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Aircraft arrestment landing dynamics simulation method

A simulation method, land dynamics technology, applied in the field of aeronautical engineering, can solve problems limited to theoretical analysis and less dynamic performance simulation analysis

Active Publication Date: 2014-08-13
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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Problems solved by technology

[0003] At present, the dynamic performance analysis of aircraft landing arrest in foreign countries is mainly through a large number of experimental studies and theoretical analysis, but there are few reports on dynamic performance simulation analysis, and the current research on aircraft arresting characteristics in my country is limited to theoretical analysis.

Method used

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  • Aircraft arrestment landing dynamics simulation method
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Embodiment Construction

[0049] The present invention will be described in further detail below through specific embodiments and in conjunction with the accompanying drawings.

[0050] See Table 1 for the selection of parameters related to an aircraft’s intercepted landing.

[0051] Table 1 Tail hook and cable parameters

[0052]

[0053] Through trial calculation, when the integral step h=△t≤0.003s, the algorithm has better convergence and stability, here the integral step h=△t=0.001s. The calculated tail hook load-running distance curve is shown in Figure 4 , see the tail hook overload curve Figure 5 . Main landing gear vertical load see Image 6 , the vertical load of the nose landing gear see Figure 7 .

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Abstract

The invention belongs to the technical field of aeronautical engineering and particularly relates to a dynamics simulation model of an aircraft arrestment landing process. The method is characterized in that a many-body dynamics theory is combined, a complete aircraft arrestment landing dynamics mathematic model is established, and arrestment landing use conditions of various typical landing attitudes are comprehensively considered, so that a complete aircraft arrestment landing dynamic characteristic analysis method of the system is established. The method has the beneficial effects that by virtue of dynamics simulation calculation, the aircraft landing tailhook load and the load impacting an aircraft body are obtained, reference is provided for the aircraft arrestment characteristic analysis, and meanwhile a basis is provided for designing a tailhook; the modeling time can be saved, the manufacture and test expenses of a test piece are reduced, the working efficiency is improved, and the method has important engineering application value.

Description

technical field [0001] The invention belongs to the technical field of aeronautical engineering, and in particular relates to a dynamic simulation model for an aircraft arresting landing process. Background technique [0002] The landing arrest of aircraft is one of the important characteristics different from land-based aircraft. Landing arrest is directly related to the safety of aircraft recovery and is one of the key technologies to solve the problem of safe landing of aircraft. The main difference between the dynamic performance analysis of landing arrest and the conventional unobstructed landing dynamic performance analysis of land-based aircraft is that it is also subjected to the arresting force given to it by the arresting cable. [0003] At present, the dynamic performance analysis of aircraft landing arrest in foreign countries is mainly through a large number of experimental research and theoretical analysis, but there are few reports on dynamic performance simul...

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Application Information

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IPC IPC(8): G06F17/50
Inventor 周栋卢学峰孟凡星曲林锋
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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