Qualification of a pulsed, millinewton class metal plasma thruster for broad mission applications [0.03%]
一种微牛金属等离子体脉冲电推进装置的广泛任务适用性考核研究
John Kent Frankovich,Mahadevan Krishnan,Jonathan Mackey et al.
John Kent Frankovich et al.
In the field of low power (< 100W) electric propulsion, all thruster options demand significant trade-offs between operating parameters, systemic simplicity and scalable cost. With many systems on the market there are concerns with reliabil...
Data-driven analysis of anomalous transport and three-wave-coupling effects in an [Formula: see text] plasma [0.03%]
基于数据驱动的异常输运及三波耦合效应分析
Borja Bayón-Buján,Enrique Bello-Benítez,Jiewei Zhou et al.
Borja Bayón-Buján et al.
The collisionless cross-field electron transport in an E × B plasma configuration, representative of a Hall thruster, is studied using bispectral analysis on the data of a fully-kinetic simulation. The nonlinear, in-phase interaction ...
Richard R Hofer,Jacob B Simmonds,Dan M Goebel et al.
Richard R Hofer et al.
Magnetic shielding technology has extended the operating life of Hall thrusters to timescales enabling them to expand beyond missions in Earth orbit, which typically require less than 10 kh of operation, to deep-space missions requiring 10-...
Celia S Chari,Richard R Hofer,Bryan W McEnerney et al.
Celia S Chari et al.
The performance of an innovative dielectric bimaterial is assessed for use in Hall-effect thrusters. The bimaterial consists of a structural body of graphite with a converted surface layer of hexagonal boron nitride (h-BN). The bimaterial c...
Steven M Arestie,Colleen M Marrese-Reading,Saba Z Shaik
Steven M Arestie
Electrospray thruster ground testing, with well understood facility effects, is of critical importance to qualify the technology for long duration flight missions. While there has been substantial work to understand the beam physics and plu...
Collin Whittaker,Steven Arestie,Colleen Marrese-Reading et al.
Collin Whittaker et al.
A porous conical type electrospray array thruster consisting of 6102 individual emitters is operated at up to 13.3 W power. The design and manufacture of the thruster are described, including its porous glass emitter chip and metallized cer...
Plume divergence characterization for electric propulsion via standard deviation and emittance [0.03%]
通过标准差和发射度对电力推进的羽流发散特性进行表征
McKenna J D Breddan,Richard E Wirz
McKenna J D Breddan
Electric propulsion systems require careful consideration of plume divergence and evolution over a range of operating conditions and environments. Existing means of describing plume divergence such as outlines, plume profiles, and snapshots...
Ion current and energy in the magnetic arch of a cluster of two ECR plasma sources [0.03%]
两个ECR等离子体源聚集体磁拱内的离子电流和能值
C Boyé,J Navarro-Cavallé,M Merino
C Boyé
The feasibility of a novel 'magnetic arch' topology for controlled contactless plasma beam acceleration is experimentally demonstrated using a pair of coaxial electron cyclotron resonance sources with opposing magnetic polarities, such that...
Current pathways model for hall thruster plumes in ground-based vacuum test facilities: measurements and observations [0.03%]
地面真空试验设施霍尔推进器羽流的流动路径模型：测量和观察
David R Jovel,Janice D Cabrera,Mitchell L R Walker
David R Jovel
A previous companion paper introduced a current pathways model that represents the electrical coupling between the Hall effect thruster (HET) and the ground-based vacuum test facility operational environment. In this work, we operated a 7-k...
Multimodal electrospray thruster for small spacecraft: design and experimental characterization [0.03%]
小型航天器的多模电喷雾推进器：设计与实验表征
Peter Mallalieu,Manish Jugroot
Peter Mallalieu
Electrospray thrusters are a promising electric micropropulsion technology which could be used to meet the propulsion needs of nanosatellites, or for fine attitude control of larger spacecraft. Multimodal propulsion is the integration of tw...