Arcjet rocket

About: Arcjet rocket is a research topic. Over the lifetime, 1121 publications have been published within this topic receiving 9687 citations. The topic is also known as: Arcjet.

Micro-Discharge Micro-Thruster

Abstract: This paper summarizes the experiments and analysis of the micro-discharge micro- thruster developed jointly by Ewing Technology Associates and the University of Washington. The key experimental result has been the demonstration of a sustained discharge in a very simple micro-discharge type of structure (aperture ~ 300 micron) under demanding flow conditions. The micro-discharge provides for power addition to the neutral gas in discharges that transition from relatively high pressure (~ 10 - 30 Torr) to vacuum on the supersonic flow side of the limiting aperture "nozzle" separating the discharge region from the vacuum region. The fact that a fairly stable discharge is maintained on the downstream side suggests that the fairly hot plasma (~ 2 eV) deposits power into the neutral gas (Argon) in a manner that produces a neutral flow of similar energy, much like an arcjet but at very low power (1-5 W). A crude measurement of the power deposition into the gas via an energy balance approach was obtained from thermocouple measurements, which also imply that the gas temperature may be as high as 1-2 eV. Thrust measurements as well as characterization of discharge and plasma properties are an integral part of the current experimental work. Concurrently, a numerical a model is being developed to explain the gas and plasma dynamics involved in the device. A description of the device, the experimental setup as well as results from the experiments will be presented.

Performance Characteristics of a DME Propellant Arcjet Thruster

Abstract: This paper describes the influence of cathode configuration on performance of an arcjet thruster using dimethyl ether (DME) propellant. DME, an ether compound, has suitable characteristics for a space propulsion system; DME is storable in a liquid state without being kept under a high pressure, and requires no sophisticated temperature management such as a cryogenic device. DME can be gasified and liquefied simply by adjusting temperature whereas hydrazine, a conventional propellant, requires an iridium-based particulate catalyst for its gasification. In this study, thrust of a 1-kW class DME arcjet thruster is measured at a discharge current of 13 A, DME mass flow rates ranging 15 to 60 mg/s under three cathode configurations: flat-tip rods of 2 and 4 mm in diam. and 4-mm-diam. rod having a cavity of 2 mm in diameter. Thrust measurements show that thrust is increased with propellant mass flow rate. Among the tested cathodes, the flat-tip rod of 4 mm in diam. with 55 mg/s DME flow rate yielded the highest performance: specific impulse of 330 s, thrust of 0.18 N, discharge power of 1400 W and specific power of 25 MJ/kg.

Design features and experimental researches of an arcjet thruster for small satellite

Abstract: The direction of solution of actual problems of further improvement of the small satellites with propulsion system (PS) by designing arcjet thruster with low power consumption (up to 70 W) and high specific impulse (up to 350 s) was considered on the basis of the research on the maneuvering smallsat with ammonia corrective propulsion system with Electroheat Microthrusters (EHMT). The purpose of the research is confirming technical possibility of designing an arcjet thruster for smallsat with power consumption 60…70 W and specific impulse 300…350 s. In the course of research tasks on determination of construction appearance of a demo sample of No. 2 of arcjet thruster, exploration of its temperature characteristics defining gauge of specific traction impulse of a study of erosion resistance of thruster cathode material at impact of an electric arc are resolved. A constructional scheme of arcjet thruster with visualization of an electric arc is developed, demo arcjet thruster samples are made and experimental arcjet thruster research is conducted in operation on nitrogen, argon. Working fluid temperature in arcjet thruster nozzle behind critical section is reached 1400 K at 68 W, which allows to predict specific impulse value of arcjet thruster in operation on ammonia in 300…350 s. On basis of experimental researches of erosion resistance of arcjet thruster cathode material (tungsten) at impact of an electric arc the necessity of the further research is shown for substantiation of a technical possibility of design arcjet thruster in composition of PS smallsat with required resource of operation. The experimental researches is the continuation of the works in the field of design of EHMT of various construction and represents practical interest during creation of PS for maneuvering smallsat.