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Publication
Development of a retractable landing gear for an aircraft
| Name: | Description: | Size: | Format: | |
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| 2.6 MB | Adobe PDF |
Authors
Abstract(s)
The focus of this project is the development of a retractable landing gear system for an aircraft, with the goal of improving overall efficiency, safety and performance. The project emphasizes in dimensioning a realistic solution for an initial draft of an aircraft, with several parameters defined taking into account current market requirements. The project encompasses various critical aspects such as the landing gear arrangement, retraction movements, shock absorption solutions and braking systems while also referring to regulations and guidelines.
In order to dimension an initial solution for the landing gear, a thorough research was conducted regarding the current solutions as well as any up-and-coming alternatives that may be more suitable for the project. With all the information gathered, a set of requirements was then obtained taking into account market demands, which would be further applied to the methodology developed, helping in the development of an initial solution.
As a result, several findings were obtained, regarding the position, movement and requisites for the components of the landing gear structure. For the landing configuration, a tricycle layout was selected and then dimensioned through a series of steps in order to find the best position for both the main and front landing gear, ensuring a reliable maneuverability and safe structure. In regard to the retraction movement, a forward retractable system was suggested as the best option, mainly due to the restrictions in payload areas in the fuselage, with the usage of additional wheel bays as the most suitable solution for storage. For the shock absorption, an oleo-pneumatic solution was deemed the most appropriate, and then dimensioned to have at least a stroke of 8.8 in and a diameter of 0.105 ft. At last, the braking requirements resulted in a brake capable of absorbing at least 98578 ft.lbf of energy and capable of producing more than the minimum value of torque, at 525.95 lbf.in.
These findings and results, serve as an introduction towards the development of a full landing gear structure, with a long series of steps still needed to be taken into account before the final solution is ready.
Description
Keywords
Retractable landing gear Aircraft design Shock absorption Braking system Aviation safety Regulation