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For the case of intercepting maneuvering target, A new nonlinear terminal guidance law with robustness is proposed by adopting nonlinear H∞ control theory. The mathematic model was built according to nonlinear kinematics relationship between missile and target whose acceleration as disturbance was introduced. Based on the terminal guidance law's measure of zeroing the line-of-sight angular rate and...
Morphing concepts for missiles have been a topic of current research interest in aerospace engineering. For the morphing wings technology of missile, a kind of autopilot design method is proposed by H∞ control theory. In order to have the better flight performance in the different regimes, the missile can automatically change the wings area symmetrically. The nonlinear dynamic model is established,...
For the case of a three-dimensional interception, a new continuous nonlinear H∞ guidance law with robustness is proposed. The mathematic model was built according to relationship between missile and target whose acceleration as disturbance was introduced and considering two-order autopilot dynamic. Based on the method of zeroing the rate of line-of-sight angle, a global nonlinear H∞ control strategy...
For the case of homing missile against ground fixed target, a new scheme of integrated guidance and autopilot design is proposed with impact angular constraint. An integrated guidance and control model in the pitch plane is formulated, by combining the relative relationship between homing missile and target and the dynamic of autopilot, where the information is obtained directly from the instrument...
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