Experimental Study on Ignition Reliability of Pulsed Plasma Thrusters

doi:10.13675/j.cnki. tjjs. 190363

Journal of Propulsion Technology ›› 2020, Vol. 41 ›› Issue (1): 205-211.DOI: 10.13675/j.cnki. tjjs. 190363

• Electric Propulsion • Previous Articles Next Articles

Experimental Study on Ignition Reliability of Pulsed Plasma Thrusters

School of Aerospace Engineering,Beijing Institute of Technology,Beijing 100081,China

Online:2020-01-20 Published:2020-01-20

脉冲等离子体推力器点火可靠性试验研究

丁一墁¹,刘向阳¹,黄昕昊¹,LINGYeong Liang¹,武志文¹,谢侃¹,王宁飞¹

北京理工大学宇航学院，北京 100081

作者简介:丁一墁，硕士生，研究领域为脉冲等离子体推力器。E-mail：2120170058@bit.edu.cn
基金资助:
国家自然科学基金（51576018）。

Abstract

Abstract: To determine the relationship between the characteristic parameters of ignition reliability of a pulsed plasma thruster （PPT） and the effects of the discharge energy on these parameters, PPT reliability tests were performed in this study, including two propellants which are traditional polytetrafluoroethylene (PTFE) and PTFE mixed with carbon, respectively. By recording the ignition failure rate and analyzing the discharge delay time, it was possible to determine the PPT ignition reliability with different propellants, providing a new research solution for analyzing PPT ignition reliability. The results show that under different discharge voltages, the variation regularity of the discharge delay time of PPT using PTFE is obviously different with the increase of ignition times. When the discharge voltage is 1kV, the discharge delay time increases from 1μs to 15μs. It obviously increases at the initial stage, and then rises with fluctuation, accompanied by ignition fault. When the discharge voltages are 1250V and 1500V, the discharge delay time fluctuates within 1μs to 5μs, respectively, and no ignition fault occurs. The discharge delay threshold of PTFE mixed with carbon changes exponentially with the discharge voltage.

Key words: Pulsed plasma thruster;Discharge delay time;Ignition reliability;Electric propulsion;Experiment

摘要： 为了得到PPT点火可靠性表征参量的内在联系及放电能量对其影响规律，开展了传统PTFE与掺碳PTFE两种工质的可靠性试验研究，通过记录点火故障率和分析放电延迟时间，得到了不同工质PPT的点火可靠性，为PPT点火可靠性分析提供了新的研究思路。研究结果表明：在不同放电电压下，PTFE工质PPT放电延迟时间随点火次数增加的变化规律明显不同。放电电压为1kV时，放电延迟时间在1μs~15μs内变化，在初始阶段时明显增加，然后在波动中上升，并伴随有点火故障发生；放电电压为1250V和1500V时，放电延迟时间在1μs~5μs之内波动，且没有点火故障发生。两种工质的放电延迟时间均随点火故障率增加呈非线性规律变化，掺碳PTFE的放电延迟阈值与放电电压之间呈指数函数规律变化。

关键词: 脉冲等离子体推力器;放电延迟时间;点火可靠性;电推进;试验

DING Yi-man¹,LIU Xiang-yang¹,HUANG Xin-hao¹,LING Yeong-Liang¹,WU Zhi-wen¹,XIE Kan¹,WANG Ning-fei¹. Experimental Study on Ignition Reliability of Pulsed Plasma Thrusters[J]. Journal of Propulsion Technology, 2020, 41(1): 205-211.

丁一墁,刘向阳,黄昕昊,LINGYeong Liang,武志文,谢侃,王宁飞. 脉冲等离子体推力器点火可靠性试验研究[J]. 推进技术, 2020, 41(1): 205-211.

References

[1] Burton R L , Turchi P J . Pulsed Plasma Thruster[J]. Journal of Propulsion and Power， 1998， 14(5): 716-735.
[2] 吴汉基，蒋远大，张志远 . 电推进技术的应用与发展趋势[J]. 推进技术， 2003， 24(5): 385-392. （WU Han-ji， JIANG Yuan-da， ZHANG Zhi-yuan. Application and Development Trend of Electric Propulsion Technology[J]. Journal of Propulsion Technology， 2003， 24(5): 385-392.）
[3] Antropov N N ， Kazeev M N ， Khodnenko V P ， et al . IONOSFERE Satellite with APPT Based EPS[C]. Washington :the 33rd International Electric Propulsion Conference， 2013.
[4] Kamimura T ， Nishimura Y ， Ikeda T ， et al . R&D and Final Operation of Osaka Institute of Technology 1st PROITERES Nano-Satellite with Electrothermal Pulsed Plasma Thrusters and Development of 2nd and 3rd Satellites [C]. Kobe：34th International Electric Propulsion Conference， 2015.
[5] Tamura K ， Igarashi M ， Kumagai N ， et al . Evaluation of Low Power Pulsed Plasma Thruster for μ-Lab SatⅡ[R]. AIAA 2002-4272.
[6] Ciaralli S ， Coletti M ， Gabriel S B . Performance and Lifetime Testing of a Pulsed Plasma Thruster for Cubesat Applications[J]. Aerospace Science & Technology， 2015， 47: 291-298.
[7] 王尚民，田立成，张天平，等 . 基于12U标准立方体星的μ-PPT电推进系统研制[J]. 推进技术， 2018， 39(12): 2863-2872.
[8] Vondra R J ， Thomassen K I . Performance Improment in Solid Fuel Microthrusters[J]. Journal of Spacecraft and Rockets， 1972， 9(10): 738-742.
[9] Palumbo D J . Solid Propellant Pulsed Propulsion Development for N-S Station Keeping[R]. AIAA 79-2097.
[10] An S M . The Effect of Ignition Energy on Main Discharge Process [C]. Colorado Springs:19th Intrenational Electric Propulsion Conference， 1987.
[11] Brady M E ， Aston G . Pulsed Plasma Thruster Ignitor Plug Ignition Characteristics[J]. Journal of Spacecraft and Rockets， 1983， 20(5): 450-451.
[12] X-Z Feng， H-Ji Wu . Spark Plug for Pulsed Plasma Thruster[C]. Colorado Springs， :19th International Electric Propulsion Conference， 1987.
[13] 侯大立，赵万生，康小明 . 脉冲等离子体推力器火花塞的性能实验[J]. 推进技术， 2007， 28(6): 679-682. （HOU Da-li， ZHAO Wan-sheng， KANG Xiao-ming. Experiment on Spark Plug of Pulsed Plasmathruster[J]. Journal of Propulsion Technology. 2007， 28(6): 679-682.）
[14] Aston G ， Pless L C . Ignitor Plug Operation in a Pulsed Plasma Thruster[J]. Journal of Spacecraft & Rockets， 2015， 19(3): 250-256.
[15] Pottinger S J ， Scharlemann C A . Micro Pulsed Plasma Thruster Development[C]. Florence：30th International Electric Propulsion Conference， 2007.
[16] Keidar M ， Boyd I D ， Antonsen E L ， et al . Optimization Issues for a Micropulsed Plasma Thruster[J]. Journal of Propulsion and Power， 2006， 22(1): 48-55.
[17] Kumagai N ， Sato K ， Tamura K ， et al . Research and Development Status of Low Power Pulsed Plasma Thruster System for μ-Lab Sat II[C]. Toulouse：28th International Electric Propulsion Conference， 2003.
[18] Huang T ， Wu Z ， Liu X ， et al . Study of Breakdown in an Ablative Pulsed Plasma Thruster[J]. Physics of Plasmas， 2015， 22(10).
[19] Wu Z ， Sun G ， Yuan S ， et al . Discharge Reliability in Ablative Pulsed Plasma Thrusters[J]. Acta Astronautica， 2017， 137: 8-14.

Experimental Study on Ignition Reliability of Pulsed Plasma Thrusters

脉冲等离子体推力器点火可靠性试验研究

PDF

Knowledge

Abstract

Cite this article

share this article

References

Related Articles 0

Recommended Articles

Metrics

Comments