Masters Theses

Date of Award

12-1988

Degree Type

Thesis

Degree Name

Master of Science

Major

Aviation Systems

Major Professor

Ralph D. Kimberlin

Committee Members

Arthur A. Mason, Robert B. Richards

Abstract

The purpose of this evaluation was to assess the flying qualities and performance of the AH-64A helicopter for the USMC attack mission. The evaluation was completed during four flights totalling 6.0 flight hours and a 4.0 hour ground test. The Digital Automatic Stabilization Equipment (DASE) off flying qualities of the AH-64A will allow the pilot to continue the mission during a DASE failure with only a small increase in workload. In the event of a tail rotor failure, the engine chop collar will allow the pilot to reduce engine power to idle without removing his hand from the collective. The DASE off flying qualities and the engine chop collar are enhancing characteristics which should be incorporated in future designs. The excessive transient droop encountered during rapid collective application will result in settling of the aircraft into the ground or other obstacles to flight when conducting Nap of the Earth operations. The slow main rotor wind down following actuation of the rotor brake will result in excessive blade flapping and droop stop pounding during shipboard gusty wind conditions. The two previous deficiencies are Part 1 deficiencies which should be corrected as soon as possible. The extremely high lateral control sensitivity will result in an abrupt and jerky aircraft response to rapid lateral cyclic inputs and will result in pilot induced oscillations during iii high gain tasks. The lateral control sensitivity is a Part II deficiency and nine additional Part II deficiencies were identified which should be corrected as soon as practicable. Eight Part III deficiencies were identified which should be avoided in future designs. Upon correction of the two Part I deficiencies identified during this evaluation, the AH-64A will have excellent potential for the USMC attack mission. A final determination of the suitability of the aircraft will be based on the results of a mission systems and a shipboard compatibility evaluation.

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