THE EXISTENCE OF PERIODIC SOLUTIONS PASSING NEAR BOTH MASSES OF THE RESTRICTED THREE BODY PROBLEM
Periodic solutions passing near both masses of the restricted three-body problem - keplerian ellipses
KEPLER LAW↗
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Rejection to infinity in the problem of three bodies when the total energy is negative
Rejection to infinity in three-body problem when total energy is negative
THREE-BODY PROBLEM↗
Stability of a class of periodic orbits in the restricted three-body problem.
Bounded isoenergetic displacement of periodic orbits in restricted circular three-body problem
DYNAMIC STABILITY↗
Two-center problem orbits as intermediate orbits for the restricted three-body problem
Two-center problem orbit as intermediate orbit for restricted three-body problem
CELESTIAL MECHANICS↗
SIMULATION F TH5 RESTRICTED THREE-BODY PROBLEM USING THE TRICE-PB250 SYSTEM
Integration of the restricted three body problem using the trice-pb250 system with the selection of appropriate variables and programming techniques
THREE-BODY PROBLEM↗
Analytical Flow Theory in the Three Bodies Problem with the Use of Regularizing Variables
Perturbation analysis for spatial three-body problem with Kepler motion
KEPLER LAW↗
Numerical determination of short period Trojan orbits in the restricted three body problem
Short period orbit calculations around equilateral libration points in plane restricted three-body problem
LIBRATION↗
Outline of a theory of nonperiodic motions in the neighborhood of the long-period librations about the equilateral points of the restricted problem of three bodies
Nonperiodic motions near long-period librations about equilateral points of restricted three-body problem
PERIODIC ORBIT↗
Satellite motion for arbitrary eccentricity and inclination around the smaller primary in the restricted three-body problem.
Motion of close satellite of smaller primary in restricted three-body problem referred to conventional rotating frame in which central angle is chosen as independent variable
ORBIT EQUATION↗
A new Lie series method for the numerical integration of ordinary differential equations, with an application to the restricted problem of three bodies
New Lie series method for numerical integration of ordinary differential equations, and restricted three-body problem application
THREE-BODY PROBLEM↗
Some numerical comparisons of three-body trajectories with patched two body trajectories for low thrust rockets
Comparisons of three body trajectories with patched two body trajectories for low thrust rockets
Strack, W. C.↗
Theoretical and experimental three-body ionic recombination coefficients.
Low density limit to three body ionic recombination coefficients in various gases
Flannery, M. R.↗
A pseudostate theory for the approximation of three-body trajectories
Closed form approximate solution for restricted three body motion of lunar or interplanetary spacecraft, demonstrating accuracy and flexibility in lunar mission trajectory calculations
Wilson, S. W., Jr.↗
Outline of a theory of nonperiodic motions in the neighborhood of the long-period librations about the equilateral points of the restricted problem of three bodies.
Long period of nonperiodic librational motion about equilateral points of restricted three-body problem
TROJAN ORBIT↗
Use of Invariant Manifolds for Transfers Between Three-Body Systems
The Lunar L1 and L2 libration points have been proposed as gateways granting inexpensive access to interplanetary space. To date, only individual solutions to the transfer between three-body systems have been found. The methodology to solve the problem for arbitrary three-body systems and entire families of orbits does not exist. This paper presents the initial approaches to solve the general problem for single and multiple impulse transfers. Two different methods of representing and storing 7-dimensional invariant manifold data are presented. Some particular solutions are presented for the transfer problem, though the emphasis is on developing methodology for solving the general problem.
Beckman, Mark↗
Representations of Invariant Manifolds for Applications in Three-Body Systems
The Lunar L1 and L2 libration points have been proposed as gateways granting inexpensive access to interplanetary space. To date, only individual solutions to the transfer between three-body systems have been found. The methodology to solve the problem for arbitrary three-body systems and entire families of orbits is currently being studied. This paper presents an initial approach to solve the general problem for single and multiple impulse transfers. Two different methods of representing and storing the invariant manifold data are presented. Some particular solutions are presented for two types of transfer problems, though the emphasis is on developing the methodology for solving the general problem.
Howell, K.↗
PERIODIC SOLUTIONS OF THE RESTRICTED THREE BODY PROBLEM REPRESENTING ANALYTIC CONTINUATIONS OF KEPLERIAN ELLIPTIC MOTIONS
Periodic solution of restricted three body problem as analytic continuation of keplerian elliptical motions
KEPLER LAW↗
Instability of periodic motions near collinear points of libration in the restricted problem of three bodies
Instability of periodic motions near collinear points of libration in plane restricted three- body problem examined with Liapunov theory
PERIODIC OSCILLATION↗