Guaranteed performance based adaptive attitude tracking of spacecraft with control constraints

The guaranteed performance control problem of spacecraft attitude tracking with control constraint, disturbance and time-varying inertia parameters is investigated. A new saturation function is designed to satisfy different magnitude constraints by introducing a piecewise smooth asymmetric Gauss error function. Based on the mean-value theorem, the constrained problem is transformed into an unconstrained control design subject to an unknown bounded coefficient matrix. To satisfy the constraints by performance functions, a tracking error constrained control is developed based on a hyperbolic arc-tangent asymmetric barrier Lyapunov function (BLF). In the backstepping framework, an adaptive robust control law is proposed by employing a smooth robust term simultaneously counteracting the parametric and non-parametric uncertainties, where the unknown coefficient matrix resulting from the control constraint is compensated by a Nussbaum function matrix. Rigorous stability analysis indicates that the proposed control law realizes the asymptotically tracking of spacecraft attitude and that the tracking error remains in a prescribed set which implies the achievement of the guaranteed transient performance. Numerical simulations validate the proposed theoretical results.     

轨迹跟踪伺服系统的鲁棒复合控制

针对控制输入饱和受限且带有未知扰动的电机伺服系统,提出一种实现曲线轨迹准确跟踪的鲁棒复合控制方案。该方案引入一个参考信号生成器和一个扩展状态观测器,其中参考信号生成器可根据目标轨迹信号构造出对应的状态量,扩展状态观测器用于对系统的状态量和扰动进行估计, 采用反馈与前馈相结合构成最终的控制律。利用Lyapunov理论对闭环系统的稳定性进行了严格分析。在MATLAB中进行了仿真研究,随后在一个DSP控制的永磁直线电机二维伺服平台进行了试验验证。结果表明:所提的控制方案能在轨迹跟踪任务中取得优越的瞬态性能和稳态准确性,而且对目标轨迹和扰动的幅值差异具有较好的鲁棒性。     

High precision attitude dynamic tracking control of a moving space target

On-orbit spacecraft face many threats, such as collisions with debris or other spacecraft.Therefore, perception of the surrounding space environment is vitally important for on-orbit spacecraft.Spacecraft require a dynamic attitude tracking ability with high precision for such missions.This paper aims to address the above problem using an improved backstepping controller.The tracking mission is divided into two phases: coarse alignment and fine alignment.In the first phase,a traditional saturation controller is utilized to limit the maximum attitude angular velocity according to the actuator's ability.For the second phase, the proposed backstepping controller with different virtual control inputs is applied to track the moving target.To fulfill the high precision attitude tracking requirements, a hybrid attitude control actuator consisting of a Control Moment Gyro(CMG) and Reaction Wheel(RW) is constructed, which can simultaneously avoid the CMG singularity and RW saturation through the use of an angular momentum optimal management strategy, such as null motion.Finally, five simulation scenarios were carried out to demonstrate the effectiveness of the proposed control strategy and hybrid actuator.     

基于Doppler估计的弹载接收机抗欺骗干扰研究

GNSS接收机在军用方面尤其是高精度制导武器中的应用日益增强.针对卫星信号易受敌方欺骗信号干扰的问题,设计一种基于Doppler频率估计的弹载接收机抗欺骗干扰的方法.首先分析了欺骗干扰和真实信号的Doppler变化特点;然后在捕获阶段利用残留信号检测存在欺骗干扰的卫星编号;最后根据弹载的高动态特性,在跟踪阶段采取扩展 Kalman 滤波器(EKF)进行载波Doppler频率估计,并根据Doppler变化的相似性提取出欺骗信号.通过仿真实验验证,该方法可以有效排除欺骗信号的干扰.     

时延遥操作系统的非对称双通道波变量补偿法

为保证遥操作系统在时延条件下的稳定性,以及减少传统波变量方法的跟踪误差,提出一种非对称双通道波变量补偿法。该方法在前向通道波变量补偿法的基础上,采用能量整定器对反向通道的波变量进行补偿。通过调节波阻抗、滤波器和能量整定器的相关参数可以充分保证遥操作系统的稳定性和跟踪性能。实验结果表明该方法在保证时延遥操作系统稳定性的基础上,速度跟踪平均误差比传统波变量法减少70%以上,力跟踪平均误差比前向通道波变量补偿法减少60%以上。为了比较不同时延下本方法的效果,设计时延分别为3s和0.6s的2种实验。结果表明本方法在不同时延条件下均可以取得较好的效果。     

内转式进气道/冯·卡门乘波体一体化设计方法

应用特征线理论设计了内转式轴对称基准流场以及外压缩轴对称基准流场，利用激波交线、流线追踪方法等相关技术提出了一种头部进气式的高超声速飞行器内转式进气道/冯·卡门乘波体一体化设计方法，并对生成的一体化构型进行了数值模拟及分析，数值结果验证了该方法的正确性和有效性。该一体化设计方法基本保留了内转式进气道的优良特性，并以高升阻比乘波体为原型构建较高升阻比的一体化构型，从流场耦合的角度出发为减弱机体与进气道之间复杂的波系干扰，实现飞行器内外流的完全耦合进行了探索。     

基于浸入与不变理论的航天器姿态跟踪自适应控制

针对惯性参数不确定的航天器姿态跟踪控制问题，基于浸入与不变（I&I）方法设计出了一种新的姿态跟踪控制器。研究结果表明，传统的浸入与不变方法运用到姿态跟踪模型，存在参数回归矩阵不可积进而导致偏微分方程无解析解的问题。针对该问题，提出了一种对回归矩阵改造使其满足可积条件的方法，通过动态放缩技术消除了回归矩阵改造前后的差异对闭环系统稳定性的影响，设计出了一种新的航天器姿态跟踪自适应控制器。通过李雅普诺夫稳定性分析方法证明了所设计的控制器能够保证闭环系统的全局渐近稳定性。相对于已有的基于动态放缩法的浸入与不变控制器，设计了一种全新的缩放因子，使得控制器的执行不需要缩放因子的信息，并且也不需要惯量矩阵的先验信息。最后，仿真对比实验进一步验证了所设计控制器的有效性和优越性。     

A novel strong tracking cubature Kalman filter and its application in maneuvering target tracking

The fading factor exerts a significant role in the strong tracking idea. However, traditional fading factor introduction method hinders the accuracy and robustness advantages of current strong-tracking-based nonlinear filtering algorithms such as Cubature Kalman Filter (CKF) since traditional fading factor introduction method only considers the first-order Taylor expansion. To this end, a new fading factor idea is suggested and introduced into the strong tracking CKF method. The new fading factor introduction method expanded the number of fading factors from one to two with reselected introduction positions. The relationship between the two fading factors as well as the general calculation method can be derived based on Taylor expansion. Obvious superiority of the newly suggested fading factor introduction method is demonstrated according to different nonlinearity of the measurement function. Equivalent calculation method can also be established while applied to CKF. Theoretical analysis shows that the strong tracking CKF can extract the third-order term information from the residual and thus realize second-order accuracy. After optimizing the strong tracking algorithm process, a Fast Strong Tracking CKF (FSTCKF) is finally established. Two simulation examples show that the novel FSTCKF improves the robustness of traditional CKF while minimizing the algorithm time complexity under various conditions.     

面向复杂场景的鲁棒KCF行人跟踪方法

经典核相关滤波(Kernel correlation filter,KCF)目标跟踪算法是判别式跟踪算法中效果最好的一种跟踪算法。但该算法不能很好地适应目标尺度的变化,且在遇到目标短暂消失或被其他物体遮挡等复杂情形时不具备处理目标重显的能力,因此,为使得目标跟踪能够有效地应对遮挡情形,本文从提高特征表达能力、增加尺度匹配策略和抗遮挡3个方面对经典KCF算法进行改进,提出了一种鲁棒的KCF行人跟踪算法。首先对方向梯度直方图(Histogram of oriented gradients,HOG)特征和色调、饱和度、值(Hue-saturation-value,HSV)特征的响应分布进行特征融合。其次,设置动态选择尺度池来改进滤波器的固定尺寸匹配。最后,通过滤波器响应最大值的变化率衡量目标的遮挡情况,并根据上一成功帧的目标信息,通过EdgeBoxes和感知哈希算法找回目标,更新滤波器。本文所提方法在公开视频跟踪数据集Benchmark上进行测试,实验结果表明与其他目标跟踪方法相比,本文算法提高了尺度变化、遮挡等复杂情形下跟踪的鲁棒性,确保了较高的跟踪精度。     

基于跟瞄和加表PI滤波近程相对导航方法

针对由于加速度计存在漂移和目标星加速度未知,基于C-W(Clohessey-Whiltshire)方程递推的近程相对导航无法长时间使用的问题,提出了一种基于跟瞄相对测量信息修正相对位置/相对速度误差和估计加表漂移的方法,并给出了比例积分(PI)滤波近程相对导航算法。最后,进行了工程应用方式分析和仿真验证。相对位置误差估计精度优于50 m。仿真结果表明:该方法既能确保相对位置和相对速度输出的连续性,又可抑制跟瞄观测噪声并消除长时间积分累积误差。基于PI滤波的近程相对导航方法计算简单,易于工程实现,且已通过在轨考核验证。