(中南大学 粉末冶金国家重点实验室， 长沙 410083)
摘 要: 采用针刺整体毡炭/炭(C/C)复合材料整体喉衬进行小型固体火箭发动机地面点火实验， 结合扫描电镜(SEM)及能谱分析(EDS)， 分别对烧蚀后整体喉衬收敛部位、 喉径部位和扩张部位的烧蚀形貌进行分析。 结果表明： 在较高压强 (12~14 MPa)条件下， 针刺整体毡C/C复合材料整体喉衬烧蚀均匀， 烧蚀型面光滑、 烧蚀率低， 但因轴向纤维少及轴向强度较低， 接近喉径部位的收敛部位和喉径部位易产生分层； 不同部位的烧蚀形貌不同， 是由于整体喷管中的燃气温度、 组分浓度和速度所致。
关键字: 固体火箭发动机； C/C复合材料； 整体喉衬； 地面点火实验； 烧蚀
（State Key Laboratory of Powder Metallurgy, Central South University,
Changsha 410083, China）
Abstract: The firing test was carried out to test the ablation performance of bulk needled carbon fiber felts reinforced carbon composites integrated throat. The ablation morphologies of the entrance part, throat and exit part were investigated by scanning electron microscopy (SEM) and energy diffraction spectrum(EDS).The results show that under the high pressure of about 12-14 MPa, the ablation of the carbon/carbon throat is homogeneous, and the throat contour is smooth. But at the throat or near to the entrance part, it is easy to be delaminated because of its weak strength of the axial direction caused by not enough axial fibers. The ablation morphologies between each parts are different which may closely relate with temperature, velocity and concentration of the fuel.
Key words: solid rocket motor; C/C composites; integrated throat; firing test; ablation
