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首页> 外文期刊>Aerospace science and technology >Designing a closed-loop guidance system to increase the accuracy of satellite-carrier boosters' landing point
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Designing a closed-loop guidance system to increase the accuracy of satellite-carrier boosters' landing point

机译：设计闭环制导系统以提高卫星运载助推器着陆点的精度

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A novel closed loop guidance method is provided in this paper to increase the accuracy of satellite carrier boosters' landing point. The proposed method can be used in the first stage of flight vehicles that fly in atmosphere. In this case, solid motor propelled boosters would be able to more accurately land on the desired point. Moreover, in sub-optimal technique, the closed-loop guidance system would produce commands after booster separation, which guide second stage of satellite-carrier from initial conditions to the desired condition of orbit injection. In this method, sub-optimal integrated solution of control and guidance in closed-loop is developed. This sub-optimal technique named as Model Predictive Static Programming (MPSP) that is based on nonlinear optimal control theory and derived from combined philosophies of Model Predictive Control and Approximate Dynamic Programming; solves a class of finite horizon optimal control problems with terminal constraints. Furthermore because sensitivity matrices that are necessary for obtaining this solution can be computed recursively, this technique is computationally efficient and is appropriate for online implementation. In this paper, the dynamic equations of system are modeled in the presence of aerodynamic loading and the servo-mechanism dynamic. Moreover, by considering integrated guidance and control loops, a solution of the guidance and control system is proposed by three-degree of freedom spherical earth simulation model in atmosphere. Result show that proposed closed-loop guidance not only is able to remove aerodynamic and thrust modeling errors in first stage by flight data update that caused to more accurate of boosters' landing point, but also would still be able to guide second stage of satellite-carrier to the desired condition of placement in the orbit. (C) 2018 Elsevier Masson SAS. All rights reserved.
机译：本文提出了一种新颖的闭环制导方法，以提高卫星运载助推器着陆点的精度。所提出的方法可以用于在大气中飞行的飞行器的第一阶段。在这种情况下，固体发动机推动的助力器将能够更准确地降落在所需点上。此外，在次优技术中，闭环引导系统将在助推器分离后产生命令，从而将卫星载波的第二阶段从初始状态引导到所需的轨道注入状态。在这种方法中，开发了闭环控制和制导的次优集成解决方案。这种次优技术称为模型预测静态规划（MPSP），它基于非线性最优控制理论，并源于模型预测控制和近似动态规划的组合思想；解决了带有终端约束的一类有限水平最优控制问题。此外，由于可以递归计算获得此解决方案所需的灵敏度矩阵，因此该技术在计算上非常有效，适用于在线实施。本文在存在空气动力学载荷和伺服机构动力学的情况下，对系统的动力学方程进行建模。此外，通过考虑集成的制导与控制回路，提出了一种基于大气三自由度球形地球模拟模型的制导与控制系统解决方案。结果表明，拟议的闭环制导不仅能够消除飞行数据更新导致的第一阶段的空气动力学和推力建模误差，从而使助推器的着陆点更加准确，而且还能指导卫星的第二阶段-载运到所需的轨道位置。 （C）2018 Elsevier Masson SAS。版权所有。

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