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These advantages make it reasonable to apply the space tethered system for deorbiting the fast-growing low-cost micro/nano-satellites and no-fuel cargo transfer. Compared with existing technologies adopted by large spacecraft such as the rocket or thruster, the space tether technology has the advantages of fuel-efficiency (little or no propellant required), compact size, low mass, and ease-of-use. Their interest technologies include the electrodynamic tether (EDT) propulsion technology, retrieval of tethered satellite system, multibody tethered system and space elevator system. Recently, there is continuous interest in the space tether systems, in leading space agencies such as, NASA’s US National Aeronautics and Space Administration, ESA’s European Space Agency, and JAXA’s Japan Aerospace Exploration Agency. It has wide potential applications in the space debris mitigation & removal, space detection, power delivery, cargo transfer and other newly science & technic missions. Space tether system is a promising technology over decades. The numerical results show that the proposed parallel optimal algorithm is very effective in dealing with the optimal control problems for complex nonlinear dynamic systems in aerospace engineering area. Two cases are simulated with the proposed algorithm to validate the effectiveness of proposed algorithm. By considering the convergence of system error, the current closed-loop control tracking interval and next open-loop control predicting interval are processed simultaneously. The optimal control problems in both programs are solved by a direct collocation method based on the discretized Hermite–Simpson method with coincident nodes. The finite receding horizon control method is used in the tracking program.
Matlab 2018b piecewise full#
The tracking phase concerns the closed-loop optimal tracking control for the optimal reference trajectory with full system model subject to real space perturbations. The predicting phase deals with the open-loop state trajectory optimization with simplified system model and evenly discretized time interval of the state trajectory.
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The proposed algorithm contains two phases. This chapter studies a new optimal algorithm that can be implemented in a piecewise parallel manner onboard spacecraft, where the capacity of onboard computers is limited.