design and development of composite landing gear strut

5 Student's Name Academic Supervisor(s) Industrial Supervisor(s) Abstract: Landing gear strut is one of the important components of aircraft which takes various types of loads. Main landing gear bears with impact load while the nose landing gear bears side, break and impact loads. In aerospace industry, weight reduction is an important aspect and use of composite plays a major role by providing better strength to weight ratio. In this work, weight of landing gear strut is considered for optimization by using composite material. A light weight aircraft is selected for the analysis. The design of landing gear strut is carried out as per the CS-23 Certification specification. Analytical calculations are carried out to find the magnitude of side, break and impact loads. To start with, existing landing gear strut made of titanium alloy is considered for optimization. Numerical analysis is carried out on the existing design with appropriate loading and boundary conditions to arrive at optimized landing gear strut cross section. Later, use of composite material is explored for the landing gear strut. Numerical analysis is carried out on carbon/epoxy laminate composite material under the same loading conditions. Fifteen layers o o of laminate of 0.6 mm ply thickness with 0 /45 orientation are considered for the analysis. Fatigue life for the composite landing gear strut is also estimated using SN curve approach. With the optimization of existing titanium alloy landing gear strut, mass of the strut is reduced by only 4.5%. In the case of landing gear strut with composite material, overall weight of the strut is reduced by 64.34%, along with good fatigue property. The fatigue life of composite landing gear strut is exceeding expected fatigue life of 73,200 cycles. Stresses and deflections under all loading conditions are within the acceptable limit. ............................................................ Conclusion: Analysis result shows that the composite landing gear strut can be used for some of the load bearing components in aerospace industries. Fatigue analysis of landing gear strut is limited by the availability of experimental data. Results can be further improved with more experimental testing data on different types of laminates. Chethan B. Arun R. Rao Keywords: Landing Gear Strut, Optimization, Composites, Fatigue Life Book of Abstracts November 2017 Design and Development of Composite Landing Gear Strut AMD (FT-2015) Chethan B. [email protected] Ph. No: 0 90306 09055 Landing gear strut Optimization with Titanium alloy Peak stress for impact load Peak stress for side load Peak stress for break load Fatigue life Results with composite landing gear strut

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Page 1: Design and Development of Composite Landing Gear Strut

Student's Name

Academic Supervisor(s)

Industrial Supervisor(s)

Abstract:

Landing gear strut is one of the important components of aircraft which takes various types of loads. Main landing gear bears with impact load while the nose landing gear bears side, break and impact loads. In aerospace industry, weight reduction is an important aspect and use of composite plays a major role by providing better strength to weight ratio. In this work, weight of landing gear strut is considered for optimization by using composite material.

A light weight aircraft is selected for the analysis. The design of landing gear strut is carried out as per the CS-23 Certification specification. Analytical calculations are carried out to find the magnitude of side, break and impact loads. To start with, existing landing gear strut made of titanium alloy is considered for optimization. Numerical analysis is carried out on the existing design with appropriate loading and boundary conditions to arrive at optimized landing gear strut cross section. Later, use of composite material is explored for the landing gear strut. Numerical analysis is carried out on carbon/epoxy laminate composite material under the same loading conditions. Fifteen layers

o oof laminate of 0.6 mm ply thickness with 0 /45 orientation are considered for the analysis. Fatigue life for the composite landing gear strut is also estimated using SN curve approach.

With the optimization of existing titanium alloy landing gear strut, mass of the strut is reduced by only 4.5%. In the case of landing gear strut with composite material, overall weight of the strut is reduced by 64.34%, along with good fatigue property. The fatigue life of composite landing gear strut is exceeding expected fatigue life of 73,200 cycles. Stresses and def lect ions under a l l loading condit ions are with in the acceptable l imit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Conclusion: Analysis result shows that the composite landing gear strut can be used for some of the load bearing components in aerospace industries. Fatigue analysis of landing gear strut is limited by the availability of experimental data. Results can be further improved with more experimental testing data on different types of laminates.

Chethan B.

Arun R. Rao

Keywords: Landing Gear Strut, Optimization, Composites, Fatigue Life

Book of Abstracts November 2017

Design and Development of Composite Landing Gear Strut

AMD (FT-2015)

Chethan [email protected]. No: 0 90306 09055

Landing gear strut

Optimization with Titanium alloy

Peak stress for impact load� Peak stress for side load

Peak stress for break load Fatigue life

Results with composite landing gear strut