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| 1 | Linear Quadratic Differential Game Strategies with Two-pursuit Versus Single-evader显示文摘In order to intercept the future targets that are characterized by high maneuverability, multiple interceptors may be launched and aimed at single target. The scenario of two missiles P and Q intercepting a single target is modeled as a two-pursuit single-evader non-zero-sum linear quadratic differential game. The intercept space is decomposed into three subspaces which are mutually disjoint and their union covers the entire intercept space. The effect of adding the second interceptor arises in the intercept space of both P and Q (PQ-intercept space). A guidance law is derived from the Nash equilibrium strategy set (NESS) of the game. Simulation studies are focused on the PQ-intercept space. It is indicated that 1) increasing the target's maneuverability will enlarge PQ-intercept space; 2) the handover conditions will be released if the initial zero-effort-miss (ZEM) of both interceptors has opposite sign; 3) overvaluation of the target's maneuverability by choosing a small weight coefficient will generate robust performance with respect to the target maneuvering command switch time and decrease the fuel requirement; and 4) cooperation between interceptors increases the interception probability. | LIU Yanfang QI Naiming TANG Zhiwei | 2012 | Chinese Journal of Aeronautics2012，25，6： | 19 |
| 2 | Differential game strategy in three-player evasion and pursuit scenarios显示文摘A conflict of three players, including an attacker, a defender, and a target with bounded control is discussed based on the differential game theories in which the target and the defender use an optimal pursuit strategy. The current approach chooses the miss distance as the outcome of the conflict. Different optimal guidance laws are investigated, and feasible conditions are analyzed for the attacker to accomplish an attacking task. For some given conditions, the attacker cannot intercept the target by only using a one-to-one optimal pursuit guidance law; thus, a guidance law for the attacker to reach a critical safe value is investigated.Specifically, the guidance law is divided into two parts. Before the engagement time between the defender and the attacker, the attacker uses this derived guidance law to guarantee that the evasion distance from the defender is safe, and that the zero-effort-miss(ZEM) distance between the attacker and the target is the smallest.After that engagement time, the attacker uses the optimal one-toone guidance law to accomplish the pursuit task. The advantages and limited conditions of these derived guidance laws are also investigated by using nonlinear simulations. | SUN Qilong QI Naiming XIAO Longxu LIN Haiqi | 2018 | Journal of Systems Engineering and Electronics2018，29，2： | 9 |
| 3 | Neural integrated control for a free-floating space robot with suddenly changing parameters显示文摘Because the state of a free-floating space robot model is uncertain and sudden changes in the model parameters might undermine the stability of the system,this paper proposes a control strategy based on a variable structure neural integrated controller.This scheme does not need a precise space robot model,making use of the radial basis function neural network ability approach to learn about an uncertain model.The network weights are adjusted online in real-time.During the early period of the control phase and parameter changes,the variable structure controller compensates for the uncertain model which the neural network could not learn well.It also creates global asymptotic stability for the whole closed-loop system.Simulation results show that the controller can handle bad changeable conditions and has important application value for defense,aerospace and other major security fields. | ZHANG WenHui QI NaiMing MA Jing XIAO AYang | 2011 | Science China(Information Sciences)2011，54，10： | 8 |
| 4 | An optimal one-way cooperative strategy for two defenders against an attacking missile显示文摘This paper investigates a cooperative strategy for protecting an aerial target.The problem is solved as a game among four players(a target,two defenders,and a missile).In this scenario,the target launches two defenders(defender-1 and defender-2)simultaneously,to establish a oneway cooperation system(OCS)against an attacking missile.A new optimal evasion strategy for the target is also derived.During the engagement,the target takes into account the reaction of the attacking missile,and guides defender-1 to the interception point by receiving information from defender-1.Depending on the control effort of the target,defender-2 can choose appropriate launch conditions and use very limited maneuvering capability to intercept the missile.For adversaries with first-order dynamics,simulation results show that the OCS allows two defenders to intercept the missile.During the engagement,even if one defender or communication channel is broken,the OCS still allows an interception to be made,thus increasing the target’s survivability. | Qilong SUN Naiming QI Zheyao XU Yanfang LIU Yong ZHANG | 2017 | Chinese Journal of Aeronautics2017，30，4： | 6 |
| 5 | Evasion and pursuit guidance law against defended target显示文摘This paper investigates a new approach for a scenario in which an Attacker attempts to intercept a defended aerial Target. The problem is formulated as a game among three players, an Attacker, a Defender, and a Target, with bounded controls. In the considered pursuit–evasion problem, the Target uses an optimal evasion strategy and the Defender uses an optimal pursuit strategy.The proposed approach focuses on the miss distance as the outcome of the conflict. The infeasible region for the initial Zero-Effort-Miss(ZEM) distance between the Attacker and the Defender, for a scenario in which the Attacker evades the Defender, is analyzed, assuming that the Attacker uses a control effort chosen from the permitted control region. The sufficient conditions are investigated under which, for ideal players, the Attacker can pursue the Target while evading the Defender launched by the Target. The guidance provided on how the Attacker can accomplish the task is divided into two parts. During the final time between the Attacker and the Defender, the Attacker chooses the control effort that guarantees the miss distance, and then uses the optimal pursuit strategy to accomplish the task. The derived guidance law is verified by nonlinear simulation. | Naiming QI Qilong SUN Jun ZHAO | 2017 | Chinese Journal of Aeronautics2017，30，6： | 5 |
| 6 | Guidance laws for attacking defended target显示文摘In this paper,two new guidance laws based on differential game theory are proposed and investigated for the attacker in an attacker-defender-target scenario.The conditions for the attacker winning the game are analyzed when the target and defender using the differential game guidance law based on the linear model.The core ideas underlying the two guidance laws are the attacker evading to a critical safe boundary from the defender,and then maintaining a critical miss distance.The guidance law more appropriate for the attacker to win the game differs according to the initial parameters.Unlike other guidance laws,when using the derived guidance laws there is no need to know the target and the defender’s control efforts.The results of numerical simulations show that the attacker can evade the defender and hit the target successfully by using the proposed derived guidance laws. | Qilong SUN Chenfeng ZHANG Ning LIU Weixue ZHOU Naiming QI | 2019 | Chinese Journal of Aeronautics2019，32，10： | 4 |
| 7 | Fast cooperative trajectory optimization and test verification for close-range satellite formation using Finite Fourier Series method显示文摘The process of formation reconfiguration for close-range satellite formation should take into account the risk of collisions between satellites.To this end,this paper presents a method to rapidly generate low-thrust collision-avoidance trajectories in the formation reconfiguration using Finite Fourier Series(FFS).The FFS method can rapidly generate the collision-avoidance threedimensional trajectory.The results obtained by the FFS method are used as an initial guess in the Gauss Pseudospectral Method(GPM)solver to verify the applicability of the results.Compared with the GPM method,the FFS method needs very little computing time to obtain the results with very little difference in performance index.To verify the effectiveness,the proposed method is tested and validated by a formation control testbed.Three satellite simulators in the testbed are used to simulate two-dimensional satellite formation reconfiguration.The simulation and experimental results show that the FFS method can rapidly generate trajectories and effectively reduce the risk of collision between satellites.This fast trajectory generation method has great significance for on-line,constantly satellite formation reconfiguration. | Mingying HUO Zichen FAN Naiming QI Zhiguo SONG Xin SHI | 2020 | Chinese Journal of Aeronautics2020，33，8： | 3 |
| 8 | ANALYSIS OF METHOD FOR DETERMINING AZIMUTH OF PRINCIPAL AXIS OF INERTIA BASED ON DYNAMIC BALANCE MEASUREMENT显示文摘一个旋转目标的动态平衡质量是一个重要因素为运动维持稳定性和精确性。惯性的主要的轴的方位角是动态平衡的一个主要符号。一个平常的方法在一台旋转惯性机器上相对一些基础坐标正在是惯性矩阵的时刻以便计算惯性的主要的轴的方位角。由使用测量失衡二上的结果在一架垂直难适用双飞机上整修了飞机夫妇的动态平衡机器,尺寸和方向失衡能被发现。为惯性的主要的轴的一个方位角角度公式被使用导出并且被解决失衡数量。实验显示那个方法基于动态平衡测量被证明合理、有效并且有好精确。 | ZHAO Jun GUAN Yingzi QI Naiming | 2006 | Chinese Journal of Mechanical Engineering2006，19，4： | 3 |
| 9 | Modeling of disturbance torque in an aerostatic bearings-based nano-satellite simulator显示文摘The disturbance torque of aerostatic bearings is in the same order of the reaction wheel, which causes difficulty in evaluation of the designed attitude control strategy of a nano-satellite based on the aerostatic bearing. Two approaches are proposed to model the disturbance torque. Firstly, the gravity induced moment,the vortex torque, and the damping moment are modeled separately. However, the vortex torque and the damping moment are coupled with each other as both of them are caused by the viscosity. In the second approach, the coupling effect is considered. A nano-satellite is constructed based on aerostatic bearing. The time history of the free rotation rate from an initial speed is measured by the gyro, which is further used to calculate the rotation angle and acceleration. The static vortex torque is measured via the removable micro-torque measurement system. Based on these data, the model parameters are identified and modeling errors are presented. Results show that the second model is more precise.The root mean squire error is less than 0.5×10^(-4) N·m and the relative error of the static vortex torque is 0.16%. | LIU Yanfang HUO Mingying QI Naiming | 2018 | Journal of Systems Engineering and Electronics2018，29，3： | 1 |
| 10 | Capture condition for endo-atmospheric interceptors steered by ALCS and ARCS显示文摘这贡献为飞行器电梯的控制系统(ALCS ) 和态度反应喷气控制系统(弧) 驾驶的阻止的人导弹处理俘获状况。与法律从围住的微分比赛明确的表达导出的指导,俘获地区的存在状况为阻止的人有的盒子被学习可操作性上的优点和活泼上的劣势。为开的俘获地区的存在,在约会终止以后,弧能仅仅关门。而且,也,在最小上贡献可操作性的需要要求了的弧珍视。如果,更多的燃料将被要求弧增加它对可操作性的贡献。最小的要求的燃料发生在二条曲线的正切点:批评参数的曲线和一条候选人限制曲线,它甚至为复杂燃料也真抑制。这些结果的有效性被模拟也表明。 | Yanfang LIU Naiming Qi Tianye WANG | 2014 | Control Theory and Technology2014，12，1： | 1 |
| 11 | Ground- based space microgravity simulation test method overview 显示文摘 | QI Naiming ZHANG Wenhui GAO Jiuzhou | 2011 | Aerospace Control2011，29，3： | 1 |
| 12 | Coupled attitude-vibration analysis of an E-sail using absolute nodal coordinate formulation显示文摘In this study,the effects of solar wind on an electric sail(E-sail)are modeled and analyzed using an absolute nodal coordinate formulation(ANCF).First,the thrust of the charged metal tether that makes up the E-sail was analyzed and a model was established.Numerical simulations of a single metal tether were performed.Then,an overall E-sail model was established using the connection matrix,and E-sails subjected to different angular velocities were compared.Simulation results of the ANCF model and a dumbbell model were compared at different angular velocities.The results confirm that with a relatively high angular velocity,the flexible metal chain can be approximately regarded as a rigid body.However,with a small angular velocity,the flexibility of the metal chain cannot be ignored. | Ce Zhao Mingying Huo Ji Qi Shilei Cao Dongfang Zhu Lujun Sun Hongli Sun Naiming Qi | 2020 | Astrodynamics2020，4，3： | 0 |
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