Showing papers on "Arcjet rocket published in 2020"

Numerical study of plasma-fluid characteristics and thrust performance of a low-power argon inductively coupled plasma electrothermal thruster

Abstract: Low-power (from the sub-kilowatt range up to a few kilowatts) inductively coupled plasma (ICP) electrothermal thrusters for space propulsion are potential alternatives to low-power arcjet thrusters, which are often implemented on geostationary satellites for north–south station keeping. We develop an axisymmetric two-dimensional magnetohydrodynamic (MHD) numerical simulation technique using a two-temperature plasma model as a computer-aided engineering tool for low-power argon ICP electrothermal thrusters. Furthermore, to the best of our knowledge, this is the first study to provide a basic understanding of the plasma-fluid characteristics of low-power ICP electrothermal thrusters. To this end, we perform the MHD numerical simulation for a low-power argon ICP electrothermal thruster model that was developed for thrust measurement experiments to validate the proposed numerical simulation technique. The numerical results indicate that the plasma flow produced in the low-power argon ICP electrothermal thruster model is basically in a strongly thermal and ionizing nonequililbrium state. In addition, the numerical results show that the experimentally measured thrust forces can be reproduced with an underestimation of 10% or less over the RF input power range of 0–0.6 kW considered in the experiment. Moreover, the numerical results suggest that the main reason why the performance of the low-power argon ICP electrothermal thruster model is significantly lower than the target performance is the considerable heat loss of more than 90% of the input power through the flow-channel wall.

Radiative Transfer in a Low-Density Ablative Material Under Arcjet Flow Conditions

Abstract: Highly porous carbon-based materials, referred to as 120, 150, and 270 kg/m3 materials hereafter, are heated in nitrogen arcjet conditions; and their respective thermal responses are analyzed both...

Extension of the Frozen Sonic Flow Method to mixtures of polyatomic gases

Abstract: A contemporary issue of crucial importance for further developments in the field of thermal protection systems and related arcjet-based testing activities calls for improvements in existing abiliti...

Methods and means of the experimental research of the electrothermal arcjet thrusters of spacecrafts

Abstract: The subject of the research in this article is the measurement of the main characteristics of the electrothermal arcjet thrusters in the process of the working fluid acceleration during the bench tests. The purpose is to form a bench research facility to study the characteristics of the electric heating propulsion system for use in a space tugboat, taking into account the launch dynamics, operating conditions and shutdown dynamics. Tasks: measuring the thrust of the electric propulsion system as the main characteristic in the established and transient mode; determining the flow rate of the working fluid correlated with the thrust; measuring the parameters of electrical consumption ‒ currents, voltage, power in static and dynamic modes; measuring the external conditions of the simulating space environment, namely the vacuum, in the test chamber. The methods used are: tensometry, differential pressure gauge, four-probe measurement of power supplied to engine heaters, steam generator and tank of the electric heating system, ionization-thermocouple vacuum measurement. The following results have been obtained: the composition of the information and control system consisting of the tensometric sensor used with the electric heating propulsion system, flowmeter of the working body of the electric heating propulsion system, power meter of the heater, steam generator and the tank of the electric heating propulsion system, ionization-thermocouple sensors for vacuum determination. The software product for graduation of the tensometric sensor has been developed. The scientific innovation of the obtained results is as follows: the method of measuring the thrust of the electric heating propulsion system by means of tensometric sensor has been further developed, the method of measuring the flow of the working body of the electric heating propulsion system has been further developed, the method of measuring the power of the engine heater, steam generator, tank of the electric heating propulsion system has been further developed. For the first time an algorithm for graduation of the tensometric sensor for the electric heating propulsion system was developed and implemented in the software product.

Preliminary Measurements of the Motion of Arcjet Current Channel Using Inductive Magnetic Probes

Abstract: This paper covers the design and first measurements of non-perturbative, external inductive magnetic diagnostics for arcjet constrictors which can measure the motion of the arc current-channel. These measurements of arc motion are motivated by previous simulations using the ARC Heater Simulator (ARCHeS), which predicted unsteady arc motion due to the magnetic kink instability. Measurements of the kink instability are relevant to characterizing motion of the enthalpy profile of the arcjet, the arcjet operational stability, and electrode damage due to associated arc detachment events. These first measurements indicate $\pm4$ mm oscillations at 0.5-2 kHz of the current profile.

Correcting the Arcjet Thruster Disturbance in GOES‐16 Magnetometer Data

Abstract: The GOES‐R series magnetometers provide observations of the Earth's magnetic field at geostationary orbit for operational use by National Oceanic and Atmospheric Administration (NOAA)'s SpaceWeather Prediction Center. The GOES‐R spacecraft use arcjet thrusters for orbital stationkeeping, and the partially ionized thruster plume creates a relatively large (~20 nT) disturbance in themagnetometer data. This study presents a correction algorithm that removes the arcjet signal from the magnetometer data. The algorithm is based on an observed linear relationship between the arcjet disturbance and the ambient magnetic field. We estimate correction parameters using data from GOES‐16 (the first spacecraft of the GOES‐R series), evaluate the uncertainties in the corrected data during arcjet events, and discuss limitations and considerations for arcjet correction in the GOES‐R series magnetometers.