Li B.,Harbin Institute of Technology |
Chen X.,Harbin Institute of Technology |
Zheng X.,Shanghai Aerospace Control Engineering Institute |
Pan H.,Shanghai Aerospace Control Engineering Institute
Hongwai yu Jiguang Gongcheng/Infrared and Laser Engineering | Year: 2012
The number of pixels scanned in star image can be large with conventional star tracking algorithm under large maneuvering of the vehicle. The feasibility of irrelevant star within threshold scan windows is increased. And the number of calculating angular separation between two stars is increased. This results in the decreasing of the update rate of star sensor. Therefore, the feasibility of error stars from star image is increased. Above all, an autonomous star tracking algorithm with high angle velocity was presented in this paper. Firstly, the next frame potential attitude was estimated according to previous attitudes. Secondly, the next frame ideal star centriodings of stars in FOV was calculated according to the potential attitude. Finally, all the real star centriodings would be obtained within the threshold scan windows of the ideal star centriodings. This algorithm can not only improve update rate of star sensor, but also avoid fault star pattern recognition. At last, the algorithm was tested by simulation and night sky experiment. The algorithm will be applied star sensor of satellite GNC.
Sun J.,Harbin Institute of Technology |
Sun J.,Shanghai Aerospace Control Engineering Institute |
Zhang S.-J.,Harbin Institute of Technology |
Li B.-H.,Harbin Institute of Technology
Guangxue Jingmi Gongcheng/Optics and Precision Engineering | Year: 2013
An autonomous navigation algorithm is proposed using the sensor with functions of a star sensor and an ultraviolet earth sensor. The sensor has two Field of Views (FOVs ) named FOV1 and FOV2. The FOV1 is used for star sensor and for calculating the optical axis direction of the FOV1. The FOV2 is used for ultraviolet earth sensor and for calculating the vector of the earth. The state equation of integrated system is established by the deduced orbit dynamic model based on orbit six elements and the attitude kinematic model. Then, the observed equation of integrated system is established by using the difference of the measurement value and the estimated value, and the satellite orbit parameters were calculated according to the Discrete Extend Kalman Filter(DEKF)algorithm. An experiment on the ultraviolet sensor shows that not only the errors of satellite positions is improved from 1000 m to 500 m and the errors for satellite velocities are improved from 100 m/s to 40 m/s, but also the errors of periodic sine resulted from the angle between the sun light and ground level is eliminated. These results show the algorithm to be well robust.
Zhang S.J.,Harbin Institute of Technology |
Cao X.B.,Harbin Institute of Technology |
Zhang F.,Harbin Institute of Technology |
He L.,Shanghai Aerospace Control Engineering Institute
Science in China, Series F: Information Sciences | Year: 2010
To determine the relative pose between an object and a single camera using 2D-to-3D point correspondences, a kind of iterative methods based on inverse projection ray approach is proposed. An iterative algorithm which is divided into depth recovery stage and absolute orientation stage is also proposed. In the first stage, the optimal translation vector is first computed in terms of rotation matrix via least square method, then the depths of the observed points are estimated by projecting the estimated point orthogonally to the inverse projection ray defined by the image point, and finally 3D points are reconstructed using the estimated depths from previous step. In the second stage, the optimal rotation matrix is estimated by applying Umeyama algorithm to fitting of the 3D model points and 3D estimated points. The above two stages are repeated until the result converges. The global convergence of the two-stage iterative algorithm is proven based on the global convergence theorem. Finally, a spacecraft docking application is implemented to test the effectiveness and convergence of the proposed algorithm by mathematical simulation and physical simulation. © 2010 Science China Press and Springer-Verlag Berlin Heidelberg.
Shijie Z.,Harbin Institute of Technology |
Fenghua L.,Harbin Institute of Technology |
Xibin C.,Harbin Institute of Technology |
Liang H.,Shanghai Aerospace Control Engineering Institute
Chinese Journal of Aeronautics | Year: 2010
Visual sensors are used to measure the relative state of the chaser spacecraft to the target spacecraft during close range rendezvous phases. This article proposes a two-stage iterative algorithm based on an inverse projection ray approach to address the relative position and attitude estimation by using feature points and monocular vision. It consists of two stages: absolute orientation and depth recovery. In the first stage, Umeyama's algorithm is used to fit the three-dimensional (3D) model set and estimate the 3D point set while in the second stage, the depths of the observed feature points are estimated. This procedure is repeated until the result converges. Moreover, the effectiveness and convergence of the proposed algorithm are verified through theoretical analysis and mathematical simulation. © 2010 Chinese Journal of Aeronautics.
Li C.,Harbin Institute of Technology |
Jiang B.,Harbin Institute of Technology |
Zhu Q.,Shanghai Aerospace Control Engineering Institute |
Yu C.,Harbin Institute of Technology
Chinese Control Conference, CCC | Year: 2015
In this paper, the finite-time attitude control problem for rigid spacecraft with external disturbance is addressed. First, a problem of existing non-singular terminal sliding mode is raised, and then we design a non-singular finite-time attitude controller by using a special Lyapunov function with a power integrator form, which enables the system states converge to a residual set in a finite time. Further, an adaptive non-singular terminal sliding mode controller is proposed to deal with the external disturbance. Numerical simulations are performed to illustrate the effectiveness of the proposed control schemes with fast convergence, high accuracy and good disturbance rejection property in the spacecraft control system. © 2015 Technical Committee on Control Theory, Chinese Association of Automation.
Cheng Y.,Nanjing University of Aeronautics and Astronautics |
Jiang B.,Nanjing University of Aeronautics and Astronautics |
Sun J.,Shanghai Aerospace Control Engineering Institute |
Sun J.,Shanghai Key Laboratory of Space Intelligent Control Technology |
And 2 more authors.
ICIC Express Letters | Year: 2011
This paper is concerned with the design of a robust actuator fault diagnosis and tolerant control scheme for satellite attitude control systems. A bank of sliding mode observers (SMOs) are firstly investigated to detect and isolate single actuator fault for satellite attitude control systems with input disturbance. When an actuator undergoes unknown fault, it is disabled. Under such condition, a novel fault tolerant controller based on sliding mode control method is proposed to keep system safe using the remaining actuators. Simulation results demonstrate the effectiveness of the proposed method for satellite attitude control systems. © 2011 ISSN 1881-803X.
Wang M.,Harbin Institute of Technology |
Gu Y.,Shanghai Aerospace Control Engineering Institute |
Li X.,Harbin Institute of Technology
Journal of Control Theory and Applications | Year: 2013
This paper is concerned with the control synthesis problem for systems with time-varying delay and actuator saturation. A new controller design method is proposed in which auxiliary feedback matrix method is adopted to handle the saturation term in the system. The improvement of the proposed method lies in the application of delay partitioning idea to further enlarge the estimated domain of attraction. All the results are given in terms of linear matrix inequalities. Finally, a numerical example is provided to demonstrate the effectiveness and superiority of our obtained results. © 2013 South China University of Technology, Academy of Mathematics and Systems Science, Chinese Academy of Sciences and Springer-Verlag Berlin Heidelberg.
Qu Y.,Harbin Institute of Technology |
Qu Y.,Shanghai Aerospace Control Engineering Institute |
Zhang J.,Harbin Institute of Technology |
Wu Y.,Harbin Institute of Technology |
Wang C.,Harbin Institute of Technology
ISSCAA2010 - 3rd International Symposium on Systems and Control in Aeronautics and Astronautics | Year: 2010
A so called sliding-backstepping controller for attitude maneuver in some large flexible satellite is put forward. Further, combined with theory of Extended State Observer (ESO), the controller has been improved to estimate and compensate the uncertainties. After the stability analysis, simulation was carried out in particular using Single Gimbal Control Moment Gyros (SGCMGs) as the momentum actuator and considering the first ten elastic modes. The results achieve the mission requirements and conform to aforementioned theoretical analysis. Furthermore, the improved controller has significant advantages in pointing accuracy and flexible suppression. ©2010 IEEE.
Liu F.,Harbin Institute of Technology |
Liu F.,Shanghai Aerospace Control Engineering Institute |
Ma G.,Harbin Institute of Technology |
Mei J.,Harbin Institute of Technology
Chinese Control Conference, CCC | Year: 2012
In this paper, the problem of cooperative control for relative translation of modular spacecraft is addressed under a general undirected communication topology without velocity measurements. We consider the full nonlinear translation dynamics near earth. Two cases are studied, namely, the coordinated regulation problem with a stationary reference and the leaderless consensus problem without any leader. In the first case, a control algorithm is proposed to aim that the modules rendezvous at a prescribed point where the position of the point can be measured by only a few modules. In the second case, we propose a control algorithm without velocity measurements for the leaderless consensus of modular spacecraft. The modules rendezvous at a fixed point which is determined by the initial positions and the control gains of the modules. In both cases, passivity-based estimators are designed for the constraints that no velocity information is used. © 2012 Chinese Assoc of Automati.
Chang J.,Beijing Institute of Technology |
Zhao L.,Beijing Institute of Technology |
Han F.,Shanghai Aerospace Control Engineering Institute
AIAA SPACE 2015 Conference and Exposition | Year: 2015
Taking a space-based operationally responsive system (SORS) as background, a deployment design for space platform of a SORS is proposed and a specific way of noncoplanar orbital transfer is analyzed. Firstly, the components of the SORS are briefly introduced. According to the analysis of the time and impulse for transfer, a deployment design for space platform of a SORS is designed. Secondly a specific way of non-coplanar orbital transfer is analyzed, which is transfer at the intersection. The impulse for transfer and transfer time are optimized to be minimum at the same time, and the space launch platforms of deployed in advance in the deployment design are taken as design variable. Under the deployment design for space platform of a SORS, the results show that transfer at the intersection not only could reduce a lot of time in the SORS, but also can generate a smaller impluse. © 2015, American Institute of Aeronautics and Astronautics Inc, AIAA. All Rights Reserved.