Description
Priority 2 activities will only be initiated on the explicit request of at least one delegation.
Objective:
Development of 4-7 m aperture antenna reflector technology for telecommunications, based on elastic foldable material, PIM-free and lightweight.
Targeted Improvements:
The main benefit is an enabling antenna product in a demanded frequency band where increased aperture can enhance performances. Current technologies do not allow for accommodation on European platforms and competitive launchers.
Furthermore a significant mass reduction of up to 50% can be obtained and a PIM free product should be developed.
Description:
Apertures of at least 6 m have been identified as necessary to fulfill mission requirements in terms of directivity at end-of-coverage (EOC) or C/I. The targeted applications are mainly in C-band missions, but could be extended later on to Ku- and possibly Ka-band. Current technologies based on solid reflectors in one piece or multiple pieces are difficult to accommodate on conventional platforms and competitive launcher fairings. Therefore the elastically foldable option provides a volume reduction that can allow for easier accommodation on European spacecraft, increasing competitiveness vis a vis American products.
The proposed work programme can benefit from on-going TRP activities, scheduled to be finalised in 2014, whereby a demonstrator is being tested up to 5 m aperture for general applications. Further development is required to incorporate Telecom requirements (offset optics and shaping of surface). Detailed verification of PIM has been already considered but further consolidation is necessary.
The purpose of this ARTES 5.1 will be the adaptation of the membrane technologies to telecom requirements and the development of a design able to be accommodated in European telecom platforms, in a more competitive way than existing technologies. The proposed architecture is consisting of a reflecting surface constructed in shell-membrane technology, a supporting frame based on deployable structure or alternatively a mechanism-free integrated backing structure.
The work logic is as follows:
- State-of-the art review and selection of baseline solution;
- Preliminary design of a reflector assembly flight unit;
- Detailed design of a demonstrator;
- Testing and verification of performance.
An engineering model with limited testing will be requested, with 6 m aperture and folding ratio 4:1. The test campaign will require PIM testing (at sample level), mechanical testing (folding, deployment and vibration) and thermal cycling. A maximum mass of 40 kg for the 6 m offset reflector is considered as a target.