Method for determining airplane critical circumvention parameters in low-altitude wind shear

A low-altitude wind shear and method-determining technology, which is applied in electrical digital data processing, special data processing applications, instruments, etc., can solve problems such as long working hours, heavy workload, and low efficiency

Inactive Publication Date: 2014-02-12
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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  • Abstract
  • Description
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  • Application Information

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Problems solved by technology

Its disadvantages are: heavy workload, long working hours and low efficiency
However, the above method must go through multiple simulations to obtain the critical avoidance parameters. It also has the disadvantages of heavy workload, long working hours and low efficiency.

Method used

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  • Method for determining airplane critical circumvention parameters in low-altitude wind shear
  • Method for determining airplane critical circumvention parameters in low-altitude wind shear
  • Method for determining airplane critical circumvention parameters in low-altitude wind shear

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Embodiment

[0054] It is known that the detection distance of the aircraft is L=[500,1000]m; the wind shear scale is 2000m. Firstly, the avoidance turning radius R of the aircraft is calculated according to the formula in calculation step 1. The calculation results are as follows:

[0055] Table 1 Avoidance turning radius R

[0056]

[0057] Substitute the calculated evasive turning radius R into the calculation formula in step 2, and calculate the normal overload coefficient n at different speeds z , as shown in Table 2.

[0058] Table 2 Normal overload factor n z

[0059]

[0060] The normal overload factor n z Substituting the formula in step 3 to get the turning time t of the aircraft, the calculation results are shown in Table 3:

[0061] Table 3 Aircraft turning time t

[0062]

[0063] The normal overload factor n z Substituting the formula in step 4, the aircraft turning angular velocity ω and aircraft slope φ at different speeds can be calculated. The calculation res...

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Abstract

The invention belongs to the design field of flight safety, and relates to a method for determining airplane critical circumvention parameters in low-altitude wind shear. The method is characterized in that the method for circumventing the low-altitude wind shear in a critical mode for an airplane includes the following steps that a circumvention turning radius R is calculated; a normal direction overload coefficient nz is calculated; turning time t of the airplane is calculated; airplane turning angular speed omega and airplane gradient phi are calculated; minimum flight safety height Hs of the airplane is calculated. The method for determining the airplane critical circumvention parameters in the low-altitude wind shear substantially reduces workloads, and improves working efficiency.

Description

technical field [0001] The invention belongs to the field of flight safety design and relates to a method for determining critical avoidance parameters of an aircraft in low-altitude wind shear. Background technique [0002] The determination of the critical trajectory of the aircraft to avoid wind shear can ensure the safe flight of the aircraft. If it directly penetrates or partially penetrates the wind shear, it may cause flight hazards, so the determination of the critical trajectory to avoid is particularly important. figure 1 is a schematic diagram of an aircraft avoiding a windshear area. ( figure 1 D is the scale of wind shear; the small circle with scale D represents the wind shear area; L is the radar detection distance of the aircraft; AB section is the critical avoidance trajectory; R is the avoidance radius; R+D / 2 represents the center of the wind shear area Distance to the center of the avoidance trajectory. ) At present, for the problem of wind shear avoida...

Claims

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Application Information

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IPC IPC(8): G06F19/00
Inventor 武虎子耿建中李伟
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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