CN109229428B - Three-way impact isolation device suitable for microsatellite - Google Patents
Three-way impact isolation device suitable for microsatellite Download PDFInfo
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- CN109229428B CN109229428B CN201811208827.6A CN201811208827A CN109229428B CN 109229428 B CN109229428 B CN 109229428B CN 201811208827 A CN201811208827 A CN 201811208827A CN 109229428 B CN109229428 B CN 109229428B
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- 238000002955 isolation Methods 0.000 title claims abstract description 82
- 108091092878 Microsatellite Proteins 0.000 title claims abstract description 34
- 230000035939 shock Effects 0.000 claims description 53
- 239000006096 absorbing agent Substances 0.000 claims description 31
- 239000000463 material Substances 0.000 claims description 12
- 238000013016 damping Methods 0.000 claims description 7
- 238000009413 insulation Methods 0.000 claims description 7
- 238000000034 method Methods 0.000 claims description 7
- 229920000459 Nitrile rubber Polymers 0.000 claims description 4
- 229910000838 Al alloy Inorganic materials 0.000 claims description 3
- 229920001967 Metal rubber Polymers 0.000 claims description 3
- 229910001069 Ti alloy Inorganic materials 0.000 claims description 3
- 239000004814 polyurethane Substances 0.000 claims description 3
- 229920003225 polyurethane elastomer Polymers 0.000 claims description 3
- 230000000149 penetrating effect Effects 0.000 claims description 2
- 239000002360 explosive Substances 0.000 abstract description 15
- 230000000977 initiatory effect Effects 0.000 abstract description 15
- 238000004880 explosion Methods 0.000 abstract description 9
- 230000000694 effects Effects 0.000 abstract description 8
- 230000009467 reduction Effects 0.000 abstract description 8
- 238000009434 installation Methods 0.000 abstract description 7
- 230000004044 response Effects 0.000 description 14
- 238000000926 separation method Methods 0.000 description 10
- 230000001681 protective effect Effects 0.000 description 6
- 238000000429 assembly Methods 0.000 description 5
- 230000000712 assembly Effects 0.000 description 5
- 238000004519 manufacturing process Methods 0.000 description 5
- 230000008569 process Effects 0.000 description 3
- 238000011161 development Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000002474 experimental method Methods 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- 238000003032 molecular docking Methods 0.000 description 2
- 230000002787 reinforcement Effects 0.000 description 2
- 125000006850 spacer group Chemical group 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 230000002238 attenuated effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000003638 chemical reducing agent Substances 0.000 description 1
- 239000003795 chemical substances by application Substances 0.000 description 1
- 239000013078 crystal Substances 0.000 description 1
- 238000005474 detonation Methods 0.000 description 1
- 229920001971 elastomer Polymers 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
- 239000005060 rubber Substances 0.000 description 1
- 238000001612 separation test Methods 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 238000001228 spectrum Methods 0.000 description 1
- 230000001052 transient effect Effects 0.000 description 1
Classifications
-
- 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
- B64G1/52—Protection, safety or emergency devices; Survival aids
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
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- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Health & Medical Sciences (AREA)
- Critical Care (AREA)
- Emergency Medicine (AREA)
- General Health & Medical Sciences (AREA)
- Physics & Mathematics (AREA)
- Astronomy & Astrophysics (AREA)
- General Physics & Mathematics (AREA)
- Vibration Prevention Devices (AREA)
- Vibration Dampers (AREA)
Abstract
The three-way impact isolation device is used for being installed between a satellite bottom plate and a satellite main frame and comprises a structure adapter plate and an impact isolation assembly; the structure adapter plate is arranged on the satellite bottom plate and is provided with a through hole; the isolation assembly is connected with the satellite main frame, and the middle part of the isolation assembly is connected with the structure adapter plate through the through hole. The impact isolation assembly has axial and radial vibration reduction impact isolation effects, effectively isolates and absorbs impact loads generated when initiating explosive devices such as explosion bolts and the like explode, and ensures that the impact loads reaching a single machine installation point meet the use index of a single machine, thereby ensuring the safety of micro satellite emission; and the original satellite bottom plate can be reliably connected with the satellite main frame, so that the strength and rigidity of the whole satellite of the microsatellite are ensured.
Description
Technical Field
The invention relates to the technical field of aircraft impact reduction equipment, in particular to a three-way impact isolation device suitable for microsatellites.
Background
With the rise of commercial aerospace, the number of satellites in China is increased in recent years, and high-volume development and launching cost of large satellites are difficult to bear for certain universities and enterprises, so that the large satellites are usually developed, and because of the difference of structures and shapes, the large satellites are not provided with standard and general docking devices, and most docking devices can generate great impact at the time of separating satellites and arrows in order to ensure reliability or choose explosive bolts.
The satellite-rocket separation impact environment is one of the most severe mechanical environments experienced by satellites in the launching process, and is a high-frequency and high-magnitude transient impact response generated by initiating actions of initiating agents on a satellite structure. In general, the high-frequency initiating explosive device impact load cannot damage the structure of the spacecraft, but can damage precise electronic equipment such as crystal oscillator, brittle materials and the like, so that the failure of the aerospace task is caused. For example, a satellite in a three-point explosion bolt unlocking mode is adopted, the satellite connects a satellite-rocket separating mechanism with the whole satellite through three explosion bolts, and the three explosion bolts detonate simultaneously at the moment of satellite-rocket separation, so that the separation of the satellite and a carrying system is realized. The shock waves generated by the three initiating explosive devices are directly transmitted to the satellite main frame connected with the initiating explosive devices through the satellite-rocket interface and the separation sleeve cover, and because the impact load of the explosion of the initiating explosive devices is large, the impact load of the explosion of the initiating explosive devices does not fall to less than 2000g at the 50mm position of the separation surface, the impact waves exceed the requirements of the task books of the separation mechanism and the single-machine task books, the problem of damage to precise electronic equipment exists, and the failure of the aerospace task is easy to cause.
Disclosure of Invention
In order to solve the problem that the initiating explosive device detonates to damage precise electronic equipment in a satellite, the invention provides a three-way impact isolation device suitable for a microsatellite.
The technical scheme adopted by the invention for solving the technical problems is as follows:
the three-way impact isolation device suitable for the microsatellite is arranged between a satellite bottom plate and a satellite main frame, and comprises a structural adapter plate and an impact isolation assembly; the structure adapter plate is arranged on the satellite bottom plate and is provided with a through hole; the isolation assembly is connected with the satellite main frame, and the middle part of the isolation assembly is connected with the structure adapter plate through the through hole.
Further, the shock insulation assembly comprises a shaft sleeve penetrating through the through hole, two shock absorbers and two shock absorber protection shells; the two vibration absorbers are sleeved on the shaft sleeve and are respectively arranged at two sides of the through hole; the two shock absorber protective shells are sleeved on the two shock absorbers in one-to-one correspondence and are connected with the structural adapter plate.
Still further, the shock insulation assembly further comprises a vibration reduction gasket, wherein the vibration reduction gasket is arranged on the vibration damper close to the satellite bottom plate and is positioned on the end face of one end of the vibration damper close to the satellite bottom plate.
Furthermore, the shock insulation assembly is connected with the satellite main frame through screws, and the vibration reduction gasket is positioned between the vibration reducer and the screws.
Furthermore, the materials of the shock absorber gasket, the shock absorber protective shell and the shaft sleeve are titanium alloy.
Further, the material of the shock absorber is nitrile rubber, polyurethane or metal rubber.
Further, the axial section of the impact isolation assembly is I-shaped.
Further, the structure adapter plate comprises a flat plate and a downward protruding portion arranged on the flat plate, the through hole is formed in the flat plate, a threaded hole is formed in the downward protruding portion, and the structure adapter plate is connected with the satellite bottom plate through the threaded hole.
Further, the structural adapter plate is made of 2A12 aluminum alloy.
The method for using the three-way impact isolation device suitable for the microsatellite comprises the steps of installing and fixing the impact isolation assembly on a satellite main frame after the satellite main frame is assembled and vertically overturned, installing and fixing a satellite bottom plate on the structure adapter plate, and finally vertically overturned the installed satellite main frame, the isolation device and the satellite bottom plate at the same time.
The beneficial effects of the invention are as follows:
1. based on the propagation and attenuation characteristics of shock waves in the structure, the middle part of the shock isolation assembly is connected with the structural adapter plate, the shock isolation assembly has an axial shock isolation effect and a radial shock isolation effect, can play a role in reducing shock in three directions of a microsatellite, can effectively isolate and absorb shock loads generated when initiating explosive devices such as an explosion bolt and the like are exploded, has higher shock isolation efficiency, and enables the shock loads reaching a single installation point to meet the use index of a single machine, thereby solving the problem of damage to precise electronic equipment in the satellite caused by initiating explosive devices and ensuring the safety of microsatellite emission.
2. The original satellite bottom plate can be reliably connected with the main bearing frame (namely the satellite main frame) through the structural adapter plate and the isolation assembly, so that the strength and the rigidity of the whole satellite of the microsatellite are ensured, and the sine and random response, particularly the random response, of the whole satellite can be greatly reduced while the isolation is realized; the safety of the microsatellite under the severe transmitting section environment is ensured.
3. The invention has strong adaptability, can adjust the shape and the size according to the structure of the microsatellite, is easy to assemble and is simple to use and install.
4. The three-way impact isolation device suitable for the microsatellite has the advantages of low cost, easiness in processing, short manufacturing period and simple structure, and can achieve excellent impact isolation performance by adopting the existing mature material which is verified on the day.
Drawings
Fig. 1 is a view showing an installation state of a three-way impact isolation device suitable for a microsatellite according to the present invention.
Fig. 2 is a schematic structural view of a three-way impact isolation device suitable for a microsatellite according to the present invention.
Fig. 3 is a block diagram of a spacer assembly suitable for use in a microsatellite according to the present invention.
FIG. 4 is a graph of the impact response value of a stand-alone mounting point 50mm from the parting plane when the present invention is not in use.
FIG. 5 is a graph of the impact response of a stand-alone mounting point 50mm from the parting plane after use of the present invention.
In the figure: 1. 1.1 parts of structural adapter plates, 1.1 parts of downward protruding parts, 2 parts of shock isolation components, 2.1 parts of shock absorption gaskets, 2.2 parts of shock absorbers, 2.3 parts of shock absorber protective shells, 2.4 parts of shaft sleeves, 3 parts of satellite main frames, 4 parts of satellite bottom plates, 5 parts of screws.
Detailed Description
In order to make the technical solution of the present invention more clear, the technical solution of the present invention will be described in detail with reference to the accompanying drawings and specific examples, which will help those skilled in the art to further understand the present invention, but do not limit the present invention in any way. It should be noted that several variations and modifications of the device can be made by a person skilled in the art without departing from the concept of the invention. These are all intended to be within the scope of the present invention.
A three-way impact isolation device suitable for microsatellites comprises a structural adapter plate 1 and an impact isolation assembly 2. The structure adapter plate 1 is used for being installed on the satellite bottom plate 4, through holes are formed in the structure adapter plate 1, and the number of the through holes can be plural. The middle position of each isolation assembly 2 passes through the through hole and is connected to the structure adapter plate 1 in the middle, the number of the isolation assemblies 2 can be plural, specifically, each isolation assembly 2 can pass through one through hole, each isolation assembly 2 is connected to the structure adapter plate 1, the isolation assemblies 2 are used for connecting with the satellite main frame 3, that is, when the isolation assemblies are installed on a satellite, one end of each isolation assembly 2 is connected with the satellite main frame 3, the middle is connected with the structure adapter plate 1, and the other end of each isolation assembly 2 can be suspended. As shown in fig. 1, the three-way impact isolation device of the present invention is installed between a satellite base plate 4 and a satellite main frame 3.
The action and effect are as follows:
aiming at the problem that initiating explosive device detonation affects satellites, based on the fact that initiating explosive device impact propagates in a wave mode in a structure, impact response is attenuated rapidly along with the increase of propagation distance or through a connecting link, and the three-way impact isolation device suitable for microsatellites is provided. The middle part of the isolation assembly 2 is connected with the structure adapter plate 1, the isolation assembly 2 has an axial isolation effect and a radial isolation effect (perpendicular to the axial plane), and the impact reduction effect can be achieved in three directions of the microsatellite. The three-way impact isolation device can effectively isolate and absorb impact load generated when initiating explosive devices such as explosion bolts and the like explode, has higher impact isolation efficiency, namely high impact attenuation efficiency, and ensures that the impact load reaching a single machine installation point meets the use index of a single machine, thereby solving the problem of damage to precise electronic equipment in a satellite caused by initiating explosive devices and ensuring the safety of micro satellite emission.
The three-way impact isolation device suitable for the microsatellite can reliably connect the original satellite bottom plate 4 with the main bearing frame (namely the satellite main frame 3) through the structural adapter plate 1 and the impact isolation assembly 2, ensure the strength and the rigidity of the whole satellite of the microsatellite, and can greatly reduce the sine and the random response, especially the random response, of the whole satellite while isolating; the safety of the microsatellite under the severe transmitting section environment is ensured.
The three-way impact isolation device has strong adaptability, can adjust the shape and the size according to the structure of the microsatellite, and is easy to assemble. The three-way impact isolation device is low in cost, easy to process, light in weight, low in production cost, short in manufacturing period, simple in structure and excellent in impact isolation performance, and is manufactured by adopting the existing mature material verified on the day.
With the development of commercial satellites in China being popular, the number of domestic research and development satellites is increased, the invention has the advantages of low production cost, short manufacturing period, small size, no occupation of space on the satellite, simple structure, easy assembly, light weight, high reliability, high impact attenuation efficiency and the like, and has wide application prospect.
The invention relates to a mounting and using method of a three-way impact isolation device suitable for a microsatellite, which is simple and easy to operate, and comprises the following specific processes: firstly, the assembly of the isolation assembly 2 and the structural adapter plate 1 is completed according to the diagram shown in fig. 2, the isolation assembly 2 is slightly pressed, the isolation assembly 2 elastically deforms in the axial direction and the radial direction, and the installation consistency of the isolation assemblies 2 and the integrity of the isolation assembly 2 are checked to obtain the three-way impact isolation device. And secondly, after the satellite main frame 3 is assembled, the satellite main frame 3 is vertically turned over, the shock isolation assembly 2 of the assembled three-way shock isolation device is mounted on the satellite main frame 3 through a standard component, and standard moment is added for reinforcement. And finally, the satellite bottom plate 4 is arranged on the structural adapter plate 1 of the three-way impact isolation device through a standard component, standard moment is added for reinforcement, and then the whole body (the satellite main frame 3, the isolation device and the satellite bottom plate 4) is vertically turned over.
The specific shape structure of the structure adapter plate 1 can be that the structure adapter plate comprises a flat plate and downward protruding portions 1.1, through holes are formed in the flat plate (namely, the structure adapter plate 1 is provided with the through holes), a plurality of downward protruding portions 1.1 are further formed in the flat plate, the downward protruding portions 1.1 are used for being connected with a satellite bottom plate 4, the downward protruding portions 1.1 are provided with threaded holes, the downward protruding portions 1.1 are connected with the satellite bottom plate 4 through the threaded holes, in the embodiment, the number of the downward protruding portions 1.1 is 14, and each downward protruding portion 1.1 is provided with one threaded hole. Through holes are formed in the positions, not downward protruding portions 1.1, of the flat plate, 12 through holes are formed in the position, in this embodiment, the through holes are divided into two rows, the two rows are symmetrically arranged, the through holes are located between the downward protruding portions 1.1, and a shock insulation assembly 2 is installed at each through hole. The height of the downward bulge 1.1 is larger than the height of the part of the baffle assembly 2 located at the lower side of the through hole, i.e. the lower half of the baffle assembly 2 does not contact the satellite bottom plate 4. The structure adapter plate 1 is installed between the satellite bottom plate 4 and the satellite main frame 3 as structure adapter. In the embodiment, the structural adapter plate 1 is 278mm long and 232mm wide, the used material is 2A12 aluminum alloy, and structural optimization and light weight treatment are carried out according to the whole star response and the fundamental frequency. The above-described structural patch panel 1 may be modified according to the weight of the satellite and the variation of the envelope size.
The specific structure of the shock absorber assemblies 2 can be as shown in fig. 3, and each shock absorber assembly 2 comprises a shock absorbing gasket 2.1, two shock absorbers 2.2, two shock absorber protecting shells 2.3 and a shaft sleeve 2.4. The shaft sleeve 2.4 sequentially passes through the two vibration absorbers 2.2, one vibration absorber 2.2 is positioned on the upper side of the through hole on the structural adapter plate 1, and the other vibration absorber 2.2 is positioned on the lower side of the through hole, namely the shaft sleeve 2.4 passes through the through hole. The height of the downward bulge 1.1 is larger than that of the damper 2.2 positioned on one side of the satellite bottom plate 4, the two dampers 2.2 can be in contact with each other, in the embodiment, the material of the damper 2.2 is nitrile rubber, the material of the damper 2.2 is not limited to nitrile rubber, and other types of space rubber, polyurethane or metal rubber and other damping vibration-damping isolation materials can be selected. Each damper 2.2 is sleeved with a damper protecting shell 2.3, the damper protecting shell 2.3 is sleeved on the side surface of the outer side of the damper 2.2, as shown in fig. 3, the damper protecting shell 2.3 is connected to the structural adapter plate 1, that is, the connection of the shock isolation assembly 2 and the structural adapter plate 1 is realized through the damper protecting shell 2.3. The damper protective housing 2.3 adopts the metal protective housing. The damping shim 2.1 is arranged on that damper 2.2 which is close to the satellite bottom plate 4, in particular on the end face of that damper 2.2 which is close to the end of the satellite bottom plate 4. The connection of the shock insulation assembly 2 and the satellite main frame 3 is realized by the connection of the screw 5 and the satellite main frame 3 after the screw 5 passes through the shaft sleeve 2.4, and as shown in fig. 3, the vibration reduction gasket 2.1 is positioned between the vibration absorber 2.2 and the screw 5. The two dampers 2.2 are vertically symmetrical with respect to the through hole or the flat plate, and the damper protecting shell 2.3 is vertically symmetrical with respect to the through hole or the flat plate. The shaft sleeve 2.4 passes through the through hole, the two shock absorbers 2.2 are respectively arranged at two sides of the through hole, the two shock absorber protection shells 2.3 are sleeved on the two shock absorbers 2.2, and the two shock absorber protection shells 2.3 are respectively arranged at two sides of the through hole, namely the middle part of the shock isolation assembly 2 passes through the through hole; in addition, the shock absorber protection shell 2.3 is connected to the structural adapter plate 1, and the connection part between the shock absorber protection shell 2.3 and the structural adapter plate 1 is the middle part of the whole shock isolation assembly 2, namely the middle part of the shock isolation assembly 2 is connected with the structural adapter plate 1. The axial section of the baffle assembly 2 is I-shaped, and the middle concave part of the I shape is arranged at the through hole. In consideration of weight and remanence, the shock absorber gasket 2.1, the shock absorber protective shell 2.3 and the shaft sleeve 2.4 are all made of titanium alloy. The various components of the spacer assembly 2 described above may be modified in response to changes in satellite weight and envelope dimensions.
By taking a micro-nano satellite ground separation experiment as an example, the impact reduction effect of the invention is verified by adopting a drop hammer method preliminary simulation and a real explosion bolt separation experiment. The results of the actual explosive bolt separation test are shown in fig. 4 and 5, wherein fig. 4 shows the impact response value of a single machine installation point at 50mm from the separation surface when the present invention is not applied, and fig. 5 shows the impact response value of a single machine installation point at 50mm from the separation surface after the present invention is applied. As can be seen by comparing fig. 4 and fig. 5, the three-way impact isolation device suitable for the microsatellite can remarkably reduce the three-way impact response, and the impact isolation efficiency reaches about 65% -73%. The Log representation in fig. 4 and 5 shows that the impulse response spectrum shown in the graph is generated logarithmically, X, Y, Z for three directions and Curve for the Curve.
Claims (7)
1. The three-way impact isolation device suitable for the microsatellite is used for being installed between a satellite bottom plate (4) and a satellite main frame (3), and is characterized by comprising a structure adapter plate (1) and an impact isolation assembly (2); the structure adapter plate (1) is arranged on the satellite bottom plate (4), and a through hole is formed in the structure adapter plate (1); the isolation assembly (2) is connected with the satellite main frame (3), and the middle part of the isolation assembly (2) is connected with the structure adapter plate (1) through a through hole;
the axial section of the shock insulation assembly (2) is I-shaped;
the structure adapter plate (1) comprises a flat plate and a downward protruding part (1.1) arranged on the flat plate, the through hole is arranged on the flat plate, a threaded hole is formed in the downward protruding part (1.1), and the structure adapter plate (1) is connected with the satellite bottom plate (4) through the threaded hole;
the shock insulation assembly (2) comprises a shaft sleeve (2.4) penetrating through the through hole, two shock absorbers (2.2) and two shock absorber protection shells (2.3); the two shock absorbers (2.2) are sleeved on the shaft sleeve (2.4) and are respectively arranged at two sides of the through hole; the two shock absorber protection shells (2.3) are sleeved on the two shock absorbers (2.2) in one-to-one correspondence and are connected with the structural adapter plate (1).
2. A three-way impact isolation device for microsatellites according to claim 1, wherein said shock isolation assembly (2) further comprises a vibration damping pad (2.1), said vibration damping pad (2.1) being arranged on a vibration damper (2.2) close to the satellite bottom plate (4) and on an end face of said vibration damper (2.2) close to one end of the satellite bottom plate (4).
3. A three-way impact isolation device for microsatellites according to claim 2, characterized in that said impact isolation assembly (2) is connected to the satellite main frame (3) by means of screws (5), and that the damping pad (2.1) is located between the damper (2.2) and the screws (5).
4. A three-way impact isolation device suitable for microsatellites according to claim 2, wherein the materials of the vibration damping pad (2.1), the vibration damper protecting shell (2.3) and the shaft sleeve (2.4) are all titanium alloy.
5. A three-way impact isolation device for microsatellites according to claim 1, characterized in that the material of said damper (2.2) is nitrile rubber, polyurethane or metal rubber.
6. A three-way impact isolation device for microsatellites according to claim 1, characterized in that the material of said structural adaptor plate (1) is 2a12 aluminium alloy.
7. A method of using a three-way impact isolator for microsatellites according to any one of claims 1 to 6, wherein after the satellite main frame (3) is assembled and turned vertically, the impact isolator assembly (2) is mounted and fixed to the satellite main frame (3), the satellite base plate (4) is mounted and fixed to the structural adaptor plate (1), and finally the mounted satellite main frame (3), isolator and satellite base plate (4) are turned vertically at the same time.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811208827.6A CN109229428B (en) | 2018-10-17 | 2018-10-17 | Three-way impact isolation device suitable for microsatellite |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811208827.6A CN109229428B (en) | 2018-10-17 | 2018-10-17 | Three-way impact isolation device suitable for microsatellite |
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| Publication Number | Publication Date |
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| CN109229428A CN109229428A (en) | 2019-01-18 |
| CN109229428B true CN109229428B (en) | 2024-02-20 |
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| CN201811208827.6A Active CN109229428B (en) | 2018-10-17 | 2018-10-17 | Three-way impact isolation device suitable for microsatellite |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6199801B1 (en) * | 1997-12-01 | 2001-03-13 | Csa Engineering, Inc. | Whole-spacecraft passive isolation devices |
| CN103939514A (en) * | 2014-03-20 | 2014-07-23 | 上海卫星工程研究所 | Three-way equivalent-rigidity vibration isolator for satellite |
| CN104058107A (en) * | 2014-05-23 | 2014-09-24 | 北京空间飞行器总体设计部 | Connecting device capable of reducing impact during satellite-rocket separation |
| CN104290927A (en) * | 2014-09-12 | 2015-01-21 | 上海卫星工程研究所 | One-way impact isolating device for satellite |
| CN208979117U (en) * | 2018-10-17 | 2019-06-14 | 长光卫星技术有限公司 | A kind of three-dimensional shock isolating apparatus suitable for microsatellite |
-
2018
- 2018-10-17 CN CN201811208827.6A patent/CN109229428B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6199801B1 (en) * | 1997-12-01 | 2001-03-13 | Csa Engineering, Inc. | Whole-spacecraft passive isolation devices |
| CN103939514A (en) * | 2014-03-20 | 2014-07-23 | 上海卫星工程研究所 | Three-way equivalent-rigidity vibration isolator for satellite |
| CN104058107A (en) * | 2014-05-23 | 2014-09-24 | 北京空间飞行器总体设计部 | Connecting device capable of reducing impact during satellite-rocket separation |
| CN104290927A (en) * | 2014-09-12 | 2015-01-21 | 上海卫星工程研究所 | One-way impact isolating device for satellite |
| CN208979117U (en) * | 2018-10-17 | 2019-06-14 | 长光卫星技术有限公司 | A kind of three-dimensional shock isolating apparatus suitable for microsatellite |
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| CN109229428A (en) | 2019-01-18 |
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Address after: No. 1299, Mingxi Road, Beihu science and Technology Development Zone, Changchun City, Jilin Province Applicant after: Changguang Satellite Technology Co.,Ltd. Address before: No.1759 Mingxi Road, Gaoxin North District, Changchun City, Jilin Province Applicant before: CHANG GUANG SATELLITE TECHNOLOGY Co.,Ltd. |
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Denomination of invention: A Three way Shock Isolation Device Suitable for Micro Satellites Granted publication date: 20240220 Pledgee: Jilin credit financing guarantee Investment Group Co.,Ltd. Pledgor: Changguang Satellite Technology Co.,Ltd. Registration number: Y2024220000032 |