Optimal Design of Aircraft Landing Gear Mechanism Actuating Force

DOI

10.2991/jimec-18.2018.61How to use a DOI?

Keywords

landing gear (aircraft); optimization; dynamics; inverse problems; design of experiments; quadratic programming

Abstract

Lowering the actuating force is preferable when designing aircraft landing gear mechanism, which may lessen friction and prevent lock-up of joints. In this research, driving kinematics of operating actuator is modified in addition to geometric dimensions to achieve optimal actuating force during landing gear retraction. The primary purpose is to exploit the dynamics of specific problem and develop optimization strategy with minimum computational cost and compromise in results compared with general approaches. Optimization problem of actuating force is modeled in the context of inverse dynamic analysis of a three-dimensional landing gear mechanism. Actuator brace dimensions and stroke function parameters are chosen as design variables while the maximum power of actuator is limited. Retracting duration and two relative positions of the interpolation point in the stroke function serve as design variables after the optimal dimensions are set. Design of experiments indicates that the ratio between maximum actuating force and maximum actuating power is maximized when the two relative position variables are set equal. Sequential quadratic programming is employed in solving the simplified optimization problem with only two design variables. Lower cost function value is obtained compared with solving the original problem with three driving kinematic variables directly, indicating resistance to converging to local minima in the simplified problem. Global optimization techniques are then used to explore the design space. Results prove that the simplified optimization problem exploiting the dynamics of this problem generates similar optimal actuating force with much smaller computational cost.

Copyright

© 2019, the Authors. Published by Atlantis Press.

Open Access

This is an open access article distributed under the CC BY-NC license (http://creativecommons.org/licenses/by-nc/4.0/).

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TY  - CONF
AU  - Chen Huang
AU  - Yuhong Jia
PY  - 2018/12
DA  - 2018/12
TI  - Optimal Design of Aircraft Landing Gear Mechanism Actuating Force
BT  - Proceedings of the 2018 3rd Joint International Information Technology，Mechanical and Electronic Engineering Conference (JIMEC 2018)
PB  - Atlantis Press
SP  - 287
EP  - 292
SN  - 2589-4943
UR  - https://doi.org/10.2991/jimec-18.2018.61
DO  - 10.2991/jimec-18.2018.61
ID  - Huang2018/12
ER  -