Performance testing of a resistojet thruster for small satellite applications

Lawrence, Timothy; Sweeting, Martin; Paul, Malcolm; Sellers, Jerry J.; LeDuc, J. R.; Malak, J.; Spanjers, Gregory G.; Spores, Ronald A.; Schilling, John H.

doi:10.2514/6.1998-3933

Cited by 15 publications

(7 citation statements)

References 2 publications

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“…6. The heat transfer efficiency decreased from the Mark-I to the Mark-II thruster, which was verified by conducting a Knudsen number and Reynolds number analysis looking at the nozzle flow conditions [3]. The heat transfer efficiency only reached 12 per cent with an I sp of 84 s (see Fig.…”

Section: Efficiency This Was a Factor Of 2 Higher Than That Formentioning

confidence: 63%

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Low-cost orbit manoeuvres for minisatellites using novel resistojet thrusters

Sweeting

Lawrence

LeDuc

1999

Proceedings of the Institution of Mechanical Engineers, Part G:

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Electric propulsion using resistojets operating at low power ($100 W) and using liquid propellants have re-emerged as attractive propulsion options for small satellites. Compared to low-power pulsed plasma thrusters (PPT), the resistojet achieves 50 times the increase in thrust ($1±50 mN), which is necessary to overcome drag at solar maximum for small satellites in high drag obits ($200 km). Two resistojet thrusters have been developed at the Surrey Space Centre (SSC), which utilize a packed bed of silicon carbide (SiC) particles for the heat exchanger. A thermodynamic model has been developed to study and optimize the thruster design and a series of practical performance tests with both nitrous oxide and water as propellants has been completed at the USAF Research Lab (Edwards AFB) using the NASA-JPL inverted pendulum thrust stand. Endurance tests ($300 h duration) were conducted to determine possible lifetime limitations or failure modes. The results are very encouraging and resistojet thrusters are now proposed as options for future USAF and SSC minisatellite missions. This paper describes the complete resistojet system, test results for the USAF Mighty Sat II. I and its flight performance, its performance and integration on the UoSAT-12 minisatellite and its launch in April 1999 where this novel technique was demonstrated for the first time in low Earth orbit on 26 July 1999.

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Section: Efficiency This Was a Factor Of 2 Higher Than That Formentioning

confidence: 63%

“…This system was chosen due to its density I sp , self-pressurization, ease of handling and performance. More information about UoSAT-12 can be found in reference [3]. Table 6 shows the performance of the UoSAT-12 resistojet system including the mass breakdown and system specifications.…”

Section: Uosat-12mentioning

confidence: 99%

Low-cost orbit manoeuvres for minisatellites using novel resistojet thrusters

Sweeting

Lawrence

LeDuc

1999

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…Clogging may occur, for example, due to oxidation of nozzle material ( Figure 5). 11 Micronozzle blockage occurs by in-flow particles since their size becomes comparable with micronozzle throat diameter. These particles are also responsible for the erosion of nozzle material.…”

Section: F -2n (P E -P a )A Ementioning

confidence: 99%

“…The oxidation of the 316 stainless steel at temperatures about 1000°C caused flaking which gradually clogged the nozzle. Hastelloy (oxidant resistant up to temperatures above 1000°C) was successfully used in the later designs 11. …”

mentioning

confidence: 99%

Specifics of small satellite propulsion. II

Zakirov

Gibbon

Sweeting

et al. 2001

37th Joint Propulsion Conference and Exhibit

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Small space vehicle propulsion is not only a technological challenge of scaling systems down, but also a combination of fundamental physical constraints. Several of these constraints related to small cold-gas, resistojet, and chemical thrusters are discussed in this paper. In particular, the trades of small size nozzle and reaction chamber designs are considered. NOMENCLATUREa -sonic velocity, m/s A c h s , A cs and A e -reaction chamber surface, crosssection, and nozzle exit areas, m 2 c -effective exhaust velocity, m/ŝand d th -chamber and nozzle throat diameters respectively, m F -thrust, N h -heat transfer coefficient, W/m 2 /K H °f-enthalpy of formation, J/mol I sp -specific impulse, s I ^t -minimum impulse bit, mN-s k( T) -heat transfer coefficient, J/m 2 /K 1 L -characteristic body dimension, m l ch and l noz -reaction chamber and nozzle lengths respectively, m m -propellant mass flow rate, kg/s n -number density, number of molecules per unit volume in the gas, #_of_molecules/m 3 p a , p ch and p e -ambient, chamber, and nozzle exit pressure respectively, Pa R = 8.31441 J/mol/K -universal gas constant Q g and £)/,/ -heat generation due to exothermic chemical reaction and heat losses out of the thruster, J Q and Q hl -.rates of heat generation inside and heat loss out of the reaction chamber respectively, W r , r c and r, -radius-vector, nozzle throat and inlet radii of curvature, respectively, m Re -Reynolds number T ch -chamber temperature, K t and t p -time and pulse duration respectively, s u and u e -flow and exit (or exhaust) velocities, m/s u -mean flow velocity, m/s U -maximum flow velocity, m/s V ch -reaction chamber volume, m 3 W-thruster mass, gm x -distance from beginning of boundary-layer, m a-nozzle divergence half-angle, deg. /?-nozzle convergence half-angle, deg. Y -specific heat ratio 1 American Institute of Aeronautics and Astronautics Downloaded by Duke University on September 24, 2012 | http://arc.aiaa.org |

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“…Initially, there was some uncertainty about the launch vehicle which drove the program office to consider a propulsion system to perform the orbit raising. A traditional PPT-based system developed by Primex Aerospace under a NASA contract was initially planned [10], but was later exchanged for a higher thrust system based on a water resistojet (WRT) developed by Surrey Satellite Technologies, LTD [11]. Ultimately, the OSP was selected as the launch vehicle which eliminated the need for a propulsion system, and it was removed from the satellite.…”

Section: Techsat 21 Overviewmentioning

confidence: 99%

A proposed on-orbit demonstration of an advanced pulsed-plasma thruster for small satellite applications

Bromaghim

Spanjers²,

Spores³

et al.

2000 IEEE Aerospace Conference. Proceedings (Cat. No.00TH8484)

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Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing this collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden to Department of Defense, Washington Headquarters Services, Directorate for Information Operations and Reports (0704-0188), 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302. Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to any penalty for failing to comply with a collection of information if it does not display a currently valid OMB control number. PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ADDRESS. . This experiment will demonstrate a high performance PPT, making it a viable thruster for various applications such as orbit raising and initiating and maintaining clusters of small satellites. The experiment will also be the first flight of a new micro-propulsion thruster -a miniaturized version of the PPT, known as the micro-PPT (u-PPT). The u-PPT is ideal for very precise attitude control and pointing, formation flying, and for primary propulsion on microsatellites. A novel on-board diagnostic package will be used to assess the contamination of optical and thermal control surfaces as a result of firing the PPTs. Ground-based observations will also be conducted to assess the on-orbit performance and possible communication impacts of the thruster firings. REPORT DATE

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Performance testing of a resistojet thruster for small satellite applications

Cited by 15 publications

References 2 publications

Low-cost orbit manoeuvres for minisatellites using novel resistojet thrusters

Low-cost orbit manoeuvres for minisatellites using novel resistojet thrusters

Specifics of small satellite propulsion. II

A proposed on-orbit demonstration of an advanced pulsed-plasma thruster for small satellite applications

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