Summary:
Belarusian university has developed an electrostatic colloidal microthruster for CubeSat satellites using micro-electromechanical system (MEMS) technology. They are interested in technical and research cooperation with industrial and academic partners in respect to joint development and testing of systems for propulsion and positioning of microsatellites. Potential partners could be scientific organizations, universities, and private companies.
Description:
Small CubeSat satellites are becoming an increasingly popular type of spacecraft. They can be used for the exploration of outer space, the atmosphere and the Earth's surface, and communication. Other applications include the development and demonstration of technologies related to aerospace technology, and the study of other celestial objects. As for Nanosatellite and CubeSat Database, the number of nano- and picosatellites launched into near-Earth orbit is increasing exponentially every year. In the third quarter of 2020 it amounted to more than 1200 units. However, only 6.1% of nanosatellites are equipped with thrusters, which is due to the lack of reliable universal devices with an optimal ratio of mass, thrust and generated pulse. Currently, cold-gas, chemical, ion, hall, plasma, thermoresistive and electrostatic reactive microthrusters have been developed.
The University has developed an electrostatic colloidal microthruster for nanosatellites, in which an ionic liquid is used as a fuel, providing a thrust of up to 0.2 mN at a total pulse value of 1000 N*s. The power consumption is 15 W. The dimensions of the microthruster are 100x100x90 mm, which does not exceed the dimension of one 1U CubeSat unit.
The advantage of this development is the use of MEMS technologies to create the main components of an electrostatic colloidal microthruster. This allows one to lower the standards for machining accuracy, hardness and viscosity of the structural materials used. As a result, it allows to achieve parameters similar to competitive developments with reduced cost of manufacturing and materials.
The dimensions of the developed microthruster sample make it possible to install it on CubeSat microsatellites with dimensions from 3U to 9U.
Low power consumption for the use of an effective electrostatic principle of reactive thrust formation enables to reduce the load on the onboard power supply system of the microsatellite.
In contrast to solid-fuel or liquid-propellant combustion thrusters, the electrostatic operating principle of the microthruster allows more accurate control of the pulse generated by it and repeated restart thereof during the life cycle of a microsatellite. The generated thrust and specific pulse allow maintaining the orbit of a 3U microsatellite with a height of 300 km for 3..4 years.
In its characteristics, the microthruster sample is comparable to similar developments of Accion Systems (USA), Busek (USA) and Inpulsion (Austria). But it has technological advantages associated with the use of MEMS technologies for manufacturing.
The offer is aimed at establishing technical cooperation with industrial partners to conduct joint work on the pilot operation of an electrostatic colloidal microthruster for further use in small spacecrafts.
Collaboration with an industrial partner within technical or research cooperation agreements is possible for the implementation of joint scientific and technical developments with regard to electrostatic systems for spacecraft micropropulsion. These developments should be targeted at improving the developed technology and/or creating devices with the required parameters.
It is assumed to conduct joint developments of new technologies with scientific partners for the use in the microthrusters of small spacecraft propulsion systems.
Universities, scientific organizations, and private companies are considered as partners.
Type (e.g. company, R&D institution…), field of industry and Role of Partner Sought:
The industrial partner within the technical cooperation agreement for the pilot operation of an electrostatic colloidal microthruster. The partners required to have the equipment and experience to conduct ground-based pilot operation and the ability to test microthruster samples in low-earth orbit.
The industrial partner within the research cooperation agreement or the technical cooperation agreement for improving the developed manufacturing technology and design of the microthruster and/or to create devices with the required parameters. The partner is required to have high-precision machining technologies, including solid materials, manufacturing of microporous media, high-precision 3D printing, experience in modeling and designing electrostatic and capillary systems.
The scientific partner within the research cooperation agreement for the development of new technologies for the use in microthruster of small spacecraft propulsion systems. The partner is required to have experience in modeling gas and thermodynamic processes, designing electrostatic and capillary systems.
Stage of Development:
Prototype available for demonstration
Comments Regarding Stage of Development:
An experimental sample of the electrostatic colloidal microthruster was created and tested in laboratory.
IPR Status:
Patent(s) applied for but not yet granted
External code:
TOBY20201221001
