Study of Vortex Structures in 3D Unsteady Aerodynamics using Experiment and Simulation

利用实验和仿真研究 3D 非定常空气动力学中的涡结构

• 批准号: 2125927
• 金额: --
• 依托单位: University of Glasgow
• 依托单位国家: 英国
• 项目类别: Studentship
• 财政年份: 2018
• 资助国家: 英国
• 起止时间: 2018 至 无数据
• 项目状态: 已结题
• 来源: https://gtr.ukri.org/projects?ref=studentship-2125927
• 关键词: Study; Vortex; Structures; 3D; Unsteady

With the termination of the Space Shuttle program, the challenge emerges for a successor strategy to take its place. For access to space to be both feasible and affordable, vast leaps forward must be taken in our current understanding of all aspects of aerospace design, not least importantly propulsion systems. This reinvention of our current space access systems has brought about the need for a new concept of spacecraft to be implemented: The single-stage-to-orbit (SSTO) re-usable launch vehicle. They seek to address the high cost of achieving low-earth orbit by removing the need for parts jettisoned during launch, significantly reducing the recurring costs required in their replacement. A key aspect to their success is a propulsion system which operates efficiently across the whole mission profile, from take-off to orbit. One such approach is the combined cycle hybrid engine, which utilizes both air-breathing and rocket modes to achieve low-earth orbit. However, as each propulsive mode has both its benefits and its drawbacks, the engine must be required to effectively transition between modes mid-flight, in order to utilise each mode when most prudent. This requires a high level of complexity in its design to maximise the engines' efficacy in each distinct phase. To date, there has been no successfully operated re-usable launch vehicles (launched from Earth). It is therefore reasonable to concentrate research efforts on the early stage design of these craft and their subsystems. Dr Taylor's recent work in this direction has had a particular emphasis on scramjet engines, with the conception of a novel tool for the initial design and optimisation of both performance and configuration of hybrid engines, with specific consideration for the scramjet mode. This has been conducted alongside investigations into the complicated behaviour of shock patterns generated as a result of the inlet and general assembly of hypersonic engines, with special attention given to their influence on combustion processes.

随着航天飞机计划的终止，接替其代替其继任策略的挑战。为了获得可行且负担得起的空间，必须在我们当前对航空航天设计的各个方面的理解中进行巨大的飞跃，尤其是重要的是推进系统。对我们当前的太空访问系统的这种重新发明使需要实施新的航天器概念：单阶段至轨道（SSTO）可重复使用的发射车。他们试图通过消除发射期间抛弃零件的需求来解决高地轨道的高昂成本，从而大大降低了其更换所需的经常性成本。他们成功的一个关键方面是一个推进系统，该系统在整个任务概况中有效运行，从起飞到轨道。一种方法是合并的循环混合动力发动机，它利用空气呼吸和火箭模式来实现低地球轨道。但是，由于每个推进模式都具有其优势和缺点，因此必须需要发动机才能在飞行中部模式之间有效过渡，以便在最审慎的情况下使用每种模式。这需要其设计的高度复杂性，以最大程度地提高引擎在每个不同阶段的功效。迄今为止，还没有成功操作可重复使用的发射车（从地球发射）。因此，将研究工作集中在这些工艺及其子系统的早期设计上是合理的。泰勒博士在这个方向上的最新工作特别强调了板球发动机，并构思了一种新颖的工具，用于最初设计和优化混合发动机的性能和配置，并对Scramjet模式进行了特定的考虑。这是对高超音速发动机入口和大会产生的冲击模式的复杂行为的研究，并特别注意它们对燃烧过程的影响。