Design method of low Mach number flight total enthalpy platform based on existing hypersonic wind tunnel

A hypersonic and Mach number technology, applied in aircraft component testing, machine/structural component testing, instruments, etc., can solve problems such as inability to simulate local conditions, achieve rapid formation of test capabilities, expand the scope of test capabilities, and improve tests The effect of the competency system

Active Publication Date: 2022-05-17
中国空气动力研究与发展中心超高速空气动力研究所
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Existing conventional hypersonic wind tunnels have formed large, medium and small supporting test capability systems with reasonable dimensions, which are necessary for simulating aircraft flight Mach number, local pressure, flight angle, etc., but cannot simulate local conditions under real flight conditions. Zong Han

Method used

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  • Design method of low Mach number flight total enthalpy platform based on existing hypersonic wind tunnel
  • Design method of low Mach number flight total enthalpy platform based on existing hypersonic wind tunnel
  • Design method of low Mach number flight total enthalpy platform based on existing hypersonic wind tunnel

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Embodiment 1

[0082] This embodiment is a wind tunnel test platform that reproduces the total flight enthalpy of Mach number 2-3.

[0083] like figure 2 As shown, in this embodiment, an existing wind tunnel with a Mach number 8 heater 2 is selected to establish a wind tunnel test platform that reproduces the total flight enthalpy of Mach number 2-3. On the existing wind tunnel equipment support device 6, the existing wind tunnel high pressure air source system 1, the existing wind tunnel Mach number 8 heat valve 4, the Mach number 2-3 stable section and the transition section 9, and the Mach number 2~ 3. Nozzle 10, new nozzle with Mach number 2 to 3 connecting with the original test section 11, existing wind tunnel test section 7 and existing wind tunnel diffuser 8, and inside the existing wind tunnel diffuser 8 The cavity set mounts the platform diffuser 12 .

Embodiment 2

[0085] This embodiment is a wind tunnel test platform that reproduces the total flight enthalpy of Mach number 3.5-4.

[0086] like image 3 As shown, in this embodiment, an existing wind tunnel with a Mach number of 10 heaters 3 is selected to establish a wind tunnel test platform that reproduces the total flight enthalpy of Mach numbers 2 to 3. On the existing wind tunnel equipment support device 6, the existing wind tunnel high pressure air source system 1, the existing wind tunnel Mach number 10 heat valve 5, the Mach number 3.5-4 stable section and the transition section 13, and the Mach number 3.5~ 4. Nozzle 14, new nozzle with Mach number 3.5 to 4 connecting with the original test section 15, existing wind tunnel test section 7 and existing wind tunnel diffuser 8, and inside the existing wind tunnel diffuser 8 The cavity set mounts the platform diffuser 12 .

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Abstract

The invention belongs to the field of hypersonic wind tunnel test equipment and discloses a method for designing a low Mach number flight total enthalpy platform based on an existing hypersonic wind tunnel. This method uses the existing hypersonic wind tunnels of different calibers to carry out corresponding nozzles, stable sections, transition sections, and diffusers to complete the flight total enthalpy wind tunnel test of low Mach number 2-4 range of different calibers. The platform has a simulated total temperature range of 390K to 950K, a simulated altitude of 15 km to 30 km, and an effective running time of the test platform of ≥30 seconds, which meets the test of the combined power performance of the engine of the aircraft at low Mach number and the thermal coupling test of the integrated internal and external flow of the aircraft. Carry out basic theory and experimental technology research, carry out special tests and verifications, and provide test data and test verification support for aircraft development.

Description

technical field [0001] The invention belongs to the field of hypersonic wind tunnel test equipment, and in particular relates to a method for designing a low Mach number flight total enthalpy platform based on an existing hypersonic wind tunnel. Background technique [0002] In the early days, the wind tunnel test of supersonic aircraft mainly measured the aerodynamic characteristics (aerodynamic force, flight attitude, aerodynamic shape, etc.) or performance of the aircraft. In a supersonic or hypersonic wind tunnel, the airflow expands violently through the nozzle, causing the static temperature of the airflow to drop rapidly. For example, when M≥5, when the temperature of the airflow in the stable section of the wind tunnel is 288K, the temperature of the airflow in the test section of the wind tunnel drops to 48K. At such a low temperature, the air itself condenses, and the condensation heat is released as the condensation proceeds. , and passed to the airflow, so that ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M9/00G01M9/04B64F5/60
CPCY02T90/00
Inventor 孙启志范孝华许晓斌将万秋凌岗巣根明陈映东
Owner 中国空气动力研究与发展中心超高速空气动力研究所
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