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A novel retractable landing gear of a light amphibious airplane design, synthesis, analysis, and implementation

A novel retractable landing gear of a light amphibious airplane design, synthesis, analysis, and... The purpose of this paper is to present a novel retractable main landing gear for a light amphibious airplane, while the design, synthesis and analysis are given in details for constructing the main landing gear.Design/methodology/approachThe constraint three-position synthesis has given the correct path of all linkages that suitably fit the landing gear into the compartment. The additional lock-link is introduced into the design to ensure the securement of the mechanism while landing. Having the telescopic gas-oil shock strut as a core element to absorb the impact load, it enhances the ability and efficiency to withstand higher impact than others type of light amphibious airplane.FindingsBy kinematics bifurcation analysis, the optimized value of the unlock spring stiffness at 90 N/m can be found to tremendously reduce the extended-retracted linear actuator force from 500 N to 150 N at the beginning of the retraction sequence. This could limit the size and weight of the landing gear actuator of the light amphibious airplane.Practical implicationsThe drop test of the landing gear to comply with the ASTM f-2245 (Standard Specification for Design and Performance of a Light Sport Airplane) reveals that the novel landing gear can withstand the impact load at the drop height determined by the standard. The maximum impact loading 4.8 G occurs at the drop height of 300 mm, and there is no sign of any detrimental or failure of the landing gear or the structure of the light amphibious airplane. The impact settling time response reaches the 2% of steady-state value in approximately 1.2 s that ensure the safety and stability of the amphibious airplane if it subjects to an accidentally hard landing.Originality/valueThis paper presents unique applications of a retractable main landing gear of a light amphibious airplane. The proposed landing gear functions properly and complies with the drop test standard, ensuring the safety and reliability of the airplane and exploiting the airworthiness certification process. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Aircraft Engineering and Aerospace Technology Emerald Publishing

A novel retractable landing gear of a light amphibious airplane design, synthesis, analysis, and implementation

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Publisher
Emerald Publishing
Copyright
© Emerald Publishing Limited
ISSN
1748-8842
DOI
10.1108/aeat-10-2020-0237
Publisher site
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Abstract

The purpose of this paper is to present a novel retractable main landing gear for a light amphibious airplane, while the design, synthesis and analysis are given in details for constructing the main landing gear.Design/methodology/approachThe constraint three-position synthesis has given the correct path of all linkages that suitably fit the landing gear into the compartment. The additional lock-link is introduced into the design to ensure the securement of the mechanism while landing. Having the telescopic gas-oil shock strut as a core element to absorb the impact load, it enhances the ability and efficiency to withstand higher impact than others type of light amphibious airplane.FindingsBy kinematics bifurcation analysis, the optimized value of the unlock spring stiffness at 90 N/m can be found to tremendously reduce the extended-retracted linear actuator force from 500 N to 150 N at the beginning of the retraction sequence. This could limit the size and weight of the landing gear actuator of the light amphibious airplane.Practical implicationsThe drop test of the landing gear to comply with the ASTM f-2245 (Standard Specification for Design and Performance of a Light Sport Airplane) reveals that the novel landing gear can withstand the impact load at the drop height determined by the standard. The maximum impact loading 4.8 G occurs at the drop height of 300 mm, and there is no sign of any detrimental or failure of the landing gear or the structure of the light amphibious airplane. The impact settling time response reaches the 2% of steady-state value in approximately 1.2 s that ensure the safety and stability of the amphibious airplane if it subjects to an accidentally hard landing.Originality/valueThis paper presents unique applications of a retractable main landing gear of a light amphibious airplane. The proposed landing gear functions properly and complies with the drop test standard, ensuring the safety and reliability of the airplane and exploiting the airworthiness certification process.

Journal

Aircraft Engineering and Aerospace Technology – Emerald Publishing

Published: Nov 30, 2021

Keywords: Kinematics bifurcation analysis; Light amphibious airplane; Retractable landing gear

References

  • Application of bifurcation methods to the prediction of low-speed aircraft ground performance
    Coetzee, E.B.; Krauskopf, B.; Lowenberg, M.H.
  • A method for landing gear modeling and simulation with experimental validation
    Daniels, J.N.
  • Numerical continuation applied to landing gear mechanism analysis
    Knowles, J.A.C.; Krauskopf, B.; Lowenberg, M.H.
  • A bifurcation study to guide the design of a landing gear with a combined uplock/downlock mechanism
    Knowles, J.A.C.; Lowenberg, M.H.; Neild, S.A.; Krauskopf, B.
  • Landing-gear drop-test rig development and application for light airplanes
    Xue, C.J.; Han, Y.; Qi, W.G.; Dai, J.H.
  • Bifurcation mechanism design – from optimal flat taxes to improved cancer treatments
    Yang, G.; Piliouras, G.; Basanta, D.
  • Standard specification for design and performance of a light-sport airplane
  • Six-degree of freedom mathematical dynamic model of a light sport aircraft
    Chinvorarat, S.; Watjatrakul, B.; Nimdum, P.; Sangpet, T.; Soontornpasatch, T.; Vallikul, P.
  • Dynamical systems toolbox for MATLAB
    Coetzee, E.; Lowenberg, M.H.
  • Crash testing and simulation of a cessna 172 airplane: pitch up impact onto soft soil
    Fasanella, E.L.; Jackson, K.E.
  • The lie group of rigid body displacements, a fundamental tool for mechanism design
    Hervé, J.M.
  • A novel kinematic coupling-based trajectory planning method for overhead cranes
    Ning, S.; Yongchun, F.; Yudong, Z.; Bojun, M.
  • Optimization of a hybrid carbon/glass composites after body of the amphibious plane with finite element analysis
    Thianwiboon, M.