A combined detonation engine, aircraft and combined detonation method

CN116104665BActive Publication Date: 2026-07-07BEIJING POWER MACHINERY INST +1

Patent Information

Authority / Receiving Office: CN · China
Patent Type: Patents(China)
Current Assignee / Owner: BEIJING POWER MACHINERY INST
Filing Date: 2021-11-09
Publication Date: 2026-07-07

AI Technical Summary

Technical Problem

Existing combined detonation engines have difficulty achieving stable transitions between rotating detonation and oblique detonation combustion modes under transition conditions, resulting in complex structures, large sizes, low thrust-to-weight ratios, and difficulty in achieving ultra-wide-range flight.

Method used

The system employs an annular flow channel composed of an inner column and an outer shell. An adjustable boss structure is provided on the inner column. By adjusting the inclination angle of the adjustable stage structure, the conversion between the rotating detonation combustion mode and the oblique detonation combustion mode can be achieved. The adjustable boss structure is used to induce detonation and stationary oblique detonation waves at different Mach numbers.

Benefits of technology

It enables the engine to fly in an ultra-wide range of Ma2.5 to Ma15+. The compact combustion chamber structure reduces friction loss and thermal protection difficulty, ensures stable operation of two combustion modes, and improves payload.

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Figure CN116104665B_ABST

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Abstract

This invention proposes a combined detonation engine, aircraft, and combined detonation method. An adjustable boss structure is provided on the inner column, consisting of at least two adjustable graded structures. The length of each adjustable graded structure increases sequentially along the incoming flow direction. The tilt angles of each adjustable graded structure are consistent in the rotating detonation combustion mode. When the Mach number increases to the second Mach number, the tilt angles of each adjustable graded structure are adjusted so that they decrease sequentially along the incoming flow direction. The adjustable boss structure induces initiation of oblique detonation, and the engine transitions from the rotating detonation combustion mode to the oblique detonation combustion mode. In the oblique detonation combustion mode, the tilt angles of each adjustable graded structure decrease sequentially along the incoming flow direction. This invention utilizes the unique advantages of detonation combustion, combining rotating and oblique detonation modes, to significantly widen the engine's speed and airspace range, shorten engine size, and significantly increase engine payload, achieving ultra-wide-range flight coverage (Ma2.5–15+).

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