Development of xenon collisional radiative model for plasma diagnostics of Hall Effect thrusters

Rajput, Rajendrasing; Khaustova, Aloyna; Loyan, A.V.

doi:10.15587/1729-4061.2017.96649

Cited by 6 publications

(4 citation statements)

References 9 publications

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“…This simple sensor could be an excellent non-intrusive diagnostic of the electron temperature, which is a key health diagnostic for xenon electric thrusters. The development of this sensor has to go hand in hand with the enhancement of collisional-radiative models (CRM), which are presently under development and evaluation at various institutions [16], [17]. The models would be used to obtain thruster plasma properties from the OES measured line intensities.…”

Section: Discussion and Analysismentioning

confidence: 99%

Flight plasma diagnostics for high-power, solar-electric deep-space spacecraft

Johnson

Pich

Conroy

et al. 2018

2018 IEEE Aerospace Conference

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NASA's Asteroid Redirect Robotic Mission (ARRM) mission concept plans included a set of plasma and space environment instruments, the Plasma Diagnostic Package (PDP), to fulfill ARRM requirements for technology extensibility to future missions. The PDP objectives were divided into the classes of 1) Plasma thruster dynamics, 2) Solar array-specific environmental effects, 3) Plasma environmental spacecraft effects, and 4) Energetic particle spacecraft environment. A reference design approach and interface requirements for ARRM's PDP was generated by the PDP team at JPL and GRC. The reference design consisted of redundant single-string avionics located on the ARRM spacecraft bus as well as solar array, driving and processing signals from multiple copies of several types of plasma, effects, and environments sensors distributed over the spacecraft and array. The reference design sensor types were derived in part from sensors previously developed for USAF Research Laboratory (AFRL) plasma effects campaigns such as those aboard TacSat-2 in 2007 and AEHF-2 in 2012.ARRM project leadership also encouraged the PDP team to convene a team of topical subject matter experts from across the country to review and confirm the reference design and to consider effective alternatives and/or enhancements to the reference design. This activity was proposed and accepted as an interactive, informal JPL "A-team" study and a cadre of 25 participants gathered in early 2017 for discussions. The outcome of the two-day A-team study was that the PDP reference design would allow the most important induced-environment unknowns to be measured in the appropriate space environment. Another outcome addressed technology developments of new or improved space plasma environmental sensors. The A-team study concluded that selected developments would lead to improved measurements that could efficiently provide important and otherwise unavailable information about plasma thruster operation in the space environment as well as the plasma induced spacecraft environment. Specifically, the A-team group recommended greater sensor diversity, by inclusion of deployed sensor capabilities in the thruster plume, or by occasional gimbaling of the thruster(s) toward the sensor arrays. The A-team also recommended developing high-speed probes, optical plasma probes, energy selective probes, and direct erosion/deposition sensors, among others; and recommended the inclusion of cameras as well as, since ARRM was to be recovered in cis-lunar orbit by a crewed mission, astronaut assessments of thruster induced environments and collection of sample coupons. pointed out important directions for future flight plasma sensor development. TABLE OF CONTENTSTABLE OF CONTENTS .

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Section: Discussion and Analysismentioning

confidence: 99%

Flight plasma diagnostics for high-power, solar-electric deep-space spacecraft

Johnson

Pich

Conroy

et al. 2018

2018 IEEE Aerospace Conference

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“…The statistical data show that during the time of the cathode block lifetime tests with duration of more than 8000 hours, the emitter volume loss is less than 8%. The predicted emitter lifetime is not less than 15,000 hours [15].…”

Section: The Cathode Lifetime (Ignition Electrode and Emitter)mentioning

confidence: 92%

“…To determine the exact value of the AlI line 396.15 nm, a numerical method of data approximation was used for Gauss's multi-profile profile. The radiation level is also occupied by electrons excited from their ground state 2P 0 1=2 [15].…”

Section: Oes Studies Of the Ht Erosion At Different Operation Modesmentioning

confidence: 99%

Hall Thruster Erosion

Loyan¹,

Khaustova²

2019

Propulsion Systems

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Hall thruster (HT) is one of the thrusters that are systematically applied in space. If to compare HT with plasma ion thrusters, it has lower lifetime and specific impulse. HT has a set of advantages, and that is why interest to this plasma thruster is high. It has relatively simple design and technology of production. HT does not require a complex power supply unit, and it is very important for spacecraft. Propulsion system on the base of HT has lower mass, simpler technology, and less time of production. One of the main HT characteristics that require improvement is the lifetime of thruster. As it is known, one of the main factors that decrease thruster lifetime is the wear of discharge chamber (DCh). With the analysis of demands to HT, it is understandable that the required lifetime is more than 10 years. So the question about lifetime of the HT is still open. This chapter presents the overview of the thruster elements lifetimes and the overview of methods of thruster erosion investigation. It shows advantages and disadvantages of optical methods of DCh erosion rate investigation. Chapter presents modified method of optical investigation. The results of HT research under various modes of operation and results of tests with different ceramic are presented.

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“…Moreover, the saturation process at the discharge voltage V 1 = 150 V can also be observed, as the emission intensity increases with increasing mass flow rates until it reaches a plateau at higher mass flow rates. It is worth noting that OES combined with a collisional-radiative model (CRM) for Xe and Kr can provide information about the electron temperature and density in the plumes of Hall thrusters [34][35][36][37] and cathodes [38,39]. Real-time OES at high acquisition frequencies may be employed for cathode mode transition monitoring and offer insights on changes in plasma properties during the transition from spot to plume and vice versa.…”

Section: Plasma Diagnostics For Electric Propulsion Systemsmentioning

confidence: 99%

A Review of Low-Power Electric Propulsion Research at the Space Propulsion Centre Singapore

et al. 2020

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The age of space electric propulsion arrived and found the space exploration endeavors at a paradigm shift in the context of new space. Mega-constellations of small satellites on low-Earth orbit (LEO) are proposed by many emerging commercial actors. Naturally, the boom in the small satellite market drives the necessity of propulsion systems that are both power and fuel efficient and accommodate small form-factors. Most of the existing electric propulsion technologies have reached the maturity level and can be the prime choices to enable mission versatility for small satellite platforms in Earth orbit and beyond. At the Plasma Sources and Applications Centre/Space Propulsion Centre (PSAC/SPC) Singapore, a continuous effort was dedicated to the development of low-power electric propulsion systems that can meet the small satellites market requirements. This review presents the recent progress in the field of electric propulsion at PSAC/SPC Singapore, from Hall thrusters and thermionic cathodes research to more ambitious devices such as the rotamak-like plasma thruster. On top of that, a review of the existing vacuum facilities and plasma diagnostics used for electric propulsion testing and characterization is included in the present research.

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Development of xenon collisional radiative model for plasma diagnostics of Hall Effect thrusters

Cited by 6 publications

References 9 publications

Flight plasma diagnostics for high-power, solar-electric deep-space spacecraft

Flight plasma diagnostics for high-power, solar-electric deep-space spacecraft

Hall Thruster Erosion

A Review of Low-Power Electric Propulsion Research at the Space Propulsion Centre Singapore

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