In this paper,a new homing guidance method is used to control the flying time and falling angle for guided missiles. Through this approach,it finds the approximate solution to the quadratic equation of time-togo,which...In this paper,a new homing guidance method is used to control the flying time and falling angle for guided missiles. Through this approach,it finds the approximate solution to the quadratic equation of time-togo,which is used for the formula derivation of the flying time control command. In this guidance law design,the acceleration rate control command is adopted. The guidance law is composed of a PN guidance command and a flying time control command. Firstly,it obtains a desired falling angle with accurate guidance. Secondly,it introduces to satisfy the constraint of flying time. The flying time control requires an assumption on the future evolution of missile,which is called time-to-go. To cope with the time-varying speed of missiles,a method of compensating the estimation of time-to-go is presented. The new guidance law is evaluated by using a simulation of typical terminal guidance for rocket-propelled torpedo. The simulation results show that the guidance achieves excellent control performance and exhibits insensitivity to initial trajectory parameter over a widen flight envelope.展开更多
主要介绍了基于M ATLAB/S im u link和D e lph i两种途径的鱼雷尾追式弹道的设计与仿真方法。首先给出鱼雷导引系统的数学模型,然后介绍如何应用S im u link建立系统的仿真模型并进行仿真计算,并使用D e lph i语言进行了仿真,最后给出...主要介绍了基于M ATLAB/S im u link和D e lph i两种途径的鱼雷尾追式弹道的设计与仿真方法。首先给出鱼雷导引系统的数学模型,然后介绍如何应用S im u link建立系统的仿真模型并进行仿真计算,并使用D e lph i语言进行了仿真,最后给出相应的仿真结果和分析。S im u link的仿真方法克服了其他传统编程语言如D e lph i仿真时繁杂、难度高、周期长的缺点,使动态系统的仿真变得容易、直观、迅捷。展开更多
文摘In this paper,a new homing guidance method is used to control the flying time and falling angle for guided missiles. Through this approach,it finds the approximate solution to the quadratic equation of time-togo,which is used for the formula derivation of the flying time control command. In this guidance law design,the acceleration rate control command is adopted. The guidance law is composed of a PN guidance command and a flying time control command. Firstly,it obtains a desired falling angle with accurate guidance. Secondly,it introduces to satisfy the constraint of flying time. The flying time control requires an assumption on the future evolution of missile,which is called time-to-go. To cope with the time-varying speed of missiles,a method of compensating the estimation of time-to-go is presented. The new guidance law is evaluated by using a simulation of typical terminal guidance for rocket-propelled torpedo. The simulation results show that the guidance achieves excellent control performance and exhibits insensitivity to initial trajectory parameter over a widen flight envelope.
文摘主要介绍了基于M ATLAB/S im u link和D e lph i两种途径的鱼雷尾追式弹道的设计与仿真方法。首先给出鱼雷导引系统的数学模型,然后介绍如何应用S im u link建立系统的仿真模型并进行仿真计算,并使用D e lph i语言进行了仿真,最后给出相应的仿真结果和分析。S im u link的仿真方法克服了其他传统编程语言如D e lph i仿真时繁杂、难度高、周期长的缺点,使动态系统的仿真变得容易、直观、迅捷。
