(中南大學 粉末冶金國家重點實驗室， 長沙 410083)
摘 要: 采用針刺整體氈炭/炭(C/C)復合材料整體喉襯進行小型固體火箭發(fā)動機地面點火實驗， 結合掃描電鏡(SEM)及能譜分析(EDS)， 分別對燒蝕后整體喉襯收斂部位、 喉徑部位和擴張部位的燒蝕形貌進行分析。 結果表明： 在較高壓強 (12~14 MPa)條件下， 針刺整體氈C/C復合材料整體喉襯燒蝕均勻， 燒蝕型面光滑、 燒蝕率低， 但因軸向纖維少及軸向強度較低， 接近喉徑部位的收斂部位和喉徑部位易產生分層； 不同部位的燒蝕形貌不同， 是由于整體噴管中的燃氣溫度、 組分濃度和速度所致。
關鍵字: 固體火箭發(fā)動機； C/C復合材料； 整體喉襯； 地面點火實驗； 燒蝕
（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
