridium, rhenium, and carbon-carbon.

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