Development and Evaluation of an Inverse Solution Technique for Studying Helicopter Maneuverability and Agility
Abstract
An inverse solution technique for determining the maximum maneuvering performance of a helicopter using smooth, pilotlike control inputs is presented. Also described is a piloted simulation experiment performed on the NASA Ames Advanced Cab and Visual System to investigate the accuracy of the solution resulting from this technique. The maneuverability and agility capability of the helicopter math model was varied by varying the pitch and roll damping, the maximum pitch and roll rate, and the maximum load factor capability. Three maneuvers were investigated: a 180-degree turn, a longitudinal pop-up, and a lateral jink. The inverse solution technique yielded accurate predictions of pilot-in-the-loop maneuvering performance for two of the three maneuvers.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1991
- Accession Number
- ADA241980
Entities
People
- Matthew S. Whalley
Organizations
- United States Army Aviation and Missile Command