CN114551024B - Stop gear and spacecraft magnetic buoyancy ware - Google Patents
Stop gear and spacecraft magnetic buoyancy ware Download PDFInfo
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- CN114551024B CN114551024B CN202210143234.6A CN202210143234A CN114551024B CN 114551024 B CN114551024 B CN 114551024B CN 202210143234 A CN202210143234 A CN 202210143234A CN 114551024 B CN114551024 B CN 114551024B
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- 230000007246 mechanism Effects 0.000 claims abstract description 19
- 230000000712 assembly Effects 0.000 abstract description 20
- 238000000429 assembly Methods 0.000 abstract description 20
- 238000000034 method Methods 0.000 abstract description 5
- 230000008569 process Effects 0.000 abstract description 2
- 238000009434 installation Methods 0.000 description 6
- 238000000926 separation method Methods 0.000 description 3
- 230000003068 static effect Effects 0.000 description 3
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 229910052742 iron Inorganic materials 0.000 description 1
- 229910000889 permalloy Inorganic materials 0.000 description 1
Classifications
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01F—MAGNETS; INDUCTANCES; TRANSFORMERS; SELECTION OF MATERIALS FOR THEIR MAGNETIC PROPERTIES
- H01F5/00—Coils
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
- B64G1/645—Separators
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01F—MAGNETS; INDUCTANCES; TRANSFORMERS; SELECTION OF MATERIALS FOR THEIR MAGNETIC PROPERTIES
- H01F27/00—Details of transformers or inductances, in general
- H01F27/28—Coils; Windings; Conductive connections
- H01F27/30—Fastening or clamping coils, windings, or parts thereof together; Fastening or mounting coils or windings on core, casing, or other support
- H01F27/306—Fastening or mounting coils or windings on core, casing or other support
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01F—MAGNETS; INDUCTANCES; TRANSFORMERS; SELECTION OF MATERIALS FOR THEIR MAGNETIC PROPERTIES
- H01F7/00—Magnets
- H01F7/02—Permanent magnets [PM]
- H01F7/0231—Magnetic circuits with PM for power or force generation
- H01F7/0236—Magnetic suspension or levitation
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- Aviation & Aerospace Engineering (AREA)
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- Electromagnetism (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Radar, Positioning & Navigation (AREA)
- Electromagnets (AREA)
- Linear Motors (AREA)
Abstract
The application provides a limiting mechanism and a spacecraft magnetic buoyancy device. The limiting mechanism comprises a limiting structure; the limiting structure is used for limiting the movement range of the coil assembly relative to the magnetic pole assembly and the shell of the spacecraft magnetic buoyancy device. The first limiting assembly comprises a first fixed rod assembly, a second fixed rod assembly, a first fixed ring assembly and a second fixed ring assembly. The second limiting assembly comprises a third fixed rod assembly, a fourth fixed rod assembly, a third fixed ring assembly and a fourth fixed ring assembly. By limiting the range of motion of the first, second, third, and fourth fixed rod assemblies, the range of motion of the coil assembly can be limited. The limiting mechanism provided by the application can limit the mutual movement range of the shell and the coil bracket in three moving directions and three rotating directions in the ground debugging and on-orbit running processes, ensures the safety of products, and has good processing manufacturability and assembly manufacturability.
Description
Technical Field
The application relates to the field of spacecrafts, in particular to a limiting mechanism and a spacecraft magnetic buoyancy device.
Background
The dynamic and static separation type satellite platform breaks through the traditional design thought of the fixed connection of the satellite load and the platform, adopts a brand new design method of 'dynamic and static separation non-contact and master-slave decoupling high precision' based on a magnetic buoyancy device, breaks through the technical bottleneck of 'difficult detection and difficult control' of micro vibration in the fixed connection design method, and can fundamentally solve the important problem that the load pointing precision and stability are difficult to be greatly improved. The magnetic buoyancy device is an important executing mechanism in a dynamic and static separation type satellite platform control system. The general structure is composed of a coil and a magnetic pole, and the coil and the magnetic pole are not in physical contact and can move mutually.
However, in the fault state, the fragile coil inside the magnetic buoyancy device may directly collide with the hard magnetic pole or the shell, so that the coil is short-circuited and broken or redundant is generated. Therefore, the contact between the coil and the magnetic pole or the shell is prevented from being one of the key steps of designing the magnetic buoyancy device under the fault state, and the limiting device for protecting the collision of the coil is also one of the key parts of the magnetic buoyancy device.
Patent document CN108945524a discloses a magnetic buoyancy device for a spacecraft, which comprises an outer shield, an inner shield movably arranged in the outer shield, permanent magnets fixed at the middle parts of two inner side walls of the inner shield, and a coil fixed at the inner central position of the outer shield through a coil bracket, wherein the two permanent magnets are arranged at two sides of the coil; the outer shield is of a U-shaped structure, the inner shield is of an inverted U-shaped structure, the inner shield and the outer shield are in fit and sleeve joint, the gap between the outer wall of the inner shield and the outer wall of the outer shield is not less than 5mm, the gap between the end face of an opening of the inner shield and the inner bottom face of the outer shield is not less than 5mm, and mechanical limit is arranged in all movement directions between the inner shield and the outer shield under the working state; the coil and the outer shield are connected with the spacecraft platform, the permanent magnets are connected with the controlled load, and the electrified coil generates electromagnetic force in a magnetic field between the permanent magnets to adjust the gesture precision of the controlled load. However, the limiting rod of the scheme is not easy to install, and the limiting rigidity is weak.
Disclosure of Invention
Aiming at the defects in the prior art, the application aims to provide a limiting mechanism and a spacecraft magnetic buoyancy device.
The limiting mechanism comprises a limiting structure; the limiting structure is used for limiting the movement range of the coil assembly relative to the magnetic pole assembly and the shell of the spacecraft magnetic buoyancy device;
the limiting structure, the coil component and the magnetic pole component are all arranged on the shell;
the limiting structure comprises a first limiting component and a second limiting component;
the first limiting assembly comprises a first fixed rod assembly, a second fixed rod assembly, a first fixed ring assembly and a second fixed ring assembly;
the first fixed rod assembly and the second fixed rod assembly are both arranged on the coil assembly, and the first fixed ring assembly and the second fixed ring assembly are both arranged on the magnetic pole assembly;
the first fixed rod assembly is matched with the first fixed ring assembly, and the first fixed ring assembly can limit the movement range of the first fixed rod assembly; the second fixed rod assembly is matched with the second fixed ring assembly; and the second fixed ring assembly is capable of limiting the range of motion of the second fixed rod assembly;
the second limiting assembly comprises a third fixed rod assembly, a fourth fixed rod assembly, a third fixed ring assembly and a fourth fixed ring assembly;
the third fixed rod assembly and the fourth fixed rod assembly are both arranged on the coil assembly, and the third fixed ring assembly and the fourth fixed ring assembly are both arranged on the magnetic pole assembly;
the third fixed rod assembly is matched with the third fixed ring assembly, and the third fixed ring assembly can limit the movement range of the third fixed rod assembly; the fourth fixed rod component is matched with the fourth fixed ring component; and the fourth stationary ring assembly is capable of limiting a range of motion of the fourth stationary rod assembly;
by limiting the movement ranges of the first, second, third, and fourth fixed rod assemblies, the movement range of the coil assembly can be limited.
Preferably, the first fixing rod assembly comprises a first limiting part and a first mounting part, and the second fixing rod assembly comprises a second limiting part and a second mounting part;
the first limiting part comprises a first connecting piece and a second connecting piece;
the second limiting part comprises a third connecting piece and a fourth connecting piece;
one end of the first connecting piece is integrally connected with the first mounting part, the other end of the first connecting piece is connected with the second connecting piece, and the first mounting part is mounted on the coil assembly;
one end of the third connecting piece is integrally connected with the second mounting part, the other end of the third connecting piece is connected with the fourth connecting piece, and the second mounting part is mounted on the coil assembly;
the first fixed rod assembly is arranged above the second fixed rod assembly, and the first fixed rod assembly and the second fixed rod assembly are oppositely arranged;
the first fixing rod assembly and the second fixing rod assembly are matched with the first fixing ring assembly and the second fixing ring assembly through the second connecting piece and the fourth connecting piece respectively;
the structures of the third fixed rod assembly and the fourth fixed rod assembly are respectively the same as those of the first fixed rod assembly and the second fixed rod assembly.
Preferably, the first fixing ring assembly includes a first limiting ring portion and a fifth mounting portion; the second fixing ring assembly comprises a second limiting ring part and a sixth mounting part;
the first limiting ring part and the second limiting ring part are respectively and integrally connected with the fifth mounting part and the sixth mounting part;
the first limiting ring part and the second limiting ring part are respectively provided with a first hollow part and a second hollow part;
one end of the second connecting piece and the first connecting piece are positioned below the first limiting ring part, and the other end of the second connecting piece penetrates through the first hollow part and extends to the upper side of the first limiting ring part; the distance between the first connecting piece and the first limiting ring part allows the top end of the first connecting piece to move to abut against the bottom end of the first limiting ring part;
one end of the fourth connecting piece and the third connecting piece are positioned above the second hollow part, and the other end of the fourth connecting piece penetrates through the second hollow part and extends to the lower part of the second limiting ring part; the distance between the third connecting piece and the second limiting ring part allows the bottom end of the third connecting piece to move to abut against the top end of the second limiting ring part;
the first hollow portion is sized to allow the second connector to move to the edge of the first hollow portion, wherein the inner ring of the first defining ring portion prevents the second connector from continuing to move in the original direction;
the second hollow portion is sized to allow movement of the fourth connector to the edge of the second hollow portion, wherein the inner ring of the second defining ring portion prevents continued movement of the fourth connector in the original direction;
the structures of the third fixed ring component and the fourth fixed ring component are respectively the same as those of the first fixed ring component and the second fixed ring component.
Preferably, the shape of the first hollow part and the second hollow part is round, oval or square.
The spacecraft magnetic buoyancy device provided by the application comprises the limiting mechanism, a shell, a coil assembly and a magnetic pole assembly
The coil assembly includes a coil and a coil support; the coil support comprises a vertical beam assembly;
the vertical beam assembly is fixedly connected with the coil;
the vertical beam assembly comprises a first vertical beam and a second vertical beam and is arranged at two ends of the coil;
the first fixing rod assembly and the second fixing rod assembly are sequentially sleeved on the first vertical beam from top to bottom along the axial direction of the first vertical beam.
The third fixing rod assembly and the fourth fixing rod assembly are sequentially sleeved on the second vertical beam from top to bottom along the axial direction of the second vertical beam;
the positions of the third fixed rod assembly and the fourth fixed rod assembly correspond to the positions of the first fixed rod assembly and the second fixed rod assembly respectively.
Preferably, the magnetic pole component comprises a magnetic pole, an inner framework and an end cover;
the magnetic pole is fixedly arranged on the inner framework, and the first fixed ring component and the third fixed ring component are fixedly arranged on the inner framework;
the two ends of the inner framework are respectively provided with a supporting part, the lower ends of the supporting parts are fixedly connected with the upper ends of the end covers, and the inner framework is supported in the middle of the shell;
the end cover is arranged at the bottom end of the shell, and the second fixed ring component and the fourth fixed ring component are fixedly arranged on the end cover;
the positions of the third fixed ring component and the fourth fixed ring component respectively correspond to the positions of the first fixed ring component and the second fixed ring component.
Preferably, the first fixing ring assembly is connected with the inner skeleton through a connecting piece.
Preferably, the second retaining ring assembly is connected to the end cap by a connector.
Preferably, the support part is connected with the upper end of the end cover through a connecting piece.
Preferably, the vertical beam assembly is connected to the coil by a connector.
Compared with the prior art, the application has the following beneficial effects:
1. the limiting mechanism and the spacecraft magnetic buoyancy device provided by the application can limit the movement range of the coil assembly relative to the shell and the magnetic pole assembly in three moving directions and three rotating directions in the ground debugging and on-orbit running processes, ensure the safety of products, and have good processing manufacturability and assembly manufacturability.
2. The application adopts a large amount of fasteners to connect the components, is convenient to install and is easy to detach.
3. The application has compact integral structure, compact appearance and good applicability.
Drawings
Other features, objects and advantages of the present application will become more apparent upon reading of the detailed description of non-limiting embodiments, given with reference to the accompanying drawings in which:
FIG. 1 is a schematic structural view of a spacecraft magnetic buoyancy device in the application, wherein the installation structure of a limiting mechanism is shown;
FIG. 2 is a schematic view of the installation structure of a first fixed rod assembly, a second fixed rod assembly, a third fixed rod assembly, a fourth fixed rod assembly, a second fixed ring assembly and a fourth fixed ring assembly of the spacecraft magnetic buoyancy device according to the present application, wherein the installation structure of the limiting mechanism is shown;
FIG. 3 is a schematic view of the mounting structure of the first fixing rod assembly and the first fixing ring assembly of the limiting mechanism according to the present application;
FIG. 4 is a schematic view of the installation structure of the first fixed ring assembly and the third fixed ring assembly of the spacecraft magnetic buoyancy device according to the application, wherein the installation structure of the limiting mechanism is shown;
FIG. 5a is a schematic view showing a coil assembly in a spacecraft magnetic buoyancy device moving in parallel to a limit position in the +Z direction;
FIG. 5b is a schematic view showing the coil assembly moving in parallel in the-Z direction to the extreme position in the spacecraft magnetic buoyancy device according to the present application;
FIG. 5c is a schematic view showing the coil assembly moving in parallel to the +X direction to the extreme position in the spacecraft magnetic buoyancy device according to the present application;
FIG. 5d is a schematic view showing the coil assembly moving in parallel in the-X direction to the extreme position in the spacecraft magnetic buoyancy device according to the present application;
FIG. 5e is a schematic view of the coil assembly of the spacecraft magnetic buoyancy device of the present application moving in parallel in the-Y direction to an extreme position;
FIG. 5f is a schematic view showing the coil assembly in the spacecraft magnetic buoyancy device moving in parallel to the limit position in the +Y direction;
FIG. 6a is a schematic view of a rotational movement of a coil assembly in a +Z-axis counter-clockwise direction to an extreme position in a spacecraft magnetic buoyancy device according to the present application;
FIG. 6b is a schematic view of the rotational movement of the coil assembly to the extreme position in the +Z-axis clockwise direction in the spacecraft magnetic buoyancy device of the present application;
FIG. 6c is a schematic view of the rotational movement of the coil assembly to the extreme position in the +Y-axis clockwise direction in the spacecraft magnetic buoyancy device of the present application;
FIG. 6d is a schematic view of the rotational movement of the coil assembly in the +Y-axis counterclockwise direction to an extreme position in the spacecraft magnetic buoyancy device of the present application;
FIG. 6e is a schematic view of the rotational movement of the coil assembly in the +X-axis counter-clockwise direction to an extreme position in the spacecraft magnetic buoyancy device of the present application;
FIG. 6f is a schematic view of the rotational movement of the coil assembly to the extreme position in the +X direction in the spacecraft magnetic buoyancy according to the present application.
The figure shows:
Detailed Description
The present application will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the present application, but are not intended to limit the application in any way. It should be noted that variations and modifications could be made by those skilled in the art without departing from the inventive concept. These are all within the scope of the present application.
The application provides a limiting mechanism, which comprises a limiting structure.
The limiting structure is used for limiting the movement range of the coil assembly relative to the magnetic pole assembly and the shell 33 in the spacecraft magnetic buoyancy device. Under normal conditions, both the coil assembly and the pole assembly are free of physical contact and are relatively movable.
As shown in fig. 1, the limit structure, the coil assembly, and the magnetic pole assembly are all mounted on the housing 33. The limiting structure comprises a first limiting component and a second limiting component. The first limiting assembly comprises a first fixed rod assembly 1, a second fixed rod assembly 2, a first fixed ring assembly 3 and a second fixed ring assembly 4. The first fixing rod assembly 1 and the second fixing rod assembly 2 are both installed on the coil assembly, and the first fixing ring assembly 3 and the second fixing ring assembly 4 are both installed on the magnetic pole assembly. The first fixed rod assembly 1 is matched with the first fixed ring assembly 3, and the first fixed ring assembly 3 can limit the movement range of the first fixed rod assembly 1; the second fixed rod assembly 2 is matched with the second fixed ring assembly 4; and the second fixing ring assembly 4 can limit the movement range of the second fixing rod assembly 2.
The second limiting component comprises a third fixed rod component 23, a fourth fixed rod component 24, a third fixed ring component 25 and a fourth fixed ring component 26. The third fixing rod assembly 23 and the fourth fixing rod assembly 24 are all installed on the coil assembly, and the third fixing ring assembly 25 and the fourth fixing ring assembly 26 are all installed on the magnetic pole assembly. The third fixed rod assembly 23 is matched with the third fixed ring assembly 25, and the third fixed ring assembly 25 can limit the movement range of the third fixed rod assembly 23; the fourth securing lever assembly 24 mates with the fourth securing ring assembly 26; and the fourth retaining ring assembly 26 is capable of limiting the range of motion of the fourth retaining rod assembly 24. By limiting the movement ranges of the first, second, third, and fourth fixed rod assemblies 1, 2, 23, 24, the movement range of the coil assembly can be limited.
As shown in fig. 1, 2 and 3, the first fixing rod assembly 1 includes a first limiting portion 5 and a first mounting portion 6, and the second fixing rod assembly 2 includes a second limiting portion 7 and a second mounting portion 8. The first limiting part 5 comprises a first connecting piece 9 and a second connecting piece 10. The second limiting portion 7 comprises a third connecting piece 11 and a fourth connecting piece 12. One end of the first connecting piece 9 is integrally connected with the first mounting part 6, the other end of the first connecting piece 9 is connected with the second connecting piece 10, and the first mounting part 6 is mounted on the coil assembly. In a preferred embodiment, the first connector 9 is arranged perpendicular to the second connector 10. One end of the third connecting piece 11 is integrally connected with the second mounting portion 8, the other end of the third connecting piece 11 is connected with the fourth connecting piece 12, and the second mounting portion 8 is mounted on the coil assembly. In a preferred embodiment, the third connecting member 11 is disposed perpendicularly to the fourth connecting member 12. The first fixing rod assembly 1 is arranged above the second fixing rod assembly 2, and the first fixing rod assembly 1 and the second fixing rod assembly 2 are reversely arranged.
The first fixing rod assembly 1 and the second fixing rod assembly 2 are respectively matched with the first fixing ring assembly 3 and the second fixing ring assembly 4 through the second connecting piece 10 and the fourth connecting piece 12. The third and fourth fixing rod assemblies 23 and 24 have the same structures as the first and second fixing rod assemblies 1 and 2, respectively.
As shown in fig. 1, 2, 3, 4, the first stationary ring assembly 3 includes a first defined ring portion 13 and a fifth mounting portion 14; the second retaining ring assembly 4 includes a second confinement ring portion 15 and a sixth mounting portion. The first limiting ring portion 13 and the second limiting ring portion 15 are integrally connected to the fifth mounting portion 14 and the sixth mounting portion, respectively.
The first and second limiting ring portions 13 and 15 have first and second hollow portions 16 and 17, respectively. In a preferred embodiment, the first hollow portion 16 and the second hollow portion 17 are circular, elliptical or square in shape.
One end of the second connecting piece 10 and the first connecting piece 9 are located below the first limiting ring part 13, and the other end of the second connecting piece 10 passes through the first hollow part 16 and extends to above the first limiting ring part 13; the distance of the first connecting piece 9 from the first defined ring portion 13 allows the top end of the first connecting piece 9 to move in the +z direction against the bottom end of the first defined ring portion 13. At this time, the first connecting piece 9 is blocked by the bottom end of the first limiting ring portion 13, and the first connecting piece 9 cannot continue to move in the +z direction. The origin of the coordinate system formed by +Z, -Z, +X, -X, +Y, -Y is located in the center of the coil 18, and in the drawing, the coordinate system is drawn to the upper right of the drawing in order to avoid overlapping of the coordinate system with the component and to interfere with the reading of the drawing
One end of the fourth connecting member 12 and the third connecting member 11 are located above the second hollow portion 17, and the other end of the fourth connecting member 12 passes through the second hollow portion 17 and extends below the second limiting ring portion 15; the distance of the third connecting piece 11 from the second limiting ring 15 allows the bottom end of the third connecting piece 11 to move in the-Z direction against the top end of the second limiting ring 15. At this time, the third link 11 is blocked by the tip of the second limiting ring portion 15, and the third link 11 cannot continue to move in the-Z direction.
The first hollow portion 16 is sized to allow the second connector 10 to move in any one of the directions +x, -X, +y, -Y, or any combination of the directions to the edge of the first hollow portion 16, where the inner ring of the first confinement ring portion 13 prevents the second connector 10 from continuing to move in the original direction.
The second hollow portion 17 is sized to allow the fourth connector 12 to move in any one of the directions +x, -X, +y, -Y, or any combination of the directions to the edge of the second hollow portion 17, where the inner ring of the second confinement ring portion 15 prevents the fourth connector 12 from continuing to move in the original direction.
The third and fourth fixed ring assemblies 25 and 26 have the same structures as the first and second fixed ring assemblies 3 and 4, respectively.
The third hollow portion of the third fixing ring assembly 25 is sized to allow the sixth link 29 of the third fixing rod assembly 23 to move in any one of the +x direction, -X direction, +y direction, -Y direction, or any combination of the above to the edge of the third hollow portion, while the inner ring of the third limiting ring portion 30 of the third fixing ring assembly 25 prevents the sixth link 29 from continuing to move in the original direction.
The fourth hollow portion of the fourth retaining ring assembly 26 is sized to allow the eighth link 32 of the fourth retaining rod assembly 24 to move in any one of the +X direction, -X direction, +Y direction, -Y direction, or any combination thereof to the edge of the fourth hollow portion, wherein the inner ring of the fourth limiting ring 31 of the fourth retaining ring assembly 26 prevents the eighth link 32 from continuing to move in the original direction.
Therefore, when the coil assembly moves along any one of the directions of +X direction, -X direction, +Y direction, -Y direction, +Z direction and-Z direction or any combination of the directions, the corresponding fixed ring assembly can prevent the corresponding fixed rod assembly from moving continuously towards the original direction, so that the purpose of limiting the movement of the coil assembly is achieved. It is noted that when the coil assembly is rotated about any one of the X-direction, the Y-direction, the Z-direction, or a combination of any of the plurality of directions, the corresponding securing ring assembly also prevents the corresponding securing lever assembly from continuing to rotate about the original direction, thereby limiting movement of the coil assembly.
The application also provides a spacecraft magnetic buoyancy device, which comprises the limiting mechanism, a shell 33, a coil assembly and a magnetic pole assembly. The housing 33 has a shielding function, and mainly functions to realize magnetic shielding, thereby greatly reducing magnetic leakage. In a preferred embodiment, the housing may be made of permalloy (1J 50, 1J 22) or industrial pure iron (DT-4), and the coil assembly includes the coil 18 and a coil support; the coil support comprises a vertical beam assembly; the vertical beam assembly is securely connected to the coil 18.
The vertical beam assembly comprises a first vertical beam 19 and a second vertical beam 28, and is arranged at two ends of the coil 18; the first fixing rod assembly 1 and the second fixing rod assembly 2 are sequentially sleeved on the first vertical beam 19 from top to bottom along the axial direction of the first vertical beam 19. The third fixing rod assembly 23 and the fourth fixing rod assembly 24 are sleeved on the second vertical beam 28 in sequence from top to bottom along the axial direction of the second vertical beam 28; the positions of the third fixing rod assembly 23 and the fourth fixing rod assembly 24 correspond to the positions of the first fixing rod assembly 1 and the second fixing rod assembly 2 respectively. The vertical beam assembly is connected to the coil 18 by a connector, which in one preferred embodiment is a screw.
The magnetic pole assembly comprises a magnetic pole 20, an inner framework 21 and an end cover 22. The magnetic pole 20 is fixedly arranged on the inner framework 21, and the first fixed ring assembly 3 and the third fixed ring assembly 25 are fixedly arranged on the inner framework 21; both ends of the inner frame 21 are provided with supporting parts 27, and the lower ends of the supporting parts 27 are fixedly connected with the upper ends of the end covers 22 to support the inner frame 21 in the middle of the shell. The end cap 22 is mounted at the bottom end of the housing, and the second and fourth retaining ring assemblies 4 and 26 are securely mounted to the end cap 22. The positions of the third fixing ring assembly 25 and the fourth fixing ring assembly 26 correspond to the positions of the first fixing ring assembly 3 and the second fixing ring assembly 4 respectively.
The first retaining ring assembly 3 is connected to the inner frame 21 by a connector, which in a preferred embodiment is a screw.
The second retaining ring assembly 4 is connected to the end cap 22 by a connector, which in a preferred embodiment is a screw.
The support 27 is connected to the upper end of the end cap 22 by a connector, which in a preferred embodiment is a screw.
The installation method of the application is as follows: as shown in fig. 2, the vertical beam assembly is threaded into the end cap 22, and then the first, third, second and fourth fixing bar assemblies 1, 23, 2 and 24 are installed on the vertical beam assembly. The second retaining ring assembly 4 and the fourth retaining ring assembly 26 are then mounted to the end cap 22. The second fixed ring component 4 and the fourth fixed ring component 26 are required to be sleeved into the second fixed rod component 2 and the fourth fixed rod component 24 respectively, and then the coil 18 and other components are installed to form a coil bracket assembly;
next, as shown in fig. 4, the first fixing ring assembly 3 and the third fixing ring assembly 25 are installed on the upper end surface of the inner frame 21, and then the inner frame 21 is installed into the outer shell; then, the coil support assembly is fitted into the housing from the open end at the bottom of the housing, and the first fixing rod assembly 1 and the third fixing rod assembly 23 are respectively fitted into the first fixing ring assembly 3 and the third fixing ring assembly 25, and the end cap 22 is mounted to the bottom of the inner bobbin 21 using screws, and finally the end cap 22 in the coil support assembly is fixed to the housing to form a closed housing.
When the spacecraft magnetic buoyancy device generates motion of the coil assembly relative to the magnetic pole assembly and the shell due to faults or other reasons, the working principle of the application is as follows:
as shown in fig. 5 a; when the coil 18 and the vertical beam assembly move to a certain distance along the +Z direction, the first connecting piece 9 and the third fixed rod assembly 23 are respectively limited by the first fixed ring assembly 3 and the third fixed ring assembly 25 to move continuously along the +Z direction, so that the coil assemblies connected with the first fixed rod assembly 1 and the third fixed rod assembly 23 also stop moving along the +Z direction, and the purposes of limiting the movement of the coil assemblies and avoiding collision of the coil assemblies with other components are achieved.
As shown in fig. 5 b; when the coil 18 and the vertical beam assembly move to a certain distance along the-Z direction, the third connecting piece 11 and the fourth fixing rod assembly 24 are respectively limited by the second fixing ring assembly 4 and the fourth fixing ring assembly 26 to move along the-Z direction, so that the coil assemblies connected with the second fixing rod assembly 2 and the fourth fixing rod assembly 24 also stop moving along the-Z direction, and the purposes of limiting the movement of the coil assemblies and avoiding collision of the coil assemblies with other components are achieved.
As shown in fig. 5c, as shown in fig. 5d, as shown in fig. 5e, as shown in fig. 5 f; when the coil 18 and the vertical beam assembly move to a certain distance along the +X direction, -X direction, -Y direction or +Y direction, the first fixed rod assembly 1, the second fixed rod assembly 2, the third fixed rod assembly 23 and the fourth fixed rod assembly 24 are respectively limited by the first fixed ring assembly 3, the second fixed ring assembly 4, the third fixed ring assembly 25 and the fourth fixed ring assembly 26 to continue to move along the original direction. Therefore, the coil assemblies connected with the first fixing rod assembly 1, the second fixing rod assembly 2, the third fixing rod assembly 23 and the fourth fixing rod assembly 24 also stop moving along the original direction, so that the purposes of limiting the movement of the coil assemblies and avoiding collision of the coil assemblies with other components are achieved.
As shown in fig. 6a, when the coil 18 and the vertical beam assembly rotate around the +z axis counterclockwise by a certain angle, the first fixing rod assembly 1 and the second fixing rod assembly 2 are respectively limited by the first fixing ring assembly 3 and the second fixing ring assembly 4 to continue moving.
As shown in fig. 6b, when the coil 18 and the vertical beam assembly rotate clockwise around the +z axis by a certain angle, the third fixing rod assembly 23 and the fourth fixing rod assembly 24 are respectively limited by the third fixing ring assembly 25 and the fourth fixing ring assembly 26 to continue moving.
As shown in fig. 6c, when the coil 18 and the vertical beam assembly rotate around +y clockwise by a certain angle, the first fixing rod assembly 1 and the third fixing rod assembly 23 are limited to continue movement by the first fixing ring assembly 3 and the third fixing ring assembly 25, respectively.
When the coil 18 and the vertical beam assembly are rotated around the +y counterclockwise direction by a certain angle, the second and fourth fixed rod assemblies 2, 24 are restricted from continuing movement by the second and fourth fixed ring assemblies 4, 26, respectively, as shown in fig. 6 d.
As shown in fig. 6e, when the coil 18 and the vertical beam assembly rotate around the +x counterclockwise direction by a certain angle, the first fixing rod assembly 1 and the fourth fixing rod assembly 24 are respectively limited by the first fixing ring assembly 3 and the fourth fixing ring assembly 26 to continue moving.
As shown in fig. 6f, when the coil 18 and the vertical beam assembly rotate around the +x clockwise direction by a certain angle, the third fixing rod assembly 23 and the second fixing rod assembly 2 are respectively limited by the third fixing ring assembly 25 and the second fixing ring assembly 4 to continue moving.
In the description of the present application, it should be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are merely for convenience in describing the present application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present application.
The foregoing describes specific embodiments of the present application. It is to be understood that the application is not limited to the particular embodiments described above, and that various changes or modifications may be made by those skilled in the art within the scope of the appended claims without affecting the spirit of the application. The embodiments of the application and the features of the embodiments may be combined with each other arbitrarily without conflict.
Claims (9)
1. A limiting mechanism, which is characterized by comprising a limiting structure; the limiting structure is used for limiting the movement range of the coil assembly relative to the magnetic pole assembly and the shell (33) in the spacecraft magnetic buoyancy device;
the limiting structure, the coil component and the magnetic pole component are all arranged on the shell (33);
the limiting structure comprises a first limiting component and a second limiting component;
the first limiting assembly comprises a first fixed rod assembly (1), a second fixed rod assembly (2), a first fixed ring assembly (3) and a second fixed ring assembly (4);
the first fixed rod assembly (1) and the second fixed rod assembly (2) are both arranged on the coil assembly, and the first fixed ring assembly (3) and the second fixed ring assembly (4) are both arranged on the magnetic pole assembly;
the first fixed rod assembly (1) is matched with the first fixed ring assembly (3), and the first fixed ring assembly (3) can limit the movement range of the first fixed rod assembly (1); the second fixed rod assembly (2) is matched with the second fixed ring assembly (4); and the second fixed ring assembly (4) can limit the movement range of the second fixed rod assembly (2);
the second limiting assembly comprises a third fixed rod assembly (23), a fourth fixed rod assembly (24), a third fixed ring assembly (25) and a fourth fixed ring assembly (26);
the third fixed rod assembly (23) and the fourth fixed rod assembly (24) are both arranged on the coil assembly, and the third fixed ring assembly (25) and the fourth fixed ring assembly (26) are both arranged on the magnetic pole assembly;
the third fixed rod assembly (23) is matched with the third fixed ring assembly (25), and the third fixed ring assembly (25) can limit the movement range of the third fixed rod assembly (23); the fourth stationary bar assembly (24) cooperates with the fourth stationary ring assembly (26); and the fourth stationary ring assembly (26) is capable of limiting the range of motion of the fourth stationary rod assembly (24);
the movement range of the coil assembly can be limited by limiting the movement ranges of the first fixed rod assembly (1), the second fixed rod assembly (2), the third fixed rod assembly (23) and the fourth fixed rod assembly (24);
the first fixed rod assembly (1) comprises a first limiting part (5) and a first mounting part (6), and the second fixed rod assembly (2) comprises a second limiting part (7) and a second mounting part (8);
the first limiting part (5) comprises a first connecting piece (9) and a second connecting piece (10);
the second limiting part (7) comprises a third connecting piece (11) and a fourth connecting piece (12);
one end of the first connecting piece (9) is integrally connected with the first mounting part (6), the other end of the first connecting piece (9) is connected with the second connecting piece (10), and the first mounting part (6) is mounted on the coil assembly;
one end of the third connecting piece (11) is integrally connected with the second mounting part (8), the other end of the third connecting piece (11) is connected with the fourth connecting piece (12), and the second mounting part (8) is mounted on the coil assembly;
the first fixed rod assembly (1) is arranged above the second fixed rod assembly (2), and the first fixed rod assembly (1) and the second fixed rod assembly (2) are reversely arranged;
the first fixed rod assembly (1) and the second fixed rod assembly (2) are respectively matched with the first fixed ring assembly (3) and the second fixed ring assembly (4) through the second connecting piece (10) and the fourth connecting piece (12);
the structures of the third fixing rod assembly (23) and the fourth fixing rod assembly (24) are respectively the same as those of the first fixing rod assembly (1) and the second fixing rod assembly (2).
2. A spacing mechanism according to claim 1, characterized in that the first fixed ring assembly (3) comprises a first limiting ring portion (13) and a fifth mounting portion (14); the second stationary ring assembly (4) comprises a second defined ring portion (15) and a sixth mounting portion;
the first limiting ring part (13) and the second limiting ring part (15) are respectively and integrally connected with the fifth mounting part (14) and the sixth mounting part;
the first limiting ring part (13) and the second limiting ring part (15) are respectively provided with a first hollow part (16) and a second hollow part (17);
one end of the second connecting piece (10) and the first connecting piece (9) are positioned below the first limiting ring part (13), and the other end of the second connecting piece (10) passes through the first hollow part (16) and extends to the upper part of the first limiting ring part (13); the distance of the first connecting piece (9) from the first limiting ring part (13) allows the top end of the first connecting piece (9) to move to abut against the bottom end of the first limiting ring part (13);
one end of the fourth connecting piece (12) and the third connecting piece (11) are positioned above the second hollow part (17), and the other end of the fourth connecting piece (12) penetrates through the second hollow part (17) and extends to the lower part of the second limiting ring part (15); the distance of the third connecting piece (11) from the second limiting ring part (15) allows the bottom end of the third connecting piece (11) to move to abut against the top end of the second limiting ring part (15);
the first hollow portion (16) is sized to allow the second connector (10) to move to the edge of the first hollow portion (16), wherein the inner ring of the first limiting ring portion (13) prevents the second connector (10) from continuing to move in the original direction;
the second hollow portion (17) is sized to allow the fourth connecting member (12) to move to the edge of the second hollow portion (17) when the inner ring of the second limiting ring portion (15) prevents the fourth connecting member (12) from continuing to move in the original direction;
the third fixed ring component (25) and the fourth fixed ring component (26) have the same structures as the first fixed ring component (3) and the second fixed ring component (4) respectively.
3. A spacing mechanism according to claim 2, characterized in that the first hollow part (16), the second hollow part (17) are circular, oval or square in shape.
4. A spacecraft magnetic buoyancy device, characterized by comprising the limit mechanism of any one of claims 1 to 3, further comprising a housing (33), a coil assembly, and a pole assembly;
the coil assembly includes a coil (18) and a coil support; the coil support comprises a vertical beam assembly;
the vertical beam assembly is fixedly connected with the coil (18);
the vertical beam assembly comprises a first vertical beam (19) and a second vertical beam (28) and is arranged at two ends of the coil (18);
the first fixing rod assembly (1) and the second fixing rod assembly (2) are sequentially sleeved on the first vertical beam (19) from top to bottom along the axial direction of the first vertical beam (19);
the third fixing rod assembly (23) and the fourth fixing rod assembly (24) are sequentially sleeved on the second vertical beam (28) from top to bottom along the axial direction of the second vertical beam (28);
the positions of the third fixing rod assembly (23) and the fourth fixing rod assembly (24) respectively correspond to the positions of the first fixing rod assembly (1) and the second fixing rod assembly (2).
5. The spacecraft magnetic buoyancy according to claim 4 wherein the pole assembly comprises a pole (20), an inner frame (21), an end cap (22);
the magnetic pole (20) is fixedly arranged on the inner framework (21), and the first fixed ring assembly (3) and the third fixed ring assembly (25) are fixedly arranged on the inner framework (21);
both ends of the inner framework (21) are provided with supporting parts (27), the lower ends of the supporting parts (27) are fixedly connected with the upper ends of the end covers (22), and the inner framework (21) is supported in the middle of the outer shell (33);
the end cover (22) is arranged at the bottom end of the shell, and the second fixed ring assembly (4) and the fourth fixed ring assembly (26) are fixedly arranged on the end cover (22);
the positions of the third fixed ring component (25) and the fourth fixed ring component (26) respectively correspond to the positions of the first fixed ring component (3) and the second fixed ring component (4).
6. Spacecraft magnetic buoyancy according to claim 5, characterized in that the first stationary ring assembly (3) is connected to the inner skeleton (21) by means of a connection.
7. Spacecraft magnetic buoyancy according to claim 5, characterized in that the second stationary ring assembly (4) is connected to the end cap (22) by a connection.
8. Spacecraft magnetic buoyancy according to claim 5, characterized in that the support part (27) is connected to the upper end of the end cap (22) by means of a connection piece.
9. Spacecraft magnetic buoyancy according to claim 4, characterized in that the vertical beam assembly is connected to the coil (18) by means of a connection.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210143234.6A CN114551024B (en) | 2022-02-16 | 2022-02-16 | Stop gear and spacecraft magnetic buoyancy ware |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210143234.6A CN114551024B (en) | 2022-02-16 | 2022-02-16 | Stop gear and spacecraft magnetic buoyancy ware |
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| CN114551024A CN114551024A (en) | 2022-05-27 |
| CN114551024B true CN114551024B (en) | 2023-12-12 |
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| WO2016057640A2 (en) * | 2014-10-07 | 2016-04-14 | Magna Powertrain Of America, Inc. | An electro-mechanical clutch apparatus |
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| CA2871227A1 (en) * | 2013-11-11 | 2015-05-11 | Andre Beaulieu | Magnetostatic voltage/current limiting system for wind turbine generator and generator comprising the same |
| CN105529130A (en) * | 2016-01-29 | 2016-04-27 | 德力西电气有限公司 | Electromagnet structure |
| CN208077717U (en) * | 2018-01-11 | 2018-11-09 | 深圳市宗泰电机有限公司 | A kind of ultrahigh speed electromagnet and component |
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