Coupling utilization coordination control method suitable for transversal and lateral maneuvering of aircraft
A coordinated control, horizontal and lateral technology, applied in the direction of adaptive control, general control system, control/regulation system, etc., can solve the problems of lack of optimality of effect, failure to actively use coupling characteristics, etc., to simplify design and iteration process, improve control quality, and simplify the effect of the solution process
Active Publication Date: 2017-02-15
BEIHANG UNIV
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Literature [3] designed a nonlinear generalized predictive control law to achieve the goal of coordinated control for the serious coupling problem between the attitude and motion of near-space vehicles. Active use of coupling characteristics, the effect of control often lacks the optimality under a given index
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[0035] The present invention will be further described in detail with reference to the accompanying drawings and embodiments.
[0036] The invention is a coupling utilization coordination control method suitable for lateral maneuvering of an aircraft. By actively utilizing the aerodynamic coupling characteristics of the aircraft, a sideslip angle command distributor suitable for lateral maneuvering is designed to realize the coordination between lateral passages. Coordinated control to improve the limitation of insufficient maneuverability due to the saturation of actuators during rapid maneuvering is of great significance for solving problems such as hypersonic or conventional aircraft's wide-range lateral optimal maneuvering flight and control quality improvement.
[0037]The main steps include: first, on the basis of the designed full-channel high-disturbance attitude controller, with the minimum aileron loss as the optimization index, the coupling utilization problem is tra...
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The invention discloses a coupling utilization coordination control method suitable for transversal and lateral maneuvering of an aircraft. The method comprises the following steps: 1, by taking minimization of aileron loss as an optimization index, converting a coupling utilization problem into a univariant online searching optimization problem, and establishing a concrete mathematic description of the optimization problem; 2, by means of the unique advantage of a nonlinear tracking differentiator in independence from an object analysis formula in the aspect of nonlinear searching optimization, constructing adaptive sideslip angle instruction distributor based on online searching optimization and iteration of the nonlinear tracking differentiator; and 3, according to a change scope allowed by a sideslip angle instruction, performing amplitude-limiting processing on the sideslip angle instruction, sending the sideslip angle instruction to a designed all-channel high-noise immunity attitude controller to obtain control energy, and returning to the second step so as to implement closed-loop high-precision tracking control. According to the invention, under the condition of limited control, optimal maneuvering flight under given index significance is realized, and under the condition that closed-loop control performance and robustness are not satisfied, the control quality of the transversal and lateral maneuvering is improved.
Description
technical field [0001] The invention relates to a coupling utilization coordinated control method suitable for aircraft lateral maneuvering, which is mainly used to solve problems such as hypersonic or conventional aircraft large-scale lateral lateral optimal maneuvering flight and control quality improvement. Background technique [0002] There are strong aerodynamic coupling, control coupling and inertial coupling among the longitudinal, lateral and lateral channels of advanced aircraft such as hypersonic aircraft and super maneuverable fighter jets. And significantly enhanced. Large-scale maneuvering flight is the most serious stage of coupling between channels of this type of aircraft, which brings great challenges to the design of the control system. This kind of coupling is inevitable for aircraft, and it has advantages and disadvantages. It is unrealistic to try to completely decouple it. On the basis of analyzing the essential characteristics of this coupling, it i...
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IPC IPC(8): G05B13/04
CPCG05B13/042
Inventor 王宏伦邵星灵刘畅黄宇
Owner BEIHANG UNIV