Abstract: Provided is a deployable reflector that includes a reflector, a tensioning frame with a deploying ring including upper booms and lower booms, sections composed of lower rods and upper rods and including pantograph levers, stanchions mounted between the upper booms and the lower booms, scissors-like levers located at an intersection of the pantograph levers, first sleeves put on the pantograph levers, second sleeves disposed on the lower rods and the upper rods, cylindrical joints disposed on the second sleeves, an expansion ring for connecting the upper rods and the lower rods, a reflector fixing mesh having triangular cells composed of elastic rods, an upper concave mesh and a lower convex mesh fastened with peripheral units and composed of triangular shape cells, where the reflector is attached to the upper concave mesh directly or is fastened to the upper concave mesh with a spatial shape gasket.

Abstract: An integrated nozzle set for injecting a substance into a turbine is provided. The nozzle set includes an outer nozzle container arranged around a part of a circle and an inner nozzle container having a first part arranged around a remaining part of the circle and a second part concentric with the outer nozzle container. The nozzle set further includes a diaphragm connected to the inner nozzle container and configured to seal a cavity of the turbine, a flange having spokes connected to the inner nozzle container, a set of nozzles, and collectors inserted into the outer nozzle container and configured to collect a substance. The nozzles include a first group of nozzles disposed in the outer nozzle container, a second group of nozzles disposed in the first part of the inner nozzle container, and a third group of nozzles disposed in the second part of the inner nozzle container.

Abstract: A solenoid valve assembly is provided. The solenoid valve assembly includes a pilot assembly, a body, and a main poppet valve assembly. The pilot assembly includes a frame having an external wall and an internal wall forming an annular cavity. The body includes an inlet cavity, a channel, an outlet cavity, and a main poppet valve seat disposed in the channel between the inlet cavity and the outlet cavity. The main poppet valve assembly includes a main poppet valve and two movable sealing elements. The main poppet valve has a cylindrical shape having an internal diameter, an external diameter, and grooves. The main poppet valve is at least partially disposed in the annular cavity and configured to shut the main poppet valve seat. The movable sealing elements are disposed in the grooves to seal the main poppet valve to the external wall and the internal wall of the frame.

Abstract: A heater for a hollow cathode and a method for manufacturing the heater for the hollow cathode are provided. An example heater includes a tube and a thickening located at an edge of the tube. The tube has a side wall of a predetermined thickness and a cut in the side wall. The thickening is configured for attaching two electrical current leads. The tube and the thickening are made of a carbon fiber composite.

Abstract: A method for heat-resistant protection of machinery components made of metal alloy is provided. The method includes preparing a surface of the machinery component to remove impurities, applying at least one layer of a coating composition to the surface of the machinery component, and drying the layer prior to applying a next layer of the coating composition to the surface. The coating composition includes a clay deposit, a polyvinyl alcohol solution, a distilled water, and a mixture including, by weight, from 40% to 60% of nickel, from 5% to 7% of chromium, from 12% to 15% of silicon, from 6% to 8% of titanium diboride, from 3% to 13% of barium oxide, from 1% to 10% of boron oxide, and from 4% to 6% by weight of silicon oxide, up to 2% of molybdenum disilicide, up to 5% of zinc oxide, and up to 2% of magnesium oxide.

Abstract: Provided is a pressure vessel. An example pressure vessel includes a spherical portion and a conical portion that extends from the spherical portion and has an opening for pumping in and pumping out a pressurized gaseous substance. The spherical portion and the conical portion are made in a single technological cycle by 3D printing. The thicknesses of the wall of the spherical portion changes from ? 1 = P ? R 1 2 ? [ ? ] to ? 2 = 3 ? P ? R 2 2 ? [ ? ] ? ? cos ? ? ? and the thickness of the wall of the conical portion changes linearly from ?2 to ? 3 = 3 ? P ? R 3 2 ? [ ? ] ? ? cos ? ? ? , where P is predetermined operating pressure, R1 is a radius of the spherical portion, R2 is a radius of a base of the conical portion, R3 is a radius of the opening of the conical portion, [?] is an allowable material stress, and a is an angle between a generatrix and a symmetry axis of the conical portion.

Abstract: A method for heat-resistant protection of machinery components made of metal alloy is provided. The method includes preparing a surface of the machinery component to remove impurities, applying at least one layer of a coating composition to the surface of the machinery component, and drying the layer prior to applying a next layer of the coating composition to the surface. The coating composition includes a clay deposit, a polyvinyl alcohol solution, a distilled water, and a mixture including, by weight, from 40% to 60% of nickel, from 5% to 7% of chromium, from 12% to 15% of silicon, from 6% to 8% of titanium diboride, from 3% to 13% of barium oxide, from 1% to 10% of boron oxide, and from 4% to 6% by weight of silicon oxide, up to 2% of molybdenum disilicide, up to 5% of zinc oxide, and up to 2% of magnesium oxide.

Abstract: Methods and systems for electric propulsion are provided. An example method includes providing a magnetic shield using an accelerating channel made of a soft magnetic material; generating, by a magnetic system, a radial magnetic field in the accelerating channel to ionize a working substance, wherein the magnetic system includes a central magnetic pole, an outer annular pole, a magnetic circuit, and coils to carry an electrical current; and generating, using an outer hollow cathode and an anode-gas distributor disposed within the accelerating channel, an electrical discharge along the accelerating channel. The accelerating channel provides the magnetic shield to force the radial magnetic field to have a maximum gradient at a location of the central magnetic pole and at a location of the outer annular pole and to force ions of a working substance to pass isolators of magnetic poles, thereby decreasing erosion of the isolators.

Abstract: Methods and systems for a discharge power supply for providing a stabilized discharge power to a Hall-effect thruster are provided. A method includes sensing, by a first sensor circuit and based on a discharge power, a voltage sense signal, sensing, by a second sensor circuit and based on the discharge power, a current sense signal, multiplying, by a multiplying circuit, the voltage sense signal and the current sense signal to generate a feedback signal, generating, by a control logic circuit and based on control signals, further control signals, generating, by an impulse generation circuit and based on the further control signals and the feedback signal, control impulses, producing, by a transistor bridge and using the control impulses and a power source, an electrical impulses, and modifying, by an output circuit, the electrical impulses to generate the stabilized discharge power.