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Dynamic stability judgment method of single-slider variable-mass-center control aircraft

A technology of dynamic stability and judgment method, applied in attitude control, adaptive control, general control system, etc.

Inactive Publication Date: 2014-11-26
BEIJING INSTITUTE OF TECHNOLOGYGY
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At present, there is no public information to study the dynamic stability determination method of this type of aircraft

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  • Dynamic stability judgment method of single-slider variable-mass-center control aircraft
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  • Dynamic stability judgment method of single-slider variable-mass-center control aircraft

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Embodiment Construction

[0020] The stability judging method proposed by the invention is suitable for judging the stability of an aircraft controlled by a single slider with variable center of mass. By calculating the maximum stable offset distance and comparing the relationship between the current offset distance of the slider and the maximum stable offset distance, the stability of the system can be judged.

[0021] The following takes a reentry vehicle model as an example to illustrate the specific calculation steps.

[0022] 1) Obtain the projectile structure parameters and flight condition parameters of the reentry vehicle to be analyzed;

[0023] m 1 =40kg, m 2 =1kg,J x =2kg·m 2 , J y =20kg·m 2 , J z =19.5kg·m 2 ,

[0024] S=0.1m 2 , L=1.25m.

[0025] 2) According to the definition of aerodynamic parameters, the dynamic pressure of the aircraft and the values ​​of each aerodynamic coefficient are given

[0026] q=1×10 6 kg m / s 2 , c x =0.12, c y0 =-0.05,

[0027] m z0 =0.01,...

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Abstract

The invention provides a dynamic stability judgment method of a single-slider variable-mass-center control aircraft. Dynamic stability of a system under different slider offset distances can be judged. The method includes the steps that first, projectile body parameters and flight condition parameters of a reentry vehicle to be analyzed are obtained; second, the aerodynamic coefficient of the aircraft under the flight condition is obtained through aerodynamic analysis software or a wind tunnel test; third, the maximum stable offset distance zm is calculated according to the obtained parameters and the aerodynamic coefficient; fourth, whether the slider offset distance is smaller than the maximum stable offset distance obtained in the third step obtained in the third step or not is judged, if the slider offset distance meets the formula that |z|< zm, the system is stable in terms of attitude dynamics, and nutation movement of the aircraft can converge to a balance point; if |z|>= zm, the system is unstable in terms of attitude dynamics, and at the moment, the nutation angle of the aircraft tends to diverge along with time.

Description

technical field [0001] The invention relates to a dynamic stability determination method of a single-slider variable center of mass control aircraft, 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, controller 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 contro...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B13/04G05D1/08
Inventor 于剑桥王亚飞王林林沈元川艾晓琳蒋虎超
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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