Lagrangian point

In celestial mechanics, the Lagrangian points (/ləˈɡrɑːndʒiən/; also Lagrange points, L-points, or libration points) are positions in an orbital configuration of two large bodies where a small object effected only by gravity can maintain a stable position relative to the two large bodies. The Lagrange points mark positions where the combined gravitational pull of the two large masses provides precisely the centripetal force required to orbit with them. There are five such points, labeled L₁ to L₅, all in the orbital plane of the two large bodies. The first three are on the line connecting the two large bodies; the last two, L₄ and L₅, each form an equilateral triangle with the two large bodies. The two latter points are stable, which implies that objects can orbit around them in a rotating coordinate system tied to the two large bodies.

Several planets have satellites near their L₄ and L₅ points (trojans) with respect to the Sun, with Jupiter in particular having more than a million of these. Artificial satellites have been placed at L₁ and L₂ with respect to the Sun and Earth, and Earth and the Moon, for various purposes,^[1] and the Lagrangian points have been proposed for a variety of future uses in space exploration.

Lagrange points in the Sun–Earth system (not to scale)

History

The three collinear Lagrange points (L₁, L₂, L₃) were discovered by Leonhard Euler a few years before Lagrange discovered the remaining two.^[2]^[3]

In 1772, Joseph-Louis Lagrange published an "Essay on the three-body problem". In the first chapter he considered the general three-body problem. From that, in the second chapter, he demonstrated two special constant-pattern solutions, the collinear and the equilateral, for any three masses, with circular orbits.^[4]

Lagrange points

The five Lagrangian points are labeled and defined as follows:

The L₁ point lies on the line defined by the two large masses M₁ and M₂, and between them. It is the most intuitively understood of the Lagrangian points: the one where the gravitational attraction of M₂ partially cancels M₁'s gravitational attraction.

Explanation: An object that orbits the Sun more closely than Earth would normally have a shorter orbital period than Earth, but that ignores the effect of Earth's own gravitational pull. If the object is directly between Earth and the Sun, then Earth's gravity counteracts some of the Sun's pull on the object, and therefore increases the orbital period of the object. The closer to Earth the object is, the greater this effect is. At the L₁ point, the orbital period of the object becomes exactly equal to Earth's orbital period. L₁ is about 1.5 million kilometers from Earth.^[5]

The L₂ point lies on the line through the two large masses, beyond the smaller of the two. Here, the gravitational forces of the two large masses balance the centrifugal effect on a body at L₂.

Explanation: On the opposite side of Earth from the Sun, the orbital period of an object would normally be greater than that of Earth. The extra pull of Earth's gravity decreases the orbital period of the object, and at the L₂ point that orbital period becomes equal to Earth's. Like L₁, L₂ is about 1.5 million kilometers from Earth.

The L₃ point lies on the line defined by the two large masses, beyond the larger of the two.

Explanation: L₃ in the Sun–Earth system exists on the opposite side of the Sun, a little outside Earth's orbit but slightly closer to the Sun than Earth is. (This apparent contradiction is because the Sun is also affected by Earth's gravity, and so orbits around the two bodies' barycenter, which is, however, well inside the body of the Sun.) At the L₃ point, the combined pull of Earth and Sun again causes the object to orbit with the same period as Earth.

Gravitational accelerations at L₄

The L₄ and L₅ points lie at the third corners of the two equilateral triangles in the plane of orbit whose common base is the line between the centers of the two masses, such that the point lies behind (L₅) or ahead (L₄) of the smaller mass with regard to its orbit around the larger mass.

The triangular points (L₄ and L₅) are stable equilibria, provided that the ratio of M₁/M₂ is greater than 24.96.^{[note 1]}^[6] This is the case for the Sun–Earth system, the Sun–Jupiter system, and, by a smaller margin, the Earth–Moon system. When a body at these points is perturbed, it moves away from the point, but the factor opposite of that which is increased or decreased by the perturbation (either gravity or angular momentum-induced speed) will also increase or decrease, bending the object's path into a stable, kidney bean-shaped orbit around the point (as seen in the corotating frame of reference).

In contrast to L₄ and L₅, where stable equilibrium exists, the points L₁, L₂, and L₃ are positions of unstable equilibrium. Any object orbiting at L₁, L₂, or L₃ will tend to fall out of orbit; it is therefore rare to find natural objects there, and spacecraft inhabiting these areas must employ station keeping in order to maintain their position.

Natural objects at Lagrangian points

It is common to find objects at or orbiting the L₄ and L₅ points of natural orbital systems. These are commonly called "trojans"; in the 20th century, asteroids discovered orbiting at the Sun–Jupiter L₄ and L₅ points were named after characters from Homer's Iliad. Asteroids at the L₄ point, which leads Jupiter, are referred to as the "Greek camp", whereas those at the L₅ point are referred to as the "Trojan camp". See also Trojan (astronomy).

Other examples of natural objects orbiting at Lagrange points:

The Sun–Earth L₄ and L₅ points contain interplanetary dust and at least one asteroid, 2010 TK7, detected in October 2010 by Wide-field Infrared Survey Explorer (WISE) and announced during July 2011.^[7]^[8]
The Earth–Moon L₄ and L₅ points may contain interplanetary dust in what are called Kordylewski clouds; however, the Hiten spacecraft's Munich Dust Counter (MDC) detected no increase in dust during its passes through these points. Stability at these specific points is greatly complicated by solar gravitational influence.^[9]
Recent observations suggest that the Sun–Neptune L₄ and L₅ points, known as the Neptune trojans, may be very thickly populated,^[10] containing large bodies an order of magnitude more numerous than the Jupiter trojans.
Several asteroids also orbit near the Sun-Jupiter L₃ point, called the Hilda family.
The Saturnian moon Tethys has two smaller moons in its L₄ and L₅ points, Telesto and Calypso. The Saturnian moon Dione also has two Lagrangian co-orbitals, Helene at its L₄ point and Polydeuces at L₅. The moons wander azimuthally about the Lagrangian points, with Polydeuces describing the largest deviations, moving up to 32° away from the Saturn–Dione L₅ 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.
One version of the giant impact hypothesis suggests that an object named Theia formed at the Sun–Earth L₄ or L₅ points and crashed into Earth after its orbit destabilized, forming the Moon.
Mars has four known co-orbital asteroids (5261 Eureka, 1999 UJ7, 1998 VF31 and 2007 NS2), all at its Lagrangian points.
Earth's companion object 3753 Cruithne is in a relationship with Earth that is somewhat trojan-like, but that is different from a true trojan. Cruithne occupies one of two regular solar orbits, one of them slightly smaller and faster than Earth's, and the other slightly larger and slower. It periodically alternates between these two orbits due to close encounters with Earth. When it is in the smaller, faster orbit and approaches Earth, it gains orbital energy from Earth and moves up into the larger, slower orbit. It then falls farther and farther behind Earth, and eventually Earth approaches it from the other direction. Then Cruithne gives up orbital energy to Earth, and drops back into the smaller orbit, thus beginning the cycle anew. The cycle has no noticeable impact on the length of the year, because Earth's mass is over 20 billion (7010200000000000000♠2×10¹⁰) times more than that of 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.
In a binary star system, the Roche lobe has its apex located at L₁; if a star overflows its Roche lobe, then it will lose matter to its companion star.

Mathematical details

A contour plot of the effective potential due to gravity and the centrifugal force of a two-body system in a rotating frame of reference. The arrows indicate the gradients of the potential around the five Lagrange points—downhill toward them (red) or away from them (blue). Counterintuitively, the L₄ and L₅ points are the high points of the potential. At the points themselves these forces are balanced.

Visualisation of the relationship between the Lagrangian points (red) of a planet (blue) orbiting a star (yellow) anticlockwise, and the effective potential in the plane containing the orbit (grey rubber-sheet model with purple contours of equal potential).^[11]
Click for animation.

Lagrangian points are the constant-pattern solutions of the restricted three-body problem. For example, given two massive bodies in orbits around their common barycenter, there are five positions in space where a third body, of comparatively negligible mass, could be placed so as to maintain its position relative to the two massive bodies. As seen in a rotating reference frame that matches the angular velocity of the two co-orbiting bodies, the gravitational fields of two massive bodies combined with the minor body's centrifugal force are in balance at the Lagrangian points, allowing the smaller third body to be relatively stationary with respect to the first two.^[12]

L₁

The location of L₁ is the solution to the following equation, balancing gravitation and the centrifugal force:

{\frac {M_{1}}{(R-r)^{2}}}={\frac {M_{2}}{r^{2}}}+{\frac {M_{1}}{R^{2}}}-{\frac {r\left(M_{1}+M_{2}\right)}{R^{3}}}

where r is the distance of the L₁ point from the smaller object, R is the distance between the two main objects, and M₁ and M₂ are the masses of the large and small object, respectively. (The quantity in parentheses on the right is the distance of L₁ from the center of mass.) Solving this for r involves solving a quintic function, but if the mass of the smaller object (M₂) is much smaller than the mass of the larger object (M₁) then L₁ and L₂ are at approximately equal distances r from the smaller object, equal to the radius of the Hill sphere, given by:

r\approx R{\sqrt[{3}]{\frac {M_{2}}{3M_{1}}}}

This distance can be described as being such that the orbital period, corresponding to a circular orbit with this distance as radius around M₂ in the absence of M₁, is that of M₂ around M₁, divided by √3 ≈ 1.73:

T_{s,M_{2}}(r)={\frac {T_{M_{2},M_{1}}(R)}{\sqrt {3}}}.

L₂

The location of L₂ is the solution to the following equation, balancing gravitation and inertia:

{\frac {M_{1}}{(R+r)^{2}}}+{\frac {M_{2}}{r^{2}}}={\frac {M_{1}}{R^{2}}}+{\frac {r\left(M_{1}+M_{2}\right)}{R^{3}}}

with parameters defined as for the L₁ case. Again, if the mass of the smaller object (M₂) is much smaller than the mass of the larger object (M₁) then L₂ is at approximately the radius of the Hill sphere, given by:

r\approx R{\sqrt[{3}]{\frac {M_{2}}{3M_{1}}}}

L₃

The location of L₃ is the solution to the following equation, balancing gravitation and the centrifugal force:

{\frac {M_{1}}{(R-r)^{2}}}+{\frac {M_{2}}{(2R-r)^{2}}}=\left({\frac {M_{2}}{M_{1}+M_{2}}}R+R-r\right){\frac {M_{1}+M_{2}}{R^{3}}}

with parameters defined as for the L₁ and L₂ cases except that r now indicates how much closer L₃ is to the more massive object than the smaller object. If the mass of the smaller object (M₂) is much smaller than the mass of the larger object (M₁) then:

r\approx R{\frac {7M_{2}}{12M_{1}}}

L₄ and L₅

The reason these points are in balance is that, at L₄ and L₅, the distances to the two masses are equal. Accordingly, the gravitational forces from the two massive bodies are in the same ratio as the masses of the two bodies, and so the resultant force acts through the barycenter of the system; additionally, the geometry of the triangle ensures that the resultant acceleration is to the distance from the barycenter in the same ratio as for the two massive bodies. The barycenter being both the center of mass and center of rotation of the three-body system, this resultant force is exactly that required to keep the smaller body at the Lagrange point in orbital equilibrium with the other two larger bodies of system. (Indeed, the third body need not have negligible mass.) The general triangular configuration was discovered by Lagrange in work on the three-body problem.

Net radial acceleration of a point orbiting along the Earth-Moon line.

Radial acceleration

The radial acceleration a of an object in orbit at a point along the line passing through both bodies is given by:

a=-{\frac {GM_{1}}{r^{2}}}\operatorname {sgn}(r)+{\frac {GM_{2}}{(R-r)^{2}}}\operatorname {sgn}(R-r)+{\frac {G((M_{1}+M_{2})r-M_{2}R)}{R^{3}}}

Where r is the distance from the large body M₁. The terms in this function represent respectively: force from M₁; force from M₂; and centrifugal force. The points L₃, L₁, L₂ occur where the acceleration is zero — see chart at right.

Stability

Although the L₁, L₂, and L₃ points are nominally unstable, there are (unstable) periodic orbits called "halo" orbits around these points in a three-body system. A full n-body dynamical system such as the Solar System does not contain these periodic orbits, but does contain quasi-periodic (i.e. bounded but not precisely repeating) orbits following Lissajous-curve trajectories. These quasi-periodic Lissajous orbits are what most of Lagrangian-point space missions have used until now. Although they are not perfectly stable, a modest effort of station keeping keeps a spacecraft in a desired Lissajous orbit for a long time. Also, for Sun–Earth-L₁ missions, it is preferable for the spacecraft to be in a large-amplitude (100,000–200,000 km or 62,000–124,000 mi) Lissajous orbit around L₁ than to stay at L₁, because the line between Sun and Earth has increased solar interference on Earth–spacecraft communications. Similarly, a large-amplitude Lissajous orbit around L₂ keeps a probe out of Earth's shadow and therefore ensure a better illumination of its solar panels.

Solar System values

This table lists sample values of L₁, L₂, and L₃ within the solar system. Calculations assume the two bodies orbit in a perfect circle with separation equal to the semimajor axis and no other bodies are nearby. Distances are measured from the larger body's center of mass with L₃ showing a negative location. The percentage columns show how the distances compare to the semimajor axis. E.g. for the Moon, L₁ is located 7008326400000000000♠326400 km from Earth's center, which is 84.9% of the Earth-Moon distance or 15.1% in front of the Moon; L₂ is located 7008448900000000000♠448900 km from Earth's center, which is 116.8% of the Earth-Moon distance or 16.8% beyond the Moon; and L₃ is located 2991618300000000000♠−381700 km from Earth's center, which is 99.3% of the Earth-Moon distance or 0.7084% in front of the Moon's 'negative' position. The L₃ percent value has been magnified by 100.

Lagrangian points in Solar System
Body pair	Semimajor axis (SMA)	L1	1-L1/SMA %	L2	L2/SMA-1 %	L3	(1+L3/SMA)*100 %
Earth-Moon	7008384400000000000♠3.844×10⁸ m	7008326390000000000♠3.2639×10⁸ m	7001150900000000000♠15.09	7008448900000000000♠4.489×10⁸ m	7001167800000000000♠16.78	2991618320000000000♠−3.8168×10⁸ m	7001708400000000000♠70.84
Sun-Mercury	7010579090000000000♠5.7909×10¹⁰ m	7010576890000000000♠5.7689×10¹⁰ m	6999380600000000000♠0.3806	7010581300000000000♠5.813×10¹⁰ m	6999381500000000000♠0.3815	2989420910000000000♠−5.7909×10¹⁰ m	6996968300000000000♠0.0009683
Sun-Venus	7011108210000000000♠1.0821×10¹¹ m	7011107200000000000♠1.072×10¹¹ m	6999931500000000000♠0.9315	7011109220000000000♠1.0922×10¹¹ m	6999937300000000000♠0.9373	2988891790000000000♠−1.0821×10¹¹ m	6998142800000000000♠0.01428
Sun-Earth	7011149600000000000♠1.496×10¹¹ m	7011148110000000000♠1.4811×10¹¹ m	6999997000000000000♠0.997	7011151100000000000♠1.511×10¹¹ m	7000100400000000000♠1.004	2988850400000000000♠−1.496×10¹¹ m	6998175200000000000♠0.01752
Sun-Mars	7011227940000000000♠2.2794×10¹¹ m	7011226860000000000♠2.2686×10¹¹ m	6999474800000000000♠0.4748	7011229029999999999♠2.2903×10¹¹ m	6999476300000000000♠0.4763	2988772060000000000♠−2.2794×10¹¹ m	6997188200000000000♠0.001882
Sun-Jupiter	7011778340000000000♠7.7834×10¹¹ m	7011726450000000000♠7.2645×10¹¹ m	7000666700000000000♠6.667	7011832649999999999♠8.3265×10¹¹ m	7000697800000000000♠6.978	2988222090000000000♠−7.7791×10¹¹ m	7000556300000000000♠5.563
Sun-Saturn	7012142670000000000♠1.4267×10¹² m	7012136250000000000♠1.3625×10¹² m	7000449600000000000♠4.496	7012149280000000000♠1.4928×10¹² m	7000463500000000000♠4.635	2987857360000000000♠−1.4264×10¹² m	7000166700000000000♠1.667
Sun-Uranus	7012287070000000000♠2.8707×10¹² m	7012280110000000000♠2.8011×10¹² m	7000242099999999999♠2.421	7012294130000000000♠2.9413×10¹² m	7000246100000000000♠2.461	2987712940000000000♠−2.8706×10¹² m	6999254600000000000♠0.2546
Sun-Neptune	7012449840000000000♠4.4984×10¹² m	7012438340000000000♠4.3834×10¹² m	7000255700000000000♠2.557	7012461540000000000♠4.6154×10¹² m	7000260200000000000♠2.602	2987550170000000000♠−4.4983×10¹² m	6999300400000000000♠0.3004

Spaceflight applications

Sun–Earth

Sun–Earth L₁ is suited for making observations of the Sun–Earth system. Objects here are never shadowed by Earth or the Moon and, if observing Earth, always view the sunlit hemisphere. The first mission of this type was the International Sun Earth Explorer 3 (ISEE-3) mission used as an interplanetary early warning storm monitor for solar disturbances. Since June 2015, DSCOVR has orbited the L₁ point.

Sun–Earth L₂ is a good spot for space-based observatories. Because an object around L₂ will maintain the same relative position with respect to the Sun and Earth, shielding and calibration are much simpler. It is, however, slightly beyond the reach of Earth's umbra,^[13] so solar radiation is not completely blocked at L2. (Real spacecraft generally orbit around L2, avoiding partial eclipses of the Sun to maintain a constant temperature). From locations near L2, the Sun, Earth and Moon are relatively close together in the sky; this means that a large sunshade with the telescope on the dark-side can allow the telescope to cool passively to around 50 K – this is especially helpful for infrared astronomy and observations of the cosmic microwave background. The James Webb Space Telescope is due to be positioned at L2.

Sun–Earth L₃ was a popular place to put a "Counter-Earth" in pulp science fiction and comic books. Once space-based observation became possible via satellites^[14] and probes, it was shown to hold no such object. The Sun–Earth L₃ is unstable and could not contain a natural object, large or small, for very long. This is because the gravitational forces of the other planets are stronger than that of Earth (Venus, for example, comes within 0.3 AU of this L₃ every 20 months).

A spacecraft orbiting near Sun–Earth L₃ would be able to closely monitor the evolution of active sunspot regions before they rotate into a geoeffective position, so that a 7-day early warning could be issued by the NOAA Space Weather Prediction Center. Moreover, a satellite near Sun–Earth L₃ would provide very important observations not only for Earth forecasts, but also for deep space support (Mars predictions and for manned mission to near-Earth asteroids). In 2010, spacecraft transfer trajectories to Sun–Earth L₃ were studied and several designs were considered.^[15]

Missions to Lagrangian points generally orbit the points rather than occupy them directly.

Another interesting and useful property of the collinear Lagrangian points and their associated Lissajous orbits is that they serve as "gateways" to control the chaotic trajectories of the Interplanetary Transport Network.

Earth–Moon

Earth–Moon L₁ allows comparatively easy access to Lunar and Earth orbits with minimal change in velocity and this has as an advantage to position a half-way manned space station intended to help transport cargo and personnel to the Moon and back.

Earth–Moon L₂ would be a good location for a communications satellite covering the Moon's far side and would be "an ideal location" for a propellant depot as part of the proposed depot-based space transportation architecture.^[16]

The satellite ACE in an orbit around L₁

Sun–Venus

Scientists at the B612 Foundation are planning to use Venus's L₃ point to position their planned Sentinel telescope, which aims to look back towards Earth's orbit and compile a catalogue of near-Earth asteroids.^[17]

Lagrangian spacecraft and missions

Spacecraft at Sun–Earth L₁

International Sun Earth Explorer 3 (ISEE-3) began its mission at the Sun–Earth L₁ before leaving to intercept a comet in 1982. The Sun–Earth L₁ is also the point to which the Reboot ISEE-3 mission was attempting to return the craft as the first phase of a recovery mission (as of September 25, 2014 all efforts have failed and contact was lost).^[18]

Solar and Heliospheric Observatory (SOHO) is stationed in a halo orbit at L₁, and the Advanced Composition Explorer (ACE) in a Lissajous orbit. WIND is also at L₁.

Deep Space Climate Observatory (DSCOVR), launched on 11 February 2015, began orbiting L₁ on 8 June 2015 to study the solar wind and its effects on Earth.^[19] DSCOVR is unofficially known as GORESAT, because it carries a camera always oriented to Earth and capturing full-frame photos of the planet similar to the Blue Marble. This concept was proposed by then-Vice President of the United States Al Gore in 1998^[20] and was a centerpiece in his film An Inconvenient Truth.^[21]

LISA Pathfinder (LPF) was launched on 3 December 2015, and arrived at L₁ on 22 January 2016, where, among other experiments, it will test the technology needed by (e)LISA to detect gravitational waves. LISA Pathfinder uses an instrument consisting of two small gold alloy cubes.

Spacecraft at Sun–Earth L₂

Spacecraft at the Sun–Earth L₂ point are in a Lissajous orbit until decommissioned, when they are sent into a heliocentric graveyard orbit.

1 October 2001 – October 2010—Wilkinson Microwave Anisotropy Probe^[22]
November 2003 – April 2004—WIND, then it returned to Earth orbit before going to L₁ where it still remains
July 2009 – 29 April 2013—Herschel Space Telescope^[23]
3 July 2009 – 21 October 2013—Planck Space Observatory
25 August 2011 – April 2012—Chang'e 2,^[24]^[25] from where it travelled to 4179 Toutatis and then into deep space
January 2014 – 2018—Gaia Space Observatory
2018 — James Webb Space Telescope will use a halo orbit
2020 — Euclid Space Telescope
2024 — Wide Field Infrared Survey Telescope (WFIRST) will use a halo orbit
2028 — Advanced Telescope for High Energy Astrophysics (ATHENA) will use a halo orbit

Past and planned missions

Color key:
– Unflown or planned mission		– Mission en route or in progress (including mission extensions)		– Mission at Lagrangian point completed successfully (or partially successfully)

Mission	Lagrangian point	Agency	Description
International Sun–Earth Explorer 3 (ISEE-3)	Sun–Earth L₁	NASA	Launched in 1978, it was the first spacecraft to be put into orbit around a libration point, where it operated for four years in a halo orbit about the L₁ Sun–Earth point. After the original mission ended, it was commanded to leave L₁ in September 1982 in order to investigate comets and the Sun.^[26] Now in a heliocentric orbit, an unsuccessful attempt to return to halo orbit was made in 2014 when it made a flyby of the Earth–Moon system.^[27]^[28]
Advanced Composition Explorer (ACE)	Sun–Earth L₁	NASA	Launched 1997. Has fuel to orbit near L₁ until 2024. Operational as of 2016.^[29]
Deep Space Climate Observatory (DSCOVR)	Sun–Earth L₁	NASA	Launched on 11 February 2015. Planned successor of the Advanced Composition Explorer (ACE) satellite. Operational as of 2016.^[30]
LISA Pathfinder (LPF)	Sun–Earth L₁	ESA, NASA	Launched one day behind revised schedule (planned for the 100th anniversary of the publication of Einstein's General Theory of Relativity), on 3 December 2015. Arrived at L₁ on 22 January 2016.^[31]
Solar and Heliospheric Observatory (SOHO)	Sun–Earth L₁	ESA, NASA	Orbiting near L₁ since 1996. Operational as of 2017.^[32]
WIND	Sun–Earth L₁	NASA	Arrived at L₁ in 2004 with fuel for 60 years. Operational as of 2017.^[33]
Wilkinson Microwave Anisotropy Probe (WMAP)	Sun–Earth L₂	NASA	Arrived at L₂ in 2001. Mission ended 2010,^[34] then sent to solar orbit outside L₂.^[35]
Herschel Space Telescope	Sun–Earth L₂	ESA	Arrived at L₂ July 2009. Ceased operation on 29 April 2013; will be moved to a heliocentric orbit.^[36]^[37]
Planck Space Observatory	Sun–Earth L₂	ESA	Arrived at L₂ July 2009. Mission ended on 23 October 2013; Planck has been moved to a heliocentric parking orbit.^[38]
Chang'e 2	Sun–Earth L₂	CNSA	Arrived in August 2011 after completing a lunar mission before departing en route to asteroid 4179 Toutatis in April 2012.^[25]
Chang'e 5-T1 service module	Earth–Moon L₂	CNSA	Arrived in a Lissajous orbit with period of 14 days around the EM-L₂ point on November 27, 2014 after its primary mission, the re-entry demonstration of the sample return capsule was completed. It left the EM-L₂ orbit on January 4, 2015 and returned to lunar orbit on January 13.
ARTEMIS mission extension of THEMIS	Earth–Moon L₁ and L₂	NASA	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.^[39]^[40]
WIND	Sun–Earth L₂	NASA	Arrived at L₂ in November 2003 and departed April 2004.
Gaia Space Observatory	Sun–Earth L₂	ESA	Launched 19 December 2013. Operational as of 24 January 2017.^[41]^[42]

Future and proposed missions

Mission	Lagrangian point	Agency	Description
"Lunar Far-Side Communication Satellites"	Earth–Moon L₂	NASA	Proposed in 1968 for communications on the far side of the Moon during the Apollo program, mainly to enable an Apollo landing on the far side—neither the satellites nor the landing were ever realized.^[43]
Space colonization and manufacturing	Earth–Moon L₄ or L₅	—	First proposed in 1974 by Gerard K. O'Neill^[44] and subsequently advocated by the L5 Society.
James Webb Space Telescope (JWST)	Sun–Earth L₂	NASA, ESA, CSA	As of 2013, launch is planned for October 2018.^[45]
EQUULEUS	Earth-Moon L₂	University of Tokyo, JAXA	6U CubeSat, launch planned in 2019 as a secondary payload onboard SLS Exploration Mission 1.^[46]
Aditya	Sun–Earth L₁	ISRO	Launch planned for 2019–20; it will be going to a point 1.5 million kilometers away from Earth, from where it will observe the Sun constantly and study the solar corona, the region around the Sun's surface.^[47]
Euclid	Sun–Earth L₂	ESA, NASA	As of 2013, launch is planned in 2020.^[48]
Demonstration and Experiment of Space Technology for INterplanetary voYage (DESTINY)	Earth–Moon L₂	JAXA	Candidate for JAXA's next "Competitively-Chosen Medium-Sized Focused Mission", possible launch in the early 2020s.^[49]
Exploration Gateway Platform	Earth–Moon L₂^[50]	NASA	Proposed in 2011.^[51]
Wide Field Infrared Survey Telescope (WFIRST)	Sun–Earth L₂	NASA, USDOE	As of 2013, in a "pre-formulation" phase until at least early 2016; possible launch in the early 2020s.^[52]
LiteBIRD	Sun–Earth L₂^[53]	JAXA, NASA	As of 2015, one of two finalists for JAXA's next "Strategic Large Mission"; would be launched in 2024 if selected.^[54]
Planetary Transits and Oscillations of stars (PLATO)	Sun–Earth L₂	ESA	Planned for launch in 2024 for an initial six-year mission.^[55]
Space Infrared Telescope for Cosmology and Astrophysics (SPICA)	Sun–Earth L₂	JAXA, ESA, SRON	As of 2015, awaiting approval from both Japanese and European side, launch proposed for 2025.^[56]
Advanced Telescope for High Energy Astrophysics (ATHENA)	Sun–Earth L₂	ESA	Launch planned for 2028.^[57]

Notes

↑ Actually 25 + √621/2 ≈ 7001249599357944000♠24.9599357944

References

↑ One Year on Earth – Seen From 1 Million Miles on YouTube
↑ Koon, W. S.; Lo, M. W.; Marsden, J. E.; Ross, S. D. (2006). Dynamical Systems, the Three-Body Problem, and Space Mission Design. p. 9. (16MB)
↑ Euler, Leonhard (1765). De motu rectilineo trium corporum se mutuo attrahentium (PDF).
↑ Lagrange, Joseph-Louis (1867–92). "Tome 6, Chapitre II: Essai sur le problème des trois corps". Œuvres de Lagrange (in French). Gauthier-Villars. pp. 229–334.
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External links

Wikimedia Commons has media related to Lagrange points.

Joseph-Louis, Comte Lagrange, from Oeuvres Tome 6, "Essai sur le Problème des Trois Corps"—Essai (PDF); source Tome 6 (Viewer)
"Essay on the Three-Body Problem" by J-L Lagrange, translated from the above, in http://www.merlyn.demon.co.uk/essai-3c.htm.
Considerationes de motu corporum coelestium—Leonhard Euler—transcription and translation at http://www.merlyn.demon.co.uk/euler304.htm.
What are Lagrange points?—European Space Agency page, with good animations
Explanation of Lagrange points—Prof. Neil J. Cornish
A NASA explanation—also attributed to Neil J. Cornish
Explanation of Lagrange points—Prof. John Baez
Geometry and calculations of Lagrange points—Dr J R Stockton
Locations of Lagrange points, with approximations—Dr. David Peter Stern
An online calculator to compute the precise positions of the 5 Lagrange points for any 2-body system—Tony Dunn
Astronomy cast—Ep. 76: Lagrange Points Fraser Cain and Dr. Pamela Gay
The Five Points of Lagrange by Neil deGrasse Tyson
Earth, a lone Trojan discovered

Gravitational orbits

Types

General	Box Capture Circular Elliptical / Highly elliptical Escape Graveyard Hyperbolic trajectory Inclined / Non-inclined Osculating Parabolic trajectory Parking Synchronous semi sub Transfer orbit
Geocentric	Geosynchronous Geostationary Sun-synchronous Low Earth Medium Earth High Earth Molniya Near-equatorial Orbit of the Moon Polar Tundra
About other points	Areosynchronous Areostationary Halo Lissajous Lunar Heliocentric Heliosynchronous

Parameters

Shape Size	$e$ Eccentricity $a$ Semi-major axis $b$ Semi-minor axis $Q$ , $q$ Apsides
Orientation	$i$ Inclination $Ω$ Longitude of the ascending node $ω$ Argument of periapsis $ϖ$ Longitude of the periapsis
Position	$M$ Mean anomaly $ν$ True anomaly $E$ Eccentric anomaly $L$ Mean longitude $l$ True longitude
Variation	$T$ Orbital period $n$ Mean motion $v$ Orbital speed $t 0$ Epoch

Maneuvers

Orbital mechanics

List of orbits

Authority control	BNF: cb16258674h (data)

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