CN115126821A - Vibration isolation unlocking device for sky inspection module - Google Patents
Vibration isolation unlocking device for sky inspection module Download PDFInfo
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- CN115126821A CN115126821A CN202210855511.6A CN202210855511A CN115126821A CN 115126821 A CN115126821 A CN 115126821A CN 202210855511 A CN202210855511 A CN 202210855511A CN 115126821 A CN115126821 A CN 115126821A
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- 238000002955 isolation Methods 0.000 title claims abstract description 87
- 238000007689 inspection Methods 0.000 title abstract description 6
- 230000005540 biological transmission Effects 0.000 claims abstract description 9
- 238000003825 pressing Methods 0.000 claims description 75
- 229910001285 shape-memory alloy Inorganic materials 0.000 claims description 35
- 229910000831 Steel Inorganic materials 0.000 claims description 31
- 239000010959 steel Substances 0.000 claims description 31
- 229920002379 silicone rubber Polymers 0.000 claims description 8
- 238000009434 installation Methods 0.000 claims description 5
- 230000009471 action Effects 0.000 claims description 3
- 230000003044 adaptive effect Effects 0.000 claims 1
- 230000003287 optical effect Effects 0.000 abstract description 7
- 238000000034 method Methods 0.000 abstract description 6
- 230000008569 process Effects 0.000 abstract description 6
- 230000009467 reduction Effects 0.000 abstract description 5
- 238000010521 absorption reaction Methods 0.000 abstract description 2
- 238000013016 damping Methods 0.000 description 15
- 230000006835 compression Effects 0.000 description 13
- 238000007906 compression Methods 0.000 description 13
- 238000013461 design Methods 0.000 description 5
- 230000003068 static effect Effects 0.000 description 5
- 229920001971 elastomer Polymers 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 230000007246 mechanism Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 238000004026 adhesive bonding Methods 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005284 excitation Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 230000006870 function Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000005312 nonlinear dynamic Methods 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
- F16F15/04—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means
- F16F15/08—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means with rubber springs ; with springs made of rubber and metal
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B1/00—Devices for securing together, or preventing relative movement between, constructional elements or machine parts
- F16B1/02—Means for securing elements of mechanisms after operation
- F16B1/04—Means for securing elements of mechanisms after operation disengaged by movement of the actuating member of the element
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B2200/00—Constructional details of connections not covered for in other groups of this subclass
- F16B2200/77—Use of a shape-memory material
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Acoustics & Sound (AREA)
- Remote Sensing (AREA)
- Vibration Prevention Devices (AREA)
Abstract
The invention relates to the technical field of protection of space load in a rocket launching stage and vibration reduction in an on-orbit stage, in particular to a vibration isolation unlocking device for an inspection 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 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 invention not only can ensure the rigidity of the patrolling module in the launching process without violent vibration, but also can ensure good vibration isolation and energy absorption in the on-orbit stage, and reduce the influence of vibration transmission in the patrolling module on the optical load cabin.
Description
Technical Field
The invention relates to the technical field of protection of space load in a rocket launching stage and vibration reduction in an on-orbit stage, in particular to a vibration isolation unlocking device for an inspection 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 selection parameters mainly comprise: static performance (static rigidity, compression displacement), dynamic performance (dynamic rigidity, damping coefficient), installation and arrangement position and angle. If the device is used on the orbit for a long time, the working environment use requirement and the fatigue performance 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.
Disclosure of Invention
In view of the above problems, an object of the present invention is to provide a vibration isolation unlocking device for a skyward module, so as to provide sufficient rigidity and vibration damping performance in the launching process and the subsequent stage of the skyward module, and ensure that the skyward module does not vibrate violently in the rocket launching stage and the vibration of vibration sources such as a refrigerator is transmitted to an optical load compartment in the stage of reducing the orbit.
In order to achieve the purpose, the invention adopts the following technical scheme:
the invention 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 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 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 pressing rod, and two ends of the spring are respectively abutted against the limiting table at the upper end part of the pressing 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 pressing 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, 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 invention has the advantages and beneficial effects that:
1. the invention provides an annular laminated damping structure, namely a vibration isolation ring for short, by utilizing the geometric nonlinear characteristic of an annular structure and combining the viscoelastic damping of a rubber material, so as to inhibit the micro-vibration caused by an 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. According to the invention, the memory alloy unlocking module is adopted, and the characteristics of high static rigidity and low dynamic rigidity of the annular structure are matched, so that the whole system of the sky patrol module still has enough rigidity without severe vibration in the rocket launching stage.
3. The invention has the advantages that the main structure is compact, the reasonable design tool can be conveniently suitable for various installation environments, and the layout is flexible.
4. The vibration isolation device has wider applicability, and design parameters and materials of the vibration isolation ring can be conveniently adjusted according to the actual vibration working condition so as to meet the vibration reduction requirement.
Drawings
Fig. 1 is a schematic structural diagram of a vibration isolation unlocking device for a sky patrol module, which is disclosed by the invention;
FIG. 2 is a schematic view of the vibration isolation device according to the present invention;
FIG. 3 is a schematic structural diagram of the 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 more apparent, the present invention will be described in detail with reference to the accompanying drawings and specific embodiments.
As shown in fig. 1, the invention provides a vibration isolation unlocking device for a sky patrol module, which comprises 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 a 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 generate severe vibration; in the track-in stage, the locking/unlocking 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, where the vibration isolation ring is an annular laminated damping structure and is used for reducing transmission of vibration of the vibration source to the optical device in the on-track stage of the sky patrol module; 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.
In the embodiment of the invention, the vibration isolation ring comprises an inner steel ring 242 and an outer steel ring 241 which are arranged concentrically inside and outside, and silicon rubber 25 is arranged between the inner 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.
In the embodiment of the present invention, 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 inside the vibration isolating ring, the upper fixing cover 211 is disposed outside the vibration isolating ring, the upper fixing cover 211 is fixedly connected to the upper inner pressing cover 221 by a bolt, and the upper fixing cover 211 is fixedly connected to the upper mounting plate 31. 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 corresponding to the outer surface of the outer steel ring 241, and the end surfaces of the upper inner pressing cover 221 and the lower inner pressing cover 222 contacting the inner surface of the inner steel ring 242 are convex arc surfaces corresponding to the inner surface of the inner steel ring 242, so that the upper fixing cover 211, the upper pressing cover 221, the lower fixing cover 212 and the lower inner pressing 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 and unlocking device 1 includes a pressing bush 12, a memory alloy unlocking module 13, a supporting seat 14, a pressing rod 15 and an ejecting 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 in a top mounting hole of the support base 14.
Further, a plurality of connecting platforms are arranged on the outer circumference of the pressing bushing 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.
In the embodiment of the invention, the locking and unlocking device 1 is locked by inserting the pressing rod 15 into the memory alloy unlocking module 13, and the unlocking device 1 is fixed on the upper mounting plate 31 by matching with the pressing bush 12. 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 and release the fixed constraint of the unlocking device 1 and the upper mounting plate 31 when the memory alloy unlocking module 13 is in a 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 invention provides a vibration isolation unlocking device for a sky patrol module, which has the working principle that:
the vibration isolation device 2 utilizes the geometric non-linear 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 so as to inhibit 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 track entering, before the equipment such as the refrigerator starts working, 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 constraint 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 track entering. 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 invention has correct testing principle, comprehensively considers the influence of the pretightening force and the radial load factors on the dynamic stiffness of the bearing, simulates the actual working condition, tests the dynamic characteristic parameters of different bearings under different working conditions and can provide data for the online regulation and control of related equipment.
The invention provides a vibration isolation unlocking device for a sky inspection module, which ensures sufficient rigidity and vibration damping performance of the sky inspection module in a launching process and a subsequent orbit entering stage. 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 invention not only can ensure the rigidity of the patrolling module in the launching process without violent vibration, but also can ensure good vibration isolation and energy absorption in the on-orbit stage, and reduce the influence of vibration transmission in the patrolling module on the optical load cabin.
The above description is only an 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 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 according to 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 with 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 recited in claim 2, wherein said supporting base (14) is a square frame structure, and the top 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 silicon 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 comprises an upper fixing cover (211) and an upper inner pressing cover (221), wherein the upper inner pressing cover (221) is arranged on the inner side of the vibration isolation ring, the upper fixing cover (211) is arranged on the outer side of the vibration isolation ring, the upper fixing cover (211) is fixedly connected with the upper inner pressing cover (221) through bolts, 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).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210855511.6A CN115126821A (en) | 2022-07-20 | 2022-07-20 | Vibration isolation unlocking device for sky inspection module |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210855511.6A CN115126821A (en) | 2022-07-20 | 2022-07-20 | Vibration isolation unlocking device for sky inspection module |
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| CN115126821A true CN115126821A (en) | 2022-09-30 |
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| CN202210855511.6A Pending CN115126821A (en) | 2022-07-20 | 2022-07-20 | Vibration isolation unlocking device for sky inspection module |
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| US20130221163A1 (en) * | 2012-02-28 | 2013-08-29 | Honeywell International Inc. | Launch lock assemblies including axial gap amplification devices and spacecraft isolation systems including the same |
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