Simultaneous Particle Trajectory and Temperature Diagnosis System for Developing Space Propellants

全球卫星行业正在指数级增加小型卫星的使用，这些卫星提供低功率推力、广角机动性和发现、观测、巡逻和商业任务的价值。姿态控制推进器可以用亚稳态分子间复合材料(MIC)作为一种绿色替代品和一种破坏性、高能量密度和低成本的燃料组件来驱动，以限制在太空轨道上运行的卫星的轴向。要使基于MIC的推进器商业化，需要克服三个障碍：产生可持续的高火焰速度；产生高气体压力；以及将装药密度提高到50%以上的理论最大密度。为了应对这些挑战，温博士和希基博士正在开发新的MIC技术，以改进配方和纳米结构，并重新设计能够利用其独特特性的卫星推进器。我们需要一个同步的颗粒大小、轨迹和温度诊断系统(SPTTD)，以缩小对固体燃料及其产品之间的反应界面的可视化和分析。这项研究对于测试MIC的特性和实现对反应燃料颗粒的反应动力学和热力学状态的直接分析至关重要。如果没有所需的设备，就不可能可视化与颗粒和羽流之间的实际反应界面相关的现象，也不可能获得羽流中注入的铝颗粒的图像和轨迹。PIS开发的新技术将带来突破性的固体推进剂和发动机技术，这些技术可以转移到航天工业。将皮希基的推进器设计和建模与皮文的新颖MIC公式相结合，将使下一代无人机或小型卫星驱动的麦克风的制造成为可能。如果没有所需的SPTTD系统，这是不可能的，该系统将允许申请者和他们的合作者测量对颗粒和设备设计至关重要的具有时间和空间分辨率的同步颗粒轨迹、流速和温度信号。重要的是，准确的实验数据将使数值模型的开发成为可能，这些模型将指导未来的推进器和发动机设计。为了抓住小型卫星制造日益增长的市场机会，加拿大迫切需要促进该部门的研发和HQP培训。所要求的SPTTD系统将满足安大略省南部专门的空间研究设施的需求，并使文博士和希基博士及其HQP和合作者能够进行重要的推进剂评估和推力评估。这对于推动创新走出实验室至关重要，并将促进推进技术突破和知识转移，从而将用于小卫星和无人机姿态控制的新型第四代燃料推进器推向市场。

The global satellite industry is exponentially increasing the use of small satellites, which offer low-power thrusting, wide-angle maneuverability and value for discovery, observation, patrolling and commercial missions. Attitude control thrusters, restraining the orientation of the axis of satellites orbiting in space, can be fueled with metastable intermolecular composites (MICs), which have emerged as a green alternative and a disruptive, high-energy-density, and low-cost fuel component. Three obstacles need to be overcome in order to commercialize MICs based thrusters: producing a sustainable and high flame speed; generating high gas pressure; and increasing charge density above 50% theoretical maximum density. To address these challenges, Dr. Wen and Dr. Hickey are developing novel MIC technologies to improve formulations and nanostructures and redesigning satellite thrusters that can leverage their unique properties. We are requesting a simultaneous particle size, trajectory, and temperature diagnosis system (SPTTD) to scale down visualization and analysis to the reacting interface between the solid fuel and its products. This investigation is essential to test the MICs' characteristics and to enable the direct analysis of reaction kinetics and thermodynamic states of the reacting fuel particles. Without the requested equipment, it is not possible to visualize phenomena associated with the actual reaction interface between the pellet and the plume, nor to acquire the images and trajectory of injected aluminum particles in the plume. The novel technology developed by the PIs will lead to breakthrough solid propellants and engine technologies which is transferrable to the space industry. Combining PI Hickey's thruster design and modeling with PI Wen's novel MIC formulae will enable the manufacture of next-generation drones or small satellites powered MICs. This is impossible without the requested SPTTD system, which will allow the applicants and their collaborators to measure synchronized particle trajectory, flow velocity and temperature singles with temporal and spatial resolutions that are critical for pellet and device design. Importantly, accurate experimental data will enable the development of numerical models that will guide future thruster and engine design. To seize the growing market opportunity in manufacturing small satellites, Canada urgently needs to foster research and development and HQP training in the sector. The requested SPTTD system will fill the need of specialized Space research facility in Southern Ontario and enable Drs. Wen and Hickey, their HQP and collaborators to perform vital propellant assessment and thrust evaluations. This is critical for moving innovation out of the lab and will facilitate propulsion technology breakthroughs and knowledge transfer that will bring new quaternary fuel-based thrusters for attitude control of small satellites and drones to the market.