CN217736153U - Vibration isolation unlocking device for sky patrol module - Google Patents
Vibration isolation unlocking device for sky patrol module Download PDFInfo
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- CN217736153U CN217736153U CN202221874308.5U CN202221874308U CN217736153U CN 217736153 U CN217736153 U CN 217736153U CN 202221874308 U CN202221874308 U CN 202221874308U CN 217736153 U CN217736153 U CN 217736153U
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Abstract
The utility model relates to a space load is in the protection of rocket launch stage and the damping technical field in the stage of the orbit, in particular to a vibration isolation unlocking device for patrolling sky module. The device comprises a locking and unlocking device, a vibration isolation device, an upper mounting plate and a lower mounting plate, wherein the locking and unlocking device and the vibration isolation device are both arranged between the upper mounting plate and the lower mounting plate, and in the launching stage of the sky patrol module, the locking and unlocking device and the vibration isolation device ensure the rigidity of the whole structure without severe vibration; in the rail entering stage, the locking and unlocking device is disconnected from the upper mounting plate, and vibration transmission between the upper mounting plate and the lower mounting plate is reduced through the vibration isolation device. The utility model discloses not only can guarantee to patrol the rigidity of sky module in the transmission process and not violent vibration, can also guarantee to have good vibration isolation energy-absorbing in the rail stage, reduce the influence of vibration transmission to optical load cabin in patrolling the sky module.
Description
Technical Field
The utility model relates to a space load is in the protection of rocket launch stage and the damping technical field in the stage of the orbit, in particular to a vibration isolation unlocking device for patrolling sky module.
Background
During the on-orbit operation of the spacecraft, the disturbance generated by the normal operation of certain equipment carried on the spacecraft can cause the body of the spacecraft to vibrate. The main characteristics of these vibrations are small amplitude, wide frequency distribution range, and various vibration forms, which are called micro-vibrations. The disturbance source generating the micro-vibration mainly comprises: spacecraft attitude control and adjustment mechanisms, solar sailboard unfolding driving mechanisms, cooling mechanisms (refrigerators), thrusters and the like. When the large flexible solar sailboard enters and exits the ground shadow, the temperature gradient generated by cold and hot alternation will also induce micro-vibration.
The micro-vibration can cause that sensitive equipment installed on the spacecraft cannot work normally or the working performance is reduced, and in such a situation, necessary vibration isolation and vibration reduction measures need to be taken so as to reduce adverse effects caused by the micro-vibration. The existing micro-vibration isolation devices mainly comprise: the rubber vibration isolator, the metal spring parallel electromagnetic damper, the corrugated pipe fluid damper and the like. The type selection parameters mainly comprise: static performance (static rigidity, compression displacement), dynamic performance (dynamic rigidity, damping coefficient), installation and arrangement position and angle. If the cable is used on the orbit for a long time, the working environment using requirements and the fatigue performance of the cable are also considered.
According to the vibration reduction theory, in order to ensure that the system has good vibration isolation performance, the system is generally structured according to the frequency characteristic of the external excitation force to determine reasonable natural frequency and damping, small natural frequency usually corresponds to better vibration isolation performance, but too small natural frequency means that the system has small rigidity and poor bearing capacity, and the whole system can generate severe vibration during the emission stage to possibly cause equipment damage.
SUMMERY OF THE UTILITY MODEL
In view of the above problem, an object of the utility model is to provide a vibration isolation unlocking device for patrolling day module to satisfy and have enough rigidity and damping performance in module launching process and follow-up stage of going into the orbit patrolling, can guarantee to patrol the day module and do not take place violent vibration and reduce the vibration of vibration sources such as stage of going into the orbit refrigerator in the rocket launching stage and transmit to optics load cabin.
In order to realize the purpose, the utility model adopts the following technical scheme:
the utility model provides a vibration isolation unlocking device for a sky patrol module, which comprises a locking unlocking device, a vibration isolation device, an upper mounting plate and a lower mounting plate, wherein the locking unlocking device and the vibration isolation device are both arranged between the upper mounting plate and the lower mounting plate; in the stage of track entering, the locking and unlocking device is disconnected with the upper mounting plate, and vibration transmission between the upper mounting plate and the lower mounting plate is reduced through the vibration isolation device.
The locking and unlocking device comprises a pressing bushing, a memory alloy unlocking module, a supporting seat, a pressing rod and an ejection spring, wherein the bottom of the supporting seat is fixedly connected with the lower mounting plate, and the pressing bushing and the memory alloy unlocking module are vertically arranged at the top of the supporting seat and are fixedly connected with the supporting seat; the lower end of the compression rod sequentially penetrates through the upper mounting plate and the compression bush and is inserted into the memory alloy unlocking module, and the compression rod is held tightly by the memory alloy unlocking module; the spring is sleeved on the compression rod, and two ends of the spring are respectively abutted with the limiting table at the upper end part of the compression rod and the upper mounting plate; when the power-on state is achieved, the memory alloy unlocking module releases the pressing rod, and the pressing rod is ejected out of the memory alloy unlocking module under the elastic force action of the ejection spring.
And a limiting sleeve is arranged above the upper mounting plate, and the upper end of the compressing rod is accommodated in the limiting sleeve.
The supporting seat is of a square frame structure, and the top of the supporting seat is provided with a mounting hole; the memory alloy unlocking module is accommodated in the support seat and is connected with the top of the support seat through a bolt; the pressing bushing is installed in the top installation hole of the supporting seat.
The outer circumference of the pressing bush is circumferentially provided with a plurality of connecting platforms, and the connecting platforms are in positioning contact with the upper surface of the top of the supporting seat and are connected through bolts.
The vibration isolation device comprises an upper fixing component, a lower fixing component and a vibration isolation ring, wherein the axis of the vibration isolation ring is parallel to the upper mounting plate and the lower mounting plate, the top of the vibration isolation ring is fixedly connected with the upper mounting plate through the upper fixing component, and the bottom of the vibration isolation ring is fixedly connected with the lower mounting plate through the lower fixing component.
The vibration isolation ring comprises an inner steel ring and an outer steel ring which are arranged concentrically inside and outside, and silicon rubber is arranged between the inner steel ring and the outer steel ring.
The upper fixing assembly comprises an upper fixing cover and an upper inner pressing cover, wherein the upper inner pressing cover is arranged on the inner side of the vibration isolation ring, the upper fixing cover is arranged on the outer side of the vibration isolation ring, the upper fixing cover is fixedly connected with the upper inner pressing cover through a bolt, and the upper fixing cover is fixedly connected with the upper mounting plate.
The lower fixing component comprises a lower fixing cover and a lower inner pressing cover, wherein the lower inner pressing cover is arranged on the inner side of the vibration isolation ring, the lower fixing cover is arranged on the outer side of the vibration isolation ring, the lower fixing cover is fixedly connected with the lower inner pressing cover through a bolt, and the lower fixing cover is fixedly connected with the lower mounting plate.
The inner side surfaces of the upper fixing cover and the lower fixing cover are concave arc surfaces which are matched with the outer surface of the outer steel ring;
the end surfaces of the upper inner pressing cover and the lower inner pressing cover, which are in contact with the inner surface of the inner steel ring, are convex arc surfaces which are matched with the inner surface of the inner steel ring.
The utility model has the advantages and beneficial effects that:
1. the utility model provides an annular laminated damping structure, namely vibration isolation ring for short, by utilizing the geometric nonlinear characteristic of the annular structure and combining the viscoelastic damping of rubber materials, so as to inhibit the micro-vibration caused by the optical cabin refrigerator; the designed structure can effectively attenuate the micro-vibration transmitted to the optical load of the satellite structure, the vibration isolation rate reaches more than 95% under the working frequency, and the vibration isolation ring has better vibration isolation performance.
2. The utility model discloses a memory alloy unblock module, cooperation ring structure's the low dynamic stiffness characteristic of high static rigidity guarantees to patrol sky module entire system and still has sufficient rigidity and does not take place violent vibration in the rocket launching phase.
3. The utility model discloses major structure is comparatively compact, through reasonable design frock, and is fit for various installation environment that can be very convenient, and the overall arrangement is nimble.
4. The utility model discloses well vibration isolation device has comparatively extensive suitability, according to actual vibration operating mode, adjustment vibration isolation ring design parameter, material that can be very convenient are in order to satisfy the damping requirement.
Drawings
Fig. 1 is a schematic structural view of a vibration isolation unlocking device for a sky patrol module according to the present invention;
fig. 2 is a schematic structural view of the vibration isolation device of the present invention;
fig. 3 is a schematic structural view of a locking and unlocking device of the present invention;
fig. 4 is a cross-sectional view of the locking and unlocking device of the present invention;
in the figure: 1 is an unlocking device, 11 is a limiting sleeve, 12 is a compression bushing, 13 is a memory alloy unlocking module, 14 is a supporting seat, 15 is a compression rod, 16 is an ejection spring, 2 is a vibration isolation device, 211 is an upper fixing cover, 212 is a lower fixing cover, 221 is an upper inner compression cover, 222 is a lower inner compression cover, 241 is an outer steel ring, 242 is an inner steel ring, and 25 is silicon rubber.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention clearer, the present invention is described in detail with reference to the accompanying drawings and specific embodiments.
As shown in fig. 1, the utility model provides a vibration isolation unlocking device for patrolling module, including locking unlocking device 1, vibration isolation device 2, upper mounting panel 31 and lower mounting panel 32, wherein locking unlocking device 1 and vibration isolation device 2 are all installed between upper mounting panel 31 and lower mounting panel 32, and in the module transmission phase of patrolling, locking unlocking device 1 and vibration isolation device 2 guarantee the rigidity of overall structure and do not take place violent vibration; in the track-in stage, the lock/unlock device 1 is disconnected from the upper mounting plate 31, and the vibration transmission between the upper mounting plate 31 and the lower mounting plate 32 is reduced by the vibration isolation device 2.
As shown in fig. 2, in the embodiment of the present invention, the vibration isolation device 2 includes an upper fixing component, a lower fixing component, and a vibration isolation ring, wherein the vibration isolation ring is an annular laminated damping structure for reducing the transmission of the vibration source vibration of the orbiting module to the optical device in the on-track stage; during specific installation, the axis of the vibration isolation ring is parallel to the upper mounting plate 31 and the lower mounting plate 32, the top of the vibration isolation ring is fixedly connected with the upper mounting plate 31 through the upper fixing component, and the bottom of the vibration isolation ring is fixedly connected with the lower mounting plate 32 through the lower fixing component.
The embodiment of the utility model provides an in, the vibration isolation ring includes interior steel ring 242 and the outer steel ring 241 of inside and outside concentric setting, is equipped with silicon rubber 25 between interior steel ring 242 and the outer steel ring 241. The vibration isolation device 2 uses the outer steel ring 241 and the inner steel ring 242 as main bearing parts, the damping of the structure is increased by matching with the silicon rubber 25, and the silicon rubber 25 is connected with the outer steel ring 241 and the inner steel ring 242 by gluing to form a ring-shaped laminated damping structure. The annular laminated damping structure has high static and low dynamic stiffness characteristics, and vibration transmission between the upper mounting plate 31 and the lower mounting plate 32 can be effectively reduced through reasonable design.
The embodiment of the utility model provides an in, go up fixed subassembly including last fixed lid 211 and the last interior pressure lid 221, wherein go up interior pressure lid 221 and set up in the inboard of vibration isolation ring, go up fixed lid 211 and set up in the outside of vibration isolation ring, go up fixed lid 211 through bolt and last interior pressure lid 221 fixed connection, go up fixed lid 211 and last mounting panel 31 fixed connection. The lower fixing assembly includes a lower fixing cover 212 and a lower inner pressing cover 222, wherein the lower inner pressing cover 222 is disposed on the inner side of the vibration isolation ring, the lower fixing cover 212 is disposed on the outer side of the vibration isolation ring, the lower fixing cover 212 is fixedly connected with the lower inner pressing cover 222 through a bolt, and the lower fixing cover 212 is fixedly connected with the lower mounting plate 32.
Furthermore, the inner side surfaces of the upper fixing cover 211 and the lower fixing cover 212 are concave arc surfaces adapted to the outer surface of the outer steel ring 241, and the end surfaces of the upper inner compressing cover 221 and the lower inner compressing cover 222 contacting the inner surface of the inner steel ring 242 are convex arc surfaces adapted to the inner surface of the inner steel ring 242, so that the upper fixing cover 211, the upper compressing cover 221, the lower fixing cover 212 and the lower inner compressing cover 222 are fixed on the annular structure. The upper fixing cover 211 and the lower fixing cover 212 are respectively fitted with an upper inner pressing cover 221 and a lower inner pressing cover 222 to fix the vibration damping device 2 to the upper mounting plate 31 and the lower mounting plate 32.
As shown in fig. 3-4, in the embodiment of the present invention, the locking/unlocking device 1 includes a pressing bush 12, a memory alloy unlocking module 13, a supporting seat 14, a pressing rod 15 and an ejection spring 16, wherein the bottom of the supporting seat 14 is fixedly connected to a lower mounting plate 32 through a screw, and the pressing bush 12 and the memory alloy unlocking module 13 are coaxially disposed at the top of the supporting seat 14 and are both fixedly connected to the supporting seat 14; the lower end of the pressing rod 15 sequentially penetrates through the upper mounting plate 31 and the pressing bush 12 and is inserted into the memory alloy unlocking module 13, and the pressing rod 15 is held tightly by the memory alloy unlocking module 13; the spring 16 is sleeved on the pressing rod 15, and two ends of the spring are respectively abutted against the limiting table and the upper mounting plate 31 at the upper end part of the pressing rod 15; when the power is on, the memory alloy unlocking module 13 releases the pressing rod 15, and the pressing rod 15 is ejected out of the memory alloy unlocking module 13 under the elastic force action of the ejection spring 16.
Further, a limiting sleeve 11 is arranged above the upper mounting plate 31, the upper end of the pressing rod 15 is accommodated in the limiting sleeve 11, and the limiting cap 11 is used for realizing certain space constraint on the pressing rod 15.
Specifically, the supporting seat 14 is a square frame structure, and the top of the supporting seat is provided with a mounting hole; the memory alloy unlocking module 13 is accommodated in the support seat 14 and is connected with the top of the support seat 14 through a bolt; the compression bushing 12 is mounted within the top mounting hole of the support base 14.
Further, a plurality of connecting platforms are arranged on the outer circumference of the pressing bush 12 along the circumferential direction, the connecting platforms are in positioning contact with the upper surface of the top of the supporting seat 14, and the connecting platforms are connected through the top of the screw supporting seat 14.
The embodiment of the utility model provides an in, locking unlocking device 1 is locked through inserting memory alloy unblock module 13 with compressing tightly pole 15, and the cooperation compresses tightly bush 12 and fixes unlocking device 1 on last mounting panel 31. The memory alloy unlocking module 13 can lock the pressing rod 15 inserted into the memory alloy unlocking module in a power-off state, and the memory alloy unlocking module 13 deforms in a power-on state, so that the pressing rod 15 is released, further, equipment fixed on the two mounting plates in a launching stage is realized to ensure the rigidity of the whole structure without violent vibration, and fixing constraint is finished in a track entering stage.
Specifically, the compression rod 15 has a certain pre-compression amount on the ejection spring 16 in the process of inserting the compression rod 15 into the memory alloy unlocking module 13, so that the compression rod 15 can eject the memory alloy unlocking module 13 to release the fixed constraint of the unlocking device 1 and the upper mounting plate 31 when the memory alloy unlocking module 13 is in the power-on state. The limit cap 11 is mounted on the upper mounting plate 31 coaxially with the pressing rod 15, and functions as a limit when the pressing rod 15 is ejected by the eject spring 16 upon unlocking.
The utility model provides a pair of a vibration isolation unlocking device for patrolling sky module, its theory of operation is:
the vibration isolation device 2 utilizes the geometric nonlinear characteristic of an annular structure, combines the viscoelastic damping of rubber materials, takes the outer steel ring 241 and the inner steel ring 242 as main bearing parts, is matched with the silicon rubber 25 to increase the damping of the structure, adopts cementing connection between the silicon rubber 25 and the outer steel ring 241 and the inner steel ring 242 to form an annular laminated damping structure, and inhibits the micro-vibration caused by the optical chamber refrigerator; the device with the vibration isolation device is subjected to nonlinear dynamics modeling by adopting a composite structure theory and a beam theory, the vibration transfer rate of the system can be deduced, and the parametric design can be realized, so that the parameters can be conveniently changed to meet the vibration isolation requirements under different working conditions.
The unlocking device 1 takes a memory alloy unlocking module 13 as a main body, a pressing rod 15 is inserted into the memory alloy unlocking module 13 to be locked, the unlocking device 1 is fixed on an upper mounting plate 31 by matching with a pressing bush 12, and a supporting seat 14 is connected with a lower mounting plate 32 through screws, so that the upper mounting plate 31 and the lower mounting plate 32 are fixed, and the whole system is ensured to have enough rigidity without violent vibration in the rocket launching stage. In the stage of entering the track, before the equipment such as the refrigerator starts to work, the memory alloy unlocking module 13 is electrified to release the pressing rod 15, the pressing rod 15 is ejected out of the memory alloy unlocking module 13 by the ejection spring 16, so that the restraint between the unlocking device 1 and the upper mounting plate 31 is released, and the vibration isolation device 2 plays a role in vibration isolation in the whole stage of the track. The vibration isolation device 2 is an annular laminated damping structure, has the rigidity characteristics of high static and low dynamic, and can effectively reduce the vibration transmission between the two mounting plates through reasonable design.
The utility model discloses the test principle is correct, and the influence of pretightning force and radial load factor to bearing dynamic stiffness is taken into account in the synthesis, and simulation operating condition tests different bearing dynamic characteristic parameters under the different operating modes, can provide data to relevant equipment on-line regulation and control.
The utility model provides a pair of a vibration isolation unlocking device for patrolling a day module guarantees its enough rigidity and damping performance to patrolling a day module launching process and follow-up stage of coming into the orbit, including vibration isolation device and unlocking device, wherein the vibration isolation device is responsible for guaranteeing the vibration isolation performance in the module stage of coming into the orbit of patrolling a day through lamination damping structure. The unlocking device is used for fixing the patrolling module on the satellite in the launching process of the patrolling module through the cooperation of the memory alloy unlocking module and the pressing rod and the pop-up spring, and the unlocking device is released in the track entering stage to unlock and release the patrolling module so as not to hinder the vibration isolation performance of the vibration isolation device on the patrolling module. The utility model discloses not only can guarantee to patrol the rigidity of sky module in the transmission process and not violent vibration, can also guarantee to have good vibration isolation energy-absorbing in the rail stage, reduce the influence of vibration transmission to optical load cabin in patrolling the sky module.
The above description is only for the embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, improvement, extension, etc. made within the spirit and principle of the present invention are all included in the protection scope of the present invention.
Claims (10)
1. The vibration isolation unlocking device for the sky patrol module is characterized by comprising a locking unlocking device (1), a vibration isolation device (2), an upper mounting plate (31) and a lower mounting plate (32), wherein the locking unlocking device (1) and the vibration isolation device (2) are both mounted between the upper mounting plate (31) and the lower mounting plate (32), and in the launching stage of the sky patrol module, the locking unlocking device (1) and the vibration isolation device (2) ensure the rigidity of the whole structure and do not vibrate violently; in the rail entering stage, the locking and unlocking device (1) is disconnected from the upper mounting plate (31), and vibration transmission between the upper mounting plate (31) and the lower mounting plate (32) is reduced through the vibration isolation device (2).
2. The vibration isolation unlocking device for the sky patrol module as claimed in claim 1, wherein the locking unlocking device (1) comprises a pressing bushing (12), a memory alloy unlocking module (13), a supporting seat (14), a pressing rod (15) and an ejection spring (16), wherein the bottom of the supporting seat (14) is fixedly connected with the lower mounting plate (32), and the pressing bushing (12) and the memory alloy unlocking module (13) are vertically arranged on the top of the supporting seat (14) and are fixedly connected with the supporting seat (14); the lower end of the pressing rod (15) sequentially penetrates through the upper mounting plate (31) and the pressing bush (12) and is inserted into the memory alloy unlocking module (13), and the pressing rod (15) is held tightly by the memory alloy unlocking module (13); the spring (16) is sleeved on the pressing rod (15), and two ends of the spring are respectively abutted against the limiting table at the upper end part of the pressing rod (15) and the upper mounting plate (31); when the power-on state is achieved, the memory alloy unlocking module (13) releases the pressing rod (15), and the pressing rod (15) is ejected out of the memory alloy unlocking module (13) under the elastic force action of the ejecting spring (16).
3. The vibration isolation unlocking device for the sky patrol module as claimed in claim 2, wherein a limiting sleeve (11) is arranged above the upper mounting plate (31), and the upper end of the pressing rod (15) is accommodated in the limiting sleeve (11).
4. The vibration isolation unlocking device for the sky patrol module as claimed in claim 2, wherein the supporting seat (14) is of a square frame structure, and the top of the supporting seat is provided with a mounting hole; the memory alloy unlocking module (13) is accommodated in the support seat (14) and is connected with the top of the support seat (14) through a bolt; the pressing bushing (12) is installed in a top installation hole of the supporting seat (14).
5. The vibration isolation unlocking device for the sky patrol module as claimed in claim 4, wherein a plurality of connecting platforms are arranged on the outer circumference of the pressing bush (12) along the circumferential direction, and the plurality of connecting platforms are in positioning contact with the top upper surface of the supporting seat (14) and are connected through bolts.
6. The vibration isolation unlocking device for the sky patrol module according to claim 1, wherein the vibration isolation device (2) comprises an upper fixing component, a lower fixing component and a vibration isolation ring, wherein the axis of the vibration isolation ring is parallel to the upper mounting plate (31) and the lower mounting plate (32), the top of the vibration isolation ring is fixedly connected with the upper mounting plate (31) through the upper fixing component, and the bottom of the vibration isolation ring is fixedly connected with the lower mounting plate (32) through the lower fixing component.
7. The vibration isolation unlocking device for the sky module as claimed in claim 6, wherein the vibration isolation ring comprises an inner steel ring (242) and an outer steel ring (241) which are concentrically arranged inside and outside, and a silicone rubber (25) is arranged between the inner steel ring (242) and the outer steel ring (241).
8. The vibration isolation unlocking device for the sky module as claimed in claim 7, wherein the upper fixing assembly includes an upper fixing cover (211) and an upper inner pressing cover (221), wherein the upper inner pressing cover (221) is disposed at an inner side of the vibration isolation ring, the upper fixing cover (211) is disposed at an outer side of the vibration isolation ring, the upper fixing cover (211) is fixedly connected with the upper inner pressing cover (221) through a bolt, and the upper fixing cover (211) is fixedly connected with the upper mounting plate (31).
9. The vibration isolation unlocking device for the sky module as claimed in claim 8, wherein the lower fixing assembly comprises a lower fixing cover (212) and a lower inner pressing cover (222), wherein the lower inner pressing cover (222) is arranged on the inner side of the vibration isolation ring, the lower fixing cover (212) is arranged on the outer side of the vibration isolation ring, the lower fixing cover (212) is fixedly connected with the lower inner pressing cover (222) through bolts, and the lower fixing cover (212) is fixedly connected with the lower mounting plate (32).
10. The vibration isolation unlocking device for the sky patrol module according to claim 9, wherein the inner side surfaces of the upper fixing cover (211) and the lower fixing cover (212) are concave arc surfaces adapted to the outer surface of the outer steel ring (241);
the end surfaces of the upper inner pressing cover (221) and the lower inner pressing cover (222) which are in contact with the inner surface of the inner steel ring (242) are convex arc surfaces which are adaptive to the inner surface of the inner steel ring (242).
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221874308.5U CN217736153U (en) | 2022-07-20 | 2022-07-20 | Vibration isolation unlocking device for sky patrol module |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202221874308.5U CN217736153U (en) | 2022-07-20 | 2022-07-20 | Vibration isolation unlocking device for sky patrol module |
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| CN217736153U true CN217736153U (en) | 2022-11-04 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115126821A (en) * | 2022-07-20 | 2022-09-30 | 中国科学院沈阳自动化研究所 | Vibration isolation unlocking device for sky inspection module |
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2022
- 2022-07-20 CN CN202221874308.5U patent/CN217736153U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115126821A (en) * | 2022-07-20 | 2022-09-30 | 中国科学院沈阳自动化研究所 | Vibration isolation unlocking device for sky inspection module |
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