Multichannel attitude controller of aircraft

Abstract

The present invention discloses a multichannel attitude controller of an aircraft. The controller comprises an execution mechanism and an inertia platform, and also comprises a calculating unit used for calculating the current angular velocities and the current air-flow angles of the three channels of rolling, yaw and pitching of the aircraft according to the measurement information of the inertia platform, and then feeding back and outputting. An external loop control unit is used to calculate the angular velocity adjustment values of the three channels according to the current air-flow angles and the received air-flow angle control values of the three channels. For the yaw (pitching) channel, the angular velocity adjustment value is added with a yaw (pitching) angular velocity caused by a parallel branch to obtain an angular velocity control value, and the angular velocity adjustment value of the rolling channel is used as the angular velocity control value of the rolling channel. An internal loop control unit is used to generate a control plane deflection instruction to output to the execution mechanism according to the current angular velocities and the current angular velocity control values of the three channels. The multichannel attitude controller of the aircraft of the present invention obtain a stronger channel decoupling effect by compensating the angular velocity control values of the three channels.

Description

technical field [0001] The invention relates to the field of aerospace, in particular to a multi-channel attitude controller of an aircraft. Background technique [0002] An aircraft usually has its internal attitude controller to control its flight attitude, such as pitch angle, yaw angle and roll angle. [0003] The phenomenon of motion coupling usually exists during the flight of the aircraft. For example, the yaw of the aircraft will cause its roll, and the roll of the aircraft will also cause its yaw; when the aircraft changes its flight attitude, the change of the flight attitude is nonlinear and uncertain. The unique characteristics greatly increase the difficulty of controlling the flight attitude of the aircraft. [0004] When the flight attitude of the aircraft changes slowly and with a small magnitude (for example, a civil airliner adjusts its course), the influence of kinematic coupling on the flight attitude of the aircraft can be regarded as a random small dis...

AI Technical Summary

Problems solved by technology

However, when the aircraft is at a large elevation angle, when the angular velocity of the pitch channel, yaw channel or roll channel is changed, there will be serious kinematic coupling among the three channels, and the change of the angular velocity of the three channels is obviously nonlinear

However, the existing three single-channel attitude controllers still independently and linearly control the angular velocity of the three channels, resulting in a mismatch between the control and the actual flight attitude of the aircraft, which can easily lead to unstable flight or out-of-control crashes of the aircraft.

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