By Danwei Wang, Baolin Wu, Eng Kee Poh
This ebook systematically describes the thoughts and ideas for multi-satellite relative movement, passive and close to passive formation designs, trajectory making plans and regulate for gas optimum formation maneuvers, and formation flying upkeep regulate layout. As such, it offers a legitimate origin for researchers and engineers during this box to advance extra theories and pursue their implementations.
Though satellite tv for pc formation flying is broadly thought of to be an immense boost in area expertise, there are few systematic remedies of the subject within the literature. Addressing that hole, the booklet bargains a necessary source for teachers, researchers, postgraduate scholars and practitioners within the box of satellite tv for pc technological know-how and engineering.
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Additional info for Satellite Formation Flying: Relative Dynamics, Formation Design, Fuel Optimal Maneuvers and Formation Maintenance
5) is linear to the differential orbit elements and is independent of the right ascension of ascending node X of the reference satellite S0 . The independence property of the right ascension of ascending node is identical to the exact satellite relative dynamics under J2 perturbation obtained in Xu and Wang (2008). However, this property is due to somewhat different reasons. 2 Passive and Periodic Relative Motion Under J2 Perturbation 47 satellite relative motion depends on X of the reference satellite S0 .
46 3 Passive and Periodic Satellite Formation Design … Fig. 1 Curvilinear coordinate The relative motion of the member satellite Sj can be presented in the local curvilinear coordinate xyz in terms of the orbit elements ða; e; i; x; f Þ of the reference satellite S0 and the differential orbit elements ðdaj ; dej ; dij ; dxj ; dXj ; dMj Þ between the reference satellite and the jth member satellite. In the literature, the expressions of such satellite relative motion have been derived by Schaub (Schaub and Junkins 2003; Schaub 2004), Lane and Axelrad (2006), as well as Hamel and Lafontaine (2007).
11 shows the function chart of the model comparison method. 5 Comparison Study of Relative Dynamic Models 29 Fig. 11 Function chart of model comparison method including relative positions and relative velocities. In the second step, the STK– MATLAB interface is utilized to transfer data into STK/Astrogator. Then, the initial conditions are propagated in STK which includes various orbital disturbances. Meanwhile, the same initial conditions are integrated numerically by the selected relative dynamics in MATLAB.