CN113753266A - Fuse type pressing and releasing device - Google Patents
Fuse type pressing and releasing device Download PDFInfo
- Publication number
- CN113753266A CN113753266A CN202111113954.XA CN202111113954A CN113753266A CN 113753266 A CN113753266 A CN 113753266A CN 202111113954 A CN202111113954 A CN 202111113954A CN 113753266 A CN113753266 A CN 113753266A
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- Prior art keywords
- rope
- sailboard
- rope joint
- fuse wire
- joint
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- 238000003825 pressing Methods 0.000 title claims abstract description 19
- 238000002844 melting Methods 0.000 claims abstract description 11
- 230000008018 melting Effects 0.000 claims abstract description 11
- 239000002994 raw material Substances 0.000 claims description 8
- 238000007789 sealing Methods 0.000 claims description 7
- 239000004698 Polyethylene Substances 0.000 claims description 4
- 239000000835 fiber Substances 0.000 claims description 4
- -1 polyethylene Polymers 0.000 claims description 4
- 229920000573 polyethylene Polymers 0.000 claims description 4
- 229910001120 nichrome Inorganic materials 0.000 claims description 2
- 108091092878 Microsatellite Proteins 0.000 abstract description 29
- 238000009434 installation Methods 0.000 abstract description 11
- 238000005056 compaction Methods 0.000 abstract description 5
- 239000000155 melt Substances 0.000 description 4
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 230000007797 corrosion Effects 0.000 description 2
- 238000005260 corrosion Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 229910000623 nickel–chromium alloy Inorganic materials 0.000 description 2
- 230000004224 protection Effects 0.000 description 2
- 230000006750 UV protection Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 230000005389 magnetism Effects 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
Images
Classifications
-
- 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
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
- B64G1/443—Photovoltaic cell arrays
-
- 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
- B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Photovoltaic Devices (AREA)
Abstract
The application relates to a fusible link type compaction release device, which comprises a compaction device and an unlocking device; the pressing device comprises a sailboard rope joint, a star body rope joint and a melting rope; the fusible line rope is respectively connected with the sailboard rope joint and the star body rope joint, and the fusible line rope mutually tensions the solar sailboard and the satellite body through the sailboard rope joint and the star body rope joint so as to keep the closing state of the solar sailboard; the unlocking device comprises a melting wire, a sliding seat, a mounting support and a spring; the installation support is connected with the satellite body, the sliding seat includes sliding section and spacing section, sliding section and installation support sliding fit, spacing section ability butt installation support, the fuse wire is connected with the terminal surface of spacing section, the fuse wire passes through between fuse wire and the spacing section, the spring is around establishing the sliding section and being used for making the fuse wire support tight fuse wire, this application does not just realize being connected of solar array pressure release and solar array using the structure, alleviates microsatellite dead weight, reduces microsatellite envelope volume.
Description
Technical Field
The application relates to the technical field of a microsatellite solar sailboard mechanism, in particular to a fuse type pressing and releasing device.
Background
In recent years, with the rise of commercial aerospace, the development of technologies such as micro devices and components, integrated multifunctional structures, space plug and play, integrated electronics and the like are widely applied to micro satellites, new opportunities and challenges are brought to the design of the micro satellites, and the micro satellites are developing towards high integration and high functions. The solar sailboard is used as an important component of a power supply system and plays a crucial role in the whole service life cycle of the satellite, and due to the small size of the microsatellite, the energy provided by the body-mounted battery piece is difficult to meet the energy requirement of the high-function and high-density microsatellite, so the expandable solar sailboard is a necessary part for solving the problem of energy shortage of the high-function microsatellite.
The compression release and the expansion locking of the microsatellite solar sailboard are key technologies for the satellite in-orbit flight. The stable compression state of the solar sailboard can ensure that the solar cell has a good mechanical environment in the satellite launching stage so as not to be damaged by the harsh environment of the launching section; the successful unlocking and unfolding locking of the solar sailboard can ensure the effective supply of energy in the in-orbit flight state of the satellite.
With respect to the related art among the above, the inventors consider that the following drawbacks exist: the related microsatellite solar sailboard pressing and releasing device needs to be connected with the solar sailboard by adopting a special structural member, so that the self weight of the microsatellite is increased, the installation area is overlarge, and the envelope volume of the microsatellite is occupied excessively.
Disclosure of Invention
In order to realize the direct connection with the solar sailboard of the solar sailboard pressing and releasing device on the premise of not using a structural member, the dead weight of a microsatellite is reduced, the installation area is reduced, and the envelope volume of the microsatellite is reduced, the fuse type pressing and releasing device is provided.
The melting line type compaction and release device adopts the following technical scheme:
a fuse type compaction and release device comprises a compaction device and an unlocking device which are arranged between a solar sailboard and a satellite body; the pressing device comprises a sailboard rope joint, a star body rope joint and a melting rope; the two ends of the fusible rope are respectively connected with the sailboard rope joint and the star body rope joint, the sailboard rope joint is connected with the solar sailboard, the star body rope joint is connected with the satellite body, and the fusible rope mutually tensions the solar sailboard and the satellite body through the sailboard rope joint and the star body rope joint to keep the closing state of the solar sailboard; the unlocking device comprises a melting wire, a sliding seat, a mounting support and a spring; the installation support is connected with the satellite body, and the sliding seat includes interconnect's slip section and spacing section, and the slip section runs through the installation support and with installation support sliding fit, and spacing section can butt installation support, and the fuse wire deviates from the terminal surface of slip section with spacing section and is connected, and the fuse wire passes in the space between fuse wire and the spacing section, and the spring is around establishing the slip section and being used for making the fuse wire support tight fuse wire.
By adopting the technical scheme, the fuse wire rope tensions the solar sailboard through the star rope joint and the sailboard rope joint in the launching and lifting stage of the microsatellite, so that the solar sailboard is always in a closed state. When the microsatellite enters a preset orbit and starts to fly in orbit, the fuse wire is powered on to heat and fuse, then the solar sailboard is unlocked and can be automatically unfolded in space, after the fuse wire is fused, the spring gradually extends and recovers the natural state, and the sliding seat is driven to move along the mounting support, so that the fuse wire is far away from the fused fuse wire. The whole unlocking device and the whole pressing device do not need to be installed by means of structural parts, the dead weight of the microsatellite can be reduced, the installation area is reduced, and the envelope volume of the microsatellite is reduced.
Optionally, the end portions of the windsurfing board rope joint and the star body rope joint, which are away from each other, are spherical.
By adopting the technical scheme, the satellite rope joint is conveniently screwed into the satellite body to install the satellite rope joint, and the sailboard rope joint is conveniently screwed into the solar sailboard to install.
Optionally, an adjusting nut is fixedly arranged at the end of the star rope joint facing the windsurfing board rope joint.
Through adopting above-mentioned technical scheme, through twisting adjusting nut, can twist the star rope joint more conveniently to adjust the elasticity of melt-spun rope.
Optionally, the fusible rope is a fusible rope made of a high-strength polyethylene fiber raw material.
By adopting the technical scheme, the high-strength polyethylene fiber raw material is adopted to manufacture the melt wire rope, so that the melt wire rope has the advantages of high strength, low weight, high cutting resistance, difficult fluffing on the surface, strong corrosion resistance, high radiation resistance and high ultraviolet resistance.
Optionally, the pressing device further comprises a mounting seat and a pre-tightening nut, a through hole is formed in the middle of the mounting seat and is connected with the solar sailboard, the sailboard rope joint penetrates through the mounting seat, the sailboard rope joint is in threaded fit with the pre-tightening nut, and the pre-tightening nut abuts against the mounting seat tightly.
Through adopting above-mentioned technical scheme, through rotating the pretension nut, can adjust the position that sailboard rope connects for the mount pad and can adjust sailboard rope and connect the distance between the two with the star rope promptly, be convenient for realize freely adjusting the pretightning force of fuse rope.
Optionally, the fuse wire is a fuse wire manufactured from a nichrome raw material.
By adopting the technical scheme, the nickel-chromium alloy raw material is adopted to manufacture the melting wire, so that the melting wire has higher resistivity, good processing performance and weldability, long service life, higher strength which can be still kept at high temperature, no brittleness, no magnetism and better corrosion resistance after long-term use.
Optionally, the sliding seat is hollow, and positive and negative wires of the external power supply penetrate through the sliding seat through the inside of the sliding seat and are respectively connected with two ends of the fuse wire.
Through adopting above-mentioned technical scheme, establish the slide holder inside into cavity, can alleviate the weight of slide holder, be convenient for alleviate the holistic weight of microsatellite.
Optionally, the end of the sliding section, which is far away from the limiting section, is fixedly provided with a rear sealing cover, and two ends of the spring are respectively abutted to the rear sealing cover and the mounting support.
Through adopting above-mentioned technical scheme, back closing cap and erection support can carry out spacingly to the spring simultaneously, the assembly of the spring of being convenient for.
In summary, the present application includes at least one of the following beneficial technical effects:
1. the whole unlocking device and the whole pressing device do not need to be installed by a structural part, so that the dead weight of the microsatellite can be reduced, the installation area is reduced, and the envelope volume of the microsatellite is reduced;
2. by rotating the pre-tightening nut, the position of the windsurfing rope joint relative to the mounting seat can be adjusted, namely the distance between the windsurfing rope joint and the star body rope joint can be adjusted, and the pre-tightening force of the fusible rope can be freely adjusted;
3. by screwing the adjusting nut, the star rope joint can be screwed more conveniently to adjust the tightness of the melting rope.
Drawings
FIG. 1 is a schematic structural view of a solar panel in a closed state according to an embodiment of the present disclosure;
FIG. 2 is a schematic structural diagram of the relative positions of the locking device and the unlocking device when the solar panel is in a closed state;
fig. 3 is a structural schematic diagram of the relative positions of the pressing device and the unlocking device in the unfolded state of the solar sailboard.
Description of reference numerals: 1. a solar array; 2. a satellite body; 3. a pressing device; 31. a windsurfing board rope joint; 32. a star rope joint; 321. adjusting the nut; 33. melting the wire rope; 34. a mounting seat; 341. a limiting ring; 35. pre-tightening the nut; 4. an unlocking device; 41. fusing the wire; 42. a sliding seat; 421. a sliding section; 4211. sealing the cover; 422. a limiting section; 43. mounting a support; 431. an ear plate; 44. a spring; 5. and (7) lightening holes.
Detailed Description
The present application is described in further detail below with reference to figures 1-3.
The embodiment of the application discloses a fuse type compressing and releasing device, referring to fig. 1 and 2, the fuse type compressing and releasing device comprises a compressing device 3 and an unlocking device 4, the compressing device 3 is arranged between a solar array panel 1 and a satellite body 2, the unlocking device 4 is fixedly connected with the satellite body 2, the compressing device 3 is used for tensioning the solar array panel 1 to enable the solar array panel 1 to keep a closed state, and the unlocking device 4 and the compressing device 3 are linked to control the solar array panel 1 to automatically unfold.
In the launching and launching stage of the microsatellite, the pressing device 3 always keeps the solar sailboard 1 in a closed state; when the microsatellite enters the orbit and starts to fly in orbit, the unlocking device 4 starts to actuate the pressing device 3, so that the solar sailboard 1 is automatically unfolded.
Referring to fig. 2 and 3, the hold-down device 3 includes a windsurfing rope connector 31, a fusible link rope 33, a pre-tightening nut 35, a mounting seat 34 and a star rope connector 32.
Referring to fig. 2 and 3, the windsurfing rope joint 31 and the star body rope joint 32 are both cylindrical and hollow inside, two ends of the melt rope 33 respectively penetrate into the windsurfing rope joint 31 and the star body rope joint 32, and two ends of the melt rope 33 are respectively fixedly connected with the windsurfing rope joint 31 and the star body rope joint 32; in the present embodiment, the fusible link 33 is made of a high-strength polyethylene fiber raw material; the end parts of the sailboard rope joint 31 and the star body rope joint 32 which are deviated from each other are all in spherical shapes.
Referring to fig. 2 and 3, the star string connector 32 is screwed into the satellite body 2 and is screw-coupled to the satellite body 2, and an adjustment nut 321 is integrally formed at an end of the star string connector 32 facing the windsurfing board string connector 31.
Referring to fig. 2 and 3, a through hole is formed in the middle of the mounting seat 34 and is connected with a side of the solar panel 1 away from the satellite body 2, the through hole is reserved in the solar panel 1 opposite to the through hole of the mounting seat 34, screws penetrate through four corners of the mounting seat 34, and the mounting seat 34 and the solar panel 1 are fixedly connected through the screws; the mounting seat 34 is integrally formed with a limiting ring 341 at the edge of its own through hole, and the mounting seat 34 is located between the limiting ring 341 and the solar array 1. The windsurfing board rope joint 31 penetrates through the mounting seat 34, the windsurfing board rope joint 31 is in threaded fit with the pre-tightening nut 35, and the pre-tightening nut 35 abuts against the limiting ring 341 of the mounting seat 34.
The star string connector 32 can be conveniently twisted by twisting the adjusting nut 321 to adjust the tightness of the fusible link 33. By rotating the pre-tightening nut 35, the position of the windsurfing board rope joint 31 relative to the mounting seat 34 can be adjusted, namely, the distance between the windsurfing board rope joint 31 and the star body rope joint 32 can be adjusted, and the pre-tightening force of the melting rope 33 can be freely adjusted conveniently. In the launching and lifting stage of the microsatellite, the fusible rope 33 tensions the solar sailboard 1 through the star rope connector 32 and the sailboard rope connector 31, so that the solar sailboard 1 is always in a closed state.
Referring to fig. 2 and 3, the unlocking device 4 includes a mounting bracket 43, a sliding seat 42, a fuse wire 41, and a spring 44.
Referring to fig. 2 and 3, the mounting bracket 43 is hollow and integrally formed with two ear plates 431 facing away from each other, and a screw is simultaneously passed through the ear plates 431 and the satellite body 2 to fixedly connect the mounting bracket 43 with the satellite body 2.
Referring to fig. 2 and 3, the sliding seat 42 includes an integrally formed sliding section 421 and a limiting section 422, the sliding section 421 penetrates through the mounting support 43 and is in sliding fit with the mounting support 43, the limiting section 422 can abut against the mounting support 43, a rear sealing cover 4211 is integrally formed at an end of the sliding section 421 away from the limiting section 422, and the sliding seat 42 is hollow and is provided with a through hole in the rear sealing cover 4211, wherein the through hole is communicated with the inside of the sliding seat 42.
Referring to fig. 2 and 3, the fuse wire 41 is fixedly connected with the end surface of the limiting section 422 away from the sliding section 421, the fuse wire 41 is in a curved arc shape, and in this embodiment, the fuse wire 41 is made of a nickel-chromium alloy raw material; the fuse cord 33 passes through the space between the fuse wire 41 and the spacing segment 422.
Referring to fig. 2 and 3, the sliding section 421 is wound around the spring 44, two ends of the spring 44 respectively abut against the rear cover 4211 and the mounting support 43, when the fuse wire 41 is located between the star rope connector 32 and the windsurfing rope connector 31, the spring 44 is compressed and shortened, the fuse wire 41 tightly abuts against the fuse wire 33, and the contact area between the fuse wire 41 and the fuse wire 33 is large; when the spring 44 returns to the natural state, the fusible link 41 is further away from the star rope connector 32 or the windsurfing board rope connector 31.
During the launching and launching phase of the microsatellite, the fusible link 41 is always tightly pressed against the fusible link 33. When the microsatellite enters a preset orbit and starts to fly in orbit, the fuse wire 41 is powered on to heat and fuse the fuse wire 33, then the solar panel 1 is unlocked and can be automatically unfolded in space, after the fuse wire 33 is fused, the spring 44 gradually extends and recovers to a natural state, and drives the sliding seat 42 to move along the mounting support 43, so that the fuse wire 41 is far away from the fused fuse wire 33.
The fuse type pressing and releasing device of the embodiment of the application has the implementation principle that: in the launching and lifting stage of the microsatellite, the fusible rope 33 tensions the solar sailboard 1 through the star rope connector 32 and the sailboard rope connector 31, so that the solar sailboard 1 is always in a closed state. The spring 44 applies a tensile force to the fuse wire 41 via the slide holder 42, and the fuse wire 41 is pressed against the fuse wire 33, thereby ensuring effective fuse wire 33 in the future.
When the microsatellite enters a preset orbit and starts to fly in orbit, the fuse wire 41 is powered on to heat and fuse the fuse wire 33, then the solar panel 1 is unlocked and can be automatically unfolded in space, after the fuse wire 33 is fused, the spring 44 gradually extends and recovers to a natural state, and drives the sliding seat 42 to move along the mounting support 43, so that the fuse wire 41 is far away from the fused fuse wire 33.
The embodiments of the present invention are preferred embodiments of the present application, and the scope of protection of the present application is not limited by the embodiments, so: all equivalent changes made according to the structure, shape and principle of the present application shall be covered by the protection scope of the present application.
Claims (8)
1. The utility model provides a fuse formula compresses tightly release which characterized in that: comprises a pressing device (3) and an unlocking device (4) which are arranged between a solar sailboard (1) and a satellite body (2); the pressing device (3) comprises a sailboard rope joint (31), a star body rope joint (32) and a fusible link rope (33); two ends of a fusible link (33) are respectively connected with a sailboard rope joint (31) and a star body rope joint (32), the sailboard rope joint (31) is connected with the solar sailboard (1), the star body rope joint (32) is connected with the satellite body (2), and the fusible link (33) mutually tensions the solar sailboard (1) and the satellite body (2) through the sailboard rope joint (31) and the star body rope joint (32) to keep the closing state of the solar sailboard (1); the unlocking device (4) comprises a melting wire (41), a sliding seat (42), a mounting support (43) and a spring (44); installing support (43) are connected with the satellite body (2), sliding seat (42) are including the sliding section (421) and spacing section (422) of interconnect, sliding section (421) run through installing support (43) and with installing support (43) sliding fit, spacing section (422) can butt installing support (43), fuse wire (41) and spacing section (422) deviate from the terminal surface of sliding section (421) and are connected, fuse rope (33) pass in the space between fuse wire (41) and spacing section (422), spring (44) are around establishing sliding section (421) and are used for making fuse wire (41) support tight fuse rope (33).
2. The fusible link pressure relief device of claim 1, wherein: the end parts of the sailboard rope joint (31) and the star body rope joint (32) which are deviated from each other are all in spherical shapes.
3. The fusible link pressure relief device of claim 1, wherein: an adjusting nut (321) is fixedly arranged at the end part of the star body rope joint (32) facing the sailboard rope joint (31).
4. The fusible link pressure relief device of claim 1, wherein: the fusible rope (33) is a fusible rope (33) made of high-strength polyethylene fiber raw materials.
5. The fusible link pressure relief device of claim 2, wherein: the pressing device (3) further comprises a mounting seat (34) and a pre-tightening nut (35), a through hole is formed in the middle of the mounting seat (34) and is connected with the solar sailboard (1), the sailboard rope joint (31) penetrates through the mounting seat (34), the sailboard rope joint (31) is in threaded fit with the pre-tightening nut (35), and the pre-tightening nut (35) abuts against the mounting seat (34).
6. The fusible link pressure relief device of claim 1, wherein: the fuse wire (41) is a fuse wire (41) manufactured by using a nichrome raw material.
7. The fusible link pressure relief device of claim 1, wherein: the sliding seat (42) is arranged in a hollow mode, and positive and negative leads of an external power supply penetrate through the sliding seat (42) through the inside of the sliding seat (42) and are connected with two ends of the fuse wire (41) respectively.
8. The fusible link pressure relief device of claim 7, wherein: the end part, far away from the limiting section (422), of the sliding section (421) is fixedly provided with a rear sealing cover (4211), and two ends of the spring (44) are respectively abutted to the rear sealing cover (4211) and the mounting support (43).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111113954.XA CN113753266A (en) | 2021-09-23 | 2021-09-23 | Fuse type pressing and releasing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111113954.XA CN113753266A (en) | 2021-09-23 | 2021-09-23 | Fuse type pressing and releasing device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113753266A true CN113753266A (en) | 2021-12-07 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111113954.XA Pending CN113753266A (en) | 2021-09-23 | 2021-09-23 | Fuse type pressing and releasing device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113753266A (en) |
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2021
- 2021-09-23 CN CN202111113954.XA patent/CN113753266A/en active Pending
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Application publication date: 20211207 |