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<p>All modern aircraft are designed in accordance with the requirements of the certification basis (CB). FAR.25 contains numerous clauses that impose requirements on the strength of the main landing gear (MLG) hinge structure. In this paper, two typical landing gear hinge configurations were identified, an analytical analysis was conducted, and the main analytical formulas for determining reactions at the landing gear hinge nodes were derived, with the goal of creating a simple mathematical model. Trivial algebraic methods, such as solving statically indeterminate frames, were used to determine the main reactions. This model allows for the creation of a model for optimizing the landing gear hinge design, the main goal of which is to identify hazardous areas that do not meet the requirements for safe MLG failure when the airframe load is exceeded. At the same time, this mathematical model is planned to be used to determine reactions for the design of durable structures in the early stages of aircraft design.</p>

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Approach to the main landing gear linkage design for the requirement of ultimate loads on links during emergency landing

  • 期刊论文

  • 发表日期：

    2026年5月21日

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  • Egor Titov,
  • Sergey Serebryansky

摘要

All modern aircraft are designed in accordance with the requirements of the certification basis (CB). FAR.25 contains numerous clauses that impose requirements on the strength of the main landing gear (MLG) hinge structure. In this paper, two typical landing gear hinge configurations were identified, an analytical analysis was conducted, and the main analytical formulas for determining reactions at the landing gear hinge nodes were derived, with the goal of creating a simple mathematical model. Trivial algebraic methods, such as solving statically indeterminate frames, were used to determine the main reactions. This model allows for the creation of a model for optimizing the landing gear hinge design, the main goal of which is to identify hazardous areas that do not meet the requirements for safe MLG failure when the airframe load is exceeded. At the same time, this mathematical model is planned to be used to determine reactions for the design of durable structures in the early stages of aircraft design.