ArianeGroup

The present disclosure relates to a radio frequency, RF, coaxial cable to be used in an environment requiring transmission of a high alternating current, AC, with a high frequency, the RF coaxial cable comprising a single hollow inner conductor comprising a flexible metallic shielding. The present disclosure also relates to an RF coaxial cable to be used in an environment requiring transmission of a high AC with a high frequency, the RF coaxial cable consisting of a single hollow inner conductor comprising a flexible metallic shielding, an insulator on the single hollow inner conductor, an outer conductor on the insulator, wherein the outer conductor is formed of a second flexible metallic shielding, an outer sleeve on the outer conductor and an electromagnetic compatibility, EMC, overbraid on the outer sleeve.

Disclosed is a spacecraft propulsion system comprising a propellant tank (11, 12), a main engine (50), an evaporator unit (27, 28), and a boost pump (13, 14). The main engine (50) comprises a thrust chamber (1), a nozzle (2), and a powerpack including a main turbopump unit (MTP, MTP<F>, MTP<O>). The evaporator unit (27, 28) is configured to vaporise liquid propellant (7, 8) to be supplied to a reaction control system (RCS, 101, 102, 103, 104) of the spacecraft. The boost pump (13, 14) is configured to feed both the main turbopump unit (MTP, 3, 4) and the evaporator unit (27, 28) with propellant (7, 8) originating from the propellant tank (11, 12). Preferably, the boost pump is configured to be driven with energy transmitted, from a turbine (17, 18) integrated in an autogenous tank pressurisation system. Further disclosed is a spacecraft comprising such propulsion system.

A storage system for a cryogenic liquid in an in-space application is provided. The system comprises a storage tank for storing the cryogenic liquid, the storage tank having an outlet for discharging boil-off gas into a boil-off gas line and an inlet for introducing re-liquefied cryogenic liquid, and a cooling section for carrying a cooling medium. The cooling section comprises a space background cooling radiator for radiating heat from the cooling medium into space, the space background cooling radiator being configured to cool down the cooling medium, and a cooling element configured to carry the cooling medium after having passed the space background cooling radiator. The cooling element is in thermal contact with the boil-off gas discharged from the storage tank. The cooling element is configured to cool down the boil-off gas. The cooling section is configured to at least partially re-liquefy the cooled down boil-off gas to become the re-liquefied cryogenic liquid introduced via the inlet into the storage tank. Further, a corresponding method is provided.

Offenbart ist eine Separationsvorrichtung für einen kryogenen Treibstofftank einer Raketenstufe, indem ein zum Kleintriebwerk führender Nebenstrom baulich von einem Hauptstrom zu einem Haupttriebwerk getrennt ist, wobei im Einlassbereich des Nebenstromes eine fächerförmige Innenstruktur angeordnet ist, die die kryogene Flüssigkeit durchströmen muss, um zum Kleintriebwerk zu gelangen und die derart ausgeführt ist, dass sie sich zum einen in Schwerelosigkeit bzw. bei nur geringer Beschleunigung mit Flüssigkeit füllt als auch während des Betriebes des Kleintriebwerks unter Beschleunigung, sowie ein Treibstofftank für kryogene Treibstoffe.

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