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Digital Flight Control Actuation
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English
Abstract
A two part description of two digital-hydrostatic servoactuators is presented. The first servoactuator described is based on a digital valve that can be hydraulically or pneumatically powered. The actuator is incremented by discrete volumes of fluid discharged by the valve at a frequency and polarity dependent on the servo error magnitude and sign.
The basic principle of operation of the fluid-powered servoactuator applies to an electrically-powered one. In this version, however, the discrete flow is derived from a digitally controlled pump driven by a constant speed motor. This part of the paper includes a preliminary layout of a dual power-hinge servoactuator which shows that a compact, fully integrated module is feasible.
Authors
Citation
Escobosa, A., "Digital Flight Control Actuation," SAE Technical Paper 951992, 1995, https://doi.org/10.4271/951992.Also In
References
- Acee, Hap “The Integrated Actuation Package Approach to Primary Flight Control” SAE Paper 920968 April 1992
- Lyle, B.S. “Reducing the Complexity in Fly-By-Wire Flight Control Actuators” SAE Paper 851752 October 1985
- Van Loon, J. “Fluid Power Conversion” SAE Aerospace Engineering February 1992
- Robinson, C.W. “The Use of Power-Adaptive and Power-Reversible Flight Control Actuation Systems” SAE Paper 801190 October 1980
- Fenner, J.H. “Magnetic Latch Improves Computer Controlled Pump” Machine Design October 1990