Method and device for measuring and controlling surface temperature of ablated carbon layer

Abstract

The invention discloses an ablation carbon layer surface temperature measurement control method and device. The control method comprises the following steps: independently controlling heating power ofa plane heater and an annular heater to realize independent controllability of heat transfer flows on two directions; embedding temperature thermocouples at an internal axis of the ablation carbon layer to measure temperature at two points, and acquiring ablation carbon layer surface temperature dynamic data through a method for computing surface temperature based on the single-face heat source one-dimensional heat transfer model, and realizing the accurate collection and closed-loop control of the surface temperature of the ablation carbon layer by controlling the power of the plane heater;performing two-point temperature measurement by embedding the temperature thermocouples at the same depth and different radial locations at the near surface of the ablation carbon layer so as to acquire the surface temperature uniformity dynamic data of the ablation carbon layer, and controlling the surface temperature uniformity and consistency by controlling the heating power of the annular heater. The device can effectively inhibit the surface temperature testing error caused by the high thermal radiation characteristic of the ablation carbon layer and internal low heat conduction heat transmission characteristic, thereby realizing the accurate measurement and control of the ablation carbon layer surface temperature.

Description

technical field [0001] The invention relates to a method and a device for measuring and controlling the surface temperature of an ablation carbon layer, belonging to the field of heat radiation performance testing of materials. Background technique [0002] The outer heat-resistant structure of atmospheric re-entry vehicles and near-space hypersonic vehicles usually generates high surface temperature due to the aerodynamic heating effect. According to Planck's law, the amount of thermal radiation and heat dissipation on the surface of a material increases with the increase of temperature in the form of a fourth power function. During high-temperature service, the radiation heat exchange between the aircraft's heat-resistant structure and outer space is the most important way of heat dissipation. one. [0003] Resin-based heat-resistant composite materials, represented by quartz phenolic heat-resistant composite materials and heat-insulated integrated heat-resistant composit...

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Problems solved by technology

[0007] In summary, due to the heat transfer characteristics of the ablation carbon layer with poor internal thermal conductivity and strong surface heat radiation and heat dissipation, the current surface temperature control device of the existing material is not suitable for the ablation carbon layer material, resulting in high temperature heat radiation of the ablation carbon layer The test results are seriously biased

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