Background and context: The aim of this activity is to breadboard the Straylight LIDAR instrument concept and to verify its performance experimentally. This activity aims to raise the TRL to 4 and follows the TDE activity (T216-104MM Verification of straylight rejection of optical science payloads using a pulsed laser source). The aim of this smooth follow-on is to verify the concept experimentally using an available flight spare space telescope baffle as a representative test object.Description of the concept: The technique is called ?straylight LIDAR?

The SpaceLiner Main Engine (SLME) designed by SoftInWay Switzerland and DLR-SART funded by GSTP with European Space Agency (ESA) is a 200t class staged combustion engine designed for reusable heavy launch applications. The SLME-NIOPP features an Integrated Oxygen Power Pack (NIOPP) in-line with the Main Combustion Chamber. The SLME-NIOPP architecture is unique for Europe and offers significant advantages for Thrust to Weight Ratios. The relatively low combustion chambers and turbine inlet temperatures result in a cheaper and more accessible engine.

Photonic integrated circuits (PICs) are indispensable for data transmission within modern data centers and pervade multiple application spheres traditionally limited to bulk optics, such as LiDAR and biosensing. Recent advances in thin film Lithium Niobate (LNOI) have shown the major potential of LNOI integrated photonic circuits, which exhibit strong Pockels effect enabling ultrafast and efficient electro-optical modulation but are difficult to process via dry etching.

A critical moment during the launch of a mission is when communication is established for the first time. For ground control to communicate with a satellite or payload, the engineering teams must formulate the communication protocols as early as the requirements definition phase, refine and implement them during the design, verification, and production phases, and maintain them after launch. ESA addresses this need for reliability despite constant change with the OPUS and the ASN1SCC projects.

The need for high-thrust propulsion systems compatible with small satellites for constellation deployment, orbit maintenance and stationkeeping is particularly emerging. A high-thrust propulsion system provides large velocity increments in a short time, which enables orbit transfer, orbital plane change, re-entry, and planetary orbit insertion for deep space exploration.

The project focused on the development of technology for wireless energy transmission from a fixed station to a vehicle. A rover-like vehicle on the surface of the moon was assumed for the definition of the system parameters. Previous studies and projects for SPS WPT systems focused on the frequency ranges at 2.4GHz or 5.8GHz and less in the mm-wave range when selecting the transmission frequency. The reason for this is the lower attenuation of the transmission through the atmosphere.

In this study we explore the potential of Large Language Models (LLMs) to interact with Earth Observation (EO) data with some promising first results. We source a first testing set for the BIG Bench framework. With 20+ subtasks, we aim for a large variety of questions which are currently beyond the capabilities of LLM and other models. Further, we implement a methodology to test proprietary state of the art models where token distribution may not be available.