CN111140447A - Vector magnetic nozzle for electric propulsion comprising a bypass electromagnetic coil - Google Patents
Vector magnetic nozzle for electric propulsion comprising a bypass electromagnetic coil Download PDFInfo
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- CN111140447A CN111140447A CN201911334628.4A CN201911334628A CN111140447A CN 111140447 A CN111140447 A CN 111140447A CN 201911334628 A CN201911334628 A CN 201911334628A CN 111140447 A CN111140447 A CN 111140447A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H—PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H1/00—Using plasma to produce a reactive propulsive thrust
- F03H1/0081—Electromagnetic plasma thrusters
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K44/00—Machines in which the dynamo-electric interaction between a plasma or flow of conductive liquid or of fluid-borne conductive or magnetic particles and a coil system or magnetic field converts energy of mass flow into electrical energy or vice versa
- H02K44/02—Electrodynamic pumps
- H02K44/04—Conduction pumps
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- Combustion & Propulsion (AREA)
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- Plasma & Fusion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Plasma Technology (AREA)
Abstract
The invention provides a vector magnetic nozzle for electric propulsion comprising a bypass electromagnetic coil. The vector magnetic nozzle includes: an electric thruster for generating a plasma jet; a main coil having an inner bore; and a plurality of side electromagnetic coils which are uniformly arranged in the inner hole of the main coil, the size of the side electromagnetic coils is smaller than that of the inner hole of the main coil, the axis of each side electromagnetic coil is parallel to the axis of the electric thruster, the side electromagnetic coils are respectively electrified with exciting currents with different magnitudes and directions and are superposed on the magnetic field generated by the main coil to generate an asymmetric vector magnetic nozzle, and then a plasma stream discharged from the electric thruster is guided to expand and accelerate along a required direction to generate a required thrust vector.
Description
Technical Field
The present invention relates to an electrically propelled vectored magnetic nozzle for a spacecraft, and in particular to a vectored magnetic nozzle comprising a by-passed electromagnetic coil.
Background
The on-orbit propulsion technology of the spacecraft is various, and the chemical propulsion and the electric propulsion are most widely applied at present. The chemical propulsion is the most mature and is the propulsion technology which is most applied to the spacecraft in China at present. Compared with chemical propulsion, electric propulsion has the advantages of reducing the propellant required to be filled, prolonging the working time and the like. With the development of electric propulsion technology, more and more space vehicles, such as satellites and the like, are also being equipped with electric propulsion systems.
The electric propulsion system comprises a magnetic nozzle. Magnetic lines of force without physical boundaries produce a nozzle effect, known as a magnetic nozzle, that confines and accelerates charged particles. The magnetic field distribution which is symmetrical about the axis of the thruster can realize the acceleration effect on the plasma, and the plasma is separated from the magnetic field under certain conditions after the acceleration is finished to generate the thrust. The correct use of the magnetic nozzle can improve the performance of the electric thruster, which is widely applied in many electric thrusters, such as an additional magnetic field magnetic plasma thruster (AF-MPDT), a variable specific impulse plasma rocket (VASIMR), a helicon wave plasma thruster (HPT), and the like.
The spacecraft is often required to control a thrust vector to meet requirements of attitude control and orbit correction during working, and the direction control of the thrust vector is very important for the control. The thrust vector is usually controlled by installing more thrusters on the spacecraft according to corresponding required directions or by turning a nozzle of the thrusters or the thrusters themselves by using mechanical devices. Such a conventional thrust vector control approach not only increases the weight of the system but also increases the complexity of the system, which is detrimental to the operation of the spacecraft.
Disclosure of Invention
In view of the above problems, the present invention is directed to a magnetic nozzle structure, which can control the thrust vector of an electric thruster and improve the thrust by adjusting an asymmetric magnetic field generated by a current without moving parts.
To achieve the above object, one embodiment of a vector magnetic nozzle for electric propulsion including a bypass electromagnetic coil according to the present invention includes: an electric thruster for generating a plasma jet; a main coil having an inner bore; and a plurality of side electromagnetic coils which are uniformly arranged in the inner hole of the main coil, the size of the side electromagnetic coils is smaller than that of the inner hole of the main coil, wherein the axes of the side electromagnetic coils are parallel to the axis of the electric thruster, the side electromagnetic coils are respectively electrified with exciting currents with different magnitudes and directions and are superposed on the magnetic field generated by the main coil to generate an asymmetric vector magnetic nozzle, and then the plasma jet flow discharged from the electric thruster is guided to expand and accelerate along a required direction to generate a required thrust vector.
In an alternative embodiment, the vector magnetic nozzle comprises four side electromagnetic coils, and the four side electromagnetic coils are in central symmetry, and the symmetry center of the four side electromagnetic coils is coincident with the center of an outlet plane of the electric thruster.
In another alternative embodiment, the bypass solenoids included in the vectored magnetic nozzle are the same size as each other.
In another alternative embodiment, the bypass electromagnetic coil and the main coil are fixed by welding.
In yet another alternative embodiment, the bypass electromagnetic coil is a superconducting coil.
In a further alternative embodiment, the main configuration of the magnetic nozzle is produced by a larger main coil, the magnetic nozzle formed by the coil being distributed axially symmetrically with respect to the thruster axis. Four small side coils are arranged in four directions perpendicular to each other in an inner hole of the main coil, the side coils are parallel to the central axis of the main coil, a magnetic nozzle structure which is asymmetric about the axis of the thruster can be obtained by adjusting the directions and the sizes of exciting currents in the four side coils, and the combined coil is arranged at a beam outlet of an electric thruster, so that plasma can be guided to expand and deflect along the direction of the axis of the magnetic nozzle, and thrust vector control is realized. In the generated expanded magnetic field, due to the effects of bipolar electric field acceleration, a reverse magnetic mirror effect, angular current acceleration and the like, the ion velocity in the beam current of the thruster is greatly improved, and the performance of the thruster is improved.
The invention has the advantages that:
1. the thrust vector can be controlled only by adjusting the exciting current in the coil without moving parts, so that the integrity and the reliability of the system are improved;
2. the weight burden caused by using a plurality of thrusters is avoided, the launching cost of the spacecraft is reduced, and the effective load ratio is increased;
3. the kinetic energy of the plasma beam of the thruster, which is perpendicular to the thrust vector direction, is converted into the kinetic energy parallel to the thrust vector direction by using the magnetic nozzle effect, so that the propelling performance in the required direction is improved.
Drawings
The invention is further illustrated by the following examples in conjunction with the accompanying drawings:
FIG. 1 is a schematic diagram of a vector magnetic nozzle for electric propulsion including a side coil, according to an embodiment of the present invention.
The reference numerals in the figures denote the following parts,
1. electric thruster
2. Main coil
3. First side-set electromagnetic coil
4. Second side electromagnetic coil
5. Third side electromagnetic coil
6. The fourth side is provided with an electromagnetic coil.
Detailed Description
The following detailed description of embodiments of the invention refers to the accompanying drawings. Certain terminology is used herein for convenience only and is not to be taken as a limitation on the present invention. For example, terms such as "upper," "lower," "left," "right," "horizontal," "vertical," "upward," and "downward" merely describe the configuration shown in the figures. Indeed, the components may be oriented in any direction and the terminology, therefore, should be understood as encompassing all such variations unless specified otherwise. In this specification, the word "comprising" is to be understood in its "open" sense, i.e. having the meaning of "and therefore should not be taken to be limited to the" closed "sense, i.e. to the meaning of" including only ". The corresponding meaning also applies to the corresponding words "comprising", "including", etc. Although expressions such as "1 st", "2 nd", "first" and "second" may be used to describe the respective elements of the present invention, they are not intended to limit the corresponding elements. For example, the above expressions are not intended to limit the order or importance of the corresponding elements. The above description is only intended to distinguish one element from another.
FIG. 1 is a schematic diagram of a vector magnetic nozzle for electric propulsion including a side coil, according to an embodiment of the present invention. Referring to fig. 1, a vectored magnetic nozzle for electric propulsion including a side coil in accordance with one embodiment of the present invention comprises: an electric thruster 1 for generating a plasma jet, a main coil 2 having an inner bore, and at least one side electromagnetic coil arranged around the electric thruster 1 in the inner bore of the main coil 2. The size of the bypass electromagnetic coil is smaller than the size of the inner hole of the main coil 2, so that the bypass electromagnetic coil is arranged in the inner hole. In the embodiment shown in the figure, four bypass solenoids, a first bypass solenoid 3, a second bypass solenoid 4, a third bypass solenoid 5, and a fourth bypass solenoid 6, are provided, symmetrically arranged around the main coil 2 and evenly distributed. Although not shown, it should be understood that the number of bypass solenoids may be increased or decreased as desired, and is not limited to the four bypass solenoids shown in the drawings.
The first bypass electromagnetic coil 3, the second bypass electromagnetic coil 4, the third bypass electromagnetic coil 5 and the fourth bypass electromagnetic coil 6 are respectively annular ordinary electromagnetic coils or superconducting coils, and the ordinary coils can be subjected to heat protection by adding internal forced water cooling. The first bypass solenoid coil 3, the second bypass solenoid coil 4, the third bypass solenoid coil 5, and the fourth bypass solenoid coil 6 may be provided to have substantially the same size. The first bypass electromagnetic coil 3, the second bypass electromagnetic coil 4, the third bypass electromagnetic coil 5, the fourth bypass electromagnetic coil 6 and the main coil 2 can be fixed through welding and the like, the four bypass electromagnetic coils are arranged in a centrosymmetric relation, and the symmetric center of the four bypass electromagnetic coils is basically coincident with the center of an outlet plane of the electric thruster 1. In other words, the plurality of bypass electromagnetic coils 3-6 are in a centrosymmetric relationship with respect to the center of the outlet plane of the electric thruster 1. Such an arrangement enables better control and adjustment of the thrust vector.
The main coil 2, the first bypass electromagnetic coil 3, the second bypass electromagnetic coil 4, the third bypass electromagnetic coil 5 and the fourth bypass electromagnetic coil 6 are uniformly powered by a power supply processing unit (PPU) of the spacecraft electric propulsion system, and a required vector declination is converted into a combination of the magnitude and the direction of exciting current in the bypass coils according to a control program which is programmed in advance to generate an asymmetric expanded magnetic field. The electric thruster 1 generates plasma beams and sprays the plasma beams into the magnetic spray pipe from an outlet plane, and bipolar electric fields for accelerating ions are generated by bipolar diffusion because the thermal motion speed of electrons is far higher than that of the ions. Due to the strong degree of electron magnetization, the direction of the electric field is along the direction of the desired thrust vector. And the electrons cause the drift motion of diamagnetism due to radial thermal expansion, the generated Hall current further accelerates the electrons to move downstream, the charge separation tendency is aggravated, and a bipolar electric field is further enhanced. Therefore, the energy of the electrons perpendicular to the thrust vector direction is converted into the energy parallel to the thrust vector direction, and then the energy is transferred to ions through the electric field, so that the propelling performance of the electric thruster is enhanced. Downstream of the plasma beam, due to partial electron magnetic freezing or due to strong inertia of ions, the plasma is separated from the magnetic nozzle, thereby generating thrust in the required deflection direction, and the magnetic nozzle effect is greatly enhanced.
Furthermore, the foregoing describes only some embodiments and alterations, modifications, additions and/or changes may be made without departing from the scope and spirit of the disclosed embodiments, which are intended to be illustrative rather than limiting. Furthermore, the described embodiments are directed to embodiments presently contemplated to be the most practical and preferred, it being understood that the embodiments should not be limited to the disclosed embodiments, but on the contrary, are intended to cover various modifications and equivalent arrangements included within the spirit and scope of the embodiments. Moreover, the various embodiments described above can be used in conjunction with other embodiments, e.g., aspects of one embodiment can be combined with aspects of another embodiment to realize yet another embodiment. In addition, each individual feature or element of any given assembly may constitute additional embodiments.
The foregoing description of the embodiments has been presented for purposes of illustration and description and is not intended to be exhaustive or to limit the disclosure. The various elements or features of a particular embodiment are generally not limited to that particular embodiment, but, where applicable, are interchangeable and can be used in a selected embodiment, even if not specifically shown or described. Such variations are not to be regarded as a departure from the disclosure, and all such modifications are intended to be included within the scope of the disclosure.
Accordingly, it is to be understood that the drawings and description are proffered by way of example to facilitate comprehension of the invention and should not be construed to limit the scope thereof.
Claims (5)
1. A vector magnetic nozzle for electric propulsion comprising a bypass electromagnetic coil, said vector magnetic nozzle comprising:
an electric thruster for generating a plasma jet;
a main coil having an inner bore;
and a plurality of bypass electromagnetic coils uniformly arranged in the inner hole of the main coil, the size of the bypass electromagnetic coils being smaller than that of the inner hole of the main coil,
the axes of the side electromagnetic coils are parallel to the axis of the electric thruster, the side electromagnetic coils are respectively electrified with exciting currents with different sizes and directions and are superposed on a magnetic field generated by the main coil to generate an asymmetric vector magnetic nozzle, and then a plasma jet flow discharged from the electric thruster is guided to expand and accelerate along a required direction to generate a required thrust vector.
2. The vector magnetic nozzle for electric propulsion comprising a side solenoid coil of claim 1, wherein the vector magnetic nozzle comprises four side solenoid coils, and the four side solenoid coils are centrosymmetric, and the center of symmetry coincides with the center of the outlet plane of the electric thruster.
3. The vector magnetic nozzle for electric propulsion comprising a side electromagnetic coil according to claim 1 or 2, characterized in that the side electromagnetic coils comprised by the vector magnetic nozzle are of the same size as each other.
4. Vectoring magnetic nozzle for electric propulsion comprising a side electromagnetic coil according to claim 1 or 2, characterized in that the side electromagnetic coil is fixed to the main coil by welding.
5. A vector magnetic nozzle for electric propulsion comprising a by-pass electromagnetic coil according to claim 1 or 2, characterized in that the by-pass electromagnetic coil is a superconducting coil.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911334628.4A CN111140447A (en) | 2019-12-23 | 2019-12-23 | Vector magnetic nozzle for electric propulsion comprising a bypass electromagnetic coil |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911334628.4A CN111140447A (en) | 2019-12-23 | 2019-12-23 | Vector magnetic nozzle for electric propulsion comprising a bypass electromagnetic coil |
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| CN111140447A true CN111140447A (en) | 2020-05-12 |
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| CN201911334628.4A Pending CN111140447A (en) | 2019-12-23 | 2019-12-23 | Vector magnetic nozzle for electric propulsion comprising a bypass electromagnetic coil |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2741401C1 (en) * | 2020-01-29 | 2021-01-25 | Андрей Иванович Шумейко | Module with multichannel plasma propulsion system for small spacecraft |
| CN112392675A (en) * | 2020-10-23 | 2021-02-23 | 北京精密机电控制设备研究所 | Array type electric heating plasma accelerating device |
| CN112412720A (en) * | 2020-10-29 | 2021-02-26 | 中国科学院合肥物质科学研究院 | Superconducting magnetic plasma propeller |
| CN112555114A (en) * | 2020-12-01 | 2021-03-26 | 中国人民解放军战略支援部队航天工程大学 | Electromagnetic combined vector accelerating spray pipe for laser ablation propulsion |
| CN113357109A (en) * | 2021-06-30 | 2021-09-07 | 哈尔滨工业大学 | Ignition device of radio frequency ion thruster |
| GB2600493A (en) * | 2020-11-03 | 2022-05-04 | Neutronstar Systems Ug | Propulsion unit for spacecraft |
| RU2796728C1 (en) * | 2022-08-24 | 2023-05-29 | Общество С Ограниченной Ответственностью "Эдвансд Пропалшн Системс" | Multichannel plasma engine with a hemispherical gas-discharge chamber |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| RU2741401C1 (en) * | 2020-01-29 | 2021-01-25 | Андрей Иванович Шумейко | Module with multichannel plasma propulsion system for small spacecraft |
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| GB2600493A (en) * | 2020-11-03 | 2022-05-04 | Neutronstar Systems Ug | Propulsion unit for spacecraft |
| CN112555114A (en) * | 2020-12-01 | 2021-03-26 | 中国人民解放军战略支援部队航天工程大学 | Electromagnetic combined vector accelerating spray pipe for laser ablation propulsion |
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| CN113357109A (en) * | 2021-06-30 | 2021-09-07 | 哈尔滨工业大学 | Ignition device of radio frequency ion thruster |
| RU2796728C1 (en) * | 2022-08-24 | 2023-05-29 | Общество С Ограниченной Ответственностью "Эдвансд Пропалшн Системс" | Multichannel plasma engine with a hemispherical gas-discharge chamber |
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Application publication date: 20200512 |