Learnings from implementation of a detumbling algorithm for a nanosatellite.
- Paper number
IAC-21,E2,3-GTS.4,11,x66574
- Author
Mr. Shivam Hire, India, College of Engineering Pune
- Coauthor
Mr. Onkar Bhakare, India, College of Engineering, Pune
- Coauthor
Mr. Shubham Thorat, India, College of Engineering, Pune
- Coauthor
Ms. Manali Durgule, India, College Of Engineering , Pune
- Coauthor
Mr. Atharva Karaguppi, India, College Of Engineering , Pune
- Coauthor
Mr. Aman Gupta, India, College of Engineering Pune
- Coauthor
Mr. Sushil Mahajan, India, College of Engineering, Pune
- Coauthor
Mr. Bhaskar Pardeshi, India, College of Engineering, Pune
- Coauthor
Mr. Juber Shaikh, India, College of Engineering, Pune
- Coauthor
Mr. Rahul Patil, India, College of Engineering Pune
- Coauthor
Mr. Akshay Deodhar, India, College of Engineering, Pune
- Coauthor
Mr. Kishan Patel, India, College Of Engineering , Pune
- Coauthor
Mr. IDRIS BANDUKWALA, India, College Of Engineering , Pune
- Coauthor
Mr. Akash Rathod, India, College of Engineering, Pune
- Year
2021
- Abstract
Nanosatellites, on ejection from the launch vehicle, tumble with random angular velocities and have to be stabilized before they can commence their normal working. Due to the restriction on the mass and size of the nanosatellite, the use of exhaustive massive thrusters is not feasible. Hence, nanosatellites must use alternative methods to stabilize themselves. For the COEPSAT-2 nanosatellite, the BDot algorithm will be used to damp the angular velocities along all 3 axes. BDot uses the torque generated by the interaction between the torque rods and the earth’s magnetic field to stabilize the satellite. This paper presents the implementation, testing procedure, and experimental results obtained during the testing of the Bdot algorithm. The BDot algorithm requires control of magnetic dipole moment, which is achieved by controlling the current through the magnetorquer coils. A low-power controlled current source was developed using linear regulator topology. The detailed design procedure and testing results of the current control circuit are presented in this paper. A design of an alternative switch mode topology is also discussed in the paper. For on-ground testing, an air-bearing was used for levitating the test setup, allowing it to rotate freely about one axis. This enabled us to evaluate the damping effect of BDot algorithm on angular velocity in space-like conditions. An exponential decay in angular velocity was observed in these experiments. We present the angular velocity data acquired in these experiments and the effects that various factors like magnetic field strength, maximum torquer current, gain values, initial velocity, and sensor calibration have on stabilization time. Additionally, obtained results are compared with the expected results obtained through mathematical analysis. With the help of these results, we have shown how to find the expected stabilization time and residual angular momentum of satellites in space.
- Abstract document
- Manuscript document
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