FINAL SYSTEMS ANALYSIS AND FLIGHT SIMULATION REPORT. VOLUME 2
Abstract
Stability augmentation (SA) system gains were optimized by piloted flight simulator evaluation of hovering under gusty wind conditions. While operation of the SA system poses no problems during transition, stability augmentation is unnecessary above 40 knots IAS. For the 2,500 ft. hot day conditions simulated, the rapidity with which a constant altitude transition from hovering could be accomplished was limited by power available and, at the more aft c.g. locations when using a nose fan thrust reversal capability of 30%, by longitudinal trim capability. An automatic horizontal trim feature has been selected for transition which programs the tail to the full 20 degree incidence limit at all louver vector angles of 40 degrees or less. Conversion between conventional and fan flight modes is accomplished by timed sequencing of the wing fan door opening and horizontal tail incidence change as a function of diverter valve motion. Failure studies have shown that uncommanded tail motion could result in a dangerous flight condition.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1965
- Accession Number
- AD0639230
Entities
Organizations
- General Electric