Detonation Propulsion (Submission Deadline: May 31, 2026)
爆轰推进技术
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Co-chairs: |
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| Bo Zhang |
Ke Wang |
Yuejin Zhu |
| Shanghai Jiao Tong University, China |
Northwestern Polytechnical University, China |
Jiangsu University, China |
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| Topics: |
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- Rotating Detonation Engine (旋转爆轰发动机)
- Oblique Detonation Engine (斜爆轰发动机)
- Detonation Propulsion (爆轰推进)
- Detonation Wave Initiation (爆轰波起爆)
- Detonation Wave Propagation (爆轰波传播)
- Non-Ideal Detonation Wave (非理想爆轰波)
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| Summary: |
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- Detonation propulsion, based on near-constant-volume combustion, offers significantly higher thermal efficiency than conventional constant-pressure combustion. It is regarded as a disruptive propulsion technology for hypersonic flight, space access, and low-cost space transportation, holding major strategic significance for enhancing vehicle performance and integrated propulsion system metrics. This sub-forum targets researchers, engineers, and graduate students in propulsion theory, combustion diagnostics, engine design, and hypersonic vehicle systems. It aims to systematically exchange knowledge on detonation initiation and stabilization mechanisms, rotating/oblique detonation engine design methodologies, experimental testing techniques, and engineering bottlenecks, fostering interdisciplinary collaboration and accelerating the transition from fundamental research to engineering application.
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- 爆轰推进基于近等容燃烧，热效率显著高于传统等压燃烧，被视为实现高超声速飞行、天地往返及低成本航天运输的颠覆性动力技术，对提升飞行器性能与推进系统综合指标具有重大战略意义。本分论坛面向从事推进理论、燃烧诊断、发动机设计和高超声速飞行器总体研究的科研人员、工程师及研究生，旨在系统交流爆轰起爆与稳定机理、旋转/斜爆轰发动机设计方法、试验测试技术及工程化瓶颈，促进跨学科协同创新，加速该技术从基础研究向工程应用转化。
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