РАЗРАБОТКА СТЕНДА ИЗМЕРЕНИЯ ТЯГИ НА ОСНОВЕ АЭРОДИНАМИЧЕСКОГО МЕТОДА ДЛЯ ЭЛЕКТРОРАКЕТНЫХ ДВИГАТЕЛЕЙ МАЛЫХ КОСМИЧЕСКИХ АППАРАТОВ

Abstract

A traction measurement stand based on the aerodynamic method has been developed. To test the stand, a prototype electric rocket engine was used as a cold gas engine. The working medium was nitrogen gas. At a flow rate of 1.2 mg/s, the thrust value was from 0.674 to 0.736 mN, at a flow rate of 1.7 mg/s, the thrust value was 0.934-1 mN and at a flow rate of 2.6 mg/s, the thrust value was from 1.59 to 1.634 mN. The experimental specific thrust impulse was at a flow rate of 1.2 mg/s from 574 to 613 m/s, at a flow rate of 1.7 mg/s from 549 to 588 m/s and at a flow rate of 2.6 mg/s from 612 to 623 m/s. According to the measured pressure values in the chamber of the prototype electric rocket engine, the values of the ideal flow rate of the working fluid from the nozzle were obtained, which amounted to 661 m/s at a flow rate of 1.2 mg/s, 667 m/s at a flow rate of 1.7 mg/s and 674 m/s at a flow rate of 2.6 mg/s. The obtained values of the specific thrust impulse do not contradict the previously obtained experimental data on cold gas jet engines using nitrogen as the working fluid, and also do not exceed the ideal design flow rate