Exploration And Research On Electrically Controlled Solid Propulsion Technology

Electrically controlled solid propellant is a new type of solid energetic material with special electronically controlled properties,which breaks through the inherent obstacle that conventional solid propellant cannot be extinguished or restarted at will.The propellant can be ignited by a certain current input,and extinguished immediately after the power is cut off.In the combustion process,the burning rate of the propellant can also be adjusted by changing the input current or voltage.In addition,electrically controlled solid propellant has the advantages of insensitiveness,simple preparation,safety and environmental protection.Therefore,electrically controlled solid propellant has the potential to become the next generation propellant widely used in the field of space propulsion.At present,the research on electrically controlled solid propellant and its related technology is still in its infancy at home and abroad.In this paper,the ignition and combustion process of electrically controlled solid propellant under the application of electric energy is preliminarily analyzed through the experiments of electrified ignition and laser ignition.The current density distribution at the end face of the propellant is simulated and analyzed with the propellant as quasi-steady state when it is electrified.The prototype of electrically controlled solid rocket motor is designed,the ignition verification and internal ballistic test are carried out.This paper lays a foundation for the further study on the ignition and combustion process of electrically controlled solid propellant,puts forward a method to improve its injection efficiency,and provides a reference for the structural design and optimization of electrically controlled solid rocket motor in the future.The ignition and combustion process of electrically controlled solid propellant under electric energy was preliminarily analyzed.The electrified ignition process,laser ignition process and flame structure of electrically controlled solid propellant were studied by means of high-speed camera system,electrified ignition system and laser ignition system.Based on the above experimental results,the physical and chemical changes in the ignition and combustion process of electronically controlled solid propellant under the application of electric energy are analyzed.The current density distribution at the end face of the propellant is simulated and analyzed with the propellant as quasi-steady state when it is electrified.The effects of resistivity,insulation layer,electrode spacing and electrode arrangement on the current density distribution at the end surface of electrically controlled solid propellant were investigated.The simulation results show that the current density distribution on the end surface can be more uniform by properly arranging electrodes,which is beneficial to expanding the combustion surface of the propellant and improving the injection efficiency.Meanwhile,the simulation results were verified by experiments.According to the characteristics of electrically controlled solid propellant,a prototype of electrically controlled solid rocket motor with novel structure was designed.The electric control performance of the motor were verified by experiments,and the design goal was achieved.The internal ballistic test of the motor shows that the pressure is about 0.3 MPa at the stable working stage.Combining with the phenomena of the static firing,the working process of the engine is analyzed.