Combined Chemical–Electric Propulsion for a Stand-Alone Mars CubeSat

Abstract

Stand-alone interplanetary CubeSats require primary propulsion systems for orbit maneuvering and precise trajectory control. The current work focuses on the design and performance characterization of the combined chemical-electric propulsion systems that shall enable a stand-alone 16U CubeSat mission on a hybrid high-thrust-low-thrust trajectory from a Supersynchronous Geostationary Transfer Orbit to a circular orbit about Mars. The high-thrust chemical propulsion is used to escape Earth and to initiate stabilization at Mars. The low-thrust electric propulsion is used in heliocentric transfer, ballistic capture, and circularization. For chemical propulsion, design and performance characteristics of a monopropellant thruster and feed system utilizing ADN-based FLP-106 propellant are presented. For electric propulsion, a performance model of an Iodine-propelled inductively coupled miniature radiofrequency ion thruster is implemented to calculate the variation of thrust, specific impulse and efficiency with input power. A power constrained low-thrust trajectory optimization utilizing the thruster performance model is pursued to calculate the transfer time, ∆V and the required propellant mass for fuel-optimal and time-optimal transfers. Overall, the combined chemical-electric systems yield a feasible propulsion solution for stand-alone CubeSat missions to Mars that balances propellant mass and transfer time.

Review of State-of-the-Art Green Monopropellants: For Propulsion Systems Analysts and Designers

“…"Dual propulsion" is another configuration for the combined chemical-electric propulsion systems as proposed by Mani et al [91,92], which differs from the multi-mode configuration by utilizing two separate systems, a chemical system and another electric propulsion system, alongside each other in the spacecraft. The dual (combined chemical-electric) propulsion system designed by Mani et al consisted of a green monopropellant regulated pressure-fed system burning the ADN-based FLP-106 green monopropellant, and an electric propulsion RF ion thruster fueled by iodine.…”

Multi-Disciplinary Design Optimization for Relative Navigation in Non-cooperative Rendezvous

“…On the opposite, liquid chemical propulsion systems include, as its main parts, a combustion chamber and a convergent-divergent nozzle. These two types of chemical propulsion have the advantage of having excellent flight heritage and are reliable and simple [21]. Figure 14 and 15 show the Isp and the thrust of the listed thrusters with respect to their mass.…”

Novel 3U Stand-Alone CubeSat Architecture for Autonomous Near Earth Asteroid Fly-By

“…The micro-propulsion system is usually the largest and the most demanding in terms of mass and volume, thus it is seen as one of the driving subsystems for this mission (MR7 in Table 1). Moreover, commercial launches are more frequent than deep-space ones (respectively around five per year and one per year), so they can be used as a rideshare more easily [34]. For this reason an Earth sphere-of-influence (SOI) escape scenario is considered, with the goal of achieving a transfer able to fly-by an asteroid.…”

“…For this reason an Earth sphere-of-influence (SOI) escape scenario is considered, with the goal of achieving a transfer able to fly-by an asteroid. The Earth escape problem has been investigated in previous work and solutions have been proposed-chemical propulsion followed by electric low-thrust trajectory [34], low-thrust escape trajectory [35], and micro-propulsion staging [36]. However, all of these solutions consider customized propulsion systems, which are not in line with the off-the-shelf approach used in this mission concept.…”