几何可调燃烧室虽然能够满足超燃发动机对动力性能的需求，但其具有多变量、强耦合的特性，不仅难以针对性地开发高性能控制算法，而且成为阻碍超燃发动机领域发展的难点、痛点问题。为缓解控制器设计与机械耦合之间的矛盾，首先，针对传统的几何可调超燃冲压发动机，重新设计了多点燃料注入机械架构，使得几何可调燃烧室获得了更多的可操作自由度，确保了理论上提升超燃发动机性能的能力。同时，在重构的多点燃料注入模式基础上，提出了一种改进的LSTM/DDPG控制方案，用以解决在超声速燃烧情况下的精准压力分布式控制难题，进而充分发挥出超燃发动机在宽速域、长时间飞行下的潜在性能。仿真结果充分验证了提出方案的有效性，即提出的针对多点燃料注入架构的LSTM/DDPG改进控制方案，能够有效地改善/优化几何可调燃烧室在不同工况下的燃烧性能。最后，通过硬件在环 （HIL） 仿真验证了所提出的控制方法的实用性，在不同扩张比下压力分布均可有效跟随指令控制，实现了宽速域几何可调燃烧室多点压力的高精度控制目标。

Generally， the variable geometry combustor can ensure suitable performance of scramjets. However， its multivariate and strong coupling characteristics make it difficult to develop high-performance control algorithms， and also become an intractable problem hindering the development of the scramjet field. To solve the contradiction between control design and mechanical coupling， this paper firstly proposes a multipoint fuel injection structure for the conventional variable geometry combustor. The newly proposed structure can provide more operable inputs， thereby ensuring a theoretical ability to improve the system performance. On the basis of the multipoint fuel injection structure， a new LSTM/DDPG-based control scheme is proposed to solve the problem of distributed pressure control in the case of supersonic combustion. This scheme can effectively improve the potential performance of the scramjet at wide range velocities and in long flight time. The effectiveness of the proposed scheme is then verified with the simulation results， i.e.， the LSTM/DDPG-based control scheme can significantly optimize the combustion performance of variable geometry combustor under different operating conditions. Finally， the applicability of the proposed scheme is validated on the Hardware-In-the-Loop （HIL） simulation platform， and the pressure distribution can be effectively controlled at different expansion ratios. The high-accuracy control of multipoint pressure distribution at wide range velocities for the variable geometry combustor is shown to be realized.