ESA Technology’s Post

A major milestone has been successfully achieved on schedule! The ESA FIRESPELL activity has successfully completed its Preliminary Design Review. The objective of FIRESPELL is to develop a unified particle radiation model for interplanetary missions that extends the European Specification modelling of solar energetic particles to energies down to 0.04 MeV and includes the contribution of Jovian electrons. For this purpose, a large volume of energetic electron and ion flux measurements from cornerstone European and US missions - such as Wind, ACE, SOHO, IMP8 and ARTEMIS - were evaluated, reprocessed, and calibrated. FIRESPELL is led by SPARC (GR) in partnership with the University of Athens (GR), the Max Planck Institute for Solar System Research (DE), the University of Barcelona (ES) and the Catholic University of Leuven (BE). The activity is funded by the European Space Agency under ESA Contract No. 4000142510/23/NL/CRS awarded by SPARC in response to the Open Invitation to Tender "Particle Radiation Modelling for interplanetary missions extending to low energies".

Small nation, big impact: Estonia is pioneering an instrument called OPIC which will collect vital information on the ESA–JAXA Comet Interceptor mission. This marks the first Estonian industrial contract through ESA’s Prodex programme involving Estonian space technology company, Crystalspace. Read more about OPIC and Prodex (Programme for the Development of scientific Experiments), an ESA programme which offers research institutes and industry from Participating States the opportunity to get involved in designing and building a scientific instrument for ESA missions. https://lnkd.in/e2CReXCe

Dear Space Propulsion Community, what an intense week was at the Space Propulsion Conference 2024 in Glasgow!! There seems to be challenging but very promising years ahead for Space Propulsion Systems and Technologies. The dawn of this period probably started already few years ago and it is going to boost into shining days for a number of reasons - listing here some key ones ▪ space propulsion systems will be required for future space logistic infrastructures, in-orbit servicing, transportation systems, EOL disposal ▪ this will require improvement of existing technologies and, more importantly, a faster release to market of innovative concept ▪ this can be achieved by better cooperation between the various players - Agencies, the Industry, Research Institutes and Universities, Private Investors ▪ the approach and mindset for future development will change from "failure is not an option" to "a safe failure is tolerated" in order to make trials, gain experience and arrive at the end of the process with a qualified product/technology ECRAFT can support through a diverse network of partners the entire product lifecycle, from design to implementation. We offer comprehensive support, addressing both technical and management aspects at different levels, tailoring to our clients' needs, and effectively intervening in resolving all non-standardized or predictable challenges. In addition to that, ECRAFT is an ESA Classified SME open for Partnership / International Co-operation in technological studies, hardware development roadmaps and all other ESA funded bids where involvement of an SME is mandatory.

The Smallsat Technology Accelerated Maturation Platform-1 (STAMP-1): A Proposal to Advance Ultraviolet Science, Workforce, and Technology for the Habitable Worlds Observatory We present a concept for the Smallsat Technology Accelerated Maturation Platform (STAMP), an integrated facility, laboratory, and instrument prototype development program that could be supported through the GOMAP framework and applied to any of NASA’s Future Great Observatories (FGOs). This brief describes the recommendation for the first entrant into this program, “STAMP-1”, an ESPA Grande-class mission advancing key technologies to enable the ultraviolet capabilities of HWO. https://lnkd.in/gVmuqhU4

🚀🌍 Finally sharing my research from the 38th International Electric Propulsion Conference (IEPC) in Toulouse, France – better late than never! 🌍🚀 My paper, "3-Dimensional Characterization of Ion Beam Current using a Hemispherical Sweep Apparatus," introduces a novel diagnostic tool for electric propulsion systems. By mapping ion beam currents in 3D, we’ve significantly advanced the characterization of 5kW Hall Effect Thruster plumes. This method enhances the precision of thrust vector tracking, identifies previously undetectable plume asymmetries, and opens new doors for understanding plasma non-uniformities in space propulsion. This apparatus provides a more accurate diagnostic framework compared to traditional 2D methods, crucial for optimizing thruster performance in future missions. The adaptability of this setup allows researchers to measure ion currents across various configurations, facilitating the investigation of complex thruster behaviors and aiding in the development of next-generation electric propulsion systems. You can read more about it here : https://lnkd.in/gBiV_3Mb #IEPC2024 #ElectricPropulsion #AerospaceEngineering #SpaceTech #Research #Innovation #HallThrusters

❓ What are the trends in space propulsion? How can patent data provide such insights? And why is propulsion an important topic to consider in future space policymaking? 🚀 Our latest 𝗣𝗮𝘁𝗲𝗻𝘁 𝗜𝗻𝘀𝗶𝗴𝗵𝘁 𝗥𝗲𝗽𝗼𝗿𝘁 by European Patent Office and ESPI, and in collaboration with European Space Agency - ESA, is now live! ➡ Access the key takeaways and full report at: https://lnkd.in/eYHNXfgz

Executive Summary :"Propulsion is a key element in all space activities because it provides the fundamental function of producing thrust to move launchers, satellites, and other assets from Earth to space or within space. Space propulsion encompasses different principles, most prominently chemical and electric propulsion concepts as well as alternative and emerging concepts accompanied by a variety of propellants and even “fuel-less” concepts, such as solar sails. The significance of propulsion capabilities stems from their transversal enabling role for a spectrum of applications, including access to space; collision avoidance; on-orbit servicing, assembly, manufacturing and space exploration. For this study a total number of 4559 patent families filed at 52 patent authorities have been identified with applicants registered in 43 countries and inventors residing in 53 countries. The data set comprises 1178 international patent families (IPF) in four distinct technology principles, namely chemical propulsion, electrical propulsion, “alternative” propulsion and propellants." EPSI ESA Propulsion systems for space Patent insight report May 2024 https://lnkd.in/eUBrm7tC

Invitation to read the Article: ANTITHERMAL SHIELD FOR SHUTTLES, ROCKETS… EXPANDED COANDA EFFECT published by European Space Agency ESA FULL PAPER, Research Gate, Berlin: https://lnkd.in/dvZqqBMg   PATENT: https://lnkd.in/duXkzZE At high speed, the friction of air mass with the rocket surface produce local heating more than 1000 0C. For heat protection of rocket, on their outside surface are install antithermal shields. Studing Coanda effect, respectively, the fluid flow on solids surface, the author Ioan Rusu discover by simply researches that the Coanda effect could be expanded also for the fluid flow on discontinuous solids, respectively, gon solids with orifices. This phenomenon was named by the author, the expanded Coanda effect. Start with this discovery, the author Ioan Rusu invent an antithermal shield, registered at Romanian Patent Office, OSIM, deposit F 2010 0153   The paper “ANTITHERMAL SHIELD FOR ROCKETS WITH HEAT EVACUATION BY INFRARED RADIATION REFLECTION” was published by EUROPEAN SPACE AGENCY, ESA : https://lnkd.in/gYcP2Q8

Invitation to read the Article: ANTITHERMAL SHIELD FOR SHUTTLES, ROCKETS… EXPANDED COANDA EFFECT published by European Space Agency ESA FULL PAPER, Research Gate, Berlin: https://lnkd.in/dvZqqBMg   PATENT: https://lnkd.in/duXkzZE At high speed, the friction of air mass with the rocket surface produce local heating more than 1000 0C. For heat protection of rocket, on their outside surface are install antithermal shields. Studing Coanda effect, respectively, the fluid flow on solids surface, the author Ioan Rusu discover by simply researches that the Coanda effect could be expanded also for the fluid flow on discontinuous solids, respectively, gon solids with orifices. This phenomenon was named by the author, the expanded Coanda effect. Start with this discovery, the author Ioan Rusu invent an antithermal shield, registered at Romanian Patent Office, OSIM, deposit F 2010 0153 The paper “ANTITHERMAL SHIELD FOR ROCKETS WITH HEAT EVACUATION BY INFRARED RADIATION REFLECTION” was published by EUROPEAN SPACE AGENCY, ESA : https://lnkd.in/gYcP2Q8

In space electrical interconnection applications, derating the wire is a complex task and indeed crucial due to constrained heat dissipation in space. Indeed, optimizing the wire gauges becomes a sensitive analysis to ensure efficiency within the mass budget as a substantial portion of spacecraft or payload mass is allocated to the wire harnesses (~ 6-13%) It would be beneficial to compare how different space agencies approach the derating the wires using an example as follows: Lets assume, the plan is to design and build a wire harness for a 3-phase rotary actuator with two primary and redundant heaters, PRTs. temperature sensor for output , hall sensors and so on which ends to up to a bundle of 26 conductors. Hear is the ampacity for the power wire gauge 20 at the maximum operating temperature 80°C. ESA (European Space Agency) is considered the most conservative space agency in this context. In matter of fact since the nominal current for the actuator is 3 Amp versus the 2.37 ampacity for ESA standard, the ESA wire harness design needs to consider using a 18 AWG wire which is more massive. Source: Analysis uses the new developed application software “EZDerate” .