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Reentry flying attitude control method based on exponential time-varying second order sliding mode

A second-order sliding mode, flight attitude technology, applied in the field of aircraft control, can solve problems such as interference and parameter uncertainty

Inactive Publication Date: 2013-02-13
BEIJING INSTITUTE OF TECHNOLOGYGY
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Problems solved by technology

[0005] The purpose of the present invention is to solve the re-entry aircraft buffeting problem with parameter uncertainty and external interference, and propose a re-entry aircraft attitude control method based on exponential time-varying second-order sliding mode

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  • Reentry flying attitude control method based on exponential time-varying second order sliding mode

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Embodiment Construction

[0091] In order to better illustrate the objectives and advantages of the present invention, further descriptions are given below with reference to the drawings and embodiments.

[0092] After the feedback linearization of the reentry aircraft attitude control system, the system is decoupled into three independent subsystems, as shown in equation (5). Design controllers for α, β and μ subsystems respectively. Taking the α subsystem as an example, the global robustness and error convergence characteristics of the attitude control method of the present invention are analyzed below.

[0093] The design of the sliding mode surface is shown in equation (6), if the control law is:

[0094] v 1 = U eq1 +u sw1

[0095] u eq 1 = α · · c ( t ) - λ α ~ · ( t ) + λ c 1 e - λt

[0096] u sw1 =-k 2 ∫sign[J(t)]

[0097] Where parameter k 2 Satisfy: k 2 > k 3 | σ · ( t ) | + Γ 1 ...

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Abstract

The invention relates to a reentry stage aircraft attitude control method based on an exponential time-varying second order sliding mode, belonging to the technical field of aircraft control. According to the reentry stage aircraft attitude control method, a plane symmetric unpowered aircraft model is taken as an object, feedback linearization is carried out on an affine nonlinear system of an aircraft, and the attitude control problem of the aircraft when reentering into the atmospheric layer is studied. The aircraft provides operating force and operating torque only through a pneumatic control surface. A control surface deflection angle signal [delta e delta a delta r]T is given through the designed control law, so that an attitude instruction omega c=[alpha c beta c mu c]T given by a guidance loop can be effectively tracked, the attitude angle tracking error can be guaranteed to be asymptotically converged, and strong robustness is generated for tremendous environment change, uncertain pneumatic parameters and external disturbance and the like in the reentry process. Meanwhile, the control law in the method only has integral of a switching function, so that the reaching stage of a sliding mode surface is eliminated, the control quantity is enabled to be a continuous signal, the buffeting phenomenon is effectively reduced, and good control accuracy is achieved.

Description

Technical field [0001] The invention relates to an aircraft reentry section attitude control method based on an exponential time-varying second-order sliding mode, and belongs to the technical field of aircraft control. Background technique [0002] During the unpowered high-speed reentry flight of the aircraft, the Mach number and altitude change drastically, the flight environment is complex and changeable, the high and low aerodynamic characteristics are hugely different, and the coupling between channels is very serious, showing strong multivariable coupling and nonlinearity. Moreover, during the flight, it is often subject to various disturbances and uncertainties that cannot be fully predicted in advance. Therefore, the channel nonlinear decoupling method and nonlinear robust control method are the key to the design of the reentry aircraft attitude control system. [0003] Sliding mode control is an effective method to achieve system robust control. It has good robustness to...

Claims

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Application Information

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IPC IPC(8): G05B13/04G05D1/08
Inventor 盛永智耿洁刘向东陈振
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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