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Design Considerations for an EVA Simulator
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English
Abstract
A new EVA/IVA simulation technique in which a servo-driven/computer-controlled simulator provides motion to the astronaut equivalent to that experienced in a zerog environment is described. The instrumentation systems required to generate the necessary input data to the analog computer, programed with the EVA/IVA dynamic equations, are discussed.
The instrumentation consists of a load cell array to sense the forces and moments applied to the spacecraft by the astronaut during orbital activity and a unique limb motion sensor that continuously measures the astronaut's limb positions. The design considerations for the simulator are presented, and various space missions conducted on the simulator, with primary emphasis on EVA, are discussed.
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Citation
Tewell, J. and Johnson, C., "Design Considerations for an EVA Simulator," SAE Technical Paper 670568, 1967, https://doi.org/10.4271/670568.Also In
References
- Tewell J. R. Tobey W. H. “Gemini Orbital Tracking.” IEEE Transactions on Aerospace and Electronic Systems AES-2 3 May 1966
- Danner R. V. DeRocher W. L. Jr. “A Full-Scale Docking Simulation Using a Rendezvous Radar.” IEEE International Space Electronics Symposium Las Vegas, Nev. October 1964
- Wudell A. E. DeRocher W. L. Jr. “Technique for Evaluating Space-Vehicle Docking Mechanisms.” Research Report No. R-64-7 Martin-Marietta Corp. Denver, Col. November 1964
- Tewell J. R. Johnson C. H. “EVA/IVA Simulation Dynamics.” Research Report No. R-67-8 Martin Marietta Corp. Denver, Col. February 1967
- Tewell J. R. Murrish C. H. “Engineering Study and Experiment Definition for an Apollo Applications Program Experiment on Vehicle Disturbances Due to Crew Activity.” Final Report to NASA under Contract No. NAS 1-6713 March 1967