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Pandemic influenza A (H1N1) has spread rapidly across the globe. In the event of pandemic influenza A (H1N1), decision-makers are required to act in the face of substantial uncertainties. Simulation models can be used...
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Landing footprint of an entry vehicle provides critical information for mission planning. Conventional methods calculate it through solving a family of multi-constraints optimal control problems. It is difficult to so...
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Parameters selection of support vector machine is the key issue that impacts its accurate performance. A method for support vector regression machine with standard particle swarm optimization (SPSO) algorithm is propo...
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This paper presents a method for extracting and recognizing the billet numbers according to the feature of each number. Its advantages lie in that no template image is required, the requirement to the number in the im...
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This paper proposed a H∞ based controller design method for MIMO system. We use the bound real lemma to design the controller when the reference model is given. The BMI (Bi-linear Matrix Inequality) problem is turned...
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In the process of billet detection and recognition, the self-adaptability research of billet character segmentation in the complex scene is a highly complicated intelligence problem. On account of a good many of facto...
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In this paper, an optimal guidance algorithm is proposed for atmospheric *** optimal guidance algorithm updates the reference trajectory to deal with the impact of disturbance by solving an optimal control problem ***...
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ISBN:
(纸本)9781467315241
In this paper, an optimal guidance algorithm is proposed for atmospheric *** optimal guidance algorithm updates the reference trajectory to deal with the impact of disturbance by solving an optimal control problem *** the strong nonlinear ascent dynamic, the optimal control problem is transformed into nonlinear programming problem by trajectory *** direct optimization method is implemented for this nonlinear programming *** a segment of the reference trajectory is updated by the optimal guidance *** to the small amount of the discrete nodes and the initial guess solution which is close to the optimization solution, the direct optimization method is fast enough to generate a new reference *** simulation for the Generic Hypersonic Vehicle model and scramjet engine is done for different cases of the aerodynamic coefficient *** results show the accuracy and the effectiveness of this optimal guidance algorithm.
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