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这项计划的目的是研究液体和固体燃料整体式火箭冲压发动机进气道用的先进孔盖方案。为了说明每种方案的优缺点,我们将讨论几种设计方案,并给出试验数据。这些孔盖分四类:易碎孔盖、用线性聚能装药割开的孔盖、半消耗性孔盖和挠性薄膜孔盖。在两次全尺寸结构试验中,在模拟从助推器向冲压发动机工作转换的条件下,利用炸药使氧化铝易碎孔盖成功地裂成了碎片。在两次全尺寸模拟转换试验中,为产生一个进气口,利用线性聚能装药成功地割开了母体金属燃烧室壁。由薄钢片制成的,并放在一个模拟孔径上的半消耗性孔盖,经受住了高到4,000磅/英寸~2的压力,这远远超过了目前的要求。使用挠性薄膜孔盖(由给钢丝布盖上固化的氯丁橡胶构成的)的两次试验,造成了孔盖的过早破裂。
The purpose of this program is to study advanced porthole solutions for the inlet of liquid and solid fuel integrated rocket ramjet engines. To illustrate the advantages and disadvantages of each approach, we discuss several design options and give experimental data. There are four types of hole covers: frangible hole covers, hole covers cut with a linear shaped charge, semi-consumable hole covers, and flexible film hole covers. In two full-scale structural tests, the alumina frangible hole cover was successfully broken into pieces using explosives, simulating the transition from booster to ramjet operation. In two full-scale analog conversion tests, the parent metal combustion chamber wall was successfully severed using a linear shaped charge to create an air inlet. The semi-consumable orifice cap, made of thin steel sheet and placed on a simulated aperture, withstands pressures as high as 4,000 psi, far exceeding current requirements. Two tests using a flexible film hole cap (consisting of a neoprene cured with a wire cloth cover) resulted in premature rupture of the hole cap.