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- At first, the thermodynamic calculation of Solid Ducted Rocket is researche. 在此基础上，首先对固体冲压发动机热力计算展开了研究分析。
- In this paper, the theory of minitype Solid Ducted Rocket with shot is researche nd analyzed. 本文研究和分析了炮射小型固体火箭冲压发动机的工作原理。
- It would be of great reference value for development of air-to-air missile propelled by integral solid ducted rocket. 对我国发展采用整体式固冲发动机的空空导弹具有重要的参考价值。
- unchoked solid ducted rocket engine 非壅塞固体火箭冲压发动机
- The Optimum Intermediate Guidance Law of Missile Considering the Characteristic of Solid Ducted Rocket 考虑冲压发动机特性的导弹最优中制导律研究
- Influence of afterburning chamber length on secondary combustion for solid ducted rocket motor 补燃室长度对固冲发动机二次燃烧的影响
- Theoretical analysis on effect of direct heating on ground simulation performance for solid ducted rocket motor 直接加热对固冲发动机地面模拟性能影响的理论分析
- solid ducted rocket motor 固体火箭冲压发动机
- solid ducted rocket engine 固体火箭冲压发动机
- Solid ducted rocket (SDR) 固体火箭冲压发动机
- solid ducted rocket 固体火箭冲压发动机
- Mayer A E H J,Stowe R A.Experimental study into mixing in a solid fuel ducted rocket combustion chamber[R].AIAA 2000-3346. 余勇;陈小前;等.;三维实验固体火箭冲压发动机燃烧室湍流反应流数值模拟[J]
- Mayer A E H J,Stowe R A. Experimental Study Into Mixing in a Solid Fuel Ducted Rocket Combustion Chamber[R]. AIAA Paper 2000-3346. 张炜;夏智勋;姜春林;等.;新型非壅塞式固体火箭冲压发动机试验研究[J]
- Stowe R A, Champlain A De, Mayer A E H J. Modeling combustor performance of a ducted rocket[R]. AIAA paper 2000-3728. 张炜;方丁酉;夏智勋;等.;非壅塞固体火箭冲压发动机工作特性研究[J]
- Stowe R A,Champlain A D,Mayer A E H J.Modelling combustor performance of a ducted rocket[R].AIAA 2000-3728. 陈林泉;毛根旺;霍东兴;等.;燃气喷射方式对冲压发动机补燃室掺混效果的影响[J]
- The characterization of the combustion properties of the aluminum? magnesium fuel? rich propellant for unchoked ducted rocket was studied. 系统研究了铝镁贫氧推进剂低压燃烧特性的表征方法。
- In this paper, the researchs on Solid Ducted Ramjet (SDR) inner flowfield with swirling injection were done and the applications of the swirl injection in SDR were explored. 针对固体火箭冲压发动机，本文开展了旋转射流进气对固体火箭冲压发动机内流场影响的研究，探索了旋转射流进气在固体火箭冲压发动机中的应用。
- The effects of TMOs and their mixtures on the burning rate and the pressure exponent of the aluminum magnesium fuel rich propellant for unchoked ducted rocket are investigated. 研究了过渡金属氧化物(TMO)及其复配物对非壅塞固体火箭冲压发动机铝镁贫氧推进剂燃烧特性的影响。
- Flight tests for an integrated ducted rocket were carried out successfully following ground tests in order to investigate the performance of the ducted rocket. 在地面试验基础上进行了整体式固体火箭冲压发动机飞行试验,以验证发动机的工作可靠性和飞行性能。
- In addition, the USAF continues to fund development work of the Aerojet (formerly Atlantic Research) Variable Flow Ducted Rocket ramjet system as a future propulsion option for an extended range AAM. 此外，美国空军继续投资于航空喷气研究所（原来的大西洋研究所）的可变喷流管火箭发动机系统，将其作为增程空空导弹的未来推进选项。
