The Key Technology Research Of The High-thrust And Short-duration Individual Rocket Engine

The high-thrust and short-duration individual rocket engine adopts high burningspeed propellant, thin thickness, high packing density and it has been widely applied inthe individual weapon dynamic system. Setting the high-thrust and short-durationindividual rocket engine as the research object, this thesis attempts to solve the keytechnological problems in the engine design from the perspective of theory calculation,design analysis and experimental research, grain design, optimization design of internalballistics, etc. The result can provide important theoretical and technological support forthe engine design and manufacturing.Shape of Ω grain, multiple-tube grain, multiple spoke wagon wheel grain andbeehive grain is analyzed. According to the result, a propellant shape design method isput forward. Based on this method, motor prototype validation experiment is analyzed.Under the condition that the equivalent pressure is adopted to replace the interiorand the exterior pressure in the same section and the erosion combustion effect isignored, a one-dimensional internal ballistic calculation model is put forward.Simultaneity, optimization design of internal ballistics is finished and ddifferentialpressure of inside-and-outside grain is analyzed. Meanwhile, the differential pressure ofthe interior and the exterior of the multiple spoke wagon wheel grain is investigated.Also, a structure integrity calculation is completed under low temperature.To obtain the performance of the crucial components and the integrity, ignitingpowder, ignition device and nozzle breaking pressure etc. are investigated. Dependingon igniting experiment, igniter project is optimized. Also, through the experiment,internal ballistics quality under both high and low temperature is obtained, and thefeasibility and reliability of the engine design are validated.The conclusions achieved in the dissertation will surely promote the application ofthe high-thrust and short-duration individual rocket engine. Therefore, the research willbe of great theoretical value as well as engineering practice meaning for the propulsionof individual weapon research in the future.