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.
Heavy Lift Helicopter Flight Control System. Volume II. - Primary Flight Control System Development and Feasibility Demonstration
1977
123 pages
Report
Keine Angabe
Englisch
Aircraft , Avionics , Hydraulic & Pneumatic Equipment , Fly by wire control , Helicopters , Flight control systems , Flight testing , Development tests , Hydraulic servomechanisms , Servoamplifiers , Electrohydraulic valves , Hydraulic actuators , Transducers , Control sticks , Control knobs , Backup systems , Failure , Hydraulic equipment , Failure(Electronics) , Reliability , Redundant components , Cockpits , Magnetic brakes , Drives , H-47 aircraft , CH-47 aircraft , Heavy lift helicopters
Multi-Helicopter Heavy Lift System Feasibility Study
NTIS | 1972
|Model Helicopter Flight Control
British Library Conference Proceedings | 2009
|Model helicopter flight control
Tema Archiv | 2009
|