Titlebook: Orbital Relative Motion and Terminal Rendezvous; Analytic and Numeric Jean Albert Kéchichian Book 2021 The Editor(s) (if applicable) and Th

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Guileless

The Second-Order Analytic Approximation to the Solution of the Euler-Hill Equations of Relative Mote numerically integrated exact solution, at greater distances from the origin of the rotating reference frame. These solutions have been developed to study the problem of the terminal rendezvous guidance where an active spacecraft at several hundred km from its rendezvous target centered at the rota

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Analytic Solutions for the Perturbed Motion of a Spacecraft in Near-Circular Orbit, Under the Influ small eccentricity and arbitrary inclination, energy, node and perigee location is analyzed. The second-order Euler-Hill differential equations are solved after expanding the forcing terms to first-order in the small parameter defining the orbit eccentricity. The construction of the circular refere

Ovulation

Analytic Solutions for the Perturbed Motion of a Spacecraft in Near-Circular Orbit, Under the Influturbed by Earth’s . and . zonals, and described in the rotating Euler-Hill frame, the same approach is used in this chapter and based on Reference [2] to obtain analytic expression for the spacecraft motion perturbed by the luni-solar gravity.

Eviction

Effect of Luni-Solar Gravity Perturbations on a Near-Circular Orbit: Third-Body Orbit Eccentricity rder to simplify the analysis, the lunar as well as the apparent solar orbits were assumed to be circular. In this chapter, this assumption is removed such that the third-body orbits are now allowed to describe Keplerian ellipses. Second and higher-order terms in the eccentricities of the lunar and

Gum-Disease

Effect of Atmospheric Drag Perturbation on Circular Orbits: Atmosphere Rotation Considerations,nergy, and perigee location and small eccentricity. Following the practice used in References [1, 2], and the preceding chapters, the rotating Euler-Hill frame is used to describe the perturbed motion of the spacecraft by assuming that the atmospheric density obeys an exponential decay law with radi

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得意人

Techniques of Accurate Analytic Terminal Rendezvous in Near-Circular Orbit,ed to the active maneuvering vehicle is determined with high accuracy, such that, the error in interceptmg the passive spacecraft in a given time is negligible. This error is evaluated by numerically integrating both spacecraft orbits, by accounting for the second zonal harmonic .. A typical large t

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Coplanar Two-Impulse Rendezvous in General Elliptic Orbit with Drag,ral elliptic orbit is presented in this chapter. The motion of the passive vehicle is described by the inverse square gravitational field of the primary body and by atmospheric drag. The center of a rotating reference frame is attached to this vehicle, and the motion of the active maneuvering vehicl

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The Analysis of the Relative Motion in General Elliptic Orbit with Respect to a Dragging and Preces in general elliptic orbit, relative to a rotating reference frame which drags and precesses exactly as a given spacecraft attached to its center is derived. This attached spacecraft is itself flying a general elliptic orbit and can be considered as the passive or non-maneuvering vehicle. The unaver