The classical two–body problem is the dynamical system which describes the motion of two objects. Of course, it is the simplest and only integrable system within frame of the classical Newtonian potential between two–bodies is applied. There are many applications in mathematical astronomy or in engineering and physical sciences can be analyzed within the frame work of two–body systems, it can be used in both quantum mechanics (particles motion) and celestial mechanics (Stars motion)
The multivariate of the perturbed forces in inner and outer space change the two–body from a simple and integrable system to one is complex and is not integrable. Thereby the analytical solutions will be invalid in most real applications. The analysis of two–body problem under the effect of many perturbed forces have received a comprehensive an extended study in the literature space dynamics. For example, the perturbed two–body problem by radiation pressure force and many types of drag forces or both together has been investigated [6,9,10,11,12]. Furthermore, the analytical solutions of the satellite motion within frame of non–sphericity and zonal harmonics perturbations effect have been studied by [7, 8].  have studied also the dynamics of anisotropic Kepler problem with small anisotropy. They proved that at every energy level the anisotropic dynamical system has two periodic orbits.
The perturbed two–body system is not limited to the perturbations of either radiation pressure and drag force or the non–sphericity of the bodies. But the other bodies can be taken as a perturbed forces for the motion of two–body system . Another consequence of two–body problem is that the three-body problem can be reduced to the system of two–body, if we consider either the third body has mass equals zero or if it moves to infinity while the other primary does not. There are a considerable work have been constructed to find the periodic solution for many perturbed two–body systems, see for details [1, 2, 13]. In addition the two–body problem within frame of the corrections law of Newtonian inverse square law of gravitation can be studied as a perturbed model .
The motion of planets and asteroids is a very important field of interest in astronomy, and space dynamics. It can be formulated as a dynamical system of differential equations based on the Newton’s laws of gravitation . The law states that everybody attracts every other body along a line intersecting the two bodies with a force equals to F = Gm1m2/r2, where F is the force between the two bodies, G is the gravitational constant, m1 is the mass o f the first body, m2 is the mass of the second body, and r the distance between the centres of masses of the bodies .
Additionally, the Newtonian gravitation can be extended to N–bodies by simply summing the forces [16,17,18]. Moreover, various analytical and numerical methods have been used to examine such problems of celestial mechanics comprising of the two–body, three–body and the generalized N–body problem, see [19,20,21,22,23,24,25,26]. But we aim in this paper to computationally tackle the gravitational two–body problem with the application of the power series method .
2 Vector two–body equation
3 Power series solution
3.1 Lagrange’s fundamental invariants
3.2 Basic differential equations
3.3 f and g functions
Also in the next section, analytical computations determine for the values of fn and gn for n = 10 using a designed algorithm called FGPS, see Appendix B for the algorithm.
4 Results and Discussion
In this chapter, computational values determine for the values qn +2 for n=9, fn and gn for n = 10 using Mathematica software with designed computational algorithms QPS and FGPS are given in Appendix A and Appendix B, respectively.
Furthermore, a mathematical modules establish to find the scalar values of the position and velocity vectors of the two-body motion via Mathematica software with the designed computational algorithm RVPS is given in Appendix C then we apply this module for different kinds of orbits (elliptic, parabolic and hyperbolic).
4.1 Values of qn
4.2 Values of fn
4.3 Values of gn
4.4 Applications on orbits
With the application of RVPS algorithm on different kinds of orbits with the initial values components for the position and velocity vectors is given by then, we get the final scalar values of the position and velocity vectors
The dynamical system of the two–body problem is addressed, by applying the mathematical modules, which are established to find the scalar values of the position and velocity vectors of the two–body motion. The Application of this module for different kinds of orbits (elliptic, parabolic and hyperbolic) leads to accurate results, that prove module efficiency.
Appendix A: QPS
- *PurposeTo generate n symbolic expressions of the q’s coefficients of the time power series solution
of the single harmonic oscillator .
- *Inputq0, q1, ε0, λ0, ψ0, n
- *Outputn symbolic expressions of the q’s coefficients.
- *Module list.
The initial values components for the position and velocity vectors
|Orbit Type||x0 (km)||y0 (km)||z0 (km)||ẋ0 (km/s)||ż0 (km/s)|
The final scalar values of the position and velocity vectors
Appendix B: FGPS
- *PurposeTo generate n symbolic expressions of the f’s or g’s coefficients of the time power series of the Lagrange functions f or g.
- *InputT:A positive integer takes the value 1 or 2, such that:
- T = 1 if it is required to find the f’s coefficients,
- T = 2 if it is required to find the g’s coefficients, ε0, λ0, ψ0, n
- *Outputn symbolic expressions of the f’s or g’s coefficients according to the value of T.
- *Module list.
Appendix C: RVPS
- *PurposeTo generate the position and velocity values for any orbit.
- *Inputx0, y0, z0, ẋ0,
, ż0, μ, m, t and t0.
- *OutputThe position and velocity values for any orbit.
- *Module list.
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