CN105156290A - Novel three-annulus mixed electric thruster - Google Patents

Abstract

The invention discloses a new three-ring hybrid electric thruster, through the mixed use of three thrusters, up to seven working modes can be realized, and corresponding working modes can be adopted according to different space propulsion requirements, on the one hand, it has good performance Range expansion, on the other hand, has good optimizeability combined with specific missions, so that the three-ring hybrid thruster has a wide range of application space; therefore, it can achieve a wide range of power, thrust, specific impulse range coverage and adjustment capabilities, Satisfies multi-purpose and wide mission; power ranges from the smallest kilowatts to the largest hundreds of kilowatts, and the specific impulse ranges from 2000 to 6000 seconds; (2) The three-ring mixed ion thruster of the present invention can solve the manufacturing, assembly, anti-corrosion and A series of problems such as mechanics and thermal stability have created conditions for the simultaneous realization of high power and high specific impulse.

Description

A New Three-ring Hybrid Electric Thruster

technical field

The invention relates to the technical field of spacecraft propulsion, in particular to a three-ring hybrid electric thruster for space.

Background technique

my country's future military and civil aerospace needs a new generation of space propulsion technology with high performance. Electric propulsion technology with high specific impulse is the main development direction. The maximum power of electric propulsion is tens of kilowatts, and there is still a large technical gap between hundreds of kilowatts and megawatts required for future large-scale spacecraft orbit transfer, manned spaceflight, and interstellar exploration; (2) Future space missions require Multi-mode electric propulsion systems, such as manned spaceflight and earth orbit transfer, need to shorten the cycle as much as possible to avoid the adverse effects of radiation environment, requiring electric propulsion to have a large thrust characteristic like Hall, while robotic interstellar exploration and HEO orbit maintenance need to save as much as possible The amount of propellant used to reduce mission costs requires electric propulsion to have high specific impulse properties like ions. In fact, a large number of space missions in the future require multi-mode electric propulsion systems to meet the needs of electric propulsion systems at different stages and achieve overall mission optimization; (3) the developing magnetoplasma power (MPD), variable ratio impulse ), pulse induction (PIT) and other electric propulsion types are suitable for missions with high power requirements, but there is still a big gap in technological maturity, especially the long-life problem is still hopeless.

Contents of the invention

In view of this, the present invention provides a three-ring hybrid electric thruster for space, which overcomes the shortcomings of the existing mature ion and Hall electric thrusters, and realizes high power, multi-mode and long life of the electric thruster.

In order to solve the problems of the technologies described above, the present invention is achieved in that:

A three-ring hybrid electric thruster, three coaxial annular cavity structures are sequentially processed from the inside to the outside on the installation base, which are respectively defined as the first, second and third annular cavity structures;

The neutralizer cathode is fixedly installed in the middle of the top of the first annular cavity structure, and two Hall component anodes are symmetrically arranged at the bottom of the annular cavity, thereby forming a Hall component;

The cavity bottom of the second annular cavity structure is symmetrically arranged with two main cathodes of the first ion assembly, the circumferential direction of the annular cavity is arranged with permanent magnets, and the first ion assembly grid is arranged above the opening of the annular cavity, thereby forming a first ionic assembly;

The cavity bottom of the third annular cavity structure is symmetrically arranged with two second ion assembly main cathodes, the circumferential direction of the annular cavity is arranged with permanent magnets, and the second ion assembly grid is arranged above the opening of the annular cavity, thus A second ionic assembly is formed.

When the inner diameter of the annular discharge chamber of the Hall assembly is 15cm, the power is 5kW, the outer diameter of the annular discharge chamber of the first ion assembly is 30cm, the power is 10kW and the outer diameter of the annular discharge chamber of the second ion assembly is 45cm 1. When the power is 10kW, the mixed ion thruster also includes the second neutralizer cathode and the third neutralizer cathode, both of which are cylindrical, symmetrical along the direction parallel to the generatrix of the cylindrical shape of the second ion assembly placed outside it.

The neutralizer cathode is inlaid on the top of the first annular cavity structure, and the neutralizer cathode can move up and down along the central axis of the first annular cavity structure, and its moving distance is within 2cm.

Beneficial effect:

(1) The three-ring mixed ion thruster of the present invention can realize up to seven working modes through the mixed use of three thrusters, and adopt corresponding working modes according to different space propulsion requirements, on the one hand, it has a good performance range Scalability, on the other hand, has good optimizeability combined with specific missions, so that the three-ring hybrid thruster has a wide range of application space; therefore, it can achieve a wide range of power, thrust, specific impulse range coverage and adjustment capabilities to meet Multi-purpose and wide mission; power range from minimum kilowatts to maximum hundreds of kilowatts, specific impulse range 2000-6000 seconds;

(2) The three-ring mixed ion thruster of the present invention can solve a series of problems such as the manufacture, assembly, mechanical resistance, and thermal stability of large-scale grids, creating conditions for simultaneously realizing high power and high specific impulse;

(3) The three-ring mixed ion thruster of the present invention is composed of a Hall thruster and an annular ion thruster. Since both thrusters have a relatively mature technical foundation, the cost, period, and risk of development can be reduced.

Description of drawings

Fig. 1 is a schematic cross-sectional structure diagram of a three-ring hybrid electric thruster of the present invention.

Fig. 2 is a schematic diagram of a three-ring hybrid electric thruster with two neutralizing cathodes in the present invention.

Among them, 1-first ion component grid, 2-second ion component II grid, 3-neutralizer cathode, 4-ion component I, 5-ion component I main cathode, 6-ion component II, 7- Ion component II main cathode, 8-permanent magnet, 9-Hall component anode, 10-Hall component, 11-installation base, 12-second neutralizer cathode, 13-third neutralizer cathode.

Detailed ways

The present invention will be described in detail below with reference to the accompanying drawings and examples.

A three-ring hybrid electric thruster, three coaxial annular cavity structures are sequentially processed on the installation base 11 from the inside to the outside, which are respectively defined as the first, second and third annular cavity structures;

The neutralizer cathode 3 is fixedly installed in the middle of the top of the first annular cavity structure, and two Hall element anodes 9 are symmetrically arranged at the bottom of the annular cavity, thus forming the Hall element 10; the cavity bottom of the second annular cavity structure is symmetrical to the center Two first ion assembly main cathodes 5 are arranged, permanent magnets 8 are arranged in the circumferential direction of the annular cavity, and the first ion assembly grid 1 is arranged above the opening of the annular cavity, thus forming the first ion assembly 4; Two second ion component main cathodes 7 are symmetrically arranged in the center of the cavity bottom of the three-ring cavity structure, permanent magnets 8 are arranged in the circumferential direction of the ring cavity, and the second ion component grid 2 is arranged above the opening of the ring cavity, thereby The second ion assembly 6 is formed.

The neutralizer cathode is inlaid on the top of the first annular cavity structure, and the neutralizer cathode 3 can move up and down along the central axis of the first annular cavity structure, and its moving stroke is within 2cm.

The Hall assembly 10, the first ion assembly 4 and the second ion assembly 6 can work alone or in combination as three thrusters. Assuming that each thruster has only one working mode, the three-ring hybrid electric thruster can realize seven kinds of work Mode, respectively, the first ion assembly 4 works alone, the second ion assembly 6 works alone, the Hall assembly 10 works alone, the first ion assembly 4 and the second ion assembly 6 work together, and the first ion assembly 4 and the Hall assembly work together Work, the joint work of the second ion assembly 6 and the Hall assembly 10 and the joint work of the three electric thrusters. The corresponding working mode is adopted according to different space propulsion requirements. Therefore, the three-ring hybrid electric thruster has a wide application space.

As shown in Figure 2, the three-ring mixed ion thruster power of the present invention will reach 30kW, and wherein the diameter of Hall assembly 10 is 15cm, and its power is 5kW, and the outer diameter of the first ion assembly 4 in the middle is 30cm, and its power is 10kW, the outer diameter of the second ion component 6 of the outer ring is 45cm, and the power is 15kW.

The function of the cathode 3 of the neutralizer mainly includes two negative aspects: one is to prevent the establishment of a high potential in the beam current, so that the motion of the ions is reversed, so that the thrust disappears; the other is to maintain the electrical neutrality of the spacecraft. For the three-ring hybrid thruster, the layout of the cathode 3 of the neutralizer should consider both the simplicity of the structure and the effect of neutralization. Therefore, the neutralizer layout scheme of the 30kW hybrid thruster is to arrange a neutralizer cathode 3 on the axis of the thruster, and the neutralizer cathode 3 is used to neutralize the beam current of the inner ring Hall assembly 10 and the intermediate ring first For the beam current of an ion assembly 4, since the diameter of the second ion assembly 6 of the outer ring reaches 45 cm, it is difficult for the neutralizer cathode 3 to effectively neutralize the beam current, so two symmetrical layouts are arranged outside the second ion assembly 6 of the outer ring. The neutralizer cathode is respectively a cylindrical second neutralizer cathode 12 and a third neutralizer cathode 13, both of which are symmetrically arranged on the outside along the direction parallel to the generatrix of the cylindrical shape of the second ion assembly 6, the two A neutralizer cathode is used to neutralize the beam current of the second ion assembly 6 .

To sum up, the above are only preferred embodiments of the present invention, and are not intended to limit the protection scope of the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention shall be included within the protection scope of the present invention.

Claims (3)

1. three ring mixing electric thruster, is characterized in that, mounting base (11) are processed with from inside to outside successively three coaxial toroidal cavity structures, are defined as first, second, and third ring cavity structure respectively;

Top middle portion position fixed installation neutralizer negative electrode (3) of described first ring cavity structure, toroidal cavity bottom symmetrical arranges two Hall subassembly anodes (9), forms Hall subassembly (10) thus;

The cavity bottom Central Symmetry of described second ring cavity structure arranges two the first deionization unit main cathodes (5), the circumferentially permanent magnet (8) of this toroidal cavity, the overthe openings of toroidal cavity arranges the first deionization unit grid (1), forms the first deionization unit (4) thus;

The cavity bottom Central Symmetry of described 3rd ring cavity structure arranges two the second deionization unit main cathodes (7), the circumferentially permanent magnet (8) of this toroidal cavity, the overthe openings of toroidal cavity arranges the second deionization unit grid (2), forms the second deionization unit (6) thus.

2. a kind of three ring mixing electric thruster as claimed in claim 1, it is characterized in that, internal diameter when the ring discharge room of described Hall subassembly (10) is 15cm, power is 5kW, the external diameter of the ring discharge room of the first deionization unit (4) is 30cm, power is 10kW and the external diameter of the ring discharge room of the second deionization unit (6) is 45cm, when power is 10kW, described hybrid ionic thruster also comprises and is columned second neutralizer negative electrode (12) and the 3rd neutralizer negative electrode (13), both are arranged symmetrically in outside it along the direction parallel with the bus of the cylindrical shape of the second deionization unit (6).

3. a kind of three ring mixing electric thruster as claimed in claim 1, it is characterized in that, described neutralizer negative electrode (3) is embedded in the top of described first ring cavity structure, and neutralizer negative electrode can move up and down along the central axis of the first ring cavity structure, and its shift motion is within 2cm.