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- Numerical solutions of full Navier-Stokes equations with chemical reaction flow were obtained for of the LOX/HTPB hybrid rocket motor. 利用二维轴对称N-S方程和组分方程对选用液氧/端羟基聚丁二烯推进剂的固液混合火箭发动机的燃烧室和喷管进行了一体化计算。
- Numerical solutions of full Navier-Stokes equations with chemical reaction flow were established for the nozzle flow of the LOX/HTPB hybrid rocket motor. 利用二维轴对称N-S方程和组分方程对选用液氧/端羟基聚丁二烯推进剂的固液混合火箭发动机喷管流动进行了计算。
- Estey Paul N, Whittinghill Geroge R. Hybrid rocket motors propellant selection alternative. AIAA Paper 92-3592. 单建胜等.;固液火箭发动机的研制及其应用
- Chiaverini, M.J. et.Al., ”Fuel Decomposition and Boundary Layer Combustion Processes of Hybrid Rocket Motors,” AIAA Paper 95-2686, 1995. 林涌丰;“混合火箭燃烧特性之研究”;国立成功大学航空太空工程研究所硕士论文(2000).
- Models of the Fuel Surface Regression Rate in Hybrid Rocket Motor 混合发动机燃面后退速率模型分析
- The Opportunity for Hybrid Rocket Motor in Commercial Space Applications 固液火箭发动机在空间发射上的应用前景
- Effects of combustion chamber structure on combustion and flow of hybrid rocket motor 燃烧室结构对固液火箭发动机燃烧与流动的影响研究
- Regression rate calculation for the solid fuel surface of hybrid rocket motor based on fluid-solid coupling technique 基于流-固耦合的混合火箭发动机固体燃料表面退移速率计算
- Keywords hybrid rocket motor;low density polyethylene;pyrolysis;pyrolytic model; 固液火箭发动机;低密度聚乙烯;热解;热解模型;
- Computation of fuel regression rate in classical hybrid rocket motors 固液混合火箭发动机固体燃料的燃速计算
- hybrid rocket motor 固液火箭发动机
- Altman D. Hybrid rocket development history. AIAA Paper 91-2515. 单建胜等.;固液火箭发动机的研制及其应用
- Numerical Simulation of Combustion Chamber and Nozzle Flow in Classical Hybrid Rocket Motors 固液混合火箭发动机燃烧室和喷管流动数值模拟
- 9 Estey Paul N, Whittinghill Geroge R. Hybrid rocket motors propellant selection alternative. AIAA Paper 92-3592. 10单建胜等.;固液火箭发动机的研制及其应用
- Rocket motor cases and the specially designed production equipment therefor. 四、火箭发动机的壳体及为其专门设计的生产设备。
- Kniffen B J. Hybrid rocket development at the American rocket company. AIAA Paper 90-2762. 单建胜等.;固液火箭发动机的研制及其应用
- Rocket motors have many advantages over other forms of propulsion. 火箭发动机比其他推进器有许多优点。
- Chiaverini, M.J. et.Al., “Pyrolisis Behavior of Hybrid Rocket Solid Fuels Under Rapid Heating Conditions,” AIAA Paper No. 97-3078, 1997. 施耿维;“混合推进剂燃烧组织与性能”;国立成功大学航空太空工程研究所硕士论文(1999).
- Four nozzles, canted outboard, split the exhaust of the solid rocket motor into four equal tails. 四个向外倾斜的喷管把固体火箭发动机的排气流分成四个相等的尾巴。
- Another unconventional design element, the hybrid rocket engine that powers the suborbital vehicle, provides unique operational options. 另一个异于传统的设计要素,是提供次轨道载具动力的混合式火箭引擎,它能提供独特的操作选择。