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本文综述了先进巡航导弹发动机的寿命要求和耐久性试验程序。整个发动机的寿命要求包括两次设计验收试验和一次在热或冷天气中进行的飞行任务要求。从这种发动机工作周期分析中获得的数据编入了发动机技术条件耐久性试验,以便在执行ALCM航程改进计划(ALCM-L)的发动机研制计划时用来对发动机进行论证,初始飞行投放和鉴定试验,从这项研究的特殊结果得知。需要对不同的耐久性试验周期訂出不同的试验要求,这些不同的寿命试验周期代表在热或冷的大气条件下发动机的受热部件所承受的不同应力的情况。在热天气下,要求发动机以大功率起动连续工作,试验重点是发动机的热端部件的应力破坏特性。在冷天气下,要提供更大的可用推力,低的疲劳周期变得更为重要。确定发动机寿命要求和寿命试验周期的基本方法可以应用于任何巡航导弹的发动机试验。然而,文中所用的方法要用于其他的发动机试验时,必须对特定飞行器发动机推力,地形和马赫数进行飞行要求修正模拟。
This article reviews the life requirements and durability testing procedures for advanced cruise missile engines. Lifetime requirements throughout the engine include two design acceptance tests and one mission request in hot or cold weather. Data obtained from this engine duty cycle analysis incorporate engine durability tests to demonstrate engine performance during initial ALCM-L engine development planning, initial flight launch and qualification The experiment, learned from the special results of this study. Different test requirements need to be set for different durability test periods, which represent the different stresses experienced by the heated components of the engine under hot or cold atmospheric conditions. Under hot weather, the engine is required to start continuously at high power. The test focus is on the stress-breaking characteristics of the hot end components of the engine. In cold weather, to provide greater available thrust, low fatigue cycles become even more important. The basic method of determining engine life requirements and life test cycles can be applied to any cruise missile engine test. However, the approach used in this paper, when applied to other engine tests, requires a simulation of the flight requirements revision of engine-specific thrust, topography and Mach number.