The Experts below are selected from a list of 5913 Experts worldwide ranked by ideXlab platform
Yingmin Jia - One of the best experts on this subject based on the ideXlab platform.
-
analytical solutions to the matrix inequalities in the robust control scheme based on implicit lyapunov function for spacecraft rendezvous on Elliptical Orbit
Iet Control Theory and Applications, 2017Co-Authors: Xiwen Tian, Yingmin JiaAbstract:In this study, the problem of robust control for spacecraft rendezvous on Elliptical Orbit, which contains parameter uncertainties and external disturbances, is investigated based on the implicit Lyapunov function method. A state-feedback controller is first designed, and its existence conditions are derived in terms of linear matrix inequalities (LMIs) which should be solved in real time. An analytical solution to these LMIs is provided to greatly reduce the computational burden. On the basis of the state-feedback analysis, an observer-based output-feedback controller is proposed, and it is proved finite-time stable by constructing an analytical solution to the parameterised nonlinear matrix inequalities (NLMIs). The advantage brought by the proposed analytical solution is that whether these NLMIs hold only need to be checked at two points, while in previous researches they were supposed to be checked at infinite points. The effectiveness of the theoretical results is illustrated by simulation examples.
-
robust control for Elliptical Orbit spacecraft rendezvous using implicit lyapunov function
Chinese Intelligent Systems Conference, 2016Co-Authors: Xiwen Tian, Mingdong Hou, Yingmin Jia, Changqing ChenAbstract:In this paper, a robust control scheme using implicit Lyapunov function is proposed to solve the Elliptical Orbit spacecraft rendezvous problem in the presence of parameter uncertainties and external disturbances. First, an implicit Lyapunov function is constructed that is to be used in control design, and the finite-time convergence is guaranteed by some linear matrix inequalities depending on variable parameter and the implicit Lyapunov function. Then, an analytical feasible solution of these inequalities is provided for practical implementation. Simulation example is given to illustrate the effectiveness of the proposed method.
Xiangyu Gao - One of the best experts on this subject based on the ideXlab platform.
-
an optimal control approach to spacecraft rendezvous on Elliptical Orbit
Optimal Control Applications & Methods, 2015Co-Authors: Xiangyu Gao, K L Teo, Guangren DuanAbstract:Summary In this paper, we consider a linear quadratic regulator control problem for spacecraft rendezvous in an Elliptical Orbit. A new spacecraft rendezvous model is established. On the basis of this model, a linear quadratic regulator control problem is formulated. A parametric Lyapunov differential equation approach is used to design a state feedback controller such that the resulting closed-loop system is asymptotically stable, and the performance index is minimized. By an appropriate choice of the value of a parameter, an approximate state feedback controller is obtained from a solution to the periodic Lyapunov differential equation, where the periodic Lyapunov differential equation is solved on the basis of a new numerical algorithm. The spacecraft rendezvous mission under the controller obtained will be accomplished successfully. Several illustrative examples are provided to show the effectiveness of the proposed control design method. Copyright © 2014 John Wiley & Sons, Ltd.
-
robust h control of spacecraft rendezvous on Elliptical Orbit
Journal of The Franklin Institute-engineering and Applied Mathematics, 2012Co-Authors: Xiangyu Gao, K L Teo, Guangren DuanAbstract:Abstract This paper investigates the robust H ∞ control problem of spacecraft rendezvous on Elliptical Orbit. Based on Lyapunov theory, a sufficient condition for the existence of the robust H ∞ controller is given in terms of the periodic Riccati differential equation (RDE). Then, a stabilizable controller design method based on a fast multi-shot algorithm is proposed. With the controller obtained, the spacecraft rendezvous mission can be accomplished. An illustrative example is provided to show the effectiveness of the proposed control design method.
Xiwen Tian - One of the best experts on this subject based on the ideXlab platform.
-
analytical solutions to the matrix inequalities in the robust control scheme based on implicit lyapunov function for spacecraft rendezvous on Elliptical Orbit
Iet Control Theory and Applications, 2017Co-Authors: Xiwen Tian, Yingmin JiaAbstract:In this study, the problem of robust control for spacecraft rendezvous on Elliptical Orbit, which contains parameter uncertainties and external disturbances, is investigated based on the implicit Lyapunov function method. A state-feedback controller is first designed, and its existence conditions are derived in terms of linear matrix inequalities (LMIs) which should be solved in real time. An analytical solution to these LMIs is provided to greatly reduce the computational burden. On the basis of the state-feedback analysis, an observer-based output-feedback controller is proposed, and it is proved finite-time stable by constructing an analytical solution to the parameterised nonlinear matrix inequalities (NLMIs). The advantage brought by the proposed analytical solution is that whether these NLMIs hold only need to be checked at two points, while in previous researches they were supposed to be checked at infinite points. The effectiveness of the theoretical results is illustrated by simulation examples.
-
robust control for Elliptical Orbit spacecraft rendezvous using implicit lyapunov function
Chinese Intelligent Systems Conference, 2016Co-Authors: Xiwen Tian, Mingdong Hou, Yingmin Jia, Changqing ChenAbstract:In this paper, a robust control scheme using implicit Lyapunov function is proposed to solve the Elliptical Orbit spacecraft rendezvous problem in the presence of parameter uncertainties and external disturbances. First, an implicit Lyapunov function is constructed that is to be used in control design, and the finite-time convergence is guaranteed by some linear matrix inequalities depending on variable parameter and the implicit Lyapunov function. Then, an analytical feasible solution of these inequalities is provided for practical implementation. Simulation example is given to illustrate the effectiveness of the proposed method.
Guangren Duan - One of the best experts on this subject based on the ideXlab platform.
-
an optimal control approach to spacecraft rendezvous on Elliptical Orbit
Optimal Control Applications & Methods, 2015Co-Authors: Xiangyu Gao, K L Teo, Guangren DuanAbstract:Summary In this paper, we consider a linear quadratic regulator control problem for spacecraft rendezvous in an Elliptical Orbit. A new spacecraft rendezvous model is established. On the basis of this model, a linear quadratic regulator control problem is formulated. A parametric Lyapunov differential equation approach is used to design a state feedback controller such that the resulting closed-loop system is asymptotically stable, and the performance index is minimized. By an appropriate choice of the value of a parameter, an approximate state feedback controller is obtained from a solution to the periodic Lyapunov differential equation, where the periodic Lyapunov differential equation is solved on the basis of a new numerical algorithm. The spacecraft rendezvous mission under the controller obtained will be accomplished successfully. Several illustrative examples are provided to show the effectiveness of the proposed control design method. Copyright © 2014 John Wiley & Sons, Ltd.
-
robust h control of spacecraft rendezvous on Elliptical Orbit
Journal of The Franklin Institute-engineering and Applied Mathematics, 2012Co-Authors: Xiangyu Gao, K L Teo, Guangren DuanAbstract:Abstract This paper investigates the robust H ∞ control problem of spacecraft rendezvous on Elliptical Orbit. Based on Lyapunov theory, a sufficient condition for the existence of the robust H ∞ controller is given in terms of the periodic Riccati differential equation (RDE). Then, a stabilizable controller design method based on a fast multi-shot algorithm is proposed. With the controller obtained, the spacecraft rendezvous mission can be accomplished. An illustrative example is provided to show the effectiveness of the proposed control design method.
Alexander P Trishchenko - One of the best experts on this subject based on the ideXlab platform.
-
observing polar regions from space comparison between highly Elliptical Orbit and medium earth Orbit constellations
Journal of Atmospheric and Oceanic Technology, 2019Co-Authors: Alexander P Trishchenko, Louis Garand, L TrichtchenkoAbstract:AbstractContinuous observation of polar regions from space remains an important unsolved technical challenge of great interest for the international meteorological community. This capacity would al...
-
assimilation of circumpolar wind vectors derived from highly Elliptical Orbit imagery impact assessment based on observing system simulation experiments
Journal of Applied Meteorology and Climatology, 2013Co-Authors: Louis Garand, J Feng, Sylvain Heilliette, Y J Rochon, Alexander P TrishchenkoAbstract:AbstractThere is a well-recognized spatiotemporal meteorological observation gap at latitudes higher than 55°, especially in the region 55°–70°. A possible solution to address this issue is a constellation of four satellites in a highly Elliptical Orbit (HEO), that is, two satellites for each polar region. An important satellite product to support weather prediction is atmospheric motion wind vectors (AMVs). This study uses observing system simulation experiments (OSSEs) to evaluate the benefit to forecasts resulting from the assimilation of HEO AMVs covering one or both polar regions. The OSSE employs the operational global data assimilation system of the Canadian Meteorological Center. HEO AMVs are assimilated north of 50°N and south of 50°S. From 2-month assimilation cycles, the study examines the following three issues: 1) the impact of AMV assimilation in the real system, and how this compares to the impact seen in the simulated system, 2) the added value of HEO AMVs in the Arctic on top of what is c...
-
observing polar regions from space advantages of a satellite system on a highly Elliptical Orbit versus a constellation of low earth polar Orbiters
Canadian Journal of Remote Sensing, 2012Co-Authors: Alexander P Trishchenko, Louis GarandAbstract:Recent reports on Arctic climate change sparked an interest in the development of a new observing system for this region, specifically a satellite system making use of a highly Elliptical Orbit (HEO), an idea supported by the World Meteorological Organization. This paper attempts to quantify the advantages of such a system relative to a traditional constellation of Lower Earth Orbit (LEO) polar satellites. A realistic two-satellite HEO system is compared with currently operating two-, four-, and seven-satellite LEO constellations in terms of spatio-temporal coverage and capability to provide sequences of single, dual, and triplet images at a required temporal resolution. This is important to properly monitor dynamic events, such as volcanic ash transport, frontal systems, smoke from wild fires, and cloud motion from which wind vectors are derived. A two-satellite HEO system is 5–10 times more efficient for monitoring dynamic events from image pairs above 70°N than a standard four-satellite morning-afterno...
-
three apogee 16 h highly Elliptical Orbit as optimal choice for continuous meteorological imaging of polar regions
Journal of Atmospheric and Oceanic Technology, 2011Co-Authors: Alexander P Trishchenko, Louis Garand, L TrichtchenkoAbstract:AbstractA highly Elliptical Orbit (HEO) with a 16-h period is proposed for continuous meteorological imaging of polar regions from a two-satellite constellation. This Orbit is characterized by three apogees (TAP) separated by 120°. The two satellites are 8 h apart, with repeatable ground track in the course of 2 days. Advantages are highlighted in comparison to the Molniya 12-h Orbit described in detail in a previous study (Trishchenko and Garand). Orbital parameters (period, eccentricity, and inclination) are obtained as a result of an optimization process. The principles of Orbit optimization are based on the following four key requirements: spatial resolution (apogee height), the altitude of crossing the trapped proton region at the equator (minimization of radiation doze caused by trapped protons), imaging time over the polar regions, and the stability of the Orbit, which is mostly defined by the rotation of perigee. The interplay between these requirements points to a 16-h period with an eccentricity...