EXPLORATORY FULL-SCALE GROUND AND FLIGHT TEST EVALUATION OF THE ROBERTSON ULTRA-LOW SPEED FLIGHT CONTROL SYSTEM
Abstract
The results of an exploratory full-scale ground and flight test evaluation of the stability, control, performance, handling, and maintenance characteristics of the Robertson Ultra-Low-Speed Control System (ULS) are presented. The (ULS) consists of a small set of aerodynamic control surfaces placed immediately behind the propeller disk and permanently connected to the airplane's conventional flight control system. The results of this program showed that, at 40 mph., the ULS increased pitch, yaw, and roll control powers to 256, 280, and 250%, respectively, of basic airplane values. This increase also reduced the airplane's minimum speed from a control-limited 40 to a power- limited 20 mph with an attendant 50% reduction in landing and take-off distance. Glide angle was increased from 10 to 20 degrees through installation of the new system. The ULS installation did not appreciably affect stability or handling qualities, and caused no 'oversensitivity' at maximum speed (168 mph). Test results indicate that the rudimentary ULS system tested is a light, simple, and inexpensive way of generating the powerful low-speed control moments required for V/STOL operation.
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1962
- Accession Number
- AD0282123
Entities
People
- James L. Robertson