|
|
|
题名
|
作者
|
年代
|
出处
|
被引量
|
| 1 | 航天器近距离交会的固定时间终端滑模控制显示文摘针对航天器近距离交会段的位置姿态耦合控制问题,假设航天器受外界干扰且目标航天器存在空间自由翻滚情形时,基于固定时间概念设计了一种六自由度位姿终端滑模自适应控制器,通过引入显含正弦函数的切换项来避免奇异问题。此外所设计的控制器含双幂次项,不仅能全局提高姿态和位置的跟踪速度及精度,还能估计系统稳定所需的时间上界,且该上界与状态初始值无关。基于Lyapunov方法分析了闭环系统的固定时间稳定性。仿真结果表明,该控制器能快速实现对航天器近距离交会时相对位置和姿态的控制,具有较高的精度和良好的干扰抑制能力。 | 袁利 马广富 董经纬 李传江 姜博严 | 2018 | 宇航学报2018，29，2： | 15 |
| 2 | Accelerated Landweber iteration based control allocation for fault tolerant control of reusable launch vehicle显示文摘This paper presents a novel Fault Tolerant Control(FTC)scheme based on accelerated Landweber iteration and redistribution mechanism for a horizontal takeoff horizontal landing reusable launch vehicle(RLV).First,an adaptive law based on fixed-time non-singular fast terminal sliding mode control(NFTSMC),which focuses on the attitude tracking controller design for RLV in the presence of model couplings,parameter uncertainties and external disturbances,is proposed to produce virtual control command.On this basis,a novel Control Allocation(CA)based on accelerated Landwber iteration is presented to realize proportional allocation of virtual control command among the actuators according to the effective gain as well as the distance from the current position of actuator to corresponding saturation limit.Meanwhile a novel redistribution mechanism is introduced to redistribute oversaturated command among healthy actuators(non-faulty or redundant).The proposed method can be applied to a real-time FTC system so that the controller reconfiguring is not required in case of actuator faults.Finally,the effectiveness of the proposed method is demonstrated by numerical simulations. | Changzhu WEI Mingze WANG Baogang LU Jialun PU | 2022 | Chinese Journal of Aeronautics2022，35，2： | 4 |
| 3 | Fault-tolerant control with mixed aerodynamic surfaces and RCS jets for hypersonic reentry vehicles显示文摘This paper proposes a fault-tolerant strategy for hypersonic reentry vehicles with mixed aerodynamic surfaces and reaction control systems(RCS) under external disturbances and subject to actuator faults.Aerodynamic surfaces are treated as the primary actuator in normal situations,and they are driven by a continuous quadratic programming(QP) allocator to generate torque commanded by a nonlinear adaptive feedback control law.When aerodynamic surfaces encounter faults,they may not be able to provide sufficient torque as commanded,and RCS jets are activated to augment the aerodynamic surfaces to compensate for insufficient torque.Partial loss of effectiveness and stuck faults are considered in this paper,and observers are designed to detect and identify the faults.Based on the fault identification results,an RCS control allocator using integer linear programming(ILP) techniques is designed to determine the optimal combination of activated RCS jets.By treating the RCS control allocator as a quantization element,closed-loop stability with both continuous and quantized inputs is analyzed.Simulation results verify the effectiveness of the proposed method. | He Jingjing Qi Ruiyun Jiang Bin Zhai Rongyu | 2017 | Chinese Journal of Aeronautics2017，30，2： | 4 |
| 4 | 空天飞行器姿态直接力/气动力复合控制显示文摘针对空天飞行器再入段姿态控制问题,根据神经网络、滑模控制理论和控制分配技术,提出了一种有限时间复合控制策略。首先,根据空天飞行器再入段姿态模型设计了一种有限时间收敛的神经网络滑模控制器,得到使姿态角误差有限时间收敛的虚拟控制力矩。其次,采用控制分配技术将期望控制力矩映射到气动舵面和反推力系统。最后,通过对直接力/气动力复合控制的空天飞行器的仿真研究,验证了所提出复合控制策略的有效性。 | 李爱军 王瑜 郭永 王长青 | 2019 | 西北工业大学学报2019，37，3： | 4 |
| 5 | 基于稳定性判据的高超声速复合控制方法显示文摘针对传统直气复合控制系统侧喷发动机开启策略对先验数据的依赖性较强,导致鲁棒性较差的问题,提出基于稳定性判据的直气复合控制方法.根据高超声速飞行器模型推导稳定性判据,按照该判据预测飞行器的稳定状态,当飞行器即将失稳时开启侧喷发动机,及时增加直接力矩,控制飞行器稳定.该方法不依赖先验数据,可满足飞行器高马赫数下的稳定飞行和高机动性要求.通过建立全状态六自由度高超声速模型进行仿真研究,结果表明所提出的控制器具有较好的抗干扰能力,比传统控制策略鲁棒性更强. | 杨春宁 方家为 李春 葛晖 | 2017 | 浙江大学学报(工学版)2017，51，2： | 3 |
| 6 | 基于反步法的空天飞行器有限时间姿态跟踪控制显示文摘针对空天飞行器再入段姿态跟踪控制问题,根据反步法和控制分配技术提出了一种有限时间复合控制策略,处理在未知扰动和参数不确定性情况下RLV进行再入飞行时的姿态镇定问题。首先,根据多时间尺度,将RLV模型分为双回路子系统——姿态角子系统和姿态角速度子系统,并在反步法框架下定义误差向量,结合快速幂次趋近律设计虚拟角速度指令;然后,设计有限时间观测器,补偿包含虚拟指令微分组合的不确定项,并实时反馈给有限时间控制律,避免'参数膨胀';最后,利用分离原理和Lyapunov有限时间稳定性理论,证明了整体系统的收敛性,分析并给出了闭环系统的收敛时间。仿真结果表明了该控制策略的有效性。。 | 李婧忱 李爱军 黄兵 秦天煜 张媛 | 2019 | 飞行力学2019，37，1： | 3 |
| 7 | 研究自适应固定时间的空天飞行器姿态滑模控制显示文摘空天飞行器属于新一代天地往返飞行器,具有成本低、速度快、收益高的优势,然而对其控制系统要求比较高,于是研究控制器的有限时间收敛比较重要。于是,文章首先对空天飞行器姿态变化的数学模型进行建立,然后当存在干扰情况下,设计自适应固定时间滑膜控制。通过仿真对模型进行检测,发现具有更好的鲁棒性、稳定性和实用性。 | 宋杉 丁美丽 王桂明 杨毅 陶涛 | 2020 | 粘接2020，44，11： | 2 |
| 8 | Active disturbance rejected predictive functional control for space vehicles with RCS显示文摘Reaction control system(RCS) is a powerful and efficient actuator for space vehicles attitude control, which is typically characterized as a pulsed unilateral effector only with two states(off/on). Along with inevitable internal uncertainties and external disturbances in practice, this inherent nonlinear character always hinders space vehicles autopilot from pursuing precise tracking performance. Compared to most of pre-existing methodologies that passively suppress the uncertainties and disturbances, a design based on predictive functional control(PFC) and generalized extended state observer(GESO) is firstly proposed for three-axis RCS control system to actively reject that with no requirement for additional fuel consumption. To obtain a high fidelity predictive model on which the performance of PFC greatly depends, the nonlinear coupling multiple-input multiple-output(MIMO) flight dynamics model is parameterized as a state-dependent coefficient form. And based on that, a MIMO PFC algorithm in state space domain for a plant of arbitrary orders is deduced in this paper.The internal uncertainties and external disturbances are lumped as a total disturbance, which is estimated and cancelled timely to further enhance the robustness. The continuous control command synthesised by above controller-rejector tandem is finally modulated by pulse width pulse frequency modulator(PWPF) to on-off signals to meet RCS requirement. The robustness and feasibility of the proposed design are validated by a series of performance comparison simulations with some prominent methods in the presence of significant perturbations and disturbances, as well as measurement noise. | TIAN Jiayi ZHANG Shifeng | 2018 | Journal of Systems Engineering and Electronics2018，29，5： | 2 |
| 9 | 基于改进再分配伪逆法的高速飞行器RCS控制分配设计显示文摘高超声速飞行器再入段需要反作用控制系统(RCS)维持姿态稳定。设计一种固定推力器开启数的再分配伪逆控制分配方法,并应用在了高超声速飞行器再入段姿态控制中。首先,建立高超声速飞行器再入段RCS姿态模型,采用有限时间终端滑模算法设计姿态跟踪控制器。针对给定8推力器配置的RCS,设计固定3推力器开启的再分配伪逆法对RCS进行控制分配,能提高系统实时性并且降低燃料消耗。最后将设计的控制分配系统应用于高超声速飞行器再入姿态仿真,仿真结果表明设计的方法具有很好的控制效果,在保证控制性能和实时性的同时能够降低燃料消耗。 | 宋佳 张严雪 | 2021 | 郑州大学学报(理学版)2021，53，2： | 2 |
| 10 | Application of hybrid robust three-axis attitude control approach to overactuated spacecraft——A quaternion based model显示文摘A novel hybrid robust three-axis attitude control approach, namely HRTAC, is considered along with the well-known developments in the area of space systems, since there is a consensus among the related experts that the new insights may be taken into account as decision points to outperform the available materials. It is to note that the traditional control approaches may generally be upgraded, as long as a number of modifications are made with respect to state-of-the-art, in order to propose high-precision outcomes. Regarding the investigated issues, the robust sliding mode finite-time control approach is first designed to handle three-axis angular rates in the inner control loop, which consists of the pulse width pulse frequency modulations in line with the control allocation scheme and the system dynamics. The main subject to employ these modulations that is realizing in association with the control allocation scheme is to be able to handle a class of overactuated systems, in particular. The proportional derivative based linear quadratic regulator approach is then designed to handle three-axis rotational angles in the outer control loop, which consists of the system kinematics that is correspondingly concentrated to deal with the quaternion based model. The utilization of the linear and its nonlinear terms, simultaneously, are taken into real consideration as the research motivation, while the performance results are of the significance as the improved version in comparison with the recent investigated outcomes. Subsequently, there is a stability analysis to verify and guarantee the closed loop system performance in coping with the whole of nominal referenced commands. At the end, the effectiveness of the approach considered here is highlighted in line with a number of potential recent benchmarks. | A.H.Mazinan | 2016 | Journal of Central South University2016，23，7： | 2 |
| 11 | 再入飞行器的RCS控制系统设计显示文摘针对再入飞行器初始再入段的发动机反作用控制系统(RCS)控制精度问题,提出了一种新型发动机控制方法。首先,将飞行器模型分为慢回路和快回路分别进行控制器设计,采用非线性干扰观测器(DOB)来获取不确定项的估计值,并使用反演法及滑模控制方法设计了飞行器的慢回路和快回路控制律;其次,采用线性规划方法来获取最优RCS指令分配方案;在此基础上,对传统PWPF调制器进行改进,提出了积分补偿型PWPF调制器(IPWPF),采用描述函数法证明了该IPWPF的调制稳定性;最后,通过仿真验证了该方法相比于传统的控制方法具有较高的控制精度。 | 郭建国 张添保 周军 王国庆 | 2017 | 固体火箭技术2017，40，4： | 2 |
| 12 | 采用ESO补偿的再入飞行器姿态预测控制方法显示文摘针对飞行器再入姿态运动设计了一种基于扩张状态观测器(extended states observer,ESO)的预测控制方法。为了降低系统的阶数,将姿态系统分成姿态角子系统和姿态角速率子系统,分别设计控制器。采用动态逆方法将运动方程线性化,并基于此推导了解析的最优预测控制律。为了提高控制器的精度和鲁棒性,采用ESO对模型误差和不确定扰动进行估计,并在预测控制律中进行补偿。最后证明了算法的稳定性。通过六自由度仿真分析,验证了控制方法的良好性能。 | 王涛 张洪波 汤国建 | 2018 | 系统工程与电子技术2018，40，7： | 1 |
| 13 | Fast self-adapting high-order sliding mode control for a class of uncertain nonlinear systems显示文摘A fast self-adapting high-order sliding mode(FSHOSM)controller is designed for a class of nonlinear systems with unknown uncertainties.As for uncertainty-free nonlinear system,a new switching condition is introduced into the standard geometric homogeneity.Different from the existing geometric homogeneity method,both state variables and their derivatives are considered to bring a reasonable effective switching condition.As a result,a faster convergence rate of state variables is achieved.Furthermore,based on the integral sliding mode(ISM)and above geometric homogeneity,a self-adapting high-order sliding mode(HOSM)control law is proposed for a class of nonlinear systems with uncertainties.The resulting controller allows the closed-loop system to conduct with the expected properties of strong robustness and fast convergence.Stable analysis of the nonlinear system is also proved based on the Lyapunov approach.The effectiveness of the resulting controller is verified by several simulation results. | GUO Fuhui LU Pingli | 2021 | Journal of Systems Engineering and Electronics2021，32，3： | 1 |
| 14 | 自适应固定时间的空天飞行器姿态滑模控制显示文摘针对空天飞行器的姿态控制问题,设计了一种自适应的固定时间滑模控制器。其主要分为三大部分:固定时间收敛的滑模面、控制律和自适应律。固定时间滑模控制器的优势在于,可以在不知道系统任何初始信息的情况下,使飞行器姿态在固定的时间内收敛到镇定状态。但是其没有考虑干扰带来的问题,因此引入自适应的方法处理干扰,增加系统的鲁棒性。最终通过数学分析、仿真结果和与其它控制器的比较,验证了设计的控制器的有效性和鲁棒性。 | 刘伯健 李爱军 黄兵 | 2019 | 计算机仿真2019，36，11： | 1 |
| 15 | ESO-based robust predictive control of lunar module with fuel sloshing dynamics显示文摘An extended-state-observer(ESO) based predictive control scheme is proposed for the autopilot of lunar landing.The slosh fuel masses exert forces and torques on the rigid body of lunar module(LM),such disturbances will dramatically undermine the stability of autopilot system.The fuel sloshing dynamics and uncertainties due to the time-varying parameters are considered as a generalized disturbance which is estimated by an ESO from the measured attitude signals and the control input signals.Then a continuous-time predictive controller driven by the estimated states and disturbances is designed to obtain the virtual control input,which is allocated to the real control actuators according to a deadband logic.The 6-DOF simulation results reveal the effectiveness of the proposed method when dealing with the fuel sloshing dynamics and parameter perturbations. | 宋征宇 颜钢锋 赵党军 | 2017 | Journal of Central South University2017，24，3： | 1 |
| 16 | 基于鲁棒微分器的全阶非奇异终端滑模再入姿态控制显示文摘针对飞行器再入段的强耦合和非线性的问题,提出了一种基于鲁棒微分器(robust exact differentiator,RED)的全阶非奇异终端滑模控制(full-order nonsingular terminal sliding mode control,FONTSMC)方法.首先,设计了一种新的全阶非奇异终端滑模函数,保证在控制器中不存在带有分数次幂项的状态量的导数,同时证明了跟踪误差可以在有限时间内收敛到0;然后,针对该滑模运动方程存在误差二阶导数的特殊情况,引入了超螺旋算法(super-twisting algorithm,STA)作为鲁棒微分器(RED),避免了由直接采用普通微分器引入的干扰噪声.进一步为了避免滑模控制的抖振问题,采用边界层技术与低通滤波技术共同消除控制量的抖振.最后,仿真结果验证了所设计的控制器可以实现有限时间姿态跟踪控制,且具有较好的鲁棒性. | 赖汝 金震 盛永智 刘向东 | 2016 | 北京理工大学学报2016，36，12： | 1 |
| 17 | L1 adaptive control of a generic hypersonic vehicle model with a blended pneumatic and thrust vectoring control strategy显示文摘The extreme aeroheating at hypersonic regime and the insufficient dynamic pressure in the near space limit the achievable performance of the hypersonic vehicles using aerosurfaces alone. In this paper, an integrated pneumatic and thrust vectoring control strategy is employed to design a control scheme for the longitudinal dynamics of a hypersonic vehicle model. The methodology reposes upon a division of the model dynamics, and an L_1 adaptive control architecture is applied to the design of the inner-loop and outer-loop controllers. Further, a control allocation algorithm is developed to coordinate pneumatic and thrust vectoring control. Simulation results demonstrate that the allocation algorithm is effective in control coordination, and the proposed control scheme achieves excellent tracking performance in spite of aerodynamic uncertainties. | Qi CHEN Jing WAN Jianliang AI | 2017 | Science China(Information Sciences)2017，60，3： | 0 |
| 18 | Robust sliding mode control with ESO for dual-control missile显示文摘This paper proposes a novel composite dual-control by combing the integral sliding mode control(ISMC) method based on the finite time convergence theory with extended state observer(ESO) for a tracking problem of a missile with tail fins and reactionjet control system(RCS). First, the ISMC method based on finite time convergence is utilized to design the control law of tail fins and the pulse control of RCS for the dual-control system, ensuring the system with rapid response and high accuracy of tracking. Then,ESO is employed for the estimation of aerodynamic disturbances influenced by the airflow of thruster jets. With the characteristic of high accuracy estimation of ESO, the chattering free tracking performance of the attack angle command and the robustness of the control law are achieved. Meanwhile, the stability of the dual-control system is analyzed based on finite time convergence stability theorem and Lyapunov's theorem. Finally, numerical simulations demonstrate the effectiveness of the proposed design. | wei shang shengjing tang jie guo yueyue ma yuhang yun | 2016 | Journal of Systems Engineering and Electronics2016，27，5： | 0 |
| 19 | Drag derived altitude aided navigation method显示文摘The navigation problem of the lifting reentry vehicles has attracted much research interest in the past decade. This paper researches the navigation in the blackout zone during the reentry phase of the aircraft, when the communication signals are attenuated and even interrupted by the blackout zone. However, when calculating altitude, a pure classic inertial navigation algorithm appears imprecise and divergent. In order to obtain a more precise aircraft altitude, this paper applies an integrated navigation method based on inertial navigation algorithms, which uses drag derived altitude to aid the inertial navigation during the blackout zone. This method can overcome the shortcomings of the inertial navigation system and improve the navigation accuracy. To further improve the navigation accuracy, the applicable condition and the main error factors, such as the atmospheric coefficient error and drag coefficient error are analyzed in detail. Then the damping circuit design of the navigation control system and the damping coefficients determination is introduced. The feasibility of the method is verified by the typical reentry trajectory simulation, and the influence of the iterative times on the accuracy is analyzed. Simulation results show that iterative three times achieves the best effect. | Hua SONG Meiling WANG Jing YANG Dantong SUN Longtao KONG Chunling WEI | 2017 | Chinese Journal of Aeronautics2017，30，5： | 0 |
您所在的机构暂未开通此部分的功能，请联系管理员