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Method for calculating turning load of four-point type aircraft landing gear

A technology for aircraft landing gear and load calculation, which can be used in calculations, special data processing applications, instruments, etc., and can solve problems such as the inability to accurately calculate the load of four-point aircraft landing gear

Active Publication Date: 2016-02-17
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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Problems solved by technology

[0004] The purpose of the present invention is to provide a four-point aircraft landing gear turning load calculation method to solve the problem that the existing aircraft landing gear load calculation method cannot accurately calculate the four-point aircraft landing gear load

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  • Method for calculating turning load of four-point type aircraft landing gear
  • Method for calculating turning load of four-point type aircraft landing gear
  • Method for calculating turning load of four-point type aircraft landing gear

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Embodiment Construction

[0031] In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the invention. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below ...

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Abstract

The invention relates to the field of aircraft landing gear turning load calculation, in particular to a method for calculating turning load of a four-point type aircraft landing gear, and aims to solve the problem that the load of the four-point type aircraft landing gear cannot be precisely calculated by using a conventional aircraft landing gear load calculation method. The method comprises the following steps: establishing a force balance equation of a four-point type aircraft in a turning state in the vertical direction; establishing a pitch moment balance equation of the four-point type aircraft in the turning state; establishing a rolling moment balance equation of the four-point type aircraft in the turning state; and calculating vertical load and lateral load of landing gears. By adopting the method for calculating the turning load of the four-point type aircraft landing gear, as a dynamic balance method is adopted to calculate the load of the four-point type aircraft landing gear, the calculation result is relatively precise, and the portion of vertical load and the lateral load shared by single-side and single landing gears of the aircraft can be relatively really reflected.

Description

technical field [0001] The invention relates to the field of calculating the turning load of an aircraft landing gear, in particular to a method for calculating the turning load of a four-point aircraft landing gear. Background technique [0002] The four-point aircraft is a very special landing gear layout scheme, which is different from the rear tricycle landing gear layout of early propeller aircraft, and also different from the front tricycle landing gear layout commonly used in current jet military and civilian aircraft. The calculation of the four-point aircraft landing gear load cannot apply the general algorithm of the three-point aircraft landing gear in the military aircraft load calculation specification or the civil aircraft airworthiness regulations. [0003] In particular, the turning situation in the load calculation of the four-point aircraft landing gear becomes the difficulty and focus of the load output due to the complexity of the topological relationship...

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Application Information

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IPC IPC(8): G06F17/50
CPCY02T90/00
Inventor 姚念奎吴江鹏曲林峰周栋
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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