Sphere of influence (astrodynamics) explained

A sphere of influence (SOI) in astrodynamics and astronomy is the oblate-spheroid-shaped region where a particular celestial body exerts the main gravitational influence on an orbiting object. This is usually used to describe the areas in the Solar System where planets dominate the orbits of surrounding objects such as moons, despite the presence of the much more massive but distant Sun.

In the patched conic approximation, used in estimating the trajectories of bodies moving between the neighbourhoods of different bodies using a two-body approximation, ellipses and hyperbolae, the SOI is taken as the boundary where the trajectory switches which mass field it is influenced by. It is not to be confused with the sphere of activity which extends well beyond the sphere of influence.^[1]

Models

The most common base models to calculate the sphere of influence is the Hill sphere and the Laplace sphere, but updated and particularly more dynamic ones have been described.^{[2] [3]} The general equation describing the radius of the sphere

r _{SOI} of a planet:^[4] $$r\_\backslash text\; \backslash approx\; a\backslash left(\backslash frac\backslash right)^$$wherea is the semimajor axis of the smaller object's (usually a planet's) orbit around the larger body (usually the Sun).m and M are the masses of the smaller and the larger object (usually a planet and the Sun), respectively.

In the patched conic approximation, once an object leaves the planet's SOI, the primary/only gravitational influence is the Sun (until the object enters another body's SOI). Because the definition of r_SOI relies on the presence of the Sun and a planet, the term is only applicable in a three-body or greater system and requires the mass of the primary body to be much greater than the mass of the secondary body. This changes the three-body problem into a restricted two-body problem.

Table of selected SOI radii

The table shows the values of the sphere of gravity of the bodies of the solar system in relation to the Sun (with the exception of the Moon which is reported relative to Earth):^[4]

Body	SOI			Body Diameter		Body Mass (10^24 kg)	Distance from Sun
	(10^6 km)	(mi)	(radii)	(km)	(mi)		(AU)	(10^6 mi)	(10^6 km)
Mercury	0.117	72,700	46	4,878	3,031	0.33	0.39	36	57.9
Venus	0.616	382,765	102	12,104	7,521	4.867	0.723	67.2	108.2
Earth + Moon	0.929	577,254	145	12,742 (Earth)	7,918 (Earth)	5.972 (Earth)	1	93	149.6
Moon (Luna)	0.0643	39,993	37	3,476	2,160	0.07346	See Earth + Moon
Mars	0.578	359,153	170	6,780	4,212	0.65	1.524	141.6	227.9
Jupiter	48.2	29,950,092	687	139,822	86,881	1900	5.203	483.6	778.3
Saturn	54.5	38,864,730	1025	116,464	72,367	570	9.539	886.7	1,427.0
Uranus	51.9	32,249,165	2040	50,724	31,518	87	19.18	1,784.0	2,871.0
	86.2	53,562,197	3525	49,248	30,601	100	30.06	2,794.4	4,497.1

An important understanding to be drawn from this table is that "Sphere of Influence" here is "Primary". For example, though Jupiter is much larger in mass than say, Neptune, its Primary SOI is much smaller due to Jupiter's much closer proximity to the Sun.

Increased accuracy on the SOI

The Sphere of influence is, in fact, not quite a sphere. The distance to the SOI depends on the angular distance

\theta from the massive body. A more accurate formula is given by^[4] $$r\_\backslash text(\backslash theta)\; \backslash approx\; a\backslash left(\backslash frac\backslash right)^\backslash frac$$

Averaging over all possible directions we get:$$\backslash overline\; =\; 0.9431\; a\backslash left(\backslash frac\backslash right)^$$

Derivation

Consider two point masses

A and B at locations r _{A} and r _{B} , with mass m _{A} and m _{B} respectively. The distance R = |r _{B-r} _{A|} separates the two objects. Given a massless third point C at location r _{C} , one can ask whether to use a frame centered on A or on B to analyse the dynamics of C .

Consider a frame centered on

A . The gravity of B is denoted as g _{B} and will be treated as a perturbation to the dynamics of C due to the gravity g _{A} of body A . Due to their gravitational interactions, point A is attracted to point B with acceleration a _{A} = (Gm _{B})/(R ^{3}) (r _{B-r} _{A)} , this frame is therefore non-inertial. To quantify the effects of the perturbations in this frame, one should consider the ratio of the perturbations to the main body gravity i.e. \chi _{A} = (|g _{B-a} _{A|})/(|g _{A|}) . The perturbation g _{B-a} _{A} is also known as the tidal forces due to body B . It is possible to construct the perturbation ratio \chi _{B} for the frame centered on B by interchanging A \leftrightarrow B .

	Frame A	Frame B
Main acceleration	g _{A}	g _{B}
Frame acceleration	a _{A}	a _{B}
Secondary acceleration	g _{B}	g _{A}
Perturbation, tidal forces	g _{B-a} _{A}	g _{A-a} _{B}
Perturbation ratio \chi	\chi _{A} = (|g _{B-a} _{A|})/(|g _{A|})	\chi _{B} = (|g _{A-a} _{B|})/(|g _{B|})

As C gets close to A , \chi _{A} → 0 and \chi _{B} → inf ty , and vice versa. The frame to choose is the one that has the smallest perturbation ratio. The surface for which \chi _{A} = \chi _{B} separates the two regions of influence. In general this region is rather complicated but in the case that one mass dominates the other, say m _{A} \ll m _{B} , it is possible to approximate the separating surface. In such a case this surface must be close to the mass A , denote r as the distance from A to the separating surface.

	Frame A	Frame B
Main acceleration	g _{A} = (G m _{A})/(r ^{2})	g _{B} ≈ (G m _{B})/(R ^{2}) + (G m _{B})/(R ^{3}) r ≈ (G m _{B})/(R ^{2})
Frame acceleration	a _{A} = (G m _{B})/(R ^{2})	a _{B} = (G m _{A})/(R ^{2}) ≈ 0
Secondary acceleration	g _{B} ≈ (G m _{B})/(R ^{2}) + (G m _{B})/(R ^{3}) r	g _{A} = (G m _{A})/(r ^{2})
Perturbation, tidal forces	g _{B-a} _{A} ≈ (G m _{B})/(R ^{3}) r	g _{A-a} _{B} ≈ (G m _{A})/(r ^{2})
Perturbation ratio \chi	\chi _{A} ≈ (m _{B})/(m _{A}) (r ^{3})/(R ^{3})	\chi _{B} ≈ (m _{A})/(m _{B}) (R ^{2})/(r ^{2})

The distance to the sphere of influence must thus satisfy (m _{B})/(m _{A}) (r ^{3})/(R ^{3}) = (m _{A})/(m _{B}) (R ^{2})/(r ^{2}) and so r = R\left( (m _{A})/(m _{B}) \right) ^{2/5} is the radius of the sphere of influence of body A

Gravity well

Gravity well is a metaphorical name for the sphere of influence, highlighting the gravitational potential that shapes a sphere of influence, and that needs to be accounted for to escape or stay in the sphere of influence.

See also

• Hill sphere
• Sphere of influence (black hole)
• Clearing the neighbourhood

General references

• Book: Bate , Roger R. . Donald D. Mueller . Jerry E. White . Fundamentals of Astrodynamics . 1971 . . New York . 0-486-60061-0 . 333–334 . registration .
• Book: Sellers , Jerry J. . Astore, William J. . Giffen, Robert B. . Larson, Wiley J. . Kirkpatrick, Douglas H.. Understanding Space: An Introduction to Astronautics. limited. 2nd. 2004. McGraw Hill. 0-07-294364-5. 228, 738.
• Book: Danby. J. M. A.. Fundamentals of celestial mechanics . 2003 . Willmann-Bell. Richmond, Va., U.S.A. . 0-943396-20-4 . 352–353. 2. ed., rev. and enlarged, 5. print..

External links

• Project Pluto

Notes and References

1. Souami . D. . Cresson . J. . Biernacki . C. . Pierret . F. . On the local and global properties of gravitational spheres of influence . Monthly Notices of the Royal Astronomical Society . 2020 . 496 . 4 . 4287–4297 . 2005.13059 . 10.1093/mnras/staa1520 .
2. Cavallari . Irene . Grassi . Clara . Gronchi . Giovanni F. . Baù . Giulio . Valsecchi . Giovanni B. . A dynamical definition of the sphere of influence of the Earth . Communications in Nonlinear Science and Numerical Simulation . Elsevier BV . 119 . 2023 . 1007-5704 . 10.1016/j.cnsns.2023.107091 . 107091. 2205.09340 . 2023CNSNS.11907091C . 248887659 .
3. Araujo . R. A. N. . Winter . O. C. . Prado . A. F. B. A. . Vieira Martins . R. . Sphere of influence and gravitational capture radius: a dynamical approach . Monthly Notices of the Royal Astronomical Society . Oxford University Press (OUP) . 391 . 2 . 2008-12-01 . 0035-8711 . 10.1111/j.1365-2966.2008.13833.x . 675–684. 2008MNRAS.391..675A . free . 11449/42361 . free .
4. Book: Seefelder, Wolfgang . 2002. Lunar Transfer Orbits Utilizing Solar Perturbations and Ballistic Capture. Munich. Herbert Utz Verlag. 76. 3-8316-0155-0. July 3, 2018.