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- W77453957 abstract "Analysis of entry dynamics was discussed in Chapter 2. It is the purpose of this chapter to discuss basic equations governing the flight mechanics before entry into a planetary atmosphere. When a vehicle approaches a planet in the absence of air, its orbital trajectory may be in the form of an ellipse when its speed is less than (sqrt {2gr,})*, a parabola when its speed is equal to (sqrt {2gr,}), or a hyperbola when its speed is greater than (sqrt {2gr,}), the basic equations** are (see References 1, 2, 3). $$eqalign{frac{{{d^2}r}}{{d{t^2}}} - r{left( {frac{{dtheta }}{{dt}}} right)^2} = - g cr rfrac{{{d^2}theta }}{{d{t^2}}} + 2left( {frac{{dr}}{{dt}}} right)left( {frac{{dtheta }}{{dt}}} right) = 0 cr}$$" @default.
- W77453957 created "2016-06-24" @default.
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- W77453957 date "1968-01-01" @default.
- W77453957 modified "2023-09-25" @default.
- W77453957 title "Orbital and Celestial Mechanics" @default.
- W77453957 cites W646966733 @default.
- W77453957 doi "https://doi.org/10.1007/978-3-642-48927-3_4" @default.
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