Dynamic attack angle amplitude limiting method for reducing missile body overload when aerodynamic configuration changes

Abstract

The invention discloses a dynamic attack angle amplitude limiting method for reducing missile body overload when aerodynamic configuration changes. The method dynamically limits the amplitude the attack angle of the missile in order to reduce missile body overload when aerodynamic configuration changes. The method for dynamically limiting the amplitude of the attack angle of the missile comprises: S1, computing a maximum attack angle amplitude value of the missile in a before-separation stable process and a after-separation stable process and a maximum attack angle amplitude value of the missile when aerodynamic configuration changes, and variation ranges of the attack angle and the flight speed of the missile; S2, determining a attack angle limiting amplitude function varying with the flight speed of the missile; S3, determining a function relationship between a maximum lift coefficient, attack angle limiting amplitude value, and the flight speed; and S4, acquiring the reference area and the mass of the missile, the flight dynamic pressure, the flight speed, and the trajectory inclination angle of the missile at the current time so as to determine the upper limit value and the lower limit value of a overload amplitude limiter at a current time. The method may determine an optimum attack angle limiting amplitude value according to the real-time flight state of the missile and reduce missile body overload when aerodynamic configuration changes.

Description

technical field [0001] The invention belongs to the technical field of missile flight control, and more specifically relates to a dynamic angle-of-attack limiting method for reducing the overload of a missile body when its shape jumps. Background technique [0002] The flight angle of attack of a missile is an important parameter that characterizes the flight state of the missile. Its magnitude, sign, and change rule of the sign play an important role in the flight state of the missile and the design of the control system. At present, in order to achieve a certain aerodynamic design index and provide a good controllable aircraft aerodynamic shape for the guidance and control profession, the purpose of changing the aerodynamic characteristics is usually achieved by changing the local structural shape of the aircraft near a specific state point. However, the jump of aerodynamic shape will bring about large separation interference (torque interference and force interference), w...

AI Technical Summary

Problems solved by technology

The traditional angle-of-attack limiter algorithm uses a fixed angle of attack to design the limiter with the maximum fixed angle of attack value. This method cannot suppress the large overload generated when the aerodynamic shape jumps, and cannot meet the requirements of the control system.

Images