Landing Gear Of An Aircraft Essay

The landing gear of an aircraft supports it during ground maneuvering operations, by providing a suitable suspension system and also cushions the landing impact. It features a shock strut which dissipates the kinetic energy associated with the vertical velocity on landing and provides ease and stability for ground maneuvering’s. To put it down roughly, an a/c touches down with vertical velocity of about 2 to 3 m/s, and the vertical impact load is contained within 2 to 3 times the static reaction by having suitable energy absorbing and dissipating means in the landing gear. Some gears have to undergo sequenced shape change, such as retraction or planing in order to fit in the wheel well when retracted. Another example is shrinking of the shock strut during retraction in order to clear the gear into the wheel well. Another example is shrinking of the shock strut during retraction in order to clear the gear into the wheel well. The main landing gear is one of the most critical components of an aircraft, capable of reacting the largest local loads on the airplane. It is a primary source of shock attenuation at landing. It controls the rate of compression extension and prevents damage to the vehicle by controlling load application rates

At the completion of each incremental solution, the program adjusts the stiffness matrix to reflect the nonlinear changes in structural stiffness before proceeding to the next load increment Before each solution, the Newton – Raphson method evaluates the out of – balance load vector, which is the difference between the restoring forces (the loads corresponding to the element stresses) and the applied loads. The program then performs a linear solution, using the out-of-balance loads and checks for convergence. If convergence criteria are not satisfied, the out-of balance load of vector is re-evaluated, the stiffness matrix is updated, and a new solution is obtained. This iterative procedure continues until the problem