Reconfigurable Flight Control Design for Combat Flying Wing with Multiple Control Surfaces

With control using redundant multiple control surface arrangement and large-deflection drag rudders,a combat flying wing has a higher probability for control surface failures.Therefore,its flight control system must be able to reconfigure after such failures.Considering three types of typical control surface failures(lock-in-place(LIP),loss-of-effectiveness(LOE) and float),flight control reconfiguration characteristic and capability of such aircraft types are analyzed.Because of the control surface redundancy,the aircraft using the dynamic inversion flight control law already has a control allocation block.In this paper,its flight control configuration during the above failures is achieved by modifying this block.It is shown that such a reconfigurable flight control design is valid,through numerical simulations of flight attitude control task.Results indicate that,in the circumstances of control surface failures with limited degree and the degradation of the flying quality level,a combat flying wing adopting this flight control reconfiguration approach based on control allocation could guarantee its flight safety and perform some flight combat missions.     

立方体星的技术发展和应用前景

系统论述了立方体星技术发展的三个阶段;从2010-2013年已成功发射的立方体星与纳卫星中挑选了10颗典型卫星,研究分析其技术水平、应用价值和特点优势;并重点论述了立方体纳卫星的应用;最后预测了立方体纳卫星的未来应用前景。     

基于一致关联数最大化的航迹关联算法

航迹关联(TTTA)是多传感器数据融合系统的核心模块之一,是系统误差估计和航迹融合的前提和基础。传感器存在的固有系统误差使得目标位置状态估计与真值发生偏离,容易诱发TTTA错误。传统的基于全局最小距离准则的TTTA算法,需要获得较高精度的系统误差估计,来对航迹数据进行误差补偿。针对传感器具有系统误差环境下的TTTA问题,在对TTTA进行间接评估的基础上,定义了一致关联数的概念,提出了一致关联数最大化的TTTA准则,并在稳健交替迭代的框架下完成算法设计。与距离函数不同,一致关联数是一个离散量,放松了对系统误差估计精度的要求。最后,仿真实验验证了所提算法的有效性。     

一种基于机动辨识预测的空空导弹导引律

现有的空空导弹导引头在有噪声和干扰的环境下获得目标精确信息存在时间延迟,且新一代目标的机动能力更强,不对导弹加以补偿会造成较大脱靶量,所以需对目标状态有效预测。针对新一代目标规避空空导弹常用的大机动模式,为满足新一代空空导弹发展需求,设计了一种新型复合导引律。从目标自身出发,研究高机动目标规避导弹采用的典型机动形式,对机动轨迹进行离线建模,构建具有扩展能力的目标机动模型库。设计自适应滤波器对测量噪声进行降噪。同时,利用模型库设计了机动辨识预测器,对目标实际机动进行在线辨识。基于在线辨识的结果对目标机动进行预测,并对时间延迟进行补偿和修正,实现对高机动目标的精确打击。仿真结果表明:该方法对不同类型的机动目标均有较高的预测精度和命中精度。     

手工计划模拟CDA燃油的节省

飞机在飞行中,普遍采用的阶梯下降程序,这需要航空器频繁改变推力、增加下降角度和调整高度,这样加大了飞行员和管制员的工作压力,同时对最后阶段飞行的油量也有增加。通过对连续下降进近（CDA）的现状进行分析,给出连续下降进近相对传统进近方式的优势,并结合航空公司手工飞行计划制作的方法及原理对连续下降进近在最后阶段飞行时间和燃油方面的节约进行验证。     

Periodic relative orbits of two spacecraft subject to differential gravity and electrostatic forcing

Coulomb forces between charged close-flying satellites can be used for formation control, and constant electric potentials enable static equilibria solutions. In this work, open-loop time-varying potential functions, which produce periodic, two-craft, Coulomb formation motions are demonstrated for the first time. This is done in the rotating Hill-Frame, with linearized gravity, and craft position components assumed in the form of simple harmonic oscillators. Substitution of the oscillatory functions into the dynamics, further constrains these functions, and yields necessary potential histories, to produce the periodic flow. The assumed position functions, however, are not arbitrary, since the dynamical model restricts what oscillatory trajectories are allowed. Specifically, a Hill-Frame integral of motion is derived, and this is used to show certain candidate periodic functions to be inadmissible. The system dynamics are then linearized to expose stability properties of the solutions, and it is established that asymptotic stability is impossible for all orbit families. Finally, the degree of instability in the assumed motions, over free parameter ranges, is determined numerically via the Floquet multipliers of the associated full-cycle state-transition matrices.     

一种新型测距仪的研制

介绍了一种在中，小范围内，采用激光定位，超声测距的新型测量仪器，该仪器以单片微处理器为核心，对不同的测量距离，采用不同频率的超声波，结合信号处理方法，从而实现０．６～１４ｍ范围内高精度实时测量目标距离，其测量相对误差优于１％。     

Hybrid optimization for multiple-impulse reconfiguration trajectories of satellite formation flying

A hybrid optimization method is developed for fuel-optimal reconfigurations of a group of satellites flying in formation. The genetic algorithm performs a global search to find two-impulse trajectories, and primer vector analysis finds multiple-impulsive local optimal trajectories with the two-impulse trajectories as initial guesses. Hybrid optimization finds globally optimal trajectories for formation reconfigurations, including formation resizing, reassignment and reorientation maneuvers. Multiple-impulse trajectories reduce the fuel consumption from the two-impulse trajectories by up to 4.4% for those maneuvers. In real missions, satellites can follow two-impulse trajectories to gain the advantage of a smaller number of impulses, with the cost of slightly more propellant. The qualitative characteristics of the optimal trajectories are analyzed from the number of optimal trajectories found by hybrid optimization.     

俯仰轴飞行品质中频域准则的计算与模拟

简要介绍了军用飞机飞行品质MIL—STD—1797A中有关俯仰轴频域难则的要求和原由。提出了对这些难则的理论计算和模拟试验方法。并以某飞机为例，利用所提出的方法，对其飞行品质进行了计算和模拟。结果表明，所提出的计算和模拟方法是合理的。最后，讨论了驾驶员模型形式对俯仰轴飞行品质的影响。     

中层大气受迫Rossby波包的非线性相互作用：Ⅱ.数值计算

本文对中层大气受迫Ｒｏｓｓｂｙ波包的非线性三波相互作用问题作了进一步的数值分析，结果表明，三个波包随时间演化达到的平衡态与文献［１］的理论结果完全一致，而且仅当系统中只有中等波长波包不受外源强迫时，系统运动有可能出现两个稳定平衡态，在一定外源强度范围内，平衡态会产生尖点突变，平衡态随外源的变化有滞后分岔的特征，系统运动最终达到的平衡态不仅与外源强度的变化方式有关，而且依赖于初始状态。