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861.
862.
Liang Zhang Peiqi Ge 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2021,67(7):2185-2198
For spacecraft hovering in low orbit, a high precision spacecraft relative dynamics model without any simplification and considering J2 perturbation is established in this paper. Using the derived model, open-loop control and closed-loop control are proposed respectively. Gauss's variation equations and the coordinate transformation method are combined to deal with the relative J2 perturbation between the two spacecraft. The sliding mode controller is adopted as the closed-loop controller for spacecraft hovering. To improve the control accuracy, the relative J2 perturbation is regarded as a known parameter term in the closed-loop controller. The external uncertainty perturbations except J2 perturbation are estimated by numerical difference method, and the boundary layer method is used to weaken the impact of chattering on the sliding mode controller. The open-loop control of spacecraft hovering with the relative J2 perturbation and without the relative J2 perturbation are simulated and compared, and the results prove that the accuracy of open-loop control with relative J2 perturbation has been significantly improved. Similarly, the simulation of the closed-loop control are presented to validate the effectiveness of the designed sliding mode controller, and the results demonstrate that the designed sliding mode controller including the derived relative J2 perturbation can guarantee the high accuracy and robustness of spacecraft hovering in long-term mission. 相似文献
863.
864.
Jianqiao Zhang Dong Ye James D. Biggs Zhaowei Sun 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2019,63(3):1161-1175
This paper addresses the relative position tracking and attitude synchronization control problem for spacecraft formation flying (SFF). Based on the derived relative coupled six-degree-of-freedom dynamics, a robust adaptive finite-time fast terminal sliding mode controller is proposed to achieve the desired formation in the presence of model uncertainties and external disturbances. It is shown that the designed controller is effective for changing information exchange topology making it robust to node failure. Then, the artificial potential function method is employed to generate collision avoidance schemes to modify the controller such that inter-agent collision avoidance can be ensured during the formation maneuver, which is critical for practical missions. The stability of the overall closed-loop system is proved by using Lyapunov theory. Finally, numerical examples for a given SFF scenario are presented to illustrate the performance of the controller. 相似文献
865.
866.
Junoh Jung Sang-Young Park Sung-Woo Kim Youngho Eun Young-Keun Chang 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2013
A nonlinear control technique pertaining to attitude synchronization problems is presented for formation flying spacecraft by utilizing the State-Dependent Riccati Equation (SDRE) technique. An attitude controller consisting of relative control and absolute control is designed using a reaction wheel assembly for regulator and tracking problems. To achieve effective relative control, the selective state-dependent connectivity is also adopted. The global asymptotic stability of the controller is confirmed using the Lyapunov theorem and is verified by Monte-Carlo simulations. An air-bearing-based Hardware-In-the-Loop Simulator (HILS) is also developed to validate the proposed control laws in real-time environments. The SDRE controller is discretized for implementation of a real-time processor in the HILS. The pointing errors are about 0.2° in the numerical simulations and about 1° in the HILS simulations, and experimental simulations confirm the effectiveness of the control algorithm for attitude synchronization in a spacecraft formation flying mission. Consequently, experiments using the HILS in a real-time environment can appropriately perform spacecraft attitude synchronization algorithms for formation flying spacecraft. 相似文献
867.
Masahiko Uetsuhara Toshiya Hanada 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2013
Identifying spacecraft breakup events is an essential issue for better understanding of the current orbital debris environment. This paper proposes an observation planning approach to identify an orbital anomaly, which appears as a significant discontinuity in archived orbital history, as a spacecraft breakup. The proposed approach is applicable to orbital anomalies in the geostationary region. The proposed approach selects a spacecraft that experienced an orbital anomaly, and then predicts trajectories of possible fragments of the spacecraft at an observation epoch. This paper theoretically demonstrates that observation planning for the possible fragments can be conducted. To do this, long-term behaviors of the possible fragments are evaluated. It is concluded that intersections of their trajectories will converge into several corresponding regions in the celestial sphere even if the breakup epoch is not specified and it has uncertainty of the order of several weeks. 相似文献
868.
Liang Sun 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2019,63(7):2229-2238
A saturated fault-tolerant attitude tracking controller for disturbed rigid spacecraft is derived using nonlinear state feedback control method. The proposed controller achieves the constraints of control inputs by directly using the bounded function instead of the traditional saturation compensator technique, and the active tolerance to the partial loss of actuator effectiveness is also achieved by directly using the known bounds of the actuator faults in the controller. Specifically, compared with the traditional saturated control methods, a continuously bounded nonlinear function in the proposed controller is used to guarantee that the actuator outputs are smoothly bounded under the prescribed constraints. Based on some properties of the attitude tracking dynamics, the proposed controller can ensure the attitude tracking errors converge to small neighborhoods of zero via stability analysis in the Lyapunov framework. Simulation results are presented to illustrate the effectiveness of the control scheme. 相似文献
869.
孟志华 《郑州航空工业管理学院学报(管理科学版)》2011,29(1)
当前,环境问题已经逐渐超越国界成为一个全球性的问题,世界各国对于环境相关的财务问题尤其是环境会计和环境审计越来越重视,而环境绩效审计是环境审计的重要方面和发展趋势。为了对环境绩效审计研究的发展轨迹与现状得到一个全面、准确的认识,文章在掌握了国内大量相关资料的基础上,运用规范研究方法,对环境绩效审计研究所涉及的定义、内容和方法进行了简要地总结和评价,并对未来的环境绩效审计研究提出了相应的建议,以期丰富我国的环境绩效审计理论。 相似文献
870.
随着工业的快速发展,环保问题日趋严重,人们对环境保护的意识日益提高,要求对污染源必须进行24小时不间断的实时监测。设计一种采用GPRS技术的方式,解决原有环保监测传输控制器费用高、覆盖范围小的问题,实现在环保监测系统中增加或减少污染源的环保监测点对污染值影响的最小化。 相似文献