Unsteady process of aerodynamic throat for solid rocket motor
School of Astronautics, Beijing Univ. of Aeronautics and Astronautics, Beijing 100191, China;School of Astronautics, Beijing Univ. of Aeronautics and Astronautics, Beijing 100191, China;School of Astronautics, Beijing Univ. of Aeronautics and Astronautics, Beijing 100191, China
[2] John N,Victoria G.Controllable solid propulsion for launch vehicle and spacecraft application[R].AIAA 2006-0468. [3] 王毅林,何国强,李江,等.非同轴式喉拴变推力固体火箭发动机试验[J]。固体火箭技术,2008,31(1):43-46. [4] 李娟,李江,王毅林,等.喉拴式变推力发动机性能研究[J].固体火箭技术,7,0(6):505-509. [5] Miller D N, Catt J A.Conceptual development of fixed-geometry nozzles using fluidic injection for throat-area control[R].AIAA 95-2603. [6] McArdle J G.Internal characteristics and performance of an aerodynamically controlled, variable discharge convergent nozzle[R].NACA-TN42,8. [7] Damiel Y, Miller N, Patrick J Y,et al.Fluidic throat skewing for thrust vectoring in fixed-geometry nozzles[R].AIAA 99-0365. [8] Baruzzini D, Domel N, Miller D N, et al.Pulsed injection flow control for throttling in supersonic nozzles-a computational fluid dynamics design study[R].AIAA 2007-4215. [9] 谢侃,刘宇,任军学,等.两相流环缝塞式喷管理想型面的设计方法[J].航空学报,2007,28(6):1339-1344. [10] 陈军涛,蹇泽群,陈林泉.固体火箭发动机点火瞬时内流场轴对称数值分析[J].固体火箭技术,2004,27(3):173-176.