Microwave electrothermal thruster, also known as MET, is a propulsion device that converts microwave energy (a type of electromagnetic radiation) into thermal (or heat) energy. These thrusters are predominantly used in spacecraft propulsion, more specifically to adjust the spacecraft’s position and orbit. A MET sustains and ignites a plasma in a propellant gas. This creates a heated propellant gas which in turn changes into thrust due to the expansion of the gas going through the nozzle. A MET’s heating feature is like one of an arc-jet (another propulsion device); however, due to the free-floating plasma, there are no problems with the erosion of metal electrodes, and therefore the MET is more efficient.
The MET contains key features and parts that contribute to its efficiency. The parts include: two endplates (nozzle and antenna), plasma, and a dielectric separation plate.
The resonant cavity is the round overlapping section waveguide that is shorted by the two endplates. The cavity is near the separation plate. There are two end plates inside the MET: the nozzle and the antenna. The nozzle’s function is to convert the gaseous plasma into thrust. The antenna is used to input the microwave power. Although most of the power is absorbed by the plasma, some of it is reflected. Another part of the MET is the plasma. In some cases, plasma is also referred to as the fourth state of matter. The plasma is the main portion of the MET. It is created inside of the system by heating the propellant and is exhausted to generate thrust. The last part of the MET is the dielectric separation plate. This piece of the MET allows both parts of the cavity to be controlled at various pressures.
In order for the MET to create thrust, it must go through a 4 step process of converting electrical energy into heat energy.
During this process, the antenna section is held at atmospheric pressure to ensure that there is no plasma formation close to the antenna. It also ensures that the separation plates are not held at two significantly different pressures, which would put stress upon the two plates.
The physical process for what takes place on a molecular level can also be explained in the following manner:
Thrust is the force that is applied on the rocket caused by when the propellant is released. The formula for thrust is given as:
Where thrust is given as in Newtons(N), as mass flow rate in kilograms/second(kg/s), as exhaust velocity in meters/second(m/s), as exit pressure, as atmospheric pressure, and as nozzle exit area in meters^2(m^2).
Specific impulse is how efficiently the fuel of the MET is used to create thrust. The formula for specific impulse is given as:
Where is given as specific impulse, as thrust in N, as mass flow rate in kg/s, and as the gravitational acceleration of the earth.
When applying the conservation of momentum law, the relationship between mass of propellant and initial mass of the spacecraft can be shown as:
Where is given as propellant mass, as initial spacecraft mass, as change in velocity, is as specific impulse, and as earth’s gravity.
The MET’s main purpose is spacecraft propulsion. The energy that is created is meant to be converted into kinetic energy, which will produce thrust in space. Some tasks include orbit raising and stationkeeping. Orbit raising is changing the orbit of a ship using propulsion systems, while stationkeeping is maintaining a spacecraft’s position in relation to other spacecraft. This includes the maintenance of satellites at certain positions.
This is one of the more recent applications of a microwave electrothermal thruster created in August 2020. This invention used the functions of a MET to create a precise control system. When the MET changes the energy from electromagnetic waves to propellant, it allows for the small impulses of the MET to give control over the satellite.
This invention is pertaining to the MET adaption for space electrothermal propulsion. In order to control the altitude of a satellite/spacecraft and for primary propulsion, the tunable frequency MET was provided. Instead of a magnetron (microwave generating device), there were alternative constructional features which included using generators and semiconductors. This made it more efficient allowing the thruster to operate at two separate frequencies.
Relative to other electrothermal thrusters, the MET ranks higher than arc-jets and resistojets. This is because the MET provides higher specific impulses, or in simpler terms more thrust for the amount of fuel. Another advantage is that because microwaves can be collected and fed directly into the thrust chamber, the MET is extremely compatible with space transport. Finally, the MET can be run on water vapor as a propellant, which can be found in many different parts of the cosmos.
Electrothermal thrusters have the lowest efficiency among most other electric propulsion systems. Among electrothermal thrusters themselves, the MET ranks lower than ion thrusters. Another disadvantage is that the MET has relatively low thrusts, compared to rocket engines.