CN109178347B - Unidirectional impact isolation device suitable for microsatellite - Google Patents
Unidirectional impact isolation device suitable for microsatellite Download PDFInfo
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- CN109178347B CN109178347B CN201811208406.3A CN201811208406A CN109178347B CN 109178347 B CN109178347 B CN 109178347B CN 201811208406 A CN201811208406 A CN 201811208406A CN 109178347 B CN109178347 B CN 109178347B
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- 238000002955 isolation Methods 0.000 title claims abstract description 42
- 108091092878 Microsatellite Proteins 0.000 title claims abstract description 33
- 230000035939 shock Effects 0.000 claims abstract description 33
- 238000009413 insulation Methods 0.000 claims abstract description 25
- 238000000034 method Methods 0.000 claims description 9
- 229910000838 Al alloy Inorganic materials 0.000 claims description 3
- 229920001967 Metal rubber Polymers 0.000 claims description 3
- 229920000459 Nitrile rubber Polymers 0.000 claims description 3
- 239000004814 polyurethane Substances 0.000 claims description 3
- 229920003225 polyurethane elastomer Polymers 0.000 claims description 2
- 230000000149 penetrating effect Effects 0.000 claims 1
- 239000002360 explosive Substances 0.000 abstract description 17
- 230000000977 initiatory effect Effects 0.000 abstract description 17
- 238000005474 detonation Methods 0.000 abstract description 4
- 230000000694 effects Effects 0.000 abstract description 4
- 230000009467 reduction Effects 0.000 abstract description 4
- 230000004044 response Effects 0.000 description 13
- 238000000926 separation method Methods 0.000 description 9
- 238000004880 explosion Methods 0.000 description 8
- 239000000463 material Substances 0.000 description 6
- 239000006096 absorbing agent Substances 0.000 description 5
- 238000009434 installation Methods 0.000 description 5
- 238000004519 manufacturing process Methods 0.000 description 5
- 230000008569 process Effects 0.000 description 5
- 230000009471 action 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
- 125000006850 spacer group Chemical group 0.000 description 2
- 230000002238 attenuated effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 239000003795 chemical substances by application Substances 0.000 description 1
- 239000013078 crystal Substances 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 229920001971 elastomer Polymers 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
- 229920002635 polyurethane Polymers 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
- 238000001612 separation test Methods 0.000 description 1
- 239000011359 shock absorbing material Substances 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
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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
- B64G1/52—Protection, safety or emergency devices; Survival aids
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- 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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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02D—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN INFORMATION AND COMMUNICATION TECHNOLOGIES [ICT], I.E. INFORMATION AND COMMUNICATION TECHNOLOGIES AIMING AT THE REDUCTION OF THEIR OWN ENERGY USE
- Y02D30/00—Reducing energy consumption in communication networks
- Y02D30/70—Reducing energy consumption in communication networks in wireless communication networks
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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 Dampers (AREA)
Abstract
A unidirectional impact isolation device suitable for a microsatellite relates to the technical field of impact reduction equipment of aircrafts and solves the problem that initiating explosive device detonation causes damage to precise electronic equipment in the satellite, the device comprises a first structural plate, a second structural plate, a shock insulation pad and screws, the first structural plate and the second structural plate comprise bosses arranged on the lower surfaces of the first structural plate and the second structural plate, and the sum of the heights of the shock insulation pad and screw heads is smaller than the height of the bosses; the satellite main frame, the first structural plate, the second structural plate and the satellite bottom plate are connected by screws sequentially from top to bottom; and the upper and lower parts of the connection parts of the first structural plate, the second structural plate, the satellite bottom plate and the screws are respectively provided with a shock insulation pad. The isolation device has excellent longitudinal vibration reduction and impact isolation effects, effectively isolates and absorbs impact load generated when an initiating explosive device explodes, solves the problem that precision electronic equipment in a satellite is damaged by initiating explosive device detonation, and ensures the safety of micro satellite emission; and the 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 impact reduction equipment of aircrafts, in particular to a unidirectional 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 3 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 be within 2000g at the 50mm position of the separation surface, the impact waves exceed the requirements of the task book of the separation mechanism and the task book of the single machine, 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 precision electronic equipment in a satellite is damaged due to initiating explosive device detonation, the invention provides a unidirectional impact isolation device suitable for a microsatellite.
The technical scheme adopted by the invention for solving the technical problems is as follows:
the one-way impact isolation device suitable for the microsatellite is used for being installed between a satellite bottom plate and a satellite main frame, and comprises a first structural plate, a second structural plate, an impact isolation pad and screws, wherein the screws comprise screw heads and screw rods, the impact isolation pad and the screws are plural, the first structural plate and the second structural plate comprise bosses arranged on the lower surfaces of the first structural plate and the second structural plate, and the sum of the heights of the impact isolation pad and the screw heads is smaller than the height of the bosses; the satellite main frame is connected with the first structural plate through screws, the second structural plate is connected with the first structural plate through screws, and the satellite bottom plate is connected with the second structural plate through screws; a shock insulation pad is sleeved on a screw rod of a screw for connecting the first structural plate and the satellite main frame, and a shock insulation pad is sleeved between the screw head and the first structural plate and between the first structural plate and the satellite main frame; a shock insulation pad is sleeved on a screw rod of a screw for connecting the second structural plate and the first structural plate, and a shock insulation pad is sleeved between the screw head and the second structural plate and between the second structural plate and the first structural plate; and a shock insulation pad is sleeved between the screw head and the satellite bottom plate and between the satellite bottom plate and the structural plate II on the screw rod of the screw for connecting the satellite bottom plate and the structural plate II.
Further, through holes are formed in the first structural plate and the second structural plate, and the first structural plate penetrates through the through holes in the first structural plate through screws to be connected with the satellite main frame; the second structural plate is connected with the boss of the first structural plate through a through hole on the second structural plate.
Further, screw holes are formed in the boss of the first structural plate and the boss of the second structural plate, the second structural plate is connected with the first structural plate through screw fit screw holes, and the satellite bottom plate is connected with the second structural plate through screw fit screw holes.
Further, the material of the shock-absorbing pad is nitrile rubber, polyurethane or metal rubber.
Further, the first structural plate and the second structural plate are made of 2A12 aluminum alloy.
The method for using the unidirectional impact isolation device suitable for the microsatellite comprises the steps of installing and fixing a first structural plate on a satellite main frame after the satellite main frame is assembled and vertically overturned, installing and fixing a second structural plate on the first structural plate, installing and fixing a satellite bottom plate on the second structural plate, and finally vertically overturned the installed satellite main frame, the first structural plate, the second structural plate 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 shock absorber can play a role in isolating impact in the longitudinal direction of the microsatellite through the combined action of the shock absorber on the first structural plate, the shock absorber on the upper and lower structural plates, the shock absorber on the second structural plate and the shock absorber on the bottom plate of the satellite, can effectively isolate and absorb impact load generated when initiating explosive devices such as explosion bolts and the like explode, has higher shock isolation efficiency, and enables the impact load reaching a single machine installation point to meet the use index of the 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 the emission of the microsatellite.
2. The original satellite bottom plate and the satellite main frame can be reliably connected through the first structural plate and the second structural plate, so that the strength and rigidity of the whole satellite of the microsatellite are ensured, and the sine and random response, especially the random response, of the whole satellite can be greatly reduced while the whole satellite is isolated; 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 unidirectional 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 one-way impact isolation device suitable for a microsatellite according to the present invention.
Fig. 2 is a schematic structural view of a unidirectional impact isolation device suitable for a microsatellite according to the present invention.
Fig. 3 is an enlarged view of the invention at a in fig. 2.
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. a first structural plate, a second structural plate, a third structural plate, a satellite main frame, a fourth structural plate and a satellite bottom plate, 5, a shock-proof pad, 6, a screw, 6.1, a screw head, 6.2, a screw rod, 7 and a boss.
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.
It should be noted that all directional indicators (such as up, down, left, right, front, and rear … …) in the embodiments of the present invention are merely used to explain the relative positional relationship, movement, etc. between the components in a particular posture (as shown in the drawings), and if the particular posture is changed, the directional indicator is changed accordingly.
In the present invention, the terms "coupled," "fixed," and the like are to be construed broadly unless otherwise specifically indicated and defined. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.
A unidirectional impact isolation device suitable for microsatellites is arranged between a satellite bottom plate 4 and a satellite main frame 3, and comprises a first structural plate 1, a second structural plate 2, an impact isolation pad 5 and screws 6. As shown in fig. 1 to 3, fig. 2 is a connection diagram of a first structural plate 1 and a second structural plate 2 in fig. 1, and fig. 3 is an enlarged diagram at a in fig. 2. The screw 6 comprises a screw head 6.1 and a screw shaft 6.2. The number of the shock-absorbing pad 5 is plural, and the number of the screw 6 is plural. The first structural plate 1 includes a boss 7 provided on a lower surface thereof, and the second structural plate 2 includes a boss 7 provided on a lower surface thereof. The satellite main frame 3, the first structural plate 1, the second structural plate 2 and the satellite bottom plate 4 are sequentially connected from top to bottom through screws 6, specifically, the satellite main frame 3 is connected with the first structural plate 1 through screws 6, the second structural plate 2 is connected with a boss 7 of the first structural plate 1 through screws 6, and the satellite bottom plate 4 is connected with a boss 7 of the second structural plate 2 through screws 6, wherein the above-mentioned "top from top" is defined as the upper part of fig. 1. On the screw rod 6.2 of the screw 6 connecting the first structural plate 1 and the satellite main frame 3, two isolating impact pads 5 are sleeved at two positions, namely, between the screw head 6.1 and the first structural plate 1 and between the first structural plate 1 and the satellite main frame 3. On the screw rod 6.2 of the screw 6 connecting the structural plate two 2 and the structural plate one 1, two isolating impact pads 5 are sleeved at two positions, namely between the screw head 6.1 and the structural plate two 2 and between the structural plate two 2 and the structural plate one 1 respectively. On the screw rod 6.2 of the screw 6 connecting the satellite bottom plate 4 and the structural plate two 2, two isolating impact pads 5 are sleeved at two positions, namely between the screw head 6.1 and the satellite bottom plate 4 and between the satellite bottom plate 4 and the structural plate two 2. The sum of the heights of the spacer 5 and the screw heads 6.1 is smaller than the height of the boss 7, namely, the screws 6 on the first structural plate 1 do not contact the second structural plate 2, and the screws 6 on the second structural plate 2 do not contact the satellite bottom plate 4.
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 form in a structure, impact response is attenuated rapidly along with the increase of propagation distance or through a connecting link, and the unidirectional impact isolation device suitable for microsatellites is provided. Through the combined action of the first structural plate 1, the upper and lower shock insulation pads 5 of the first structural plate 1, the second structural plate 2, the shock insulation pads 5 on the second structural plate 2 and the shock insulation pads 5 on the satellite bottom plate 4, the shock insulation effect can be achieved in the longitudinal direction of the microsatellite. The unidirectional 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 which reaches 61.7%, and ensures that the impact load reaching a single machine installation point meets the use index of a single machine, thereby solving the problem that the initiating explosive devices explode to damage precise electronic equipment in a satellite and ensuring the safety of micro satellite emission.
The unidirectional 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 plates 1 and 2, ensure the strength and rigidity of the whole satellite, and can greatly reduce the sine and random response, especially the random response, of the whole satellite while isolating impact; the safety of the microsatellite under the severe transmitting section environment is ensured.
The unidirectional 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 unidirectional 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 previous 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 unidirectional impact isolation device suitable for a microsatellite, which is simple and easy to operate, and comprises the following specific processes: after the satellite main frame 3 is assembled, the satellite main frame 3 is turned over, a layer of shock insulation pads 5 are respectively placed on the upper and lower corresponding positions of the connection part of the first structural plate 1 and the satellite main frame 3, the shock insulation pads 5 on the lower surface of the first structural plate 1, the first structural plate 1 and the shock insulation pads 5 on the upper surface of the first structural plate 1 and the satellite main frame 3 are sequentially penetrated by bolts 6, the first structural plate 1 and the satellite main frame 3 are connected and fastened, and the problem that the shock insulation pads 5 are very easy to fall off due to small size in the assembling process of the step is solved, and the assembling process is very careful; a layer of shock insulation pad 5 is respectively arranged on the upper and lower corresponding positions of the connection part of the structural plate II 2 and the structural plate I1, the shock insulation pad 5 and the structural plate II 2 on the lower surface of the structural plate II 2 are sequentially penetrated by bolts 6, and the shock insulation pad 5 and the structural plate I1 on the upper surface of the structural plate II 2 are fixedly connected with the structural plate II 2 and the structural plate I1; a layer of shock insulation pad 5 is respectively arranged on the satellite bottom plate 4 and at the corresponding upper and lower positions of the joint of the satellite bottom plate 4 and the structural plate II 2, the shock insulation pad 5 on the lower surface of the satellite bottom plate 4, the shock insulation pad 5 on the upper surface of the satellite bottom plate 4 and the structural plate II 2 are sequentially penetrated by bolts 6, and the satellite bottom plate 4 is fixedly connected with the structural plate II 2 by bolts 6; the whole (satellite main frame 3, structural plate 1, structural plate 2 and satellite bottom plate 4) is finally turned over vertically.
The length of the structural plate I and the length of the structural plate II are 266mm, the width of the structural plate I and the structural plate II are 220mm, the height of the structural plate I and the structural plate II are 33mm, and the structural plates I and the structural plate II can be modified according to the weight of a satellite and the change of envelope dimensions. The materials used for the structural plate I and the structural plate II are 2A12 aluminum alloy, and structural optimization and light weight treatment are carried out according to the whole star response and the fundamental frequency. The first and second structure plates 2 may be modified according to the weight of the satellite and the envelope size. Through holes are formed in the first structural plate 1 and the second structural plate 2, and the first structural plate 1 is connected with the satellite main frame 3 through the through holes in the first structural plate 1 by screws 6. The second structural plate 2 is connected with the boss 7 of the first structural plate 1 through the through hole on the second structural plate 2 by the screw 6. The first structural plate 1 and the second structural plate 2 specifically may each include a flat plate, a through hole and a boss 7, the flat plate is provided with the through hole, the through hole is provided in a place of the non-boss 7 on the flat plate, and the impact pad 5 is arranged corresponding to the through hole, i.e. above and below the through hole. Be equipped with the screw hole on the boss 7 of structural slab 1, be equipped with the screw hole on the boss 7 of structural slab 2, structural slab 2 passes through screw 6 cooperation screw hole and connects structural slab 1, and satellite bottom plate 4 passes through screw 6 cooperation screw hole and connects structural slab 2. In this embodiment, the first structural plate 1 has 13 through holes and 11 bosses 7, the second structural plate 2 has 11 through holes and 13 bosses 7,
the unidirectional impact isolation device suitable for the microsatellite is not limited to the quantity of the impact isolation pads 5 and the type of the impact isolation pads 5, and the impact isolation pads 5 in the embodiment are made of metal rubber materials, so that demagnetizing treatment is needed during use. The shock-absorbing cushion 5 can also be made of other types of space rubber such as nitrile rubber or damping shock-absorbing materials such as polyurethane which can ensure the strength and rigidity of the whole star. The spacer 5 may be modified according to the satellite weight and envelope size variations.
By taking a micro-nano satellite ground 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 longitudinal impact response can be remarkably reduced by adopting the unidirectional impact isolation device suitable for the microsatellite, and the impact isolation efficiency can reach about 61.7%. The Log representation in fig. 4 and 5 shows that the impulse response spectrum shown in the graph is generated logarithmically, X represents the transverse direction and Y represents the longitudinal direction.
Claims (5)
1. A unidirectional impact isolation device suitable for microsatellites, which is used for being installed between a satellite bottom plate (4) and a satellite main frame (3), and is characterized by comprising a first structural plate (1), a second structural plate (2), an impact isolation pad (5) and screws (6), wherein the screws (6) comprise screw heads (6.1) and screw rods (6.2), the impact isolation pad (5) and the screws (6) are plural, the first structural plate (1) and the second structural plate (2) comprise bosses (7) arranged on the lower surfaces of the first structural plate and the second structural plate, and the sum of the heights of the impact isolation pad (5) and the screw heads (6.1) is smaller than the height of the bosses (7); the satellite main frame (3) is connected with a screw (6) of the first structural plate (1), the second structural plate (2) is connected with a screw (6) of a boss (7) of the first structural plate (1), and the satellite bottom plate (4) is connected with the screw (6) of the boss (7) of the second structural plate (2); a shock insulation pad (5) is sleeved between the screw head (6.1) and the first structural plate (1) and between the first structural plate (1) and the satellite main frame (3) on a screw rod (6.2) for connecting the first structural plate (1) and a screw (6) of the satellite main frame (3); a shock insulation pad (5) is sleeved between the screw head (6.1) and the structural plate II (2) and between the structural plate II (2) and the structural plate I (1) on the screw rod (6.2) of the screw (6) for connecting the structural plate II (2) and the structural plate I (1); a shock insulation pad (5) is sleeved between the screw head (6.1) and the satellite bottom plate (4) and between the satellite bottom plate (4) and the structural plate II (2) on the screw rod (6.2) of the screw (6) for connecting the satellite bottom plate (4) and the structural plate II (2);
the application method of the unidirectional impact isolation device suitable for the microsatellite comprises the following steps: after the satellite main frame (3) is assembled and vertically overturned, the first structural plate (1) is installed and fixed on the satellite main frame (3), the second structural plate (2) is installed and fixed on the first structural plate (1), the satellite bottom plate (4) is installed and fixed on the second structural plate (2), and finally the installed satellite main frame (3), the first structural plate (1), the second structural plate (2) and the satellite bottom plate (4) are vertically overturned at the same time.
2. A unidirectional impact isolation device suitable for microsatellites as claimed in claim 1, wherein the first structural plate (1) and the second structural plate (2) are respectively provided with a through hole, and the first structural plate (1) is connected with a satellite main frame (3) by penetrating a screw (6) through the through holes on the first structural plate (1); the second structural plate (2) is connected with the boss (7) of the first structural plate (1) through the through hole on the second structural plate (2) by the screw (6).
3. A unidirectional impact isolation device suitable for a microsatellite according to claim 1, wherein threaded holes are formed in the boss (7) of the first structural plate (1) and the boss (7) of the second structural plate (2), the second structural plate (2) is connected with the first structural plate (1) through the screw (6) matched with the threaded holes, and the satellite bottom plate (4) is connected with the second structural plate (2) through the screw (6) matched with the threaded holes.
4. A unidirectional impact isolation apparatus for microsatellites as claimed in claim 1, wherein said impact pad (5) is made of nitrile rubber, polyurethane or metal rubber.
5. A unidirectional impact isolation apparatus for a microsatellite according to claim 1 wherein said first structural plate (1) and said second structural plate (2) are each made of a 2a12 aluminum alloy.
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| CN201811208406.3A CN109178347B (en) | 2018-10-17 | 2018-10-17 | Unidirectional impact isolation device suitable for microsatellite |
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| CN201811208406.3A CN109178347B (en) | 2018-10-17 | 2018-10-17 | Unidirectional impact isolation device suitable for microsatellite |
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| CN109178347B true CN109178347B (en) | 2023-08-29 |
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| CN112407342B (en) * | 2020-11-06 | 2022-03-04 | 北京宇航系统工程研究所 | Expansion pipe recess board isolating construction |
| CN114352674A (en) * | 2021-02-08 | 2022-04-15 | 北京强度环境研究所 | Three-dimensional space lattice structure all-metal buffer |
| CN114291304B (en) * | 2021-12-31 | 2022-11-18 | 北京国电高科科技有限公司 | One-way impact isolation device suitable for microsatellite |
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| CN104290927A (en) * | 2014-09-12 | 2015-01-21 | 上海卫星工程研究所 | One-way impact isolating device for satellite |
| CN105909714A (en) * | 2016-04-19 | 2016-08-31 | 长光卫星技术有限公司 | Impact damping device suitable for unfolding of solar panel substrate |
| CN106246800A (en) * | 2016-08-12 | 2016-12-21 | 上海卫星工程研究所 | For the priming system of satellite antenna development mechanism every flushing device |
| CN209097035U (en) * | 2018-10-17 | 2019-07-12 | 长光卫星技术有限公司 | A kind of unidirectional shock isolating apparatus suitable for microsatellite |
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| CN109178347A (en) | 2019-01-11 |
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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 unidirectional shock isolation device suitable for small satellites Granted publication date: 20230829 Pledgee: Jilin credit financing guarantee Investment Group Co.,Ltd. Pledgor: Changguang Satellite Technology Co.,Ltd. Registration number: Y2024220000032 |