In-Orbit Capture Mechanism for a Mars Sample Return Mission
- Paper number
IAC-07-E2.2.04
- Author
Ms. Alison Gibbings, Kingston University, United Kingdom
- Year
2007
- Abstract
A Mars Sample Return (MSR) mission represents a mission of both scientific and technological importance. Within the current framework of the European Space Agency’s (ESA’s) Aurora programme the MSR is considered to be a fundamental precursor and flagship mission for the eventual human exploration of Mars by 2030-2033 [1]. For a successful MSR mission three samples – one of Martian atmosphere, one of surface and one of subsurface rock and regolith will be collected and returned to Earth for further analysis. This will enable scientists to perform detailed mineralogical, geochemical and petrologic analysis that can not be currently conducted in situ or through remote sensing instruments. This will hopefully answer the fundamental question of whether or not life exists or ever existed on Mars. Within the proposed mission architecture [2] three operational sequences are required, this includes, the Martian ascent, the rendezvous and the Earth return. Once the three samples have been collected and positioned into a sample canister they will be transferred to a Mars Ascent Vehicle (MAV) and subsequently launched from the Martian surface into an orbit of 500 km +/- 50 km [1]. When in orbit, the MAV will release the sample canister into a ‘free flying’ orbit around Mars, where the sample canister will await retrieval by the external capture mechanism mounted onboard the Mars Orbiter. Once captured, the sample canister is transferred into the Earth Return Vehicle (ERV) stowed onboard the Orbiter. Only when all these steps have been accomplished is the rendezvous and transfer chain complete. It is critical that the Martian samples are transferred effectively and correctly, ensuring that the initial geology and chemical composition of the samples are preserved. The success of a MSR capture mechanism relies heavily on the development and integration of a reliable mechanical system. Therefore the main focus of this paper is to exclusively address, formulate and present an external capture mechanism to be utilised on the return phase of the MSR mission, as defined in the Mars Sample Return capture scenario [3]. Issues contained within the terminal rendezvous operational sequence have been considered and critically evaluated this includes capture mechanisms derived from both terrestrial and space applications. Such issues include, mechanical performance, inertia, sample bouncing, contamination and subsystem integration (including jettisoning), thereby proposing an optimal design and transfer mechanism against the pre-defined mission requirements and constraints. [1] EADS Astrium (2004) Mars Sample Return Study Executive Study, Issue 1, CI Code TN/MSR/AST/101, UK Export Control Rating: 9E001 [2] European Space Agency (2006) Mars Sample Return Phase A2, Mission and System Requirements, Issue 1, Revision 2, Reference MSR-SRD-ESA (HME)-0001 [3] ESA-ESTEC (2005) Statement of Work, Capture/Docking Mechanism Testing Specification, Issue 1, Reference TEC-MMM/2005/978
- Abstract document
- Manuscript document
IAC-07-E2.2.04.pdf (🔒 authorized access only).
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