Landing gear stress analysis

Published on 01 Jul 2021. Written by Gurudutt

The landing gear forms a structure, which supports the aircraft on the ground. All the load will be acting on the landing gear during take-off and landing. The larger the aircraft more the wheels are added to the landing gear. The position of landing gear depends on the design, load, and type of aircraft. Most of them are mounted on the wing.

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In the current project, stress analysis is done on landing gear beams on either side. Load-carrying beams are then modeled and studied for further analysis.

Types of structural stress:  

The five basic structural stresses that act on aircraft are:

• Tension: Apply a force to which tends to stretch it.
• Compression: It refers to the reduction in volume.
• Torsion: Itis the twisting of an object due to an applied torque
• Shear: It arises from the force vector component
• Bending: Object which bends on the application of force.

Project Implementation:

Generally, the following method is used for doing global analysis:

• Importing Solid model designed using modeling software (CATIA V5)
• Converting 3D into 2D models.
• Meshing: The 2D model is meshed using the Quad 4 and Tri element.
• Meshing is done in patron software
• Cross-section of beams must be assigned
• Materials properties must be assigned. Such as young’s modulus (7000) and poison’s ratio (0.3)
• Boundary conditions and loads are applied to the structure.
• linear static stress analysis

Steps in linear static stress analysis:

Step 1: Requirements and loads of determination loads

• Static (or equivalent static)
• Strength, displacement, cyclic life

Step 2: Material Characterization

• Structural goals vs. material parameters

Step 3: Structural modeling

• Discretized numerical model (e.g., finite element model)
• Analytical solution of idealized geometry and loading

Step 4: Determination of structural response

• Linear/non-linear
• Deformations, internal forces, and stresses

Step 5: Failure modes analysis

• Safe life for fracture
• Fatigue test

Step 6: Optimization and redesign if necessary

Conclusions:

• Stress analysis is determined, maximum stress near the rivet is found having lower strength.
• Fatigue cracks have occurred where there is maximum tensile stress located, Since the damage is lesser than critical, it is safer.
• Fatigue crack growth analysis carried out in other parts of landing gear

Future work:

Future scope of work which can give a strong knowledge of the failure analysis like failure prediction and critical usage of materials or part compared with conventional materials.

Kit required to develop Landing gear stress analysis:

• CATIA V5

Technologies you will learn by working on Landing gear stress analysis:

• CATIA
• ANSYS

Any Questions?