A new three-dimensional missile guidance law to control the impact vector against a stationary target is proposed.The composite guidance law has two well-known components:Apollo descent guidance and trajectory shaping...A new three-dimensional missile guidance law to control the impact vector against a stationary target is proposed.The composite guidance law has two well-known components:Apollo descent guidance and trajectory shaping guidance.These respectively linear and planar guidance laws are combined to achieve a specified impact direction.The main idea is to define an impact plane and to steer the missile onto this plane using Apollo descent guidance while concurrently performing trajectory shaping with reference to the impact plane.The resulting guidance law is expressed by a single equation in vector form,which is straightforward to implement.Because it originates from an optimal formulation,the performance of the proposed technique is expected to be satisfactory.This is confirmed by comparative simulation runs,which also involve the method known as generalized explicit guidance.展开更多
A novel biased proportional navigation guidance （BPNG） law is proposed for the close approach phase, which aims to make the spacecraft rendezvous with the target in specific relative range and direction. Firstly, in...A novel biased proportional navigation guidance （BPNG） law is proposed for the close approach phase, which aims to make the spacecraft rendezvous with the target in specific relative range and direction. Firstly, in order to describe the special guidance requirements, the concept of zero effort miss vector is proposed and the dangerous area where there exists collision risk for safety consideration is defined. Secondly, the BPNG, which decouples the range control and direc- tion control, is designed in the line-of-sight （LOS） rotation coordinate system. The theoretical anal- ysis proves that BPNG meets guidance requirements quite well. Thirdly, for the consideration of fuel consumption, the optimal biased proportional navigation guidance （OBPNG） law is derived by solving the Schwartz inequality. Finally, simulation results show that BPNG is effective for the close approach with the ability of evading the dangerous area and OBPNG consumes less fuel compared with BPNG.展开更多
现有的standoff跟踪制导方法在进行机动目标跟踪时不能同时满足响应速度和稳态精度的要求.对用于航路跟踪的参考点制导法(RPG,Reference Point Guidance)进行改进,推导了无人机(UAV,Unmanned Aerial Vehicle)在跟踪机动目标时的横侧向...现有的standoff跟踪制导方法在进行机动目标跟踪时不能同时满足响应速度和稳态精度的要求.对用于航路跟踪的参考点制导法(RPG,Reference Point Guidance)进行改进,推导了无人机(UAV,Unmanned Aerial Vehicle)在跟踪机动目标时的横侧向制导规律.采用二阶非线性微分方程对UAV和目标相对距离的调节过程进行建模,在此基础上分析了改进后RPG的渐近稳定性.仿真结果表明,相比Lyapunov向量场(LVFG,Lyapunov Vector Field Guidance)和模型预测控制(MPC,Model-based Predictive Control)的制导方法,改进RPG的跟踪误差和时间乘以误差绝对值积分(ITAE,Integrated Time Absolute Error)指标均优于LVFG和MPC.因此,所提制导规律能够对机动目标的运动进行有效补偿,并具有更快的响应速度、更高的稳态精度和较好的实时性.展开更多
文摘A new three-dimensional missile guidance law to control the impact vector against a stationary target is proposed.The composite guidance law has two well-known components:Apollo descent guidance and trajectory shaping guidance.These respectively linear and planar guidance laws are combined to achieve a specified impact direction.The main idea is to define an impact plane and to steer the missile onto this plane using Apollo descent guidance while concurrently performing trajectory shaping with reference to the impact plane.The resulting guidance law is expressed by a single equation in vector form,which is straightforward to implement.Because it originates from an optimal formulation,the performance of the proposed technique is expected to be satisfactory.This is confirmed by comparative simulation runs,which also involve the method known as generalized explicit guidance.
基金co-supported by the National Natural Science Foundation of China(No.11372345)the National Basic Research Program of China(No.2013CB733100)
文摘A novel biased proportional navigation guidance （BPNG） law is proposed for the close approach phase, which aims to make the spacecraft rendezvous with the target in specific relative range and direction. Firstly, in order to describe the special guidance requirements, the concept of zero effort miss vector is proposed and the dangerous area where there exists collision risk for safety consideration is defined. Secondly, the BPNG, which decouples the range control and direc- tion control, is designed in the line-of-sight （LOS） rotation coordinate system. The theoretical anal- ysis proves that BPNG meets guidance requirements quite well. Thirdly, for the consideration of fuel consumption, the optimal biased proportional navigation guidance （OBPNG） law is derived by solving the Schwartz inequality. Finally, simulation results show that BPNG is effective for the close approach with the ability of evading the dangerous area and OBPNG consumes less fuel compared with BPNG.
文摘现有的standoff跟踪制导方法在进行机动目标跟踪时不能同时满足响应速度和稳态精度的要求.对用于航路跟踪的参考点制导法(RPG,Reference Point Guidance)进行改进,推导了无人机(UAV,Unmanned Aerial Vehicle)在跟踪机动目标时的横侧向制导规律.采用二阶非线性微分方程对UAV和目标相对距离的调节过程进行建模,在此基础上分析了改进后RPG的渐近稳定性.仿真结果表明,相比Lyapunov向量场(LVFG,Lyapunov Vector Field Guidance)和模型预测控制(MPC,Model-based Predictive Control)的制导方法,改进RPG的跟踪误差和时间乘以误差绝对值积分(ITAE,Integrated Time Absolute Error)指标均优于LVFG和MPC.因此,所提制导规律能够对机动目标的运动进行有效补偿,并具有更快的响应速度、更高的稳态精度和较好的实时性.
