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Design Refinement and Modeling Methods for Highly-Integrated Hypersonic Vehicles.

机译:高集成超音速飞行器的设计改进和建模方法。

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摘要

A method for early-stage design of high-speed airplanes is presented based on analysis of vehicle performance, including internal flow in the engine and external flows around the body. Several ways of evaluating vehicle performance are shown, including thrust maps, combustor mode stability concerns, combustor optimization and trajectory optimization.;The design performance analysis relies on a routine that computes the thrust of a dual-mode scramjet, which is a geometric-compression (ramjet) engine with a combustor that can operate both subsonically and supersonically. This strategy applies to any internal flow which is predominantly one-dimensional in character. A reduced-order model for mixing and combustion has been developed that is based on non-dimensional scaling of turbulent jets in crossflow and tabulated flamelet chemistry, and is used in conjunction with conventional conservation equations for quasi one-dimensional flow to compute flowpath performance. Thrust is computed by stream-tube momentum analysis. Vehicle lift and drag are computed using a supersonic panel method, developed separately.;Comparisons to computational fluid dynamics solutions and experimental data were conducted to determine the validity of the combustion modeling approach, and results of these simulations are shown. Computations for both ram-mode and scram-mode operation are compared to experimental results, and predictions are made for flight conditions of a hypersonic vehicle built around the given flowpath. Trajectory performance of the vehicle is estimated using a collocation method to find the required control inputs and fuel consumption. The combustor is optimized for minimum fuel consumption over a short scram trajectory, and the scram-mode trajectory is optimized for minimum fuel consumption over a space-access-type trajectory. A vehicle design and associated optimized trajectory are shown, and general design principles for steady and efficient operation of vehicles of this type are discussed.
机译:在分析车辆性能的基础上,提出了一种高速飞机的早期设计方法,包括发动机内部的流动和车身周围的外部流动。显示了几种评估车辆性能的方法,包括推力图,燃烧室模式稳定性问题,燃烧室优化和轨迹优化。设计性能分析依赖于计算双模超燃冲压发动机推力的例程,这是一种几何压缩(ramjet)发动机,其燃烧器可以进行亚音速和超音速操作。此策略适用于特征主要为一维的任何内部流。已开发出一种基于混流中湍流射流的无量纲缩放和列表式小火焰化学的降阶混合和燃烧模型,并将其与准一维流的常规守恒方程结合使用以计算流路性能。通过流管动量分析计算推力。车辆升力和阻力是通过超声面板方法计算的,是单独开发的;与计算流体动力学解决方案和实验数据进行了比较,以确定燃烧建模方法的有效性,并显示了这些仿真的结果。将用于冲压模式和紧急模式操作的计算结果与实验结果进行比较,并对围绕给定流路建造的高超音速飞行器的飞行条件进行了预测。使用搭配方法估算车辆的轨迹性能,以找到所需的控制输入和燃料消耗。对燃烧器进行了优化,以使其在短Scram轨迹上的耗油量最小,并且对Scram模式的轨迹进行了优化,以在空间进入型轨迹上的耗油量最小。示出了车辆设计和相关的优化轨迹,并且讨论了用于这种类型的车辆的稳定和有效操作的一般设计原理。

著录项

  • 作者

    Torrez, Sean Michael.;

  • 作者单位

    University of Michigan.;

  • 授予单位 University of Michigan.;
  • 学科 Engineering Aerospace.;Engineering Mechanical.
  • 学位 Ph.D.
  • 年度 2012
  • 页码 122 p.
  • 总页数 122
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

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