PAGE CONTENTS
Objectives
The overall objective of the ARTES 5.2 activity was to establish TRL 5 for a HiPeR flexible film radiator based on the technology described above.
In particular, the activity was performed in two phases:
1 A bread board programme was aimed at establishing material properties after exposure to environmental conditions. In particular radiation exposure tests were performed during this phase on flight-standard coupons according to qualification levels.
2 A confidence test programme on a representative Engineering Model was aimed at establishing TRL 5. Focus was on mechanical (acoustic) and thermal tests.
SYSTEM ARCHITECTURE
As an illustration of the above, consider an example application where a “stood-off” radiator is needed which is required to be mounted on an existing S/C wall. Such applications occur frequently in science and/or EO missions where components require large dedicated radiator panels mounted on the S/C structure (e.g. the 2m2 ALADIN radiator on the Aeolus spacecraft or the 1.5m2 SORA radiators on the Solar Orbiter spacecraft). The HiPeR flexible film radiator system architecture is shown below in comparison to a conventional solution based on an aluminium sandwich panel. Clearly, the replacement of a relatively heavy aluminium sandwich panel by an equally- or better thermally conductive lightweight film offers a mass-benefit. In addition, the mounting of such a flexible film radiator is significantly simplified applying “MLI-like” standoffs in contrast to the heavy isostatic mounts required for a rigid panel.
Challenges
The key issues which the ARTES 5.2 programme has addressed were the following:
- Compatibility of the technology with the space environment, in particular radiation
- Thermal Performance of the HiPeR concept.
- Mechanical performance the HiPeR concept during launch loads (sine, random, acoustic).
Plan
The activity was kicked off at ESTEC premises on 17-09-2014.
Work until the BDR on 01-10-2014 focused on establishing a requirements baseline in collaboration with the end-user Airbus DS Toulouse and on the conceptual design of a HiPeR flexible film radiator.
From October to the MTR on 05-12-2014, work focused on performing breadboard tests and establishing the detailed design for the HiPeR Engineering Model EM-1.
After the EM-1 TRR on 09-04-2015, testing was performed including thermal balance testing, thermal cycling and acoustic noise testing.
The final project results will be presented at the Final Review.
Current Status
All project activities with exception of the Final Review (scheduled mid-September 2015) have currently been completed.
HiPeR has been shown to survive Sine-, Random and Acoustic noise environments corresponding to launch and the thermal- and radiation environment corresponding to 18 years in GEO orbit.
During TB testing it was found that thermal performance is above the predicted performance, validating the thermal design.
Also the market assessment and cost model for HiPeR radiators were updated taking into account the latest insights, confirming the validity of the business case and resulting in a follow-on proposal for ARTES 34 development.
Companies
