In the study, main components of the multi-cycle two phase pulse detonation engine utilizing liquid gasoline/air mixture are designed carefully, which includes detonation tube, air intake valve-aerovalve, fuel injection device, ignition system and controller etc.

Numerical investigation of multi-tube pulse detonation engine with common nozzle;

Exprimental investigation of integrating pulse detonation engine system;

Experimental investigation of air-breathing valveless pulse detonation engine;

Numerical simulation of the flow field of multicycle pulse detonation engine(PDE) is helpful for understanding the engine principle and performance analysis,and can provide the useful information for PDE design.

To improve the reliability of pressure measurement in detonation combustor of pulse detonation engine(PDE),the pressure/time curves of detonation were measured at single detonation and multicycle detonation,respectively,by using a dynamic pressure measurement system.

The results show that all nozzles can augment the thrust of baseline pulse detonation engine(PDE)and there is an optimal nozzle area ratio where thrust augmentation is maximized.

A new device system was developed to measure the pulsed temperature and vapor concen- tration in the exhaust flow during the multicycle process of pulsed detonation engine.

A pulse detonation engine(PDE) with diameter and length of 61mm and 1140mm respectively,was used to get the heat loads of detonation tubes which were designed into two types.

Numerical simulation of converging-diverging nozzle flow in pulse detonation rocket engine;

Investigation on two-phase pulse detonation rocket engine with solenoid valve;

A pulse detonation rocket engine(PDRE) is a new propulsion system that generates thrust by using high-temperature and high-pressure air produced by pulse detonation waves.