In order to know combustion process of hybrid rocket,pyrolysis test of solid fuel was carried out by using hot-plate heat conduction mode,then chemical kinetic parameters of solid fuel were obtained.

Remarkable advantage such as low costing, high security, high reliability, low exhaust plume signal characteristic and environment non-pollution, which does not belong to Solid Rocket Motor (SRM) or Liquid Rocket Engine (LRE), advances astronautic experts to have much more interest in Hybrid Rocket Motor (HRM).

Investigation on pyrolytic product distribution of low density polyethylene of hybrid rocket motor;

Effects of combustion chamber structure on combustion and flow of hybrid rocket motor;

Research on Working Process of the 85% H_2O_2-PE Hybrid Rocket Motor;

Computation of fuel regression rate in classical hybrid rocket motors;

Experimental study on hydrogen peroxide and polyethylene hybrid rocket motors;

Numerical solutions of full Navier-Stokes equations were obtained for a nozzle two-phase flow of the nitrous oxide(N2O)/hydroxyl-terminated polybutadiene(HTPB) based fuels hybrid rocket motor.