离子液体电喷微推力器系统设计及性能初步研究

In order to study the effects of emission voltage and flow rate on the performance of ionic liquid electrospray micro-thruster, a type of active supply ionic liquid electrospray micro-thruster was designed. The propellant supply system, vacuum system and time of flight (TOF) test system were established. Firstly, the flow rate of the propellant supply system was calibrated, and then time of flight method was used to test the thruster under various conditions of flow rate and emission voltage. Lastly, the basic performances of the thruster were obtained based on the time of flight curves. Experiments show that the thruster can alternately work in positive and negative modes under vacuum environment. The flow rate range of the propellant supply system and the effects of the emission voltage and flow rate on the performance of the thruster are obtained. The results show that the flow rate range of the propellant supply system is 100nL/s~500nL/s. The emission current increases with the increase of the emission voltage and flow rate, and it is more significantly affected by the emission voltage. The thrust of the thruster is greatly influenced by the emission voltage while and specific impulse is more influenced by the flow rate. Under the experimental conditions, the thrust range of the thruster is 112μN~183μN, the specific impulse range is 250s~315s, and the efficiency is 77%~90%, which indicates that the thruster is in colloid emission mode.