Motor system for stratosphere environment simulation

Abstract

The invention discloses a motor system for stratosphere environment simulation, which comprises a structural system, a sealing system, a heat dissipation system, a heat preservation system and a rectification structure, and is characterized in that the structural system is integrally designed based on a fan tail cover and provides installation interfaces for a fan motor and other hardware, and the sealing system provides sealing boundary conditions; the heat dissipation system is composed of a static seal and a cabin-penetrating dynamic seal, the heat dissipation system mainly comprises a pipeline, a fan and the like, heat of a motor is taken away by introducing normal-pressure and normal-temperature air, and the heat preservation system is composed of a foaming material and an electric heater and installed in the structural system. According to the invention, the wind field simulation requirement in a low-temperature and extremely-low-pressure environment is met by using the goods shelf product fan, and meanwhile, the structure of the system is optimized and the space requirement of the system is reduced through the conformal design of the heat preservation system and the fan tail cover and the fusion design of the heat dissipation channel, the cable channel and the rectification structure.

Description

technical field [0001] The invention relates to the technical field of ground special tests, in particular to a motor system for stratospheric environment simulation. Background technique [0002] Stratospheric aircraft such as high-altitude drones and stratospheric airships generally operate at an altitude of 16km to 30km, the air pressure is generally 1.2kPa to 10.3kPa, the air temperature range is generally -60°C to -40°C, and the wind speed is generally around 20m / s . For the low Reynolds number flow under low pressure, there is still a lack of basic data support, lack of convection and heat transfer empirical correlation support, and simulation data often need to be corrected by experimental means. Therefore, in order to achieve the purpose of thermal model correction and thermal control system performance assessment, it is necessary to conduct thermal environment simulation tests on the key loads of high-altitude UAVs and stratospheric airships in ground simulation en...

AI Technical Summary

Problems solved by technology

[0003] In order to form a stable, uniform and continuous wind field under low pressure, the current technical solutions include the return type and the ejection type, among which the latter can only be used for short-term simulation, and it is difficult to accurately evaluate the heat transfer characteristics. Therefore, the return air duct is generally used for key tests and verifications.

Different from the wind tunnel tests commonly used in aviation at present, the pressure is often lower, so the convective heat transfer capacity of the air is greatly reduced, and it is difficult to effectively dissipate heat from the motor itself through the wind field. At the same time, in the cooling process of the system, the fan needs to be considered own insulation problem

Some previous test equipment adopted the scheme of installing the motor outside the equipment, but the system is often more complicated, and the motor drive shaft needs to pass through the vacuum container, heat exchanger and air duct in sequence, so the design is more complicated

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