Multi-discharge-channel helicon wave plasma thruster suitable for space application
阅读说明：本技术 适用于空间应用的多放电通道的螺旋波等离子体推力器 (Multi-discharge-channel helicon wave plasma thruster suitable for space application ) 是由 刘佳 余水淋 贾晴晴 金逸舟 杭观荣 田雷超 黄浩 于 2020-07-17 设计创作，主要内容包括：本发明提供了一种适用于空间应用的多放电通道的螺旋波等离子体推力器,包括：若干个耦合天线、若干个放电室、天线支架和磁路；每个耦合天线分别对应安装在一个放电室外侧,若干个耦合天线之间通过天线支架相连,耦合天线通过天线支架共用一套射频电源(含匹配网络)；放电室之间相互平行,且在同一圆周上轴向分布；耦合天线之间相互平行,且在同一圆周上轴向分布；所述磁路形成容置空间；耦合天线、放电室和天线支架安装在容置空间中,若干个耦合天线、若干个放电室构成阵列与容置空间轴线重合。本发明的螺旋波等离子体推力器功率在数千瓦特以下,输出推力在牛级以下,通过采用若干个小尺寸放电室和耦合天线实现较大功率、较大推力输出的目的。(The invention provides a helical wave plasma thruster with multiple discharge channels and suitable for space application, which comprises: the device comprises a plurality of coupling antennas, a plurality of discharge chambers, an antenna bracket and a magnetic circuit; each coupling antenna is correspondingly arranged outside one discharge chamber, a plurality of coupling antennas are connected through an antenna bracket, and the coupling antennas share a set of radio frequency power supply (including a matching network) through the antenna bracket; the discharge chambers are parallel to each other and axially distributed on the same circumference; the coupled antennas are parallel to each other and axially distributed on the same circumference; the magnetic circuit forms an accommodating space; the coupling antennas, the discharge chambers and the antenna supports are arranged in the accommodating space, and the plurality of coupling antennas and the plurality of discharge chambers form an array and coincide with the axis of the accommodating space. The power of the helicon wave plasma thruster is below several kilowatts, the output thrust is below the Newton level, and the purpose of outputting higher power and higher thrust is realized by adopting a plurality of small-size discharge chambers and coupling antennas.)
1. A multi-discharge-channel helicon wave plasma thruster suitable for space applications, comprising: a plurality of coupling antennas (100), a plurality of discharge chambers (200), an antenna support (300) and a magnetic circuit (400);
each coupling antenna (100) is correspondingly arranged on the outer side of one discharge chamber (200), and the axes of the coupling antennas (100) and the discharge chambers (200) are superposed;
the plurality of coupling antennas (100) are connected through the antenna bracket (300), the antenna bracket (300) is connected with a radio frequency power supply, and the plurality of coupling antennas (100) share one set of radio frequency power supply through the antenna bracket (300);
the discharge chambers (200) are parallel to each other and axially distributed on the same circumference;
the coupled antennas (100) are mutually parallel and distributed on the same circumference in a radial-axial manner;
the magnetic circuit (400) forms an accommodating space (500);
the coupling antennas (100), the discharge chambers (200) and the antenna bracket (300) are arranged in the accommodating space (500), and the plurality of coupling antennas (100) and the plurality of discharge chambers (200) form an array and coincide with the axis of the accommodating space (500).
2. The helicon wave plasma thruster of multiple discharge channels adapted for space applications as claimed in claim 1, wherein said coupled antennas (100) share a set of rf power supply through antenna bracket (300).
3. The multi-discharge-channel helicon wave plasma thruster suitable for space applications as claimed in claim 1, wherein the coupled antennas (100) have front faces that together form a regular polygon.
4. The multi-discharge-channel helicon wave plasma thruster suitable for space applications as claimed in claim 1, wherein the front faces of the discharge chambers (200) together form a regular polygon.
5. The multi-discharge-channel helicon wave plasma thruster suitable for space applications as claimed in claim 1, wherein the number of sides L of the regular polygon formed by the front faces of the coupled antennas (100) is equal to the number of sides M of the regular polygon formed by the discharge chambers (200), and L is equal to M.
6. The multi-discharge-channel helicon wave plasma thruster suitable for space applications as claimed in claim 1, wherein a set of magnetic circuits (400) is shared by several coupling antennas (100) and several discharge chambers (200).
7. The multi-discharge-channel helicon wave plasma thruster for space applications as claimed in claim 1, wherein the magnetic circuit (400) encloses a hollow cylindrical receiving space (500).
8. The helicon wave plasma thruster of multiple discharge channels adapted for space applications as claimed in claim 1, wherein the regular polygon formed by the coupling antenna (100) and the discharge chamber (200) is coincident with the axis of the accommodation space (500) enclosed by the magnetic circuit (400).
9. The multi-discharge-channel helicon wave plasma thruster for space applications as claimed in claim 1, wherein the coupling antenna (100) is wound on the outer wall of the discharge chamber (200).
Technical Field
The invention relates to the field of space electric propulsion, in particular to a helical wave plasma thruster with multiple discharge channels, which is suitable for space application.
Background
The helicon wave plasma thruster has the advantages of simple structure, no electrode, high reliability and the like, and becomes one of hot spots for the development of space electric propulsion. Patent document CN106014899A discloses a helicon wave plasma induction thruster, which comprises a discharge cavity, wherein a first magnet and a second magnet are sequentially arranged outside the discharge cavity; the outer wall of the discharge cavity is sequentially provided with a helical wave discharge antenna and an induction accelerating coil along the axial direction; further comprising: the spiral wave discharge circuit is used for providing a working power supply for the spiral wave discharge antenna; the pulse induction discharge circuit is connected with the induction accelerating coil and provides pulse discharge voltage for the induction accelerating coil so as to drive the spiral wave plasma to accelerate and push out; and the time sequence control circuit is connected with the spiral wave discharge circuit and the pulse induction discharge circuit.
The conventional helicon wave plasma thruster adopts a main body design of a single coupling antenna, a single discharge chamber and a single magnetic circuit, and in order to achieve the design goals of higher power and higher thrust, a method of increasing the size of the coupling antenna and the discharge chamber is generally adopted, and the design mainly faces two problems: firstly, the processing difficulty of the discharge chamber and the coupling antenna is increased; secondly, the thrust of the thruster is not increased in equal proportion with the increase of the sizes of the coupling antenna and the discharge chamber. In order to solve the problems, the invention provides a helical wave plasma thruster with multiple discharge channels, the power of the thruster is in the magnitude of 10W-1 kW, the output thrust is in the magnitude of millinewtons to hundred millinewtons, and the purpose of outputting higher power and higher thrust is realized by adopting a plurality of small-size discharge chambers and coupling antennas.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a multi-discharge-channel helicon wave plasma thruster which is suitable for space application.
According to the present invention, there is provided a multiple discharge channel helicon wave plasma thruster suitable for space applications, comprising: a plurality of
each
the plurality of
the
the coupled
the
the
Preferably, the coupled
Preferably, the
Preferably, the front surfaces of the
Preferably, the number L of sides of the regular polygon formed by the front surfaces of the
Preferably, a set of
Preferably, the
Preferably, the array of the
Preferably, the
Compared with the prior art, the invention has the following beneficial effects:
1. the invention adopts a plurality of small-sized discharge chambers and coupling antennas to realize the design purposes of higher power and higher thrust, and has small processing difficulty compared with the mode of increasing the sizes of the antennas and the discharge chambers.
2. The invention uses several coupling antennas to share one radio frequency power system through the antenna bracket, which reduces the complexity of the propulsion system.
3. The invention ensures that a single thruster unit consisting of the coupling antenna and the discharge chamber outputs equal thrust through arranging the coupling antenna and the discharge chamber in the same space of the magnetic field, and the output thrust of the thruster is the sum of the output thrust of each thruster unit.
4. According to the invention, through the coaxial design of the coupling antenna and the discharge chamber, the array formed by the coupling antenna and the discharge chamber is coaxial with the accommodating space enclosed by the magnetic circuit, and the same magnetic field of a single thruster unit formed by the coupling antenna and the discharge chamber is ensured.
5. According to the invention, a set of magnetic circuit is shared by the plurality of coupling antennas and the plurality of discharge chambers, so that the complexity of the thruster is reduced, and the envelope size and the quality of the thruster are reduced.
6. The invention provides a proper magnetic field through the accommodating space enclosed by the magnetic circuit, and ensures that a single thruster unit consisting of the coupling antenna and the discharge chamber works normally.
7. The invention ensures higher energy coupling efficiency of the coupling antenna by winding the coupling antenna on the outer wall of the corresponding discharge chamber.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a perspective view of the present invention;
FIG. 2 is a schematic structural diagram of a helicon wave plasma thruster with 2 coupled antennas and a discharge chamber according to the present invention;
FIG. 3 is a schematic structural diagram of a helicon wave plasma thruster with regular triangles formed by 3 coupled antennas and the front surface of a discharge chamber;
FIG. 4 is a schematic structural diagram of a helicon wave plasma thruster with a positive quadrilateral formed by 4 coupled antennas and the front surface of a discharge chamber according to the present invention;
fig. 5 is a schematic structural view of a helicon wave plasma thruster in which 5 coupled antennas and the front surface of a discharge chamber form a regular pentagon.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.