Developments of attitude determination and control system of microsats: A survey

He, Liang; Ma, Wenjie; Guo, Pengyu; Sheng, Tao

doi:10.1177/0959651819895173

Cited by 14 publications

(5 citation statements)

References 186 publications

(207 reference statements)

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“…An appropriate choice of α is possible with a compromise between system agility and the time required to achieve attitude control indices. The actuator specifies the maneuver rate, 29 and reaching the desired attitude with the requirements of pointing accuracy and pointing stability can be evaluated by numerical simulation. α is the setting parameter for which values close to zero make the system more agile and provide more time for stability.…”

Section: Attitude Path Design Algorithmmentioning

confidence: 99%

Attitude path design and adaptive robust tracking control of a remote sensing satellite in various imaging modes

Zarourati

Mirshams

Tayefi

2023

Proceedings of the Institution of Mechanical Engineers, Part G:

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This paper addresses the attitude path design of a remote sensing satellite in various imaging modes. The novel path design algorithm is based on local polynomial regression, which produces a smooth attitude path by receiving the size and timing of maneuvers in each axis according to the desired imaging mode. This algorithm is described for stereo and snapshot modes in an imaging operation. The adaptive robust tracking control (ARTC) law is designed using quaternion algebra to perform the required maneuvers in an attitude path. The ARTC structure includes a sliding mode strategy, a projection-based adaptive model compensation, and a linear feedback term. Suitable conditions for imaging in each mode and the time of taking the image are determined by defining and evaluating the attitude control indices. These indices are defined by the half-cone error along the payload line of sight and relative performance error as a jitter with a 3-sigma confidence level. Despite the challenges in the path design, such as smoothness, system agility, and finite time realization of indices, in a conventional stereo imaging mode, taking an image in the nadir-pointing attitude is neglected. As a result, our work provides suitable conditions for taking the image in this attitude with an interval of 1.2 s. Finally, numerical simulations and verification are performed using multidisciplinary simulation, indicating the effectiveness of the proposed algorithm and model-based ARTC law.

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Section: Attitude Path Design Algorithmmentioning

confidence: 99%

Attitude path design and adaptive robust tracking control of a remote sensing satellite in various imaging modes

Zarourati

Mirshams

Tayefi

2023

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…A S one of the most accurate sensors for determining satellite attitude [1], the star sensor can calculate the attitude without the need for prior information, which has been widely used in spacecraft. Star identification obtains the spacecraft spatial attitude information by matching stars within the current field of view(FOV) of the star sensor with reference stars in the navigation star catalog [2].…”

Section: Introductionmentioning

confidence: 99%

Star Identification Algorithm Based on Multi-Dimensional Features and Multi-Layered Joint Screening for Star Sensors

et al. 2023

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The algorithm for star identification is a crucial technology for determining the orientation of spacecraft using star sensors. Traditional star identification algorithms achieve matching by seeking a unique or a few optimal solutions. However, in high-noise environments, some solutions may be lost, which could result in matching failure. A new lost-in-space architecture algorithm aimed at rapid identification under high star position noise conditions by directly using star positions for final matching is proposed in this paper. The main idea of this algorithm is to construct sufficiently redundant navigation triangles, fully utilizing the physical relationships of the features and forming a screening method from high to low dimensions and from loose to strict. During identification, a multi-layer joint screening matching method is adopted to screen triangles as a whole, narrowing the range of matches quickly while retaining error tolerance. In a series of simulation experiments, this algorithm achieved identification rates of 99.51%, 99.06%, and 98.42% for 2.0 pixel star position noise, 1.0 Mv star magnitude noise, and 5 false stars, respectively. In terms of practical application, all 1000 star images taken by the star sensor in orbit have been successfully identified, and it only takes 28ms to identify each image. In addition, star images taken by consumer-grade cameras from the ground also show that the algorithm has strong robustness to star position noise, magnitude error and false star interference in more severe environments. This method provides partial algorithmic reference for non-specialized design of star sensors for low-cost, large-scale satellites in the future.INDEX TERMS Multi-dimensional features, multi-layered joint screening, star identification, star sensor, star tracker.

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“…8 To benefit from the complementary advantages of both systems and obtain an accurate and reliable measurement, INS/GPS integration is adopted. 9 For more detail about this research area, the readers are invited to consult the following references 10–13.…”

Section: Introductionmentioning

confidence: 99%

Robust attitude estimation for an unmanned aerial vehicle using multiple GPS receivers

Dhahbane¹,

Nemra²,

Sakhi³

2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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Estimation of the system state is an important task in the field of control, localization, and navigation. Many sensors are used to extract the attitude information. GPS (Global Positioning System) is widely used to provide position and velocity for ground and aerial vehicles. However, only a few research works have addressed the problem of attitude estimation using multiple GPS receivers. The main contribution of this paper consists on proposing a robust algorithm for attitude estimation of an unmanned aerial vehicle using INS/3GPS integration. First, we propose two alternative methods for attitude determination with three GPS receivers: Direct Computing Method (DCM) and Least Square Method (LSM) based on Singular Value Decomposition (SVD). Second, the attitude given by GPS receivers is fused with the measurement of a three-axis gyroscope using a robust Smooth Variable Structure Filter (SVSF). The optimal geometric configuration of GPS antennas is determined based on a deep performance analysis of the proposed system. Then, robustness analysis is assessed against measurement noise and parameters uncertainties. Simulation results are presented to demonstrate the robustness of the proposed approach. A more realistic evaluation of the proposed solution is obtained using an aerial vehicle type “Helicopter” from the Virtual Robot Experimentation Platform (VREP simulator). The proposed filter is compared with an Extended Kalman Filter (EKF). The obtained results have confirmed how much the SVSF is robust for attitude estimation in presence of the considered disturbances.

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Developments of attitude determination and control system of microsats: A survey

Cited by 14 publications

References 186 publications

Attitude path design and adaptive robust tracking control of a remote sensing satellite in various imaging modes

Attitude path design and adaptive robust tracking control of a remote sensing satellite in various imaging modes

Star Identification Algorithm Based on Multi-Dimensional Features and Multi-Layered Joint Screening for Star Sensors

Robust attitude estimation for an unmanned aerial vehicle using multiple GPS receivers

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