Spacecraft Propulsion Systems
Space Propulsion with more than 5000 Ns
Inert non-pressurized tank during launch
Extremely high total impulse density
Significantly cheaper than Xenon
The IFM Nano Thruster
Developed for ESA Science Missions
6th Generation PPU
> 85% efficiency
Easy and fast just Plug & Play
The IFM Nano Thruster is a mature technology, developed under ESA contracts for 15 years. In this time more than 100 emitter have been tested and an ongoing lifetime test has demonstrated more than 13.000 h of firing without degradation of the emitter performance.
The thrust can be controlled through the electrode voltages, providing excellent controllability over the full thrust range and a low thrust noise.
Due to the efficient ionization process which allows to ionize up to 60% of the evaporated Indium atoms, the IFM Nano can provide a higher specific impulse than any other ion propulsion system currently on the market.
As the IFM Nano thruster expels an ion current of up to 3 mA, the module needs means to prevent spacecraft charging. This is achieved by the use of two cold-redundant electron sources acting as neutralizers. Such an electron source consists of a Tantalum disc which is heated up to 2,200 K and biased to -200 V. Once electrons have left the neutralizer, they will be pulled towards the positive potential of the ion plume. The PPU is able to measure and control this charge balancing electron current.
The IFM Nano contains no moving parts and the propellant is in its solid state at room temperature. Avoiding any liquid and reactive propellants as well as pressurized tanks significantly simplifies handling, integration and launch procedures.
The IFM Nano thruster module is used as a compact pre-qualified building block in order to provide custom solutions at a commodity price and ultra-short lead times. Although building block is a complete self-contained propulsion system, the whole cluster can be operated as a single plug and play unit.
Using a cluster of IFM Nano Thruster modules for small satellites provides a significant thrust vectoring capability.
Field emission is an effect which is closely tied to the presence of strong electric fields. In practice, this means that the fundamental structure on which field emission takes place is shaped like a needle, due to the field-enhancing effect at the tip. An important application of this effect is the so-called ‘Liquid Metal Ion Source’ (LMIS), because it uses the process of field emission to ionize a thin film of liquid metal covering a needle which has been biased to a few kV with respect to a counter electrode. The thusly created ions are then accelerated by the strong electric fields and can be used for ion implantation in semiconductor industry or micromachining in a focused ion beam (FIB).
This principle of generating positive ions and accelerating them by the very same field can also be used to generate thrust. When a liquid metal ion source is used in this fashion, it is termed ‘field emission electric propulsion’ (FEEP).
Due to the accuracy with which it is possible to regulate the voltage between the needle and the extraction electrode, the ensuing thrust can be controlled with unmatched accuracy. The main advantage of using FEEP thrusters lies in their capability to produce thrust from the sub-µN level to several tens of µN per emission site.
For more than 15 years, research has been carried out to use this technology for providing ultra-precise thrust in the µN-range to a spacecraft for applications related to formation flight of spacecraft.
In this environment, the proprietary porous tungsten crown emitter has been developed, which employs 28 needles for field emission. Apart from the multiple emission sites, the most important new feature is the porous tungsten matrix which enables internal flow of the liquid metal to a very sharp tip.
In the frame of the development efforts for the ESA NGGM mission, extensive testing of this technology has been performed, including the characterization of more than 100 ion emitter. An ongoing lifetime test has demonstrated more than 16.000 h of operation without performance degradation.
In Orbit Demonstration in 2017
The IFM Nano Thruster has been the first European Thruster that has been sold to a commercial constellation. Since then, several companies have chosen this technology for their satellites in the range of 3-100kg satellites. ESA has recently chosen the IFM Nano thruster as the best possible thruster for the 6U e.inspector platform.
Your customized propulsion system
Made of pre-qualified building blocks
No extra cost for customization
No additional lead times!
The modular design of the IFM 350 Nano Thruster allows for an easy clustering to various configurations. This introduces an inherent redundancy of the system, as each module is completely independent.
The configuration of seven modules fits into a 15 inch (38cm) separation ring, allows for 2.4 mN of continuous thrust at 200W and a total impulse of more than 38 kNs with 1.5 kg of propellant.
Clustering of the porous tungsten crown emitter can be achieved either on sub-system level or on crown level.
Clustering Individual Modules is advantages for spacecrafts smaller than ~150kg.
The IFM Micro Thruster is currently being commercialized with the support of Airbus DS, CNRS and EPFL. A fully qualified product will be available in 2019
The modular approach of the IFM Nano Thruster allows for a large number of possible mission advantages, including attitude control capabilities.
ORBIT LIFE EXTENSION
Mission extension ranging from weeks to years, especially in low altitude orbits with increased resolution for earth remote sensing such as imaging applications
Gain flexibility in the choice of a suitable launch opportunity, including a cheap ISS deployment
FORMATION FLYING AND CONSTELLATION CONTROL
Controlling inter-satellite distance in the orbital plane
HIGHLY EFFICIENT DEORBITING
Efficiently deorbit a small satellite from a higher orbit to comply with international Space-Debris Regulations or perform an EOL maneuver putting it in a graveyard orbit
SAFE AND INERT SYSTEM COMPLIANT WITH ALL LAUNCHER REQUIREMENTS
The thruster uses liquid metals as propellant. The propellant is in its solid state at room temperature. Avoiding any liquid and reactive propellants as well as pressurized tanks significantly simplifies handling, integration and launch procedures.