Orbital elements

Orbital elements

Orbital elements refer to a set of parameters that describe the path of an object in orbit around another object. These parameters include inclination, right ascension of the ascending node, eccentricity, mean anomaly, argument of perigee, and mean motion. They can be calculated at a designated time using a TLE set. Additionally, the orbital elements can also represent the semi-major axis, eccentricity, inclination, right ascension of the ascending node, and argument of perigee.From: Multisensor Attitude Estimation [2019], Direct trajectory optimization framework for vertical takeoff and vertical landing reusable rockets: case study of two-stage rockets [2019]

The orbital motion of satellites

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Published in Martin Vermeer, Antti Rasila, Map of the World, 2019

Martin Vermeer, Antti Rasila

In advanced theory, the state of motion of the satellite is described using six so-called Kepler orbital elements, which may (slowly) evolve over time. See Figure 12.5 and Table 12.1. In Table 12.2 on page 169 again we see in light of examples, how the height of a satellite above the Earth's surface determines the satellite's orbital period P.

Direct trajectory optimization framework for vertical takeoff and vertical landing reusable rockets: case study of two-stage rockets

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Published in Engineering Optimization, 2019

Lin Ma, Kexin Wang, Zhijiang Shao, Zhengyu Song, Lorenz T. Biegler

The first stage of the rocket returns to the Earth and finally lands at a specified site at time after stage separation; thus, the terminal constraint of the first stage is given as follows: The second stage of the rocket finally delivers the payload to the desired orbit at time , and the terminal position and velocity of the second stage can be transformed into orbital elements. The terminal constraint of the second stage is hence defined as follows: where the orbital elements represent the semi-major axis, eccentricity, inclination, right ascension of the ascending node and argument of perigee, respectively. The true anomaly is left undefined because the exact location within the orbit is not constrained.

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The orbital motion of satellites

Direct trajectory optimization framework for vertical takeoff and vertical landing reusable rockets: case study of two-stage rockets