不同尺度双组分低推力喷气发动机系统运行的数学模型

Yu.V. Knyshenko, V. Durachenko
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摘要

本文采用统一的管道离散化方法,在考虑氧化剂和燃料中不同声速的情况下,利用推进剂管道系统特性数值方法对双组分低推力喷气发动机系统的综合数学模型进行了修正。本文提出了一种统一的方法来数值实现燃料成分和规则的计算截面(内部的结构截面具有恒定的几何和弹性参数)和终端截面的特性方法在管道系统的进口,截面接头,和发动机进口的每个推进剂成分。该方法考虑了推进剂喷射器和电动推进剂阀的水力阻力以及发动机燃烧室的实际压力。通过不同比例的低推力发动机系统的预设计,控制航天器相对于质心的俯仰、偏航和滚转运动,并将航天器转移到新的轨道(更高或更低)进行机动和与另一个航天器对接的实例,说明了数学模型的性能。计算结果表明,在瞬态条件下确定系统关键水力和气动力参数是可能的:以所有或部分发动机在稳定(连续)和非定常脉冲运行中改变推进剂流管流动面积为例,分析了各发动机进气道压力和推进剂组分流量分布,各发动机燃烧室压力和推力特性,以及各发动机对其推力特性的相互影响。所提出的数学模型可用于设计参数和操作条件的计算论证,以编制提案草案或用于发动机系统配置的预先设计确定。关于发动机系统的液压和气体动力性能参数的详细信息是对单发动机和发动机系统在模拟飞行环境条件下的地面试验结果的重要补充。
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Mathematical model of the operation of a different-scale two-component low-thrust jet engine system
The aim of this work is to modify a comprehensive mathematical model of a system of two-component low-thrust jet engines using the numerical method of characteristics in the propellant pipeline system with account for different sound speeds in the oxidizer and the fuel employing a unified method of pipeline discretization. This paper presents a unified approach to a numerical implementation of the method of characteristics for both fuel components and for regular computational cross-sections (internal for structural sections with constant geometrical and elastic parameters) and terminal cross-sections at the pipeline system inlets, the section joints, and the engine inlets for each propellant components. The approach accounts for the hydraulic resistances of the propellant injectors and electric propellant valves and the actual pressures in the engine combustion chambers. The performance of the mathematical model is illustrated by the example of the predesigning of a system of different-scale low-thrust engines to control the motion of a spacecraft relative to its center of mass in pitch, yaw, and roll and transfer the spacecraft to a new orbit (higher of lower) for maneuvering and docking with another spacecraft. The computed results show the possibility of determining the key hydraulic and gas-dynamic parameters of the system in transient conditions: the pressure and propellant component flow rate distribution at the inlet of any of the engines, the combustion chamber pressure and thrust characteristics of each engine, and the mutual effect of the engines on their thrust characteristics by the example of varying the flow areas of the propellant manifolds in the steady (continuous) and unsteady pulsed operation of all engines or some of them. The proposed mathematical model may be used in the computational justification of design parameters and operating conditions in the preparation of a draft proposal or in the predesign determination of an engine system configuration. Detailed information on the hydraulic and gas-dynamic performance parameters of an engine system is an important complement to the results of a ground tryout of both single engines and an engine system in conditions that simulate the flight environment.
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