Выбор оптимального аккумулятора для многороторного беспилотного вертолета (мультикоптера)

10 / 11

С.З. Свердлов
10 Инженерный журнал: наука и инновации # 5·2017
Selecting the optimum battery for a multi-rotor unmanned
electric helicopter (multicopter)
© S.Z. Sverdlov
Vologda State University, Vologda, 160000, Russia
The study deals with selecting a rechargeable battery mass that ensures maximum flight
duration for an electric multicopter in hover mode, taking into account the changes in the
electric motor energy conversion efficiency. As a result of studying a refined model that
takes into account the changes in energy conversion efficiency, we discovered that using
a relative battery mass between 1 and 2 leads to achieving the maximum flight duration
in hover mode. The relative mass value corresponding to the maximum in time greatly
depends on how rigid the speed-torque characteristic of the engine is, and depends on the
thrust-to-weight ratio to a lesser degree. Taking into account the energy conversion effi-
ciency of the engine does not really affect relative battery mass values that are deter-
mined using the integral and differential criteria. We can recommend designers to use the
values we obtained for the relative battery mass.
Keywords: multi-rotor unmanned electric helicopter, multicopter, rechargeable battery,
maximum flight duration, relative battery mass, thrust-to-weight ratio, energy conversion
efficiency, brushless electric motor
REFERENCES
[1] Andrés. Optimal Battery Capacity. 2011, April 12, 9 p.
URL
x2C*usF6KDpKiqpO4L9-hrUKYBsS-xtRMqo-K4GR5TPsM2Isq56oMw__
/battery_capacity.pdf
[2] Neitzke K.-P. Rotary Wing Micro Air Vehicle Endurance. Proceedings of the
International Micro Air Vehicle Conference and Flight Competition IMAV 2013 .
September 17–20. Toulouse, France, 2013, pp. 16–25.
[3] Sverdlov S.Z. Vestnik Vologodskogo gosudarstvennogo universiteta — Bulletin
of the Vologda State University, 2015, no. 5/15. Available at: -
CTRIC%20UNMANNED%20HELICOPTER.pdf
[4] Ovchinnikov I.E. Ventilnye elektricheskie dvigateli i privod na ikh osnove
(malaya i srednyaya moshchnost) [AC converter-fed motors and drives based on
them (low and medium power)]. St. Petersburg, Korona-Vek Publ., 2006, 336 p.
[5] Xia Ch.-l. Permanent magnet brushless DC motor drives and controls . John
Wiley & Sons, Singapore Pte. Ltd., 2012, 320 р.
[6] Sverdlov S.Z. Inzhenernyy zhurnal: nauka i innovatsii — Engineering Journal:
Science and Innovation, 2016, iss. 11.
Available at:
[7] Traub L.W. Range and Endurance Estimates for Battery-Powered Aircraft.
Journal of Aircraft, 2011, no. 48 (2):703–707. DOI: 10.2514/1.C031027
[8] Traub L.W. Optimal Battery Weight Fraction for Maximum Aircraft Range and
Endurance. Journal of Aircraft, 2016, vol. 10, no. 03. DOI: 10.2514/1.C033416
[9] Johnson W. Helicopter Theory. Princeton University Press, 1980 [In Russ.:
Johnson W. Teoriya vertoleta. In 2 vols. Moscow, Mir Publ., 1983].