CN-122018309-A - Supersonic civil aircraft control method and system based on multicell decomposition and readable storage medium

CN122018309ACN 122018309 ACN122018309 ACN 122018309ACN-122018309-A

Abstract

The invention provides a supersonic civil aircraft control method, a system and a readable storage medium based on multicell decomposition, which can be applied to control law design in the flight process of a large envelope of the supersonic civil aircraft, and comprise the following steps of S1, selecting a scheduling parameter and a variation range in the wide envelope of an aircraft, performing high-density sampling in the envelope according to the scheduling parameter and the variation range to generate a working point set, and acquiring a local linear model set at each working point by adopting a linearization method; S2, performing dimension reduction processing by applying singular value decomposition to the local linear model set, identifying a core parameter subspace and screening a polyhedral vertex linear model forming a convex envelope, S3, adopting a parallel distribution compensation frame to solve and design a local state feedback controller through a linear matrix inequality aiming at each polyhedral vertex linear model, and S4, performing convex combination weighted fusion on the local state feedback controller by utilizing a continuous weight function to generate a global control law and applying the global control law to aircraft full envelope control.

Inventors

ZHANG XIAOYU
LI SIQI
FAN ZHE
LI FEI
Guo jiuyuan

Assignees

中国商用飞机有限责任公司北京民用飞机技术研究中心
中国商用飞机有限责任公司

Dates

Publication Date: 20260512
Application Date: 20251226

Claims (10)

1. The supersonic civil aircraft control method based on multicell decomposition is characterized by comprising the following steps of: s1, selecting a scheduling parameter and a variation range thereof in a wide envelope of an aircraft, performing high-density sampling in the envelope according to the scheduling parameter and the variation range thereof to generate a working point set, and acquiring a local linear model set at each working point by adopting a linearization method; S2, performing dimension reduction processing by applying singular value decomposition to the local linear model set, identifying a core parameter subspace, and screening a polyhedral vertex linear model forming a convex envelope, wherein the polyhedral vertex linear model covers full envelope nonlinear dynamics; S3, solving and designing a local state feedback controller by adopting a parallel distribution compensation frame through a linear matrix inequality aiming at each polyhedral vertex linear model; And S4, performing convex combination weighted fusion on the local state feedback controller by using a continuous weight function to generate a global control law which is applied to the full envelope control of the aircraft.
2. The supersonic civil aircraft control method based on multicellular decomposition of claim 1 wherein in S1: The scheduling parameters comprise Mach numbers, heights and attack angles, and the variation range covers all working conditions in the wide envelope of the aircraft; The high-density sampling adopts a uniform distribution mode to generate a dynamic data set, and the sampling point spacing is set below a preset threshold value; the linearization method is Jacobian linearization, a local linear model near a balance point is obtained for each working point, the local linear model is integrated into a high-dimensional parameter space continuous track, and the high-dimensional parameter space continuous track is compared with a nonlinear dynamic model of an aircraft to verify approximate accuracy.
3. The supersonic civil aircraft control method based on multicellular decomposition of claim 1 wherein in S2: the singular value decomposition decomposes the dominant dynamic direction of the local linear model set, extracts a subspace corresponding to dominant singular values, and the subspace corresponding to dominant singular values is a core parameter subspace; The core parameter subspace is a low-dimensional space after dimension reduction, and a convex hull algorithm is applied to the core parameter subspace to calculate a minimum vertex set; the polyhedron vertex linear model is composed of a linear model corresponding to the minimum vertex set, and the convex hull accurately envelopes the linear models corresponding to all sampling working points.
4. The supersonic civil aircraft control method based on multicellular decomposition of claim 1 wherein in S3: the parallel distribution compensation framework converts the global control problem into independent linear matrix inequality groups of each vertex; the linear matrix inequality is constructed based on a common lyapunov function; And solving and obtaining the feedback gain of each vertex state through the inequality of the linear matrix, wherein the local state feedback controller is applied to a corresponding vertex closed-loop system.
5. The supersonic civil aircraft control method based on multicellular decomposition of claim 1 wherein in S4: the continuous weight function is a polyhedron membership function and is associated with the position of the current working point in the convex envelope; calculating the corresponding weight value of each vertex aiming at the current working point; And carrying out weighted summation on the local state feedback controller according to the weight value.
6. The supersonic civil aircraft control method based on multicellular decomposition of claim 2 wherein in S1 the dynamic data set contains aircraft states and parameters at all sampling working points, the preset threshold is determined according to nonlinear dynamics of the aircraft.
7. The supersonic civil aircraft control method based on multi-cell decomposition according to claim 3, wherein in the step S2, the convex hull algorithm traverses a sampling point set after dimension reduction, and the minimum top point set corresponds to an original working point for forming a convex hull network boundary point.
8. The supersonic civil aircraft control method based on multicell decomposition according to claim 5, wherein in the step S4, the weighted sum generates a global control gain corresponding to a current working point, and the global control law is obtained by multiplying the global control gain by an aircraft state.
9. A supersonic civil aircraft control system based on multicell decomposition for implementing the supersonic civil aircraft control method based on multicell decomposition according to any one of the preceding claims 1-8, characterized in that the supersonic civil aircraft control method based on multicell decomposition comprises the following steps: The point set model acquisition module is used for selecting scheduling parameters and the variation range of the scheduling parameters in the wide envelope of the aircraft, performing high-density sampling in the envelope according to the scheduling parameters and the variation range of the scheduling parameters to generate a working point set, and acquiring a local linear model set at each working point by adopting a linearization method; The dimension reduction processing module is used for carrying out dimension reduction processing by applying singular value decomposition to the local linear model set, identifying a core parameter subspace and screening a polyhedral vertex linear model forming a convex envelope, wherein the polyhedral vertex linear model covers the full envelope nonlinear dynamics; The feedback control module is used for solving and designing a local state feedback controller by adopting a parallel distribution compensation frame through a linear matrix inequality aiming at each polyhedral vertex linear model; And the weighted fusion module is used for carrying out convex combination weighted fusion on the local state feedback controller by utilizing a continuous weight function, and generating a global control law to be applied to the full envelope control of the aircraft.
10. A computer-readable storage medium, characterized in that the computer-readable storage medium has stored thereon a computer program which, when executed by a processor, implements the steps of the supersonic civil aircraft control method based on multicellular decomposition according to any one of claims 1-8.

Description

Supersonic civil aircraft control method and system based on multicell decomposition and readable storage medium Technical Field The invention relates to the technical field of supersonic civil aircraft control, in particular to a supersonic civil aircraft control method and system based on multicellular decomposition and a readable storage medium. Background At present, two architectures of linear control and nonlinear control mainly exist for civil aircraft control. The linear control method is studied earlier and has entered a relatively mature stage, and is also relatively widely used in engineering. The PID, gain scheduling, linear quadratic optimal control, pole allocation and tangent linearization methods all achieve good control effects on the control research of the aircraft. The control method of dynamic inverse, feedback linearization, sliding mode and back-stepping is widely studied in recent years. However, the conventional linear control method cannot adapt to large-scale parameter perturbation and has to perform gain scheduling according to different parameters, while the conventional nonlinear control method strongly depends on an object model and has to have large nonlinear gain for large interference and uncertainty items, which can cause buffeting phenomenon of a control system. Therefore, how to design a control method which has lower model dependence and is suitable for large-scale parameter perturbation in the large envelope flight process becomes a research hot spot for controlling supersonic civil aircraft. In CN120370812A, a balance point is selected, a nonlinear model of the unmanned aerial vehicle is converted into a linear variable parameter (LPV) model through a Jacobian linearization method, a controller of which the parameter depends on state feedback is designed aiming at the LPV model, a Lyapunov function suitable for a system is constructed, a group of Linear Matrix Inequality (LMI) conditions are deduced, control gains corresponding to the LMI conditions are obtained, gain scheduling is carried out according to the parameters, and a gain scheduling controller of the system stability conditions is met. The control strategy has significant limitations in handling strong nonlinear systems such as supersonic civil aircraft. Firstly, the selection of the balance point is highly dependent on experience and intuition of a designer, and lacks systematic guiding principles, so that the process has subjective randomness, and the completeness and representativeness of the selected point are difficult to ensure. Secondly, local controllers designed based on these discrete balance points commonly employ simple linear interpolation methods when expanding to full flight envelope. However, this interpolation strategy lacks a strict mathematical basis, cannot guarantee closed-loop system stability and dynamic performance at non-design points within the envelope, and presents a risk of control failure. Accordingly, there is a need to develop a method, system, and readable storage medium for controlling a supersonic civil aircraft based on multicellular decomposition that addresses the deficiencies of the prior art to solve or mitigate one or more of the problems described above. Disclosure of Invention In view of the above, the invention provides a supersonic civil aircraft control method and system based on multicellular decomposition and a readable storage medium, which can be applied to control law design in the flight process of a large envelope of the supersonic civil aircraft. In one aspect, the invention provides a supersonic civil aircraft control method based on multicellular decomposition, which comprises the following steps: s1, selecting a scheduling parameter and a variation range thereof in a wide envelope of an aircraft, performing high-density sampling in the envelope according to the scheduling parameter and the variation range thereof to generate a working point set, and acquiring a local linear model set at each working point by adopting a linearization method; S2, performing dimension reduction processing by applying singular value decomposition to the local linear model set, identifying a core parameter subspace, and screening a polyhedral vertex linear model forming a convex envelope, wherein the polyhedral vertex linear model covers full envelope nonlinear dynamics; S3, solving and designing a local state feedback controller by adopting a parallel distribution compensation frame through a linear matrix inequality aiming at each polyhedral vertex linear model; And S4, performing convex combination weighted fusion on the local state feedback controller by using a continuous weight function to generate a global control law which is applied to the full envelope control of the aircraft. Aspects and any one of the possible implementations as described above, further provide an implementation, where in S1: The scheduling parameters comprise Mach numbers, heights and attack a