This paper comprehensively analyzes the attitude pursuit guidance law whichis one of the simple guidance methods for strapdown homing guidance system. Via the analyticalsolution of attitude pursuit, limitations on the...This paper comprehensively analyzes the attitude pursuit guidance law whichis one of the simple guidance methods for strapdown homing guidance system. Via the analyticalsolution of attitude pursuit, limitations on the velocities of missile and target are presented. Theinfluence of damping, lagging and transfer parameter from rudder deviation to angle of attack onthe attitude pursuit guidance law is discussed by using Automatic Control Theory. It is concludedthat the velocities of missile and target should not be too large, and the stable loop of missilebody should have some damping when the missile guidance system has inherent lagging, and thetransfer parameter mentioned above should not be too large when the attitude pursuit guidance law isused.展开更多
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
The strapdown homing guidance system for some ammunition was mainly studied. A strong tracking Kalman filter was designed for the strapdown homing guidance system using the information measured by the strapdown homing...The strapdown homing guidance system for some ammunition was mainly studied. A strong tracking Kalman filter was designed for the strapdown homing guidance system using the information measured by the strapdown homing seeker to estimate relative movement variables between the ammunition and target. Then the optimal proportional law, which using the estimated information, guided the ammunition. Simulation results show that the designed strapdown homing guidance system with strong tracking Kalman filter can attack the maneuvering target effectively, and satisfy the performance index for the guided ammunition system.展开更多
文摘This paper comprehensively analyzes the attitude pursuit guidance law whichis one of the simple guidance methods for strapdown homing guidance system. Via the analyticalsolution of attitude pursuit, limitations on the velocities of missile and target are presented. Theinfluence of damping, lagging and transfer parameter from rudder deviation to angle of attack onthe attitude pursuit guidance law is discussed by using Automatic Control Theory. It is concludedthat the velocities of missile and target should not be too large, and the stable loop of missilebody should have some damping when the missile guidance system has inherent lagging, and thetransfer parameter mentioned above should not be too large when the attitude pursuit guidance law isused.
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The strapdown homing guidance system for some ammunition was mainly studied. A strong tracking Kalman filter was designed for the strapdown homing guidance system using the information measured by the strapdown homing seeker to estimate relative movement variables between the ammunition and target. Then the optimal proportional law, which using the estimated information, guided the ammunition. Simulation results show that the designed strapdown homing guidance system with strong tracking Kalman filter can attack the maneuvering target effectively, and satisfy the performance index for the guided ammunition system.
