CN115848646B - Supporting mechanism of space camera - Google Patents
Supporting mechanism of space camera Download PDFInfo
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- CN115848646B CN115848646B CN202211627041.4A CN202211627041A CN115848646B CN 115848646 B CN115848646 B CN 115848646B CN 202211627041 A CN202211627041 A CN 202211627041A CN 115848646 B CN115848646 B CN 115848646B
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- 230000000149 penetrating effect Effects 0.000 claims description 6
- 238000010586 diagram Methods 0.000 description 5
- 238000009434 installation Methods 0.000 description 5
- 230000000903 blocking effect Effects 0.000 description 3
- 239000004698 Polyethylene Substances 0.000 description 2
- 239000002360 explosive Substances 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- -1 polyethylene Polymers 0.000 description 2
- 229920000573 polyethylene Polymers 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
Abstract
The invention relates to the technical field of satellites, in particular to a supporting mechanism of a space camera. The supporting mechanism of the space camera comprises a supporting rod, a rotating assembly and a hot knife assembly, and the space camera is installed at one end of the supporting rod. The support rod is movably arranged on a star of the satellite through the rotating component, and the rotating component can drive the support rod and the space camera to be unfolded to a preset position after being unlocked. The thermal knife assembly comprises a fusing module and a stay wire, the fusing module is arranged on the support rod, one end of the stay wire is connected with the star, and the other end of the stay wire can tighten the support rod, so that the support rod and the space camera are folded on the star. The fusing module can fuse the stay wire after being electrified so as to enable the stay wire to loosen the support rod and unlock the rotating assembly. The supporting mechanism of the space camera is simple in structure, the folding and locking of the space camera are realized through the stay wire, meanwhile, the unlocking of the space camera is realized through the hot knife assembly, and the stability and reliability of folding and unfolding operation of the space camera are improved.
Description
Technical Field
The invention relates to the technical field of satellites, in particular to a supporting mechanism of a space camera.
Background
The space camera can be arranged on the outer surface of the satellite star body so as to monitor the on-orbit working state of the star body and a plurality of parts on the star body and acquire clear image information. Before the satellite enters orbit, the space camera is folded and folded on the side surface of the satellite body through the support, so that the satellite can be ensured to enter orbit smoothly. After the satellite enters orbit, the bracket is automatically unfolded, so that the space camera works at a preset unfolding angle and orientation.
At present, a motor or other driving member is used for driving the support to realize folding and unfolding actions. Because of the large volume and weight of the motor, the installation on the star is inconvenient. Moreover, the motor needs to realize the reciprocating rotation of the bracket through a transmission structure such as a gear, and accidents such as gear jamming and motor faults occur, so that the reliability is low. In addition, the traditional space locking mechanism adopts explosive materials to explode the bolt to realize unlocking operation, and the larger impact force generated by the explosive bolt can greatly reduce the safety and reliability of the normal operation of the satellite.
Therefore, a supporting mechanism of a space camera is needed to solve the above-mentioned problems.
Disclosure of Invention
The invention aims to provide a support mechanism of a space camera, which is used for improving the reliability and stability of folding and unfolding operations of the space camera.
The technical scheme adopted by the invention is as follows:
a support mechanism for a spatial camera, comprising:
a support rod, one end of which is provided with a space camera;
the rotating assembly is movably arranged on a star of a satellite through the supporting rod and is configured to be unlocked and then can drive the supporting rod and the space camera to be unfolded to a preset position; and
the thermal knife assembly comprises a fusing module and a stay wire, wherein the fusing module is arranged on the support rod, one end of the stay wire is connected with the star, and the other end of the stay wire can tighten the support rod so as to enable the support rod and the space camera to be folded on the star; the fusing module is configured to fuse the pull wire after being energized to cause the pull wire to loosen the support rod and unlock the rotating assembly.
Preferably, the hot knife assembly further comprises:
the circuit board is arranged on the supporting rod, and the fusing module is connected to the circuit board in a conducting way so as to supply power to the fusing module; and
and one end of the first elastic piece is arranged on the supporting rod, and the other end of the first elastic piece is connected with the stay wire, so that the stay wire can be pulled tightly by the first elastic piece.
Preferably, the hot knife assembly further comprises:
the threading block is fixedly arranged on the circuit board and covered on the fusing module; the threading block is provided with threading grooves penetrating through two ends of the threading block in the length direction or the width direction, and the pull wire penetrates through the threading grooves and is propped against the fusing module.
As an optimal scheme, the supporting mechanism of the space camera further comprises a positioning block, the positioning block is detachably arranged on the star, and one end, far away from the first elastic piece, of the stay wire is fixedly connected to the positioning block.
As a preferable scheme, a wire column is arranged on the alignment block and provided with a through hole, and one end of the stay wire, which is far away from the first elastic piece, passes through the through hole and is fixedly connected to the wire column.
As a preferable scheme, a limit groove is formed in one side of the alignment block, and the threading block can be clamped in the limit groove when the support rod is folded in the star.
As a preferable scheme, one of two opposite side surfaces of the threading block and the alignment block is provided with a first positioning column, the other side surface is provided with a first positioning groove, and the first positioning column can be inserted into the corresponding first positioning groove.
As a preferable scheme, the threading block and the alignment block are respectively provided with a first inspection hole and a second inspection hole, and the second inspection hole, the first inspection hole and the fusing module are arranged opposite to each other in sequence.
Preferably, the support mechanism of the space camera further comprises a base, the base is fixedly arranged on the star, and the alignment block is detachably arranged on the base.
Preferably, the rotating assembly includes:
the first chain plate, the second chain plate and the rotating shaft; the first chain plate is hinged with the second chain plate through the rotating shaft; the first chain plate is fixedly arranged on the star, and the second chain plate is connected with one end, far away from the space camera, of the supporting rod; and
the torsion spring is sleeved on the rotating shaft and respectively pressed against the first chain plate and the second chain plate, and the torsion spring is configured to enable the second chain plate to rotate towards a direction away from the first chain plate after unlocking so as to drive the support rod and the space camera to be unfolded to the preset position.
The beneficial effects of the invention are as follows:
the supporting mechanism of the space camera comprises a supporting rod, a rotating assembly and a hot knife assembly, wherein one end of the supporting rod is movably arranged on a satellite body of a satellite through the rotating assembly, and the other end of the supporting rod is provided with the space camera. Before the satellite enters orbit, the support rod is tensioned by the stay wire, so that the support rod and the space camera are folded on the star. After the satellite enters orbit, the stay wire is fused by electrifying the fusing module, so that the support rod is released, the rotating assembly is unlocked, and the rotating assembly drives the support rod and the space camera to be unfolded to a preset position. The supporting mechanism of the space camera is simple in structure, the folding and locking of the space camera are realized through the stay wire, meanwhile, the unlocking of the space camera is realized through the hot knife assembly, and the stability and reliability of folding and unfolding operation of the space camera are improved.
Drawings
Fig. 1 is a schematic structural diagram of a support mechanism of a spatial camera according to an embodiment of the present invention;
FIG. 2 is a schematic view of a rotating assembly according to an embodiment of the present invention;
FIG. 3 is a schematic structural view of a second link plate provided by an embodiment of the present invention;
FIG. 4 is a schematic view of a locking lever according to an embodiment of the present invention;
FIG. 5 is a schematic view of a thermal knife assembly according to an embodiment of the present invention;
FIG. 6 is a schematic diagram of a threading block and a fuse module according to an embodiment of the present invention;
FIG. 7 is a schematic diagram of a positioning block according to an embodiment of the present invention;
FIG. 8 is a second schematic structural diagram of an alignment block according to an embodiment of the present invention;
fig. 9 is a schematic structural diagram of a base according to an embodiment of the present invention.
The parts in the figures are named and numbered as follows:
10. a space camera;
1. a support rod; 2. a rotating assembly; 21. a first link plate; 211. a chute; 22. a second link plate; 221. a guide block; 222. a locking hole; 23. a locking lever; 231. a blocking handle;
3. a hot knife assembly; 31. a fusing module; 32. a pull wire; 33. a circuit board; 34. a first elastic member; 35. a threading block; 351. a wire penetrating groove; 352. a first positioning groove; 353. a first inspection hole; 4. an alignment block; 41. a wire column; 42. a through hole; 43. a limit groove; 44. a first positioning column; 45. a second inspection hole; 46. a second positioning column; 5. a base; 51. and a second positioning groove.
Detailed Description
In order to make the technical problems solved, the technical scheme adopted and the technical effects achieved by the invention more clear, the technical scheme of the invention is further described below by a specific embodiment in combination with the attached drawings. It is to be understood that the specific embodiments described herein are merely illustrative of the invention and are not limiting thereof. It should be further noted that, for convenience of description, only some, but not all of the drawings related to the present invention are shown.
In the description of the present invention, unless explicitly stated and limited otherwise, the terms "connected," "connected," and "fixed" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communicated with the inside of two elements or the interaction relationship of the two elements. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
In the present invention, unless expressly stated or limited otherwise, a first feature "above" or "below" a second feature may include both the first and second features being in direct contact, as well as the first and second features not being in direct contact but being in contact with each other through additional features therebetween. Moreover, a first feature being "above," "over" and "on" a second feature includes the first feature being directly above and obliquely above the second feature, or simply indicating that the first feature is higher in level than the second feature. The first feature being "under", "below" and "beneath" the second feature includes the first feature being directly under and obliquely below the second feature, or simply means that the first feature is less level than the second feature.
In the description of the present embodiment, the terms "upper", "lower", "right", etc. orientation or positional relationship are based on the orientation or positional relationship shown in the drawings, and are merely for convenience of description and simplicity of operation, and do not indicate or imply that the apparatus or elements referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as limiting the invention. Furthermore, the terms "first," "second," and the like, are used merely for distinguishing between descriptions and not for distinguishing between them.
The technical scheme of the invention is further described below by the specific embodiments with reference to the accompanying drawings.
As shown in fig. 1 and 6, the present embodiment provides a support mechanism for a space camera, which specifically includes a support rod 1, a rotating assembly 2 and a thermal knife assembly 3, wherein a space camera 10 is installed at one end of the support rod 1, the support rod 1 is movably disposed on a satellite body of a satellite through the rotating assembly 2, and the rotating assembly 2 can drive the support rod 1 and the space camera 10 to be unfolded to a preset position after being unlocked. The thermal knife assembly 3 comprises a fusing module 31 and a stay wire 32, wherein the fusing module 31 is arranged on the support rod 1, one end of the stay wire 32 is connected with the star, and the other end of the stay wire can tension the support rod 1 so that the support rod 1 and the space camera 10 are folded on the star. The fuse module 31 is energized to fuse the wire 32 so that the wire 32 releases the support rod 1 and unlocks the rotating assembly 2.
In this embodiment, one end of the support bar 1 is movably mounted on a star of a satellite through the rotating assembly 2, and the other end is mounted with a space camera 10. Before the satellite enters orbit, the supporting rod 1 is tensioned by the stay wire 32, so that the supporting rod 1 and the space camera 10 are folded on the satellite. After the satellite is in orbit, the fusing module 31 is electrified to fuse the wire 32, so that the supporting rod 1 is released, the rotating assembly 2 is unlocked, and the rotating assembly 2 drives the supporting rod 1 and the space camera 10 to be unfolded to a preset position. The supporting mechanism of the space camera is simple in structure, the folding and locking of the space camera 10 are achieved through the stay wire 32, meanwhile, the unlocking of the space camera 10 is achieved through the hot knife assembly 3, and the stability and reliability of folding and unfolding operation of the space camera 10 are improved.
The support rod 1 is a carbon fiber rod, has the characteristics of high strength and light weight, and can stably support the space camera 10 and reduce the overall weight of the satellite. In order to realize reliable connection of the support rod 1 with the space camera 10 and the rotating assembly 2, embedded parts are mounted at two ends of the support rod 1, and the embedded parts can be made of aluminum alloy materials so as to facilitate processing and manufacturing. The space camera 10 and the rotating assembly 2 are respectively arranged at two ends of the supporting rod 1 through corresponding embedded parts.
As shown in fig. 1 and 2, the rotating assembly 2 includes a first link plate 21, a second link plate 22, a rotation shaft, and a torsion spring (not shown). The first link plate 21 is hinged to the second link plate 22 through a rotating shaft. The first link plate 21 is fixedly arranged on the star, and the second link plate 22 is connected with one end of the support rod 1 far away from the space camera 10. The torsion spring is sleeved on the rotating shaft and is respectively propped against the first chain plate 21 and the second chain plate 22, and the torsion spring can enable the second chain plate 22 to rotate towards a direction far away from the first chain plate 21 after unlocking so as to drive the support rod 1 and the space camera 10 to be unfolded to a preset position. The rotating assembly 2 of the embodiment is an automatic hinge assembly, and the torsion spring drives the support rod 1 and the space camera 10 to rotate through the second chain plate 22, so that the automatic unfolding action of the space camera 10 is realized. Because the driving parts such as a motor are not required to drive the supporting rod 1 to rotate, the structure and the weight of the rotating assembly 2 are simplified, accidents such as motor faults are avoided, and the reliability and the stability of the supporting mechanism of the space camera are further improved.
Further, as shown in fig. 2 and 3, the rotating assembly 2 further includes a guide block 221, a locking lever 23, and a second elastic member (not shown in the drawings), the second link plate 22 is provided with the guide block 221, and the guide block 221 is provided with a locking hole 222. The outer side surface of the first link plate 21 is provided with a boss, a sliding groove 211 penetrating through two ends of the boss in the length direction is formed in the boss, and the locking rod 23 can slide in the sliding groove 211. The second elastic member is always in a compressed state, so as to push one end of the locking lever 23 to extend out of the sliding groove 211 to be close to the opening of the second link plate 22 and to be pressed against the guide block 221. When the guide block 221 rotates with the second link plate 22 in place, the locking hole 222 is in direct communication with the slide slot 211. At this time, the second elastic member pushes one end of the locking lever 23 to extend into the locking hole 222 to lock the first link plate 21 and the second link plate 22.
In particular, the second elastic member of the embodiment is a spring, so that the installation is convenient, and the second elastic member is cheap and easy to obtain. The rotating assembly 2 further comprises an end plate which can be mounted on the boss and block the other opening of the slide slot 211 away from the second link plate 22 when the locking lever 23 is inserted through the slide slot 211. As shown in fig. 4, the locking lever 23 is a stepped lever having a stepped surface, the spring is sleeved on the locking lever 23, and both ends of the spring are respectively pressed against the end plate and the stepped surface of the locking lever 23.
It should be noted that, the outer peripheral surface of the locking lever 23 extends outwards to provide a blocking handle 231, so that the locking lever 23 is conveniently installed in the chute 211 by taking the blocking handle 231, and the installation efficiency of the locking lever 23 is improved.
As shown in fig. 5 and 6, the thermal knife assembly 3 further includes a circuit board 33 and a first elastic member 34, the circuit board 33 is disposed on the support rod 1, and the fuse module 31 is connected to the circuit board 33 in a conductive manner to supply power to the fuse module 31. One end of the first elastic member 34 is disposed on the support bar 1, and the other end is connected to the pull wire 32, so that the pull wire 32 tightens the support bar 1 through the first elastic member 34. The first elastic member 34 is a tension spring, which is always in a stretched state under the tension of the pull wire 32. Because the tension spring 32 is easy to creep and stretch in the process of tensioning the support rod 1 for a long time, the tension spring can be adaptively contracted, so that the tension spring 32 is always in a tensioning state, and the tension spring 32 is prevented from being separated from the fusing module 31.
It should be noted that, the circuit board 33 is disposed adjacent to the space camera 10, that is, the pull wire 32 is located at an end far away from the rotating assembly 2, so that the pull force of the pull wire 32 for tensioning the support rod 1 has a larger force arm, thereby reducing the difficulty of the pull wire 32 for tensioning the support rod 1.
Specifically, the stay wire 32 is a polyethylene wire, and because the polyethylene material has low heat resistance, the quick fusing of the stay wire 32 when the fusing module 31 heats can be ensured, and the reliability of the unlocking process of the rotating assembly 2 is improved. The fusing module 31 may be a resistor or a resistor wire, and the fusing module 31 of this embodiment is a resistor, and the circuit board 33 has a power supply circuit thereon, and the resistor is soldered on the circuit board 33 and is connected to the power supply circuit in a conductive manner. When the satellite supplies power to the circuit board 33, the resistor heats up. When the resistance heat reaches a certain value, the pull wire 32 can be fused, so that the pull wire 32 releases the support rod 1.
As shown in fig. 5 and 6, the thermal knife assembly 3 further includes a threading block 35, and the threading block 35 is fixedly disposed on the circuit board 33 and covers the fuse module 31. The threading block 35 is provided with threading grooves 351 penetrating through both ends in the length direction or the width direction thereof, and the pull wire 32 passes through the threading grooves 351 and is pressed against the fusing module 31. The fusing modules 31 of the present embodiment have two fusing modules to increase the contact area with the pull wire 32, and improve the fusing reliability of the pull wire 32. The threading groove 351 can realize guiding limit of the pull wire 32 so as to ensure that the pull wire 32 is reliably contacted with the fusing module 31. Of course, the pull wire 32 may be looped around the lower portion of one fuse module 31 from the upper portion of the other fuse module 31 in an S-shape, thereby further realizing reliable contact of the pull wire 32 with the fuse module 31.
As shown in fig. 1, the support mechanism of the space camera further includes an alignment block 4, the alignment block 4 is detachably disposed on the star, and one end of the pull wire 32 away from the first elastic member 34 is fixedly connected to the alignment block 4. When the pull wire 32 is installed, the alignment block 4 is separated from the star so as to quickly install the pull wire 32 on the alignment block 4. After the stay wire 32 is installed, the alignment block 4 can be fixedly installed on the star body, so that the stay wire 32 tightens the support rod 1, and the space camera 10 is folded on the star body.
Specifically, as shown in fig. 1 and 7, the alignment block 4 is provided with a wire post 41 and a through hole 42, and one end of the pull wire 32 far away from the first elastic member 34 passes through the through hole 42 and is fixedly connected to the wire post 41. One end of the pull wire 32 is fixedly connected to the tension spring, and the other end of the pull wire 32 sequentially passes through the wire penetrating groove 351 and the through hole 42 and is then bound on the wire column 41, so that the reliable installation of the pull wire 32 is realized.
As shown in fig. 1 and 8, a limit groove 43 is formed on one side of the alignment block 4, and the threading block 35 can be clamped in the limit groove 43 when the support rod 1 is folded in the star, so as to prevent the support rod 1 and the space camera 10 from shaking before the star enters the orbit, thereby enabling the support rod 1 and the space camera 10 to be folded in the star stably and reliably and improving the safety before the satellite enters the orbit.
Further, as shown in fig. 5 and 8, one of two opposite sides of the threading block 35 and the alignment block 4 is provided with a first positioning column 44, the other side is provided with a first positioning groove 352, and the first positioning column 44 can be inserted into the corresponding first positioning groove 352, so that the threading block 35 can realize secondary limiting on the alignment block 4, and stability and reliability of the support rod 1 and the space camera 10 in a furled state are further improved. Two first positioning posts 44 are provided on the alignment block 4 in this embodiment, and two first positioning grooves 352 are correspondingly provided on the threading block 35. In other embodiments, two first positioning grooves 352 are formed on the alignment block 4, and two first positioning posts 44 are correspondingly disposed on the threading block 35. Of course, the number of the first positioning posts 44 and the first positioning grooves 352 may be the same and correspond to each other, and the number of the first positioning posts 44 and the first positioning grooves 352 is not particularly limited.
As shown in fig. 5 to 8, the threading block 35 and the alignment block 4 are provided with a first inspection hole 353 and a second inspection hole 45, respectively, and the second inspection hole 45, the first inspection hole 353 and the fuse module 31 are disposed in the opposite direction in order. Specifically, when the wire 32 is installed, the routing condition of the wire 32 can be checked through the first check hole 353 and the second check hole 45 to ensure that the wire 32 is always kept in contact with the fuse module 31, improving the reliability of the support mechanism of the space camera.
As shown in fig. 9, the support mechanism of the space camera further includes a base 5, the base 5 is fixedly disposed on the star, and the alignment block 4 is detachably disposed on the base 5. The base 5 is fixedly arranged on the outer surface of the star body through bolts, and the alignment block 4 is fixedly connected with the base 5 through bolts.
When the stay wire 32 is attached, the alignment block 4 is separated from the base 5. After the pull wire 32 is installed, the alignment block 4 is located on the threading block 35, then the support rod 1 is pushed to be close to the star body in a manual mode, meanwhile, the second chain plate 22 rotates towards the first chain plate 21 until the alignment block 4 abuts against the base 5, and finally the alignment block 4 is connected with the base 5 through bolts, so that the support rod 1 and the space camera 10 are folded and folded.
Specifically, as shown in fig. 7 and 9, two second positioning posts 46 are disposed on the side surface of the alignment block 4 facing away from the limiting slot 43, and two second positioning slots 51 are correspondingly disposed on the base 5. The second positioning column 46 can be inserted into the corresponding second positioning groove 51 to play a role in guiding and limiting, so that the alignment precision and the installation efficiency of the alignment block 4 and the base 5 are improved. In other embodiments, two second positioning grooves 51 are formed in the alignment block 4, and two second positioning posts 46 are correspondingly disposed on the base 5. Of course, the number of the second positioning posts 46 and the second positioning slots 51 may be the same and one-to-one, and the number of the second positioning posts 46 and the second positioning slots 51 is not particularly limited.
The above embodiments merely illustrate the basic principle and features of the present invention, and the present invention is not limited to the above embodiments, but may be varied and altered without departing from the spirit and scope of the present invention. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (7)
1. A support mechanism for a spatial camera, comprising:
a support rod (1), wherein one end of the support rod (1) is provided with a space camera (10);
the rotating assembly (2), the supporting rod (1) is movably arranged on a satellite body of a satellite through the rotating assembly (2), and the rotating assembly (2) is configured to be capable of driving the supporting rod (1) and the space camera (10) to be unfolded to a preset position after being unlocked; and
the thermal knife assembly (3) comprises a fusing module (31) and a stay wire (32), wherein the fusing module (31) is arranged on the support rod (1), one end of the stay wire (32) is connected with the star, and the other end of the stay wire can tighten the support rod (1) so that the support rod (1) and the space camera (10) are folded on the star; the fusing module (31) is configured to fuse the stay wire (32) after being electrified, so that the stay wire (32) loosens the support rod (1) and unlocks the rotating assembly (2);
the hot knife assembly (3) further comprises:
the circuit board (33) is arranged on the supporting rod (1), and the fusing module (31) is connected to the circuit board (33) in a conducting manner so as to supply power to the fusing module (31); and
the first elastic piece (34), one end of the first elastic piece (34) is arranged on the supporting rod (1), and the other end of the first elastic piece is connected with the stay wire (32), so that the stay wire (32) can tighten the supporting rod (1) through the first elastic piece (34);
the threading block (35) is fixedly arranged on the circuit board (33) and is covered on the fusing module (31); the threading block (35) is provided with threading grooves (351) penetrating through two ends of the threading block in the length direction or the width direction, and the pull wire (32) penetrates through the threading grooves (351) and is propped against the fusing module (31);
the support mechanism of the space camera further comprises a positioning block (4), the positioning block (4) is detachably arranged on the star, and one end, far away from the first elastic piece (34), of the stay wire (32) is fixedly connected to the positioning block (4).
2. The support mechanism of a space camera according to claim 1, wherein the alignment block (4) is provided with a wire post (41) and a through hole (42), and one end of the pull wire (32) away from the first elastic member (34) passes through the through hole (42) and is fixedly connected to the wire post (41).
3. The support mechanism of a space camera according to claim 1, wherein a limit groove (43) is formed on one side of the alignment block (4), and the threading block (35) can be clamped in the limit groove (43) when the support rod (1) is folded in the star.
4. A support mechanism for a space camera according to claim 3, wherein one of two opposite sides of the threading block (35) to the alignment block (4) is provided with a first positioning column (44), the other one is provided with a first positioning groove (352), and the first positioning column (44) can be inserted into the corresponding first positioning groove (352).
5. The support mechanism of a space camera according to claim 1, wherein the threading block (35) and the alignment block (4) are respectively provided with a first inspection hole (353) and a second inspection hole (45), and the second inspection hole (45), the first inspection hole (353) and the fusing module (31) are arranged in sequence opposite to each other.
6. The support mechanism of a space camera according to claim 1, further comprising a base (5), the base (5) being fixedly disposed on the star, the alignment block (4) being detachably disposed on the base (5).
7. The support mechanism of a spatial camera according to any one of claims 1 to 6, wherein the rotating assembly (2) comprises:
a first link plate (21), a second link plate (22) and a rotating shaft; the first chain plate (21) is hinged with the second chain plate (22) through the rotating shaft; the first chain plate (21) is fixedly arranged on the star, and the second chain plate (22) is connected with one end, far away from the space camera (10), of the supporting rod (1); and
the torsion spring is sleeved on the rotating shaft and respectively pressed against the first chain plate (21) and the second chain plate (22), and the torsion spring is configured to enable the second chain plate (22) to rotate in a direction away from the first chain plate (21) after unlocking so as to drive the support rod (1) and the space camera (10) to be unfolded to the preset position.
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| CN202211627041.4A CN115848646B (en) | 2022-12-16 | 2022-12-16 | Supporting mechanism of space camera |
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| CN202211627041.4A CN115848646B (en) | 2022-12-16 | 2022-12-16 | Supporting mechanism of space camera |
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| CN115848646B true CN115848646B (en) | 2023-10-27 |
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| CN115158712A (en) * | 2022-09-08 | 2022-10-11 | 长沙天仪空间科技研究院有限公司 | Satellite separation hot knife device |
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2022
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| KR20090081139A (en) * | 2008-01-23 | 2009-07-28 | 한국기계연구원 | Artificial Satellite of Hinge-equipment |
| US9546008B1 (en) * | 2014-06-17 | 2017-01-17 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Miniature release mechanism or diminutive assembly for nanosatellite deployables (DANY) |
| CN111453003A (en) * | 2020-05-18 | 2020-07-28 | 苏州馥昶空间技术有限公司 | Compressing and releasing mechanism |
| CN112340068A (en) * | 2020-11-06 | 2021-02-09 | 长光卫星技术有限公司 | Solar sailboard unfolding system based on hot knife |
| CN214139005U (en) * | 2021-01-20 | 2021-09-07 | 北京微纳星空科技有限公司 | Compressing and releasing device and spacecraft |
| CN214608148U (en) * | 2021-03-29 | 2021-11-05 | 上海埃依斯航天科技有限公司 | Satellite solar wing connecting and unlocking device |
| CN113071719A (en) * | 2021-04-30 | 2021-07-06 | 北京吾天科技有限公司 | Double-hot-cutter type compression and release mechanism |
| CN115158712A (en) * | 2022-09-08 | 2022-10-11 | 长沙天仪空间科技研究院有限公司 | Satellite separation hot knife device |
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| CN115848646A (en) | 2023-03-28 |
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