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Journal articles on the topic 'Micro-Satellite Attitude Determination'

Author: Grafiati
Published: 4 June 2021
Last updated: 7 September 2023

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1

Xiu-feng, He, and Ling Keck-voon. "Micro-Satellite Attitude Determination Using GPS Carrier Phases." Wuhan University Journal of Natural Sciences 8, no. 2 (2003): 693–96. http://dx.doi.org/10.1007/bf02899836.

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2

Ouyang, Gaoxiang, Xin Dong, and Xin Li. "Micro-Satellite Attitude Determination with Only a Single Horizon Sensor." MATEC Web of Conferences 51 (2016): 03008. http://dx.doi.org/10.1051/matecconf/20165103008.

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3

Cao, Lu, Wei Wei Yang, Xiao Qian Chen, and Yi Yong Huang. "The Research of Micro-Satellite Attitude Determination Based on Predictive Filter." Applied Mechanics and Materials 110-116 (October 2011): 5413–19. http://dx.doi.org/10.4028/www.scientific.net/amm.110-116.5413.

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— An extended predictive filter is presented for attitude determination of Micro-satellite based on the basic theory of predictive filter. This algorithm enhances the precision of kinematics equation, accurately estimates satellite attitude angle and angular velocity using measurement vectors from magnetometer and sun sensors by predicting model errors and angular velocity errors one step ahead. In addition, a new measurement model is derived about angular velocity, which improved the efficiency of the use of measurement vectors. Simulation results show both the high reliability and precision
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4

Chen, Yajing, Tao Meng, and Zhonghe Jin. "Agile Micro-nano Satellite Attitude Estimation with Lost Measurements." Journal of Physics: Conference Series 2459, no. 1 (2023): 012138. http://dx.doi.org/10.1088/1742-6596/2459/1/012138.

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Abstract Aiming at the problem of lost measurement in attitude determination process of the agile micro-nano satellite, a novel algorithm is proposed employing the Bernoulli process to describe the loss process. Firstly,the model of gyro and star sensors as well as the satellite attitude estimation system simplified with gyro is given. Since the missing observations, the modified EKF algorithm is derived by combining a Bernoulli random variable and a real-time measurement noise correction algorithm. Then the convergence of the improved algorihtm is analyzed, and the bottom boundary condition f
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5

Shou, Ho-Nien. "Microsatellite Attitude Determination and Control Subsystem Design and Implementation: Software-in-the-Loop Approach." Mathematical Problems in Engineering 2014 (2014): 1–12. http://dx.doi.org/10.1155/2014/904708.

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The paper describes the development of a microsatellite attitude determination and control subsystem (ADCS) and verification of its functionality by software-in-the-loop (SIL) method. The role of ADCS is to provide attitude control functions, including the de-tumbling and stabilizing the satellite angular velocity, and as well as estimating the orbit and attitude information during the satellite operation. In Taiwan, Air Force Institute of Technology (AFIT), dedicating for students to design experimental low earth orbit micro-satellite, called AFITsat. For AFITsat, the operation of the ADCS co
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6

Zhou, Meng Meng, G. M. Gao, and Hong Bo Yang. "Multi-Source Information Fusion Based on Kalman Filtering." Applied Mechanics and Materials 727-728 (January 2015): 863–66. http://dx.doi.org/10.4028/www.scientific.net/amm.727-728.863.

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Thehigh-frequency angular micro-vibration on satellite platform results in theoptical axis pointing decreasing accuracy. The Kalman filtering based on attitudeinformation fusion method is presented to solve this case and improve the pointing accuracy of attitude determination. Thesimulation results indicate that the estimated accuracy of Kalman filteringattitude information fusion method is better than the result only fromconventional low frequency sensor. Accordingly, the attitude information fusionmethod is verified and accuracy.
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7

Shou, Ho Nien. "Discoid and Asymmetrical Micro-Satellite Propulsion Mode Attitude Control with Great Mass Change and without Angular Rate Sensor." Applied Mechanics and Materials 479-480 (December 2013): 753–57. http://dx.doi.org/10.4028/www.scientific.net/amm.479-480.753.

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The center of mass of the micro-satellite can offset due to fuel consumption in the course of propulsion, with the interference of external orbital environment such as gravity gradient torque and solar radiation torque. If the structural shape is discoid and asymmetrical, the attitude control may be difficult. The only solution is to design a robust controller, so that the attitude pointing of the satellite can meet the mission requirements with the interference of internal parameter perturbation and external disturbance. This study applied the robust control theory control law in the design o
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8

Ziebart, Marek, and Paul Cross. "LEO GPS attitude determination algorithm for a micro-satellite using boom-arm deployed antennas." GPS Solutions 6, no. 4 (2003): 242–56. http://dx.doi.org/10.1007/s10291-002-0023-5.

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9

LE, XUAN HUY, KAZUYA ISHIZAKA, and SABURO MATUNAGA. "H2 A robust attitude determination algorithm based on Unscented Kalman Filter for Micro Satellite." Proceedings of the Space Engineering Conference 2010.19 (2011): _H2–1_—_H2–6_. http://dx.doi.org/10.1299/jsmesec.2010.19._h2-1_.

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10

ZHANG He, QIN Weiwei, ZHOU Cheng, SONG Hengxin, HUA Yufeng, and WANG Yu. "Attitude Determination Algorithm for Micro-satellite Based on High-order UKF Using Information Fusion." Chinese Journal of Space Science 40, no. 6 (2020): 1091. http://dx.doi.org/10.11728/cjss2020.06.1091.

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11

Yalu, Cao, Zhao Jiahao, Xing Fei, and You Zheng. "Structural process and testing of tunneling attitude sensor based on gravity gradient torque measurements." Journal of Micromechanics and Microengineering 31, no. 12 (2021): 125013. http://dx.doi.org/10.1088/1361-6439/ac3467.

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Abstract The function of determining the orientation of a satellite in orbit is known as attitude determination. Depending on the missions, this important function is typically performed by different optical instruments. Due to the limited field of view, multiple optical sensors are placed in all directions to ensure large coverage. A kind of inertial sensor that uses the gravity gradient torque as a reference for attitude determination was proposed recently. At present, the volume of this kind of sensors is large and the accuracy is not high enough. In this paper, we propose an attitude senso
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12

Kuwahara, Toshinoi, Yuji Sakamoto, Kazuya Yoshida, et al. "B2 Development and Verification Environment for the Attitude Determination and Control System of the Micro-satellite RISESAT." Proceedings of the Space Engineering Conference 2011.20 (2012): _B2–1_—_B2–5_. http://dx.doi.org/10.1299/jsmesec.2011.20._b2-1_.

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13

Liu, Changhua, Jide Qian, Zuocai Wang, and Jin Wu. "A linear computationally efficient Kalman filter for robust attitude estimation from horizon measurements and GNSS observations." Sensor Review 40, no. 2 (2020): 153–65. http://dx.doi.org/10.1108/sr-07-2019-0186.

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Purpose For fixed-wing micro air vehicles, the attitude determination is usually produced by the horizon/Global Navigation Satellite System (GNSS) in which the GNSS provides yaw estimates, while roll and pitch are computed using horizon sensors. However, the attitude determination has been independently obtained from the two sensors, which will result in insufficient usage of data. Also, when implementing attitude determination algorithms on embedded platforms, the computational resources are highly restricted. This paper aims to propose a computationally efficient linear Kalman filter to solv
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14

Zhao, Zeyang, Zhaokui Wang, and Yulin Zhang. "A Spherical Micro Satellite Design and Detection Method for Upper Atmospheric Density Estimation." International Journal of Aerospace Engineering 2019 (January 28, 2019): 1–15. http://dx.doi.org/10.1155/2019/1758956.

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A spherical microsatellite, aimed at technology verification of upper atmospheric density detection and precision orbit determination in low Earth orbit (LEO), has been developed by Tsinghua University and is scheduled to launch in the second half of 2019. In order to reduce the influence of other nonconservative forces, the area-to-mass ratio of the satellite was designed to ensure that the aerodynamic drag of the satellite is more than one to two orders of magnitude greater than the solar pressure perturbation. The influence of the components of the antenna, separation support, and solar cel
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15

Sabatini, Roberto, Leopoldo Rodríguez, Anish Kaharkar, Celia Bartel, Tesheen Shaid, and David Zammit-Mangion. "LOW-COST NAVIGATION AND GUIDANCE SYSTEMS FOR UNMANNED AERIAL VEHICLES — PART 2: ATTITUDE DETERMINATION AND CONTROL." Annual of Navigation 20, no. 1 (2013): 97–126. http://dx.doi.org/10.2478/aon-2013-0008.

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ABSTRACT This paper presents the second part of the research activity performed by Cranfield University to assess the potential of low-cost navigation sensors for Unmanned Aerial Vehicles (UAVs). This part focuses on carrier-phase Global Navigation Satellite Systems (GNSS) for attitude determination and control of small to medium size UAVs. Recursive optimal estimation algorithms were developed for combining multiple attitude measurements obtained from different observation points (i.e., antenna locations), and their efficiencies were tested in various dynamic conditions. The proposed algorith
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16

Carletta, Stefano, Augusto Nascetti, Sagar S. Gosikere Matadha, et al. "Characterization and Testing of the Passive Magnetic Attitude Control System for the 3U AstroBio CubeSat." Aerospace 9, no. 11 (2022): 723. http://dx.doi.org/10.3390/aerospace9110723.

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AstroBio CubeSat is a mission funded by the Italian Space Agency aimed at validating novel lab-on-chip technology, that would enable the use of micro- and nanosatellites as autonomous orbiting laboratories for research in astrobiology. This 3U CubeSat is equipped with a passive magnetic attitude control system (PMACS), including permanent magnets and hysteresis strips, which allows for stabilizing the spacecraft with the longitudinal axis in the direction of the geomagnetic field vector. This work presents the process followed for the experimental characterization of the system, performed on t
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17

Turner, D., A. Lucieer, M. McCabe, S. Parkes, and I. Clarke. "PUSHBROOM HYPERSPECTRAL IMAGING FROM AN UNMANNED AIRCRAFT SYSTEM (UAS) – GEOMETRIC PROCESSINGWORKFLOW AND ACCURACY ASSESSMENT." ISPRS - International Archives of the Photogrammetry, Remote Sensing and Spatial Information Sciences XLII-2/W6 (August 24, 2017): 379–84. http://dx.doi.org/10.5194/isprs-archives-xlii-2-w6-379-2017.

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In this study, we assess two push broom hyperspectral sensors as carried by small (10–15 kg) multi-rotor Unmanned Aircraft Systems (UAS). We used a Headwall Photonics micro-Hyperspec push broom sensor with 324 spectral bands (4–5 nm FWHM) and a Headwall Photonics nano-Hyperspec sensor with 270 spectral bands (6 nm FWHM) both in the VNIR spectral range (400–1000 nm). A gimbal was used to stabilise the sensors in relation to the aircraft flight dynamics, and for the micro-Hyperspec a tightly coupled dual frequency Global Navigation Sate
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18

Sabatini, Roberto, Celia Bartel, Anish Kaharkar, et al. "Low-Cost Navigation and Guidance Systems for Unmanned Aerial Vehicles — Part 1: Vision-Based and Integrated Sensors." Annual of Navigation 19, no. 2 (2012): 71–98. http://dx.doi.org/10.2478/v10367-012-0019-3.

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Abstract In this paper we present a new low-cost navigation system designed for small size Unmanned Aerial Vehicles (UAVs) based on Vision-Based Navigation (VBN) and other avionics sensors. The main objective of our research was to design a compact, light and relatively inexpensive system capable of providing the Required Navigation Performance (RNP) in all phases of flight of a small UAV, with a special focus on precision approach and landing, where Vision Based Navigation (VBN) techniques can be fully exploited in a multisensor integrated architecture. Various existing techniques for VBN wer
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19

Lin, C. L., J. C. Li, C. L. Chiu, Y. W. A. Wu, and Y. W. Jan. "Gyro-stellar inertial attitude estimation for satellite with high motion rate." Aeronautical Journal, April 18, 2022, 1–15. http://dx.doi.org/10.1017/aer.2022.38.

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Abstract For a common micro-satellite, orbiting in a circular sun-synchronous orbit (SSO) at an altitude between 500 and 600km, the satellite attitude during off-nadir imaging and staring-imaging operations can be up to ±45 degree on roll and pitch angles. During these off-nadir pointing for both multi-trip operation and staring imaging operations, the spacecraft body is commonly subject to high-rate motion. This posts challenges for a spacecraft attitude determination subsystem called Gyro Stellar Inertial Attitude Estimate (GS IAE), which employs gyros and star sensors to maintain the requir
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20

Stewart, Jon. "Oh Blessed Holy Caffeine Tree: Coffee in Popular Music." M/C Journal 15, no. 2 (2012). http://dx.doi.org/10.5204/mcj.462.

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Introduction This paper offers a survey of familiar popular music performers and songwriters who reference coffee in their work. It examines three areas of discourse: the psychoactive effects of caffeine, coffee and courtship rituals, and the politics of coffee consumption. I claim that coffee carries a cultural and musicological significance comparable to that of the chemical stimulants and consumer goods more readily associated with popular music. Songs about coffee may not be as potent as those featuring drugs and alcohol (Primack; Schapiro), or as common as those referencing commodities li
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