In celestial mechanics, the **Lagrangian points**, (also **Lagrange point**, **L-point**, or **libration point**) are the five stationary solutions of the circular restricted three-body problem. I.e. given two massive bodies in circular orbits around their common center of mass, there are five positions in space where a third body, of negligible mass, could be placed which would then maintain its position relative to the two massive bodies. As seen in a frame of reference which rotates with the same period as the two co-orbiting bodies, the gravitational fields of two massive bodies combined with the centrifugal force are in balance at the Lagrangian points, allowing the third body to be stationary relative to the first two bodies. In 1772, famed Italian mathematician, Joseph Louis Lagrange was working on the infamous “3 body problem” when he discovered an interesting quirk in the results. Originally, he had set out to discover a way to easily calculate the gravitational interaction between arbitrary numbers of bodies in a system, because Newtonian mechanics conclude that such a system results in the bodies orbiting chaotically until there is a collision, or a body is thrown out of the system so that equilibrium can be achieved. The logic behind this conclusion is that a system with one body is trivial, as it is merely static relative to itself; a system with two bodies is very simple to solve for, as the bodies orbit around their common center of gravity. However, once more than two bodies are introduced, the mathematics go crazy. A situation arises where you would have to calculate every gravitational interaction between every object at every point along its trajectory. Lagrange, however, wanted to make this simpler. He did so with a simple conclusion: “*the trajectory of an object is determined by finding a path that minimizes the action over time.*” This is found by subtracting the potential energy from the kinetic energy. With this way of thinking, Lagrange re-formulated the classical Newtonian mechanics to give rise to Lagrangian mechanics. With his new system of calculations, Lagrange’s work led him to hypothesize how a third body of negligible mass would orbit around two larger bodies which were already orbiting one another. This third body at specific points in it orbit would become stationary to one of its host bodies (planets), these points where named “Lagrangian points” in Lagrange's honor. In the more general case of elliptical orbits, there are no longer stationary *points* in the same sense: it becomes more of a Lagrangian “area” where the third body makes small odd-shaped orbits about the invisible Lagrangian point; these orbits are commonly referred to as *halo* orbits. The Lagrangian points constructed at each point in time as in the circular case form stationary elliptical orbits which are similar to the orbits of the massive bodies. This is due to the fact that Newton's second law, *p* = *m**v* (*p* the impulse, *m* the mass and *v* the velocity), remains invariant if force and position are scaled by the same factor. That a body at a Lagrangian point orbits with the same period as the two massive bodies in the circular case implies that it has the same ratio of gravitational force to radial distance as they do. This fact is independent of the circularity of the orbits, and it implies that the elliptical orbits traced by the Lagrangian points are solutions of the equation of motion of the third body. A diagram showing the five Lagrangian points in a two-body system The five Lagrangian points are labeled and defined as follows: ## L_{1}
The **L**_{1} point lies on the line defined by the two large masses M_{1} and M_{2}, and between them.
**Example:** An object which orbits the Sun more closely than the Earth would normally have a shorter orbital period than the Earth, but that ignores the effect of the Earth's own gravitational pull. If the object is directly between the Earth and the Sun, then the effect of the Earth's gravity is to weaken the force pulling the object towards the Sun, and therefore increase the orbital period of the object. The closer to Earth the object is, the greater this effect is. At the L_{1} point, the orbital period of the object becomes exactly equal to the Earth's orbital period. The Sun-Earth L_{1} is ideal for making observations of the Sun. Objects here are never shadowed by the Earth or the Moon. Solar and Heliospheric Observatory (SOHO) (NASA's site of SOHO project (*http://sohowww.nascom.nasa.gov/*)) is stationed in a halo orbit around L_{1}. The Earth-Moon L_{1} allows easy access to lunar and earth orbits with minimal Delta-v and would be ideal for a half-way manned space station for transporting cargo and personnel to the Moon and back.
## L_{2} The **L**_{2} point lies on the line defined by the two large masses, and beyond the smaller of the two.
**Example:** On the other side of the Earth, further away from the Sun, the orbital period of an object would normally be greater than that of the Earth. The extra pull of the Earth's gravity decreases the orbital period of the object, and at the L_{2} point that orbital period becomes equal to the Earth's. Sun-Earth L_{2} is a good spot for space-based observatories. Because an object around L2 will maintain the same orientation with respect to the Sun and Earth, shielding and calibration are much simpler. The Wilkinson Microwave Anisotropy Probe is already in orbit around the Sun-Earth L_{2}. The proposed James Webb Space Telescope will be placed at the Sun-Earth L_{2}. Earth-Moon L2 would be a good location for a communication satellite covering the Moon's far side. If M_{2} is much smaller than M_{1} then L_{1} and L_{2} are at approximately equal distances *r* from M_{2}, equal to the radius of the Hill sphere, given by: where *R* is the distance between the two bodies.. This distance can be described as being such that the orbital period corresponding to a circular orbit with this distance as radius around M_{2} in the absence of M_{1}, is that of M_{2} around M_{1}, divided by . Examples: - Sun and Earth: 1,500,000 km from the Earth
- Earth and Moon: 61,500 km from the Moon
## L_{3} The **L**_{3} point lies on the line defined by the two large masses, and beyond the larger of the two.
**Example:** A third Lagrangian point, L_{3}, exists on the opposite side of the Sun, a little further away from the Sun than the Earth is, where the combined pull of the Earth and Sun again causes the object to orbit with the same period as the Earth. When used with the Sun and the Earth as the two masses, the L_{3} point was a popular place to put a "Counter-Earth" in pulp science fiction and comic books.
## L_{4} and L_{5} The **L**_{4} and **L**_{5} points lie at the third point of an equilateral triangle with the base of the line defined by the two masses, such that the point is ahead of, or behind, the smaller mass in its orbit around the larger mass. L_{4} and L_{5} are sometimes called *triangular Lagrange points* or *Trojan points*.
**Example:** The Sun-Earth L_{4} and L_{5} points lie 60° ahead of and 60° behind the Earth in its orbit around the Sun.
## Stability The first three Lagrangian points are stable only in the plane perpendicular to the line between the two bodies. This can be seen most easily by considering the L_{1} point. A test mass displaced perpendicularly from the central line would feel a force pulling it back towards the equilibrium point. This is because the lateral components of the two masses' gravity would add to produce this force, whereas the components along the axis between them would balance out. However, if an object located at the L_{1} point drifted closer to one of the masses, the gravitational attraction it felt from that mass would be greater, and it would be pulled closer. (The pattern is very similar to that of tidal forces.) The L_{1} and L_{2} points have some practical value since, although a satellite would wander away if left to itself, a relatively modest effort at station-keeping can prevent it from doing so. More subtly, they serve as "gateways" to control the chaotic trajectories of the Interplanetary Superhighway. By contrast, L_{4} and L_{5} are stable equilibria (cf. attractor), provided the ratio of the masses M_{1}/M_{2} is > 24.96. This is the case for the Sun/Earth and Earth/Moon systems, though by a smaller margin in the latter. When a body at these points is perturbed, it moves away from the point, but the Coriolis force then acts, and bends the object's path into a stable, kidney bean-shaped orbit around the point (as seen in the rotating frame of reference). In the Sun-Jupiter system several thousand asteroids, collectively referred to as Trojan asteroids, are in such orbits. Other bodies can be found in the Sun-Saturn, Sun-Mars, Jupiter-Jovian satellite, and Saturn-Saturnian satellite systems. There are no known large bodies in the Sun-Earth system's Trojan points, but clouds of dust surrounding the L_{4} and L_{5} points were discovered in the 1950s. Clouds of dust, called Kordylewski clouds, even fainter than the notoriously weak gegenschein, are also present in the L_{4} and L_{5} of the Earth-Moon system.
## Examples The Earth's companion object 3753 Cruithne is in a somewhat Trojan-like orbit around the Earth, but not in the same manner as a true Trojan. Rather, it occupies one of two regular solar orbits, periodically alternating between the two due to close encounters with Earth. When the asteroid approaches Earth, it takes orbital energy from Earth and moves into a larger, higher energy orbit. Some time later, the Earth catches up with the asteroid (which is in a larger and slower orbit), at which time Earth takes the energy back and so the asteroid falls into a smaller, faster orbit and eventually catches Earth to begin the cycle anew. This has no noticeable impact on the length of the year, since Earth masses over 20 billion times more than 3753 Cruithne. Epimetheus and Janus, satellites of Saturn, have a similar relationship, though they are of similar masses and so actually exchange orbits with each other periodically. (Janus is roughly 4 times more massive, but still light enough for its orbit to be altered.) Another similar configuration is known as orbital resonance, in which orbiting bodies tend to have periods of a simple integer ratio, due to their interaction. The Saturnian moon Tethys has two smaller moons in its L_{4} and L_{5} points, Telesto and Calypso. The Saturnian moon Dione has the moon Helene in its L_{4} point. Tethys and Dione are hundreds of times more massive than their "escorts" (see the moons' articles for exact diameter figures, masses are not known in several cases), and Saturn is far more massive still, which makes the overall system stable. The L5 Society is a precursor of the National Space Society, and promoted the possibility of establishing a colony and manufacturing facility in orbit around the L_{4} and/or L_{5} points in the Earth-Moon system(see Space colonisation).
## See also ## External links |