Abstract

A micro-flow throttling device, comprising: a casing used for assembling; a throttling structure mounted inside the casing to form resistance to control a fluid flow, wherein the throttling structure comprises a first axial hole formed inside a fine threaded rod, a first radial hole is formed on one side of the first axial hole, a fine thread flow channel is mounted on one side of the first radial hole, and a second cavity is formed between the fine thread flow channel and a coarse thread flow channel; a regulating structure mounted on the casing and used for regulating the flow rate of the fluid; and a butt-joint structure mounted on the inner wall of the casing and used for performing disassembly and assembly limiting on the throttling structure.

IPC Classes  ?

• F16K 17/20 - Excess-flow valves

Abstract

The present invention provides a space electric propulsion system and a xenon filling method therefor, suitable for a filling test of an electric propulsion system using high-purity xenon as a working medium. According to the present invention, by reasonably designing a filling process, the accuracy of a xenon filling amount is ensured, and xenon filling can be performed without weighing an entire satellite. The present invention has the advantages such as simple and efficient filling device, short filling preparation time, precisely controllable xenon filling process, and safety and convenience, and can effectively meet the requirements for a high-purity xenon rapid filling task of a satellite.

IPC Classes  ?

• F17C 5/06 - Methods or apparatus for filling pressure vessels with liquefied, solidified, or compressed gases for filling with compressed gases
• B64G 5/00 - Ground equipment for vehicles, e.g. starting towers, fuelling arrangements

Abstract

A cryogenic canned pump and a thermal insulation structure thereof. The cryogenic canned pump comprises an outer pump casing (11), an inner pump casing (12), and supports (4), wherein the outer pump casing (11) and the inner pump casing (12) are both cylindrical casings, the outer diameter of the inner pump casing (12) is less than the inner diameter of the outer pump casing (11), the outer pump casing (11) is sleeved outside the inner pump casing (12), and the outer pump casing (11) is connected to the inner pump casing (12) in a sealing manner to form a pump casing (1); and the supports (4) are supported between the outer pump casing (11) and the inner pump casing (12), the plurality of supports (4) are distributed along the circumference of the pump casing (1), a cooling flow channel (2) and a vacuum interlayer (3) are formed in a space in the pump casing (1), a cooling fluid is introduced into the cooling flow channel (2) to cool the pump casing (1), and the vacuum interlayer (3) is configured to reduce heat leakage from the outside into the pump casing (1).

IPC Classes  ?

• F04D 29/58 - CoolingHeatingDiminishing heat transfer
• F04D 29/42 - CasingsConnections for working fluid for radial or helico-centrifugal pumps
• F04D 29/44 - Fluid-guiding means, e.g. diffusers

Abstract

The present invention provides an iodine storage tank and electric propulsion. The iodine storage tank comprises a storage tank upper cover assembly, a storage tank lower shell assembly, and a solid iodine working medium. The storage tank upper cover assembly is sealedly connected to the storage tank lower shell assembly. The storage tank lower shell assembly is filled with the solid iodine working medium, a porous material plate is arranged on the side of the storage tank upper cover assembly connected to the storage tank lower shell assembly, one side of the porous material plate comes into contact with the solid iodine working medium, and a heater is installed on the other side of the porous material plate.

IPC Classes  ?

• F03H 1/00 - Use of plasma to produce a reactive propulsive thrust

Abstract

A magnetic pole structure for a Hall thruster is provided. The magnetic pole structure includes: multiple wide-envelope outer magnetic pole components, a magnetic bridge, a pagoda-shaped inner magnetic pole component, a top plate, and a bottom plate, where the multiple wide-envelope outer magnetic pole components are arranged on an outer edge of the Hall thruster, symmetrical about the pagoda-shaped inner magnetic pole component, and enclose a semi-open structure; the magnetic bridge is located between each of the wide-envelope outer magnetic pole components and the pagoda-shaped inner magnetic pole component; the bottom plate is attached to a bottom part of each of the wide-envelope outer magnetic pole components and a bottom part of the pagoda-shaped inner magnetic pole component; and the top plate is attached to an upper part of each of the wide-envelope outer magnetic pole components.

IPC Classes  ?

• F03H 1/00 - Use of plasma to produce a reactive propulsive thrust

Abstract

A cryogenic engine for a space apparatus is provided. The cryogenic engine includes an injector body, a thrust chamber, and a spark plug, where the injector body is provided therein with an accommodating space; the spark plug is provided on one side of the injector body, and an electrode provided on the spark plug extends into the accommodating space; the thrust chamber is provided on the other side of the injector body and is communicated with the accommodating space; the injector body is provided with a combustion improver flow channel and a combustible agent flow channel; and the combustion improver flow channel and combustible agent flow channel are connected with the accommodating space.

IPC Classes  ?

• F02K 9/52 - Injectors
• B64G 1/40 - Arrangements or adaptations of propulsion systems
• F02K 9/44 - Feeding propellants
• F02K 9/95 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof characterised by starting or ignition means or arrangements

Abstract

A micro-flow throttling device, comprising: a casing (2) used for assembling; a throttling structure (5) mounted inside the casing (2) to form resistance to control a fluid flow, wherein the throttling structure (5) comprises a first axial hole (501) formed inside a fine threaded rod (101), a first radial hole (6) is formed on one side of the first axial hole (501), a fine thread flow channel (11) is mounted on one side of the first radial hole (6), and a second cavity (15) is formed between the fine thread flow channel (11) and a coarse thread flow channel (12); a regulating structure (1) mounted on the casing (2) and used for regulating the flow rate of the fluid; and a butt-joint structure (17) mounted on the inner wall of the casing (2) and used for performing disassembly and assembly limiting on the throttling structure (5).

IPC Classes  ?

• F16K 17/20 - Excess-flow valves

Abstract

A magnetic pole structure for a Hall thruster. The magnetic pole structure comprises wide-envelope type outer magnetic pole components (1), a magnetic bridge (2), a pagoda-shaped inner magnetic pole component (3), an upper plate (4) and a bottom plate (7), wherein a plurality of wide-envelope type outer magnetic pole components are symmetrically distributed on the outer edge of the thruster with the pagoda-shaped inner magnetic pole component at the center to enclose a semi-open outer magnetic structure; the magnetic bridge is located between the wide-envelope type outer magnetic pole components and the pagoda-shaped inner magnetic pole component; the bottom plate is tightly attached to the bottoms of the wide-envelope type outer magnetic pole components and the pagoda-shaped inner magnetic pole component; and the upper plate is tightly attached to the upper portions of the wide-envelope type outer magnetic pole components. An outer magnetic pole expands in the circumferential direction, magnetic lines of force are guided into the upper plate and the bottom plate from a wider area to be dispersed on the surfaces of the upper plate and the bottom plate, and therefore, a wide-envelope type outer magnetic pole has a better magnetic field distribution uniformity.

IPC Classes  ?

• F03H 1/00 - Use of plasma to produce a reactive propulsive thrust

Abstract

A cryogenic engine suitable for a space apparatus, the engine comprising an injector body (1), a thrust chamber (2), and a spark plug (3). An accommodating space is provided in the injector body (1). The spark plug (3) is mounted on one side of the injector body (1), and an electrode (15) provided on the spark plug (3) extends into the accommodating space. The thrust chamber (2) is mounted on the other side of the injector body (1) and communicates with the accommodating space. The injector body (1) is provided with a combustion improver flow channel (11) and a combustible agent flow channel (12), and the combustion improver flow channel (11) and the combustible agent flow channel (12) are connected to the accommodating space.

IPC Classes  ?

• F02K 9/56 - Control