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There are five Lagrange points for the Sun–Earth system, and five different Lagrange points for the Earth–Moon system. L 1, L 2, and L 3 are on the line through the centers of the two large bodies, while L 4 and L 5 each act as the third vertex of an equilateral triangle formed with the centers of the two large bodies.
Sun–Earth L 1: NASA: Planned for launch in early 2025. Space Weather Follow On - Lagrange 1 (SWFO-L1) Sun–Earth L 1: NOAA: Planned for launch in early 2025 as a rideshare to IMAP. Planetary Transits and Oscillations of stars (PLATO) Sun–Earth L 2: ESA: Planned for launch in 2026 for an initial six-year mission. [55] Space Infrared ...
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.
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 ...
Ignoring the influence of other Solar System bodies, Earth's orbit, also called Earth's revolution, is an ellipse with the Earth–Sun barycenter as one focus with a current eccentricity of 0.0167. Since this value is close to zero, the center of the orbit is relatively close to the center of the Sun (relative to the size of the orbit).
The five equilibrium points of the circular problem are known as the Lagrangian points. See figure below: Restricted three-body problem. In the restricted three-body problem math model figure above (after Moulton), the Lagrangian points L 4 and L 5 are where the Trojan planetoids resided (see Lagrangian point); m 1 is the Sun and m 2 is Jupiter.
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To escape the Solar System from a location at a distance from the Sun equal to the distance Sun–Earth, but not close to the Earth, requires around 42 km/s velocity, but there will be "partial credit" for the Earth's orbital velocity for spacecraft launched from Earth, if their further acceleration (due to the propulsion system) carries them ...