Plasma propulsion simulation using particles

This perspective paper deals with an overview of particle-in-cell / Monte Carlo collision models applied to different plasma-propulsion configurations and scenarios, from electrostatic (E x B and pulsed arc) devices to electromagnetic (RF inductive, helicon, electron cyclotron resonance) thrusters, with an emphasis on plasma plumes and their interaction with the satellite. The most important elements related to the modeling of plasma-wall interaction are also presented. Finally, the paper reports new progress in the particle-in-cell computational methodology, in particular regarding accelerating computational techniques for multi-dimensional simulations and plasma chemistry Monte Carlo modules for molecular and alternative propellan

The Role of Micro Propulsion in Enabling Autonomous Operations of Nanosatellites

Micro-Electro-Mechanical Systems (MEMS)-based propulsion devices have significant potential for providing high specific power. The application of Micro Power Generation technology to space propulsion systems can enhance orbit and station-keeping capabilities, potentially at lower costs. New-generation spacecraft and satellites are becoming smaller and require micro-propulsion systems for all aspects of their operations. The development of micro-propulsion systems with associated combustors for micro-electricity generation, utilizing liquid fuel, presents major challenges in fuel injection, mixing, combustion, and chemical reactor systems. A micro-spacecraft with high-accuracy station-keeping and attitude control capabilities needs to have low mass and deliver small impulses. Each nanosatellite will weigh a maximum of 10 kg, including the propellant mass. Provisions for orbital manoeuvres, attitude control, multiple sensors, and instruments, along with full autonomy, will result in a highly capable miniaturized satellite. All onboard electronics will endure a total radiation dose of 100 k rads over a two-year mission lifetime. Nanosatellites designed for in-situ measurements will be spin-stabilized and equipped with a complement of particles and fields instruments. Nanosatellites intended for remote measurements will be three-axis stabilized and equipped with imaging and radio wave instruments. Key technologies under development include: advanced, miniaturized chemical propulsion systems; miniaturized sensors; highly integrated, compact electronics; autonomous onboard and ground operations; miniaturized onboard orbit determination methods; onboard RF communications capable of transmitting data to Earth from significant distances; lightweight and efficient solar array panels; lightweight, high-output battery cells; a miniaturized heat transport system; lightweight yet strong composite materials for nano-satellite and deployer-ship structures; and simple, reusable ground systems

Analysis of electric propulsion electrical power conditioning component technology. Volume 1 - Data bank Final report

Analysis of electric propulsion electric power conditioning component technology - data revie

Iodine Electric Propulsion System Thrust Validation: From Numerical Modeling to In-Space Testing

In this paper, we complete a full-thrust audit of an iodine-based gridded ion thruster. Prior results have demonstrated excellent agreement between indirect and direct laboratory thrust estimates. Here, thrust estimates from numerical modeling, indirect laboratory testing from diagnostic probes and propulsion system telemetry, indirect in-space testing from onboard propulsion system telemetry, and direct in-space testing by analyzing orbital maneuvers are compared to demonstrate consistency between the four methods and complete the thrust audit. Results from recent in-space testing of the iodine-based thruster demonstrate that thrust estimates from all four methods agree to within three standard deviations of uncertainty for the 11 maneuvers studied. This thrust audit represents a critical step toward improving the understanding and technological maturity of iodine-based gridded ion thrusters for future mission applications, and it demonstrates the utility of recently developed in-space thrust inference techniques for analyzing low-thrust maneuvers

Micropropulsion Trade Study and Investigation for Attitude Control of Nanosatellites

Since their inception two decades ago, CubeSats have become dominant in the small satellite market, enabling new mission architectures, technology development, and education opportunities. However, the limited mass, power, and volume inherent in this small platform, constrains the on board subsystems and thus the capabilities compared to larger satellites. Attitude control is essential to maximizing the potential of CubeSats and other nanosatellites, though traditional momentum control systems such as reaction wheels are not feasible on the smallest CubeSats. Micropropulsion is an intriguing alternative to traditional methods, and many miniaturization efforts have been made for chemical and electrical propulsion systems. One such micro-propulsion unit is Film Evaporation Microelectromechanical System Tunable Array (FEMTA). FEMTA manipulates the temperature dependence of liquid water capillary action to produce controllable and precise thrust in the 10 to 100 microNewton range. FEMTA has been demonstrated in both thrust tests and in single axis rotation tests. This work describes the further characterization of FEMTA technology through these tests and compares it to other micropropulsion technologies in a trade study for micropropulsion as attitude control devices on various sizes of CubeSats

Research and technology highlights of the Lewis Research Center

Highlights of research accomplishments of the Lewis Research Center for fiscal year 1984 are presented. The report is divided into four major sections covering aeronautics, space communications, space technology, and materials and structures. Six articles on energy are included in the space technology section

Dormant Cathode Plasma Properties and Erosion Analysis in a Multiple-Cathode, High-Power, Rectangular Discharge Chamber

Peer Reviewedhttp://deepblue.lib.umich.edu/bitstream/2027.42/76546/1/AIAA-2005-4241-437.pd

Development of Magnetised Plasma Rockets using Inverse Design and Kinetic Simulation

Electric propulsion systems have become a leading solution for accelerating spacecraft, driving an appetite for lifetime, mass, and efficiency improvements. Advancements in additive manufacturing and computing power were leveraged to rapidly design the magnetic fields directly impacting an electric thruster’s performance. Fully kinetic particle-in-cell (PIC) simulation methods were also harnessed to characterise plasma sources beyond experimentation. To validate the plasma rocket models, simulations were first performed on existing and well characterised Cathodic Arc devices. The Cathodic Arc PIC models are the first to include continuously generated cathode spots and to model the far-field plasma jet. Results successfully predicted the evolution of the ion charge state energy distributions shown in experimental data and explored novel physics. To address the inverse design problem presented by the magnetic circuits of electric thrusters, the novel use of Monte Carlo sampling and conditional filtering was applied to design the magnetic nozzle of an RF plasma rocket. Following an analysis of designs with PIC simulation, devices were constructed with a helicon source, allowing plasma jet density and ion energy to be determined experimentally, with results further validating the model. A novel evolution-based design and optimisation strategy was developed to overcome the limitations of the sampling method. The objective function integrated a numerical model for plasma behaviour within a magnetic field to assess candidates across a large design space. Designs with different scores were constructed using an array of Neodymium magnets confined within an additively manufactured vessel situated about a helicon source. Experimentation showed a correlation between thrust and objective score, and an agreement with simulation data. The techniques developed in the research process can now be applied to improve the design of electric thrusters and other electromagnetic devices

Marshall Space Flight Center Research and Technology Report 2019

Today, our calling to explore is greater than ever before, and here at Marshall Space Flight Centerwe make human deep space exploration possible. A key goal for Artemis is demonstrating and perfecting capabilities on the Moon for technologies needed for humans to get to Mars. This years report features 10 of the Agencys 16 Technology Areas, and I am proud of Marshalls role in creating solutions for so many of these daunting technical challenges. Many of these projects will lead to sustainable in-space architecture for human space exploration that will allow us to travel to the Moon, on to Mars, and beyond. Others are developing new scientific instruments capable of providing an unprecedented glimpse into our universe. NASA has led the charge in space exploration for more than six decades, and through the Artemis program we will help build on our work in low Earth orbit and pave the way to the Moon and Mars. At Marshall, we leverage the skills and interest of the international community to conduct scientific research, develop and demonstrate technology, and train international crews to operate further from Earth for longer periods of time than ever before first at the lunar surface, then on to our next giant leap, human exploration of Mars. While each project in this report seeks to advance new technology and challenge conventions, it is important to recognize the diversity of activities and people supporting our mission. This report not only showcases the Centers capabilities and our partnerships, it also highlights the progress our people have achieved in the past year. These scientists, researchers and innovators are why Marshall and NASA will continue to be a leader in innovation, exploration, and discovery for years to come

Effects of Water Plasma Chemistry on Helicon Thruster Performance

The focus of this work is on the operation of a helicon thruster with water as the propellant. The characteristics of a water plasma are investigated and used to develop an analytical thrust efficiency model for the system. The efficiency of a helicon thruster operating with water vapor is compared to the efficiency with traditional noble gas propellants. Next, the predicted efficiency range is compared with other state-of-the-art electric propulsion devices. The addition of an ‘electrodeless’ ion cyclotron heating stage is investigated as a means of increasing thrust efficiency. The thrust efficiency model is extended to assess the parameter space for which the addition of ion cyclotron heating improves performance. Additionally, a particle-based trajectory model is developed to study antenna sizing, phasing effects, and energy conversion. Finally, the effects of second-order reactions on plasma composition and acceleration efficiency are explored using particle balance and particle-in-cell methods