![]() The impact of the eccentricity on a formation flying is further evaluated with simulation conducted by using different altitude and eccentricity.įor better showing the physical parameters, the non-dimensional simulation results are converted back to the dimensional values. Moreover, the effects of the J 2 geopotential and the atmospheric drag perturbations on a formation with small eccentricity are numerically analyzed. Its initial orbit parameters are ω = 0 degree, i = 78 degrees, Ω = 320 degrees, and M = 0 degree. The mass, the area, and the drag coefficient of the TECSAS are 175 kg, 2.22 m 2, and 2.3 kg, respectively. The TECSAS was a technology demonstration mission for on-orbit servicing such as the rendezvous maneuver. The satellite's physical parameters are specified as same as the physical parameters of the TECSAS mission led by the German Space Organization in collaboration with the Canadian Space Agency and the Federal Space Agency of Russia. In this section, numerical simulation is carried out to demonstrate the effectiveness of the new linearized equation (3.147). Bing Xiao, in Predictive Filtering for Microsatellite Control System, 2021 3.4.6.3 Verification of the established relative motion equation Modeling of microsatellite control system However, the problems of target capture and post-capture have not been fully addressed, which will be the topics of the subsequent chapters. The investigations of control during employment and retrieval have been drawn much attention. Besides, the nonlinear dynamic model of the TSR is quite complicated due to the existence of space tether and the control during the mission is challenging but very meaningful. Therefore, more efforts are required to study the dynamic modeling and behavior of the TSR deeply. Moreover, the dynamic behavior of a space tether is quite complicated, which leads to highly coupled dynamic characteristics of TSR during the employment, capture, retrieval, and deorbiting phases. Dynamic modeling is one of the most important problems for the TSR, especially the modeling of the space tether, which has been studied by many researchers. However, the TSR is a rather complex multi-body with its dynamics highly coupled and requires more investigations. In recent years, many researchers have worked on the TSR, especially the dynamics and controls of releasing and retrieving phase, resulting in many achievements. The TSR features high flexibility and greater workspace and is promising in future OSS missions such as auxiliary orbit transfer and space debris removal. The chapter presents the relative motion in an orbit, linearization of the equations of relative motion in orbit, the Clohessy–Wiltshire equations (CW equations), two-impulse rendezvous maneuver, and the relative-motion in close proximity circular orbits. To base impulsive maneuvers on observations made from a moving platform requires transforming relative velocity and acceleration measurements into an inertial frame else the true thrusting forces cannot be sorted out from the fictitious inertia forces that appear in Newton's law. In a rendezvous maneuver, two orbiting vehicles observe one another from each of their own free-falling, rotating, clearly non-inertial frames of reference. This chapter illustrates an elative motion analysis to gain familiarity with the problem of maneuvering one spacecraft relative to another, especially when they are in close proximity. ![]() Curtis, in Orbital Mechanics for Engineering Students (Second Edition), 2010 Publisher Summary
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