Orbital Performance Measurements of Air Force Electric Propulsion Space Experiment Ammonia Arcjet

Fife, J. M.; Bromaghim, D. R.; Chart, D. A.; Hoskins, W. Andrew; Vaughan, C. E.; Johnson, L. K.

doi:10.2514/2.6028

Cited by 6 publications

(3 citation statements)

References 10 publications

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“…The mass ow rate for the remaining rings was increased,however, because the arcjet power appeared higher than the nominal 26 kW. Later analysis indicated this was not the case, as discussed by Fife et al 14 Figure 2 shows a typical operational data set for a ring, in this case from ring F-4 on 23 March 1999. As shown in Fig.…”

Section: Phase II Operationsmentioning

confidence: 95%

Review of the Electric Propulsion Space Experiment (ESEX) Program

Bromaghim¹,

LeDuc²,

Salasovich³

et al. 2002

Journal of Propulsion and Power

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Section: Phase II Operationsmentioning

confidence: 95%

Review of the Electric Propulsion Space Experiment (ESEX) Program

Bromaghim¹,

LeDuc²,

Salasovich³

et al. 2002

Journal of Propulsion and Power

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“…The arcjet itself also reaches thermal equilibrium in that period. 8 Therefore, the lack of thermal equilibrium in the radiometer signal is attributable soley to the 15-min response time of the sensor, rather than a nonequilibrium thermal emission from the arcjet source.…”

Section: Flight Datamentioning

confidence: 98%

Radiometric Analysis from the 26-Kilowatt Electric Propulsion Space Experiment Flight

Spanjers

Schilling

Bromaghim

et al. 2002

Journal of Propulsion and Power

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The U.S. Air Force Research Laboratory's Electric Propulsion Space Experiment (ESEX) was launched and operated in early 1999 to demonstrate the compatibility and readiness of a 30-kW class ammonia arcjet for satellite propulsion applications. As part of this ight, an array of onboard contamination sensors was used to assess the effect of the arcjet and other environments on the spacecraft. The sensors consisted of microbalances to measure material deposition, radiometers to assess material degradation due to thermal radiation or contamination, and solar cell segments to investigate solar array degradation. Over eight rings of the ESEX arcjet, and 33 min, 26 s operating time, the radiometer near the thruster, viewing the arcjet plume and body, experiences a change in the thermal properties of its coating from the rings. Radiometers with no view of the arcjet, or a view of only the plume, show no change. In general, degradation effects are observed only on sensors near the thruster exhaust nozzle, a location unlikely to be used in an operational high-power electric propulsion system. No degradation effects are observed in the backplane of the thruster. For future programs, although engineering measures may be needed for spacecraft equipment in the immediate vicinity of the thruster body, the arcjet environment is generally benign. Nomenclature A= area, m 2 C P = speci c heat, J/kg k = thermal conductivity, W/m ¢ K m = mass, kg . Q in = heat ux into sensor, W . Q rad = radiative heat ux, W . Q T = heat ux conducted down radiometer stem, W . Q 12 = radiative heat within radiometer body, W T = temperature, K

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“…These make the arcjet thruster one of the most practical technologies for north-south station-keeping of communication satellites [1]. Research efforts on the performance of arcjet thruster and related physics are continuing for developing various special applications of different power levels, propellant types and working situation [2][3][4][5].…”

Section: Introductionmentioning

confidence: 99%

Plume Parameters and Thruster Properties of a Low Power Arcjet

Pan¹,

Meng²,

Huang³

et al. 2010

AIP Conference Proceedings

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Abstract.A low power arcjet-thruster of 1 kW-class with gas mixture of H 2 -N 2 or pure argon as the propellant is fired at a chamber pressure about 10 Pa. The nozzle temperature is detected with an infrared pyrometer; a plate set perpendicular to the plume axis and connected to a force sensor is used to measure the thrust; a probe with a tapered head is used for measuring the impact pressure in the plume flow; and a double-electrostatic probe system is applied to evaluate the electron temperature. Results indicate that the high nozzle temperature could adversely affect the conversion from enthalpy to kinetic energy. The plume flow deviates evidently from the LTE condition, and the rarefied-gas dynamic effect should be considered under the high temperature and low-pressure condition in analyzing the experimental phenomena.

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Orbital Performance Measurements of Air Force Electric Propulsion Space Experiment Ammonia Arcjet

Cited by 6 publications

References 10 publications

Review of the Electric Propulsion Space Experiment (ESEX) Program

Review of the Electric Propulsion Space Experiment (ESEX) Program

Radiometric Analysis from the 26-Kilowatt Electric Propulsion Space Experiment Flight

Plume Parameters and Thruster Properties of a Low Power Arcjet

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