The “new generation” of large satellites like ERS-1 requires modular thermal balance testing due to the physical size. The purpose of this paper is to outline the experience gained from the ERS-1 Payload Thermal Balance Test. The first part of the paper highlights the test set-up, the earthshine compensation and the selected test phases. The second part describes the temperature uncertainty approach and test correlation criteria defined for the thermal analyses and tests. The third part concentrates on the test correlation with emphasis on the thermo-optical properties of the Optical Solar Reflectors (OSRs) in the Xenon light of the simulated sun and the temperature dependent linear conductance of the honeycomb core material which played a crucial role in explaining a temperature level offset.
The paper is understood as complement to the paper presented in 1987 - Thermal Control and Design of the ERS-1 Payload -.
ERS-1 is the first
The programme is directed by the earth observation department of the
The West-German company Dornier GmbH has been awarded the prime contract to lead an industrial consortium existing of 12 European countries and Canada into the development and manufacturing of the advanced radar satellite.
The Dutch company Fokker Space and Systems has become responsible for the Payload Integration and the Thermal Control Subsystem.
In summer 1989 the
3.5 days for pump-down, back-out and cool-down
9.5 days for the TB part and
7.0 days for the TV part.
The bake-out phase at the beginning of the test was necessary to outgas the Payload Electronics Module (PEM) in order to minimize the risk of damaging the high power amplifiers by arcing.
This paper focusses on the Thermal Balance Test only.