Aircraft anti-repeated-oscillation method

Abstract

The invention discloses an aircraft anti-repeated-oscillation method. The method comprises the following steps: detecting the load weight of the aircraft, calculating to obtain a standard acceleratorthreshold value of each blade, placing the aircraft at a specified position, starting the blades to enable accelerators of the blades to gradually reach the standard accelerator threshold values of the blades, reducing the sensitivity of a gyroscope and the accelerator threshold values when the blades incline, and adjusting the accelerator threshold values of the blades according to the inclination direction to balance the accelerator threshold values. According to the aircraft anti-repeated-oscillation method, a gravity sensor is arranged at the bottom end of the aircraft, so the weight of the load-bearing object of the aircraft can be detected; the required minimum lifting force is calculated, so that the basic balance of the aircraft can be kept when the aircraft is not controlled; thesensitivity of the gyroscope is reduced, the high-frequency blade threshold value adjustment of the gyroscope can be avoided, and the repeated oscillation condition is adjusted; and in addition, the balance of the aircraft can be adjusted more stably in cooperation with the standard accelerator threshold value.

Description

technical field [0001] The invention relates to the technical field of aircraft control, in particular to a method for preventing repeated vibrations of an aircraft. Background technique [0002] The transfer function of the automatic control theory is based on the linear time-invariant system, which studies the response of the linear and time-invariant system to any input signal. Although the PID algorithm is a reliable and effective control algorithm, but For multi-rotor unmanned aerial vehicles, due to the complexity of its dynamic model, the uncertainty of model parameters and the inaccuracy of modeling, although the parameters have been adjusted repeatedly, a relatively satisfactory flight effect has been obtained in the laboratory. , but due to its mold, material, structure, outdoor weather and other factors, it is still difficult to obtain a satisfactory control attitude effect. Therefore, we propose a method for preventing repeated vibrations of the aircraft. Conte...

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Problems solved by technology

[0002] The transfer function of the automatic control theory is based on the linear time-invariant system, which studies the response of the linear and time-invariant system to any input signal. Although the PID algorithm is a reliable and effective control algorithm, but For multi-rotor unmanned aerial vehicles, due to the complexity of its dynamic model, the uncertainty of model parameters and the inaccuracy of modeling, although the parameters have been adjusted repeatedly, a relatively satisfactory flight effect has been obtained in the laboratory. , but due to its mold, material, structure, outdoor weather and other factors, it is still difficult to obtain a satisfactory control attitude effect. Therefore, we propose a method for preventing repeated vibrations of aircraft

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