**1. Introduction**

With the gradual refinement of the functions of satellite networking and spacebased network information systems, the requirements for the propulsion system necessary for satellite missions are further increased [1–3]. Compared with the traditional chemical propulsion system, the electric propulsion system has the advantages of high specific impulse, lightweight, and long lifespan, so it gradually becomes a better scheme for satellite attitude control, orbit transformation, and drag compensation [1, 3, 4].

Electric thrusters are available in a plethora of types, each boasting unique operating principles and characteristics. Regardless of the specific type employed, however, all electric thrusters must undergo three essential steps: design, trial production, and testing. For the electric thruster, it needs not only the test link to evaluate and verify the function and performance, but also the test link to expose the thruster development issues and seek potential solutions. Therefore, the pre-research, pattern, prototype, and flight application stages of the electric propulsion system development are inextricably linked to the testing and measurement technology, which serves as an indispensable cornerstone of electric propulsion [5, 6].

Unlike chemical and cold air propulsion systems, electric propulsion systems typically require a vacuum environment for ignition testing and operation. Consequently, creating a high vacuum environment artificially becomes necessary during ground testing of electric propulsion. The research on electric propulsion encompasses development, testing, identification, and application, and the testing of electric propulsion systems runs through all aspects of scientific research.

There are numerous topics covered in electric propulsion testing, and some overlap between them, but the purpose of the testing is relatively clear, which can be divided into five categories according to the intended purpose [5, 6]:


Among the above five types of tests, the performance measurement test with micro-thrust and impulse measurement as the core is the main test item of the electric propulsion system. This measurement is an essential measurement link to evaluate the performance of the electric propulsion system and is also an important reference index to measure the stability of the electric propulsion system, which runs through all stages of the spacecraft, such as the single machine level, subsystem level, and the whole star level [7–10].

Combined with the principle, working environment, and thrust level of the electric thruster, the micro-thrust and impulse measurement test for the electric thruster have the following characteristics:

1.Small impulse. At present, the thrust range of commonly used electric thrusters, such as Hall thrusters and ion Hall thrusters, covers from micro-newton to nanonewton, while the impulse element of pulse-working electric thrusters generally ranges from micro-newton to milli-newton. Therefore, the micro-thrust and impulse measurement system needs to capture weak mechanical signals in small

time scales, and the measurement system needs to have high sensitivity, resolution, and anti-interference ability.

