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基于输出反馈的飞控系数重构控制 总被引:1,自引:0,他引:1
针对一类线性控制系统,运用基于输出反馈的特征结构配置方法,提出了一种稳定而有效的控制系统重构方法,根据输出反馈特征值配置原理,给出了原不系统牲结构的确定方法和故障后系统的重构方法与步骤,通过对某飞机纵向飞行控制系统的仿真表明所提出的方法既能保证重构后闭环系统的稳定性,又性使系统性能得到最大可能的恢复。 相似文献
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基于部分状态信息的控制器是一类特殊的静态输出反馈控制器, 一般难以利用线性矩阵不等式工具求解. 本文研究T-S模糊系统的部分状态反馈镇定及部分状态反馈H∞控制问题. 首先, 通过矩阵变换, 将T-S模糊系统的部分状态反馈镇定问题转换成求解一组线性矩阵不等式(LMIs); 然后, 以此为基础得到基于LMI的部分状态反馈H∞控制器设计方法; 最后, 通数值例子验证所给方法的有效性. 相似文献
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Sophisticated control configurations are needed to meet the mission and pilotage requirements for advanced aircraft. The required vehicle performance during low altitude, low speed and high angle of attack flight, all-weather, day and night operations must be achieved, and new control technologies should be developed. This work presents a systematic control design philosophy for flight control systems when the state variables and control inputs are bounded by the prespecified constraints. The design procedure uses the dynamic programming concept. The fundamental idea involves minimization of nonquadratic functionals. A new representation of constraints is proposed using the smooth functions. The advantages of the synthesis approach are presented. To illustrate the design methodology the longitudinal control configuration for the F-18 fighter is synthesized 相似文献
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发展了一种集成旋翼状态反馈(Rotor-State Feedback,RSF)控制的飞行控制系统,以提升直升机在大气紊流环境中低速飞行时的飞行品质。基于经典显模型跟踪控制系统,对机体和旋翼状态反馈增益进行协同设计,以综合优化旋翼/机体耦合动稳定性和直升机在飞行品质相关频率范围(1~12rad/s)内的紊流缓和能力。同时,设计了一个旋翼前馈控制以增强直升机的操纵响应特性。对直升机飞行品质的线性分析表明:RSF控制的引入能够在实现旋翼/机体耦合动稳定性控制的同时使滚转和俯仰通道的指令跟踪延迟时间分别降低21.87%和25.82%,扰动抑制带宽分别提升243.22%和72.56%。最后以飞行试验验证的高阶非线性飞行动力学模型进行数值模拟验证控制系统。结果表明:RSF控制的引入使直升机滚转、俯仰角速率对紊流响应的标准差分别降低55.68%和26.81%。集成RSF的控制系统能够提升直升机在紊流中的飞行品质。 相似文献
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《Aerospace Science and Technology》2007,11(2-3):229-237
In this paper we discuss the determination of the correction manoeuvres required to control geostationary satellites within a predefined space box over a place above the Earth using a feedback control technique. The control algorithm formulated here combines an accurate numerical propagator for the orbit evolution with an iterative process for the calculation of impulsive manoeuvres that gives numerical solutions convergent to the optimal values, both for the impulses to be applied and for the times of their implementations, to minimize fuel consumption. Numerical simulations are presented to illustrate this technique and to compare it with classical stationkeeping. The numerical results for this nonlinear approach show how the magnitude of the impulses can be reduced over 3 percent per year with respect to the classical approach. This means that the orbital life-time can be increased up to 5 months for a 15 years life-time mission. 相似文献
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基于LMI(LinearMatrixInequality,线性矩阵不等式),提出一种航空发动机PI输出反馈控制器设计方法。利用被控对象中控制向量2范数上界的限制,提出了一种改进ILMI(IterativeLMI)算法,用于解决控制受约束的航空发动机PI控制器的一种LMI描述求解问题。以某型双转子涡喷发动机为被控对象,基于LMI进行了PI输出反馈控制器的设计,并分区域在飞行包线进行了航空发动机控制系统仿真验证。结果表明,所得控制器满足预期设计要求,同时具有一定鲁棒性。 相似文献
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在常态Lipschitz非线性的基础上,考虑状态参数不确定性。针对这类Lipschitz非线性系统的反馈控制问题,运用Lyapunov方法给出了该系统渐近稳定的充分条件,并提出了应用线性矩阵不等式(LMI)来求解优化反馈增益矩阵,通过定理和Matlab仿真实例得出设计的观测器有效,具有良好的稳定性和鲁棒性。 相似文献
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High dynamic tracking performance is a key technical index of hydraulic flight motion simulator(HFMS). However, the strong nonlinearities, various model uncertainties and measurement noise in hydraulic actuation systems limit the high dynamic performance improvement. In this paper, the outer axis frame of a HFMS is taken as a case study and its nonlinear dynamic model with consideration of strong nonlinearities, matched and mismatched uncertainties is established.A novel cascaded extended state ... 相似文献
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Time-domain control design for stability robustness of linear systems with structured uncertainty is addressed. Upper bounds on the linear perturbation of an asymptotically stable linear system are obtained, making it possible to maintain stability by using the structural information of the uncertainty. A quantitative measure called the stability robustness index is introduced and used to design controllers for robust stability. The proposed state feedback control design algorithm can be used, for a given set of perturbations, to select the range of control effort for which the system is stability-robust. Conversely it can be used, for a given control effort, to determine the size of the tolerable perturbation. The algorithm is illustrated with examples from aircraft control and large-space-structure control problems 相似文献
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《中国航空学报》2016,(5):1302-1312
The acceleration autopilot design for skid-to-turn (STT) missile faces a great challenge owing to coupling effect among planes, variation of missile velocity and its parameters, inexistence of a complete state vector, and nonlinear aerodynamics. Moreover, the autopilot should be designed for the entire flight envelope where fast variations exist. In this paper, a design of inte-grated roll-pitch-yaw autopilot based on global fast terminal sliding mode control (GFTSMC) with a partial state nonlinear observer (PSNLO) for STT nonlinear time-varying missile model, is employed to address these issues. GFTSMC with a novel sliding surface is proposed to nullify the integral error and the singularity problem without application of the sign function. The pro-posed autopilot consisting of two-loop structure, controls STT maneuver and stabilizes the rolling with a PSNLO in order to estimate the immeasurable states as an output while its inputs are missile measurable states and control signals. The missile model considers the velocity variation, gravity effect and parameters’ variation. Furthermore, the environmental conditions’ dynamics are mod-eled. PSNLO stability and the closed loop system stability are studied. Finally, numerical simula-tion is established to evaluate the proposed autopilot performance and to compare it with existing approaches in the literature. 相似文献
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Designing a controller for the docking maneuver in Probe-Drogue Refueling(PDR) is an important but challenging task, due to the complex system model and the high precision requirement.In order to overcome the disadvantage of only feedback control, a feedforward control scheme known as Iterative Learning Control(ILC) is adopted in this paper.First, Additive State Decomposition(ASD) is used to address the tight coupling of input saturation, nonlinearity and the property of Non Minimum Phase(NMP) b... 相似文献
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To perform transient state control of an aero-engine, a structure that combines linear controller and min–max selector is widely adopted, which is inherently conservative and therefore limits the fulfillment of the engine potential. Model predictive control is a new control method that has vast application prospects in the field of aero-engine control. Therefore, this paper proposes a wide-range model predictive controller that can control the engine over a wide range within the flight envelope.... 相似文献
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RFNN control for PMLSM drive via backstepping technique 总被引:2,自引:0,他引:2
Faa-Jeng Lin Po-Hung Shen Rong-Fong Fung 《IEEE transactions on aerospace and electronic systems》2005,41(2):620-644
A robust fuzzy neural network (RFNN) control system is proposed in this study to control the position of the mover of a permanent magnet linear synchronous motor (PMLSM) drive system to track periodic reference trajectories. First, an ideal feedback linearization control law is designed based on the backstepping technique. Then, a fuzzy neural network (FNN) controller is designed to be the main tracking controller of the proposed RFNN control system to mimic an ideal feedback linearization control law, and a robust controller is proposed to confront the shortcoming of the FNN controller. Moreover, to relax the requirement for the bound of uncertainty term, which comprises a minimum approximation error, optimal parameter vectors and higher order terms in Taylor series, an adaptive bound estimation is investigated where a simple adaptive algorithm is utilized to estimate the bound of uncertainty. Furthermore, the simulated and experimental results due to periodic reference trajectories demonstrate that the dynamic behaviors of the proposed control systems are robust with regard to uncertainties. 相似文献
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《中国航空学报》2015,(4)
The robust controller design problem for switched polytopic systems under asynchronous switching is addressed.These systems exist in many aviation applications, such as dynamical systems involving rapid variations.A switched polytopic system is established to describe the highly maneuverable technology vehicle within the full flight envelope and a robust dynamic output feedback control method is designed for the switched polytopic system.Combining the Lyapunov-like function method and the average dwell time method, a sufficient condition is derived for the switched polytopic system with asynchronous switching and data dropout to be globally,uniformly and asymptotically stable in terms of linear matrix inequality.The robust dynamic output feedback controller is then applied to the highly maneuverable technology vehicle to illustrate the effectiveness of the proposed approach.The simulation results show that the angle of attack tracking performance is acceptable over the time history and the control surface responses are all satisfying along the full flight trajectory. 相似文献
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《中国航空学报》2016,(3):722-737
Agile satellites are of importance in modern aerospace applications,but high mobility of the satellites may cause them vulnerable to saturation during attitude maneuvers due to limited rating of actuators.This paper proposes a near minimum-time feedback control law for the agile satellite attitude control system.The feedback controller is formed by specially designed cascaded sub-units.The rapid dynamic response of the modified Bang–Bang control logic achieves the near optimal property and ensures the non-saturation properties on three-axis.To improve the dynamic performance,a model reference control strategy is proposed,in which the on-line near optimal attitude maneuver path is generated by the cascade controller and is then tracked by a nonlinear back-stepping controller.Furthermore,the accuracy and the robustness of the control system are achieved by momentum-based on-line inertial identification.The rapid attitude maneuvering can be applied for tasks including the move to move case.Numerical simulations are conducted to verify the effectiveness of the proposed control strategy in terms of the saturation-free property and rapidness. 相似文献