A conical pressing mechanism

Abstract

The present invention provides a conical clamping mechanism, which relates to the field of aerospace technology and is used to clamp and release solar panels, antennas, etc., and includes a first mounting seat, a second mounting seat, a locking assembly, and an unlocking assembly: the first mounting seat and the second mounting seat are respectively provided with a first through hole and a second through hole; one end of the locking assembly is adapted to be inserted into the first through hole through the second through hole to limit the movement of the first mounting seat relative to the second mounting seat; the unlocking assembly includes a plug-in, a clamping structure, and a breaking device, the plug-in is adapted to be passed through the locking assembly, the clamping structure and the breaking device are respectively connected to the plug-in, and the clamping structure and the breaking device are respectively in contact with the first mounting seat and the other end of the locking assembly, and the breaking device is adapted to be energized to disconnect the plug-in. The conical clamping mechanism of the present invention reduces the occupation of the envelope space of the solar panel when the solar panel is clamped.

Description

Technical Field

[0001] The present invention relates to the field of aerospace technology, and in particular to a conical pressing mechanism. Background Art

[0002] The solar panels, antennas, and other components mounted on the main body of a spacecraft must be pre-folded and held in place by a clamping mechanism. They are then unlocked and deployed in orbit after launch. Due to the limited space within the spacecraft, the envelope occupied by the folded solar panels is also limited.

[0003] Existing clamping mechanisms typically use a rod-type clamping mechanism. For example, in the case of a solar wing, a long rod is vertically inserted through the folded solar wing. The unlocking component (e.g., an explosive bolt) of the rod-type clamping mechanism is typically located along the central axis of the rod between the solar wing and the main body of the spacecraft, further occupying the solar wing's envelope. Summary of the Invention

[0004] The problem solved by the present invention is how to save the envelope space of the solar wing on the spacecraft.

[0005] To solve the above problems, the present invention provides a conical pressing mechanism, comprising a first mounting seat, a second mounting seat, a locking assembly, and an unlocking assembly:

[0006] The first mounting seat and the second mounting seat are respectively provided with a first through hole and a second through hole;

[0007] One end of the locking assembly is adapted to be inserted into the first through hole through the second through hole to limit the movement of the first mounting seat relative to the second mounting seat;

[0008] The unlocking component includes a plug-in, a clamping structure and a breaking device. The plug-in is suitable for being inserted into the locking component. The clamping structure and the breaking device are respectively connected to the plug-in, and the clamping structure and the breaking device are respectively abutted against the first mounting seat and the other end of the locking component. The breaking device is suitable for being energized to disconnect the plug-in.

[0009] Optionally, the plug-in is a slotted bolt, the clamping structure is a nut, the nut is threadedly connected to the slotted bolt, the slotted bolt is provided with an annular groove, and the breaking device is suitable for being energized to cause the slotted bolt to break at the annular groove.

[0010] Optionally, the locking assembly includes a shear cone;

[0011] When the solar wing is compressed, the wall surface of the first through hole and the wall surface of the second through hole are suitable for splicing to form a tapered hole, and the shear cone is suitable for being inserted into the tapered hole to limit the movement of the first mounting seat relative to the second mounting seat.

[0012] Optionally, the locking assembly further includes an elastic member, one end of which is connected to the second mounting seat, and the other end of which is connected to the shear cone; the elastic member is suitable for driving the shear cone to pop out of the first through hole and the second through hole.

[0013] Optionally, the conical pressing mechanism further includes a first sleeve and a second sleeve, the first sleeve being mounted on the first mounting seat and covering the pressing structure, and the second sleeve being mounted on the second mounting seat and covering the expansion device and the locking assembly.

[0014] Optionally, a first buffer pad and a second buffer pad are respectively installed on the end surfaces of the first sleeve and the second sleeve facing the slotted bolt.

[0015] Optionally, the locking assembly further comprises a ball pad, one end of which is connected to the anti-shear cone spherical pair, and the other end of which abuts against the expansion device.

[0016] Optionally, a first thermal insulation pad is provided between the expansion-breaking device and the locking assembly.

[0017] Optionally, a second thermal insulation pad is provided between the nut and the second mounting seat.

[0018] Optionally, two or more expansion and breaking devices are provided, and the first thermal insulation pad is provided between adjacent expansion and breaking devices.

[0019] The conical clamping mechanism of the present invention is inserted into the first through hole through one end of the locking assembly through the second through hole when the solar wing is compressed, so as to limit the relative movement between the first mounting seat and the second mounting seat. When, for example, the solar wing and the spacecraft body are respectively connected to the first mounting seat and the second mounting seat, the conical clamping mechanism realizes the compression of the solar wing relative to the spacecraft body, that is, limits the movement of the solar wing relative to the spacecraft body, so that the spacecraft folds the solar wing in the envelope space when launching. Compared with the rod-type clamping mechanism (such as the rod-type clamping mechanism in which the explosive bolt is arranged perpendicular to the solar wing), the conical clamping mechanism can be arranged in a direction parallel to the solar wing (such as the insertion of the unlocking assembly). The central axis of the component is arranged parallel to the solar wing), which reduces the distance between adjacent solar wings or between the solar wing and the main body of the spacecraft, thereby reducing the occupation of the envelope space of the solar wing, making it easier to expand the envelope space of the solar wing to adapt to the power requirement of the spacecraft, and is connected to the plug-in through the expansion device and the clamping structure respectively, thereby realizing the limitation of the locking assembly, thereby limiting the relative movement between the first mounting seat and the second mounting seat, avoiding the plug-in from being subjected to tangential force, and facilitating the improvement of the clamping force of the solar wing; when the solar wing is released, the expansion device is energized to disconnect the plug-in, and the locking assembly is pulled out of the first through hole and the second through hole, thereby realizing the rapid unlocking and deployment of the solar wing after the spacecraft is launched. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 A schematic cross-sectional view of a conical pressing mechanism provided in an embodiment of the present invention;

[0021] Figure 2 A three-dimensional schematic diagram of the first mounting seat and the second mounting seat when the solar wing is compressed according to an embodiment of the present invention;

[0022] Figure 3 A three-dimensional schematic diagram of a shear cone provided in an embodiment of the present invention;

[0023] Figure 4 A schematic diagram of the structure of a plug-in provided in an embodiment of the present invention;

[0024] Figure 5 A three-dimensional schematic diagram of a conical pressing mechanism provided in an embodiment of the present invention.

[0025] Description of reference numerals:

[0026] 1. First mounting seat; 11. First through hole; 12. First seat body; 2. Second mounting seat; 21. Second through hole; 22. Second seat body; 3. Locking assembly; 31. Shear cone; 311. Conical surface; 312. Third through hole; 313. Mounting slot; 32. Elastic member; 33. Ball pad; 4. Unlocking assembly; 41. Plug-in; 411. Threaded rod; 412. Bolt end; 413. Annular groove; 414. Unthreaded rod; 42. Compression structure; 43. Expansion device; 431. Expansion device; 432. Memory alloy tube; 5. First sleeve; 51. First buffer pad; 6. Second sleeve; 61. Second buffer pad; 7. First thermal insulation pad; 8. Second thermal insulation pad. DETAILED DESCRIPTION

[0027] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, specific embodiments of the present invention are described in detail below with reference to the accompanying drawings.

[0028] It should be noted that in the coordinate system XYZ provided herein, the positive direction of the X axis represents the right, the negative direction of the X axis represents the left, the positive direction of the Y axis represents the back, the negative direction of the Y axis represents the front, the positive direction of the Z axis represents the top, and the negative direction of the Z axis represents the bottom. At the same time, it should be noted that the terms "first", "second", etc. in the specification and claims of the present invention and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It should be understood that the numbers used in this way can be interchanged where appropriate, so that the embodiments of the present invention described herein can be implemented in an order other than those illustrated or described herein.

[0029] The embodiment of the present invention provides a conical pressing mechanism for pressing and releasing solar panels, antennas, etc., including a first mounting seat 1, a second mounting seat 2, a locking assembly 3, and an unlocking assembly 4:

[0030] The first mounting seat 1 and the second mounting seat 2 are respectively provided with a first through hole 11 and a second through hole 21; one end of the locking assembly 3 is suitable for being inserted into the first through hole 11 through the second through hole 21 to limit the movement of the first mounting seat 1 relative to the second mounting seat 2; the unlocking assembly 4 includes a plug-in 41, a clamping structure 42 and a breaking device 43, the plug-in 41 is suitable for being passed through the locking assembly 3, the clamping structure 42 and the breaking device 43 are respectively connected to the plug-in 41, and the clamping structure 42 and the breaking device 43 are respectively abutted against one end of the first mounting seat 1 and the locking assembly 3, and the breaking device 43 is suitable for being energized to disconnect the plug-in 41.

[0031] Specifically, combined Figure 1 and Figure 2As shown, the first mounting seat 1 and the second mounting seat 2 are respectively provided with a first seat body 12 and a second seat body 22. The first mounting seat 1 can be equipped with a solar wing through the first seat body 12, and the second mounting seat 2 can be equipped with a spacecraft body through the second seat body 22. The first seat body 12 and the second seat body 22 are both parallel to the XY plane in the figure.

[0032] Taking the solar wing as an example, when the solar wing is compressed (i.e., the solar wing rotates relative to the spacecraft body until the angle between the solar wing and the spacecraft body is approximately 0°), the first through hole 11 and the second through hole 21 are arranged along the same horizontal axis (i.e., the X-axis in the figure), and the left end of the locking assembly 3 (i.e., the end facing the opposite direction of the X-axis in the figure) is inserted into the first through hole 11 through the second through hole 21 and abuts against the inner wall surfaces of the first through hole 11 and the second through hole 21, respectively, so that the relative position of the first mounting seat 1 and the second mounting seat 2 is restricted by the locking assembly 3, and the compression structure 42 and the expansion device 43 are connected to each other through the plug-in 41, the compression structure 42 abuts against the first mounting seat 1 in the positive direction of the X-axis, and the expansion device 43 abuts against the locking assembly 3 in the opposite direction of the X-axis, so that the solar wing connected to the first mounting seat 1 can maintain a compressed state;

[0033] When the solar wing is released (that is, when the first mounting seat 1 connected to the solar wing is no longer restricted and can rotate relative to the main body of the spacecraft), the expansion device 43 is energized and expanded to disconnect the plug-in 41, and the clamping structure 42 and the expansion device 43 no longer abut against the first mounting seat 1 and the locking assembly 3 accordingly. Therefore, the locking assembly 3 can be pulled out from the first through hole 11 and the second through hole 21 in the positive direction of the X-axis in the figure, and the first mounting seat 1 and the second mounting seat 2 can move relative to each other, so that the solar wing installed on the first mounting seat 1 can rotate relative to the main body of the spacecraft.

[0034] Specifically, combined Figure 1 As shown, the expansion and breaking device 43 includes an expander 431 and a memory alloy tube 432. The memory alloy tube 432 is a tube made of a shape memory alloy material and is sleeved on the plug-in 41. One end of the memory alloy tube 432 abuts the plug-in 41, and the other end abuts the right end of the locking assembly 3 (i.e., the end facing the positive direction of the X-axis in the figure). When the solar wing is released, the expander 431 is energized to heat the memory alloy tube 432, causing it to expand and deform in the direction of the X-axis in the figure. The plug-in 41 is forced to break, and the locking assembly 3 is no longer abutted by the expansion and breaking device 43. Therefore, it can move along the X-axis in the figure, allowing the first mounting seat 1 to move relative to the second mounting seat 2.

[0035] For example, when the solar wing is pressed, the locking assembly 3 includes a cylindrical end head in the shape of a cylinder, which is inserted into the first through hole 11 through the second through hole 21, and the center axis of the cylindrical end head coincides with the second through hole 21. When the solar wing is released, the locking assembly 3 is pulled out from the first through hole 11 and the second through hole 21 by a driving device (not shown in the diagram of this scheme).

[0036] It should be noted that the conical clamping mechanism can also be used for the compression and release between two adjacent solar wings, that is, the first mounting seat 1 and the second mounting seat 2 are each equipped with a solar wing to achieve the folding, compression and unfolding release of the two adjacent solar wings. The connection method between the first mounting seat 1 and the second mounting seat 2 and the different components of the aerospace vehicle is not specifically limited here.

[0037] The conical clamping mechanism of the embodiment of the present invention is inserted into the first through hole 11 through the second through hole 21 when the solar wing is compressed by one end of the locking component 3 to limit the relative movement between the first mounting seat 1 and the second mounting seat 2. When, for example, the solar wing and the spacecraft body are respectively connected to the first mounting seat 1 and the second mounting seat 2, the conical clamping mechanism realizes the compression of the solar wing relative to the spacecraft body, that is, limits the movement of the solar wing relative to the spacecraft body, so that the spacecraft folds the solar wing in the envelope space when launching. Compared with the rod-type clamping mechanism (such as the rod-type clamping mechanism in which the explosive bolt is arranged along the vertical axis Z axis), the conical clamping mechanism can be arranged along the direction parallel to the solar wing (such as the plug-in 41 of the unlocking component 4). The central axis is arranged along the horizontal axis X-axis), which reduces the distance between adjacent solar wings or between the solar wings and the main body of the spacecraft, thereby reducing the occupation of the envelope space of the solar wings, making it easier to expand the envelope space of the solar wings to adapt to the power requirements of the spacecraft, and through the expansion device 43 and the clamping structure 42 respectively connected to the plug-in 41, the locking component 3 is limited, thereby limiting the relative movement between the first mounting seat 1 and the second mounting seat 2, avoiding the plug-in 41 from being subjected to tangential force, and facilitating the improvement of the clamping force of the solar wing; when the solar wing is released, the expansion device 43 is energized to disconnect the plug-in 41, and the locking component 3 is pulled out from the first through hole 11 and the second through hole 21, thereby realizing the rapid unlocking and deployment of the solar wing after the spacecraft is launched.

[0038] Optionally, the plug-in 41 is a slotted bolt, the clamping structure 42 is a nut, the nut is threadedly connected to the slotted bolt, the slotted bolt is provided with an annular groove 413, and the breaking device 43 is suitable for being energized to cause the slotted bolt to break at the annular groove 413.

[0039] Specifically, combined Figure 1 and Figure 4As shown, the slotted bolt as an insert 41 includes a threaded shank 411, an annular groove 413, a non-threaded shank 414, and a bolt end 412. When the solar wing is compressed, the slotted bolt as an insert 41 is provided with an annular groove 413 along the circumference of the slotted bolt at a position near the first through hole 11 and the second through hole 21. The slotted bolt is threadedly connected to the nut serving as the compression structure 42 via the threaded shank 411. After the nut is tightened, the nut and the bolt end 412 respectively abut the first mounting seat 1 and the expansion device 43, so that the expansion device 43 can abut the locking assembly 3.

[0040] In this way, when the solar wing is tightened, the nut is threadedly connected to the slotted bolt and abuts against the first mounting seat 1, so that the locking assembly 3 can more firmly limit the relative movement of the first mounting seat 1 and the second mounting seat 2; when the solar wing is released, the expansion device 43 is energized to disconnect the slotted bolt. The position of the annular groove 413 on the slotted bolt designed based on relevant mechanical principles can control the position of the disconnection of the plug-in 41, thereby ensuring the smooth release of the solar wing.

[0041] Optionally, the locking assembly 3 includes a shear cone 31; when the solar wing is pressed, the wall of the first through hole 11 and the wall of the second through hole 21 are spliced to form a conical hole, and the shear cone 31 is suitable for being inserted into the conical hole to limit the movement of the first mounting seat 1 relative to the second mounting seat 2.

[0042] Specifically, combined Figures 1 to 3 As shown, the wall surface of the first through hole 11 and the wall surface of the second through hole 21 are spliced together to form a tapered hole, which includes a large hole end and a small hole end. The shear cone 31 is inserted from the large hole end to the vicinity of the small hole end, wherein the shear cone 31 includes a tapered surface 311 and a third through hole 312. The plug-in 41 is passed through the third through hole 312 so as to be connected to the clamping structure 42. After the shear cone 31 is inserted into the tapered hole, the tapered surface 311 abuts against the tapered hole (that is, abuts against the respective walls of the first through hole 11 and the second through hole 21).

[0043] It should be noted that the taper of the shear cone 31 and the tapered hole can be designed according to specific needs, and their values are not specifically limited here, as long as they do not interfere with the shear cone 31 being pulled out from the first through hole 11 and the second through hole 21.

[0044] In this way, the shear cone 31 can be inserted into the conical hole formed by the first through hole 11 and the second through hole 21 to limit the movement of the first mounting seat 1 relative to the second mounting seat 2, and can also be pulled out smoothly so that the relative movement of the first mounting seat 1 and the second mounting seat 2 is no longer restricted, thereby releasing the solar wing. Compared with the locking component 3 with a cylindrical end, the setting of the shear cone 31 and the conical hole avoids the frictional self-locking of the locking component 3 with the first through hole 11 or the second through hole 21, thereby ensuring the smooth release of the solar wing.

[0045] Optionally, combined Figure 1 As shown, when the solar wing is pressed, the first mounting seat 1 and the second mounting seat 2 abut against each other to form a joint surface with a certain inclination (at Figure 1 In this way, when the solar wing is released, the first mounting seat 1 is at Figure 1 The clockwise swing in the middle allows the solar wing installed on the first mounting seat 1 to be released and unfolded (i.e. the angle between the solar wing and the main body of the spacecraft or between the solar wing and another solar wing changes from 0° to 180°). Compared with a joint surface without an inclination, interference between the first mounting seat 1 and the second mounting seat 2 is avoided, which causes the solar wing to be unable to be released normally.

[0046] Optionally, the locking assembly 3 further includes an elastic member 32, one end of the elastic member 32 is connected to the second mounting seat 2, and the other end is connected to the anti-shear cone 31; the elastic member 32 is suitable for driving the anti-shear cone 31 to pop out of the first through hole 11 and the second through hole 21.

[0047] Specifically, combined Figure 1 and Figure 3 As shown, the elastic member 32 is a spring, and the shear cone 31 is also provided with a mounting slot 313 for installing the spring. The spring is sleeved on the shear cone 31, with one end mounted in the mounting slot 313 and the other end abutting the second mounting seat 2. When the solar wing is compressed, the spring, as the elastic member 32, is compressed because the compression structure 42 and the expansion and breaking device 43 abut against the first mounting seat 1 and the locking assembly 3 respectively. When the compression structure 42 uses a nut, the pre-tightening force of the nut is adjusted; when the solar wing is released, the plug-in 41 is disconnected, and the locking assembly 3 is no longer limited by the abutment of the expansion and breaking device 43. The elastic potential energy of the spring is converted into kinetic energy to drive the shear cone 31 toward the positive direction of the X-axis in the figure, so that the shear cone 31 pops out from the first through hole 11 and the second through hole 21.

[0048] In this way, the anti-shear cone 31 is driven to pop out by the elastic member 32, which offsets the friction force that may be generated between the first through hole 11 and the second through hole 21 and the anti-shear cone 31 to a certain extent, further improving the speed at which the anti-shear cone 31 pops out, making the release speed of the solar wing faster; in addition, the anti-shear cone 31 may move along the central axis direction of the plug-in 41, and the elastic member 32 achieves a shock-absorbing effect on the anti-shear cone 31 to a certain extent, thereby ensuring the stability of the spacecraft operation.

[0049] Optionally, the conical clamping mechanism also includes a first sleeve 5 and a second sleeve 6, the first sleeve 5 is installed on the first mounting seat 1 and covers the clamping structure 42, and the second sleeve 6 is installed on the second mounting seat 2 and covers the expansion device 43 and the locking assembly 3.

[0050] Specifically, combined Figure 1 、 Figure 4 and Figure 5 As shown, the first sleeve 5 is provided with a nut serving as a pressing structure 42 , and the second sleeve 6 is provided with a breaking device 43 , a locking assembly 3 and a slotted bolt serving as an insert 41 .

[0051] For example, in combination Figure 1 As shown, the second sleeve 6 is further provided with a cable through hole for electrical connection of the expansion device 43 , and the diameter of the cable through hole is smaller than the surface size of components such as the expansion device 43 and the locking assembly 3 .

[0052] In this way, after the solar wing is released, the first sleeve 5 and the second sleeve 6 can prevent components such as the nut and the locking assembly 3 serving as the clamping structure 42 from being thrown into space and becoming space debris, thereby avoiding damage to the spacecraft.

[0053] Optionally, a first buffer pad 51 and a second buffer pad 61 are respectively installed on the end surfaces of the first sleeve 5 and the second sleeve 6 facing the slotted bolt.

[0054] Specifically, combined Figure 1 and Figure 4 As shown, the first and second buffer pads 51 and 61 are made of aluminum honeycomb panels, which have excellent shock resistance. When the slotted bolt breaks, the nut and the broken section of the slotted bolt (e.g., the threaded shank 411) and the other broken section of the slotted bolt (e.g., the bolt end 412 and the unthreaded shank 414) separate from each other, causing an impact on the first and second sleeves 5 and 6. In this way, the first and second buffer pads 51 and 61 provide a certain degree of shock absorption, ensuring the stability of the spacecraft.

[0055] Optionally, the locking assembly 3 further includes a ball pad 33 , one end of which is connected to the spherical surface pair of the shear cone 31 , and the other end of which abuts against the expansion device 43 .

[0056] When the solar wing is released, the first mounting seat 1 is Figure 1 The locking assembly 3 swings in the clockwise direction relative to the second mounting base 2 , and interferes with the swinging of the first mounting base 1 when the locking assembly 3 is not completely pulled out of the first through hole 11 and the second through hole 21 .

[0057] Specifically, combined Figure 1 As shown, the ball pad 33 includes a spherical end and a plane end. A spherical groove corresponding to the shape of the spherical end is provided on the side of the shear cone 31 facing the positive direction of the X-axis in the figure. The spherical end of the ball pad 33 is spherically connected to the spherical groove, and the plane end of the ball pad 33 is in contact with the expansion and breaking device 43.

[0058] In this way, the shear cone 31 is connected to the spherical pair of the ball pad 33 to avoid the swing interference of the first mounting seat 1 when the locking assembly 3 is not completely pulled out, so that the release and deployment of the solar wing are smoother and faster; in addition, when assembling the conical clamping mechanism, the shear cone 31 can achieve a certain degree of swing through the ball pad 33, thereby allowing a certain assembly error and reducing the accuracy requirements for other components.

[0059] Optionally, a first thermal insulation pad 7 is provided between the expansion and breaking device 43 and the locking assembly 3 .

[0060] Specifically, the first thermal insulation pad 7 is sleeved on the plug-in 41 , and the first thermal insulation pad 7 is located between the ball pad 33 and the expansion and breaking device 43 and abuts against the ball pad 33 and the expansion and breaking device 43 respectively.

[0061] In this way, by arranging the first thermal insulation pad 7 between the locking assembly 3 and the expansion device 43, the heat generated during the power-on process of the expansion device 43 is avoided from being lost, resulting in the plug-in 41 being unable to disconnect in time to release the solar wing.

[0062] Optionally, a second thermal insulation pad 8 is provided between the nut and the second mounting seat 2 .

[0063] Specifically, the second thermal insulation pad 8 can be made of a titanium alloy gasket, which has good thermal insulation capabilities.

[0064] In this way, by setting the second thermal insulation pad 8 between the nut and the second mounting seat 2, heat loss during the power-on process of the expansion device 43 is further avoided, which causes the plug-in 41 to be unable to disconnect in time to achieve the release of the solar wing.

[0065] Optionally, two or more expansion and breaking devices 43 are provided, and the first thermal insulation pads 7 are provided between adjacent expansion and breaking devices 43 .

[0066] Specifically, combined Figure 1 and Figure 5 As shown, there are two expansion and breaking devices 43 , and a first thermal insulation pad 7 is provided between the two expansion and breaking devices 43 .

[0067] In this way, a backup function is achieved by setting up two or more expansion and breaking devices 43, that is, when one of the multiple expansion and breaking devices 43 fails and is damaged, the other expansion and breaking devices 43 can continue to be used normally, ensuring the normal unlocking of the spacecraft; at the same time, by setting a first thermal insulation pad 7 between adjacent expansion and breaking devices 43, the heat loss generated by the power supply when using one of the expansion and breaking devices 43 is avoided, which causes the plug-in 41 to be unable to disconnect in time to release the solar wing.

[0068] Finally, it should be noted that although the above description uses the example of the application of the conical clamping mechanism to the solar wing, the conical clamping mechanism provided in this embodiment can not only be used for the folding, clamping and unlocking of the solar wing, but also for the folding, clamping and unlocking of structures with folding functions such as antennas. The application of the conical clamping mechanism in structures with folding functions such as antennas is within the scope of protection of this disclosure.

[0069] Although the present disclosure is disclosed as above, the protection scope of the present disclosure is not limited thereto. Those skilled in the art may make various changes and modifications without departing from the spirit and scope of the present disclosure, and these changes and modifications will fall within the protection scope of the present invention.

Claims

1. A conical pressing mechanism, characterized in that: It comprises a first mounting seat (1), a second mounting seat (2), a locking component (3) and an unlocking component (4): The first mounting seat (1) and the second mounting seat (2) are respectively provided with a first through hole (11) and a second through hole (21); One end of the locking assembly (3) is adapted to be inserted into the first through hole (11) through the second through hole (21) to limit movement of the first mounting seat (1) relative to the second mounting seat (2); The unlocking assembly (4) comprises a plug-in (41), a pressing structure (42) and a breaking device (43), wherein the plug-in (41) is adapted to be inserted into the locking assembly (3), the pressing structure (42) and the breaking device (43) are respectively connected to the plug-in (41), and the pressing structure (42) and the breaking device (43) are respectively in contact with the first mounting seat (1) and the other end of the locking assembly (3), and the breaking device (43) is adapted to be energized to break the plug-in (41); the plug-in (41) is a slotted bolt, the pressing structure (42) is a nut, the nut is threadedly connected to the slotted bolt, the slotted bolt is provided with an annular groove (413), and the breaking device ( 43) is suitable for energizing so that the slotted bolt is disconnected at the annular groove (413); the locking assembly (3) includes a shear cone (31); the wall surface of the first through hole (11) and the wall surface of the second through hole (21) are suitable for splicing to form a tapered hole, and the shear cone (31) is suitable for being inserted into the tapered hole to limit the movement of the first mounting seat (1) relative to the second mounting seat (2); the locking assembly (3) also includes an elastic member (32), one end of the elastic member (32) is connected to the second mounting seat (2), and the other end is connected to the shear cone (31); the elastic member (32) is suitable for driving the shear cone (31) to pop out of the first through hole (11) and the second through hole (21).

2. The conical pressing mechanism according to claim 1, characterized in that: The conical pressing mechanism further comprises a first sleeve (5) and a second sleeve (6), wherein the first sleeve (5) is mounted on the first mounting seat (1) and covers the pressing structure (42), and the second sleeve (6) is mounted on the second mounting seat (2) and covers the expansion device (43) and the locking assembly (3).

3. The conical pressing mechanism according to claim 2, characterized in that: A first buffer pad (51) and a second buffer pad (61) are respectively mounted on the end surfaces of the first sleeve (5) and the second sleeve (6) facing the slotted bolt.

4. The conical pressing mechanism according to claim 1, characterized in that: The locking assembly (3) further comprises a ball pad (33), one end of which is connected to the spherical pair of the anti-shear cone (31), and the other end of which abuts against the expansion device (43).

5. The conical pressing mechanism according to claim 1, characterized in that: A first thermal insulation pad (7) is provided between the expansion and breaking device (43) and the locking assembly (3).

6. The conical pressing mechanism according to claim 1, characterized in that: A second heat insulation pad (8) is provided between the nut and the second mounting seat (2).

7. The conical pressing mechanism according to claim 5, characterized in that: Two or more expansion and breaking devices (43) are provided, and the first thermal insulation pads (7) are provided between adjacent expansion and breaking devices (43).

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