Design method for fighter course stability augmentation control system

Abstract

The invention discloses a design method for a fighter course stability augmentation control system, wherein combined feedback of yaw angle rate information, roll angle rate information and angle-of-attack information, an side slip angle and side slip angle rate feedback, and cross-linking information of ailerons are introduced into a rudder channel, and the gain of each feedback channel is determined by using a root track method. Due to the fact that the actual side slip angle is not easy to measure, the estimated side slip angle and the side slip angle rate information are used for feedback.Finally, the relation between the gain and the course static stability of the course stability augmentation system is analyzed. According to the design method in the invention, an automatic stabilityaugmentation system is added into a course operating system of the aircraft, so that the damping ratio of an oscillating mode of the aircraft is increased, the adverse effects caused by transverse lateral movement cross-linking coupling are reduced, and the stability of the aircraft is improved.

Description

technical field [0001] The invention relates to a design method of a fighter jet heading stabilization control system, and belongs to the technical field of aviation advanced flight control. Background technique [0002] In order to meet its ever-expanding flight envelope range, modern high-performance fighter jets relax or even cancel the static stability and dynamic stability requirements of the aircraft body during the aerodynamic shape design process of the aircraft, which weakens the static stability of the aircraft. After relaxing the static stability of the aircraft, the focus of the aircraft is located in front of the center of gravity of the aircraft in subsonic flight, which increases the instability of the aircraft; in near-sonic flight, the focus of the aircraft is very close to the center of gravity of the aircraft, which is close to stability In supersonic flight, although the focus of the aircraft moves behind the center of gravity of the aircraft, the distanc...

AI Technical Summary

Problems solved by technology

[0003] Modern fighter jets generally have a slender fuselage and an aerodynamic shape with a small vertical tail, which makes the static stability of the heading insufficient, and is often in a state of sideslip

Therefore, lateral oscillations with a low damping ratio often occur, and the pilot has no time to respond to this short-period oscillation mode, which easily leads to poor ride quality, sharp increase in resistance, and decreased maneuverability, which seriously affects the performance of the aircraft. maneuverability, which is not conducive to the occupation, aiming and accurate delivery of weapons in air combat

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