- We will send in 10–14 business days.
/images/books/7504405/9781288318315.jpg)
- Author: Kirk W Johnson
- Publisher: BiblioScholar
- ISBN-10: 1288318316
- ISBN-13: 9781288318315
- Format: 18.9 x 24.6 x 1.1 cm, minkšti viršeliai
- Language: English
- SAVE -10% with code: EXTRA
Relative Orbit Elements for Satellites in Elliptical Orbits (e-book) (used book) | bookbook.eu
Reviews
Description
The purpose of this research was to describe the unperturbed relative motion of Earth satellites in elliptical orbits using a simple dynamics model whose parameters allow significant geometrical insight and operational efficacy. The goal was to retain the advantages of the Relative Orbit Elements (ROE) realization of the Hill-Clohessy-Wiltshire (HCW) equations, a linearized dynamics model for circular reference orbits. Specifically, this thesis analyzed the geometry of satellite rendezvous and proximity operations using the ROE parameters to characterize the model's utility. Next, through a comprehensive literature review, this thesis sought possible approaches for developing a similarly useful parameterization for chief orbits with nonzero eccentricity. The approach selected was a novel linear time-varying system which requires both chief and deputy satellites to remain close to a virtual chief on a known circular orbit.
EXTRA 10 % discount with code: EXTRA
The promotion ends in 22d.16:49:54
The discount code is valid when purchasing from 10 €. Discounts do not stack.
- Author: Kirk W Johnson
- Publisher: BiblioScholar
- ISBN-10: 1288318316
- ISBN-13: 9781288318315
- Format: 18.9 x 24.6 x 1.1 cm, minkšti viršeliai
- Language: English English
The purpose of this research was to describe the unperturbed relative motion of Earth satellites in elliptical orbits using a simple dynamics model whose parameters allow significant geometrical insight and operational efficacy. The goal was to retain the advantages of the Relative Orbit Elements (ROE) realization of the Hill-Clohessy-Wiltshire (HCW) equations, a linearized dynamics model for circular reference orbits. Specifically, this thesis analyzed the geometry of satellite rendezvous and proximity operations using the ROE parameters to characterize the model's utility. Next, through a comprehensive literature review, this thesis sought possible approaches for developing a similarly useful parameterization for chief orbits with nonzero eccentricity. The approach selected was a novel linear time-varying system which requires both chief and deputy satellites to remain close to a virtual chief on a known circular orbit.
Reviews