高超声速飞行器气动伺服弹性的自适应抑制

针对弹性高超声速飞行器的气动伺服弹性问题，提出一种结合线性自抗扰和自适应陷波器的综合控制方案。针对强耦合和强不确定性问题，采用线性自抗扰控制对总扰动进行快速估计和补偿。为了在最小化对刚体控制性能影响的同时实现对频率未知且时变的弹性模态的抑制，采用能够在线估计弹性频率的自适应陷波器。根据气动伺服弹性抑制问题的特点提炼出对自适应陷波器的性能需求。针对这些需求设计了两种基于递推最大似然法的多频率直接辨识方案——参数单独自适应和同时自适应方案。为了提高辨识算法在各种随机扰动下的鲁棒性，在此基础上提出一种在线有效性监督机制，并通过大量的数字仿真对两种方案进行了性能对比。最后，在弹性高超声速飞行器模型上进行仿真，仿真结果验证了所提控制方案的有效性。     

基于虚拟排序与航空公司自主决策的航班推出策略研究

当机场场面出现拥堵时，新增的航班推出会增加机场的拥堵，同时增加燃油的消耗以及污染物的排放。提出了航班虚拟推出队列方法，以航班停机位等待代替航班滑行道排队等待，可以减少场面拥堵和污染物排放。在该方法的基础上提出了乘客等待时间最小及航班场面滑行成本最优的策略。仿真结果表明，对虚拟航班时隙的调整，可以降低旅客的等待时间、减少航空公司场面运行成本。     

航天器太阳能电池阵驱动系统激扰因素辨识与扰动机理分析

建立了典型太阳能电池阵驱动系统(SADS)精细动力学模型，开展了扰动特性地面试验测试，讨论了产生扰动的必要条件，分析了直接激扰因素及其对应扰动的时频特点。结果表明：所建动力学模型分析结果与试验测试扰动数据吻合良好(误差<10%)；刚体转动角加速度和模态振动加速度不同时为零是引起驱动系统扰动的前提条件；细分驱动、电机磁场非线性、时变齿轮啮合参数等是驱动系统的主要内部激扰因素；扰动力矩一般均具有周期变化特点，扰动成分集中在激扰频率及其高倍频附近，扰动幅度随细分驱动步距、齿槽激扰幅度、电磁激扰幅度和啮合参数变化幅度的增大而提高。     

Moving target localization in distributed MIMO radar with transmitter and receiver location uncertainties

In this paper, the problem of moving target localization from Bistatic Range(BR) and Bistatic Range Rate(BRR) measurements in a Multiple-Input Multiple-Output(MIMO) radar system having widely separated antennas is investigated. We consider a practically motivated scenario,where the accurate knowledge of transmitter and receiver locations is not known and only the nominal values are available for processing. With the transmitter and receiver location uncertainties,which are usually neglected in MIMO radar systems by prior studies, taken into account in the measurement model, we develop a novel algebraic solution to reduce the estimation error for moving target localization. The proposed algorithm is based on the pseudolinear set of equations and two-step weighted least squares estimation. The Cramer-Rao Lower Bound(CRLB) is derived in the presence of transmitter and receiver location uncertainties. Theoretical accuracy analysis demonstrates that the proposed solution attains the CRLB, and numerical examples show that the proposed solution achieves significant performance improvement over the existing algorithms.     

SCC evaluation of a 2297 Al-Li alloy rolled plate using the slow-strain rate technique

The stress corrosion cracking (SCC) susceptibility of 2297 Al-Li alloy in 1 M NaCl + 0.01 M H₂O₂ solution (CP solution) and 1 M NaCl + 0.01 M H₂O₂ + 0.6 M Na₂SO₄ solution (CPS solution) was investigated by slow-strain rate tests at various strain rates ranging from 10⁻⁵ s⁻¹ to 10⁻⁷ s⁻¹. The roles of H₂O₂ and SO₄²⁻ in the corrosion process were estimated by potentiodynamic polarization and electrochemical impedance spectroscopy. 2297 Al-Li alloy does not fracture ascribed to SCC in CP solution, while it undergoes SCC in CPS solution. In CPS solution, with a decreasing strain rate from 10⁻⁵ s⁻¹ to 10⁻⁷ s⁻¹, the SCC susceptibility firstly rises and then declines exhibiting a peak value at a strain rate of 10⁻⁶ s⁻¹. H₂O₂ promotes the active dissolution while SO₄²⁻ lowers the corrosion rate. The SCC fracture is associated with a decline in the dissolution rate of the crack tip by SO₄²⁻, which leads to stress concentration. In CPS solution, a reduction in the local dissolution rate of the crack tip leads to stress concentration, resulting in SCC fracture. As the preferred initiation site for a crack, pits also show a noteworthy effect on SCC of 2297 Al-Li alloy.     

A finite-time 3D guidance law based on fixed-time convergence disturbance observer

In order to achieve accurate interception of high-speed maneuvering targets, this paper presents a relative Line-of-Sight (LOS) velocity based finite-time three-dimensional guidance law design framework, and discusses the application of fixed-time convergence disturbance observer in this framework. Firstly, a simple Lyapunov function is provided to show that the coupled terms in the relative kinematics can be ignored in the proposed guidance law design framework. Secondly, the realizations of several classical guidance laws are analyzed with the proposed framework, including TPN guidance law, finite-time Input-to-State Stability (ISS) guidance law, and sliding mode guidance law. Thirdly, fixed-time convergence disturbance observers are introduced to design the composite finite-time 3D guidance law, and Lyapunov method is employed to show the stability of the guidance system. Numerical simulations with different scenarios show that the proposed generalized guidance law performs high interception accuracy.     

A composite disturbance observer and H_∞ control scheme for flexible spacecraft with measurement delay and input delay

In this paper, the attitude control algorithm of flexible spacecraft with unknown measurement delay and input delay based on disturbance observer is designed. The influence of measurement delay and input delay on the attitude control system and disturbance observer is analyzed. The disturbance estimation error equation is transformed into a differential system with a pure delay. Then, the observer gain is chosen based on the 3/2 stability theorem to ensure the stability and disturbance attenuation performance of the pure delay system. Next, the controller gain is designed based on the Linear Matrix Inequality(LMI) approach to guarantee the stability of the composite system and achieve H_∞ performance with two additive delays. The simulation results show that the proposed method can improve the anti-disturbance ability of the attitude control system.     

服务通告全面成本评估

从工作实际出发，提出了服务通告的全面成本评估方案，详细给出成本项分类和量化方法，应用投资收益率方法综合决策各成本项，帮助工程管理人员科学量化服务通告，得到更准确合理的评估结论。     

一种新型的用于深空高动态微弱信号载波跟踪环

分析了深空通信中高动态微弱信号载波跟踪方法，提出并分析了载波跟踪中状态方程非线性与量测方程的非线性取舍问题，分析了滤波过程中影响高动态与低信噪比的决定因素，给出了两个推论，提出了强跟踪算法的必要性。并以此选择了以传统卡尔曼滤波（KF）为基础，以锁相环（FLL）、无迹卡尔曼滤波（UKF）为辅助使用两种工作模式来应对不同环境。针对组合跟踪环路状态转换过渡易出现的频率阶跃问题，给出新型环路的工作模式及切换门限的数学表达式，在环路中添加计算判别器，实时控制环路输出的同时不浪费计算力地剔除了野值，提高了环路稳定性。仿真表明，该新型环路算法与现有的算法相比有很好的低信噪高动态适应能力，消除了切换峰值，剔除了野值。     

水中上升气泡体积变化率的图像分析技术

水中上升气泡的体积变化率是舰船自消隐特种气幕技术等诸多研究的重要基础.鉴于当前对这一体积变化率研究的紧迫需求,提出并较为深入地研究了水中上升气泡体积变化率的图像分析技术.首先,在理论研究的基础上,专门建立了分析计算的数学模型;进而给出了分析的实施方法,即利用摄像法获取水中上升气泡的图像序列,并从中得出所需图像的相关信息,再利用建立的模型即可求出其体积变化率;同时,设计了专门的实验,初步验证了这一分析技术的可行性.