Method for calculating longitudinal damping force generated by upward raising of tail hook after cable hooking

A calculation method and technology of damping force, applied in the field of aeronautical engineering, can solve problems such as inability to guarantee the hook cable

Inactive Publication Date: 2014-11-05
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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  • Abstract
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Problems solved by technology

[0002] The key to whether the aircraft can hook the line is whether the tail hook successfully hooks the arresting line. When t

Method used

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  • Method for calculating longitudinal damping force generated by upward raising of tail hook after cable hooking
  • Method for calculating longitudinal damping force generated by upward raising of tail hook after cable hooking
  • Method for calculating longitudinal damping force generated by upward raising of tail hook after cable hooking

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Embodiment Construction

[0030] The parameters of a certain type of fixed-wing aircraft are as follows, see Table 1.

[0031] Table 1 Tail hook and cable parameters

[0032]

[0033] Substitute the data in Table 1 into the above equations ①②③④⑤⑥, and solve each equation within the time t equal to 0 to 3 seconds. When solving translation and rotation, refer to figure 1 , when solving the damping force equation, see figure 2 , image 3 . Use the SIMULINK module in the MATLAB software to solve the problem, see Figure 4 . Choose k=2×10 6 N / m, c=6×10 4 The calculation results at N·s / m are as follows, and the calculation results of the impact between the tail hook and the road surface are shown in Figure 5 . The maximum damping force of the longitudinal buffer is 285550N during the upward rotation of the tail hook, which shows that the longitudinal buffer has a certain tendency to inhibit the upward rotation of the hook.

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Abstract

The invention belongs to the technical field of aeronautical engineering, and particularly relates to a method for calculating longitudinal damping force generated by upward raising of a tail hook after cable hooking in the airplane cable hooking process. The method is characterized in that through studying the moving characteristics of the tail hook after the airplane cable hooking, using the airplane general parameters and analyzing the dynamical characteristics when the tail hook collides with the pavement, a tail hook moving dynamical equation is built, and a tail hook longitudinal damping force analysis method is obtained. The method is favorable for engineering personnel to control through parameters, so that the expected longitudinal damping force can be realized.

Description

technical field [0001] The invention belongs to the technical field of aeronautical engineering, and in particular relates to a calculation method for the longitudinal damping force generated by the rear lift of a tail hook during the hooking process of an aircraft. Background technique [0002] The key to whether the aircraft can hook the line is whether the tail hook successfully hooks the arresting line. When the aircraft lands, the tail hook has been put down, but there is no guarantee of successful hooking. The rebound from impacting the pavement at high speeds during landing may cause the tailhook to jump off the deck and over the arresting wire. In order for the tail hook to hook the arresting cable successfully, the collision and rebound between the tail hook and the pavement must be controlled. Therefore, longitudinal damping devices are generally installed on the tail hook to absorb the vibration of the tail hook in the longitudinal plane of the aircraft. After t...

Claims

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Application Information

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IPC IPC(8): G06F19/00
Inventor 卢学峰姚念奎邱涛王成波
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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