A Control Parameter Adjustment Method Adapting to Discrete Characteristics of Aircraft Thrust

A technology of control parameters and adjustment methods, applied in the field of tactical weapon flight control, can solve problems such as poor adaptability of thrust discrete characteristics, strong discreteness, and affect the quality of flight control, achieving the effect of clear physical concepts and improved stability

Active Publication Date: 2021-04-23
SHANGHAI AEROSPACE CONTROL TECH INST
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

Under different temperature conditions, the above parameters have a strong discreteness with time, so the method of adjusting the control parameters according to the time variable has poor adaptability to the discrete characteristics of the thrust caused by the ambient temperature, which affects the control quality of the entire flight phase.

Method used

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  • A Control Parameter Adjustment Method Adapting to Discrete Characteristics of Aircraft Thrust
  • A Control Parameter Adjustment Method Adapting to Discrete Characteristics of Aircraft Thrust
  • A Control Parameter Adjustment Method Adapting to Discrete Characteristics of Aircraft Thrust

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Embodiment Construction

[0016] Hereinafter, the present invention will be further described in conjunction with the drawings and embodiments.

[0017] Obtain the thrust curves in three states within the temperature envelope of engine operation, which are normal temperature operating state, high temperature upper limit operating state and low temperature lower limit operating state.

[0018] According to the designed guidance law, the theoretical trajectories under the three engine working conditions are calculated respectively, which are marked as normal temperature trajectories, high temperature trajectories and low temperature trajectories. Each calculated trajectory data should reflect flight altitude, Mach number, angle of attack, Changes in dynamic pressure, mass, moment of inertia and other data during flight.

[0019] Comparing the corresponding relationship between mass and Mach number in the three groups of ballistics at normal temperature, high temperature and low temperature, if the disper...

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Abstract

The invention discloses a control parameter adjustment method adapting to the discrete characteristics of aircraft thrust, comprising: determining the Mach number as the basic variable for parameter adjustment; selecting the Mach number as the basis for adjusting the control parameters; selecting corresponding feature points according to the Mach number, combining The basic aerodynamic characteristics of the aircraft, design the control parameters, fit the change law of the Mach number and the control parameters, and obtain the calculation formula of the control parameters changing with the Mach number; analyze the corresponding relationship between the dynamic coefficient and the dynamic pressure of the aircraft, and further Fitting the change law of dynamic pressure and control parameters in the envelope, and obtaining the calculation formula with the change of dynamic pressure and Mach number; considering the change law of elastic modal frequency with time under typical temperature, select the lowest modal frequency state as the design state Filter design, the center frequency of the filter changes continuously with time, and keeps consistent with the changing law of the elastic mode, which improves the stability of the system in different flight states and the ability to suppress high-frequency vibrations.

Description

technical field [0001] The invention relates to the field of flight control of tactical weapons, in particular to a parameter adjustment method of a booster aircraft stability control system using a solid rocket motor, so as to improve the aircraft's adaptability to thrust discrete characteristics and flight control quality. Background technique [0002] The thrust of the aircraft comes from the combustion of fuel in the engine, and the external ambient temperature has an impact on the speed of fuel combustion. In addition to the difference in speed, it also leads to obvious differences in the changes in overall parameters such as the mass, center of mass, and moment of inertia of the aircraft under high and low temperature conditions. Under different temperature conditions, the above parameters have strong discreteness with time. Therefore, the method of adjusting control parameters according to time variables has poor adaptability to the discrete characteristics of thrust c...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05B13/04
CPCG05B13/042
Inventor 冯昊陈光山奚勇夏斌廖幻年沈红祥马学铭
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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