Demisable Primary Structural Joints for Low Earth Orbit Telecom Platforms (Artes... Tender

Procurement Summary

Country : Netherlands

Summary : Demisable Primary Structural Joints for Low Earth Orbit Telecom Platforms (Artes 4.0 at 4e.090)

Deadline : 22 Mar 2024

Other Information

Notice Type : Tender

TOT Ref.No.: 94235873

Document Ref. No. : 1-11701

Competition : ICB

Financier : Agency for the Cooperation of Energy Regulators (ACER)

Purchaser Ownership : Public

Tender Value : Refer Document

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Tender Details

Tenders are invited for Demisable Primary Structural Joints for Low Earth Orbit Telecom Platforms (Artes 4.0 at 4e.090)

The objective of this activity is to design, manufacture and test demisable primary structural joints suitable for future low Earthorbit (LEO) satellite communication platforms. Targeted improvements:- Increase compliance of LEO satcom platforms to the ESA on-ground casualty risk requirement (current threshold 1:10000) by one order of magnitude.- Enabling direct heat flux to internal unitsduring re-entry to facilitate demisability.

Description: Future platforms need to effectively demise during uncontrolled re-entriesinto the atmosphere at end-of-life disposal in order to comply with on-ground casualty risk requirements. A potential solution is to design platforms that deliberately disintegrate during the re-entry phase. One technique is to make use of demisable primary structure joints, able to produce an early break-up of the spacecraft. These joints are exposed to the atmosphere on the outside of the spacecraft and an early break-up of these will facilitate the separation of the spacecraft external panels and in turn maximise the exposure to the heat flux of the elements inside the platform in order to maximise their demise. This may enable compliance of the system with the on-ground casualty risk requirement. This activity will design, manufacture and test demisable joints. Demise testing will be conducted in a plasma wind tunnel to characterise the joints and compare the results with the predicted performances. Casualty risk budgets and system-level re-entry simulations associated with at least two different LEO satellite platforms will be carriedout. Trade-offs will be performed to identify the most promising demisable joint design for the selected platform. A simplified, scaled spacecraft primary platform structure implementing the selected demisable joint solution will be manufactured. Plasma wind tunnel and mechanical tests will be repeated with the simplified spacecraft primary platform structure in order to fully assess the demisable joint technology developed

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