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COBEM 2021
26th International Congress of Mechanical Engineering
A HYBRID ANALYTICAL-NUMERICAL MODEL FROM THE PROPELLANT TANK UP TO THE THRUSTER OF THE LOW-PRESSURE MICRO-RESISTOJET
Submission Author:
Igor Guimarães , RJ
Co-Authors:
Igor Guimarães, Daduí Cordeiro Guerrieri
Presenter: Igor Guimarães
doi://10.26678/ABCM.COBEM2021.COB2021-1361
Abstract
The increasing number of space missions involving CubeSat demonstrates the importance of those new satellite concept. However, these very small satellites still need to improve their maneuvers capabilities by implementing, for instance, an adequate propulsion system. One interesting propulsion system to be implemented in this class of satellite, in order to enable new mission types, is the Low-Pressure Micro-Resistojet (LPM). Even though there are studies on the thruster part of this propulsion system, there is a lack of studies relating to the fluid behavior through the feed system from the tank up to the thruster. The present work describes the plenum pressure and thrust variation as a function of tank pressure based on the proposed hybrid analytical-numerical model. Numerical results were used to establish a parametric relationship between the tank and the plenum where it was proposed a pressure function with an estimated maximum error of 2.8 %. Additionally, the proposed pressure function was combined with the LPM analytical model proposing a new relationship for the thrust equation allowing the use of the tank pressure as a parameter. With this new equation, it is possible to predict pressure behavior through the tank and the plenum, the number of channels, and estimate thrust for different tank pressure . In summary, this hybrid analytical-numerical model helps to design the subsystems of the LPM from the tank up to the thruster, with maximum values of thrust and specific impulse estimated in this article was 0.77 mN and 117.55 s respectively.
Keywords
LPM, nanosatellite, Propellant Tank, Micro-Thruster, cubesat
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