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The moons wander azimuthally about the Lagrange points, with Polydeuces describing the largest deviations, moving up to 32° away from the Saturn–Dione L 5 point. One version of the giant impact hypothesis postulates that an object named Theia formed at the Sun–Earth L 4 or L 5 point and crashed into Earth after its orbit destabilized ...
Mission consists of two spacecraft, which were the first spacecraft to reach Earth–Moon Lagrangian points. Both moved through Earth–Moon Lagrangian points, and are now in lunar orbit. [34] [35] WIND: Sun–Earth L 2: NASA: Arrived at L 2 in November 2003 and departed April 2004. Gaia Space Observatory: Sun–Earth L 2: ESA: Launched 19 ...
Although the forces balance at these points, the first three points (the ones on the line between a certain large mass, e.g. a star, and a smaller, orbiting mass, e.g. a planet) are not stable equilibrium points. If a spacecraft placed at the Earth–Moon L 1 point is given even a slight nudge away from the equilibrium point, the spacecraft's ...
For example, it is possible to plot an orbit from high Earth orbit to Mars, passing close to one of the Earth's Trojan points. [ citation needed ] Collectively referred to as the Interplanetary Transport Network , these highly perturbative, even chaotic, orbital trajectories in principle need no fuel beyond that needed to reach the Lagrange ...
A halo orbit is a periodic, three-dimensional orbit associated with one of the L 1, L 2 or L 3 Lagrange points in the three-body problem of orbital mechanics.Although a Lagrange point is just a point in empty space, its peculiar characteristic is that it can be orbited by a Lissajous orbit or by a halo orbit.
The horizontal, or altitude-azimuth, system is based on the position of the observer on Earth, which revolves around its own axis once per sidereal day (23 hours, 56 minutes and 4.091 seconds) in relation to the star background. The positioning of a celestial object by the horizontal system varies with time, but is a useful coordinate system ...
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A two-line element set (TLE, or more rarely 2LE) or three-line element set (3LE) is a data format encoding a list of orbital elements of an Earth-orbiting object for a given point in time, the epoch. Using a suitable prediction formula, the state (position and velocity) at any point in the past or future can be estimated to some accuracy.