依据弹道导弹被动段的测量信息,提出了发射点位置的初始解析估计方法,并在此基础上提出了弹道重构寻优估计策略及方法,进一步提高发射点位置估计精度,完成了方法的数值仿真验证,在中远程弹道导弹预警中有一定的参考价值.

在空间绳网的绳系组合体拖曳变轨运动控制中,系绳张力控制策略需要有一套卷扬机构及张力检测控制装置,将增加机构的质量、复杂度和成本,并降低操作可靠性.提出仅利用拖船飞行器上的三轴正交喷嘴控制策略,可同时实现拖曳离轨中的相对运动控制和系统质心的轨道控制,而系绳张力只作为约束,推导了组合体拖曳离轨的三维空间运动动力学模型,给出了一种准霍曼拖曳离轨控制方法,完成了同步轨道废弃目标拖曳离轨方案的初步可行性仿真验证,并给出了拖曳过程的喷气力、燃料消耗量指标,可供空间绳网研究参考.

针对导弹分导或多星发射中时序分离方式的不足,提出了一种让反推分离力同时参与闭环的组合控制策略及分离方法.通过建立分离动力学模型,运用MATLAB/Simulink软件对分离过程进行了数值仿真,并与最佳时序分离方法进行了比较,仿真结果表明反推分离力参与闭环的组合控制策略,在鲁棒性、方便性和安全性方面更有优越性,实现简单,在导弹分导与多星发射分离中具有参考和应用价值.

For the trajectory planning problem in hypersonic glide vehicle,a differential flatness based three-degree-of-freedom trajectory generation approach is proposed.Based on the flatness analysis of the simplified longitudinal motion model,the reference longitudinal trajectory planning problem was mapped into the flat output space to improve the solving efficiency by eliminating the dynamical constraints and reducing the design dimension.Then the initial problem was transformed into a nonlinear programming problem utilizing global polynomial approximations to the flat outputs.To compensate for the effects of the earth rotation and external disturbances,a Proportion-Differentiation control based reference trajectory tracking controller was designed with good convergence capability.By integrating the lateral motion determined by the error corridor of heading angle based bank angle revision,the three-degree-of-freedom gliding trajectory was ultimately generated.Numerical simulations were conducted to validate the feasibility and effectiveness of the approach presented here.

To eliminate the defects of traditional control method for spacecraft entering orbit with direct pin-point,on the basis of succeeding to the respective advantages of Saturn-5 IMG method and Space Shuttle LTG method,a direct pin-point orbital entry control method with large yaw self-adaptive capability was presented to suppress initial disturbance efficiently.Six degree of freedom numerical simulation shows that the method and its algorithm are simple and reliable,and non-linear iterative stability is good,the error of direct pin-point orbital entry is smaller than 5 km.By the proposed method,the spacecraft can be controlled to enter orbit with direct pin-point.

The magnitude of hinge moment is a prominent problem for rapid dive maneuver of hypersonic glide vehicles. A robust optimal integrated guidance law considering constraints of hinge moment and terminal impact angle is proposed with excellent performance. Based on the analogy relationship of hinge moment and normal aerodynamic load, the constraint of hinge moment is transformed to normal load constraint; and the optimal guidance law under nominal conditions is derived utilizing optimal control theory. A terminal sliding mode control based guidance modification is designed to eliminate the inevitable departure brought by uncertainties in finite time; and the hyperbolic tangent function is introduced to reduce the high-frequency chatting. The theoretical analysis and simulation results are conducted to illustrate the capability of the proposed integrated guidance law for hypersonic glide vehicle.

A manned spacecraft is supposed to have the capability of reentry and returning to the ground in emergency should a serious failure occurred during in orbit.In a rendezvous and docking mission,the orbit is adjusted continuously,where the traditional method of injecting return control parameters calculated on the ground cannot satisfy the emergency requirements.A design of autonomous emergency reentry strategy is offered to meet the demands of rendezvous and docking mission.After receiving the orbit measurement information for a period of time,the manned spacecraft would carry out orbit determination and prediction by simplifying the mean orbit elements algorithm,and then choose the appropriate landing site for emergency reentry through judging the situation of the pass-by landing area.The reentry parameters as well as the latitude and longitude of landing point can be calculated by the module trained through the artificial neural networks.

Decision-making behaviors with circular dependence are common phenomena in many areas including military decision problem.To cope with this problem,a framework for analysis and modeling of this kind of decision problems is proposed based on multi-agent influence diagram(MAID) and games,explicitly describing the competitive situation of military decision-making,accurately identifying the circular dependence relationships among decision variables and profoundly encoding the potential structural information in military decision problem.With case study,it is shown that this framework which is a new method for analysis and modeling of military decision problems has more virtues compared to existing methods.

The concept of Society Design Engineering is proposed as an engineering method to solve social problems and the framework for designing society is developed,which consists of five elements.The relationship of the elements is analyzed.Based on the framework,the formally description for the solution of society problem is presented.Through the analysis of the properties of society design problem,it seems that society design problems may not be solved by using approaches such as game theory or operations research.It may be solved using Society Design Engineering.

A method of determining the objective weight of expert based on linguistic set measure theory for linguistic multiple attribute group decision making is proposed.Following three principles as precise better than vague,minority subordinate to majority and distinguishing exactly better than roughly,the method extracts information of expert weight from multi-granularity linguistic assessment matrix,including the weight of individual assessment information amount,the weight of individual consistency with group and the weight of individual distinguishing capability.The methods of calculating these three weights are given.The total weight is calculated based on these three sub-weights.The numerical example illustrates the proposed method is feasible and effective.

Operation Process Reengineering is to drastically consider and redesign the operation process,so as to improve the operation strategy.Based on the Business Process Reengineering(BPR),the conception of Operation Process Reengineering(OPR) is presented,the extension of OPR is studied,and the flow to actualize OPR is developed.At last,an example is presented to illustrate the flow of OPR,which shows the feasibility of OPR.

Based on an analysis of the direction in which the column of an engineering crane may lose stability,a simplified model is established containing outstretched trusses and diagonal stay bars for a buckling analysis,on the basis of which a fundamental equation of column buckling is also derived.In this paper,numerical calculation examples are provided to verify the correctness of the method,the optimum length of the outstretched trusses is worked out,and the factors affecting the optimum length determination are discussed.A conclusion is reached based on the foregoing analysis that the minimum length coefficient for this type of column is two-thirds.

Focused on the problem of reusable launch vehicle(RLV) attitude control,an engineering attitude control system based on the classical control theory and BTT technology was designed.The angular rate and the acceleration were used as feedback signals controlled by the PI.Then,the mentioned attitude control system was applied to the condition of large/small side perturbation.The simulation results show that the proposed control system is easy to be implemented and has good engineering applicability because all the feedback variables can be measured directly.

Super-low frequency flexibility during motion is an important issue for a large space manipulator,,which involves not only the bending vibration of arm exists,but also the joint torsional vibration.In joint control,what is important is to stabilize and suppress low flexible vibration of joint and arm while joint position is being controlled.How gear ratio parameters for joint structure affect vibration suppression is also a required problem to analyze in joint design of space manipulator,on which gear ratio parameters depend.Combined dynamics of flexible joint and arm for space manipulator was modeled with concentrated parameter method,one strategy of suppressing joint vibration and arm vibration simultaneously was put forward,the effect of gear ratio on vibration suppression was analyzed by numerical simulation and theoretical analysis.This will be useful in design and research of large space flexible manipulator.

The theoretical analysis,modeling and numerical simulation of the KKV's hypervelocity impact damage to typical target were presented by means of basic conservation law of mass,momentum and energy,and software ANSYS/LS-DYNA.The KKV's impact damage effect to ballistic missile in condition of different attack angle and different distance of eccentric were analyzed,and the feasibility of the method were proven by simulation test.The result indicates that the KKV's impact damage database could be explored based on full-size modeling and simulation by using high-speed computer.

Space interception needs optimization initial guidance method which uses few propulsion and has high precision.Under the condition of engines' limited thrust,the task of initial guidance is real-time calculation of interceptor's attitude.This paper used self-adaptive guidance principles and relative dynamics methods to prove a optimization initial guidance law of space interception with limited thrust,and then,used a degree reduction iterate method to solve the problem of initial guidance with thrust and attitude errors.Results of simulations shown that under the conditions of 10% thrust error and 2 degrees attitude error,this guidance method led to high precision.The conclusions of this paper will be helpful to research on precise guidance methods of space interception.

随着运载火箭技术的不断发展,火箭的规模也越来越大,这导致火箭的结构纵向、局部振动频率和横向频率也越来越低,用于POGO抑制设计的安全频率窗口也变窄,一次充气式蓄压器的抑制装置已不能满足设计要求。为此对基于可变能量蓄压器的抑制技术进行了初步研究。

Near space waverider configuration hypersonic vehicle is a new kind of vehicle which has bright future. Reentry velocity and design parameters are main factors to influence its reentry trajectories. The perturbation atmosphere models were used to analyze the reentry trajectories of waverider configuration vehicle. The reentry simulations in perturbation and standard atmosphere models showed that changes of atmosphere parameters could influence the height, maximal load, maximal heat and total heat of trajectories. These factors should be considered while studying the vehicle's design parameters, structure parameters, heat shield system and guide navigate and control (GN&C) system.

Hypersonic vehicle with scramjet is a new kind of vehicle with bright future.With a study of its standard trajectories in half-velocity coordinate system,the fly velocity and design parameters were found to be the main factors to influence its skipping trajectories.The trajectory simulations in perturbation and standard atmosphere models showed that change of atmosphere parameters could influence the height,maximal load,maximal heat and total heat of trajectories.These factors should be considered while studying the vehicle design parameters,structure parameters,heat shield system and guide navigate and control(GNC) system.

《导弹总体设计与分析》是一门综合性课程,为了给国防工业部门和军队培养高水平的导弹技术人才,适应高技术战争的需要。通过本人在国外的留学调研和国内的教学实践,本文论述了课堂教学内容、教材引进与自编、教学方法与实践环节三个方面进行的改革和实践。