A Reconstruction Method of Aircraft Angular Rate Signal Based on Unscented Kalman Filter

Abstract

The invention discloses an airplane angular rate signal reconstruction method based on unscented kalman filter. The method comprises the following steps of: (1), denoising an attitude angle measurement signal containing measurement noise through a nonlinear tracking differentiator to obtain a differential signal of an attitude angle, and constructing a virtual measurement equation; (2), constructing a state equation of a system on the basis of natural characteristics of an airplane and according to tri-axial angular rate signals and torque characteristics of the airplane; and (3), reconstructing an angular rate signal of the system by selecting the unscented kalman filter technology as the processing manner because both the state equation and the measurement equation are nonlinear and the estimation precision can be influenced by traditional operation for linearizing a nonlinear equation.

Description

Technical field [0001] The invention belongs to the field of aviation technology, and relates to an aircraft angular rate signal reconstruction method based on unscented Kalman filtering. Background technique [0002] After successfully breaking through the sound barrier, the flight envelope of the aircraft has gradually expanded, and the stability of the aircraft itself has gradually deteriorated; and as the flight altitude increases, the damping torque of the aircraft itself has gradually decreased, making it difficult to control the aircraft. The angular rate feedback of the aircraft is the key feedback signal to increase the system damping, which directly affects the stability of the aircraft. Therefore, the research on fault diagnosis and signal reconstruction of angular rate sensor becomes more and more important. The sensors of modern aircraft generally use redundancy technology to improve reliability. The so-called redundancy technology is to introduce multiple systems t...

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Problems solved by technology

[0003] In the prior art, the dimensionality reduction observer is used to reconstruct the pitch rate signal, but the research object is a linear aircraft model, so it cannot be directly applied to nonlinear aircraft

Some use the extended backpropagation neural network method to reconstruct the pitch rate signal, which needs to use the current angle of attack, elevator deflection angle, pitch angle, normal overload and the historical information of the previous 4 cycles of these signals. This method is complicated to operate. , not suitable for engineering applications

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