炭/酚醛燃气舵烧蚀性能

Ablation performance of carbon-phenolic jet vanes

选用梯形舵面、六边形翼型设计,以炭/酚醛复合材料为原材料制作了炭/酚醛燃气舵,用短时间工作的固体火箭发动机提供地面射流环境。采用光栅式三维扫描仪获取烧蚀前后舵面形貌,得到了舵面烧蚀量云图,研究了15°舵偏角炭/酚醛燃气舵在不同位置处的微观烧蚀形貌。研究结果表明,炭/酚醛燃气舵在工作结束后,前缘烧蚀量最大,约为(8±0.3)mm。0°舵偏角工况下,侧面烧蚀量较小,控制在0.2 mm以内。燃气舵发生偏转后,迎风面烧蚀量随着舵偏角的增大而增大,在20°舵偏角工况下,迎风面烧蚀量达到了0.8~1 mm;而背风面几乎不发生烧蚀现象。试验结果表明,炭/酚醛燃气舵能够在短时间内保证面烧蚀率要求的前提下正常工作。

The trapezoidal profile and hexagon section was chosen to manufacture carbon-phenolic jet vanes made of carbon- phenolic composite. The jet environment was provided by solid rocket motors with short working time. Ablation contours of jet vanes were obtained by raster 3D scanner. The ablation micro-morphology of carbon-phenolic jet vanes at 15° in different locations was in- vestigated. The results show that, at the end of the work, amount of ablation at leading edge of carbon-phenolic jet vanes is the lar- gest, which is about （8±0.3）mm. The ablation on side surface is small and less than 0.2 mm under 0° angle condition. The amount of ablation on upwind side surface increases with the angle, when the jet vane deflects. Ablation on upwind side surface can reach 0.8- 1 mm at 20° angle. There is hardly any ablation on the leeward side surface. The experiment results show that, the carbon-phe- nolic jet vanes can work normally in a short working time.