Abstract: For the 5W μ-PPT electric propulsion system used in AX-3 12U standard cubic satellite， the pulsed plasma thruster unit， ignition system and energy storage and supply system were studied. Through research， an systematic optimization design were obtained， including: micro integrated design of narrow space thruster in 1U volume with one orbit controlled nozzle and two attitude control nozzles， high reliability and long life design of ignition system based on design of resonant boost ignition circuit and energy storage system based on constant power charging topology with Litz wire as energy transmission wire. Based on this research and combined with the mission requirements， the μ-PPT electric propulsion system product was developed， and performance tests， environmental tests， and life test validation studies were also performed. The test results show that under the condition of system power less than 5W and system weight no more than 2kg， the performance parameters of impulse-bit 40μN·s， specific impulse 600s and total impulse greater than 60N·s are achieved. These parameters can keep almost unchanged after the mechanical and thermal vacuum environmental tests. 2.2 million times of ground 1:1 long-life tests have been completed， verifying that the deviations of performance parameters such as impulse-bit and specific impulse are less than 10% within the life cycle. The parameter performance， durability， and environmental adaptability of the μ-PPT propulsion system all meet the mission requirements.

Key words: Micro pulsed plasma thruster；Standard cubic satellites；High reliability and long life；Test verification

摘要： 为了研究针对翱翔三号12U标准立方星应用的5W级μ-PPT电推进系统技术，分别对推力器、点火系统以及储能供电系统进行了研究，获得了一个轨控喷头和两个姿控喷头在1U体积下的狭小空间推力器微小集成化设计以及点火系统和储能供电系统的高可靠长寿命设计。以此为基础，依据任务分析，完成了μ-PPT电推进系统产品研制，对其进行了性能测试、环境试验以及寿命试验验证研究。试验结果表明:在系统功率小于5W和系统重量不大于2kg情况下，实现了元冲量40μN·s，比冲600s，总冲量大于60N·s的性能参数，并能够在力、热等环境试验后保持性能基本不变，并以飞行状态完成了220万次的地面1:1寿命考核，且寿命周期内的元冲量及比冲等性能参数偏差在10%以内。

关键词: μ-PPT；立方体卫星；高可靠长寿命；试验验证