双工况流量调节阀的设计与试验
Design and experiment of two-stage flow control valve
-
摘要: 介绍了一种双工况流量调节阀的原理与设计方法,利用上游贮箱压力作为控制气调节阀芯位移,控制阀门开启与工况调节,实现飞行用挤压式供给系统的启动以及流量快速调节.分析了阀门关键设计参数:敏感元件外径、弹簧刚度和初始压缩量对阀芯位移的影响;通过试验验证了阀门的压降损失在2种工况下能分别保持固定值;对采用该阀门的供给系统进行了试验,试验中阀门开启迅速,成功实现了氧化剂供给系统的流量调节,其中第1工况阶段流量约4.5kg/s,第2工况阶段流量为2.0kg/s,工况转换较迅速,达到了预期值,这说明阀门的原理和设计方法是可行的.Abstract: Principle and design methods of a new two-stage flow control valve were presented.Tank pressure was used to regulate the motion of the valve to open the valve and change the work status.The pressurization feeding system started and changed the mass flow rate of the oxide as the valve worked.The key parameters of the valve,including key part's outer diameter,the stiffness and initial compression of the spring,were analyzed.The tests show that the coefficients of local pressure loss of the valve were same at different working statuses.Experimental results for the feeding system using the valve were obtained.In the tests,the valve opened quickly and the feeding system changed the mass flow successfully.In the first stage,the mass flow rate of the hydrogen peroxide was 4.5kg/s.In the second stage,it was 2kg/s.It is proved that the design and test methods of the valve are feasible.
-
Key words:
- valve /
- mass flow control /
- coefficient of local pressure loss /
- feeding system /
- variable thrust engine
-
[1] 蔡国飙,李家文,田爱梅,等.液体火箭发动机设计[M].北京:北京航空航天大学出版社,2011. [2] Sutton G P.Rocket propulsion elements:an introduction to the engineering of rockets[M].7th ed.New York:John Wiley & Sons Inc.,2001. [3] Chiaverini M J,Kuo K K.Fundamentals of hybrid rocket combustion and propulsion[M].Reston VA,US:AIAA,2007. [4] 休泽尔.液体火箭发动机现代工程设计[M].朱宁昌,译.北京:中国宇航出版社,2004. [5] 张黎辉,张国舟,程显辰.液体火箭发动机输送系统(讲义)[M].北京:北京航空航天大学出版社,2000. [6] 龙乐豪.总体设计(中)[M].北京:中国宇航出版社,2005. [7] 路史光.飞航导弹总体设计[M].北京:中国宇航出版社,2005. [8] 高汉如,陈启智,杨乐平.文氏管和喷注器双调节变推力液体火箭发动机试验研究[J].航空动力学报,1989,4(1):45-49. GAO Hanru,CHEN Qizhi,YANG Loping.Experimental research on a bipropellant throttling liquid rocket engine with controllable injector and throttling cavitating venture[J].Journal of Aerospace Power,1989,4(1) :45-49.(in Chinese) [9] 陈启智,高汉如.流量可调汽蚀文氏管喉部圆柱段长度的设计方法[J].航空动力学报,1987,2(3):235-238. CHEN Qizhi,GAO Hanru.A design method for length of cylindrical segment in a throtting cavitation venturi throat[J].Journal of Aerospace Power,1987,2(3):235-238.(in Chinese) [10] Austin B L,Heister S D J,Dambach E M.Variable thrust,multiple start hybrid motor solutions for missile and space applications .AIAA 2010-7121,2010. [11] 张育林.变推力液体火箭发动机及其控制技术[M].北京:国防工业出版社,2005. [12] 张金容,靳爱国,汪亮.泵压式液体火箭发动机变推力方案选择[J].航空动力学报,2008,23(5):921-926. ZHANG Jinrong,JIN Aiguo,WANG Liang.Thrust regulation scheme selection for turbopump fed rocket engine with variable thrust[J].Journal of Aerospace Power,2008,23(5):921-926.(in Chinese) [13] 刘景华,谭建国,杨涛,等.部分催化过氧化氢变推力发动机的稳定性分析[J].航空动力学报,2007,22(11):1954-1957. LIU Jinghua,TAN Jianguo,YANG Tao,et al.Stability analysis on variable thrust engine of partially catalyzed hydrogen peroxide[J].Journal of Aerospace Power,2007,22(11):1954-1957.(in Chinese) [14] Ring E.Rocket propellant and pressurization systems[M].Englewood Cliffs,NJ:Prentice-Hall Inc.,1964. [15] 华绍曾,杨学宁.实用流体阻力手册[M].北京:国防工业出版社,1985.
点击查看大图
计量
- 文章访问数: 1460
- HTML浏览量: 3
- PDF量: 1215
- 被引次数: 0