Near space vehicle robust control method with input saturation

A near-space vehicle, robust control technology, applied in the field of flight control, can solve problems such as system buffeting

Active Publication Date: 2013-12-04
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

However, in the process of system control, the control quantity needs to be continuously changed in a jumping manner according to the current state of the system, causing the actual trajectory of the system to cross back and forth on both sides of the sliding mode, resulting in system chattering problems

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  • Near space vehicle robust control method with input saturation
  • Near space vehicle robust control method with input saturation
  • Near space vehicle robust control method with input saturation

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Embodiment Construction

[0065] Such asfigure 1 As shown, the present invention has a robust control method for near-space aircraft with input saturation. According to the principle of singular perturbation and time-scale separation, the attitude loop of the aircraft is divided into a slow loop and a fast loop. The method is based on the control system of the slow loop , a fast loop control system and a closed-loop control system composed of an aircraft to realize, it is characterized in that, comprising the following steps:

[0066] (1) Transform the slow loop control system and the fast loop control system into an affine nonlinear system equation form, as follows:

[0067] A. The affine nonlinear system equation of the slow loop is:

[0068] In the formula, Ω=[α,β,μ] T is the current attitude angle signal, α, β and μ represent the angle of attack, sideslip angle and roll angle respectively, Indicates the derivative of Ω; f s (Ω)=[f s1 ,f s2 ,f s3 ] T , ω c is the control law of the slow l...

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Abstract

The invention discloses a near space vehicle robust control method with input saturation. According to the control method, controllers are designed for a slow loop and a fast loop in a near space vehicle attitude motion system respectively; for a slow loop system, compound disturbance in a self-adaptive processing system is adopted to design the controller based on a dynamic sliding mode method, and further the problem of buffeting of the controller is solved; for a fast loop system, considering that order of magnitude of external disturbance is far higher that that of uncertain items of the system, the compound disturbance is processed by the aid of a nonlinear disturbance observer technique, the controller is designed based on a normal sliding mode method of a double-power reaching law, meanwhile a compensator is constructed by the aid of radial basis function neural networks to perform saturation compensation on the designed controller, and further the problem of limitation to saturation of a control plane of a near space vehicle is solved.

Description

technical field [0001] The invention belongs to the technical field of flight control, in particular, it relates to a robust control method for near-space aircraft with input saturation. Background technique [0002] Near space vehicle (Near Space Vehicle, NSV) refers to the aircraft operating in the range of near space (usually refers to the airspace 20-100 kilometers above the ground). The airspace below the near space is the traditional aircraft operating space. The airspace of is the spacecraft operating space. In view of the unique geographical location and potential value of the near-space region, the research of NSV has received extensive attention from all over the world. Since NSV has a wide flight range and is easily affected by severe external disturbances, it is necessary to design a robust flight controller for it. At the same time, the deflection angle of the NSV rudder surface cannot be increased infinitely, that is, the rudder surface has a saturation limit...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/08G05B13/02
Inventor 陈谋周砚龙吴庆宪姜长生
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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