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In the paper, an improved nonsingular fast terminal sliding mode (INFTSM) guidance law with impact angle constraints is proposed. The guidance law, which employs a double power reaching law and an attractor with negative exponential factor, has a fast speed no matter far from the sliding surface or approach. For the maneuvering targets, extended state observer is designed through which the unknown...
In this paper, in order to attack a fixed target and solve actuator saturation, an integrated guidance and control (IGC) scheme based on LESO and dynamic surface control algorithm with constrained terminal impact angle for missile pitch channel is proposed. Firstly, based on Coriolis theorem, an IGC model for pitch channel is established which does not assume that the initial velocity of the missile...
To control a slide to turn (STT) missile which attacks a ground moving target in the presence of input saturation, a three dimensional (3D) integrated guidance and control (IGC) law based on dynamic surface control and linear extended state observer (LESO) techniques is developed. Firstly, a novel 3D IGC model is built without assuming that the angle between line of sight (LOS) and missile velocity...
On the basis of nonlinear dynamic inversion theory, a novel scheme combining sliding-mode control and backstepping is proposed for missile attitude control. In order to handle matched and unmatched uncertainties caused by unmodeled dynamics and variations of aerodynamic coefficients, a linear extended state observer (LESO) is introduced to estimate the uncertainties and the evaluated errors are compensated...
In this paper, a planar guidance law accounting for second-order dynamics of missile autopilot and impact angle constraints is designed using backstepping method and nonsingular terminal sliding mode control (NTSM). Nonsingular terminal sliding mode was employed to drive the line of sight (LOS) angle to a desired impact angle in finite time without singularity. In backstepping design, some first-order...
A full building flow of simulation model was analyzed aiming at assessing credibility problem of simulation test for antiaircraft missile, and the works on credibility assessment of simulation within full life cycle such as concept model, data assessment, simulation model, simulation method etc. were presented. Based on the given condition and index of credibility assessment, consistency check methods...
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