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首页> 外文期刊>Journal of Aerospace Sciences and Technologies >TRAJECTORY ANALYSIS OF A SOLID FUEL RAMJET PROPELLING AN ARTILLERY SHELL
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TRAJECTORY ANALYSIS OF A SOLID FUEL RAMJET PROPELLING AN ARTILLERY SHELL

机译：推进炮壳的固体燃料拉姆喷射的轨迹分析

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This paper intends to estimate the possible range of a 155 mm artillery shell propelled using a ramjet in a fuel-rich propellant configuration. It also intends to obtain an optimum design of ramjet to maximize the range. A six degree of freedom trajectory simulation was developed to obtain the trajectories of the shell with a ramjet, which dynamically evaluates the off-design performance of the ramjet during the flight. A fuel-rich propellant was taken from literature for evaluating the performance of the ramjet. Various trajectories of shell were obtained at different initial thrusts and A/F ratios and with a constant combustion efficiency of 0.95. Results showed that with a 39-calibre gun, the range enhancement of around 105% compared to the current range of 24 km was obtained with a 155 mm artillery shell without any base bleed unit. This was achieved for the ramjet providing thrust equal to 1.2 times the drag at sea level with an initial A/F ratio of 11.
机译：本文旨在估计在富含燃料推进剂配置中使用拉米特推进的155毫米炮弹的可能范围。它还打算获得Ramjet的最佳设计，以最大化范围。开发了六程度的自由轨迹模拟，以获得带拉动喷嘴的壳体的轨迹，动态评估了在飞行期间的拉姆喷嘴的偏移设计性能。从文献中取出一种富含燃料的推进剂，用于评估Ramjet的性能。在不同的初始推力和A / F比率下获得各种壳体轨迹，恒定的燃烧效率为0.95。结果表明，用39级口径枪，与电流范围为24km的速度增强，155毫米炮弹，没有任何碱基出漏装置。这是为了将推力提供等于1.2倍的地海平面的初始A / F比率为11。

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