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Steady-state load analysis method for large aircraft tests under multiple environmental factors

A steady-state load and analysis method technology, applied in aircraft component testing, computer-aided design, geometric CAD, etc., can solve problems such as inability to provide design basis for refrigeration system selection and configuration, imperfect calculations, etc., to improve calculation accuracy and solve Selection and configuration problems, and the effect of verification

Active Publication Date: 2022-06-24
CHINA AIRPLANT STRENGTH RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] In order to reasonably configure the refrigeration system capacity and avoid over-design or under-design of the laboratory refrigeration system capacity, it is necessary to accurately calculate the steady-state heat load of the aircraft climate laboratory under different test / working conditions (solar irradiation, freezing rain, snowfall) , but the calculation of the steady-state load of large-scale aircraft tests under the condition of multiple environmental factors is not perfect at present, and cannot provide a design basis for the selection and configuration of the refrigeration system

Method used

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  • Steady-state load analysis method for large aircraft tests under multiple environmental factors
  • Steady-state load analysis method for large aircraft tests under multiple environmental factors
  • Steady-state load analysis method for large aircraft tests under multiple environmental factors

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Embodiment 1

[0056] This embodiment is: in the case that the test working condition in the aircraft climate laboratory is a solar irradiation working condition with a temperature of 28° C., a large-scale aircraft test steady-state load analysis method under the condition of multiple environmental factors, including the following steps:

[0057] S1. According to the solar irradiation working condition of 28°C, set the corresponding parameters. The corresponding parameters include: indoor air temperature value , aircraft climate laboratory altitude , aircraft climate laboratory width , the length of the aircraft climate laboratory , lighting power factor , air specific heat coefficient , Compensation for fresh air quality , the number of full-spectrum lamps , the power of the full-spectrum lamp is , The heat absorption efficiency coefficient of the aircraft to the full-spectrum lamp , the number of infrared lamps , The power of the infrared lamp , The heat absorption eff...

Embodiment 2

[0085] This embodiment is: in the case that the test working condition in the aircraft climate laboratory is the freezing rain working condition with a temperature of -10°C, a large-scale aircraft test steady-state load analysis method under the condition of multiple environmental factors, including the following steps:

[0086] S1. According to the freezing rain working condition of -10℃, set the corresponding parameters. The corresponding parameters include: indoor air temperature value , aircraft climate laboratory altitude , aircraft climate laboratory width , the length of the aircraft climate laboratory , lighting power factor , air specific heat coefficient , Compensation for fresh air quality , insulation board thickness , heat transfer coefficient of insulation board , test water consumption , specific heat coefficient of water , Test water temperature , latent heat coefficient of water , The specific heat coefficient of ice , Strong convectiv...

Embodiment 3

[0114] This embodiment is: in the case that the test working condition in the aircraft climate laboratory is a snowfall working condition with a temperature of -25°C, a large-scale aircraft test steady-state load analysis method under the condition of multiple environmental factors, including the following steps:

[0115] S1. According to the snowfall working condition of -25℃ in the test working condition, set the corresponding parameters. The corresponding parameters include: indoor air temperature value , aircraft climate laboratory altitude , aircraft climate laboratory width , the length of the aircraft climate laboratory , lighting power factor , air specific heat coefficient , Compensation for fresh air quality , air specific heat coefficient , Compensation for fresh air quality , insulation board thickness , heat transfer coefficient of insulation board , test water consumption , specific heat coefficient of water , Test water temperature , lat...

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Abstract

The invention provides a large-scale aircraft test steady-state load analysis method under the condition of multiple environmental factors, belonging to the technical field of aircraft testing, comprising the following steps: S1, setting parameters; S2, calculating the area of ​​the insulation board of the aircraft climate laboratory; S3, calculating the aircraft climate experiment indoor lighting load; S4, calculate and compensate the fresh air heat load; S5, calculate the heat load of the fan; S6, calculate the heat load of the insulation board; S7, calculate the heat load of the solar radiation array; S8, calculate the heat load of freezing rain / snowfall conditions; 1. Calculating the heat load of the floor; S10. Calculating the heat load of the test piece object; S11. Calculating the heat load required by the refrigeration system. The invention solves the problem that the calculation of the steady-state load of the large-scale aircraft test is not perfect under the condition of multiple environmental factors at present, and the problem that the design basis cannot be provided for the type selection and configuration of the refrigeration system has the advantages of comprehensive consideration of interference factors and accurate calculation.

Description

technical field [0001] The invention relates to the technical field of aircraft testing, in particular to a large-scale aircraft testing steady-state load analysis method under the condition of multiple environmental factors. Background technique [0002] The Aircraft Climate Environment Laboratory is the first ultra-large aircraft climate environment simulation facility in my country that can simulate typical climate environments such as high temperature, low temperature, solar radiation, temperature / humidity, rain, snowfall, freezing rain, and icing. The indoor climate environment test of missile weapon system and other equipment has filled the domestic gap in the field of aircraft climate environment test. [0003] The aircraft climate and environment laboratory can simulate many environmental factors. In order to reproduce various climate environments in the laboratory, the laboratory is designed with refrigeration, heating, cooling / heating, circulating air processing uni...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/15B64F5/60G06F119/08
CPCG06F30/15B64F5/60G06F2119/08
Inventor 王彬文强宝平成竹吴敬涛李闯勤
Owner CHINA AIRPLANT STRENGTH RES INST
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