CONTRIBUTION OF OERLIKON-CONTRAVES, SPACE DIVISION The conceptually simplest omnidirection-receiving object is obviously a sphere. However, an integral design of an inflatable, space rigidized structure (ISRS) supporting the sensing elements is not feasible. It is expected that the structural support has to be a good dielectric to allow proper working of the receiving elements for the microwave radiation. But such a fully dielectric sphere cannot be properly conditioned for the thermal cure process characteristic of OC’s approach. Under the most favourable conditions (illumination from the Sun, Earth’s albedo and own irradiance) such a structure would have an average temperature around 320 K, with strong gradients characteristic of spherical geometry/ (For cure, temperatures above 380 K are needed.) Therefore, a separation of the structure and sensing elements is necessary. The simplest such concept is provided by what has been dubbed the Planar Instrument Carrier (PIC), consisting of a toroidal IS RS frame deploying and supporting a membrane with the sensing elements. In the present case, the membrane could be a Kapton sheet with a microstrip-technology rectenna. A preliminary look at what could be packaged for deployment from a GAS- canister (assumed to provide a 47-1 usable volume) shows that a five meter torus, with an 18-m2 sensor surface, could be provided. Mass would be less than 3 kg for the expandable elements, plus a similar amount for pressurisation, to which one has obviously to add all the experiment’s hardware. Generally, deployment from a GAS can is considered an inefficient approach for a mission, such as the one under consideration, that requires
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