Aircraft-missile separation dynamics similar wind tunnel test method

A wind tunnel test and dynamics technology, applied in aerodynamic tests, machine/structural component testing, measuring devices, etc., can solve the inaccurate simulation of bomb-loaded displacement, the difficulty of extensive application of the heavy model method, and the difficulty in engineering And other issues

Inactive Publication Date: 2020-11-20
CHINA ACAD OF AEROSPACE AERODYNAMICS
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Problems solved by technology

However, the heavy model method has high requirements on the density of the model, which is difficult to achieve in engineering, which brings difficulties to the wide application of the heavy model method
The light model method is easier to implement in practical applications, but the...

Method used

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  • Aircraft-missile separation dynamics similar wind tunnel test method
  • Aircraft-missile separation dynamics similar wind tunnel test method
  • Aircraft-missile separation dynamics similar wind tunnel test method

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Embodiment 1

[0034] Such as figure 1 As shown, a similar wind tunnel test method for machine-shell separation dynamics includes the following steps:

[0035] (1) According to the similarity requirement of the ratio of gravity to aerodynamic force in the dynamics similarity criterion of separation and delivery, a design variable k is introduced n , to obtain an engineering-applicable design method for dynamic similarity parameters.

[0036] The kinetic similarity parameters are derived as follows:

[0037] The ratio of aerodynamic force to gravity on the model is similar to that of the real aircraft, which can be expressed as:

[0038]

[0039] In the formula: Y m is the aerodynamic force of the wind tunnel test model, Y s is the actual aircraft aerodynamic force, m m is the mass of the wind tunnel test model, m s is the mass of the actual aircraft, g zm is the vertical acceleration of the wind tunnel test, g zs is the actual aircraft vertical acceleration.

[0040] Formula (1) ...

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Abstract

The invention relates to an aircraft-missile separation dynamics similar wind tunnel test method, which aims to realize dynamics similar simulation of an aircraft-missile dynamic separation process ina wind tunnel and obtain motion/aerodynamic characteristics of a carrier missile in the separation process under the action of an aircraft interference flow field, and belongs to the field of test aerodynamics. The method comprises the following steps of (1) introducing a design variable to obtain a dynamics similar parameter design method suitable for engineering, (2) according to a dynamics similar parameter design method, obtaining dynamics similar parameters of the carrier missile, (3) obtaining a wind tunnel test model of the carrier missile by utilizing the dynamics similar parametersof the carrier missile, and (4) increasing the initial separation speed or the ejection force in the wind tunnel test process, and performing test correction on insufficient vertical acceleration simulation to obtain a more realistic carrier missile separation motion characteristic result.

Description

technical field [0001] The invention relates to a similar wind tunnel test method for machine-elastic separation dynamics, which belongs to the field of test aerodynamics. Background technique [0002] Airborne weapons will be subject to the complex aerodynamic interference effect of the aircraft at the initial stage of separation from the aircraft, making their motion characteristics significantly different from those in the free flow field, and extreme situations will endanger the safety of the aircraft. Therefore, it is necessary for airborne weapons to carry out wind tunnel simulation tests before flying to study the compatibility of aircraft and bombs. There are two types of wind tunnel test methods: capture trajectory and wind tunnel model test. Among them, the wind tunnel model test needs to ensure the dynamic similarity criterion. [0003] In the high-speed wind tunnel, the similar model launch test of the aircraft-to-bullet separation dynamics must be considered in...

Claims

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Application Information

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IPC IPC(8): G01M9/00G01M9/08
CPCG01M9/00G01M9/08
Inventor 董金刚张晨凯王帅张江
Owner CHINA ACAD OF AEROSPACE AERODYNAMICS
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