Aircraft full-section control method based on anti-interference technology

Abstract

The invention relates to an aircraft full-section control method based on the anti-interference technology. For an aircraft full-section control problem under unknown nonlinear dynamics, aerodynamic parameter uncertainty and external disturbance, the method comprises a step of establishing an aircraft six-degree-freedom model containing the above multi-source interference, converting an attitude dynamics model into an integral series type by linear state transformation and calling the uncertainty, the external disturbance and the unknown nonlinear dynamics as total disturbance, and representing with an expansion state, a step of designing an extended state observer to quickly estimate the aircraft total disturbance to obtain an interference estimation value, a step of designing an aircraftattitude controller based on active disturbance rejection control, and a step of designing attitude command correction based on a centroid motion state to complete the aircraft full-section control method based on the active disturbance rejection control. The invention realizes the full-section control of a level flight section and a going down section of an unpowered reentry vehicle, and the method has the characteristics of high robustness and easy engineering realization and is suitable for various types of flight systems requiring unpowered reentry.

Description

technical field [0001] The invention relates to an aircraft full-profile control method based on anti-jamming technology, which solves the full-profile control problem of an unpowered reentry aircraft in the level flight section and the down pressure section with unknown nonlinear dynamics, uncertain aerodynamic parameters and external interference. Background technique [0002] Near-space reentry vehicles, such as hypersonic vehicles and some missiles, are obviously different from traditional aerospace vehicles in terms of flight space, aerodynamic shape, and dynamic characteristics, showing strong uncertainty, strong interference, strong coupling, and strong Linear, fast time-varying, multi-constraint and other characteristics. For example, there is a strong nonlinear coupling between the flight channels of a hypersonic vehicle, and the induced torque caused by the coupling sometimes even exceeds the control torque of the channel control surface itself. Its flight range i...

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Problems solved by technology

[0005] The technical problem solved by the present invention is: aiming at the full profile control problem of the unpowered re-entry vehicle level flight section and the down pressure section with unknown nonlinear dynamics, uncertain aerodynamic parameters and external interference, it overcomes the deficiencies of the prior art and provides a A ful

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