A method for controlling the balance motion state of an aircraft with a single slider variable center of mass

Abstract

The invention proposes a method for controlling the balanced motion state of an aircraft by changing the center of mass of a single slider, and can calculate the nutation angle, precession angular velocity and relative roll angle of the aircraft in a balanced state under different conditions. Step 1. Obtain the projectile structure parameters and flight condition parameters of the reentry vehicle to be analyzed; Step 2. Use aerodynamic analysis software or wind tunnel tests to obtain the aerodynamic coefficient of the vehicle under flight conditions; Step 3. Specify each state quantity the initial point; step 4, obtain the nutation angle, precession angular velocity and relative roll angle in the equilibrium state; step 5, judge whether the nutation angle, precession angular velocity and relative roll angle in the equilibrium state obtained in step 4 are feasible , if it is not feasible, then modify the initial value of each state quantity, repeat steps 3 and 4, until the result is feasible; step 6, if it is necessary to calculate the value of the balance point under other flight conditions, then change the flight parameters, repeat steps 1 to 5, If it is no longer necessary to calculate a new state, the method for controlling the balance motion state of the aircraft ends.

Description

technical field [0001] The invention relates to a method for controlling the balanced motion state of an aircraft with a single slider variable center of mass, which can be widely used in the fields of dynamic characteristic analysis of reentry aircraft, single slider variable center of mass control actuator parameter design, and the like. Background technique [0002] Variable center of mass control (Moving mass control, also known as mass moment control in China) is a method to achieve the purpose of control by shifting the center of mass, and a method to affect the control torque acting on the aircraft by changing the force (such as aerodynamic rudder, trimming, etc.) wing, jet thrust), the variable center of mass control is to affect the control torque by changing the way of the moment arm. Shifting the center of mass can be achieved by moving the moving parts inside the aircraft, such as moving the warhead of the warhead. [0003] Variable center of mass control can be...

AI Technical Summary

Problems solved by technology

At present, there is no numerical calculation method for the balance motion state of the aircraft controlled by the variable center of mass of the single slider.

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