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- W1504705908 abstract "A technique for developing approximate optimal atmospheric guidance laws for gliding aerospace vehicles capable of performing aerodynamic maneuvers is examined. The Hamilton-Jacobi-Bellman equation is expanded in a series form in a small parameter /spl epsiv/. The optimal control is found for a class of dynamical systems that can be seperated into primary (zeroth-order) and perturbation dynamics with respect to the parameter /spl epsiv/. When an analytic solution to the zeroth-order problem (/spl epsiv/ = 0) is obtainable , higher order corrections for perturbation effects can be calculated and added to the zeroth-order control to form a control corrected for the effects of the perturbation dynamics. It so happens that the dynamical equations of motion of a gliding aerospace vehicle capable of aerodynamic maneuvering can be formulated in a primary plus perturbation form. Unlike certain previous expansion solutions, the dynamics here include all the terms associated with a spherical rotating planet. These terms appear in the perturbation portion of the dynamics, allowing for their respective corrections to the control. The expansion is made with respect to a small parameter that arises naturally as the ratio of the atmospheric scale height to the radius of the planet. The zeroth order problem, obtained when the small parameter is set to zero, corresponds to a solution of the problem where the aerodynamic forces dominate the inertial forces (all non-aerodynamic forces). Higher order terms in the expansion are determined from the solution of first-order linear, partial differential equations requiring only quadrature integration." @default.
- W1504705908 created "2016-06-24" @default.
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- W1504705908 date "2005-08-25" @default.
- W1504705908 modified "2023-09-25" @default.
- W1504705908 title "Development of approximate optimal atmospheric guidance laws for gliding aerospace vehicles" @default.
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- W1504705908 doi "https://doi.org/10.1109/iccon.1989.770557" @default.
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