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Three-dimensional terminal guidance law design problem of flight vehicle with terminal impact angle constraints is investigated in the paper. In order to improve the control performance of precision guided weapon in dive phase, a nonlinear guidance law with finite time convergence and terminal impact angle constrains is derived with non smooth control approach. Based on three-dimensional design model,...
A novel guidance law based on extended quadratic cost function is proposed to avoid losing performance index, which is commonly appeared when using cost function with quadratic form. Stochastic optimal guidance laws under target maneuver and target non-maneuver conditions are deducted and are validated by simulating in turn. The simulation results show that guidance trajectories based on extended...
Based on the linear time-varying relative motion equation and with consideration of the lateral acceleration limitation, the necessary boundary for controllable line-of-sight angular rate is obtained. With consideration of the dynamic time-delay property of missile autopilot, the necessary boundary for controllable line-of-sight angular rate of guidance system is analyzed. Moreover, the guidance law,...
Finite-time input-to-state stability (ISS) guarantees that for any bounded input, the system state will be bounded in finite time. This property better satisfies the demands of the terminal guidance system f or target maneuver rejection performance and convergence rate. In this paper, using the finite-time ISS theory, a novel guidance law is proposed for the interception of three-dimensional maneuvering...
Some missiles that attack targets at low velocity have no seekers, instead using preset target motion information measured by the launcher to independently predict the target's path and attack it. In this paper, a guidance law based on independently predicting target motion is presented. First, the missile-target kinematic model is established in the two-dimensional plane. Next, the guidance law is...
For the terminal guidance problem of missiles intercepting maneuvering target with impact angle constraint, autopilot lag and acceleration command saturation constraint, a constrained adaptive backstepping guidance law is developed based on a command filtered backstepping control method and adaptive control, and the second-order dynamics of missile autopilot with the external disturbance is considered...
This paper presents a new guidance law based on sliding-mode control and input-to-state stability (ISS) for approach and landing of a reusable launch vehicle (RLV). According to the idea of reference-trajectory guidance, the sliding mode surface is chosen to be a linear combination of the reference-trajectory tracking error and its rate, and a guidance law is designed to make the dynamics of the sliding...
For the missile-target relative motion equations in the three-dimensional space, a three-dimensional impact time control guidance law is proposed for multiple missiles in attacking a stationary or a slowly moving target. The engagement dynamics is decoupled approximately into the pitch channel and the yaw channel. In order to augment guidance robustness against changes of system parameters and external...
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