Hypersonic speed aircraft control method capable of suppressing constant deviation influence of sideslip angle signal

Abstract

The invention discloses a hypersonic speed aircraft control method capable of suppressing the constant deviation influence of a sideslip angle signal. The method comprises the following steps: (1) measuring the yaw angle speed omega y and the roll angle speed omega x of an aircraft in real time by utilizing an inertial measurement unit, and acquiring a roll angle gamma and a sideslip angle by utilizing the inertial measurement unit and a sensor; (2) calculating a deviation signal of the gamma and a roll angle instruction gamma c, integrating a deviation signal Delta gamma, and performing the amplitude limiting on the deviation signal, so as to obtain a roll angle integrated signal; (3) amplifying the roll angle integrated signal and the omega y, generating a control instruction, and feeding the control instruction back to a rudder of the aircraft; amplifying the omega x, generating a control instruction I and feeding the control instruction I back to an aileron of the aircraft; amplifying the Delta gamma, generating a control instruction II and feeding the control instruction II back to the rudder / aileron of the aircraft; (4) adding all the control instructions which are fed back to the rudder to serve as a general control instruction of the rudder, and controlling the rudder to track the general control instruction through a servo system on the aircraft; adding all the control instructions I fed back to the aileron to serve as a general control instruction I of the aileron, and controlling the aileron to track the general control instruction through the servo system on the aircraft.

Description

technical field [0001] The invention belongs to the technical field of hypersonic vehicle attitude control. Background technique [0002] Advanced hypersonic vehicles are increasingly becoming military or civilian high-performance aircraft that the world's aerospace powers are vying to develop. From the 1950s and 1960s to the present, the continuous flight out of control in the development of advanced plane-symmetric hypersonic vehicles in the United States shows that the attitude control technology of hypersonic vehicles is still not fully mature. Due to problems such as heat protection, the aircraft cannot use the air data system during the hypersonic flight phase, so it cannot directly measure the angle information required for attitude control such as sideslip angle and angle of attack. This part of the angle information can only be calculated by estimation. However, under the influence of slowly changing wind disturbances, there is a constant or approximately constant ...

AI Technical Summary

Problems solved by technology

In the case that there is a constant value deviation in the sideslip angle feedback signal, most of the current methods can only achieve a certain steady-state error in the real sideslip angle control result and cannot completely eliminate it, except for one type of method, namely: The roll angle is fed back to the rudder, not to the ailerons

However, on the one hand, this method is only suitable for the case where the polarity of the rudder control roll is determined and the rudder effect is high enough; error

In summary, in the case of a constant value deviation in the sideslip angle feedback signal, the current lateral heading control methods for hypersonic vehicles cannot simultaneously ensure that the true sideslip angle steady-state error and roll angle steady-state error are zero at the same time.

For example: (1) "Lateral and Lateral Control System of Reusable Vehicle Return Section" published in "Journal of Nanjing University of Aeronautics and Astronautics", Volume 41, Issue 3, this document feeds the roll angular velocity to the aileron, yaw angular velocity and The roll angle is fed back to the rudder to control the lateral heading attitude of the vehicle repeatedly, but the sideslip angle feedback is not used, so it is only applicable to the yaw statically stable aircraft, and the literature does not use the feedback of the roll angle integral to the rudder

(2) Section 5.4.3 of "Flight Control System" (Wu Sentang, Fei Yuhua. Beijing University of Aeronautics and Astronautics Press. First Edition, 2009) uses the feedback from the roll angle integral to the aileron, but for the use of The sideslip angle is integrated to the feedback of the rudder. In the case of a constant deviation in the sideslip feedback signal, this method cannot eliminate the sideslip angle error

(4) "Research on Lateral Attitude Control Technology Against Uncertain Interference" in "Journal of System Simulation" No. 2, 2010, the roll angle, roll angle integral and roll angular velocity are fed back to the aileron to realize the UAV Lateral heading control, the yaw channel is not controlled, so it is only suitable for aircraft with static stability of yaw and good damping of yaw channel itself, not suitable for hypersonic aircraft with static instability of yaw

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