To provide a focus for the calculations, two high-speed tilt-rotor aircraft are considered: a 46-passenger, civil transport and an air-combat/escort fighter, both with design speeds of about 400 knots. The basic aircraft-design parameters are optimized for minimum gross weight. Key rotor and airframe parameters are optimized for high-speed performance and stability. Rotor airfoils, rotor-hub configuration, wing airfoil, and airframe structural weights representing demonstrated advance technology are discussed.
Maneuverability is examined in terms of the rotor-thrust limit during turns in helicopter configuration. The whirl-flutter stability of the coupled-wing and rotor motion is calculated in the cruise mode. The rotor performance is examined in high-speed cruise and in hover. The feasibility of operating tilting-prop-rotor aircraft at high speeds is examined by calculating the performance, stability, and maneuverability of representative configurations. The discussion includes: (1) a brief review of pertinent high angle of attack phenomena including aerodynamics, inertia coupling, and kinematic coupling (2) effects of conventional stability augmentation systems at high angles of attack (3) high angle of attack control system concepts designed to enhance departure/spin resistance and (4) the outlook for applications of these concepts to future fighters, particularly those designs which incorporate relaxed static stability.Ĭalculated performance, stability and maneuverability of high-speed tilting-prop-rotor aircraft Some fundamental information on control system effects on controllability of highly maneuverable aircraft at high angles of attack are summarized as well as techniques for enhancing fighter aircraft departure/spin resistance using control system design. This technique is believed to have application to future aircraft dynamics and pilot-vehicle interface studies.Ĭontrol-system techniques for improved departure/spin resistance for fighter aircraft It has also demonstrated its usefulness for evaluating configuration and advanced flight control system refinements. This paper describes a technique for assessing the precision controllability of highly maneuverable aircraft, a technique that was developed to evaluate the effects of buffet intensity on gunsight tracking capability and found to be a useful tool for the general assessment of fighter aircraft handling qualities. This improved maneuvering capability has significantly expanded their operating envelope and made the task of evaluating handling qualities more difficult.
Today's emerging fighter aircraft are maneuvering as well at normal accelerations of 7 to 8 g's as their predecessors did at 4 to 5 g's. A technique for the assessment of fighter aircraft precision controllability
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