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The development of non-metallic propellant tanks, for gas and liquid media, reduces the costs and lead times related to manufacturing and delivery for all satellite configurations using metallic lined units. By using composite-polymer combinations, low pressure liquid tanks and high pressure gas tanks can be produced in a fraction of the current time and supplied from an open supply environment.
As space exploration becomes more common, the rise of objects in Earth’s orbit will lead to a significant increase in close conjunctions. Therefore, there is a need for a new tool to help Space Operators in predicting potential dangerous close encounters.
RUAG Space L-band antenna array elements have been a successful product the last ~15 years. Recently we have noticed that the power requirements on the L-band feed chain will be more stringent in the near future. It is mandatory to secure our role as a supplier in the future and therefore we need to continue the development of our antenna element.
The techno-economic evaluation of advanced techniques in design and manufacturing of RF hardware by using the potential of additive layer manufacturing for mass and lead time saving under consideration of RF performance. The conventional design and performance as a baseline for innovative (e.g. elliptical waveguide channels) and cost saving (monolithic approach saves assembly costs) RF products.
In this activity a novel high precision end-to-end manufacturing technique has been developed based on additive manufacturing techniques that allow precision mandrels to be produced and dissolved within a few hours. Targeted are RF passive hardware such as waveguide routing, feed components, Ka-band filters and diplexer which are needed in high volumes and Q / V / W-band passive components which require precision manufacturing.
The objective of this activity was to design, manufacture and test an EM of a space-borne high efficiency power flexible (both dynamic and static) HPA stage in C-band. A Doherty arrangement was determined to be the most suitable architecture. Under CW operation a PAE improvement of 15% was achieved at 6dB OBO over a Class AB amplifier.
30GHz Dielectric Channel Filter with small mass and footprint were developed and tested. This was performed by the correlation of full wave simulation to the test data from suitable designed hardware. A 10 pole filter with coaxial interface was developed and a 3-channel multiplexer was developed.The test campaign for both units was successfully completed.
A new antenna line has been developed, which will offer a good trade-off between mass and operating bandwidth. To achieve this goal, the most appropriated technology has been identified, using an antenna concept based on spline profile horns, which are light, easy to manufacture, presenting also good broadband performance.
L-band and Ku-band HPA modules using GaN Technology from UMS (GH50 and GH25) and novel thermal management solutions have been developed.
With a CW signal, at hot temperature (85°C) and in the useful frequency bandwidth of [1,518 – 1,559 GHz], the L-band HPA module delivers an output power of 48W with an associated PAE of 60%.
With a CW signal, at hot temperature (85°C) and in the useful frequency bandwidth of [11,5 – 12,5 GHz], the Ku-band HPA module delivers an output power of 48W with an associated PAE of 25%.
For the ICEYE precursor mission, FOTEC is developing an electric propulsion system. It is based on FEEP (field emission electric propulsion) ion thruster technology. A cluster of seven identical IFM nano thruster modules is manufactured - each capable of delivering up to 300 µN thrust. This redundant design ensures high reliability and versatility of the propulsion system.
The arrival of new Ka band satellite services comes with dramatic reduction in bandwidth cost, multi-spotbeam capabilities and dynamic signal strength allocation, increased transport capacity and improved interactive possibilities. Ka band services enable an IP based paradigm for delivery and consumption of content, allowing for a more personalised, on-demand driven user experience.
This project will give the answer to the question how to deliver these new Ka band IP based content services to end users, taking into account the context of terrestrial network developments. Since Ka band services will become part of the IP world of service delivery, integration with next Generation Networks (like IMS) is essential in facilitating
the uptake of these services.
The objective of the study has been is to evaluate the expected performances of on-board GNSS receivers in GTO and HEO trajectories. These types of orbits/trajectories will be encountered during orbit raising of future all-EP telecommunication satellites. The trajectories, often optimized for minimum flight time, present specific challenges to the use of on-board GNSS. These include a large variation in visibility patterns and RF power levels, a high dynamic range of GNSS signals and varying spacecraft attitude resulting in masking effects affecting antenna gain.
The project covers design and development of a DVB-RCS2 Testbed. The goal is to validate key functions of the DVB-RCS2 standard (EN301545). The Testbed is designed and implemented to provide manufacturers and researchers with a validated reference design of DVB-RCS2 sub-systems, with main focus on the satellite terminal functions. The hub functionality was emulated as required for the validation of the RCS2 terminal functions.
Carrier aggregation is an integral part of current terrestrial networks. Its ability to enhance the peak data rate, for efficiently utilizing the limited spectrum resources and satisfying the demand for data-hungry applications, has drawn a significant attention. Given the benefits of carrier aggregation in the terrestrial wireless environment, this project investigates adopting this concept in the satellite domain.
Future satellite payloads are expected to become more complex, hosting large amounts of equipment and associated R.F. waveguide harnesses. To reduce overall complexity, mass, volume and Assembly Integration Test (AIT) time, non-conventional manufacturing and joining technologies are necessary. Following a review of potential technologies, this project is focusing on developing lightweight R.F. demonstrators employing adhesives and laser welding.
This project has studied the possibility of improvement of the classical regulated bus by considering the use of a classical regulated topology whose voltage is regulated to maximum power point of the solar array. The project has consisted of two phases: the first one considered whether the basic idea improves the classical regulated bus by using ad hoc developed models; the second one, after positive conclusions of the first, tested the actual behaviour of a low power mock-up of the proposed idea.
The objective of this activity is to study, design and optimise potentially suitable antenna architectural concepts for Ka-band systems that are able to provide single aperture multi-beam capability from geostationary orbit.
A new EM L-band vertical SSPA equipment using GaN Technology from UMS and thermal management solutions has been developed.
With a CW signal, at hot temperature (85°C) and in the useful frequency bandwidth of [1,518 – 1,559 GHz], the equipment delivers an output power of 43W with an associated PAE of 53%. Total mass of the EM L-band SSPA equipment is 1,44kg with dimensions L=240mm, W=105mm, H=124mm.
The aim of this project is to investigate SSPA/EPC architectures, the EPC components, technologies and processes limiting the operation at high baseplate temperatures (90ºC - 100ºC and above) for Solid State Power Amplifier equipment and ultimately design, build, manufacture and test an EPC hardware model.
The main objective of the project was to develop and demonstrate fast and high-throughput (Tb/s) optical switching technology that could be applied for optical packet routing in a burst-switched processor in a telecommunication satellite.
A novel electrically coupled and contactless rotary sensor for angle measurement up to 0.01 degrees of resolution. The product is an attractive alternative to traditional potentiometer and optical sensors with excellent resolution of accuracy at extreme temperatures and radiation environments.
Space industry is based increasingly on full electric propulsion systems, and there is a European need to anticipate future missions. 2018 full electric propulsion Telecom satellites have a relatively low thrust and need several months (6 to 9) to rise from GTO to GEO, which is their main drawback. To reduce this delay between launch and commercial exploitation, and to offer to customers a more powerful payload, a power increase, in this study 100kW, is necessary.
TThe Generic Telco P/L EGSE is a high-performance multi-threaded client-server test-platform and environment to quickly customize or create measurements according to new requirements. Its pre-defined building blocks for measurements, telemetry packets, device drivers and PUS and EDEN interface support further rapid integration. It provides a set of ready products like reporting, configuration editing, synoptic and graphical user interface all accessible from remote.
Study defining a concept of use of Thermo-Acoustic Electric Generation for communication satellites, assessing suitable TAG systems, the benefits and constraints of introducing this type of engine into Satcom Satellites, and defining a roadmap for the introduction to market of these engines with the aim of supporting ARTES.
OSMOSIS has implemented a reference end to end satellite network which will serve as a test bed for prototyping product offerings in the areas of LTE Multimedia Broadcast (eMBMS), CDN, Adaptive Bitrate Streaming and End-to-end QoS Management.
An EQM-Level Optical passenger payload in-orbit demonstrator of Photonic Technology for On-board Reference and LO distribution by optical links has been designed and manufactured. Two optical links operating at 10 MHz and 10 GHz, including 10 meters fibre and a power splitter, have been integrated in the HISPASAT Amazonas 5 satellite, successfully launched and tested in orbit in 2018.
For the IFM Nano Thruster Module, FOTEC uses an electric propulsion system based on FEEP (field emission electric propulsion) ion thruster technology. The thruster uses Indium as the propellant, which is ionized through a strong electric field. Lifetime testing has exceeded 18,000 hours and the thrust level is controllable from 10μN-1mN with a specific impulse ranging from 2,000-5,000 seconds.
The project examines the impacts and opportunities of 5G for the satellite industry, as a technology building block to be integrated within 5G that can complement terrestrial technologies, as an enabler for innovative satellite-based solutions and as a lever to capture new markets.
AlN is an interesting new material for TWTs. Nevertheless, the requirements for space, like long-term stability and reliability are stringent for the AlN and need to be secured. This requires a good understanding of the material and the knowledge of the complete processing, including the material source. Long-term reliability had been fostered by a common approach – together with the supplier.
The developed product is a Technology Demonstrator of the Metal Hydride (MH) Hydrogen and Heat Storage System for use in future telecom satellites as part of a Regenerative Fuel Cell System. Thermal management is one of the key challenges with the RFCS, due to the significant amount of fuel cell waste heat that must be dissipated, which has a big impact on the total system mass and volume. By using a metal hydride system for hydrogen storage, waste heat from the fuel cell can be stored in the metal hydride material, and later rejected with a lower heat flux, over a longer time span.
The project covers extensions to the CCS5/SCS5 product to allow control of satellites deployed in mega-constellations. In order to support the smaller satellite architectures normally found in such constellations, adaptions enable right-sizing of both the computing resources and pricing. It also adds new features for easing monitoring and control of such a large number of satellites.