Heavy Lift Helicopter Flight Control System. Volume II. - Primary Flight Control System Development and Feasibility Demonstration
Abstract
The U.S. Army's Heavy Lift Helicopter Advanced Technology Component Program required the design, development and inflight feasibility demonstration of an electrohydraulic flight control system, referred to as fly-by-wire. Total flight testing encompassed evaluation and demonstration in two parts. First, a direct electrical linkage was successfully demonstrated in September 1973. Subsequently, an automatic flight control system was installed and evaluated with the direct electrical linkage. This volume describes the primary flight control system; its design features, installation test. Included also is a report of a related activity to design and evaluate, in laboratory tests, a compatible cockpit controller subsystem in which pilot commands are converted to electrical signals. Standard pilot interface features, such as magnetic brakes, stick position trim and force trim are included. To interface with the automatic flight control system, controller driver actuators are included.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1977
- Accession Number
- ADA049580
Entities
People
- B. L. Mcmanus
- T. H. Sanders
Organizations
- Boeing Rotorcraft Systems