JRM Vol.33 No.2 pp. 223-230
doi: 10.20965/jrm.2021.p0223


Development of Landing Rebound Reduction Mechanism Utilizing Magnetic Damper for Multicopters

Kazuki Niwa*, Susumu Hara*, and Kikuko Miyata**

*Department of Aerospace Engineering, Nagoya University
Furo-cho, Chikusa-ku, Nagoya, Aichi 464-8603, Japan

**Department of Vehicle and Mechanical Engineering, Faculty of Science and Technology, Meijo University
1-501 Shiogamaguchi, Tempaku-ku, Nagoya, Aichi 468-8502, Japan

September 18, 2020
February 2, 2021
April 20, 2021
shock response, landing, rebound reduction, magnetic damper, multicopter

This paper proposes a rebound reduction mechanism for landing multicopter. Multicopter applications in the logistics industry are expected to increase owing to the aging of logistics drivers and the decline in their numbers. Currently, most multicopters land on their designated landing pads. However, these pads are not always available at the destination, and landing on rough terrain is needed in such cases. This paper describes the development of a mechanism to reduce rebound during landing, which can easily cause tipping over. The mechanism should be lightweight to ensure that battery power is conserved and that payload transport capability is increased. Simultaneously, the mechanism should be robust against environmental variations because multicopters are used outdoors and under various temperature conditions. A mechanism consisting of a spring and a magnetic damper is proposed and is modeled using multibody dynamics. It is known that the magnetic damper possesses robustness against temperature variations. Moreover, this paper presents the design parameter optimization for the proposed mechanism considering both the rebound reduction effect and weight reduction. The spring constant and viscous damping coefficient of the proposed mechanism are determined via numerical simulations with the electromagnetic simulator JMAG. The effectiveness of the proposed mechanism is verified via vertical freefall simulations. A simple experimental system is used to evaluate the mechanism, and the experimental results indicate that the mechanism is effective.

Landing mechanism using magnetic damper

Landing mechanism using magnetic damper

Cite this article as:
K. Niwa, S. Hara, and K. Miyata, “Development of Landing Rebound Reduction Mechanism Utilizing Magnetic Damper for Multicopters,” J. Robot. Mechatron., Vol.33 No.2, pp. 223-230, 2021.
Data files:
  1. [1] K. Nonami, “World drone development trends and challenges and prospects from agricultural applications,” J. SICE, Vol.55, No.9, pp. 780-787, doi: 10.11499/sicejl.55.780, 2016 (in Japanese).
  2. [2] K. Nonami, “Prospect and recent research & development for civil use autonomous unmanned aircraft as UAV and MAV,” Trans. JSME, Series C, Vol.72, No.721, pp. 2697-2705, doi: 10.1299/kikaic.72.2697, 2006.
  3. [3] K. Nonami, “Rotary wing system robotics,” J. RSJ, Vol.34, No.2, pp. 74-80, doi: 10.7210/jrsj.34.74, 2016 (in Japanese).
  4. [4] K. Nonami, “Latest technology trends and prospects for small unmanned aerial vehicles (drones),” J. SICE, Vol.59, No.7, pp. 437-443, doi: 10.11499/sicejl.59.437, 2020 (in Japanese).
  5. [5] K. Nonami, “Drone technology, cutting-edge drone business, and future prospects,” J. Robot. Mechatron., Vol.28, No.3, pp. 262-272, doi: 10.20965/jrm.2016.p0262, 2016.
  6. [6] S. Takahashi, “Social implementation of drones in the industrial sector,” J. ITE, Vol.71, No.9, pp. 599-604, doi: 10.3169/itej.71.599, 2017 (in Japanese).
  7. [7] K. Nonami, “State of the art and issue of drone technology and business frontier,” J. Inf. Process Manag., Vol.59, No.11, pp. 755-763, doi: 10.1241/johokanri.59.755, 2017 (in Japanese).
  8. [8] S. Hara, “Shock response control technologies getting ideas from momentum or energy exchange and their applications to vehicle control,” J. SICE, Vol.57, No.4, pp. 241-246, doi: 10.11499/sicejl.57.241, 2018 (in Japanese).
  9. [9] S. Hara, S. Matsui, N. Saeki, T. Maeda, and M. Otsuki, “Proposal of non-flying-type MEID mechanism for lunar/planetary exploration spacecraft,” J. Adv. Mech. Des. Syst. Manuf., Vol.10, No.4, doi: 10.1299/jamdsm.2016jamdsm0062, 2016.
  10. [10] S. Hara, T. Watanabe, Y. Kushida, M. Otsuki, Y. Yamada, H. Matsuhisa, K. Yamada, T. Hashimoto, and T. Kubota, “Study on landing response control of planetary exploration spacecraft based on momentum exchange principles,” Trans. JSME, Series C, Vol.78, No.792, pp. 2781-2796, doi: 10.1299/kikaic.78.2781, 2012 (in Japanese).
  11. [11] T. Asami and H. Kimura, “On the effect of temperature on the damping properties of a nonviscous type of oil damper,” Trans. JSME, Series C, Vol.65, No.629, pp. 88-95, doi: 10.1299/kikaic.65.88, 1999 (in Japanese).
  12. [12] M. Iwamura, “Introduction to Multibody Dynamics,” Morikita Publishing, pp. 30-50, 58-59, 122-160, 208-210, 2018 (in Japanese).
  13. [13] Y. Takayama, A. Sueoka, and T. Kondo, “Modeling of moving-conductor type eddy current damper,” J. Syst. Des. Dynam., Vol.2, No.5, pp. 1148-1159, doi: 10.1299/jsdd.2.1148, 2008.
  14. [14] K. Kuwata, H. Oshimo, S. Kojima, Y. Ogura, E. Fujita, M. Enokizono, Y. Ueno, and S. Kaneko, “Development of vibration isolating bed for ambulance using magnetic damper,” Proc. JSME Dynamics Design Conf. 2011 (D&D 2011), Paper No.605, doi: 10.1299/jsmedmc.2011._605-1_, 2011 (in Japanese).
  15. [15] S. Saito, “Research on retreat-type shock response control mechanisms to prevent astronomical landing probe from overturning,” Master’s thesis, Graduate School of Engineering, Nagoya University, 2019 (in Japanese).
  16. [16] K. Miyata, M. Nozaki, S. Hara, K. Yamaguchi, and M. Otsuki, “Conceptual study on robust rebound suppression mechanism for small-body landing,” J. Spacecraft Rockets, Vol.2, pp. 1-16, doi: 10.2514/1.A34817, 2020.

*This site is desgined based on HTML5 and CSS3 for modern browsers, e.g. Chrome, Firefox, Safari, Edge, Opera.

Last updated on Jul. 19, 2024