确定内部和外部因素对集群推进系统推力分布的影响

S. Dolgopolov
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引用次数: 0

摘要

独立火箭发动机的推力分布是由外部因素(发动机入口推进剂成分的压力和温度)和内部因素(发动机单元和组件的几何形状和操作条件的分布)引起的,可以从实验测试中知道,也可以通过已知的程序计算出来。运载火箭下部液体推进剂推进系统通常由若干台发动机组成,由于台架设备的能力有限,这些发动机的推力分布往往无法通过点火试验确定。本工作的目的是开发一种方法来确定由两个或更多发动机组成的LPPS集群的推力分布。对于多发动机推进系统,该方法还包括建立LPPS中发动机相互作用的数学模型,以及在所有发动机参数分布相同或不同的情况下,计算LPPS在不同外部和内部因素分布组合下的启动情况。针对一种双机共氧化剂进料管道的LPPS,给出了在LPPS启动过程中,计算内外因素对各发动机推力分布和LPPS整体推力分布的影响的实例。结果表明,90%的推力的计算传播(燃烧室压力)时间在于范围- 0.0917 + 0.0792年代(1)引擎和-0.0941 + 0.0618年代的变化计算(2)引擎。燃烧室压力(发动机推力)从其名义价值在于范围-6.2% + 7.0%(引擎1)和-6.8% + 6.3%(发动机2)。90%的利差计算推力时间和牧民联盟作为一个整体的推力是小得多(约40%),时间范围为- 0.0733秒至+0.0457秒,推力范围为- 4.8%至+ 4.8%(约为标称推力)。利用皮尔逊卡方检验,估计了两个发动机和LPPS作为一个整体的90%推力时间扩展和稳定推力扩展的预期理论分布与得到的统计分布的拟合优度。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
Determination of the effect of internal and external factors on the thrust spread of a cluster propulsion system
The thrust spread of a stand-alone rocket engine caused by external (the pressure and temperature of the propellant components at the engine inlet) and internal (spread in the geometry and operating conditions of the engine units and assemblies) factors is known from experimental tests or can be computed by a known procedure. As a rule, liquid-propellant propulsion systems (LPPSs) of launch vehicle lower stages include a cluster of several engines, whose thrust spread cannot often be determined from firing tests due to limited capabilities of bench equipment. The aim of this work is to develop an approach to determining the thrust spread of an LPPS comprising a cluster of two and more engines. For a multiengine propulsion system, this methodological approach also includes the development of a mathematical model of engine interaction in an LPPS and calculations of an LPPS startup at different combinations of spread in the external and internal factors in cases where the parameter spreads of all engines are both identical and different. For an LPPS with two engines and a common oxidizer feed pipeline, the paper gives an example of calculating the effect of external and internal factors on the thrust spread of each engine and the LPPS as a whole during an LPPS startup. . It is shown that the calculated spread of the 90 percent thrust (combustion chamber pressure) time lies in the range – 0.0917 s to +0.0792 s (engine 1) and –0.0941 s to +0.0618 s (engine 2). The calculated variations of the combustion chamber pressure (engine thrust) from its nominal value lie in the range –6.2 percent to +7.0 percent (engine 1) and -6.8 percent to +6.3 percent (engine 2). The calculated spreads of the 90 percent thrust time and the thrust for the LPPS as a whole are far smaller (about by 40 percent) and lie in the range – 0.0733 s to +0.0457 s for the time and – 4.8 percent to +4.8 percent for the thrust (about the nominal thrust). Using Pearson’s chi-squared test, an estimate is obtained for the goodness of fit of the anticipated theoretical distributions of the 90 percent thrust time spread and the steady thrust spread to the obtained statistical ones both for the two engines and for the LPPS as a whole.
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