Advanced Flow Control for High Speed Propulsion Systems

高速吸气式推进的研究和发展通常与处于先进推进系统前沿的国家有关。理解和发展这些概念所需的研究往往适用于更广泛的领域。卡尔顿大学最近与日本宇宙航空研究开发机构卡库达空间推进中心合作进行的关于吸气式火箭推进的研究实验表明，交换式进气道概念在显著减少发动机长度方面是有效的，同时比更传统的设计更接近理论最佳值。等离子体致动器已被证明是有效的，在广泛的设备在低速方面修改边界层的延迟或加速分离。然而，它们对内部高速空气动力学的潜在影响是一个开放的研究领域。因此，这两种技术（交换进气道和等离子体致动器）的组合将提供一个独特的机会，通过研究可压缩空气动力学和电磁学之间的关系的基本原则，促进先进的推进技术。类似于超燃冲压发动机推进中的自由基农业概念，等离子体致动器的顺序操作可以产生电离流的口袋。如果实现足够的电离以加速、提取/输入能量或主动引导流动，则可以电磁地操纵这些袋。根据等离子体致动器的设计，可以产生小射流、再循环和涡流以产生小的流动扰动。这些对于需要混合的过程（例如快速燃烧）以及对于当流动遵循壁轮廓时通常最有效地操作的入口和内部流动是有益的。这些扰动的大小和形状可以根据等离子体致动器本身的设计而显着改变，这种影响也将在本研究提案中进行研究。利用我们研究小组目前可用的数值模拟技术，将检查许多流场。时间精确模拟潜在的等离子体致动器的设计将进行研究，并与我们的研究小组收集的实验数据进行比较。这将产生关于如何最好地优化设计以最大化期望的诱导流行为的信息，以及帮助理解结果背后的物理原理。这一建议的成功结果将推进磁流体动力学模拟，等离子体产生和高速流动操纵推进等领域的知识。通过将等离子致动器（目前在国际上正在进行大量的单独研究和开发）纳入一种新的内部火箭技术，将培训一批强大的加拿大研究人员。

The study and development of high speed airbreathing propulsion is generally associated with countries at the forefront of advanced propulsion systems. The research required to understand and develop these concepts often has application to a much wider variety of fields. Recent research conducted at Carleton University in collaboration with the JAXA Kakuda Space Propulsion Center on airbreathing rocket propulsion has experimentally shown that the Exchange Inlet concept is effective at significantly decreasing engine length while behaving closer to the theoretical optimum than more conventional designs. Plasma actuators have been shown to be effective on a wide range of devices at low speeds in terms of modifying boundary layers for the delay or acceleration of separation. However, their potential effect on internal high speed aerodynamics is an open field of research. Therefore, the combination of both of these technologies (Exchange Inlet and plasma actuator) will provide a unique opportunity to contribute to advanced propulsion technologies through studying the fundamental principles that govern the relationship between compressible aerodynamics and electromagnetics. Similar to the concept of radical farming in scramjet propulsion, sequential operation of plasma actuators can create pockets of ionized flow. These pockets can be manipulated electromagnetically if sufficient ionization is achieved to accelerate, extract/input energy, or actively guide the flow. Depending on the design of the plasma actuator, small jets, recirculation, and swirl can be generated to create small flow perturbations. These can be beneficial to processes which require mixing (such as rapid combustion) and also to inlet and internal flows which generally operate most effectively when the flow follows the wall contour. The magnitude and shape of these perturbations can be changed significantly depending on the design of the plasma actuator itself, an effect that will also be studied in this research proposal. Using numerical simulation techniques currently available in our research group, numerous flowfields will be examined. Time accurate simulations of potential plasma actuator designs will be studied and compared to experimental data collected by our research group. This will yield information on how best to optimize the design to maximize the desired induced flow behavior as well as help understand the physical principles underlying the results. A successful outcome of this proposal will advance knowledge in the areas magnetohydrodynamic simulation, plasma generation, and high speed flow manipulation for propulsion. Through the incorporation plasma actuators (which in isolation are currently under considerable research and development internationally) into a novel, in house, rocket technology, a strong body of Canadian researchers will be trained.