Research and Development of Aircraft Control Actuation Systems
Abstract
This report describes the design and test of a multipurpose actuation test rig to be used for loaded evaluation of actuation systems with rotary outputs and/or integrated as part of wing structure. It also describes a hydromechanical flutter damping module for an F-4 stabilator actuator. The module incorporates design improvements based on previous test results. Laboratory tests results on the improved module are presented. Development and test results of a linear force motor based upon a moving magnet concept, and the measured performance characteristics of the concept over a range of parameter variations are presented. A method of force enhancement for direct drive force motors and the corresponding test results applied to a moving coil force motor are described. The concept is based upon applying a limited time duration pulse to the force motor in order to increase the force output when required. The logic technique used to initiate the pulse application is presented. Applying a digital computer as a controller for an analog electrohydraulic control system requires consideration of the interface used. The effect of a pulse width modulation interface on the life of analog electrohydraulic hardware is presented. There is a potential for reducing the pumping capacity of an aircraft's flight control hydraulic system by using accumulators to store hydraulic energy. The results of a study using this approach and an F-16 simulation are presented. Keywords: Digital interface; Energy storage; Flight control hydraulics; Force enhancement, Flutter suppression.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1986
- Accession Number
- ADA177491
Entities
People
- Carl N. Allbright
- Gavin D. Jenney
- Harry W. Schreadley
- William G. Talley