Helicopter chassis drop tests mathematical modeling

Аuthors

Kruchinin M. M.^1*, Kuzmin D. A.^2**

1. Moscow Aviation Institute (National Research University), 4, Volokolamskoe shosse, Moscow, А-80, GSP-3, 125993, Russia
2. National Helicopter Center Mil & Kamov, 26/1, Garshina str., Tomilino, Moscow region, 140070, Russia

*e-mail: mmkruchinin@mi-helicopter.ru
**e-mail: dkuzmin@mi-helicopter.ru

Abstract

Drop tests present a necessary part of a helicopter design and certification. However, man-hours necessary for carrying out these tests are rather labor consuming, and the tests themselves are not safe. Thus, helicopter chassis drop test mathematical model development is considered as a topical task. Drop tests consist in dropping the aircraft landing gear with the reduced weight attached to it from a specified height. this weight is selected according to the norms of safety. The paper considers mathematical modeling of drop testing of the main and front landing gear struts of the Mi-38 helicopter with software packages LMS. Amesim. Imagine. Lab and LMS.Virtual. Lab. The authors describe the methodology and stages of front and main landing gear shock absorbers mathematical models development with the data packs, and the numerical experiment obtained results. The synthesis of shock mathematical models, as a combination of the pneumatic, hydraulic and mechanical systems operation, held in LMS.Amesim. Imagine. Lab package. Validation of models of shock absorbers made by comparing with the received data compression diagram of the manufacturer. Building a model of the landing gear mechanical and mathematical modeling of its contact with the surface of pneumatics was performed in LMS. Virtual. Lab pack. The landing gear drop tests modeling carried out by sharing calculation in packages LMS. Virtual. Lab and LMS. Amesim. Imagine. Lab. The simulation results are compared with manufacturer’s experimental data of field tests. is confirmed The reliability of the used models is confirmed by operational work diagram representing the dependence of force at the point of contact on pneumatic vertical movement of the center of gravity of the dropped cargo at various test conditions. Comparison of the calculated and experimental data demonstrated the possibility of using this method for the preliminary analysis of the permissible loads in the tests for dropping, which provides a significant reduction in the volume of drop tests. The possibilities of further development of the developed method for helicopter landing simulation in various conditions regulated by the rules of safety.

Keywords:

helicopter chassis, mathematical modeling, drop work test

References

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