Method for calculating single-sliding-block moving mass controlled aircraft balance motion state

Abstract

The invention provides a method for calculating the single-sliding-block moving mass controlled aircraft balance motion state. Angles of nutation, angular velocities of precession and relative roll angles of the aircraft balance motion states on different conditions can be calculated. The method comprises the steps that firstly, to-be-analyzed elastic structure parameters and to-be-analyzed flight condition parameters which are loaded into the aircraft are obtained; secondly, air dynamic coefficients of the aircraft on the flight conditions are obtained by means of aerodynamic analysis software or a wind tunnel test; thirdly, initial points of all state quantities are assigned; fourthly, the angle of nutation, the angular velocity of precession and the relative roll angle of the aircraft balance motion state are obtained; fifthly, whether the obtained angle of nutation, angular velocity of precession and relative roll angle of the aircraft balance motion state are feasible or not is judged; if not, the initial values of all the state quantities are amended, and the third step and the fourth step are repeatedly executed again until the result shows that the obtained angle of nutation, angular velocity of precession and relative roll angle of the aircraft balance motion state are feasible; sixthly, if balance point values on other flight conditions need to be calculated, flight parameters are changed, and the first step, the second step, the third step, the fourth step and the fifth step are executed again; if no new state needs to be calculated, implementation of the method for calculating the single-sliding-block moving mass controlled aircraft balance motion state is finished.

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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