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The development of controllable flowsolid ducted rocket promote the study on control system of solid ducted rocket.

燃气流量可控的固体火箭冲压发动机促进了其燃气流量控制系统的研究。

As the major direction of the propulsion system for supersonic missile, the ducted rocket has good prospects.

实现补燃室高效率、稳定、可靠的工作,是固体火箭冲压发动机的关键技术问题。

The altitude characteristics, velocity characteristics and throttling characteristics of solid ducted rocket were theoretically studied.

系统地研究了固体火箭冲压发动机的高度特性、速度特性和节流特性。

With connected-pipe test facility, the combustion characteristics of the unchoked ducted rocket were investigated.

采用直连式实验装置系统地研究了非壅塞固体火箭冲压发动机的燃烧特性。

And it can greatly reduce the noise, by reducing the vibration of the mechanical material, and also lessen the attrition rate , this innovation is increasing life span and security of a machiner.

可广泛用于减少高速运动物体与空气间的阻力,如:汽车,火箭,火车,飞机,涡轮机和内燃发动机的设计;并大大降低其产生的噪音,降低金属构件损耗率,增加使用寿命及安全性。

A new type of unchoked solid rocket ramjet system was established.

建立了一种新型非壅塞燃气发生器固体火箭冲压发动机系统。

When the gas generator is loaded by fuel rich propellant with high exponent, the unchoked ducted rocket can almost be worke...

贫氧推进剂的燃速压强指数越高,非壅塞固体火箭冲压发动机燃气流量的自适应调节能力越强。

The burning rates of the GAP/TMO fuel-rich propellants were measured by use of the pipe-connected unchoked ducted rocket testing facility.

采用直联式非壅塞固体火箭冲压发动机法,测定了GAP贫氧推进剂的低压燃速。

Solid ducted rocket ; choked ; unchoked ; operating characteristics

固体火箭冲压发动机;壅塞;非壅塞;工作特性

A type of high-performance fuel-rich propellant for the unchoked ducted rocket has been developed. The burning rates of the fuel-rich propellant are greater then 2mm/s at 0.5MPa, the greatest one is up to 4. 05mm/s. The burning-rate exponent is greater than 0.5, the highest one reaches 0.58. The fuel-rich propellant grain can combust steadily in the gas generator at 0.226MPa. The uniaxial mechanical properties and the processability of the fuel-rich propellant are good.

研制了一类用于非壅塞固体火箭冲压发动机的高性能铝镁贫氧推进剂:0.5MPa下燃速高于2mm/s,最高者达4.05mm/s;燃速压强指数高于0.5,最高者达0.58;直连式实验时,在0.226MPa下燃烧稳定;具有良好的力学性能和工艺性能。

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