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Redundant Damper Servoactuators for the F-111 Airplane
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English
Abstract
This paper describes the design of the self-contained electrohydraulic servo damper packages used for stability augmentation control in each axis of the F-111 airplane. These servo-actuators incorporate integral error sensing and failure shut-off provisions through nonelectrical means. Each actuator is supplied with three simultaneous signal inputs, together with dual hydraulic system pressurization. Hydromechanical error comparisons are performed and these are used to control a logic network which shuts off a portion of the actuator should a sufficient error develop. The shut-off is accomplished automatically and with no significant change in actuator performance following shut-off. The basic operation, design and performance of these rather sophisticated actuators is described.
Authors
Citation
Thayer, W., "Redundant Damper Servoactuators for the F-111 Airplane," SAE Technical Paper 650361, 1965, https://doi.org/10.4271/650361.Also In
References
- Garnjost K. D. Thayer W. J. “New Servovalves for Redundant Electrohydraulic Control” Second Congress of International Federation of Automatic Control at Basle Switzerland September 1963
- Thayer W. J. “Design Considerations for Mechanical Feedback Servoactuators” Moog Servocontrols, Inc. Technical Bulletin No. 104 April 1964
- Haugen E. B. “Statistical Methods for Structural Reliability Analysis” 10th Annual Symposium on Reliability and Quality Control Washington, D. C. January 1964
- Chamberlain B. S. “FC 11 System Tolerance Study” G. E. / J. C. Project Memorandum 63-51-857 November 22 1963
- Hall D. I. Weppner B. H. “Damper Servoactuator, Sizing Calculations” Moog Servocontrols, Inc. Report ER-68-A October 3 1963
- “Performance Specification, Servo, Damper” General Dynamics/Fort Worth ZC00001A January 1963