Direct Radiating Antenna arrays (DRAs) are an emerging solution to offer multiple beam, cellular-like coverage to satellite communication services, evolving to meet the demands for high data-rates, capacity and availability over a flexible area. A DRA array provides several advantages to the satellite: for downlink, an improved Equivalent Isotropically Radiated Power (EIRP), due to the smaller size of the beam; for uplink, an improved Gain-to-noise-Temperature (G/T).

Achievements and status: 

• Both cylinders have been manufactured up to spec and shipped to the end-user. 
• Both cylinders have been accepted by the end-user

Benefits: 

• Tailored lattice design parameters to optimise the design for the defined load cases. 
• Mass savings in comparison to traditional monolithic designs of around 50% (of the composite part, without mounted equipment)

Background and justification: ​

• Xenon storage is challenging for small satellite platforms due to the strict thermal management and the presence of high-presure components.​
• A way of solving this problem is by having a different storage method. By storing the xenon in a cool gas generator, the xenon is bound chemically before the activation of the xenon cool gas generator. This way there is no need for high pressure components and the strict thermal management of the whole system is no longer needed​

Achievements and status: ​

The space mission development process tends to show several commonalities across projects. Indeed, systems often use the same generic set of technologies, with similar assumptions and requirements. The use of a Digital Assistant would be able to recognise such commonalities and propose suggestions during the early phase of system development based on previous projects. This would speed the definition stages, while also allowing to re-use potential lessons learned and hopefully to avoid simple mistakes/omissions.

Achievements:

• Successful plasma ignition was demonstrated with SSI-developed subsystems and the IRS IPT lab model. The ignition test campaign was conducted from 11th -14th April 2023 at IRS, Stuttgart.

• Two PPU amplifiers were designed, simulated, built, and tested; the Class E amplifier successfully ignited the thruster.

Maximising the heritage of the existing ISIS ISIPOD cubesat deployers family, and building on past studies performed within ESA GSP such as LV-POD, (Low-Velocity deployer),the main task of this TFO activity will be to :-Design a Low-Velocity 6U deployer suitable for deep space missions, compatible with the low separation velocity (order cm/s) and rotation error needed for deep space mission such as Hera, taking into account a series of requirements injected by the agency -Define interfaces w.r.t.