FIELD: astronautics.
SUBSTANCE: invention relates to space technology, or more precisely to a supply block of a working fluid (WF), for example, xenon, into a jet engine of a spacecraft (SC). Supply block of the working fluid to the jet engine of the spacecraft, containing a high-pressure balloon, filled with WF, for example xenon, and having a high-pressure output manifold with a filler neck and associated with two parallel depressing manifolds, which outputs are associated with the jet engine through a receiver made with external insulation, as well as a high-pressure output manifold, made with an electric heater, controlled by a control unit for the temperature sensor, and each of which contains a sequentially-connected on-off valve, functionally associated with the control unit and the pressure reducer, the external insulation of the high pressure manifold and the receiver. In the proposed device, each additional pressure reducing manifold includes, respectively, an additional on-off valve, functionally associated with the control unit and the pressure reducer, respectively, before the main on-off valve and the pressure reducer, wherein said sections of each of the pressure-reducing manifolds between their additional and main reducers are made with one common heat supply device simultaneously from the electric heater, controlled by the control unit by its temperature sensor and from one common for both said of the manifolds sections of the condenser of the heat pipe, the evaporator of which is connected in thermal relation with the high-pressure cylinder, the heat pipe is made with external heat insulation along its entire length, as well as the structural elements of the device with which it is thermally connected. Condenser of the heat pipe is also thermally connected with the receiver.
EFFECT: invention provides an increase in the reliability of the device while improving its overall mass characteristics.
1 cl, 1 dwg
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RU2487291C2 |
Authors
Dates
2018-04-23—Published
2016-02-12—Filed