CN118188729A - Vibration isolation and heat conduction integrated device - Google Patents
Vibration isolation and heat conduction integrated device Download PDFInfo
- Publication number
- CN118188729A CN118188729A CN202410317914.4A CN202410317914A CN118188729A CN 118188729 A CN118188729 A CN 118188729A CN 202410317914 A CN202410317914 A CN 202410317914A CN 118188729 A CN118188729 A CN 118188729A
- Authority
- CN
- China
- Prior art keywords
- vibration
- vibration isolation
- damping pad
- pad
- section
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000002955 isolation Methods 0.000 title claims abstract description 82
- 238000013016 damping Methods 0.000 claims abstract description 70
- 230000007246 mechanism Effects 0.000 claims abstract description 11
- 239000000463 material Substances 0.000 claims description 13
- 230000009467 reduction Effects 0.000 claims description 13
- 229910000838 Al alloy Inorganic materials 0.000 claims description 3
- 239000004952 Polyamide Substances 0.000 claims description 3
- 239000004642 Polyimide Substances 0.000 claims description 3
- 229910001069 Ti alloy Inorganic materials 0.000 claims description 3
- 229920005549 butyl rubber Polymers 0.000 claims description 3
- 230000006835 compression Effects 0.000 claims description 3
- 238000007906 compression Methods 0.000 claims description 3
- 230000005484 gravity Effects 0.000 claims description 3
- 229920002647 polyamide Polymers 0.000 claims description 3
- 229920001721 polyimide Polymers 0.000 claims description 3
- 229920002379 silicone rubber Polymers 0.000 claims description 3
- 239000002360 explosive Substances 0.000 description 6
- 230000000977 initiatory effect Effects 0.000 description 6
- 238000004880 explosion Methods 0.000 description 4
- 238000004891 communication Methods 0.000 description 3
- 238000006073 displacement reaction Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000004044 response Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 239000013078 crystal Substances 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 229920001971 elastomer Polymers 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
Classifications
-
- 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
- F16F1/00—Springs
- F16F1/36—Springs made of rubber or other material having high internal friction, e.g. thermoplastic elastomers
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Vibration Prevention Devices (AREA)
Abstract
The invention discloses a vibration isolation and heat conduction integrated device, belongs to the technical field of vibration isolation of satellite movable parts, and aims to solve the problem that satellite loads of small hole site mechanical interfaces cannot isolate impact and realize heat conduction in the prior art. The invention relates to a plurality of groups of vibration isolation mechanisms with the same structure and a heat conducting pad; each group of vibration isolation mechanism comprises: a vibration isolation housing encased in a configuration of the mechanical interface to satellite loads; a vibration-damping pad disposed within the vibration-isolation housing between the vibration-isolation housing and the mechanical interface; the vibration damping pad comprises a split vibration damping pad upper section, a vibration damping pad middle section and a vibration damping pad lower section, wherein one sides of the vibration damping pad upper section, the vibration damping pad middle section and the vibration damping pad lower section are respectively attached to the upper wall, the side wall and the lower wall of the internal space of the vibration isolation shell; the connecting bolt sequentially penetrates through the upper wall of the vibration isolation shell, the upper section of the vibration damping pad, the mechanical interface, the lower section of the vibration damping pad and the lower wall of the vibration isolation shell; the heat conducting pad is in clearance fit with spaces formed by the side surfaces of the upper arms of the vibration isolation shells.
Description
Technical Field
The invention belongs to the technical field of vibration isolation of satellite movable parts, and particularly relates to a vibration isolation and heat conduction integrated device.
Background
The satellite communication technology is an important support and power for the development of the current informatization age, and can well serve the social and informatization development by means of the continuous improvement of the satellite communication technology level. The reflector antenna is applied to the communication satellite by virtue of high gain, large power capacity and the like. The reflection surface antenna is unlocked by means of explosion of the initiating explosive device, so that the antenna is unfolded, and according to a transmission path, impact force generated by explosion of the initiating explosive device is transmitted to a satellite platform through a bracket and finally transmitted to satellite load arranged on the surface of the platform. In general, the high-frequency impact load will not damage the structure of the spacecraft, but will damage and fail the electronic equipment containing crystal oscillator and brittle material in the components. Therefore, a means for isolating the impact of the initiating explosive device explosion on the satellite load is urgently needed, and meanwhile, the high-power satellite load heat conduction requirement is met, so that the satellite load can work stably.
The vibration isolation device in the prior art is designed to separate the protected piece from the original mounting surface, so that the requirements of vibration isolation and heat conduction cannot be met at the same time, and the conventional vibration isolation device such as a cylindrical sleeve type rubber vibration isolation device has larger mounting hole requirements, and cannot be adapted to a single machine of a small hole site mechanical interface; in addition, the structure lacks a coupling design, and reasonable distribution of design constraint and targets cannot be realized.
Disclosure of Invention
The invention aims to provide a vibration isolation and heat conduction integrated device, which solves the problem that satellite loads of small hole site mechanical interfaces cannot isolate impact and realize heat conduction in the prior art.
In order to achieve the above purpose, the vibration isolation and heat conduction integrated device of the invention comprises a plurality of groups of vibration isolation mechanisms with the same structure and a heat conduction pad;
Each group of vibration isolation mechanisms comprises:
A vibration isolation housing encased in a configuration of the mechanical interface to satellite loads;
a vibration-damping pad disposed within the vibration-isolation housing between the vibration-isolation housing and the mechanical interface; the vibration damping pad comprises a split vibration damping pad upper section, a vibration damping pad middle section and a vibration damping pad lower section, wherein one sides of the vibration damping pad upper section, the vibration damping pad middle section and the vibration damping pad lower section are respectively attached to the upper wall, the side wall and the lower wall of the internal space of the vibration damping shell, and the other sides are in contact with the upper end face, the side face and the lower end face of a mechanical interface of a load bottom plate of satellite load;
The connecting bolt sequentially penetrates through the upper wall of the vibration isolation shell, the upper section of the vibration damping pad, the mechanical interface, the lower section of the vibration damping pad and the lower wall of the vibration isolation shell;
The heat conducting pad is in clearance fit with a space formed by the side surfaces of the upper arms of the vibration isolation shells of the plurality of groups of vibration isolation mechanisms.
The sum of the heights of the upper section of the vibration reduction pad and the lower section of the vibration reduction pad is H; the height difference between the distance between the upper wall and the lower wall of the internal space of the vibration isolation shell and the mechanical interface is h; wherein H > H.
The vibration isolation shell and the mechanical interface extrude the upper section of the vibration damping pad and the lower section of the vibration damping pad so that the compression quantity generated by the upper section of the vibration damping pad and the lower section of the vibration damping pad is larger than the deformation quantity caused by gravity.
The thickness of the heat conducting pad is larger than the sum of the thickness of the lower wall of the vibration isolation shell and the thickness of the lower section of the vibration damping pad.
The vibration isolation shell is made of aluminum alloy or titanium alloy.
The material of the vibration reduction pad is a low-volatility nonmetallic material.
The vibration reduction pad is made of silicon rubber or butyl rubber.
The heat conducting pad material is polyimide or polyamide.
The beneficial effects of the invention are as follows: the vibration isolation and heat conduction integrated device comprehensively considers the dual purposes of vibration isolation and heat conduction of satellite load, and reasonably optimizes the structural rigidity and heat conduction characteristics. The mechanical response of the satellite load of the rocket launching section, such as sinusoidal vibration and random vibration, can be reduced, and the impact of initiating explosive device explosion on the satellite load can be isolated during the orbit; in addition, the high-power satellite load heat conduction requirement can be met. The vibration isolation and heat conduction integrated device has the characteristics of integration, high reliability, easiness in assembly, easiness in processing and the like, can greatly reduce the impact response magnitude born by satellite load when initiating explosive devices, and simultaneously conducts heat generated during load operation.
Drawings
Fig. 1 is a schematic diagram of the overall structure of a vibration isolation and heat conduction integrated device of the invention;
FIG. 2 is an exploded view of a portion of an integrated vibration isolation and thermal conduction device of the present invention;
FIG. 3 is a partial cross-sectional view of an integrated vibration isolation and thermal conduction device of the present invention;
Wherein: 1. satellite load, 101, load bottom plate, 102, mechanical interface, 2, vibration isolation shell, 3, damping pad, 301, damping pad upper section, 302, damping pad middle section, 303, damping pad lower section, 4, heat conducting pad, 5, connecting bolt.
Detailed Description
Embodiments of the present invention will be further described with reference to the accompanying drawings.
Referring to fig. 1-3, an integrated vibration isolation and heat conduction device of the present invention includes a plurality of groups of vibration isolation mechanisms with the same structure and a heat conduction pad 4;
Each group of vibration isolation mechanisms comprises:
A vibration isolation housing 2 encased in a configuration of the mechanical interface 102 relative to the satellite load 1;
A vibration-damping pad 3 disposed within the vibration-isolation housing 2 between the vibration-isolation housing 2 and the mechanical interface 102; the vibration damping pad 3 comprises a split vibration damping pad upper section 301, a vibration damping pad middle section 302 and a vibration damping pad lower section 303, wherein one side of the vibration damping pad upper section 301, one side of the vibration damping pad middle section 302 and one side of the vibration damping pad lower section 303 are respectively attached to the upper wall, the side wall and the lower wall of the internal space of the vibration isolation shell 2, and the other side of the vibration damping pad is in contact with the upper end face, the side face and the lower end face of the mechanical interface 102 of the load bottom plate 101 of the satellite load 1; the sectional design of the vibration damping pad 3 reduces the cycle limit of the die processing of the vibration damping pad 3, has simple and reliable structure, easy processing and high reliability;
and a connecting bolt 5 passing through the upper wall of the vibration isolation housing 2, the vibration damping pad upper section 301, the mechanical interface 102, the vibration damping pad lower section 303, and the lower wall of the vibration isolation housing 2 in this order; the connecting bolt 5 can be a standard bolt of any model, and can also be a non-standard bolt;
The heat conducting pad 4 is in clearance fit with a space formed by the side surfaces of the upper arms of the vibration isolation shells 2 of the vibration isolation mechanisms, so that lateral displacement of the heat conducting pad 4 is limited.
The processing apertures of the vibration isolation housing 2, the vibration reduction pad upper section 301 and the vibration reduction pad lower section 302 are designed in tolerance compared with the apertures of the connecting bolts 5, and the coaxial assembly is ensured, so that the connecting bolts 5 are matched and fixed on the satellite cover plate with the vibration isolation housing 2, the vibration reduction pad 3 and the mechanical interface 102 of the satellite load 1.
The mechanical interface 102 of the satellite load 1 of the existing model is configured into a trapezoid structure, so that the vibration isolation shell 2 is designed into a trapezoid outer-wrapping structure according to the structure of the satellite load 1, and has low processing cost and higher suitability. The three degrees of freedom of the load are restrained by the single vibration isolation housing 2, and the number of the vibration isolation housings 2 is plural.
The sum of the heights of the upper vibration damping pad section 301 and the lower vibration damping pad section 303 is H; the height difference between the distance between the upper wall and the lower wall of the inner space of the vibration isolation shell 2 and the mechanical interface 102 is h; wherein H > H. The upper vibration-damping pad section 301 and the lower vibration-damping pad section 303 are compressed by a certain amount, so that the whole of the upper vibration-damping pad section 301, the lower vibration-damping pad section 303 and the mechanical interface 102 are in interference fit with the vibration-isolating shell 2. According to the material parameters and the size parameters of the upper section 301, the middle section 302 and the lower section 303 of the vibration damping pad, the vibration isolation device with wide vibration isolation magnitude range can be obtained.
The vibration isolation housing 2 and the mechanical interface 102 squeeze the upper damper pad section 301 and the lower damper pad section 303 so that the compression amount generated by the upper damper pad section 301 and the lower damper pad section 303 is larger than the deformation amount caused by gravity.
The thickness of the heat conducting pad 4 is larger than the sum of the thickness of the lower wall of the vibration isolation shell 2 and the thickness of the lower section 303 of the vibration damping pad, so that the heat conducting pad 4 is tightly attached to the contact surface of the satellite load 1, and the good heat conductivity of the satellite load 1 is ensured.
The vibration isolation shell 2 is made of aluminum alloy or titanium alloy. The vibration isolator has the functions of limiting the deformation displacement of the vibration isolator and bearing the standard moment of the connecting bolt 5 when initiating explosive devices are initiated.
The material of the vibration reduction pad 3 is a low-volatility nonmetallic material. Ensuring that the material has lower elastic modulus and larger material damping. The low volatility means that the total mass loss is less than 1% under the pressure of less than 1.3 multiplied by 10 -3 pa and the temperature of 125 ℃ according to the satellite design and construction specifications; the mass of the obtained condensable volatile matter is less than 0.1% when collected at 25 ℃.
The material of the vibration reduction pad 3 is silicon rubber or butyl rubber.
The heat conducting pad 4 is made of polyimide or polyamide, and is made of flexible materials.
Claims (8)
1. The vibration isolation and heat conduction integrated device is characterized by comprising a plurality of groups of vibration isolation mechanisms with the same structure and a heat conduction pad (4);
Each group of vibration isolation mechanisms comprises:
A vibration isolation housing (2) encased in a configuration of the mechanical interface (102) to the satellite load (1);
A vibration-damping pad (3) arranged in the vibration-damping shell (2) and positioned between the vibration-damping shell (2) and the mechanical interface (102); the vibration damping pad (3) comprises a split type vibration damping pad upper section (301), a vibration damping pad middle section (302) and a vibration damping pad lower section (303), one sides of the vibration damping pad upper section (301), the vibration damping pad middle section (302) and the vibration damping pad lower section (303) are respectively attached to the upper wall, the side wall and the lower wall of the inner space of the vibration damping shell (2), and the other sides are in contact with the upper end face, the side face and the lower end face of a mechanical interface (102) of a load bottom plate (101) of the satellite load (1);
The connecting bolt (5) sequentially penetrates through the upper wall of the vibration isolation shell (2), the vibration reduction pad upper section (301), the mechanical interface (102), the vibration reduction pad lower section (303) and the lower wall of the vibration isolation shell (2);
the heat conducting pad (4) is in clearance fit with a space formed by the side surfaces of the upper arms of the vibration isolation shells (2) of the vibration isolation mechanisms.
2. The vibration isolation and heat conduction integrated device according to claim 1, wherein the sum of the heights of the upper vibration-damping pad section (301) and the lower vibration-damping pad section (303) is H; the height difference between the distance between the upper wall and the lower wall of the inner space of the vibration isolation shell (2) and the mechanical interface (102) is h; wherein H > H.
3. The vibration isolation and heat conduction integrated device according to claim 2, wherein the vibration isolation housing (2) and the mechanical interface (102) squeeze the vibration damping pad upper section (301) and the vibration damping pad lower section (303) so that the compression amount generated by the vibration damping pad upper section (301) and the vibration damping pad lower section (303) is larger than the deformation amount caused by gravity.
4. A vibration isolation and heat conduction integrated apparatus as claimed in any one of claims 1 to 3, wherein the thickness of said heat conduction pad (4) is greater than the sum of the thickness of the lower wall of the vibration isolation housing (2) and the thickness of the lower section (303) of the vibration damping pad.
5. The vibration isolation and heat conduction integrated device according to claim 1, wherein the vibration isolation housing (2) is made of aluminum alloy or titanium alloy.
6. The vibration isolation and heat conduction integrated device according to claim 1, wherein the material of the vibration reduction pad (3) is a low-volatility nonmetallic material.
7. The vibration isolation and heat conduction integrated device according to claim 6, wherein the vibration reduction pad (3) is made of silicon rubber or butyl rubber.
8. The vibration isolation and heat conduction integrated device according to claim 1, wherein the heat conduction pad (4) is made of polyimide or polyamide.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410317914.4A CN118188729A (en) | 2024-03-20 | 2024-03-20 | Vibration isolation and heat conduction integrated device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410317914.4A CN118188729A (en) | 2024-03-20 | 2024-03-20 | Vibration isolation and heat conduction integrated device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN118188729A true CN118188729A (en) | 2024-06-14 |
Family
ID=91404650
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202410317914.4A Pending CN118188729A (en) | 2024-03-20 | 2024-03-20 | Vibration isolation and heat conduction integrated device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN118188729A (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102734382A (en) * | 2012-06-18 | 2012-10-17 | 北京经纬恒润科技有限公司 | Shock reducing rubber gasket, dosing control unit (DCU) with same and diesel engine |
| US20120292476A1 (en) * | 2011-05-19 | 2012-11-22 | Honeywell International Inc. | Thermally-conductive vibration isolators and spacecraft isolation systems employing the same |
| CN202707907U (en) * | 2012-07-24 | 2013-01-30 | 北京经纬恒润科技有限公司 | Vibration-damping rubber pad, exhaust aftertreatment controller with same, and diesel engine |
| CN108662082A (en) * | 2018-06-26 | 2018-10-16 | 贵州航天控制技术有限公司 | A kind of vibration absorber of the vehicle-mounted inertial navigation system of Three-points supporting type |
| CN109068530A (en) * | 2018-07-11 | 2018-12-21 | 上海微小卫星工程中心 | A kind of high heat consumption single machine of the satellite that vibration damping is thermally conductive |
| CN215421482U (en) * | 2021-08-06 | 2022-01-04 | 杭州晴川科技有限公司 | Overcurrent and overvoltage interference isolation protection circuit for input power supply of massage chair |
| CN113905585A (en) * | 2021-10-08 | 2022-01-07 | 北京精密机电控制设备研究所 | Power driving device with heat dissipation and vibration reduction functions |
| CN218320123U (en) * | 2022-08-30 | 2023-01-17 | 杭州静之源噪声控制技术有限公司 | Vibration damper for elevator guide rail |
-
2024
- 2024-03-20 CN CN202410317914.4A patent/CN118188729A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20120292476A1 (en) * | 2011-05-19 | 2012-11-22 | Honeywell International Inc. | Thermally-conductive vibration isolators and spacecraft isolation systems employing the same |
| CN102734382A (en) * | 2012-06-18 | 2012-10-17 | 北京经纬恒润科技有限公司 | Shock reducing rubber gasket, dosing control unit (DCU) with same and diesel engine |
| CN202707907U (en) * | 2012-07-24 | 2013-01-30 | 北京经纬恒润科技有限公司 | Vibration-damping rubber pad, exhaust aftertreatment controller with same, and diesel engine |
| CN108662082A (en) * | 2018-06-26 | 2018-10-16 | 贵州航天控制技术有限公司 | A kind of vibration absorber of the vehicle-mounted inertial navigation system of Three-points supporting type |
| CN109068530A (en) * | 2018-07-11 | 2018-12-21 | 上海微小卫星工程中心 | A kind of high heat consumption single machine of the satellite that vibration damping is thermally conductive |
| CN215421482U (en) * | 2021-08-06 | 2022-01-04 | 杭州晴川科技有限公司 | Overcurrent and overvoltage interference isolation protection circuit for input power supply of massage chair |
| CN113905585A (en) * | 2021-10-08 | 2022-01-07 | 北京精密机电控制设备研究所 | Power driving device with heat dissipation and vibration reduction functions |
| CN218320123U (en) * | 2022-08-30 | 2023-01-17 | 杭州静之源噪声控制技术有限公司 | Vibration damper for elevator guide rail |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US9327847B2 (en) | Thermal straps for spacecraft | |
| US9733027B2 (en) | Thermal straps for spacecraft | |
| CN2896603Y (en) | Fast-plugging self-locking type radio coaxial connector | |
| EP2400181A2 (en) | Chassis mounting system | |
| JP2005537667A (en) | Rugged electronics enclosure | |
| CN100459317C (en) | Coaxial connector in radio frequency | |
| CN102927194A (en) | Electrical device damping structure | |
| CN118188729A (en) | Vibration isolation and heat conduction integrated device | |
| CN108749997B (en) | Elastic displacement compensation fixedly-connected unit and deep-sea multi-pressure-resistant-body combined pressure-resistant structure | |
| CN115325089B (en) | Small particle damping type rigid impact reduction device | |
| CN116816849A (en) | Quasi-zero rigidity vibration isolation and reduction device of hydraulic inertial measurement unit | |
| CN208707152U (en) | A kind of antidetonation electric power equipment cabinet | |
| CN107314072B (en) | Friction damping dynamic vibration absorber | |
| US8653922B2 (en) | Electromechanical relay housing, relay, switching assembly and electromagnetic relay support assembly | |
| US3314631A (en) | Resilient mounting system | |
| CN114718988A (en) | Satellite flywheel vibration isolator based on flexible frame body | |
| CN212290395U (en) | Locking and releasing device for satellite-borne antenna | |
| CN110486405B (en) | Vibration isolation system with annular metal rubber vibration isolator | |
| CN114278701B (en) | Broadband vibration reduction platform suitable for variable frequency load | |
| CN220130338U (en) | Flexible supporting device for fixing aircraft parts on airframe structure | |
| CN109573102B (en) | Whole cabin vibration damper without resonance peak | |
| CN219029749U (en) | Integrated unmanned aerial vehicle carries and kills and explodes warhead structure | |
| CN114180109B (en) | Impact relieving device based on particle damping | |
| CN220378772U (en) | High damping lamination rubber belleville spring device and structure | |
| CN109229428B (en) | Three-way impact isolation device suitable for microsatellite |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |