Accession Number : AD0623100

Title :   EFFECTS OF WEIGHT, INERTIA, AND VELOCITY ON CONTROL POWER REQUIREMENTS FOR VTOL AIRCRAFT.

Descriptive Note : Master's thesis,

Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OHIO SCHOOL OF ENGINEERING

Personal Author(s) : Romine,Byron Harl

Report Date : AUG 1965

Pagination or Media Count : 71

Abstract : The pilot-vehicle systems analysis is applied to the problem of determining the effects of gross weight, inertia, and velocity on the stabilization control power requirements for the single-loop roll control system of a DOAK VZ-4 VTOL aircraft. The aircraft is subjected to random roll inputs in the form of atmospheric distrubances. Only the control power required to stabilize the aircraft roll angle by the pilot's use of ailerons alone is considered. The open-loop gain of the system is determined by maximizing the closed-loop damping ratio. There are no significant differences in the stabilization control power requirements at the gross weight conditions analyzed. Increased moments of inertia do not drive the system unstable, but the control power requirements decrease by about sixty per cent as the moments of inertia are increased from 2800 slugsq ft to 3300 slug-sq ft. (Author)

Descriptors :   (*VERTICAL TAKEOFF AIRCRAFT, STABILIZATION SYSTEMS), (*STABILIZATION SYSTEMS, POWER), STABILITY, CONTROL SYSTEMS, WEIGHT, VELOCITY, ROLL, AILERONS

Distribution Statement : APPROVED FOR PUBLIC RELEASE