关键词: 双模态冲压发动机, 性能优化, 宽域运行, 模态设计, 燃烧组织

Abstract:

The flight of airline type space launchers involves a wide range of velocity and altitude with complicated mission profiles by phases. The Dual-Mode Scramjet （DMS） is required to have the capability of efficient operation in a designed profile with a large range of thrust levels， imposing a new challenge. A history overview with related knowledge and understanding of the DMS is provided in this paper， including its background and original intention， and progress in understanding its operation mechanism and performance optimization. The relationship between the thermal-dynamic cycle analysis and wide range performance optimization is discussed. Enlightened by the historical experience， we propose that the challenge could be overcome with systematic optimization to realize wide range mode-control operation with acceptable performance. Operational modes for wide range DMSs need to be designed according to a flight mission to establish a set of design-based wide-range-mode-controlling and controlled-mode-transition technology. As an example， based on conclusions from the equivalent thermal-dynamic process theory， a DMS mode-control concept and future investigation directions are proposed for wide range effective operation. In order to develop wide-range mode control and controllable mode transition technology， two main capabilities need to be developed in the future. One capability is to settle down the inlet/engine matching and the airframe/engine integration issues based on mission constraints quantitatively， and to build an “immediate-demand design” capability for airframe/engine integration. Another capability is to develop controllable combustion organization technology and build an “immediate-demand design” capability for combustion systems.

Key words: Dual-Mode Scramjet (DMS), cycle optimization, wide range operation, mode design, combustion organization