空天飞行器的经济性和载荷需求对推进系统提出了高性能、宽空域、宽速域和多模态工作等苛刻要求，爆震推进正是适合的新型燃烧和热力循环方式。针对可能用于空天推进的多种形式的爆震燃烧，包括顺流和逆流传播的脉冲爆震、驻定斜爆震、连续旋转爆震、微尺度的爆震燃烧波，围绕“短距起爆与自持机理”这一核心科学问题开展研究，特点是考虑发动机应用的实际情况，如宽速域来流、受限空间、非理想传播等，掌握宽速域来流和多尺度受限空间内各型爆震形成、演化、稳定及熄灭机理，提出适合空天动力应用的可靠短距起爆准则和自持稳定传播极限；基于系统总能量守恒提出爆震燃烧的能量高效利用方法，从能量释放/损失理论角度建立各型爆震发动机的性能模型；根据各型爆震波的来流、工作及出口条件探索模态转换规律与调控方法。力求建立统一的爆震推进的理论体系，为新型空天推进方式的问世奠定理论和技术基础。

In order to meet the increasing demands for high efficiency and payload for aerospace vehicles, advanced propulsion systems are required to possess high propulsion performance in their wide working ranges with multi-mode operation. Detonation-based propulsions have the potential to attain the goal because of their considerably high energy release rate and thermal cycle efficiency. According to different initial and operating conditions, detonations that could be potentially utilized for aerospace propulsion can be divided into various types. And, the present project aims to carry out a systematic investigation on how to initiate these detonations efficiently within a shortest Deflagration-to-Detonation Transition (DDT) distance and how to propagate self-sustained effectively. When tackling this critical, core scientific problem, the real factors which are related with the practical detonation-based engines, such as the incoming flows with wide speed range, the confined space for detonations to evolve, and the non-ideal propagation of detonations will be taken into account. By investigating the formation, evolution and quenching mechanisms of these detonations in the combustor flows, the criteria for the effective initiation of detonations in a short distance and the limit range for the self-sustained, steady propagation of detonations will be proposed in this work. Based on the universal principle of total energy conservation, a high efficient approach of utilizing the energy will be obtained. Also, the models to estimate the propulsion performance of detonation-based engines will be established by examining the energy release competing with various losses. Finally, in terms of the incoming flow, the operation, and output conditions, the transition process between different modes of detonations will be revealed and its corresponding control scheme will be proposed. The ultimate goal of this project is to establish a systematic set of theories and guidelines that could be universally applied to detonation-based propulsion designs, thereby laying solid theoretical and technical foundations for the birth of novel aerospace propulsion engines.