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为了平衡在研制和调试过程中出现的没有予见到情况,在任何宇宙飞船的设计中都留有一定的负载容量或其它特性的储备。随着计划从设计到试样和以后的进展,初始的储量,一般都被用尽。这是因为结构重量的不断增加和发动机装置的特性没有原来予想的那样好。这两种情况在“阿波罗”计划的进展中也出现。 随着初始储量的用完,发动机装置飞行后的仕细分析越来越起着重要的作用。研究发动机装置特性时,更准确的确定是在飞行试验中,比在地面试验要好。这首先是因为能很准确的获得有关加速度的参数,它是用于“阿波罗”宇宙飞船中判断飞行参数的方法中一个基本的参量。此时,发动机的特性是在实际的工作条件下确定的,而有许多条件是不能完全在地面试验时模拟。
In order to balance the unforeseen circumstances that arise during development and commissioning, a reserve of certain load capacity or other characteristics is left in the design of any spacecraft. As planning progresses from design to sample and later, the initial reserves are generally exhausted. This is because the increasing weight of the structure and the characteristics of the engine unit are not as good as originally thought. Both of these conditions have also appeared in the progress of the Apollo project. As the initial reserves run out, detailed analysis of the flying of the engine unit is increasingly playing an important role. When studying the characteristics of engine installations, a more accurate determination is better in flight tests than in ground tests. This is primarily due to the fact that parameters relating to accelerations can be obtained very accurately, which is a basic parameter used in the method of determining flight parameters in the Apollo spacecraft. At this point, the engine characteristics are determined under actual operating conditions, and many conditions are not fully emulated in the ground test.