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一、问题的提出火箭主动段主要的噪声环境有两个,一是起飞时的发动机喷流噪声;一是跨音速飞行时的空气动力噪声。由大数定律推断并经实际统计证明,这些噪声是高斯过程,而且是各态历经的。由于我们关心的是典型情况下的噪声,而这时的噪声有足够长的平稳时间,因此尽管在全程飞行中噪声变化较大,我们仍然可以认为火箭遇到的噪声环境是平稳的各态历经的高斯过程。这样的过程只需要二阶中心矩(一阶矩等于零)就可以完全描述。用这一个统计量作为载荷,
First, the issue put forward rocket active segment of the main noise environment has two, one is the jet engine noise when taking off; First, transonic aerodynamic noise when flying. Inferred by the law of large numbers and the actual statistics show that these noise is a Gaussian process, but also the various states after. Since we are concerned with typical noise and the noise has a sufficiently long settling time, we can still assume that the noise environment experienced by the rocket is stationary despite the large variations in noise throughout the flight Gaussian process. Such a process requires only a second-order central moment (the first moment equals zero) to be completely described. Use this statistic as the load,