INVESTIGATION AND DEVELOPMENT OF REDUNDANCY TECHNIQUES TO ACHIEVE DUAL FAULT CORRECTIVE CAPABILITY IN FLIGHT CONTROL ACTUATORS.
Abstract
The objective of this study and investigation was to develop dual fault corrective capability for increased reliability by applying redundancy at the element level in flight control actuation components. Studies were performed to determine the functional and operational requirements for a flight control actuator capable of operating after two failures. A survey of presently used actuator mechanizations and failure correction techniques was made to categorize them along functional lines and to establish six possible dual fault correcting actuator (DFCA) configurations. An operational and failure analysis of the six DFCA configurations was made to determine their fault corrective capability relative size, cost and potential reliability. From this analysis, the Triplex Actuator with Electronic Model and Logic and the Quadruplex Actuator with Hydraulic Logic were selected for detail design development. These designs have one active actuator which controls the output and two operating standby actuators that can be locked-in to drive the output, with undegraded performance, when a failure occurs. Detail mechanical, hydraulic and electrical design was performed to obtain the two tentative actuator designs. A detail analysis and computer simulation of the system equations was performed to determine transients due to failures. An overall relative comparison of a single system, single fault and the two DFCA designs, indicates that the Triplex Actuator achieves dual fault corrective capability with a minimum increase in weight, size, power and complexity.
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1967
- Accession Number
- AD0815059
Entities
People
- E. Musser
- J. E. Rinde
- M. Wildrick
- P. S. Coppola
- T. Honda
Organizations
- General Electric