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The Electric Orbiter
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English
Abstract
The current design base of the Space Shuttle Orbiter employs hydraulic actuation for control of aerosurfaces, engine thrust, engine thrust vector, brakes, and landing gear functions. As early as 1972, electromechanical actuation (EMA) was considered as an alternative system. As a result of continued advances in technology development, studies now indicate that EMA is a more attractive alternative. Major advantages are weight reduction, striking improvement in energy efficiency, easier maintenance, and a cleaner vehicle.
The results of a system study advocating EMA for the Orbiter are presented. Emphasis is placed on a clear understanding of the relationships between mission requirements and design parameters. EMA system energy requirements are compared with those of the existing hydraulic system. Detailed discussion of the synthesized EMA system is limited to the aerosurface actuators. The design is consistent with the Orbiter “fail operational,” “fail safe” redundancy requirement. Finally, an assessment summary of EMA for Orbiter is made.
Authors
Citation
Swingle, W. and Edge, J., "The Electric Orbiter," SAE Technical Paper 821419, 1982, https://doi.org/10.4271/821419.Also In
References
- Edge J. T. “An electromechanical actuator technology development program,” paper presented at SAE 1978, Aerospace Fluid Power and Control Technologies Symposium, Cherry Hill, NJ Apr. 1978
- Sawyer Bert Edge J. T. “Design of a samarium cobalt brushless dc motor for electromechanical actuator applications,” paper presented at IEEE 1977, National Aerospace and Electronics Conference (NAECON), Dayton, OH May 1977