CN113357114A - Main cathode assembly structure applied to thruster and assembly method thereof - Google Patents
Main cathode assembly structure applied to thruster and assembly method thereof Download PDFInfo
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- CN113357114A CN113357114A CN202110813110.XA CN202110813110A CN113357114A CN 113357114 A CN113357114 A CN 113357114A CN 202110813110 A CN202110813110 A CN 202110813110A CN 113357114 A CN113357114 A CN 113357114A
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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
- F03H1/0006—Details applicable to different types of plasma thrusters
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Abstract
The invention discloses an assembly structure of a main cathode applied to a thruster and an assembly method thereof, wherein the main cathode is arranged on a connecting base through an insulating base, so that the main cathode and the connecting base are kept in an insulating state, the connecting base is in an annular structure, a plurality of slots penetrating through the side wall of the connecting base are arranged on the annular structure along the circumferential direction, positioning pieces with different lengths can be replaced in the slots, the positioning pieces are inserted in the slots and block gaps between the slots and the insulating base, the insulating base is lapped on the positioning pieces through lapping pieces connected with the insulating base, the axial positions of the lapping pieces on the connecting base are changed through replacing the positioning pieces with different lengths, and then the insulating base is driven to change the axial positions of the insulating base on the connecting base, so that the insulating sealing between the main cathode and the connecting base can be ensured, and the axial positions of the main cathode relative to a discharge chamber of the thruster can be frequently changed, the experimental research of the thruster is satisfied.
Description
Technical Field
The invention relates to the field of ionic electric thrusters, in particular to an assembly structure and an assembly method of a main cathode applied to a thruster.
Background
The ion thruster in the prior art generates plasma in the discharge chamber and accelerates ions in the plasma to generate thrust. The discharge chamber mainly comprises a main cathode and an anode, wherein the main cathode needs to provide electrons for bombarding working media to generate plasma, and the insulation between the main cathode and the anode needs to be kept in order to ensure the normal work of the thruster. The main cathode is arranged on the anode through a flange of the main cathode, the axial position of the main cathode relative to the discharge chamber needs to be frequently changed in experimental research of the micro ion thruster, the existing cathode mounting structure cannot meet the requirement, the sealing performance of the discharge chamber needs to be guaranteed in the working process of the thruster, and otherwise, plasma in the discharge chamber leaks out of the discharge chamber through a gap of the discharge chamber and is ignited with other parts of the thruster, so that the thruster cannot normally run. For a conventional ion thruster, a complex mounting structure needs to be designed to realize the two points, and particularly, when the mounting structure is applied to a discharge chamber of a miniature ion thruster, due to the small structural size of the mounting structure, the conventional cathode mounting structure is more difficult to adapt to the small-size discharge chamber.
Patent document CN106246487B discloses a magnetic plasma thruster using additional electromagnetic field energy conversion, in which a hollow cathode is inserted into an enlarged inner hole end of a cathode connecting piece, and the hollow cathode is positioned and clamped by interference fit; the graphite gasket is sleeved into the cathode connecting piece from one end inserted with the hollow cathode, the cathode connecting piece provided with the hollow cathode and the graphite gasket is inserted into the inner hole of the insulator until the graphite gasket is pressed to the end face of the insulator, and the outer cylindrical surface of the cathode connecting piece is in clearance fit with the inner cylindrical surface of the insulator, so that radial positioning is realized and coaxiality is ensured. However, due to the interference fit, the axial position of the hollow cathode cannot be changed, and therefore, the axial position of the main cathode relative to the discharge chamber cannot be changed frequently according to experimental requirements.
Patent document CN20992515U discloses an expanding type self-magnetic field magnetic plasma thruster, wherein a cathode head is connected to the top end of a cathode main body in a detachable connection manner, wherein the cathode head extends into a conical expanding section. The cathode head is connected on the top of the cathode main body in a detachable connection mode, so that the length of the cathode head extending into the conical expansion section is convenient to control, but the cathode head is difficult to improve the structure of the cathode main body for providing electrons for bombarding the working medium to generate plasma.
Disclosure of Invention
The invention aims to provide an assembly structure of a main cathode applied to a thruster and an assembly method thereof, which are used for solving the problems in the prior art, can ensure that the length of the main cathode extending into a discharge chamber of the thruster can be adjusted along the axial direction by changing the length of a positioning piece, meet the requirement of frequently changing the axial position of the main cathode relative to the discharge chamber in the experimental research of an ion thruster, ensure the sealing and insulation between the main cathode and the discharge chamber, prevent plasma in the discharge chamber from leaking through a gap and striking fire with other parts of the thruster and ensure the normal operation of the thruster.
In order to achieve the purpose, the invention provides the following scheme: the invention provides an assembly structure of a main cathode applied to a thruster, which comprises an insulating base sleeved on the periphery of the main cathode, and a connecting base which is of an annular structure and is sealed and wound at an opening of a discharge chamber of the thruster, wherein the insulating base is inserted in the annular structure in a sealing manner, the annular structure is circumferentially provided with a plurality of slots penetrating through the side wall of the annular structure, positioning pieces with different lengths are arranged in the slots in a replaceable manner, the positioning pieces are inserted in the slots and block gaps between the slots and the insulating base, the insulating base is connected to the positioning pieces in a lap joint manner through lap joints connected with the insulating base, and the lap joints are positioned on one side of the positioning pieces, which is far away from the discharge chamber of the thruster, and are arranged in the slots in a sealing manner.
Preferably, the positioning piece abuts against the inner side edge of the side, close to the discharge chamber of the thruster, of the insulating base, and is attached to the outer peripheral wall of the insulating base.
Preferably, the cross sections of the slot and the positioning piece in the radial direction are both in a multi-stage step-shaped structure, and the narrow end of the multi-stage step-shaped structure is close to the insulating base.
Preferably, the annular structure comprises a connecting flange and an annular boss which are coaxially connected, the slot penetrates through the annular boss, the connecting flange blocks one side of the slot close to the discharge chamber of the thruster, and one side of the positioning piece close to the discharge chamber of the thruster is tightly attached to the connecting flange.
Preferably, the overlapping part comprises a plurality of connecting parts surrounding the periphery of the insulating base, one end of each connecting part is fixed on the insulating base, and the other end of each connecting part penetrates through the corresponding slot and is overlapped on the positioning part.
Preferably, the other end of the connecting part is provided with a sealing gasket which abuts against the positioning part, and the sealing gasket is connected in the groove in a sealing manner.
Preferably, the cross section of each groove in the radial direction is in a multistage step-shaped structure, the narrow end of the multistage step-shaped structure is close to the insulating base, and the sealing gasket abuts against the outer side wall of the narrow end.
Preferably, a clamping piece is arranged on one side, away from the positioning piece, of the other end of the connecting portion, and the other end of the connecting portion is clamped between the clamping piece and the positioning piece.
Preferably, the clamping piece and the positioning piece are both elastic structures, and the elastic structures are in interference fit in the grooves.
There is also provided an assembling method of an assembling structure of a main cathode applied to a thruster, including the steps of:
installing a connecting base: sleeving a connecting base ring at an opening of a discharge chamber of the thruster, and connecting the connecting base ring with the discharge chamber of the thruster in a sealing manner through a connecting flange;
installing a positioning piece: inserting each positioning piece into the corresponding slot and tightly abutting against the connecting flange;
installing a main cathode: sleeving an insulating base on the main cathode, and installing the lapping pieces on the outer peripheral side of the insulating base at positions corresponding to the grooves;
installing an insulating base: inserting the insulating base provided with the main cathode into the connecting base, separating the main cathode from the connecting base through the insulating base, and enabling the lap joint pieces to penetrate through the corresponding slots and lap joint the lap joint pieces on the positioning pieces;
replacing the positioning piece: after a group of experiments are completed, the insulating base is detached, and after the positioning pieces with other lengths are replaced, the insulating base is reinstalled, and then the next group of experiments are performed.
Compared with the prior art, the invention has the following technical effects:
first, the main negative pole passes through insulating base and installs on connecting the base, make main negative pole and connect and keep insulating state between the base, because it is the loop configuration to connect the base, and the loop configuration has seted up a plurality of along circumference and has run through the fluting of its lateral wall, removable setting element that is equipped with different length in the fluting, the setting element is pegged graft in the fluting, and the clearance of shutoff fluting and insulating base, insulating base is through the overlap joint spare overlap joint rather than being connected on the setting element, so through the setting element of changing different length, change the axial position of overlap joint spare on connecting the base, and then drive insulating base and change its axial position on connecting the base, in order can guarantee insulating sealing between main negative pole and connection base, can frequently change the axial position of main negative pole for the thruster discharge chamber, satisfy the experimental study at the thruster.
Second, the setting element butt is located insulating base at the fluting and is close to on the inboard edge of thruster discharge chamber one side to the laminating is on insulating base's periphery wall, make the setting element only need can seal between grooved inboard edge and insulating base's periphery wall can, need not to recycle the setting element and carry out the whole seal to the fluting along its radially, fully reduced the setting element to insulating base and the sealed degree of difficulty of connecting the base.
Thirdly, the sections of the groove and the positioning piece in the radial direction are in multi-stage step-shaped structures, the narrow ends of the multi-stage step-shaped structures are close to the insulating base, and a multi-stage sealing structure is formed between the groove and the insulating base by arranging the multi-stage step-shaped structures, so that the sealing strength of the positioning piece to the groove is ensured.
Fourth, the loop configuration includes coaxial coupling's flange and annular boss, utilize the flange shutoff to be close to one side of thruster discharge chamber in the fluting, and then when in actual use, one side that the setting element is close to the thruster discharge chamber closely laminates on flange, in order to make things convenient for the location to setting element itself, plug-in the fluting, and the laminating is back on flange, keep the setting element motionless, need not to adjust the setting element again, and then make things convenient for follow-up directness to peg graft insulating base in annular boss, and just place the setting element, in order to conveniently accomplish the seal installation work.
Fifthly, the overlapping pieces comprise a plurality of connecting parts surrounding the periphery of the insulating base, one ends of the connecting parts are fixed on the insulating base, the other ends of the connecting parts penetrate through the corresponding slots and are overlapped on the positioning pieces, and the insulating base is stably overlapped on the positioning pieces by arranging the overlapping pieces on the insulating base along the circumferential direction.
Sixthly, the other end of connecting portion is equipped with the seal gasket of butt on the setting element, and seal gasket sealing connection is in the fluting, and then forms detachable construction, utilize seal gasket to connect on connecting portion, with seal gasket sealing connection in the fluting when using, avoid main negative pole to appear phenomenons such as shifting after accomplishing the installation, when follow-up change spacer in addition, can dismantle from connecting portion through seal gasket to can guarantee quick installation and the change to insulator foot.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without inventive exercise.
FIG. 1 is a cross-sectional view of the overall construction of the present invention;
FIG. 2 is a top view of the overall structure of the present invention;
FIG. 3 is a bottom view of the overall structure of the present invention;
FIG. 4 is a view of the structure of the insulating base of the present invention;
FIG. 5 is a view showing the construction of the connection base according to the present invention;
FIG. 6 is a view of the structure of a gasket of the present invention;
FIG. 7 is a view showing a structure of a positioning member according to the present invention;
the device comprises a main cathode, a flange bolt 2, an insulating base 3, a connecting base 4, a sealing gasket 5, a positioning piece 6, a main cathode flange 7, a slot 8, an annular boss 9, a connecting flange 10, a threaded hole 11 and a circular through hole 12.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The invention aims to provide an assembly structure of a main cathode applied to a thruster and an assembly method thereof, which are used for solving the problems in the prior art, can ensure that the length of the main cathode extending into a discharge chamber of the thruster can be adjusted along the axial direction by changing the length of a positioning piece, meet the requirement of frequently changing the axial position of the main cathode relative to the discharge chamber in the experimental research of an ion thruster, ensure the sealing and insulation between the main cathode and the discharge chamber, prevent plasma in the discharge chamber from leaking through a gap and striking fire with other parts of the thruster and ensure the normal operation of the thruster.
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in further detail below.
Referring to fig. 1 to 7, an assembly structure of a main cathode applied to a thruster is provided, which includes an insulating base 3 sleeved on the periphery of the main cathode 1, and a connecting base 4 having an annular structure and sealing the opening of a discharge chamber of the thruster in a surrounding manner, the insulating base 3 is made of hard and insulating materials such as ceramics, the main cathode 1 is mounted on the insulating base 3, for example, a circular through hole 12 is formed in the insulating base 3, the inner diameter of the circular through hole 12 is slightly larger than the outer diameter of the main cathode 1, the main cathode 1 is inserted into the circular through hole 12, the main cathode 1 is fixed on the insulating base 3 by a bolt penetrating through a flange 7 of the main cathode, the insulating base 3 is mounted on the connecting base 4, specifically, the insulating base 3 is hermetically inserted into the annular structure, preferably, the shape structure of the insulating base 3 is adapted to the inner ring structure of the annular structure, because the insulating base 3 is sleeved on the periphery of the main cathode 1, an insulated connecting structure is further formed between the main cathode 1 and the annular structure, the main cathode 1 is not in contact with the connecting base 4 so as to avoid short circuit between the main cathode 1 and the anode of the thruster and avoid the thruster from being extinguished and power supply damage, the connecting base 4 is assembled with a discharge chamber of the thruster, and particularly, a sealing assembly is adopted to seal a shell connecting the base 4 and the discharge chamber of the thruster; the annular structure is provided with a plurality of slots 8 penetrating through the side wall of the annular structure along the circumferential direction, positioning pieces 6 with different lengths can be arranged in the slots 8 in a replaceable manner, the insulating base 3 is lapped on the positioning pieces 6 through lapping pieces connected with the insulating base, the lapping pieces are positioned on one side, far away from a discharge chamber of the thruster, of the positioning pieces 6 and are arranged in the slots 8 in a sealing manner, wherein in the same group of experiments, the lengths of the adopted positioning pieces 6 are the same, the axial position of the main cathode 1 is determined according to the lengths of the positioning pieces 6 so as to develop experimental research, the position of the main cathode 1, namely the emission position of original electrons, can influence the discharge energy loss characteristic and the discharge stability, the optimal position needs to be determined through experiments, the positioning pieces 6 are inserted in the slots 8 and block gaps between the slots 8 and the insulating base 3, so that the insulating sealing between the main cathode 1 and the connecting base 4 can be ensured, and the axial position of the main cathode 1 relative to the discharge chamber of the thruster can be frequently changed, the experimental research of the thruster is satisfied.
As a preferred embodiment of the invention, the main cathode 1 is installed on the end face of the insulating base 3 through the main cathode flange 7, three threaded holes are processed on the end face of the insulating base 3 and are uniformly distributed along the circumferential direction and aligned with the installation holes on the main cathode flange 7, the flange bolts 2 penetrate through the installation holes of the main cathode flange 7 and are screwed into the threaded holes on the end face of the insulating base 3, so that the main cathode 1 and the insulating base 3 are fixed, and the radius of the main cathode flange 7 is smaller than the outer radius of the insulating base 3, so as to prevent the main cathode flange 7 from contacting with the connecting base 4 to cause open circuit.
Furthermore, the positioning piece 6 is abutted against the inner side edge of the side, close to the discharge chamber of the thruster, of the insulating base 3, of the open slot 8 and is attached to the outer peripheral wall of the insulating base 3, so that the positioning piece 6 only needs to be sealed between the inner side edge of the open slot 8 and the outer peripheral wall of the insulating base 3, the integral sealing of the open slot 8 along the radial direction of the open slot 8 is not needed to be carried out by utilizing the positioning piece 6, and the sealing difficulty of the positioning piece 6 on the insulating base 3 and the connecting base 4 is fully reduced; as the preferred embodiment of the invention, the shape of the positioning piece 6 is matched with the structure of the slot 8, the inner side of the positioning piece 6 is tightly attached to the outer wall of the insulating base 3, and the gap of the contact part of the connecting base 4 and the insulating base 3 is sealed, so that the effect of sealing the discharge chamber is achieved, plasma in the discharge chamber is prevented from leaking through the gap and striking fire with other parts of the thruster, and the normal operation of the thruster is ensured; and two chamfers are processed at two edges along the circumferential direction on the inner side of the positioning piece 6, so that the original positioning piece 6 can be conveniently withdrawn when the positioning piece 6 is replaced.
The preferable section of the slot 8 and the section of the positioning piece 6 in the radial direction are both in a multi-stage step-shaped structure, the narrow end of the multi-stage step-shaped structure is close to the insulating base 3, and a multi-stage sealing structure is formed between the slot 8 and the insulating base 3 through the multi-stage step-shaped structure, so that the sealing strength of the positioning piece 6 to the slot 8 is ensured. Or preferably, a T-shaped groove is machined in the side wall of the annular structure along the axial direction of the thruster, the T-shaped groove penetrates through the annular structure along the axial direction and the radial direction respectively, the positioning piece 6 is inserted into the T-shaped groove, and the shape of the positioning piece 6 is matched with that of the T-shaped groove so as to seal a gap between the insulating base 3 and the annular structure.
Further, the annular structure includes coaxial coupling's flange 10 and annular boss 9, structure that can be integrated into one piece, still can be for screw connection etc., utilize flange 10 shutoff to be close to one side of thruster discharge chamber at fluting 8, and then when in actual use, one side that setting element 6 is close to the thruster discharge chamber closely laminates on flange 10, in order to make things convenient for the location to setting element 6 itself, plug-in fluting 8, and the laminating is after on flange 10, keep setting element 6 motionless, need not to adjust setting element 6 again, and then make things convenient for follow-up direct to peg graft insulator foot 3 in annular boss 9, and just place setting element 6, in order to conveniently accomplish sealed installation work. Specifically, the connecting flange 10 is assembled with the discharge chamber of the thruster, four through holes are machined in the connecting flange 10 and aligned with a mounting hole in a flange of a discharge chamber shell, the connecting flange 10 and the discharge chamber shell are fixed through bolts and nuts, the annular boss 9 is used for being assembled with the insulating base 3, the radius of the inner edge of the annular boss is equal to the radius of the outer edge of the insulating base 3, the insulating base 3 is inserted into the annular boss 9, and the outer wall of the annular boss is attached to the inner wall of the annular boss 9.
Preferably, the overlapping element comprises a plurality of connecting parts surrounding the periphery of the insulating base 3, one ends of the connecting parts are fixed on the insulating base 3, the other ends of the connecting parts penetrate through the corresponding slots 8 and are overlapped on the positioning parts 6, and each overlapping element is circumferentially and annularly arranged on the insulating base 3 to ensure that the insulating base 3 is stably overlapped on each positioning part 6.
Further, the other end of connecting portion is equipped with the seal gasket 5 of butt on setting element 6, and seal gasket 5 sealing connection is in fluting 8, and then form detachable construction, utilize seal gasket 5 to connect on connecting portion, with seal gasket 5 sealing connection in fluting 8 when using, avoid main negative pole 1 to appear phenomenons such as aversion after accomplishing the installation, when follow-up change spacer in addition, can get off through dismantling seal gasket 5 from connecting portion, thereby can guarantee quick installation and the change to insulating base 3. As a preferred embodiment of the invention, three threaded holes 11 are processed on the outer side wall of the insulating base 3 and are uniformly distributed along the circumferential direction, the axes of the threaded holes 11 point to the central axis of the annular structure and are used for assembling with the annular structure, the number of the slots 8 on the annular structure is corresponding to that of the threaded holes 11 on the outer side wall of the insulating base 3, the slots 8 are used for punching through the inner wall and the outer wall of the annular structure and are aligned with the threaded holes 11 on the outer side wall of the insulating base 3 and are used for connecting and fixing the insulating base 3 and the connecting base 4 through bolts.
Furthermore, the section of the slot 8 in the radial direction is a multi-stage step-shaped structure, the narrow end of the multi-stage step-shaped structure is close to the insulating base 3, the sealing gasket 5 is abutted to the outer side wall of the narrow end, specifically, the sealing gasket 5 is made of soft metal materials such as easily deformable copper and aluminum and is abutted to the positioning piece 6 during installation so as to determine the axial position of the main cathode 1, and the bolt is screwed in to press the sealing gasket 5 to deform through arranging the bolt and is clamped in the multi-stage step-shaped structure or on the T-shaped groove so as to prevent the connecting base 4 and the insulating base 3 from relative dislocation.
In a preferred embodiment of the present invention, the sealing gasket 5 is not used, a clamping member is provided on the other end of the connecting portion away from the positioning member 6, the other end of the connecting portion is clamped between the clamping member and the positioning member 6, and the insulating base 3 is fixed and axially positioned by the clamping member and the positioning member 6. The preferable clamping piece and the positioning piece 6 are both of elastic structures, for example, polytetrafluoroethylene and the like with better elasticity are selected as materials, the elastic structures are in interference fit in the grooves 8, the clamping piece is inserted into the grooves 8 from one side opposite to the positioning piece 6, and the machining tolerance of the clamping piece and the positioning piece 6 is a slightly larger value, so that the clamping piece and the positioning piece 6 can be in interference fit with the grooves 8, and do not move in the axial direction, so that the axial position of the main cathode 1 relative to a thruster discharge chamber can be frequently changed while the insulation sealing between the main cathode 1 and the connecting base 4 can be ensured, and the experimental research on the thruster is met.
There is also provided an assembling method of an assembling structure of a main cathode 1 applied to a thruster, including the steps of:
installing and connecting the base 4: sleeving the connecting base 4 at the opening of the discharge chamber of the thruster in a sleeving manner, and connecting the connecting base with the discharge chamber of the thruster in a sealing manner through a connecting flange 10; specifically, four through holes are processed on the periphery of the connecting base 4 and aligned with mounting holes on a flange of the discharge chamber shell, and the connecting base 4 and the discharge chamber shell are fixed by bolts and nuts;
installing the positioning piece 6: inserting each positioning piece 6 into the corresponding slot 8 and tightly abutting against the connecting flange 10; specifically, a plurality of positioning pieces 6 with equal length are inserted into corresponding slots 8, the axial position of the main cathode 1 is determined, the positioning pieces 6 are attached to the outer wall of the insulating base 3 and the slots 8, and a gap connecting the contact area of the base 4 and the insulating base 3 is sealed, so that working medium gas is prevented from leaking from the gap;
installing the main cathode 1: sleeving an insulating base 3 on the main cathode 1, and installing lap joints on the outer peripheral side of the insulating base 3 corresponding to the positions of the slots 8;
installing an insulating base 3: inserting the insulating base 3 provided with the main cathode 1 into the connecting base 4, separating the main cathode 1 from the connecting base 4 through the insulating base 3, and enabling the lap joint pieces to penetrate through the corresponding slots 8 and lap joint the lap joint pieces on the positioning pieces 6; specifically, a plurality of threaded holes 11 are processed in the outer side wall of the insulating base 3, the number of slots 8 in the annular structure corresponds to the number of the threaded holes 11 in the outer side wall of the insulating base 3, the slots 8 are used for penetrating the inner wall and the outer wall of the annular structure and are aligned with the threaded holes 11 in the outer side wall of the insulating base 3 to be used for connecting and fixing the insulating base 3 and the connecting base 4, and through arranging bolts, the bolts penetrate through the sealing gasket 5 and are screwed into the threaded holes 11, press the sealing gasket 5 to deform and are clamped on the slots 8, and therefore the connecting base 4 and the insulating base 3 are prevented from relative dislocation; or polytetrafluoroethylene and the like with better elasticity are selected as materials, the elastic structure is in interference fit in the slot 8, the clamping piece is inserted into the slot 8 from one side opposite to the positioning piece 6, and the machining tolerance of the clamping piece and the positioning piece 6 takes a slightly larger value, so that the clamping piece and the positioning piece 6 can be in interference fit with the slot 8 and do not move in the axial direction;
replacement of the positioning member 6: after a set of experiments is completed, the insulating base 3 is detached, and after the positioning pieces 6 with other lengths are replaced, the insulating base 3 is reinstalled, and the next set of experiments are performed.
The adaptation according to the actual requirements is within the protection scope of the invention
It will be evident to those skilled in the art that the invention is not limited to the details of the foregoing illustrative embodiments, and that the present invention may be embodied in other specific forms without departing from the spirit or essential attributes thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.
The principle and the implementation mode of the invention are explained by applying a specific example, and the description of the embodiment is only used for helping to understand the method and the core idea of the invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, the specific embodiments and the application range may be changed. In view of the above, the present disclosure should not be construed as limiting the invention.
Claims (10)
1. The utility model provides an assembly structure for main cathode of thruster, its characterized in that, including cup joint at the insulating base of main cathode periphery, be annular structure and sealing ring around the connection base of thruster discharge chamber opening part, insulating base seals and pegs graft in the annular structure, annular structure sets up the fluting that a plurality of runs through its lateral wall along circumference, the removable setting element that is equipped with different length in the fluting, the setting element is pegged graft in the fluting, and the shutoff fluting with insulating base's clearance, insulating base through the overlap joint rather than being connected on the setting element, the overlap joint is located one side that the thruster discharge chamber was kept away from to the setting element to sealed the setting is in the fluting.
2. The assembling structure of a main cathode applied to a thruster, according to claim 1, wherein the positioning member abuts against an inner side edge of the slot on a side of the insulating base close to the discharge chamber of the thruster and is attached to an outer peripheral wall of the insulating base.
3. The assembling structure of a main cathode applied to a thruster according to claim 2, wherein the cross section of the slot and the positioning member in the radial direction are each a multi-step structure, and the narrow end of the multi-step structure is close to the insulating base.
4. The assembling structure applied to the main cathode of the thruster, according to claim 2, wherein the annular structure comprises a connecting flange and an annular boss which are coaxially connected, the slot is arranged on the annular boss in a penetrating manner, the connecting flange is blocked at one side of the slot close to a discharge chamber of the thruster, and one side of the positioning piece close to the discharge chamber of the thruster is tightly attached to the connecting flange.
5. The assembling structure of a main cathode for a thruster according to any one of claims 1 to 4, wherein the overlapping member includes a plurality of connecting portions that are wound around the outer circumference of the insulating base, one end of each connecting portion is fixed to the insulating base, and the other end of each connecting portion passes through the corresponding slot and overlaps the positioning member.
6. The assembling structure of a main cathode applied to a thruster according to claim 5, wherein the other end of the connecting part is provided with a sealing gasket abutting against the positioning member, and the sealing gasket is hermetically connected in the groove.
7. The assembling structure of a main cathode applied to a thruster according to claim 6, wherein the cross sections of the slots in the radial direction are each a multi-step structure, a narrow end of the multi-step structure is close to the insulating base, and the sealing gasket abuts on an outer side wall of the narrow end.
8. The assembling structure of a main cathode applied to a thruster according to claim 5, wherein a clamping member is provided at a side of the other end of the connecting portion, which is away from the positioning member, and the other end of the connecting portion is clamped between the clamping member and the positioning member.
9. The assembling structure of a main cathode applied to a thruster according to claim 8, wherein the clamping member and the positioning member are both of an elastic structure, and the elastic structure is in an interference fit in the slot.
10. An assembling method of an assembling structure of a main cathode applied to a thruster is characterized by comprising the following steps of:
installing a connecting base: sleeving a connecting base ring at an opening of a discharge chamber of the thruster, and connecting the connecting base ring with the discharge chamber of the thruster in a sealing manner through a connecting flange;
installing a positioning piece: inserting each positioning piece into the corresponding slot and tightly abutting against the connecting flange;
installing a main cathode: sleeving an insulating base on the main cathode, and installing the lapping pieces on the outer peripheral side of the insulating base at positions corresponding to the grooves;
installing an insulating base: inserting the insulating base provided with the main cathode into the connecting base, separating the main cathode from the connecting base through the insulating base, and enabling the lap joint pieces to penetrate through the corresponding slots and lap joint the lap joint pieces on the positioning pieces;
replacing the positioning piece: after a group of experiments are completed, the insulating base is detached, and after the positioning pieces with other lengths are replaced, the insulating base is reinstalled, and then the next group of experiments are performed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110813110.XA CN113357114B (en) | 2021-07-19 | 2021-07-19 | Main cathode assembly structure applied to thruster and assembly method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110813110.XA CN113357114B (en) | 2021-07-19 | 2021-07-19 | Main cathode assembly structure applied to thruster and assembly method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113357114A true CN113357114A (en) | 2021-09-07 |
| CN113357114B CN113357114B (en) | 2022-05-06 |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114379824A (en) * | 2022-01-12 | 2022-04-22 | 哈尔滨工业大学 | Graphite touch electrode assembly of electric propulsion hollow cathode |
Citations (26)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EA001829B1 (en) * | 2000-02-10 | 2001-08-27 | Владимир Семенович Тверской | Plasma burner |
| US6818853B1 (en) * | 2003-05-30 | 2004-11-16 | Alameda Applied Sciences Corp. | Vacuum arc plasma thrusters with inductive energy storage driver |
| US20090294063A1 (en) * | 2001-05-18 | 2009-12-03 | Ulvac Inc. | Plasma processing apparatus |
| CN102678500A (en) * | 2012-05-10 | 2012-09-19 | 北京航空航天大学 | Magnetic plasma propeller |
| CN102800545A (en) * | 2012-08-30 | 2012-11-28 | 电子科技大学 | Cathode-adjustable single anode magnetic control electron gun |
| CN103560773A (en) * | 2013-10-17 | 2014-02-05 | 华中科技大学 | Bipolar trigger type multi-rod-electrode vacuum trigger switch |
| CN104612879A (en) * | 2015-01-19 | 2015-05-13 | 西安航天动力研究所 | High-back-pressure plasma igniter |
| CN105626410A (en) * | 2015-12-25 | 2016-06-01 | 上海空间推进研究所 | Plume neutralizer of space electric thruster |
| CN106246487A (en) * | 2016-08-26 | 2016-12-21 | 北京航空航天大学 | A kind of magnetic plasma propeller utilizing additional electromagnetic field energy to convert |
| CN106337791A (en) * | 2016-08-31 | 2017-01-18 | 北京航空航天大学 | Magnetic plasma thruster provided with conical porous hollow cathode |
| CN106373840A (en) * | 2016-08-31 | 2017-02-01 | 兰州空间技术物理研究所 | Graphite contact-holding electrode used for hollow negative electrode |
| CN106545479A (en) * | 2016-12-07 | 2017-03-29 | 兰州空间技术物理研究所 | A kind of Vacuum Arc thruster, multimode architecture, multi-mode implementation |
| CN107044396A (en) * | 2017-06-14 | 2017-08-15 | 北京航空航天大学 | A kind of water-cooling structure complementary field magnetic plasma propeller |
| CN107687404A (en) * | 2017-06-12 | 2018-02-13 | 北京航空航天大学 | A kind of negative electrode water-cooling structure of magnetic plasma propeller |
| CN107882702A (en) * | 2017-10-24 | 2018-04-06 | 哈尔滨工业大学 | Rafael nozzle formula magnetic confinement hollow cathode |
| CN108005869A (en) * | 2017-11-30 | 2018-05-08 | 中国人民解放军国防科技大学 | Ignition circuit for semiconductor spark plug of micro pulse plasma thruster |
| JP2018127917A (en) * | 2017-02-07 | 2018-08-16 | 株式会社Ｉｈｉエアロスペース | Hall thruster |
| EP3410462A1 (en) * | 2017-06-02 | 2018-12-05 | Xei Scientific, Inc. | Plasma device with an external rf hollow cathode for plasma cleaning of high vacuum systems |
| CN109236594A (en) * | 2018-09-14 | 2019-01-18 | 哈尔滨工业大学 | A kind of low-power magnetization electric propulsion hollow cathode thruster |
| CN109285745A (en) * | 2017-07-19 | 2019-01-29 | 刘梅 | A kind of Dual-anode magnetic control electronic gun with adjustable cathode |
| CN109441747A (en) * | 2018-11-02 | 2019-03-08 | 北京航空航天大学 | A kind of electric propulsion engine sparking mode |
| WO2019075051A1 (en) * | 2017-10-10 | 2019-04-18 | The George Washington University | Micro-propulsion system |
| CN110641740A (en) * | 2019-10-30 | 2020-01-03 | 哈尔滨工业大学 | Micro-cathode arc propeller |
| CN110677974A (en) * | 2019-11-13 | 2020-01-10 | 四川轻化工大学 | Plasma generator |
| CN209925157U (en) * | 2019-06-05 | 2020-01-10 | 中国人民解放军国防科技大学 | Expanding type self-magnetic field magnetic plasma thruster |
| CN111156141A (en) * | 2019-12-26 | 2020-05-15 | 兰州空间技术物理研究所 | Large-emission-current hollow cathode |
-
2021
- 2021-07-19 CN CN202110813110.XA patent/CN113357114B/en active Active
Patent Citations (26)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EA001829B1 (en) * | 2000-02-10 | 2001-08-27 | Владимир Семенович Тверской | Plasma burner |
| US20090294063A1 (en) * | 2001-05-18 | 2009-12-03 | Ulvac Inc. | Plasma processing apparatus |
| US6818853B1 (en) * | 2003-05-30 | 2004-11-16 | Alameda Applied Sciences Corp. | Vacuum arc plasma thrusters with inductive energy storage driver |
| CN102678500A (en) * | 2012-05-10 | 2012-09-19 | 北京航空航天大学 | Magnetic plasma propeller |
| CN102800545A (en) * | 2012-08-30 | 2012-11-28 | 电子科技大学 | Cathode-adjustable single anode magnetic control electron gun |
| CN103560773A (en) * | 2013-10-17 | 2014-02-05 | 华中科技大学 | Bipolar trigger type multi-rod-electrode vacuum trigger switch |
| CN104612879A (en) * | 2015-01-19 | 2015-05-13 | 西安航天动力研究所 | High-back-pressure plasma igniter |
| CN105626410A (en) * | 2015-12-25 | 2016-06-01 | 上海空间推进研究所 | Plume neutralizer of space electric thruster |
| CN106246487A (en) * | 2016-08-26 | 2016-12-21 | 北京航空航天大学 | A kind of magnetic plasma propeller utilizing additional electromagnetic field energy to convert |
| CN106337791A (en) * | 2016-08-31 | 2017-01-18 | 北京航空航天大学 | Magnetic plasma thruster provided with conical porous hollow cathode |
| CN106373840A (en) * | 2016-08-31 | 2017-02-01 | 兰州空间技术物理研究所 | Graphite contact-holding electrode used for hollow negative electrode |
| CN106545479A (en) * | 2016-12-07 | 2017-03-29 | 兰州空间技术物理研究所 | A kind of Vacuum Arc thruster, multimode architecture, multi-mode implementation |
| JP2018127917A (en) * | 2017-02-07 | 2018-08-16 | 株式会社Ｉｈｉエアロスペース | Hall thruster |
| EP3410462A1 (en) * | 2017-06-02 | 2018-12-05 | Xei Scientific, Inc. | Plasma device with an external rf hollow cathode for plasma cleaning of high vacuum systems |
| CN107687404A (en) * | 2017-06-12 | 2018-02-13 | 北京航空航天大学 | A kind of negative electrode water-cooling structure of magnetic plasma propeller |
| CN107044396A (en) * | 2017-06-14 | 2017-08-15 | 北京航空航天大学 | A kind of water-cooling structure complementary field magnetic plasma propeller |
| CN109285745A (en) * | 2017-07-19 | 2019-01-29 | 刘梅 | A kind of Dual-anode magnetic control electronic gun with adjustable cathode |
| WO2019075051A1 (en) * | 2017-10-10 | 2019-04-18 | The George Washington University | Micro-propulsion system |
| CN107882702A (en) * | 2017-10-24 | 2018-04-06 | 哈尔滨工业大学 | Rafael nozzle formula magnetic confinement hollow cathode |
| CN108005869A (en) * | 2017-11-30 | 2018-05-08 | 中国人民解放军国防科技大学 | Ignition circuit for semiconductor spark plug of micro pulse plasma thruster |
| CN109236594A (en) * | 2018-09-14 | 2019-01-18 | 哈尔滨工业大学 | A kind of low-power magnetization electric propulsion hollow cathode thruster |
| CN109441747A (en) * | 2018-11-02 | 2019-03-08 | 北京航空航天大学 | A kind of electric propulsion engine sparking mode |
| CN209925157U (en) * | 2019-06-05 | 2020-01-10 | 中国人民解放军国防科技大学 | Expanding type self-magnetic field magnetic plasma thruster |
| CN110641740A (en) * | 2019-10-30 | 2020-01-03 | 哈尔滨工业大学 | Micro-cathode arc propeller |
| CN110677974A (en) * | 2019-11-13 | 2020-01-10 | 四川轻化工大学 | Plasma generator |
| CN111156141A (en) * | 2019-12-26 | 2020-05-15 | 兰州空间技术物理研究所 | Large-emission-current hollow cathode |
Non-Patent Citations (8)
| Title |
|---|
| 卿绍伟等: "壁面二次电子发射对霍尔推力器放电通道绝缘壁面双鞘特性的影响", 《物理学报》 * |
| 宋茂江等: "Hall推力器一维流体模型的小波解", 《推进技术》 * |
| 李啸天等: "真空弧推力器构型设计发展现状", 《真空与低温》 * |
| 李照忠等: "基于Matlab的霍尔推力器低频振荡数学模型的研究与实现", 《山西大学学报(自然科学版)》 * |
| 田雷超等: "影响环形微阴极电弧推力器寿命的因素研究", 《宇航学报》 * |
| 田雷超等: "微阴极电弧推力器的设计与试验", 《推进技术》 * |
| 耿金越等: "微阴极电弧推力器磁路设计", 《中国空间科学技术》 * |
| 马宁等: "空心阴极微推力器研究进展", 《真空与低温》 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114379824A (en) * | 2022-01-12 | 2022-04-22 | 哈尔滨工业大学 | Graphite touch electrode assembly of electric propulsion hollow cathode |
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