Overview of thermal arcjet thruster development

Abstract

Purpose This paper aims to provide an overview of current and historical arcjet development. The reviewed arcjets are considered with respect to both design and thruster relevant parameters. Correspondingly, the paper enables the identification of adequate design criteria and of the probable thruster parameters. Design/methodology/approach The approach consists of a database for thruster relevant parameters in conjunction with relevant operational requirements (such as type of propellant) and specific design criteria (such as e.g. propellant injection systems). Findings The synopsis of both operational parameter and respectively assigned design allows for the derivation of development approaches for arcjets under given high level requirements such as power regime. Research limitations/implications The paper is a general review. However, its strength is in the synthesis of the arcjet classification, the functional evidence of design criteria and the application scenario. Practical implications Not only basic but also specific design criteria are analyzed and evaluated leading to a recommendation feature of the paper with respect to the overall design of adequate arcjets. Social implications Within the scope of the Clean Space initiative, new applications and scenarios from the operation of arcjets arise enabling EOL phases of spacecraft that fulfill respective levels of debris mitigation and, in addition, the requirements concerning the adequately adapted re-entry of spacecrafts that are at end of life. Originality/value The paper is a general review. However, its strength is in the synthesis of the arcjet classification, the functional evidence of design criteria and the application scenario.

A Comprehensive Review of Atmosphere-Breathing Electric Propulsion Systems

“…For Arcjet, it uses a combination of a heat exchanger connected to a resistive heater element to heat up the propellant. According to the research of Wollenhaupt et al [13], Arcjet requires a power between 0.3 and 100 kW generating thrust between 200 and 7000 mN with a higher I sp between 200 and 2000 s. For instance, an Arcjet thruster developed by the University of Stuttgart [14,15] uses hydrazine and ammonia as propellants with a thrust of 100-500 mN. In addition, the energy sources of the electrothermal thruster include solar energy, laser, and microwave thermal energy, which are transmitted and concentrated in the heat exchanger or propellant itself, so as to heat it and spray it out.…”

An automated system analysis and design tool for spacecrafts

“…Constraining the permitted c e domain to realistic values allows generating another optimal and more realistic solution. The ATOS thruster of the IRS with an effective exhaust velocity of c e = 6200 m s is used as a realistic reference [120], which will produce the solution for ammonia, orbit transfer concept B, and a thrust of F = 0.1 N and electric propulsion system mass fraction of EP = 0.1380.…”

Electric Propulsion Methods for Small Satellites: A Review

“…The arc is ignited by a high voltage, usually 1000-4000 V and then dips to either a low operating mode, 30-50 V or a high voltage operating mode, 80-160 V. Arcjets typically have four power levels ranging from very low, 100-300 W to high power, 30-200 kW. The most suitable power range for smallsats is at the lower end of the power scale, within the 100 W-1 kW range arcjets, as shown in the top right of (a) in Figure 7 [74]. Since the arc can generate significantly higher temperatures in comparison to a heating coil, the specific impulse is usually greater than that of a resistojet and while similar to chemical thrusters, the arcjets also usually have 2-3 times higher specific impulses than chemical rockets [75].…”

“…In comparison to electrospray thrusters, where lowering the propellant flow rate was shown to improve lifetime, as mentioned in Section 3.1. Another disadvantage of lowering the propellant flow for arcjets is that it reduces the specific impulse due to friction losses on the inner nozzle core [74]. Therefore, it should be noted that propellant flow rate is highly dependent on the chosen system.…”