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Lei Jin and Yingjie Li
An attitude control strategy for an under-actuated spacecraft with two reaction wheels is proposed, using the active assistance of solar radiation pressure torque. By changing the rotation angles of the solar panels, the magnitude and direction of the so...
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Charalampos Papakonstantinou, Vaios Lappas and Vassilis Kostopoulos
This paper addresses the problem of singularity avoidance in a cluster of four Single-Gimbal Control Moment Gyroscopes (SGCMGs) in a pyramid configuration when used for the attitude control of a satellite by introducing a new gimballed control moment gyr...
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Jihe Wang, Qingxian Jia and Dan Yu
The issue of active attitude fault-tolerant stabilization control for spacecrafts subject to actuator faults, inertia uncertainty, and external disturbances is investigated in this paper. To robustly and accurately reconstruct actuator faults, a novel mi...
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Charalampos Papakonstantinou, Georgios Moraitis, Vaios Lappas and Vassilis Kostopoulos
In this paper, a low-cost, miniature spacecraft attitude control simulator is presented for testing miniature actuators such as Nano Control Moment Gyroscopes (CMGs) for simple maneuvers. The experimental setup is composed by an attitude control system (...
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Limei Ma, Yongheng Zhang, Yuli Niu, Yong Zhao, Shaoya Guan, Zijing Wang and Tuoda Wu
Ball-shell rotors with non-standard shapes, non-uniform conductive coatings, and eccentric masses machined by conventional processes constrain the improvement of levitation and torque accuracy of magnetically levitated momentum balls. This paper focuses ...
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Olli Jansson and Matthew W. Harris
This paper presents new techniques for the trajectory design and control of nonlinear dynamical systems. The technique uses a convex polytope to bound the range of the nonlinear function and associates with each vertex an auxiliary linear system. Provide...
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Ting Jin, Guohua Kang, Jian Cai, Shaoxia Jia, Jinghua Yang, Xinghua Zhang, Zhenhua Zhang, Long Li and Fangfang Liu
For a novel disturbance-free payload (DFP) spacecraft, it is difficult to isolate the low-frequency disturbances owing to the umbilical cables, which decreases the pointing accuracy and stability of the payload. In this research, an improved DFP spacecra...
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Mohammed A. A. Desouky and Ossama Abdelkhalik
This paper is concerned with magnetic attitude control of spacecraft. The operation of the magnetic actuators is usually on a duty cycle; during the off times in this duty cycle the magnetometers are used to measure the magnetic field around the spacecra...
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Chao Song, Caizhi Fan, Haibo Song and Mengmeng Wang
Previous staring attitude control techniques utilize the geographic location of a ground target to dictate the direction of the camera?s optical axis, while the assembly accuracy and the internal structure of the spaceborne camera are not considered. Thi...
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Ting Song, Zixuan Zheng, Yufei Guo and Jianping Yuan
A model-free control method is applied to the attitude and orbital operation of the post-capture combined spacecraft, which consists of a space robot and debris. The main contribution of this paper lies in the following three aspects. Firstly, the discre...
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Charalampos Papakonstantinou, Ioannis Daramouskas, Vaios Lappas, Vassilis C. Moulianitis and Vassilis Kostopoulos
This paper addresses the problem of singularity avoidance for a 4-Control Moment Gyroscope (CMG) pyramid cluster, as used for the attitude control of a satellite using machine learning (ML) techniques. A data-set, generated using a heuristic algorithm, r...
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Zachary Lewis, Joshua Ten Eyck, Kyle Baker, Eryn Culton, Jonathan Lang and Timothy Sands
The novel contribution in this manuscript is an expansion of the current state-of-the-art in the geometric installation of control moment gyroscopes beyond the benchmark symmetric skewed arrays and the four asymmetric arrays presented in recent literatur...
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Ting Jin, Guohua Kang, Jian Cai, Shaoxia Jia, Jinghua Yang, Xinghua Zhang, Zhenhua Zhang, Long Li and Fangfang Liu
The low-frequency disturbances transmitted by flexible cables are difficult to be attenuated for a novel disturbance-free payload spacecraft, which decreases the payload?s pointing accuracy and stability. In this research, a new spacecraft configuration ...
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Andrew Sandberg and Timothy Sands
Spacecraft need to be able to reliably slew quickly and rather than simply commanding a final angle, a trajectory calculated and known throughout a maneuver is preferred. A fully solved trajectory allows for control based off comparing current attitude t...
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Yini Zhong and Rui Zhong
One of the important applications of the space tethered system is formation flying. To satisfy the requirement for interferometry of ground targets by remote-sensing satellites, a new type of tethered solar sail spacecraft has been proposed in recent res...
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Andrea Colagrossi and Michèle Lavagna
The capability to orient the solar arrays of a spacecraft toward the Sun is an ultimate asset for any attitude determination and control subsystem (ADCS). This ability should be maintained in any operative circumstance, either nominal or off-nominal, to ...
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Weichao Chi, He Ma, Caihua Wang and Tianyu Zhao
The Stewart platform, a classical mechanism proposed as the parallel operation apparatus of robots, is widely used for vibration isolation in various fields. In this paper, a design integrating both small attitude control and vibration isolation for high...
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Tengfei Zhang and Rongjun Mu
To deal with the attitude tracking control problem of a struck or pierced geocentric polar displaced solar sail (GPDSS), an attitude adaptive control strategy is proposed in this paper under the complex conditions of unknown inertial parameters, external...
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M. Salim Farissi, Stefano Carletta, Augusto Nascetti and Paolo Teofilatto
The subject of this work is the implementation and experimental testing of a purely magnetic attitude control strategy, which can provide stabilization after the deployment and pointing of the spacecraft without any attitude information. In particular, t...
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Ahmed Mahfouz, Gabriella Gaias, D. M. K. K. Venkateswara Rao and Holger Voos
In this paper, the problem of autonomous optimal absolute orbit keeping for a satellite mission in Low Earth Orbit using electric propulsion is considered. The main peculiarity of the approach is to support small satellite missions in which the platform ...
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