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Jacobi integral

The Jacobi integral, also known as the Jacobi constant, is a conserved quantity in celestial mechanics that arises in the circular restricted three-body problem (CR3BP), where two massive bodies orbit each other circularly and a third body of negligible mass moves under their gravitational influence.^[1] It combines kinetic and potential energy terms in a synodic (rotating) reference frame, expressed mathematically as C_J = \Omega^2 r^2 + \frac{2\mu_1}{r_1} + \frac{2\mu_2}{r_2} - v^2, where \Omega is the angular velocity of the rotating frame, r is the distance from the barycenter, \mu_1 and \mu_2 are the gravitational parameters of the primary bodies, r_1 and r_2 are distances from the third body to each primary, and v is the speed of the third body relative to the rotating frame.^[2] This integral remains constant along trajectories, providing a key tool for analyzing orbital dynamics without explicit time dependence.^[1] Named after the mathematician Carl Gustav Jacob Jacobi, the integral originated in his 1836 letter to the academies of Paris and Berlin, with a full publication in 1837, as an extension of William Rowan Hamilton's dynamical methods to time-dependent potentials in the three-body problem.^[3] Jacobi derived it by transforming to rotating coordinates for two fixed centers (approximating circular orbits) and applying a modified conservation principle, yielding a first integral for the system's equations of motion.^[3] Unlike the total energy, which is not conserved in the non-inertial rotating frame due to the motion of the primaries, the Jacobi integral is the sole known constant of motion in the CR3BP, enabling the separation of variables in certain formulations.^[1] Its significance lies in defining zero-velocity curves, regions where the third body's velocity vanishes for a given C_J value, which bound accessible orbital regions and influence stability analysis, as demonstrated in applications like the Pluto-Charon system. The integral can be derived via Lagrangian mechanics, where the Lagrangian L = T - V (with kinetic energy adjusted for rotation and effective potential V) leads to equations whose time derivative confirms conservation. In broader celestial mechanics, it facilitates studies of Lagrangian points, periodic orbits, and mission design in multi-body systems, such as Earth-Moon or Sun-Jupiter environments.^[1]

Background Concepts

Circular Restricted Three-Body Problem

The circular restricted three-body problem (CR3BP) models the motion of three point masses under mutual Newtonian gravitational attraction, where two primary bodies of masses m_1 and m_2 (with m_1 \geq m_2) orbit each other in circular paths around their common center of mass, and a third body of negligible mass m_3 \ll m_1, m_2 moves under the gravitational influence of the primaries without affecting their motion.^[4] This setup is applicable to systems such as the Sun-planet-asteroid or Earth-Moon-spacecraft, where the test particle's mass is insignificant compared to the primaries.^[2] Key assumptions include the primaries maintaining fixed circular orbits around the barycenter with constant angular speed in a common plane, the test particle having zero mass and thus exerting no gravitational perturbation on the primaries, and no additional forces acting on the test particle.^[4] These simplifications reduce the complexity of the general three-body problem while capturing essential dynamics relevant to celestial mechanics.^[2] Two primary coordinate systems are used: the inertial (sidereal) frame, which is non-rotating and centered at the barycenter with axes aligned such that the orbital plane lies in the \xi-\eta plane and the primaries start on the \xi-axis; and the rotating (synodic) frame, centered at the barycenter and rotating with the primaries' angular velocity, keeping the primaries at fixed positions.^[4]^[2] In the inertial frame, the equations of motion for the test particle at position (\xi, \eta, \zeta) are derived from Newton's law of gravitation, with the primaries' positions (\xi_1, \eta_1, \zeta_1) and (\xi_2, \eta_2, \zeta_2) evolving circularly over time:

\begin{aligned} \ddot{\xi} &= -\frac{\mu_1 (\xi - \xi_1)}{\rho_1^3} - \frac{\mu_2 (\xi - \xi_2)}{\rho_2^3}, \\ \ddot{\eta} &= -\frac{\mu_1 (\eta - \eta_1)}{\rho_1^3} - \frac{\mu_2 (\eta - \eta_2)}{\rho_2^3}, \\ \ddot{\zeta} &= -\frac{\mu_1 \zeta}{\rho_1^3} - \frac{\mu_2 \zeta}{\rho_2^3}, \end{aligned}

where \mu_1 = G m_1, \mu_2 = G m_2, \rho_1 = |\mathbf{r} - \mathbf{r}_1|, and \rho_2 = |\mathbf{r} - \mathbf{r}_2| are the distances from the test particle to each primary.^[4] The CR3BP, building on earlier work by Euler and Lagrange, was significantly advanced by Henri Poincaré in 1890 as a tractable simplification of the general three-body problem.^[5] In this context, the Jacobi integral serves as a conserved quantity that provides insight into the test particle's energy and accessible regions of phase space.^[2]

Rotating Reference Frames

In the circular restricted three-body problem (CR3BP), the synodic reference frame is a non-inertial coordinate system that rotates with constant angular velocity \omega about the barycenter of the two primary masses, keeping their positions fixed relative to the frame axes. The x-axis aligns with the line joining the primaries, the z-axis is perpendicular to the orbital plane along the angular momentum vector, and the y-axis completes the right-handed system. This rotation rate satisfies \omega^2 = G(m_1 + m_2)/d^3, where G is the gravitational constant, m_1 and m_2 are the primary masses (m_1 \geq m_2), and d is their fixed separation distance.^[6]^[5] In normalized units, the separation d = 1, the more massive primary m_1 is positioned at (- \mu, 0, 0), and the less massive m_2 at (1 - \mu, 0, 0), where the mass parameter is \mu = m_2 / (m_1 + m_2). Distances are scaled by d, masses by the total m_1 + m_2 (yielding the ratio \mu), and time by \sqrt{d^3 / G(m_1 + m_2)} such that the orbital period is $2\pi and \omega = 1. The transformation from inertial coordinates (x, y) to rotating coordinates (x', y') uses the rotation matrix for angle \theta = \omega t:

\begin{align} x' &= x \cos \theta - y \sin \theta, \\ y' &= x \sin \theta + y \cos \theta. \end{align}

This coordinate change accounts for the frame's rotation, leading to modified velocity and acceleration relations.^[5]^[6] Within the rotating frame, the dynamics incorporate two fictitious forces arising from the noninertial nature of the coordinates: the centrifugal force, which acts outward from the rotation axis as m \omega^2 \mathbf{\rho} (where \mathbf{\rho} is the perpendicular distance vector from the axis), and the Coriolis force, -2 m \boldsymbol{\omega} \times \mathbf{v}, where \mathbf{v} is the velocity relative to the rotating frame. These terms appear in the equations of motion as accelerations \boldsymbol{\omega} \times (\boldsymbol{\omega} \times \mathbf{r}) for the centrifugal effect (inward in the cross product form but outward in effective force) and -2 \boldsymbol{\omega} \times \mathbf{v} for Coriolis. In normalized units with \omega = 1 and planar motion, the Coriolis acceleration components are $2 \dot{y} in the x-direction and -2 \dot{x} in the y-direction, while centrifugal contributes x and y terms.^[7]^[5] The use of the rotating frame offers key advantages for analyzing CR3BP dynamics: it eliminates time dependence in the primaries' positions, simplifying the equations of motion to autonomous form, and highlights relative equilibria such as the Lagrange points where the third body can remain stationary in the frame. This setup generalizes the problem across different mass ratios and separations without altering the normalized equations.^[6]^[8]

Mathematical Formulation

Definition in Synodic Coordinates

In the synodic coordinate system of the circular restricted three-body problem (CRTBP), the Jacobi integral, often denoted as the Jacobi constant C, serves as the sole conserved quantity for the motion of a negligible-mass third body under the influence of two primary masses.^[2] This frame rotates with the angular velocity of the primaries, fixing their positions relative to the origin at the barycenter.^[9] The explicit form of the Jacobi constant is given by

C = x^2 + y^2 + \frac{2(1 - \mu)}{r_1} + \frac{2\mu}{r_2} - (\dot{x}^2 + \dot{y}^2 + \dot{z}^2),

where (x, y, z) are the position coordinates of the third body, (\dot{x}, \dot{y}, \dot{z}) are its velocity components, \mu is the mass parameter defined as the ratio of the smaller primary's mass to the total mass of the primaries (\mu \leq 0.5), r_1 = \sqrt{(x + \mu)^2 + y^2 + z^2} is the distance to the larger primary located at (-\mu, 0, 0), and r_2 = \sqrt{(x - 1 + \mu)^2 + y^2 + z^2} is the distance to the smaller primary at (1 - \mu, 0, 0).^[2]^[9] These coordinates and the associated quantities are nondimensionalized such that the primaries' separation is unity, their total mass is unity, and the mean motion (angular velocity) is unity, facilitating analysis across different systems like the Sun-Earth or Earth-Moon.^[2] This expression arises from twice the effective potential minus the squared speed in the rotating frame and can be interpreted as minus twice the total energy per unit mass of the third body in that frame, where the effective potential incorporates both gravitational and centrifugal contributions.^[9] Due to the autonomy of the equations of motion in the synodic frame—lacking explicit time dependence—the Jacobi constant remains invariant along any trajectory, constraining the third body's accessible phase space.^[2]^[9] For instance, at the collinear Lagrange points L1, L2, and L3, where velocities vanish, the Jacobi constant takes values on the order of 3 in normalized units (e.g., approximately 3.01 to 3.19 for the Earth-Moon system), delineating critical energy levels for orbital connectivity.^[2]

Definition in Sidereal Coordinates

In the sidereal coordinate system, which is an inertial frame fixed in space, the Jacobi integral manifests as a conserved quantity despite the time-dependent gravitational potential arising from the orbital motion of the two primary bodies. In nondimensional units with rotation rate n = 1, it is expressed as

C = 2\left( \frac{1-\mu}{r_1} + \frac{\mu}{r_2} \right) - (\dot{\xi}^2 + \dot{\eta}^2 + \dot{\zeta}^2) + 2(\xi \dot{\eta} - \eta \dot{\xi}),

where (\xi, \eta, \zeta) are the inertial position coordinates of the test particle, (\dot{\xi}, \dot{\eta}, \dot{\zeta}) are the corresponding inertial velocities, r_1 and r_2 are the distances from the test particle to the primary bodies at positions that rotate with angular rate n, \mu is the mass ratio of the secondary primary, and the term $2(\xi \dot{\eta} - \eta \dot{\xi}) represents twice the z-component of the specific angular momentum about the barycenter.^[10] The numerical value of the Jacobi constant is the same in both the sidereal and synodic frames.^[10] Although conserved along trajectories, the Jacobi integral in sidereal coordinates does not correspond directly to the total mechanical energy because the gravitational potential varies explicitly with time; instead, it equals the specific inertial energy minus the kinetic energy contribution from the rotating frame, specifically E = L_{z,\mathrm{sid}} - C/2, where L_{z,\mathrm{sid}} is the sidereal angular momentum component and energies are per unit mass.^[1] This formulation is less commonly employed than the synodic version, as the latter simplifies analysis in the co-rotating frame, but it proves valuable for direct comparisons with non-rotating two-body approximations or for establishing initial orbital conditions in inertial space, such as spacecraft launches from planetary surfaces where velocities are naturally specified in the sidereal frame.^[2] When transforming the sidereal expression back to synodic coordinates, the integral retains cross terms that capture the Coriolis acceleration effects inherent to the rotating reference frame.^[10]

Derivation

From Equations of Motion

In the synodic (rotating) frame of the circular restricted three-body problem (CRTBP), the equations of motion for a test particle of negligible mass are given by

\ddot{x} - 2\omega \dot{y} = \frac{\partial U}{\partial x}, \quad \ddot{y} + 2\omega \dot{x} = \frac{\partial U}{\partial y}, \quad \ddot{z} = \frac{\partial U}{\partial z},

where \omega is the constant angular velocity of the frame (normalized to \omega = 1 in standard units), and U(x, y, z) is the effective potential defined as

U = \frac{1-\mu}{r_1} + \frac{\mu}{r_2} + \frac{\omega^2}{2} (x^2 + y^2).

Here, \mu is the mass ratio of the secondary body, r_1 = \sqrt{(x + \mu)^2 + y^2 + z^2} is the distance to the primary mass at (-\mu, 0, 0), and r_2 = \sqrt{(x - (1 - \mu))^2 + y^2 + z^2} is the distance to the secondary mass at (1 - \mu, 0, 0).^[11] To derive the Jacobi integral, multiply the first equation by \dot{x}, the second by \dot{y}, and the third by \dot{z}:

\dot{x} \ddot{x} - 2\omega \dot{x} \dot{y} = \dot{x} \frac{\partial U}{\partial x}, \quad \dot{y} \ddot{y} + 2\omega \dot{y} \dot{x} = \dot{y} \frac{\partial U}{\partial y}, \quad \dot{z} \ddot{z} = \dot{z} \frac{\partial U}{\partial z}.

Summing these equations yields

\dot{x} \ddot{x} + \dot{y} \ddot{y} + \dot{z} \ddot{z} + 2\omega (\dot{y} \dot{x} - \dot{x} \dot{y}) = \left( \dot{x} \frac{\partial U}{\partial x} + \dot{y} \frac{\partial U}{\partial y} + \dot{z} \frac{\partial U}{\partial z} \right).

The Coriolis terms cancel since \dot{x} \dot{y} - \dot{y} \dot{x} = 0, and the left side recognizes the time derivative of the kinetic energy: \frac{d}{dt} \left[ \frac{1}{2} (\dot{x}^2 + \dot{y}^2 + \dot{z}^2) \right]. The right side is the total derivative \frac{dU}{dt}, as U depends only on position. Thus,

\frac{d}{dt} \left[ \frac{1}{2} (\dot{x}^2 + \dot{y}^2 + \dot{z}^2) - U \right] = 0,

implying that \frac{1}{2} v^2 - U is constant along any trajectory, where v^2 = \dot{x}^2 + \dot{y}^2 + \dot{z}^2. Rearranging gives the Jacobi integral in the standard form

C_J = 2U - v^2,

with C_J a constant determined by initial conditions.^[11]^[12] This conservation arises from the time-independence of both the effective potential U and the angular velocity \omega in the circular restricted problem, ensuring the equations of motion lack explicit time dependence and permitting an energy-like integral in the rotating frame.^[11]

Lagrangian Perspective

In the synodic (rotating) reference frame of the circular restricted three-body problem (CR3BP), the Lagrangian formulation provides a systematic approach to deriving the equations of motion and identifying conserved quantities. The full Lagrangian L in the rotating frame, accounting for the transformation from inertial coordinates, is

L = \frac{1}{2} (\dot{x}^2 + \dot{y}^2 + \dot{z}^2) + \omega (x \dot{y} - y \dot{x}) + \frac{1}{2} \omega^2 (x^2 + y^2) + \frac{1 - \mu}{r_1} + \frac{\mu}{r_2},

where (x, y, z) are the coordinates of the test particle, \omega is the angular velocity of the frame (normalized to 1 in standard units), \mu is the mass parameter of the secondary primary, and r_1, r_2 are the distances from the test particle to the primary bodies at fixed positions. The first term is the kinetic energy relative to the rotating frame, the second is the velocity-dependent Coriolis term arising from the coordinate transformation, the third is the centrifugal potential contribution, and the last two are the (positive) gravitational terms since L = T - V with negative gravitational potential.^[13] Applying the Euler-Lagrange equations \frac{d}{dt} \left( \frac{\partial L}{\partial \dot{q}_i} \right) = \frac{\partial L}{\partial q_i} for the generalized coordinates q_i = x, y, z yields the equations of motion in the rotating frame:

\ddot{x} - 2 \omega \dot{y} = \frac{\partial \Omega}{\partial x}, \quad \ddot{y} + 2 \omega \dot{x} = \frac{\partial \Omega}{\partial y}, \quad \ddot{z} = \frac{\partial \Omega}{\partial z},

where \Omega = \frac{1}{2} (x^2 + y^2) + \frac{1 - \mu}{r_1} + \frac{\mu}{r_2} is the effective potential (with \omega = 1), incorporating both gravitational and centrifugal terms. The Coriolis terms (-2 \omega \dot{y}, +2 \omega \dot{x}) emerge from the velocity-dependent term in L, and these equations are equivalent to the Newtonian equations of motion augmented by the fictitious forces in the non-inertial frame.^[12]^[13] Since the Lagrangian L does not depend explicitly on time (\partial L / \partial t = 0), the system is conservative with respect to time, and the energy function

h = \sum_i \dot{q}_i \frac{\partial L}{\partial \dot{q}_i} - L = \frac{1}{2} v^2 - \Omega

is conserved along trajectories (the velocity-dependent terms cancel in the expression for h). The Jacobi integral is then C_J = -2h = 2\Omega - v^2. This integral represents the total energy in the rotating frame (up to scaling) and constrains the accessible regions of phase space.^[13]^[12] The rotational symmetry of the CR3BP allows for a Routhian reduction, treating the overall rotation angle as an ignorable cyclic coordinate, which reduces the system from three to two degrees of freedom while preserving the Jacobi integral as the conserved Routhian (effective energy) in the reduced variables. This symmetry underscores the integral's origin in the time-independent nature of the problem in the synodic frame.^[3] The Jacobi integral is named after Carl Gustav Jacob Jacobi, who in 1836 submitted results on the three-body problem to the academies of Berlin and Paris and published a full account in 1837, developing a novel conserved quantity for the restricted three-body case that built on earlier work by Lagrange and Hamilton.^[3]

Physical Interpretation and Properties

Conservation Law

The Jacobi integral is conserved in the circular restricted three-body problem (CR3BP) due to the time-independence of the Lagrangian in the synodic (rotating) reference frame, which renders the system autonomous with respect to time translations. This autonomy ensures that the "energy" associated with the Lagrangian—adjusted for the rotating frame—remains constant along any trajectory satisfying the equations of motion. The conservation mechanism stems directly from this time-invariance, as the Lagrangian does not explicitly depend on time, leading to an integral that combines kinetic and potential terms in a frame corotating with the two primary bodies. Application of Noether's theorem further elucidates this conservation: the continuous rotational symmetry of the potential around the barycenter implies conservation of angular momentum in the inertial frame, while the time-translation symmetry in the rotating frame preserves an energy-like quantity; the Jacobi integral effectively merges these to yield a single conserved quantity unique to the CR3BP dynamics. This integral can be derived from the Lagrangian formulation in the rotating frame, highlighting its origin in the symmetries of the restricted problem. In normalized coordinates, the Jacobi integral C is dimensionless, with typical values around 3 for libration point orbits in the Earth-Moon system (where the mass parameter \mu \approx 0.01215).^[14] However, this conservation is specific to the CR3BP, where the primaries orbit circularly at constant angular velocity \omega; it does not hold in the elliptic restricted three-body problem, as the time-varying \omega due to elliptical orbits breaks the time-independence of the Lagrangian.^[15] In contrast, the general three-body problem admits no additional global integrals of motion beyond the total energy, the three components of linear momentum, and the three components of angular momentum, underscoring the special nature of the Jacobi integral in the restricted circular case.^[16]

Effective Potential and Zero-Velocity Surfaces

The effective potential in the circular restricted three-body problem combines gravitational and centrifugal terms in the rotating synodic frame:

U(x,y,z) = \frac{1}{2}(x^2 + y^2) + \frac{1 - \mu}{r_1} + \frac{\mu}{r_2},

where r_1 and r_2 are the distances from the test particle to the primary bodies of masses $1 - \mu and \mu (normalized such that total mass and separation are unity), respectively.^[10] This potential exhibits a saddle-shaped structure along the line connecting the primaries, with saddle points at the collinear equilibrium locations and, for small \mu, local minima at the triangular points.^[17] The Jacobi constant C defines level sets of the effective potential via the relation v^2 = 2U - C, such that zero-velocity surfaces occur where $2U = C (or U = C/2). These surfaces delineate the boundaries of the Hill regions, within which motion is allowed (U \geq C/2, ensuring nonnegative velocity).^[10] Outside these regions, the integral forbids motion due to the resulting imaginary velocities.^[17] In the orbital plane (z = 0), the topology of the zero-velocity curves—and thus the Hill regions—depends on C. For C exceeding the value at the collinear saddles (approximately 3 for small \mu), the allowed regions comprise two disconnected components: compact ovals enclosing each primary, separated by a forbidden zone. As C decreases to the critical saddle value, these components merge at the respective points. For C below this threshold, a single connected Hill region forms, permitting transit between the primaries and extending farther outward.^[17]^[10] Extending to three dimensions, the zero-velocity surfaces maintain reflection symmetry across the xy-plane (z \leftrightarrow -z), with no explicit dependence on the sign of z in U. The surfaces develop characteristic lobes aligned with the collinear points L1, L2, and L3, where necks form or open depending on C, constraining or enabling out-of-plane excursions.^[17] The geometry evolves with the mass ratio \mu; in the Sun-Jupiter system (\mu \approx 0.001), the extensive Hill region around the Sun dwarfs the confined zone near Jupiter, highlighting the primary's gravitational dominance and limiting accessible space near the secondary.^[10]

Applications

Lagrange Points Analysis

In the circular restricted three-body problem (CR3BP), the Lagrange points represent the equilibrium positions in the synodic (rotating) coordinate frame, where the test particle experiences zero acceleration, satisfying \ddot{x} = \ddot{y} = \ddot{z} = 0. These points occur where the gradient of the effective potential U vanishes, \nabla U = 0. Since the velocity vanishes at equilibrium in this frame, the Jacobi constant simplifies to C = 2U, providing a direct means to compute and verify the conserved energy level associated with each point.^[12] The three collinear Lagrange points, L1, L2, and L3, lie along the line connecting the two primaries. L1 is situated between the primaries, L2 beyond the smaller primary, and L3 beyond the larger primary. Their x-coordinates (with y = z = 0) are determined by solving the equilibrium equation derived from the x-component of the equations of motion:

x = \frac{(1 - \mu)(x + \mu)}{r_1^3} + \frac{\mu (x - 1 + \mu)}{r_2^3},

where r_1 = |x + \mu| and r_2 = |x - 1 + \mu|, with the primaries located at (-\mu, 0, 0) and (1 - \mu, 0, 0). This transcendental equation reduces to a quintic polynomial with three real roots for $0 < \mu < 0.5. The Jacobi constants at these points exceed 3, with C_{L1} \approx 3.00 plus small corrections scaling with \mu.^[12]^[18] The triangular Lagrange points L4 and L5 form equilateral triangles with the two primaries, positioned 60° ahead (L4) and behind (L5) the smaller primary in the orbital plane. Their coordinates are \left( \frac{1}{2} - \mu, \pm \frac{\sqrt{3}}{2}, 0 \right). At these points, the distances to both primaries are exactly 1 (in normalized units), yielding a Jacobi constant of C = 3 exactly.^[12] These five points were first identified by Joseph-Louis Lagrange in 1772 as solutions to the three-body problem. Regarding stability, the collinear points L1, L2, and L3 are inherently unstable, exhibiting hyperbolic behavior in the linearized equations of motion. The triangular points L4 and L5, however, are linearly stable when the mass ratio satisfies \mu < 0.0385, as determined by Routh's criterion for the eigenvalues of the characteristic equation. For instance, in the Sun-Jupiter system (\mu \approx 9.54 \times 10^{-4}), this stability enables the long-term residence of Trojan asteroids at L4 and L5.^[19]^[12]^[20]^[21]

Orbital Stability and Hill Regions

The Jacobi integral plays a crucial role in delineating the Hill regions, which are the permitted volumes in configuration space where motion is possible according to the inequality v^2 = 2\left( U - \frac{C}{2} \right) \geq 0, with U denoting the effective potential and C the Jacobi constant. These regions are bounded by zero-velocity surfaces, and their topology varies with C: for low values of C (corresponding to high energy), the regions expand and interconnect, enabling escape trajectories from the vicinity of one primary to the other or to infinity. Conversely, higher C values restrict motion to disjoint volumes around each primary, promoting bounded orbits. This structure is fundamental to understanding permissible paths in the circular restricted three-body problem (CR3BP).^[9] Orbital stability in the CR3BP is intimately linked to the Jacobi constant through criteria for periodic orbits. Near the triangular Lagrange points L4 and L5, tadpole orbits—small, stable loops enclosing one primary—are linearly stable for C < 3 in normalized units, a threshold derived from the linearized dynamics where the mass parameter \mu < 0.0385 ensures center-center-center stability at the points themselves. Beyond this value, bifurcations lead to horseshoe orbits and eventual instability. Halo orbits around the collinear point L1, which loop perpendicular to the line joining the primaries, exist for specific C values below that at L1 and are inherently unstable, characterized by hyperbolic behavior that necessitates active control for practical use.^[22] Applications of the Jacobi integral extend to spacecraft mission design and natural celestial dynamics. For instance, the James Webb Space Telescope (JWST) operates on a halo orbit around the Sun-Earth L2 point with C \approx 3.0009, selected to balance stability and solar shielding while leveraging the integral to compute station-keeping maneuvers. Similarly, asteroid families, such as the Trojans near Jupiter's L4 and L5, remain confined within Hill spheres—the spherical approximations of Hill regions for small \mu—preventing dispersal into interplanetary space. In mission planning, the impossibility of crossing forbidden Hill regions implies infinite transit times through them, guiding the use of invariant manifolds for efficient, low-energy transfers that skirt these barriers. In the Sun-Earth system, C > 3.0008 effectively bounds motion to Earth's vicinity, isolating it from solar escape routes.^[23]^[24]^[25]

References

[1]
Jacobi Integral - Richard Fitzpatrick
The Jacobi integral is the only constant of the motion in the circular restricted three-body problem.
[2]
[PDF] The Early History of Hamilton-Jacobi Dynamics 1834–1837
May 2, 2023 · If we replace UI + U2 by (3.9), we obtain Jacobi's integral. The integral (3.1) follows directly from the theory set forth in the Vorlesungen.
[3]
Circular restricted three-body problem
In the following, we shall examine this simplified problem, which is usually referred to as the circular restricted three-body problem.
[4]
[PDF] METHODOLOGY - DESCANSO
The dynamics in the circular restricted three-body system depend only on the three- body constant, µ. Furthermore, as µ goes to zero, the dynamics approach two ...
[5]
[PDF] the circular restricted three-body problem - Northern Arizona University
Although many other scientists have studied the problem, it was relatively unsolved until Poincare made groundbreaking work in the area in 1890. The typical ...
[6]
[PDF] Restricted three body problem, PHYS 2200
Dec 7, 2023 · Figure 2: The co-rotating frame. The equation of motion of mass m in the rotating reference frame are obtained by including into Eqs. (6) ...
[7]
[PDF] Circular and Elliptic Restricted Three Body Problems - arXiv
Dec 7, 2021 · This formula is used to transform equations (1) and (2) into the rotating frame with rotation rate . (3). (4). Then is an equilibrium solution ...
[8]
[PDF] generating periodic orbits in the circular restricted three- body ...
2.1 The Circular Restricted Three-Body Problem ... mass in comparison with the other two bodies, or primaries. Furthermore, it is assumed that the motion ...
[9]
[PDF] The Circular Restricted Three–Body Problem - People
rij = rj − ri. In order to solve the problem, 18 (6×3) first integrals of motion are required. ... In the three coordinates, the equations of motion are x − 2˙y =.
[10]
[PDF] 3. The circular restricted three-body problem 3.1 Definition of the ...
A close binary can be considered in terms of the circular restricted three-body problem, in which the two primaries are the two stars and the test particle is ...
[11]
Co-Rotating Frame - Richard Fitzpatrick
$$C$ is the Jacobi integral introduced in Section 13.3 [it is easily demonstrated that Equations (1039) and (1064) are identical]. Note, finally, that the ...
[12]
[PDF] Lagrangian Mechanics and the Three-body Problem - OSU Math
is an integral of motion, which was identified by Jacobi in 1836. The function H is a constant along any given trajectory that satisfies the equations of motion ...
[13]
https://arxiv.org/pdf/2312.15800.pdf
[14]
Earth–Moon L2 Quasi-Halo Orbit Family: Characteristics and ...
Aug 29, 2022 · In this form the dynamics admit one dimensionless constant of motion called the Jacobi constant [28]. ... Jacobi constant ranges from 3.046741 to ...
[15]
On the elliptic case of the restricted problem of three bodies and the ...
The existence of the well-known Jacobi integral is shown to be a singular property of the “circular” three-body problem, having no analogy in the eccentric case ...
[16]
Three body problem - Scholarpedia
Oct 3, 2007 · When the Jacobi constant increases, the components of the Hill regions around the two non zero masses merge, a case closer to the one of the ...
[17]
[PDF] 3. The gravitational three-body problem 3.1 The circular restricted ...
May 7, 2014 · → Show examples of resonant periodic orbits in the circular restricted three body problem (e.g. Sun/Jupiter, asteroid. Fig. 8.4 of MD, FIG 3.23; ...
[18]
[PDF] APPENDIX A LOCATING THE LAGRANGE POINTS - DESCANSO
analytical expressions for the Lagrange points in the circular restricted three-body problem (CRTBP). Szebehely provides more details and a clear ...
[19]
[PDF] Euler's three-body problem - Scholarly Commons
Later on, in 1772,. Lagrange dealt with the same problem, and demonstrated that for any three masses with circular orbits, there are two special constant- ...
[20]
[PDF] An Examination of the Mass Limit for Stability at the Triangular ...
After having considered the general three-body problem in Chapter 3, we return to the circular restricted three-body problem and consider the stability of the.Missing: criterion | Show results with:criterion
[21]
How Were the Trojan Asteroids Discovered and Named? - NASA
Feb 22, 2021 · It later became convention to name Jupiter's L4 asteroids after Greek characters and Jupiter's L5 asteroids after Trojan characters, so L4 ...
[22]
[PDF] Classifying orbits in the restricted three-body problem - arXiv
The motion of the test third body is restricted to a three- dimensional surface E = const, due to the existence of the Jacobi integral.
[23]
Comparison for the range of Jacobi constant values for families of...
The Sun- Earth manifold crossings, plotted in Figure 13 as red-brown vectors with square base points, exist at a Jacobi constant value of approximately 3.0009.
[24]
[PDF] SEASONAL VARIATIONS OF THE JAMES WEBB SPACE ...
(a) Jacobi constant differences between JWST average value and CR3BP corrected state. The dashed blue and red lines indicate the Winter and Summer solstices ...
[25]
[PDF] Periodic orbits in the restricted three-body problem and Arnold's J+ ...
Apr 27, 2017 · Note that in this case the Lagrange problem and the restricted 3-body problem have the same potential and therefore the same Hill's regions.