CN114291304A - One-way impact isolation device suitable for microsatellite - Google Patents
One-way impact isolation device suitable for microsatellite Download PDFInfo
- Publication number
- CN114291304A CN114291304A CN202111679185.XA CN202111679185A CN114291304A CN 114291304 A CN114291304 A CN 114291304A CN 202111679185 A CN202111679185 A CN 202111679185A CN 114291304 A CN114291304 A CN 114291304A
- Authority
- CN
- China
- Prior art keywords
- plate
- substrate
- seat
- positioning seat
- lower substrate
- 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.)
- Granted
Links
Images
Landscapes
- Vibration Dampers (AREA)
Abstract
The utility model relates to an aircraft subtracts the field of impact equipment, a one-way impact isolating device suitable for microsatellite is disclosed, it includes the infrabasal plate, the locating plate is installed to the upper end of base plate under, install the upper substrate in the upper end of locating plate, install a bolster in the upper end of upper substrate, install the mounting panel in the upper end of a bolster, install on the base plate down and run through the infrabasal plate, the locating plate, and the connecting piece of upper substrate, be provided with the end connecting seat in the connecting piece lower part, the lower part of base plate is provided with energy-absorbing mechanism down. This application has and effectively improves current buffering isolating device structural design simply, keeps apart the effect of the poor problem of effect to the buffering of impulsive force.
Description
Technical Field
The application relates to the field of aircraft shock absorption equipment, in particular to a one-way shock isolation device suitable for a microsatellite.
Background
The microsatellite refers to an artificial satellite with the weight of less than 1000 kg, and compared with the prior large satellite, the microsatellite has many advantages, such as light weight, small volume and low production cost due to batch production; the small rocket can be used for launching or used as an auxiliary load of a large rocket, so that the launching cost is low; can be launched from fighters and even balloons or launched by using land and water surface artillery, and can meet the requirement of quick response.
At present, a microsatellite is installed on a fixed main frame, the main frame is installed on a buffering and isolating device, the buffering and isolating device is connected with a satellite substrate through a bottom installation structure, the satellite substrate is connected through an explosion bolt when being installed, the explosion bolt is directly detonated when the satellite and a rocket are required to be separated, the connection part is damaged, the impact force generated by explosion is weakened through the buffering and isolating device, and the damage to the satellite structure is avoided.
In view of the above-mentioned related technologies, the inventor considers that the existing buffer isolation device has a simple structural design, insufficient structural strength and is easy to deform, and only relies on the direct contact between the plate-shaped structure and the buffer material, and the impact force generated by explosion is weakened by the elastic force of the buffer material, so that the buffer isolation effect on the impact force is poor.
Disclosure of Invention
In order to effectively improve current buffering isolating device structural design simply, to the poor problem of effect of buffering isolation of impulsive force, this application provides a one-way impact isolating device suitable for microsatellite.
The application provides a one-way impact isolation device suitable for microsatellite adopts following technical scheme:
the utility model provides a one-way impact isolating device suitable for microsatellite, includes the infrabasal plate, installs the locating plate in the upper end of lower base plate, installs the upper substrate in the upper end of locating plate, installs top bolster in the upper end of upper substrate, installs the mounting panel in the upper end of top bolster, installs the connecting piece that runs through infrabasal plate, locating plate to and upper substrate on the lower base plate, is provided with the bottom joint seat in the connecting piece lower part, is provided with energy-absorbing mechanism in the lower part of lower base plate.
By adopting the technical scheme, the satellite is arranged on the main frame, then the main frame is arranged on the mounting plate, then the device, the main frame and the satellite are arranged on the satellite substrate through the bottom connecting seat, and the satellite substrate is connected with the rocket through the explosive bolts; when the satellite needs to be separated from the rocket after being launched, the explosive bolt is detonated, the explosive impact force is transmitted to the device from the satellite substrate, the impact force is absorbed and weakened by the energy absorption mechanism when being transmitted to the energy absorption mechanism, then is transmitted to the lower substrate, the positioning plate and the upper substrate, the lower substrate, the positioning plate and the upper substrate are stably connected under the action of the connecting piece, stable support for the upper structure is guaranteed, then the impact force is transmitted to the top buffering piece, the top buffering piece performs third weakening absorption on the impact force, the impact force finally transmitted to the mounting plate is greatly weakened, and the possibility of damage of the satellite can be effectively reduced.
Optionally, the energy absorbing mechanism includes a top plate installed at a lower portion of the lower substrate, a honeycomb plate is installed at a lower portion of the lower substrate, a bottom plate is installed at a lower portion of the honeycomb plate, and a cushion pad is installed at a lower portion of the bottom plate.
By adopting the technical scheme, when the impact force is transmitted to the energy absorption mechanism, the impact force is sequentially transmitted to the cushion pad, the bottom plate and the honeycomb plate and is transmitted to the lower substrate after being weakened for three times, and the possibility of satellite damage can be further reduced by weakening for three times; the cellular board is core column structure, and this structure has excellent resistance to compression function and buffering vibration isolation function, and the impact force that the weakening that can be fine comes from the explosion bolt, and the cellular board has the advantage that matter is light simultaneously, can effectively alleviate the weight of device, is favorable to the satellite transmission more.
Optionally, one side of the positioning plate is connected with the upper substrate, the other side of the positioning plate is connected with the lower substrate, and the plurality of positioning plates are equidistantly distributed between the upper substrate and the lower substrate.
Through adopting above-mentioned technical scheme, the locating plate is the installation basis of device, can guarantee the overall structure intensity of device to keep out the impact force that comes from the explosion bolt, and guarantee that the installation of satellite is stable.
Optionally, a supporting seat is arranged at a corner of the surface of the lower substrate departing from the positioning plate, a through lower substrate and a locking bolt of the upper substrate are installed on the supporting seat in a penetrating mode, the top end of the locking bolt is in threaded connection with the top buffering piece, and a contact pad is fixedly installed at the bottom end of the locking bolt.
By adopting the technical scheme, the locking bolt can further enhance the stability of the device, enhance the resistance of the device to the impact force from the explosive bolt, further weaken the impact force, reduce the influence of the impact force on the satellite and enable the satellite to be more stable; the supporting seat can weaken part of impact force while supporting the device, and further reduces the influence of the impact force on the satellite.
Optionally, the bottom surface of the buffer pad, the bottom surface of the bottom connection seat, and the bottom surface of the contact pad are located on the same horizontal plane.
By adopting the technical scheme, the device is more stable when being connected with the rocket; after the explosion of the explosion bolt, the impact force from the explosion bolt can be uniformly transmitted to each buffer mechanism on the same plane, so that the stability of the device in the process of transmitting the impact force is ensured, and the stability of the satellite is further ensured.
Optionally, an isolation pad is disposed between the bottom connection seat and the lower substrate.
Through adopting above-mentioned technical scheme, the isolation pad can strengthen being connected between connecting piece and the infrabasal plate, and the isolation pad has the cushioning effect simultaneously, can weaken partial impact force, reduces the impact force to the influence of satellite.
Optionally, the connecting piece adopts a connecting bolt;
the top buffer piece adopts a first top buffer plate, the first top buffer plate adopts a microporous aluminum plate, a first upper positioning seat with a T-shaped cross section is integrally formed inside the first top buffer plate, the first upper positioning seat comprises a cavity plate arranged in parallel with the first top buffer plate, and a sleeve arranged on one side of the cavity plate and matched with the connecting bolt.
By adopting the technical scheme, the lower substrate, the upper substrate and the first buffer plate are connected by the connecting bolts, so that the device is more stable; the first top buffer plate is a microporous aluminum plate which is light in weight and high in structural strength, the overall weight of the satellite can be reduced, the micropores can be utilized to absorb noise while the first top buffer plate normally plays a supporting role, resonance of the whole device caused by huge noise generated when a rocket is launched is avoided, the porous structure design and the honeycomb design principle are the same, and the first top buffer plate has good sound insulation, vibration reduction and explosion impact resistance; simultaneously, the micropore aluminum plate is combined with the cavity plate, so that a cavity resonance sound absorption structure can be formed, the noise generated when the explosion bolt explodes is reduced, and the influence of the explosion on a satellite and a rocket is reduced.
Optionally, the connecting piece is a connecting rod, and a thread is formed in the middle of the connecting rod in a machining mode;
the buffering top piece adopts a second top buffer plate with a cavity, a second upper positioning seat matched with the connecting rod is arranged in the cavity of the second top buffer plate, a second spring is arranged in the second upper positioning seat, one end of the second spring is connected with the top end of the connecting rod, and the other end of the second spring is connected with the second upper positioning seat;
two ejector rods are respectively rotatably connected to two sides of the second upper positioning seat, a sliding block is rotatably connected to the other end of each ejector rod, a baffle is further arranged in the second ejector buffer plate, and the baffle is arranged on one side, away from the second upper positioning seat, of the sliding block.
By adopting the technical scheme, when the explosive bolt explodes to generate impact force, the connecting rods compress the second spring and transmit the impact force to the second upper positioning seat, part of the impact force applied to the second upper positioning seat is transmitted to the two connecting rods through the second upper positioning seat, one end of each connecting rod connected with the second upper positioning seat rotates to enable the sliding block to move, and the baffle can block the sliding block and weaken the impact force on the sliding block again; through the second spring to and two sliders, will come from the impact force dispersion of connecting rod, effectively strengthen the bradyseism ability of device.
Optionally, a slide way for the sliding block to slide is arranged on the second top buffer plate;
a first spring is arranged between the baffle and the sliding block, one end of the first spring is connected with the baffle, and the other end of the first spring is connected with the sliding block.
By adopting the technical scheme, the slide way can limit the sliding direction of the slide block, so that the slide block can slide more stably; simultaneously, the first spring can further weaken impact force, enhance the cushioning capacity of the device and reduce the influence of the impact force on the satellite.
Optionally, the cross section of the second upper positioning seat is T-shaped, and the outer plate surface of the closed end of the second upper positioning seat is coplanar with the plate surface of the second top buffer plate.
Through adopting above-mentioned technical scheme, the area of contact of positioning seat and mounting panel on the T style of calligraphy can strengthen the second reduces because the impact force is too concentrated and the possibility of destroying the mounting panel, and then effectively protects the satellite.
In summary, the present application includes at least one of the following beneficial technical effects:
through the arrangement of the lower base plate, the positioning plate, the upper base plate, the top buffer piece, the mounting plate, the energy absorption mechanism, the connecting piece and the bottom connecting seat, impact force is weakened and absorbed for three times, and finally the impact force transmitted to the mounting plate is greatly weakened, so that the possibility of damage of a satellite can be effectively reduced;
by arranging the top plate, the honeycomb plate and the cushion pad, the possibility of satellite damage can be further reduced by three times of weakening;
through setting up polylith locating plate interval equidistance and distributing between upper substrate and infrabasal plate, can guarantee the overall structure intensity of device to keep out the impact force that comes from the explosion bolt, and guarantee that the installation of satellite is stable.
Drawings
Fig. 1 is a cross-sectional view of a first embodiment of the present application.
FIG. 2 is a partial schematic view of an energy absorbing mechanism.
Fig. 3 is a bottom view of the first embodiment of the present application.
Fig. 4 is a partial structural schematic diagram of the second embodiment of the present application.
Description of reference numerals: 1. a lower substrate; 11. a supporting seat; 2. positioning a plate; 3. an upper substrate; 31. mounting a plate; 32. locking the bolt; 33. a contact pad; 4. an energy absorbing mechanism; 41. a top plate; 42. a honeycomb panel; 43. a base plate; 44. a cushion pad; 5. a top buffer; 51. a first top baffle plate; 52. a second top baffle plate; 521. a slideway; 522. a baffle plate; 523. a first spring; 6. a connecting member; 61. a connecting bolt; 62. a connecting rod; 7. an insulating pad; 8. a bottom connection seat; 9. an upper positioning member; 91. a first upper positioning seat; 911. a cavity plate; 912. a sleeve; 92. a second upper positioning seat; 921. a second spring; 922. a top rod; 923. a slide block.
Detailed Description
The present application is described in further detail below with reference to figures 1-4.
The embodiment of the application discloses a one-way impact isolation device suitable for a microsatellite.
The first embodiment is as follows:
referring to fig. 1 and 2, a unidirectional impact isolator for a microsatellite includes a base plate, a positioning plate 2 disposed on an upper portion of a lower base plate 1, an upper base plate 3 disposed on an upper portion of the positioning plate 2, a top cushion 5 disposed on an upper portion of the upper base plate 3, a mounting plate 31 disposed on an upper portion of the top cushion 5, an energy absorbing mechanism 4 disposed on a lower portion of the lower base plate 1, and a connecting member 6.
The locating plate 2 inclines and is provided with the polylith, and one side of every locating plate 2 is connected on the face of infrabasal plate 1, and the opposite side is connected on the face of upper substrate 3, and every two locating plates 2 constitute and are 2 groups of "V" style of calligraphy locating plate, and the opening of "V" style of calligraphy is towards infrabasal plate 1, and 2 groups of interval equidistance distribution of multiunit locating plate are between infrabasal plate 1 and upper substrate 3. The lower substrate 1, the positioning plate 2 and the upper substrate 3 are the installation basis of the device, and can reduce the deformation of the device under the impact of explosion.
Referring to fig. 1 and 3, a bottom connector base 8 is further disposed at a lower portion of the lower substrate 1, in this embodiment, a connecting bolt 61 is used as the connecting member 6, a bottom end of the connecting bolt 61 is connected to the bottom connector base 8, and a spacer 7 is disposed between the bottom connector base 8 and the lower substrate 1. The top cushion 5 adopts a first top cushion plate 51, and the connecting bolt 61 sequentially penetrates through the isolation pad 7, the lower substrate 1, the positioning plate 2, the upper substrate 3, and the first top cushion plate 51.
An upper positioning member 9 is integrally formed in the first top buffer plate 51, in this embodiment, the upper positioning member 9 is a first upper positioning seat 91, a cross-sectional view of the first upper positioning seat 91 is a "T" shape, the first upper positioning seat 91 includes a cavity plate 911 with a plate surface facing the plate surface supply surface of the upper substrate 3 and the mounting plate 31, and a sleeve 912, and a thread matched with the connecting bolt 61 is formed on an inner wall of the sleeve 912 through machining.
With reference to fig. 1 and 3, the upper substrate 3, the positioning plate 2, and the upper substrate 3 are all made of solid aviation aluminum plates, and the solid aviation aluminum plates have the excellent characteristics of high strength and strong corrosion resistance. The thickness of first top buffer board 51 is greater than the thickness of mounting panel 31 for first top buffer board 51 can effectively absorb the explosion impact force, also makes mounting panel 31 provide stable installation basis for the satellite simultaneously. First top buffer board 51 adopts micropore aluminum plate, and mounting panel 31 adopts high-speed steel board, consequently has the space when the installation between first top buffer board 51 and the mounting panel 31, because the expansion coefficient of aluminium is greater than the expansion coefficient of high-speed steel, the space can prevent to make overall structure warp because expend with heat and contract with cold, influences the security of satellite.
The microporous aluminum plate is light in weight and high in structural strength, the overall weight of the satellite can be reduced, the micropores can be utilized to absorb noise while the supporting effect is normally achieved, resonance of the whole device caused by huge noise generated when a rocket is launched is avoided, the porous structural design and the honeycomb design principle are the same, the microporous aluminum plate has good sound insulation, vibration reduction and explosion impact resistance, and the cavity plate 911 and the first top buffer plate 51 are combined for use, so that a cavity resonance sound absorption structure can be formed; the high-speed steel sheet has excellent properties of high strength, high wear resistance, and high heat resistance.
With reference to fig. 1 and 3, a supporting seat 11 is further disposed at a corner of a lower portion of the lower substrate 1, a locking bolt 32 penetrating through the lower substrate 1, the upper substrate 3, and the first buffer top plate 41 is further mounted on the supporting seat 11 in a penetrating manner, and one end of the locking bolt 32 far away from the supporting seat 11 is in threaded connection with the first top buffer plate 51. A contact pad 33 is mounted on the bottom of the lock bolt 32 near one end of the support base 11.
Referring to fig. 1 and 2, the energy absorbing mechanism 4 includes a top plate 41 attached to the lower substrate 1, a honeycomb plate 42 fixedly attached to a lower portion of the top plate 41, a bottom plate 43 fixedly attached to a lower portion of the honeycomb plate 42, and a cushion pad 44 disposed below the bottom plate 43.
The bottom surface of blotter 44, the bottom surface of bottom joint seat 8 and the bottom surface of contact pad 33 are in same horizontal plane, and blotter 44, and contact pad 33 all adopt butadiene acrylonitrile rubber to make, and butadiene acrylonitrile rubber has the excellent characteristics of oil resistance fabulous, the wearability is higher, and the heat resistance is better, and the adhesion is strong.
The implementation principle of the one-way impact isolation device suitable for the microsatellite in the embodiment of the application is as follows: when the device is used, the top ends of the connecting bolts 61 are locked through the first upper positioning seat 91, the lower substrate 1, the upper substrate 3 and the first top buffer plate 51 are locked through the locking bolts 32, then the mounting plate 31 is fixedly welded on the upper end surface of the top buffer plate, then the device is mounted on a satellite substrate through the bottom connecting seat 8, the satellite substrate is connected with a rocket through the explosive bolts, the satellite is mounted on a main frame, and the main frame is fixedly mounted on the mounting plate 31 to complete integral mounting; when the satellite and the rocket need to be separated after the satellite is launched, the explosion bolt is detonated, the impact force generated by explosion is transmitted to the device from the satellite substrate, the impact force is absorbed and weakened once when reaching the cushion pad 44 and the contact pad 33, the isolation pad 7 also weakens the impact force transmitted to the connecting bolt 61 through the bottom connecting seat 8, then the impact force is continuously transmitted to the top plate 41, the honeycomb plate 42 and the bottom plate 43 upwards and is weakened by secondary energy absorption of the honeycomb structure, then the impact force is transmitted upwards to the lower base plate 1, the positioning plate 2 and the upper base plate 3, the lower base plate 1, the positioning plate 2 and the upper base plate 3 have stable structures, the stable support of the upper structure is ensured, then, the impact force is transmitted to the first top buffer plate 51, the first top buffer plate 51 performs third weakening and absorption on the impact force, and the impact force finally transmitted to the mounting plate 31 is greatly weakened, so that the satellite is not damaged.
Example two:
the difference between this embodiment and the first embodiment is: referring to fig. 4, the connecting member 6 employs a connecting rod 62, the top bumper 5 employs a second top bumper plate 52, and the upper positioning member 9 employs a second upper positioning seat 92. One end of the connecting rod 62 is installed on the bottom connection seat 8, and the connecting rod 62 sequentially passes through the isolation pad 7, the lower substrate 1, the upper substrate 3 and the second top buffer plate 52.
A thread is formed at the middle position of the outer peripheral surface of the tie bar 62 to prevent the tie bar 62 from coming off from the upper base plate 3, which causes a safety hazard. The second top cushion plate 52 is a cavity plate 911, and the second upper positioning seat 92 is integrally formed inside the second top cushion plate 52. The second upper positioning seat 92 is shaped like a "T", the inside of the second upper positioning seat 92 is a cavity, one end of the second upper positioning seat is a closed end, and the plate surface of the closed end of the second upper positioning seat 92 is coplanar with the plate surface of the second top buffer plate 52. A second spring 921 is arranged inside the second upper positioning seat 92, one end of the second spring 921 is connected with the inner end face of the second upper positioning seat 92 close to the mounting plate 31, and the other end is connected with the end face of the top end of the connecting rod 62.
Referring to fig. 4, two push rods 922 are respectively disposed on two sides of the second upper positioning seat 92, one end of each push rod 922 is hinged to the outer circumferential surface of the second upper positioning seat 92, and a slider 923 is hinged to the other end of each push rod 922. The inner plate surface of the second top buffer plate 52 close to the mounting plate 31 is provided with a slide rail 521 adapted to the slide block 923. One end of the slide 521 abuts against the outer surface of the second upper positioning seat 92, and a stopper 522 is provided at the other end of the slide 521. A first spring 523 is arranged in the slideway 521, one end of the first spring 523 is connected with the baffle 522, and the other end is connected with the sliding block 923.
The implementation principle of the one-way impact isolation device suitable for the microsatellite in the embodiment of the application is as follows: after the explosion bolt explosion, the impact force transmits to connecting rod 62 department, then the impact force by being transmitted to the second on setting element 9 department, the impact force is dispersed to second spring 921, and two slider 923 departments, second spring 921, and slider 923 weaken the impact force and can be with the even transmission of remaining impact force to mounting panel 31 department simultaneously, make the atress of mounting panel 31 department more even, and then strengthen the satellite stability, slider 923 can pass through the impact force transmission to second spring 921 department simultaneously, weaken once more.
The above embodiments are preferred embodiments of the present application, and the protection scope of the present application is not limited by the above embodiments, so: all equivalent changes made according to the structure, shape and principle of the present application shall be covered by the protection scope of the present application.
Claims (10)
1. The utility model provides a one-way impact isolating device suitable for microsatellite which characterized in that: the energy-absorbing mechanism comprises a lower substrate (1), a positioning plate (2) is installed at the upper end of the lower substrate (1), an upper substrate (3) is installed at the upper end of the positioning plate (2), a top buffer piece (5) is installed at the upper end of the upper substrate (3), a mounting plate (31) is installed at the upper end of the top buffer piece (5), the lower substrate (1) is provided with a connecting piece (6) penetrating through the lower substrate (1), the positioning plate (2) and the upper substrate (3), a bottom connecting seat (8) is arranged at the lower part of the connecting piece (6), and an energy-absorbing mechanism (4) is arranged at the lower part of the lower substrate (1).
2. A unidirectional shock isolation apparatus for microsatellites according to claim 1 wherein: the energy absorption mechanism (4) comprises a top plate (41) arranged at the lower part of the lower substrate (1), a honeycomb plate (42) is arranged at the lower part of the lower substrate (1), a bottom plate (43) is arranged at the lower part of the honeycomb plate (42), and a cushion pad (44) is arranged at the lower part of the bottom plate (43).
3. A unidirectional shock isolation apparatus for microsatellites according to claim 2 wherein: one side of the positioning plate (2) is connected with the upper substrate (3), the other side of the positioning plate is connected with the lower substrate (1), and the plurality of positioning plates (2) are equidistantly distributed between the upper substrate (3) and the lower substrate (1) at intervals.
4. A unidirectional shock isolation apparatus for microsatellites according to claim 3 wherein: the corner that deviates from the face of locating plate (2) in lower base plate (1) is provided with supporting seat (11), runs through on supporting seat (11) to install and run through infrabasal plate (1) to and locking bolt (32) of upper substrate (3), the top and the top bolster (5) threaded connection of locking bolt (32), have contact pad (33) at the bottom fixed mounting of locking bolt (32).
5. A unidirectional shock isolation apparatus for microsatellites according to claim 4 wherein: the bottom surface of the cushion pad (44), the bottom surface of the bottom connection seat (8), and the bottom surface of the contact pad (33) are located on the same horizontal plane.
6. A unidirectional shock isolation apparatus for microsatellites according to claim 1 wherein: an isolation pad (7) is arranged between the bottom connecting seat (8) and the lower substrate (1).
7. A unidirectional shock isolation apparatus for microsatellites according to claim 1 wherein: the connecting piece (6) adopts a connecting bolt (61);
top bolster (5) adopt first top buffer board (51), and first top buffer board (51) adopt micropore aluminum plate, have the cross-section to be first positioning seat (91) of going up of "T" style of calligraphy in the inside integrated into one piece of first top buffer board (51), and first positioning seat (91) of going up include with first top buffer board (51) parallel arrangement's cavity board (911) to and set up sleeve pipe (912) in cavity board (911) one side and connecting bolt (61) adaptation.
8. A unidirectional shock isolation apparatus for microsatellites according to claim 1 wherein: the connecting piece (6) adopts a connecting rod (62), and a thread is formed in the middle of the connecting rod (62) in a machining mode;
the buffering top piece adopts a second top buffering plate (52) with a cavity, a second upper positioning seat (92) matched with the connecting rod (62) is arranged in the cavity of the second top buffering plate (52), a second spring (921) is arranged in the second upper positioning seat (92), one end of the second spring (921) is connected with the top end of the connecting rod (62), and the other end of the second spring is connected with the second upper positioning seat (92);
two ejector rods (922) are rotatably connected to two sides of the second upper positioning seat (92) respectively, a sliding block (923) is rotatably connected to the other end of each ejector rod (922), a baffle (522) is further arranged in the second top buffer plate (52), and the baffle (522) is arranged on one side, away from the second upper positioning seat (92), of the sliding block (923).
9. A unidirectional shock isolation apparatus for microsatellites according to claim 8 wherein: a slide way (521) for the sliding block (923) to slide is arranged on the second top buffer plate (52);
a first spring (523) is arranged between the baffle (522) and the sliding block (923), one end of the first spring (523) is connected with the baffle (522), and the other end of the first spring is connected with the sliding block (923).
10. A unidirectional shock isolation apparatus for microsatellites according to claim 8 wherein: the section of the second upper positioning seat (92) is T-shaped, and the outer plate surface of the closed end of the second upper positioning seat (92) is coplanar with the plate surface of the second top buffer plate (52).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111679185.XA CN114291304B (en) | 2021-12-31 | 2021-12-31 | One-way impact isolation device suitable for microsatellite |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111679185.XA CN114291304B (en) | 2021-12-31 | 2021-12-31 | One-way impact isolation device suitable for microsatellite |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114291304A true CN114291304A (en) | 2022-04-08 |
| CN114291304B CN114291304B (en) | 2022-11-18 |
Family
ID=80975263
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111679185.XA Active CN114291304B (en) | 2021-12-31 | 2021-12-31 | One-way impact isolation device suitable for microsatellite |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114291304B (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2895052A1 (en) * | 2005-12-21 | 2007-06-22 | Eads Astrium Sas Soc Par Actio | Vibration isolating device for e.g. gyrodyne type actuator, has isolation modules each comprising outer and inner rigid pieces that are connected by isolation plug whose traction-compression is limited by flexible stop |
| US20110283873A1 (en) * | 2007-08-16 | 2011-11-24 | University Of Virginia Patent Foundation | Hybrid Periodic Cellular Material Structures, Systems, and Methods For Blast and Ballistic Protection |
| RU2446081C1 (en) * | 2010-08-06 | 2012-03-27 | Открытое Акционерное Общество "Государственный Ракетный Центр Имени Академика В.П. Макеева" | Method rocket launching |
| CN104290927A (en) * | 2014-09-12 | 2015-01-21 | 上海卫星工程研究所 | One-way impact isolating device for satellite |
| CN104358814A (en) * | 2014-09-12 | 2015-02-18 | 上海卫星工程研究所 | Three-way shock isolation device for satellite |
| CN105083593A (en) * | 2015-08-21 | 2015-11-25 | 北京空间飞行器总体设计部 | Shock-resisting installation base for buffering and energy absorption of explosion of spacecraft pyrotechnic device |
| CN107776914A (en) * | 2017-10-16 | 2018-03-09 | 上海微小卫星工程中心 | Firer's impact damper system structure for satellite sun windsurfing |
| CN109178347A (en) * | 2018-10-17 | 2019-01-11 | 长光卫星技术有限公司 | A kind of unidirectional shock isolating apparatus suitable for microsatellite |
| 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 |
-
2021
- 2021-12-31 CN CN202111679185.XA patent/CN114291304B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2895052A1 (en) * | 2005-12-21 | 2007-06-22 | Eads Astrium Sas Soc Par Actio | Vibration isolating device for e.g. gyrodyne type actuator, has isolation modules each comprising outer and inner rigid pieces that are connected by isolation plug whose traction-compression is limited by flexible stop |
| US20110283873A1 (en) * | 2007-08-16 | 2011-11-24 | University Of Virginia Patent Foundation | Hybrid Periodic Cellular Material Structures, Systems, and Methods For Blast and Ballistic Protection |
| RU2446081C1 (en) * | 2010-08-06 | 2012-03-27 | Открытое Акционерное Общество "Государственный Ракетный Центр Имени Академика В.П. Макеева" | Method rocket launching |
| CN104290927A (en) * | 2014-09-12 | 2015-01-21 | 上海卫星工程研究所 | One-way impact isolating device for satellite |
| CN104358814A (en) * | 2014-09-12 | 2015-02-18 | 上海卫星工程研究所 | Three-way shock isolation device for satellite |
| CN105083593A (en) * | 2015-08-21 | 2015-11-25 | 北京空间飞行器总体设计部 | Shock-resisting installation base for buffering and energy absorption of explosion of spacecraft pyrotechnic device |
| CN107776914A (en) * | 2017-10-16 | 2018-03-09 | 上海微小卫星工程中心 | Firer's impact damper system structure for satellite sun windsurfing |
| CN109178347A (en) * | 2018-10-17 | 2019-01-11 | 长光卫星技术有限公司 | A kind of unidirectional shock isolating apparatus suitable for microsatellite |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114291304B (en) | 2022-11-18 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| WO2020019955A1 (en) | Assembled embedded damping interlayer double steel plate concrete composite shear wall and mounting method thereof | |
| US9194452B2 (en) | High stiffness vibration damping apparatus, methods and systems | |
| CN101384482A (en) | Energy absorber for aircraft | |
| CN105292523A (en) | Separating device and satellite and rocket separating device with buffering structure | |
| CN105864341A (en) | High-reliability combined type shock absorber | |
| CN205134616U (en) | Foamed aluminium - steel sheet viscous damping wall can reset | |
| CN114291304B (en) | One-way impact isolation device suitable for microsatellite | |
| CN201009895Y (en) | Collision-prevention device for high speed rail vehicle | |
| KR101081770B1 (en) | Honeycomb Sandwich Panel | |
| CN101384832A (en) | Energy absorber for aircraft | |
| CN114016791B (en) | Metal friction double-yield-point composite energy dissipation support | |
| CN104632976A (en) | Elastic-plastic energy-absorption buffer component | |
| CN204435205U (en) | The anti-fall anticollision device, collision-prevention device of a kind of bridge beam body | |
| CN116446266B (en) | Beam falling prevention damping device and beam falling prevention damping system | |
| CN201982576U (en) | Variable rigidity shock absorber suitable for floating floor of high-speed maglev train | |
| CN105000029A (en) | Metal tube-honeycomb core combined type anti-creeper with built-in honeycomb core | |
| CN209441446U (en) | A kind of fuel battery passenger car long wheelbase chassis structure | |
| CN110497865A (en) | A kind of modularization buffering energy-absorbing system | |
| CN115341654A (en) | Self-reset energy-consumption armpit support with friction damper | |
| CN114771720A (en) | A structure of making an uproar falls in multiple buffering that is used for icebreaking ship bulkhead to shock resistance | |
| CN209909318U (en) | Damping pipeline system based on viscoelastic damping rubber | |
| HU190312B (en) | Apparatus for decreasing the seismic loads arising on tower-like constructions of high centre of gravity for preventing the turning-over of building wedge provided with flexible members between the foundation and the wall structure | |
| CN218667124U (en) | Assembled overpass sound insulation rail guard | |
| CN114319625B (en) | Shock insulation device for resisting rare earthquakes and building shock insulation method | |
| CN219115325U (en) | Carriage convenient to protect |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |