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rezaei, mohsen, Charmacani, Kamran, Hashemi Mehne, hamed, Norouzi, Yaser. (1401). The New Generation of Attitude Determination Sensor for LEO Satellite based on Induced Electric Field. نشریه مهندسی عمران امیرکبیر, 54(1), 29-38. doi: 10.22060/eej.2021.18885.5363
mohsen rezaei; Kamran Raissi Charmacani; hamed Hashemi Mehne; Yaser Norouzi. "The New Generation of Attitude Determination Sensor for LEO Satellite based on Induced Electric Field". نشریه مهندسی عمران امیرکبیر, 54, 1, 1401, 29-38. doi: 10.22060/eej.2021.18885.5363
rezaei, mohsen, Charmacani, Kamran, Hashemi Mehne, hamed, Norouzi, Yaser. (1401). 'The New Generation of Attitude Determination Sensor for LEO Satellite based on Induced Electric Field', نشریه مهندسی عمران امیرکبیر, 54(1), pp. 29-38. doi: 10.22060/eej.2021.18885.5363
rezaei, mohsen, Charmacani, Kamran, Hashemi Mehne, hamed, Norouzi, Yaser. The New Generation of Attitude Determination Sensor for LEO Satellite based on Induced Electric Field. نشریه مهندسی عمران امیرکبیر, 1401; 54(1): 29-38. doi: 10.22060/eej.2021.18885.5363

The New Generation of Attitude Determination Sensor for LEO Satellite based on Induced Electric Field

AUT Journal of Electrical Engineering
مقاله 3، دوره 54، شماره 1، شهریور 2022، صفحه 29-38    اصل مقاله (1.41 M)
نوع مقاله: Review Article
شناسه دیجیتال (DOI): 10.22060/eej.2021.18885.5363
نویسندگان
mohsen rezaei1؛ Kamran Raissi Charmacani* 2؛ hamed Hashemi Mehne3؛ Yaser Norouzi4
1Department of Aerospace, Amirkabir University of Technology, Tehran, Iran - Aerospace Research Institute, Tehran, Iran
2Department of Aerospace, Amirkabir University of Technology, Tehran, Iran
3Aerospace Research Institute, Tehran, Iran
4Department of Electrical Engineering, Amirkabir University of Technology, Tehran, Iran
چکیده
Many satellites use closed-loop attitude control to carry out their missions. They use several sensors such as sun, magnetometer, and star tracker to close the control loop. Sun sensors are not operational during the eclipse and therefore, one of the observed vectors is lost.  For this reason, attitude determination in eclipse can be a challenging issue for control engineers. This paper presents a novel idea for producing a new generation of sensors that can measure the induced electric field vector not only in eclipse, but also in all orbit. This electric field comes from a high velocity of the spacecraft in the magnetic field of the Earth. This vector is always perpendicular to the magnetic field; thus, it is never aligned with the magnetic vector and never causes singularity and accuracy decrease. The induced electric field is measured by three RC circuits[1] that are actuated by sinusoidal voltage. The dielectrics of the capacitors are made of ferroelectric materials; therefore, the induced voltage affects the permittivity and voltage of the capacitor. By measuring and calibrating this effect in three perpendicular axes, we can measure the three components of the electric field vector. The theory of the proposed sensor has been developed, and simulation studies validate the results.
 
[1] resistor-capacitor circuit
کلیدواژه‌ها
Attitude determination؛ MEMS sensors؛ capacitive sensors؛ nonlinear capacitors؛ ferroelectric
مراجع
  1. Fadly, M., et al. "Deterministic and recursive approach in attitude determination for InnoSAT." Telkomnika9.3 (2011): 583.
  2. Markley FL and Crassidis JL. Fundamentals of spacecraft attitude determination and control. Springer, 2014.
  3. Wertz JR. Spacecraft attitude determination and control. Springer Science & Business Media, 2012.
  4. Herrera-May AL, Soler-Balcazar JC, Vázquez-Leal H, et al. Recent advances of MEMS resonators for Lorentz force based magnetic field sensors: Design, applications, and challenges. Sensors 2016; 16: 1359.
  5. Li M, Sonmezoglu S, and Horsley DA. Extended bandwidth Lorentz force magnetometer based on quadrature frequency modulation. Journal of Microelectromechanical Systems 2015; 24: 333-342.
  6. Wu G, Xu D, Xiong B, et al. Design, fabrication and characterization of a resonant magnetic field sensor based on mechanically coupled dual-microresonator. Sensors and Actuators A: Physical 2016; 248: 1-5.
  7. Laghi G, Dellea S, Longoni A, et al. Torsional MEMS magnetometer operated off-resonance for in-plane magnetic field detection. Sensors and Actuators A: Physical 2015; 229: 218-226.
  8. Gopal R. Fabrication of MEMS xylophone magnetometer by anodic bonding technique using SOI wafer. Microsystem Technologies 2017; 23: 81-90.
  9. Grosz, Asaf, Michael J. Haji-Sheikh, and Subhas C. Mukhopadhyay, eds. High sensitivity magnetometers. Switzerland: Springer, 2017.
  10. Rezaei, Mohsen, et al. "Attitude determination sensor for low Earth orbit satellite based on Lorentz force." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering233.6 (2019): 2219-2230.
  11. Damjanovic, Dragan, Paul Muralt, and Nava Setter. "Ferroelectric sensors." IEEE sensors journal1.3 (2001): 191-206.
  12. Wahba G. A least squares estimate of satellite attitude. SIAM review 1965; 7: 409-409.
  13. Shuster MD and Oh SD. Three-axis attitude determination from vector observations. Journal of Guidance, Control, and Dynamics 1981; 4: 70-77.
  14. Gibbs, Bruce P. Advanced Kalman filtering, least-squares and modeling: a practical handbook. John Wiley & Sons, 2011.
  15. Johnson, Kenneth M. "Variation of dielectric constant with voltage in ferroelectrics and its application to parametric devices." Journal of Applied Physics33.9 (1962): 2826-2831.
  16. Narayanan, Manoj, et al. "Modified Johnson model for ferroelectric lead lanthanum zirconate titanate at very high fields and below Curie temperature." Applied Physics Letters100.2 (2012): 022907.
  17. Cilden-Guler, Demet, Zerefsan Kaymaz, and Chingiz Hajiyev. "Geomagnetic disturbance effects on satellite attitude estimation." Acta Astronautica 180 (2021): 701-712.
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