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- W2045202916 abstract "The classical orbital boundary-value problem provides a means of finding feasible orbits that pass through an initial position and a fixed target position. In this paper, a method is developed that extends the boundary-value problem and allows a choice of any combination of three of the following four target parameters: altitude, downrange angle, velocity, and flight-path angle. In addition, this method is adapted for use as a guidance algorithm for spacecraft in powered flight, and is implemented in a computer simulation of spacecraft trajectories. Two cases are studied: launch from the Earth's surface into low Earth orbit, and transfer from low Earth orbit to geosynchronous orbit. Results from the computer simulations indicate that extremely good targeting accuracy can be achieved, with resulting A V values very close to optimal for many cases. Overall, the technique developed herein provides a fast and straightforward means of generating a feasible trajectory that satisfies a chosen combination of target conditions. The technique is easy to implement and can be applied to a wide range of two-body, space-flight guidance problems." @default.
- W2045202916 created "2016-06-24" @default.
- W2045202916 creator A5078748554 @default.
- W2045202916 date "1986-01-01" @default.
- W2045202916 modified "2023-10-16" @default.
- W2045202916 title "A simple targeting technique for two-body spacecraft trajectories" @default.
- W2045202916 cites W1511057778 @default.
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- W2045202916 doi "https://doi.org/10.2514/3.20062" @default.
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