Periodic Reporting for period 2 - PEGASUS (Flight Qualification of Deployable Radiator using Two Phase Technology)
Période du rapport: 2016-07-01 au 2018-09-30
Satellite payload capability implies higher power dissipation, which is rejected to space by means of larger and more efficient radiators.
The main objective of the Pegasus project is to qualify a Deployable Radiator (DPR) based on Loop Heat Pipes. Loop Heat Pipes Two-phase technology is the enabling technology for achieving the product of Deployable Radiator because it is the most suitable solution for transportation of the heat from the source to the radiator. Even more, it is needed the use of LHP with flexible lines/hoses in order to allow deployment of the panel. The DPR product has been developed so modularity and scalability (up or down) has been guaranteed. The reason to provide scalability and a modular design is that the DPR can be used in application other than telecom (i.e Low Earth Orbit (LEO) such as Earth Observation or scientific) and in several platforms, including full electric. Additionally, the proposed design provides a solution flexible enough to adapt this technology to different heat transport systems such as Loop Heat Pipes (using direct or indirect condensation) and Mechanical Pumped Loops (MPLs).
The main objective of the Pegasus project is to qualify a Deployable Radiator (DPR) based on Loop Heat Pipes. Loop Heat Pipes Two-phase technology is the enabling technology for achieving the product of Deployable Radiator because it is the most suitable solution for transportation of the heat from the source to the radiator. Even more, it is needed the use of LHP with flexible lines/hoses in order to allow deployment of the panel. The DPR product has been developed so modularity and scalability (up or down) has been guaranteed. The reason to provide scalability and a modular design is that the DPR can be used in application other than telecom (i.e Low Earth Orbit (LEO) such as Earth Observation or scientific) and in several platforms, including full electric. Additionally, the proposed design provides a solution flexible enough to adapt this technology to different heat transport systems such as Loop Heat Pipes (using direct or indirect condensation) and Mechanical Pumped Loops (MPLs).
Several DPR hardware models have been manufactured according to the resulting design.
DPR EM manufactured and successfully tested. LHP showed a stable performance during all tests being able to transport the requested 1000w along the operating temperature range.
DPR QM manufactured, integrated (thermal configuration) and successfully tested. Thermal performance tests were conducted in-orbit environment, where main performance parameter – heat rejection capability – has been verified in worst conditions (hot environment, maximum power and failure configuration)
Deployment mechanism EM as planned, and QM successfully manufactured and tested.
New material Cr(VI) free development achieved
Surtec 650 was successfully tested accoding to the evaluation and qualification protocols.
MAP EPOX11 was successfully tested accoding to the evaluation and qualification protocols
LEO Radiator panel for LEO applications designed, developed and successfully tested. Analysis and test results confirmed that LEO DPR Is able to reject 220 W with working fluid at 25ºC and external sink temperature at -60ºC. The thermal performance and mass density are competitive with those of similar products.
Main dissemination activities related to this project are as follows:
- Deployable radiator technology presentation at the following conferences and congress CCPIF, KTD and ICES.
- Replacement alodine 1200S congress at ASST 2018 and STM-32.
DPR exploitation has a high potential due to market competitiveness to increase mission capability to cope with very power demanding satellites. DPR mandatory to cover certain power demanding missions. Also allows to come with future power demand increases and permits the use of existing platforms for high performance missions without the need to entirely redesign the satellite’s architecture.
DPR EM manufactured and successfully tested. LHP showed a stable performance during all tests being able to transport the requested 1000w along the operating temperature range.
DPR QM manufactured, integrated (thermal configuration) and successfully tested. Thermal performance tests were conducted in-orbit environment, where main performance parameter – heat rejection capability – has been verified in worst conditions (hot environment, maximum power and failure configuration)
Deployment mechanism EM as planned, and QM successfully manufactured and tested.
New material Cr(VI) free development achieved
Surtec 650 was successfully tested accoding to the evaluation and qualification protocols.
MAP EPOX11 was successfully tested accoding to the evaluation and qualification protocols
LEO Radiator panel for LEO applications designed, developed and successfully tested. Analysis and test results confirmed that LEO DPR Is able to reject 220 W with working fluid at 25ºC and external sink temperature at -60ºC. The thermal performance and mass density are competitive with those of similar products.
Main dissemination activities related to this project are as follows:
- Deployable radiator technology presentation at the following conferences and congress CCPIF, KTD and ICES.
- Replacement alodine 1200S congress at ASST 2018 and STM-32.
DPR exploitation has a high potential due to market competitiveness to increase mission capability to cope with very power demanding satellites. DPR mandatory to cover certain power demanding missions. Also allows to come with future power demand increases and permits the use of existing platforms for high performance missions without the need to entirely redesign the satellite’s architecture.
1. Increase the maturity of thermal management components for spacecraft.
2. Qualify a European supplier for space critical technologies.
3. Integrate a European supply chain
4. Promote the number of Small Companies in space activities
5. Provide validated space technologies for spin-off in non-space sectors.
6. Develop a commercial evaluation of the technology, and address how to access the commercial market.
2. Qualify a European supplier for space critical technologies.
3. Integrate a European supply chain
4. Promote the number of Small Companies in space activities
5. Provide validated space technologies for spin-off in non-space sectors.
6. Develop a commercial evaluation of the technology, and address how to access the commercial market.