Investigation into recurring military helicopter landing gear failure

Krstic, Branimir; Rebhi, Lamine; Trifkovic, Dragan; Khettou, Nabil; Dodic, Marjan; Perić, Sreten; Milovancevic, Milorad

doi:10.1016/j.engfailanal.2016.02.018

Cited by 12 publications

(3 citation statements)

References 9 publications

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“…In the initial design stage for aircraft, some other landing gear systems of helicopters are also studied to meet different requirements. For example, helicopter skid landing gear can achieve equal effectiveness compared with traditional landing gear equipped with oleo-pneumatic shock absorbers [151]. The advantages of skid landing gear are the simple lay-out, light-weight and low cost.…”

Section: Crash Dynamics Of Typical Helicopter Structures 41 Landing Gearmentioning

confidence: 99%

Crashworthy design and energy absorption mechanisms for helicopter structures: A systematic literature review

Yang

Wen

et al. 2020

Progress in Aerospace Sciences

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Section: Crash Dynamics Of Typical Helicopter Structures 41 Landing Gearmentioning

confidence: 99%

Crashworthy design and energy absorption mechanisms for helicopter structures: A systematic literature review

Yang

Wen

et al. 2020

Progress in Aerospace Sciences

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“…Landing gear jenis ini memiliki satu roda di bagian depan pesawat (nose landing gear) dan dua roda di bagian belakang pesawat (main landing gear) seperti yang ditunjukkan pada Gambar 1. Landing gear merupakan komponen yang sering mengalami situasi lingkungan seperti iklim, suhu, dan landasan pacu yang ekstrem [7] [8]. Kegagalan landing gear terjadi sekitar 10% dari total kegagalan yang dilaporkan dalam industri dirgantara.…”

Section: Pendahuluanunclassified

Untitled

Wibawa¹

2020

Elemen

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Landing gear merupakan salah satu komponen penting dalam struktur pesawat UAV. Landing gear berfungsi sebagai komponen pendukung utama beban pesawat saat mendarat dan lepas landas. Makalah ini bertujuan untuk mengkaji pengaruh kecepatan landing terhadap umur fatik rangka tricycle landing gear pesawat UAV. Desain rangka tricycle landing gear menggunakan Autodesk Inventor Professional 2017, sedangkan analisis umur fatik menggunakan perangkat lunak Ansys Workbench. Kecepatan landing divariasikan 4 m/s, 6 m/s, 8 m/s, dan 10 m/s. Prediksi untuk umur fatik menggunakan teori tegangan rata-rata Gerber dengan jenis pembebanan fullreserved. Material landing gear menggunakan Aluminium paduan 6061. Hasil simulasi menunjukkan rangka tricycle landing gear dengan kecepatan landing

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“…These studies are of great significance for improving the life of engine components or the reliability of aircraft systems. They focus on the finite element theory without changing the internal structure of components, but the research methods can be used for reference in the fatigue analysis of the combined piston [9][10][11]. Liu et al has researched the relationships between the piston life and stress in different thermal, mechanical, and thermalmechanical coupling conditions, but the integral piston studied by the authors is not a combined piston.…”

Section: Introductionmentioning

confidence: 99%

Failure Analysis of the Pin Bore of the Combined Piston for the Aero Engine

Pan

Guo

2019

International Journal of Aerospace Engineering

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The combined piston can be used in an aero piston heavy fuel engine because of its light weight, so as to reduce the reciprocating inertia force and improve the engine power-weight ratio. However, the pin bore of the combined piston is prone to deform leading to the failure of the piston. Based on the structure of the piston, the stress of the piston under thermomechanical coupling is analyzed, the temperature field of the piston is determined by experiments, and the deformation rule of the piston pin bore under the thermomechanical coupling is summarized. A design scheme is proposed to change the position of the thread connection between the piston crown and the piston head. Under the same conditions, the deformation of the piston pin bore of the original scheme and the new scheme is analyzed. The results show that together with the changing of the connection thread between the piston crown and the piston head, the deformation of the piston pin bore decreases by 60 μm and the deformation of the piston pin bore is controlled. The test results show that the deformation of the pin bore is within the acceptable range, which proves the effectiveness of the improved scheme.

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Investigation into recurring military helicopter landing gear failure

Cited by 12 publications

References 9 publications

Crashworthy design and energy absorption mechanisms for helicopter structures: A systematic literature review

Crashworthy design and energy absorption mechanisms for helicopter structures: A systematic literature review

Untitled

Failure Analysis of the Pin Bore of the Combined Piston for the Aero Engine

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