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为了研究与试验整体式液体燃料冲压发动机技术,根据一项连续的海军/沃特ALVRJ/STM试验计划进行了六次十分成功的飞行试验(实际进行了五次一译者注)。本文将要讨论ALRVJ飞行器外形结构、研制、试验与五次飞行试验的情况。试验飞行器在飞行中四个进气道和尾翼的方位呈×形,飞行器采用外侧滑一转弯控制。在风洞试验中,用一个比例为1:3的风洞试验模型研究了它的气动特性。试验内容包括亚音速/跨音速/超音速和高试验雷诺数。进气道明显地影响着它的空气动力特性。为了对飞行特性和飞行弹道进行良好的予测,在飞行试验前,按详细的予测程序对其气动外形、推进系统、自动驾驶仪和控制特性进行了模拟试验。
In order to research and test the monolithic liquid-fuel ramjet technology, six very successful flight tests (in fact, five times a translator’s note) were conducted according to a continuous Navy / Waters ALVRJ / STM pilot program. This article will discuss the ALRVJ aircraft configuration, development, testing and five flight tests. The experimental aircraft in flight four intake and tail of the azimuth was X shape, the aircraft uses a sliding outside the corner control. In the wind tunnel test, a 1: 3 wind tunnel test model was used to study its aerodynamic characteristics. Tests include subsonic / transonic / supersonic and high experimental Reynolds numbers. The air intake significantly affects its aerodynamic properties. In order to make good predictions of flight characteristics and flight trajectory, the aerodynamic shape, propulsion system, autopilot and control characteristics were tested in a detailed predictive manner prior to the flight test.