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The control problem of underactuated spacecraft chaotic attitude motion is investigated based on exponential reaching law in this paper. First, the underactuated spacecraft chaotic attitude system is written in nonlinear equation form with two controls. Once the trajectory planning of angular acceleration is preset, the dynamics equation of angular velocity error can be obtained. Then, the sliding...
Now nanosatellites of the CubeSat format are most popular among the other nanosatellites. The nanosatellites of the CubeSat format can be used for various purposes, for example, for carrying out the experiments on geophysical field studying, for remote sensing of the Earth with the low/average resolution, etc. The attitude control system plays an important role in the solution of goal-oriented problems...
This paper investigates the attitude maneuver control for flexible spacecraft, in which the torque saturation and unknown parameter uncertainties are considered. Firstly, a time-fuel optimal trajectory is developed such that a PD controller based on the trajectory is proposed. Then, in order to suppress the vibration of flexible appendages, a structure filter is designed for the first order elastic...
The control moment gyro (CMG) actuators used in attitude control of spacecraft suffer from the singularity problem where they fail to generate the output torque in some particular direction called the singular direction. In connection to the avoidance of the singularity, the notion of the potential function is discussed and shown to behave as an avoidance potential. Using the theory of the superquadric...
In this paper, the attitude tracking problem of rigid spacecraft without inertial or relative angular velocity measurements is investigated. The minimal attitude description, the modified Rodrigues parameters (MRPs), are utilized as the attitude parameters for the non-redundancy. The inherent passivity of the system describing the attitude tracking motion of the spacecraft is exploited. Then an attitude...
A solution to the attitude tracking problem of rigid bodies with kinematic representation directly on the special orthogonal group SO(3) of rotation matrices is proposed. A dynamic partial state feedback controller is designed to address the case where no angular velocity measurements are available. In addition, the gains in the control design can be tuned in advance to ensure that the torque inputs...
We derive a continuous nonlinear control law for spacecraft attitude trajectory tracking of arbitrary C1 attitude trajectories based on rotation matrices. This formulation provides almost global stabilizability, that is, Lyapunov stability of the desired equilibrium of the error system as well as convergence from all initial states except for a subset whose complement is open and dense. This controller...
This article deals with a zero-propellant maneuver guidance (ZPM) architecture to provide large-angle ISS (International Space Station) rotations. ZPM guidance commands are designed to avoid CMG (control moment gyroscope) momentum saturation. CMG desaturation is required to maintain spacecraft control capability and the manipulator's direction. The ZPM momentum-optimal trajectories were developed...
This paper considers control of a class of uncertain nonlinear systems which can be decoupled by state variable feedback. A variable structure control (VSC) law is derived such that in the closed-loop system the output variable asymptotically tracks a given output trajectory in spite of the uncertainty in the system. Based on this result, a control law is derived for the attitude control of an orbiting...
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