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- W3168996847 abstract "This paper evaluates a proposed hybrid analytical/numerical approach to launch-vehicle guidance for ascent to orbit injection. The feedback-guidance approach is based on a piecewise nearly analytic zero-order solution evaluated using a collocation method. The zero-order solution is then improved through a regular perturbation analysis, wherein the neglected dynamics are corrected in the first-order term. For real-time implementation, the guidance approach requires solving a set of small dimension nonlinear algebraic equations and performing quadrature. Assessment of performance and reliability are carried out through closed-loop simulation for a vertically launched 2-stage heavy-lift capacity vehicle to a low earth orbit. The solutions are compared with optimal solutions generated from a multiple shooting code. In the example the guidance approach delivers over 99.9 percent of optimal performance and terminal constraint accuracy." @default.
- W3168996847 created "2021-06-22" @default.
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- W3168996847 date "1992-08-10" @default.
- W3168996847 modified "2023-09-23" @default.
- W3168996847 title "A hybrid approach to near-optimal launch vehicle guidance" @default.
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- W3168996847 doi "https://doi.org/10.2514/6.1992-4304" @default.
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