A Fast and High-precision Aircraft Guidance Method Based on Uncertain Aerodynamic Parameters

Abstract

The invention relates to a quick high-precision guidance method of an aircraft based on uncertainty of aerodynamic parameters. The quick high-precision guidance method comprises the following steps of1, establishing an equivalent disturbance dynamics model of the aircraft containing the uncertainty of aerodynamic parameters; 2, according to the dynamics model in step 1, designing a sliding mode disturbance observer to quickly estimate the uncertainty of aerodynamic parameters of the aircraft, so as to obtain the estimated value of the disturbance; 3, designing a sliding mode control rule to complete the task quick control requirement; 4, utilizing the estimated value of the disturbance in step 2 and the sliding mode control rule in step 3 to design a composite sliding mode controller, soas to complete the quick high-precision guidance method of the aircraft. The quick high-precision guidance method has the advantages that by combining the sliding mode disturbance observer and the sliding mode controller, the characteristics of rapidity and high precision are realized; the quick high-precision guidance method is suitable for quick high-precision guidance systems of multiple typesof flight systems and other high-altitude unmanned aerial vehicles, and can solve the aircraft fault problems of quick fault tolerance and the like.

Description

technical field [0001] The invention relates to a rapid and high-precision guidance method for aircraft based on uncertain aerodynamic parameters, which can solve the problem of rapid and high-precision guidance of aircraft with uncertain aerodynamic parameters. Background technique [0002] With the development of aircraft technology, many types of aircraft have become popular research objects recently, such as unmanned aerial vehicles, hypersonic aircraft and missiles, etc. These objects have the advantages of rapidity, long range, and high precision. [0003] The above-mentioned aircraft has become the main killer feature of various countries, which can achieve fast and precise strikes on targets. In this process, guidance is a key technology that needs to meet the requirements of speed and precision. The Minuteman No. 3 intercontinental missile in service in the United States in 1970 has a range of up to 12,500km, and the final strike error is only about 200m. China’s DF...

AI Technical Summary

Problems solved by technology

Although the above two methods use sliding mode control to enable the system to converge within a limited time, they do not consider the environmental disturbance in the system and cannot meet the precise control requirements in the presence of disturbance.

The following patents have made some progress in anti-jamming, but there are still many problems. The patent application number is 201210258036.0, which proposes a fine anti-jamming tracking controller for flexible hypersonic vehicles, but the model used in this method is a longitudinal two-dimensional model. Moreover, the interference observer used does not have limited time convergence ability, and cannot quickly estimate and compensate related interference

Patent application number 201610306205.1 proposes an anti-jamming composite online guidance method for the Mars lander's atmospheric entry section, but the observer used in this method also does not have limited time convergence capabilities and cannot meet the needs of rapid guidance

In addition, there are deficiencies in some papers: the article "A Fault-Tolerant Control Strategy Design for Hypersonic Vehicle Based on Time-Varying Disturbance Observer" designed a composite fault-tolerant reentry control method based on an adaptive disturbance observer and a backstepping sliding mode controller , although the article uses a sliding mode controller to ensure that the system converges in a finite time, but the adaptive observer cannot meet the needs of quickly estimating the disturbance

To sum up, the existing methods lack the ability to satisfy both fast and high-precision control and fast disturbance estimation and compensation in the case of interference, and it is urgent to overcome the fast and high-precision guidance method of aircraft based on uncertain aerodynamic parameters.

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