Optimization of flow properties of hypergolic fuels for hybrid propulsion systems

混合动力推进系统自燃燃料流动特性的优化

• 批准号: 521741-2017
• 负责人: Dubois, Charles
• 金额: $ 1.82万
• 依托单位: École Polytechnique de Montréal
• 依托单位国家: 加拿大
• 项目类别: Engage Grants Program
• 财政年份: 2017
• 资助国家: 加拿大
• 起止时间: 2017-01-01 至 2018-12-31
• 项目状态: 已结题
• 来源: https://www.nserc-crsng.gc.ca/ase-oro/Details-Detailles_eng.asp?id=639456
• 关键词: Optimization; flow; properties; hypergolic; fuels

Access to space and suborbital flights are of critical importance to a broad range of fields of science andindustry. The emergence of new technologies has allowed new actors to develop smaller and morecost-effective satellites to perform the same missions. However, due to the lack of operational dedicatedlaunchers, microsatellites are often constrained to launch as secondary payloads alongside larger satellites.Chemical propulsion in the aerospace sector is currently dominated by two rocket design paradigms,differentiated by the phases of the reactants used, solid in one case and either liquid of gaseous in the other.Our partner Reaction Dynamics Lab has been pioneering a novel type of rocket propulsion technology,experimentally demonstrated recently using a static fire test. Hybrid rocket engines, where liquid or gaseousoxidizer are stored separately from the solid fuel, can bring key advantages with regards to safety withoutcompromising performance. When solid fuels rubbers are used for the fuel matrix in hybrid rocket motors, theregression rate is very low compared to solid rockets. This drawback has been partially addressed by theintroduction of the concept of liquefying solid fuels matrix. It is anticipated that the combustion efficiency ofthese motord will depend on the flow properties of the melted fuel, but the characteristics of this relationshipremained to be identified. The investigation that will be supported by this grant is aimed at identifying theeffects of the melted fuel rheological properties on the combustion efficiency of hybrid rocket motors.

进入太空和亚轨道飞行对于科学和工业的广泛领域至关重要。新技术的出现使得新参与者能够开发更小、更具成本效益的卫星来执行相同的任务。然而，由于缺乏可操作的专用发射器，微型卫星通常只能作为辅助有效载荷与较大的卫星一起发射。航空航天领域的化学推进目前由两种火箭设计范式主导，这两种设计范式根据所使用的反应物的相进行区分，一种是固体，另一种是液体或气态。我们的合作伙伴反应动力学实验室一直在开创一种新型的火箭推进装置 最近使用静态火灾测试进行了实验证明。混合火箭发动机将液体或气体氧化剂与固体燃料分开储存，可以在不影响性能的情况下带来安全方面的关键优势。当固体燃料橡胶用作混合火箭发动机的燃料基质时，与固体火箭相比，回归率非常低。通过引入液化固体燃料基质的概念，部分解决了这个缺点。预计这些发动机的燃烧效率将取决于熔化燃料的流动特性，但这种关系的特征仍有待确定。这笔赠款将支持的研究旨在确定熔化燃料流变特性对混合火箭发动机燃烧效率的影响。