一種固體火箭發動機噴管擺動冷流縮比試驗方法
郭小帆
摘 要：針對研究噴管擺動工況下擴壓器工作特性的試驗中存在：噴管擺動難以實現；若以高溫高壓蒸汽或者燃氣作為引射介質，雖引射效率高但耗費巨大的人力物力等問題在發動機研制初期很難被采納。該文提出一種以擴壓器擺動等效噴管擺動，以冷空氣作為引射和被引射介質的簡化試驗方法。數值計算結果與試驗結果符合較好，試驗方法經濟實用，操作簡單，可以作為擺動噴管固體火箭發動機研制初期的試驗手段。
關鍵詞：固體火箭發動機；冷流縮比試驗；噴管擺動；試驗方法
中圖分類號：V435+.6；TM930.12；V42；V435+.23 文獻標志碼：A 文章編號：1674-5124（2013）05-0039-03
Cold-flow testing of sub-scale model for swinging nozzle of solid-rocket engines
GUO Xiao-fan， YANG Xiao-hui， HE De-sheng， LI Guang-wu
（The 401th Research Institute of the Fourth Academy of CASC，Xi’an 710025，China）
Abstract: There are two questions in the characteristics test of diffuser with the swinging nozzle. Firstly， swinging nozzle is too difficult to achieve. Secondly， although the efficiency of ejector is high in the test which the ejector media is the steam or gas with high temperature and pressure， costly human and material resources are too hard to be adopted in the early development of the solid-rocket motor. To solve problems mentioned above， this paper presented a simplified test method that swinging diffuser is equivalent to swinging nozzle and cold air is used as the ejector media. The numerical results agree well with the available test data. The test method can be applied on the solid-rocket with swinging nozzle principle design because it is convenient， economical and practical.
Key words: solid-rocket engine； cold-flow testing of sub-scale model； swinging nozzle； test method
