FIELD: rocket and space technology.
SUBSTANCE: invention relates to rocket and space technology, namely to propulsion systems. The device of the cooling system of the propulsion system includes a central body, a collector with a circulation scheme for the movement of a coolant with an emission to the environment, according to the invention, the central body consists of an electrically insulating element, an external anode, internal and external surfaces on which a thermal emission layer is applied, internal and external thermal emission the layers together with the central body form a cathode, which is electrically connected in series with the internal and external anodes through a voltage source, the internal anode is connected through electrically insulating elements to the internal thermionic layer of the cathode at a distance of up to 0.3 mm from the inner surface of the central body, the internal anode and the internal thermionic The cathode layer forms an evacuated hermetic cavity, inside which an additive from an easily ionizable element is placed, the evacuated hermetic cavity is connected through an electrically insulating element to an external anode, which is located along the cathode combustion products over the surface of the central body. Helium is used as a refrigerant. Cesium is used as an additive from an easily ionizable element.
EFFECT: invention provides a reduction in the mass of the refrigerant per unit time, as well as an increase in the reliability of a multi-chamber propulsion system with a central body due to its thermionic cooling.
3 cl, 1 dwg
Title | Year | Author | Number |
---|---|---|---|
COOLING SYSTEM OF THE CENTRAL BODY OF A MULTI-CHAMBER PROPULSION SYSTEM | 2022 |
|
RU2780911C1 |
COOLING SYSTEM OF THE CENTRAL BODY OF THE WEDGE-AIR JET ENGINE NOZZLE | 2022 |
|
RU2796360C1 |
COMPOSITE NOZZLE UNIT OF MULTI-CHAMBER PROPULSION INSTALLATION | 2021 |
|
RU2787634C1 |
Охлаждаемый составной сопловой блок многокамерной двигательной установки | 2021 |
|
RU2788489C1 |
COOLABLE GAS TURBINE BLADE | 2020 |
|
RU2749147C1 |
THERMIONIC METHOD FOR THERMAL PROTECTION OF AIRCRAFT | 2015 |
|
RU2583511C1 |
THERMIONIC ELECTRICITY GENERATING CHANNEL | 2013 |
|
RU2538768C1 |
APPARATUS FOR MEASURING THE TEMPERATURE OF THE NOZZLE OF A ROCKET ENGINE | 2021 |
|
RU2766960C1 |
HYPERSONIC AIRCRAFT WING IN AERODYNAMIC HEATING CONDITIONS | 2014 |
|
RU2572009C1 |
HYPERSONIC RAMJET ENGINE | 2017 |
|
RU2691702C2 |
Authors
Dates
2022-11-29—Published
2022-05-25—Filed