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- W1529940585 abstract "Tethered satellite systems have many potential applications, ranging from upper atmospheric research (Colombo et al., 1975) to momentum transfer (Nordley & Forward, 2001; Williams et al., 2004). The major dynamical features of the system have been studied extensively (Misra & Modi, 1986), but there still remain open questions with regard to control (Blanksby & Trivailo, 2000). Many of the open issues stem from the fact that there have been limited flight tests. The most recent flight of the Young Engineers’ Satellite 2 (YES-2) highlighted from its results that tether dynamic modelling is relatively mature, but that there is a need to provide fault tolerant design in the control and sensor subsystems (Kruijff et al., 2009). In applications such as momentum transfer and payload capture, it is imperative that robust, accurate and efficient controllers can be designed. For example, although it is conceivable to use onboard thrusters to manipulate the motion of the tethered satellite, this negates some of the advantages of using tethers, i.e., little to no fuel expenditure in ideal circumstances. The main source of control, therefore, has to be sought from manipulating the length of deployed tether. This has two main aims: first, the length of tether directly controls the distance of the tether tip from the main spacecraft, and second, changes in tether length induce Coriolis-type forces on the system due to the orbital motion, which allows indirect control over the swing motion of the tether (librations). Typically, control over the tether length is achieved via manipulating the tension at the mother satellite (Rupp, 1975; Lorenzini et al., 1996). This can help to prevent the tether from becoming slack – a situation that can lead to loss of control of the system. A variety of different control strategies have been proposed in the literature on tethered systems. Much of the earlier work focused on controlling the deployment and retrieval processes (Xu et al., 1981; Misra & Modi, 1982; Fujii & Anazawa, 1994). This was usually achieved by combining an open-loop length control scheme with feedback of the tether states, either appearing linearly or nonlinearly. Other schemes were devoted to ensuring nonlinear asymptotic stability through the use of Lyapunov’s second method (Fujii & Ishijima, 1989; Fujii, 1991; Vadali & Kim, 1991). Most of these techniques do not ensure wellbehaved dynamics, and can be hard to tune to make the deployment and retrieval fast. 10" @default.
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- W1529940585 date "2010-08-18" @default.
- W1529940585 modified "2023-09-23" @default.
- W1529940585 title "Predictive Control of Tethered Satellite Systems" @default.
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- W1529940585 doi "https://doi.org/10.5772/intechopen.83904" @default.
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