The development of a simplified Fin Folding Mechanism for a future space transportation vehicle

Details The development of a simplified Fin Folding Mechanism for a future space transportation vehicle The development of a simplified Fin Folding Mechanism for a future space transportation vehicle

Jul 2005

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2005esasp.591..143w&link_type=abstract

In: Proceedings of the 11th European Space Mechanisms and Tribology Symposium, ESMATS 2005, 21-23 September 2005, Lucerne, Switz

Computer Science

Deployment And Hold-Down Mechanisms

Scientific paper

In the time when the Crew Return Vehicle (CRV) was being considered as a follow on joint venture between ESA and NASA, Contraves Space AG was being considered as the sub-contractor for the Fin Folding Mechanism. Although due to the lack of funding in the USA, the CRV programme was stopped, ESTEC decided to continue the development of the Fin Folding Mechanism (FFM) for a "future Space Transportation Vehicle" (STV) for launch and re-entry. Contraves Space was subsequently awarded with a contract to develop a simplified mechanism to replace the mechanism that was designed for CRV. The function of the FFM is to fold the Vehicle Fin inboard so that any future STV can be accommodated in today's launchers. The FFM must be able to support the fin during launch, deploy the fin and then support the fin in the deployed position during re-entry. Contraves Space reviewed the functionality of the old CRV design, with its' different mechanisms for each of the functions, and a synchronisation system, and established a novel design where one mechanism can be used to perform all three functions. The final design utilises a four bar link mechanism, driven over-centre in both of the end positions, driven by a high-torque drive unit comprising a Harmonic Drive, a conventional gearbox and a 3 Phase DC motor. To protect the high-torque drive system against stall, a clutch has been utilised based on spring and rotating ball technology. These devices are used seldom in space, but as surviving stall is often a problem for mechanisms, the results from the test programme will be interesting with respect to the use of such devices in future space mechanisms. The design of the mechanism consists of three almost identical nodes, one of which has been built and is undergoing "qualification" testing at Contraves Space. The mechanism will be subjected to the full range of tests including, functional tests, random vibration tests, thermal vacuum tests and a static load test. This paper will detail the design of the mechanism and highlight the problems that had to be overcome in the design phase.

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