The design of mini-missiles(MMs)presents several novel challenges.The stringent mission requirement to reach a target with a certain precision imposes a high guidance precision.The miniaturization of the size of MMs m...The design of mini-missiles(MMs)presents several novel challenges.The stringent mission requirement to reach a target with a certain precision imposes a high guidance precision.The miniaturization of the size of MMs makes the design of the guidance,navigation,and control(GNC)have a larger-thanbefore impact on the main-body design(shape,motor,and layout design)and its design objective,i.e.,flight performance.Pursuing a trade-off between flight performance and guidance precision,all the relevant interactions have to be accounted for in the design of the main body and the GNC system.Herein,a multi-objective and multidisciplinary design optimization(MDO)is proposed.Disciplines pertinent to motor,aerodynamics,layout,trajectory,flight dynamics,control,and guidance are included in the proposed MDO framework.The optimization problem seeks to maximize the range and minimize the guidance error.The problem is solved by using the nondominated sorting genetic algorithm II.An optimum design that balances a longer range with a smaller guidance error is obtained.Finally,lessons learned about the design of the MM and insights into the trade-off between flight performance and guidance precision are given by comparing the optimum design to a design provided by the traditional approach.展开更多
Optimal gliding guidance for a guided bomb unit in the vertical plane is studied based on nonlinear dynamics and kinematics.The guidance law is designed under minimum energy loss index.To avoid the complexity in solvi...Optimal gliding guidance for a guided bomb unit in the vertical plane is studied based on nonlinear dynamics and kinematics.The guidance law is designed under minimum energy loss index.To avoid the complexity in solving two-point-boundary-value problems,the steady-state solutions of the adjoint states in regular equations are suggested to be used.With these considerations,a quasi-closed,optimal gliding guidance law is obtained.The guidance law is described by the angle of attack in a simple nonlinear equation.An iterative computation method can be easily used to get the optimal angle of attack.The further simplified direct computation algorithm for the optimal angle of attack is also given.The guidance properties are compared with those of maximum lift-to-drag angle of attack control.The simulation results demonstrate that the quasi-closed,optimal gliding guidance law can improve the gliding phase terminal performance with significant increase in the altitude and much little decrease in the speed.展开更多
临近空间高动态无人飞行器能够远程机动飞行,具有深远的战略意义,世界各军事大国对高动态无人飞行器的研究开展已久。再入段是高动态无人飞行器飞行的重要阶段,对飞行器的"神经中枢"——制导、导航与控制系统(guidance,naviga...临近空间高动态无人飞行器能够远程机动飞行,具有深远的战略意义,世界各军事大国对高动态无人飞行器的研究开展已久。再入段是高动态无人飞行器飞行的重要阶段,对飞行器的"神经中枢"——制导、导航与控制系统(guidance,navigation and control system,GNC)提出了严格的要求。分析了高动态无人飞行器在临近空间再入段飞行时GNC系统的体系结构、信息传递关系以及各子系统的任务功能,提出了再入过程中GNC系统的部分关键技术。展开更多
Aiming at the guidance problem under impact angle constraint for homing missile against ground targets,a new adaptive robust nonlinear terminal guidance law was proposed in this paper.According to nonlinear kinetic re...Aiming at the guidance problem under impact angle constraint for homing missile against ground targets,a new adaptive robust nonlinear terminal guidance law was proposed in this paper.According to nonlinear kinetic relationship between the missile and target in vertical plane,a mathematic model was formulated while the motion of target and the system structure perturbation were regarded as limited disturbances.Based on the ideas of zeroing the rate of line-of-sight(LOS)angle and the impact angular tracking error,a nonlinear control strategy was contrived to obtain adaptive robust guidance law by adopting Nussbaum-type gain technique under a desired impact angle.The stability of guidance system in finite time is strictly proven by using Lyapunov stability theory.Finally,the numerical simulation verifies the effectiveness of the proposed scheme.展开更多
为了实现复杂航天器导航、制导与控制(guidance navigation and control,GNC)系统的快速设计与仿真验证,加快GNC系统从算法设计到产品实现的过程,解决数字仿真与实物仿真一致性的问题,提出了一种基于星载软件在环的GNC快速原型仿真系统...为了实现复杂航天器导航、制导与控制(guidance navigation and control,GNC)系统的快速设计与仿真验证,加快GNC系统从算法设计到产品实现的过程,解决数字仿真与实物仿真一致性的问题,提出了一种基于星载软件在环的GNC快速原型仿真系统。通过虚拟GNC计算机处理器内核和硬件接口的方式实现星载GNC计算机原型,解决了快速原型仿真系统GNC软件代码与实物星载计算机软件代码的一致性;利用Simulink/Matlab进行航天器动力学/运动学建模和GNC系统测量部件及执行部件的数字化建模,基于实时扩展(real time extension,RTX)系统和功能硬件板卡实现数字化模型与实物的转化,解决数字仿真与实物仿真GNC系统内部接口特性、时序和逻辑一致性的问题。应用实例表明,基于星载软件在环的GNC快速原型仿真系统仿真数据与GNC半物理仿真系统仿真数据高度一致,证实了仿真系统设计的有效性;同时基于该仿真系统可以实现GNC系统软件、算法和单机产品的并行开发,缩短系统研制周期。展开更多
空间站在轨组装和长期运营阶段涉及到多飞行器独立飞行、飞行器间交会对接、多飞行器组合体融合控制、多飞行器分离过程控制和飞行器返回再入等复杂飞行任务,完整、真实的飞行模拟是必需且至关重要的.基于时间同步、实时数据交换的分布...空间站在轨组装和长期运营阶段涉及到多飞行器独立飞行、飞行器间交会对接、多飞行器组合体融合控制、多飞行器分离过程控制和飞行器返回再入等复杂飞行任务,完整、真实的飞行模拟是必需且至关重要的.基于时间同步、实时数据交换的分布式一体化仿真架构,设计了一种多飞行器协同的通用半物理制导、导航与控制(guidance,navigation and control,GNC)系统飞行模拟平台,可很好地满足复杂系统的飞行模拟需要.平台由若干灵活、可扩展的通用模拟器构成,单个模拟器通过配置可以实现任一飞行器的功能,能够独立对指定飞行器的全任务过程进行仿真.平台通过靶场仪器组B时间码(inter-range instramentation group-B,IRIG-B)信号进行时间同步,利用1553B总线完成动力学仿真数据实时交换,并在多模拟器之间通过协调机制实现热并网后进行协同仿真.该模拟平台成功应用于空间站飞行控制演练.展开更多
Although the channel-decoupling assumption is often used in design of three-dimensional guidance laws, it loses its rationality for aircrafts with strong kinematics coupling because body rotation arises. To overcome t...Although the channel-decoupling assumption is often used in design of three-dimensional guidance laws, it loses its rationality for aircrafts with strong kinematics coupling because body rotation arises. To overcome this trouble, a novel guiding method was proposed based on Lie-group. After a model of 3D guidance is formulated using vectors, the precision guidance with ending angular constraints can be transformed into a problem involving the relation between directional angles and rotational angular velocities of certain vectors. When the guidance model is imposed a SO(3)-based description, a novel 3D sliding mode guidance law with ending angular constraints can be developed via Lie-group control method and variable structure control theory. Finally, the feasibility and performance of the guidance law were shown by simulating the examples.展开更多
An optimum PN guidance law for maneuvering target is developed using optimal control theory.By estimating the target position and setting the cost function,the guidance law can be deduced even without knowing the miss...An optimum PN guidance law for maneuvering target is developed using optimal control theory.By estimating the target position and setting the cost function,the guidance law can be deduced even without knowing the missile lateral acceleration.Since the quadratic cost function can make a compromise between the miss distance and the control constraint,the optimum guidance law obtained is more general.Also,introduced line of sight rate as the input,a practical form of this guidance law is derived.The simulation results show the effectiveness of the guidance laws.展开更多
文摘The design of mini-missiles(MMs)presents several novel challenges.The stringent mission requirement to reach a target with a certain precision imposes a high guidance precision.The miniaturization of the size of MMs makes the design of the guidance,navigation,and control(GNC)have a larger-thanbefore impact on the main-body design(shape,motor,and layout design)and its design objective,i.e.,flight performance.Pursuing a trade-off between flight performance and guidance precision,all the relevant interactions have to be accounted for in the design of the main body and the GNC system.Herein,a multi-objective and multidisciplinary design optimization(MDO)is proposed.Disciplines pertinent to motor,aerodynamics,layout,trajectory,flight dynamics,control,and guidance are included in the proposed MDO framework.The optimization problem seeks to maximize the range and minimize the guidance error.The problem is solved by using the nondominated sorting genetic algorithm II.An optimum design that balances a longer range with a smaller guidance error is obtained.Finally,lessons learned about the design of the MM and insights into the trade-off between flight performance and guidance precision are given by comparing the optimum design to a design provided by the traditional approach.
文摘Optimal gliding guidance for a guided bomb unit in the vertical plane is studied based on nonlinear dynamics and kinematics.The guidance law is designed under minimum energy loss index.To avoid the complexity in solving two-point-boundary-value problems,the steady-state solutions of the adjoint states in regular equations are suggested to be used.With these considerations,a quasi-closed,optimal gliding guidance law is obtained.The guidance law is described by the angle of attack in a simple nonlinear equation.An iterative computation method can be easily used to get the optimal angle of attack.The further simplified direct computation algorithm for the optimal angle of attack is also given.The guidance properties are compared with those of maximum lift-to-drag angle of attack control.The simulation results demonstrate that the quasi-closed,optimal gliding guidance law can improve the gliding phase terminal performance with significant increase in the altitude and much little decrease in the speed.
文摘临近空间高动态无人飞行器能够远程机动飞行,具有深远的战略意义,世界各军事大国对高动态无人飞行器的研究开展已久。再入段是高动态无人飞行器飞行的重要阶段,对飞行器的"神经中枢"——制导、导航与控制系统(guidance,navigation and control system,GNC)提出了严格的要求。分析了高动态无人飞行器在临近空间再入段飞行时GNC系统的体系结构、信息传递关系以及各子系统的任务功能,提出了再入过程中GNC系统的部分关键技术。
基金Sponsored by Fundamental Science Foundation Grant of Northwestern Polytechnical University(JC201024)
文摘Aiming at the guidance problem under impact angle constraint for homing missile against ground targets,a new adaptive robust nonlinear terminal guidance law was proposed in this paper.According to nonlinear kinetic relationship between the missile and target in vertical plane,a mathematic model was formulated while the motion of target and the system structure perturbation were regarded as limited disturbances.Based on the ideas of zeroing the rate of line-of-sight(LOS)angle and the impact angular tracking error,a nonlinear control strategy was contrived to obtain adaptive robust guidance law by adopting Nussbaum-type gain technique under a desired impact angle.The stability of guidance system in finite time is strictly proven by using Lyapunov stability theory.Finally,the numerical simulation verifies the effectiveness of the proposed scheme.
文摘为了实现复杂航天器导航、制导与控制(guidance navigation and control,GNC)系统的快速设计与仿真验证,加快GNC系统从算法设计到产品实现的过程,解决数字仿真与实物仿真一致性的问题,提出了一种基于星载软件在环的GNC快速原型仿真系统。通过虚拟GNC计算机处理器内核和硬件接口的方式实现星载GNC计算机原型,解决了快速原型仿真系统GNC软件代码与实物星载计算机软件代码的一致性;利用Simulink/Matlab进行航天器动力学/运动学建模和GNC系统测量部件及执行部件的数字化建模,基于实时扩展(real time extension,RTX)系统和功能硬件板卡实现数字化模型与实物的转化,解决数字仿真与实物仿真GNC系统内部接口特性、时序和逻辑一致性的问题。应用实例表明,基于星载软件在环的GNC快速原型仿真系统仿真数据与GNC半物理仿真系统仿真数据高度一致,证实了仿真系统设计的有效性;同时基于该仿真系统可以实现GNC系统软件、算法和单机产品的并行开发,缩短系统研制周期。
文摘空间站在轨组装和长期运营阶段涉及到多飞行器独立飞行、飞行器间交会对接、多飞行器组合体融合控制、多飞行器分离过程控制和飞行器返回再入等复杂飞行任务,完整、真实的飞行模拟是必需且至关重要的.基于时间同步、实时数据交换的分布式一体化仿真架构,设计了一种多飞行器协同的通用半物理制导、导航与控制(guidance,navigation and control,GNC)系统飞行模拟平台,可很好地满足复杂系统的飞行模拟需要.平台由若干灵活、可扩展的通用模拟器构成,单个模拟器通过配置可以实现任一飞行器的功能,能够独立对指定飞行器的全任务过程进行仿真.平台通过靶场仪器组B时间码(inter-range instramentation group-B,IRIG-B)信号进行时间同步,利用1553B总线完成动力学仿真数据实时交换,并在多模拟器之间通过协调机制实现热并网后进行协同仿真.该模拟平台成功应用于空间站飞行控制演练.
基金Sponsored by the National Natural Science Foundation of China (60374006)
文摘Although the channel-decoupling assumption is often used in design of three-dimensional guidance laws, it loses its rationality for aircrafts with strong kinematics coupling because body rotation arises. To overcome this trouble, a novel guiding method was proposed based on Lie-group. After a model of 3D guidance is formulated using vectors, the precision guidance with ending angular constraints can be transformed into a problem involving the relation between directional angles and rotational angular velocities of certain vectors. When the guidance model is imposed a SO(3)-based description, a novel 3D sliding mode guidance law with ending angular constraints can be developed via Lie-group control method and variable structure control theory. Finally, the feasibility and performance of the guidance law were shown by simulating the examples.
文摘An optimum PN guidance law for maneuvering target is developed using optimal control theory.By estimating the target position and setting the cost function,the guidance law can be deduced even without knowing the missile lateral acceleration.Since the quadratic cost function can make a compromise between the miss distance and the control constraint,the optimum guidance law obtained is more general.Also,introduced line of sight rate as the input,a practical form of this guidance law is derived.The simulation results show the effectiveness of the guidance laws.
