CN111140448A - Vector magnetic nozzle for electric propulsion consisting of interwoven electromagnetic coils - Google Patents
Vector magnetic nozzle for electric propulsion consisting of interwoven electromagnetic coils Download PDFInfo
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- CN111140448A CN111140448A CN201911334834.5A CN201911334834A CN111140448A CN 111140448 A CN111140448 A CN 111140448A CN 201911334834 A CN201911334834 A CN 201911334834A CN 111140448 A CN111140448 A CN 111140448A
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- electromagnetic coil
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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)
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- Plasma Technology (AREA)
Abstract
The invention relates to a vector magnetic nozzle for electric propulsion, consisting of interwoven electromagnetic coils. The vector magnetic nozzle for electric propulsion composed of interwoven electromagnetic coils comprises: an electric thruster that generates a plasma jet; the plasma jet engine comprises a first electromagnetic coil, a second electromagnetic coil and a third electromagnetic coil which are fixed together in an interlaced mode, wherein the axes of the first electromagnetic coil, the second electromagnetic coil and the third electromagnetic coil form a certain angle with the axis of the electric thruster and are evenly distributed along the space, exciting currents with different sizes and directions are respectively conducted on the first electromagnetic coil, the second electromagnetic coil and the third electromagnetic coil to generate asymmetric vector magnetic jet pipes, and then plasma jet streams are guided to expand and accelerate along the required direction to generate the required thrust vector.
Description
Technical Field
The present invention relates to an electric propulsion arrangement for spacecraft, and in particular to a vectoring magnetic nozzle made up of interwoven electromagnetic coils for electric propulsion of spacecraft.
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 spacecrafts, such as satellites and the like, are also 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 control of the direction 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.
In order to achieve the above object, one embodiment of a vector magnetic nozzle for electric propulsion constructed by an electromagnetic coil according to the present invention includes: an electric thruster that generates a plasma jet; the plasma jet engine comprises a first electromagnetic coil, a second electromagnetic coil and a third electromagnetic coil which are fixed together in an interlaced mode, wherein the axes of the first electromagnetic coil, the second electromagnetic coil and the third electromagnetic coil form a certain angle with the axis of the electric thruster and are evenly distributed along the space, exciting currents with different sizes and directions are respectively conducted on the first electromagnetic coil, the second electromagnetic coil and the third electromagnetic coil to generate asymmetric vector magnetic jet pipes, and then plasma jet streams are guided to expand and accelerate along the required direction to generate the required thrust vector.
In an alternative embodiment, the first, second and third electromagnetic coils are interleaved such that their centers coincide at a point and coincide with the center of the outlet plane of the electric thruster.
In an alternative embodiment, the first, second and third electromagnetic coils are welded together.
In another alternative embodiment, the first, second and third electromagnetic coils are arranged with their axes at 15 degrees to the axis of the electric thruster, respectively.
In another alternative embodiment, the first, second and third electromagnetic coils are superconducting coils.
In yet another alternative embodiment, the vectoring magnetic nozzle further comprises more electromagnetic coils arranged in the same manner as the first, second and third electromagnetic coils.
According to an optional embodiment, three electromagnetic coils which are interwoven with each other are used for generating a magnetic field of the magnetic nozzle, the circle centers of the three electromagnetic coils are overlapped, the axes of the three electromagnetic coils are not overlapped with each other, and the three electromagnetic coils are uniformly distributed in space relative to the axis of the thruster and form an angle of 15 degrees with the axis of the thruster respectively. The 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 three coils, and the interweaving coil is arranged at a beam outlet of the electric thruster, so that the plasma can be guided to expand and deflect along the axis of the magnetic nozzle, and the control of a thrust vector 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. kinetic energy of a plasma beam of the thruster, which is perpendicular to the direction of the thrust vector, is converted into kinetic energy parallel to the direction of the thrust vector by using a magnetic nozzle effect, so that the propelling performance in the required direction is improved;
4. the axis of the deflection coil is not parallel to the axis of the thruster, so that the invention needs less current to achieve the expected deflection effect and has simple structure of the magnetic jet pipe;
drawings
The invention is further illustrated by the following examples in conjunction with the accompanying drawings:
FIG. 1 is a schematic diagram of a vectored magnetic nozzle for electric propulsion constructed with interleaved electromagnetic coils in accordance with one embodiment of the present invention.
The reference numerals in the figures denote the following parts,
1. electric thruster
2. First electromagnetic coil
3. Second electromagnetic coil
4. Third electromagnetic coil
5. Axis of the first electromagnetic coil
6. Axis of the second electromagnetic coil
7. Axis of third 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 constructed from interleaved electromagnetic coils, according to one embodiment of the present invention. Referring to fig. 1, one embodiment of a vector magnetic nozzle for electric propulsion according to the present invention includes: the electromagnetic thruster comprises an electric thruster 1 for generating a plasma stream, a first electromagnetic coil 2, a second electromagnetic coil 3 and a third electromagnetic coil 4, wherein the axis 5 of the first electromagnetic coil A, the axis 6 of the second electromagnetic coil and the axis 7 of the third electromagnetic coil are respectively at a certain angle with the axis of the electric thruster 1 and are uniformly distributed along the space. Although the illustrated vector magnetic nozzle includes three electromagnetic coils, it should be understood that a greater or lesser number of electromagnetic coils may be provided as desired in a manner similar or identical to that described above. Still alternatively, the first electromagnetic coil 2, the second electromagnetic coil 3, and the third electromagnetic coil 4 may be disposed so that their centers are at one point to achieve a better direction adjustment effect.
The first coil 2, the second coil 3 and the third coil 4 are ordinary electromagnetic coils or superconducting coils in the shape of a ring, and the ordinary coils can be subjected to heat protection by adding internal forced water cooling. The first electromagnetic coil 2, the second electromagnetic coil 3 and the third electromagnetic coil 4 can be fixed together by any suitable means, such as welding, and the like, and the centers of the three electromagnetic coils are located at one point, and the axes of the three electromagnetic coils, namely the axis 5, the axis 6 and the axis 7, are uniformly distributed around the central axis of the thruster 1. Optionally, the first electromagnetic coil 2, the second electromagnetic coil 3, and the third electromagnetic coil 4 are fixed such that each of the axis 5, the axis 6, and the axis 7 forms an angle of 15 degrees with a central axis of the electric thruster 1, which can achieve a better direction adjustment effect. It should be understood that the first solenoid coil 2, the second solenoid coil 3 and the third solenoid coil 4 may be arranged such that the respective axes 5, 6 and 7 are at equal angles of more or less than 15 degrees with respect to the central axis of the electric thruster 1, respectively, according to the requirements. The central points of the first, second and third electromagnetic coils 2, 3, 4 are arranged at the center of the outlet plane of the electric thruster 1, which can be ensured by a structure on a spacecraft or a support structure of a ground test stand.
The first electromagnetic coil 2, the second electromagnetic coil 3 and the third electromagnetic coil 4 are uniformly powered by a power supply processing unit (PPU) of the spacecraft electric propulsion system, and a required vector deflection angle is converted into a combination of the magnitude and the direction of an exciting current in the coils according to a control program which is programmed in advance, so that an asymmetric expanded magnetic field is generated. 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 the ions, the plasma is separated from the magnetic nozzle, thereby generating thrust in the desired deflection direction and being greatly enhanced by the magnetic nozzle effect.
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 (6)
1. A vectored magnetic nozzle for electric propulsion constructed from interleaved electromagnetic coils, characterized by:
the vector magnetic nozzle comprises:
an electric thruster that generates a plasma jet;
the plasma jet engine comprises a first electromagnetic coil, a second electromagnetic coil and a third electromagnetic coil which are fixed together in an interlaced mode, wherein the axes of the first electromagnetic coil, the second electromagnetic coil and the third electromagnetic coil form a certain angle with the axis of the electric thruster and are evenly distributed along the space, exciting currents with different sizes and directions are respectively conducted on the first electromagnetic coil, the second electromagnetic coil and the third electromagnetic coil to generate asymmetric vector magnetic jet pipes, and then plasma jet streams are guided to expand and accelerate along the required direction to generate the required thrust vector.
2. The vectoring magnetic nozzle for electric propulsion made up of interleaved coils as claimed in claim 1, characterized in that:
the first, second, and third electromagnetic coils are disposed such that centers thereof coincide at a point and coincide with an outlet plane center of the electric thruster.
3. The vectoring magnetic nozzle for electric propulsion made up of interleaved coils as claimed in claim 1, characterized in that:
the first electromagnetic coil, the second electromagnetic coil and the third electromagnetic coil are welded and fixed together.
4. A vector magnetic nozzle for electric propulsion made up of interwoven coils according to any of claims 1-3, characterized in that:
the first electromagnetic coil, the second electromagnetic coil and the third electromagnetic coil are arranged such that axes thereof are at an angle of 15 degrees to an axis of the electric thruster, respectively.
5. A vector magnetic nozzle for electric propulsion made up of interwoven coils according to any of claims 1-3, characterized in that:
the first electromagnetic coil, the second electromagnetic coil and the third electromagnetic coil are superconducting coils.
6. A vector magnetic nozzle for electric propulsion made up of interwoven coils according to any of claims 1-3, characterized in that:
the vectoring magnetic nozzle also includes further electromagnetic coils arranged in the same manner as the first, second and third electromagnetic coils.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911334834.5A CN111140448A (en) | 2019-12-23 | 2019-12-23 | Vector magnetic nozzle for electric propulsion consisting of interwoven electromagnetic coils |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911334834.5A CN111140448A (en) | 2019-12-23 | 2019-12-23 | Vector magnetic nozzle for electric propulsion consisting of interwoven electromagnetic coils |
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| CN111140448A true CN111140448A (en) | 2020-05-12 |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN113217228A (en) * | 2021-06-18 | 2021-08-06 | 西北工业大学 | Magnetic control type thrust vector control device for solid rocket engine |
| GB2600493A (en) * | 2020-11-03 | 2022-05-04 | Neutronstar Systems Ug | Propulsion unit for spacecraft |
| DE102021109963A1 (en) | 2021-04-20 | 2022-10-20 | Technische Universität Dresden, Körperschaft des öffentlichen Rechts | Magnetoplasmadynamic propulsion unit for space applications |
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| WO2002037521A3 (en) * | 2000-11-03 | 2003-03-13 | Tokyo Electron Ltd | Hall effect ion source at high current density |
| US8205428B2 (en) * | 2009-02-05 | 2012-06-26 | Lockheed Martin Corporation | Capacitive stator |
| CN102777342A (en) * | 2012-08-03 | 2012-11-14 | 北京卫星环境工程研究所 | Vector magnetic nozzle used for electric propulsion |
| WO2015082739A1 (en) * | 2013-12-05 | 2015-06-11 | Universidad Politécnica de Madrid | Thrust vectoring system and method for space plasma thrusters |
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2019
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| WO2002037521A3 (en) * | 2000-11-03 | 2003-03-13 | Tokyo Electron Ltd | Hall effect ion source at high current density |
| US8205428B2 (en) * | 2009-02-05 | 2012-06-26 | Lockheed Martin Corporation | Capacitive stator |
| CN102777342A (en) * | 2012-08-03 | 2012-11-14 | 北京卫星环境工程研究所 | Vector magnetic nozzle used for electric propulsion |
| WO2015082739A1 (en) * | 2013-12-05 | 2015-06-11 | Universidad Politécnica de Madrid | Thrust vectoring system and method for space plasma thrusters |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2600493A (en) * | 2020-11-03 | 2022-05-04 | Neutronstar Systems Ug | Propulsion unit for spacecraft |
| WO2022096506A1 (en) * | 2020-11-03 | 2022-05-12 | 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 |
| DE102021109963A1 (en) | 2021-04-20 | 2022-10-20 | Technische Universität Dresden, Körperschaft des öffentlichen Rechts | Magnetoplasmadynamic propulsion unit for space applications |
| CN113217228A (en) * | 2021-06-18 | 2021-08-06 | 西北工业大学 | Magnetic control type thrust vector control device for solid rocket engine |
| CN113217228B (en) * | 2021-06-18 | 2022-04-08 | 西北工业大学 | Magnetic control type thrust vector control device for solid rocket engine |
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Application publication date: 20200512 |