Aircraft landing gear wheels actuator

Machine-building Engineering and Machine Science

Machine science, drive systems and machinery


Nadaraia T. G.1*, Shestakov I. Y.2**, Fadeev A. A.2***

1. Design, implementation of new equipment, 75, Svobodny av., Krasnoyarsk, 660041, Russia
2. Siberian State University of Science and Technology named after academician M.F. Reshetnev, 31, Krasnoyarsky Rabochy av., Krasnoyarsk, 660014, Russia



According to the item of the State Program “Development of the aviation industry for 2013–2025” creation of scientific and technological capacity ensuring global leadership in aviation technology and product promotion of domestic aviation industry on the domestic and foreign markets should ensure high competitiveness of domestic aircraft by introduction of innovative developments. Operation and maintenance analysis of the existing civil aircraft park revealed that while aircraft aerodrome maneuvering the hundreds of kilograms of kerosene are wasted, and drive trucks waste tens of kilograms of fuel. When kerosene burns in an aircraft engine, and fuel burns in combustion engine the atmosphere is contaminated by noxious substances. While aircraft maneuvering on the runway the noise level is 90 dB. Using combined actuator in landing gearwheels will allow decrease negative effect on the environment and eliminate completely the majority of shortcomings.

The paper presents the schematic diagram of electromechanical landing gear wheel actuator in which brushless switched-reluctance motors are mounted inside cylindrical gearwheels. Due to low cost materials implementation, small size and weight, low energy consumption and high efficiency maintainability better design and operating characteristics of aircraft landing gear wheel actuator are ensured. While motor-reducer design, specifics of its operation in the landing gear wheel were accounted for. The results of motor-reducer computation, which demonstrated the wide specter of implementation of such kind of actuator for various types of aircraft components, such as landing gear wheels actuators, high-lift devices' elements are given. The presented motor-reducer possesses diversified structural concepts, which allows use it for various types of aircraft both civil and military oriented, as well as for unmanned aerial vehicles (UAV) and spacecraft of various kinds. The prototype of motor-reducer, used for UAV's high-lift devices, displayed its apparent advantage compared to the other actuators, such as design compactability, manufacturability and cost effectiveness. Implementation of the above-described structure will allow fuel consumption saving by both an aircraft, and airfield servicing facilities. The structural concept of the motor-reducer in aircraft landing gear wheel does not have counterparts either in Russia or abroad.


electromechanical actuator, gear-wheel, brushless induction motor


  1. Eger S.M., Matveenko A.M., Shatalov I.A. Osnovy aviatsionnoi tekhniki (Fundamentals of aviation technology), Moscow, Mashinostroenie, 2003, 720 p.

  2. Asautov M.L. Zagryaznenie okruzhayushchei sredy pri aviatransportnykh protsessakh (Environmental pollution in air transport processes), St. Petersburg, Universitet grazhdanskoi aviatsii, 2010, pp. 7-8.

  3. Karasev D.A., Arutyunov A.G., Zagordan A.A. Vestnik Moskovskogo aviatsionnogo instituta, 2015, vol. 21, no. 1, pp. 132–139.

  4. Gerashchenko A.N., Makhrov V.P. Vestnik Moskovskogo aviatsionnogo instituta, 2015, vol. 22, no. 2, pp. 178–187.

  5. Nadaraia Ts.G., Shestakov I.Ya., Fadeev A.A. Vestnik Sibirskogo gosudarstvennogo aerokosmicheskogo universiteta im. akademika M.F. Reshetneva, 2014, no. 2 (54), pp. 137–140.

  6. Nadaraia Ts.G. Shestakov I.Ya., Fadeev A.A. Materialy XIX Mezhdunarodnoi nauchno-prakticheskoi konferentsii “Reshetnevskie chteniya” (10-14 November 2015), Krasnoyarsk, 2015, vol. 1, no. 19, pp. 36–37.

  7. Nadaraia Ts.G. Patent no. 96707 RF, 10.08.2010.

  8. Kudryavtsev V.N., Kirdyashev Yu.N. Planetarnye peredachi (Planetary gear), Leningrad, Mashinostroenie, 1977, 536 p.

  9. Kiselev Yu.V., Kiselev D.Yu. Shassi samoleta Superjet (Superjet landing gear), Samara, SGAU, 2012.

  10. Chassis specification,

  11. Vulgakov E.B. Aviatsionnye zubchatye peredachi i reduktory (Aviation, gears and gearboxes), Moscow, Mashinostroenie, 1981, 374 p.

  12. Il'inskii N.F., Shtainbrunn I., Prudnikova Yu.I., Fedorov A.G., Bychkova E.V. Vestnik MEI, 2004, no. 1, pp. 37–43.

  13. Nesterov E.V. Elektrichestvo, 2006, no. 5, pp. 63–65. — informational site of MAI

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