航空计算技术
航空計算技術
항공계산기술
AERONAUTICAL COMPUTER TECHNIQUE
2014年
2期
77-80
,共4页
杨帆%刘增文%刘帅%王占学%张晓博
楊帆%劉增文%劉帥%王佔學%張曉博
양범%류증문%류수%왕점학%장효박
短距/垂直起降%三轴承旋转喷管%型面设计%数值模拟%推力矢量有效偏转角
短距/垂直起降%三軸承鏇轉噴管%型麵設計%數值模擬%推力矢量有效偏轉角
단거/수직기강%삼축승선전분관%형면설계%수치모의%추력시량유효편전각
short takeoff/vertical landing%three bearing swivel nozzle%inner contour design%numerical simulation%effective thrust vector angle
通过对短距/垂直起降用三轴承旋转喷管工作原理的分析，给出了型面设计的技术指标，并对三轴承旋转喷管型面进行了分析，探讨了等直段、型面过渡段、收缩喷管段的设计方法。同时，基于某型涡喷发动机开展了数值模拟分析，发现喷管推力矢量有效偏转角与喷管偏转角度大致呈线性关系，且前者约为后者的1．021倍，则设计的三轴承旋转喷管具有产生矢量推力的能力，满足了型面设计的要求。
通過對短距/垂直起降用三軸承鏇轉噴管工作原理的分析，給齣瞭型麵設計的技術指標，併對三軸承鏇轉噴管型麵進行瞭分析，探討瞭等直段、型麵過渡段、收縮噴管段的設計方法。同時，基于某型渦噴髮動機開展瞭數值模擬分析，髮現噴管推力矢量有效偏轉角與噴管偏轉角度大緻呈線性關繫，且前者約為後者的1．021倍，則設計的三軸承鏇轉噴管具有產生矢量推力的能力，滿足瞭型麵設計的要求。
통과대단거/수직기강용삼축승선전분관공작원리적분석，급출료형면설계적기술지표，병대삼축승선전분관형면진행료분석，탐토료등직단、형면과도단、수축분관단적설계방법。동시，기우모형와분발동궤개전료수치모의분석，발현분관추력시량유효편전각여분관편전각도대치정선성관계，차전자약위후자적1．021배，칙설계적삼축승선전분관구유산생시량추력적능력，만족료형면설계적요구。
According to the analysis of the working principle of three bearing swivel nozzle ,the technical index of the inner contour design was given .Besides ,the analysis of three bearing swivel nozzle inner con-tour was carried on and the design method of the straight section ,transition section ,contraction section of nozzle were discussed .Meanwhile ,based on a turbojet engine ,numerical simulation was carried out .It has been found that the effective thrust vector angle with the nozzle deflection angle is roughly linear relation -ship,and the former is approximately 1.021 times of the latter.In conclusion,the three bearing rotating nozzle has the ability to produce thrust vector between 0 degree and 95 degree ,which reaches the indexes of the inner contour design requirements .
