CN112607057A - High-rigidity high-damping satellite platform structure - Google Patents
High-rigidity high-damping satellite platform structure Download PDFInfo
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- CN112607057A CN112607057A CN202011578709.1A CN202011578709A CN112607057A CN 112607057 A CN112607057 A CN 112607057A CN 202011578709 A CN202011578709 A CN 202011578709A CN 112607057 A CN112607057 A CN 112607057A
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- 238000013016 damping Methods 0.000 title claims abstract description 65
- 230000003287 optical effect Effects 0.000 claims abstract description 39
- 210000001503 joint Anatomy 0.000 claims abstract description 36
- 238000005192 partition Methods 0.000 claims abstract description 30
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims abstract description 19
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 19
- 238000009434 installation Methods 0.000 claims abstract description 7
- 238000003032 molecular docking Methods 0.000 claims description 16
- 229910000733 Li alloy Inorganic materials 0.000 claims description 8
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 claims description 8
- 239000001989 lithium alloy Substances 0.000 claims description 8
- GCICAPWZNUIIDV-UHFFFAOYSA-N lithium magnesium Chemical compound [Li].[Mg] GCICAPWZNUIIDV-UHFFFAOYSA-N 0.000 claims description 8
- 239000011777 magnesium Substances 0.000 claims description 8
- 229910052749 magnesium Inorganic materials 0.000 claims description 8
- 229910000838 Al alloy Inorganic materials 0.000 claims description 6
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 5
- 239000004917 carbon fiber Substances 0.000 claims description 5
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 5
- 239000004411 aluminium Substances 0.000 claims description 4
- 229910000861 Mg alloy Inorganic materials 0.000 claims description 3
- 229920005549 butyl rubber Polymers 0.000 claims description 3
- 229920002379 silicone rubber Polymers 0.000 claims description 3
- 238000005728 strengthening Methods 0.000 abstract description 4
- 238000000034 method Methods 0.000 description 6
- 238000007789 sealing Methods 0.000 description 4
- 230000007547 defect Effects 0.000 description 3
- 238000009826 distribution Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000002955 isolation Methods 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 230000003321 amplification Effects 0.000 description 1
- 230000001808 coupling effect Effects 0.000 description 1
- 125000004122 cyclic group Chemical group 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000005284 excitation Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000005486 microgravity Effects 0.000 description 1
- 238000003199 nucleic acid amplification method Methods 0.000 description 1
- 125000006850 spacer group Chemical group 0.000 description 1
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Classifications
-
- 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
-
- 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
-
- 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
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
- B64G1/646—Docking or rendezvous systems
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- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Astronomy & Astrophysics (AREA)
- General Physics & Mathematics (AREA)
- Laminated Bodies (AREA)
Abstract
The invention discloses a high-rigidity high-damping satellite platform configuration, which belongs to the field of overall design of spacecrafts and comprises a satellite-rocket butt joint ring, a rocket adapter and a satellite-rocket butt joint ring, wherein the satellite-rocket butt joint ring is used for butt joint with the rocket adapter; one side of the mounting plate is fixedly connected with the satellite-rocket butt joint ring, and the other side of the mounting plate is fixedly connected with an optical load plate which bears optical loads; damping layers are laid on the outer surface of the optical load plate and the outer wall of the satellite-rocket butt joint ring; the outer surface of the damping layer is laid with a restraint layer, and the mounting plate comprises a butt plate, a partition plate, an outer plate and an optical load plate; the partition board is of a # -shaped structure, the outer board is arranged on the periphery of the partition board, the butt joint board, the partition board, the outer board and the optical load board are all aluminum honeycomb sandwich boards, and embedded parts are embedded in the single-machine equipment installation position and the rigidity strengthening position of each aluminum honeycomb sandwich board.
Description
Technical Field
The invention relates to the technical field of overall design of spacecrafts, in particular to a high-rigidity high-damping satellite platform configuration.
Background
The satellite is subjected to mechanical environments such as vibration, impact, noise, acceleration, microgravity and the like in the stages of manufacturing assembly, ground transportation, reflection in orbit, in-orbit operation to active return and the like, and the mechanical environments not only reduce the precision and reliability of precise electronic instruments and equipment on the satellite, but also greatly reduce the fatigue life and service time of a structural member;
at present, the traditional vibration reduction method mainly comprises decoupling, vibration isolation, structural rigidity and the like, and the methods have defects;
1) the decoupling method needs to be allocated among different structural frequencies, is complex, needs to increase additional mass as cost, and is not suitable for large complex structures with intensive modes;
2) the vibration isolation technology mainly isolates sensitive equipment needing vibration attenuation through a vibration isolator, and has the defects that a resonance amplification peak is easily introduced into a low-frequency vibration area and the structural stability is poor;
3) the stiffening method is to increase the natural frequency of the structural part by improving the structural rigidity so as to relieve the coupling effect of the structural part and excitation, and usually the additional mass is increased as the cost, so that the method does not meet the development requirement of satellite light weight.
Disclosure of Invention
The invention aims to overcome the defects in the prior art, provides a high-rigidity high-damping satellite platform structure, improves the mechanical environment by vibration and noise reduction treatment by using a damping material and a structure with high mechanical property and high damping property, so as to prolong the service time of a structural member for bearing cyclic load and impact, and can effectively increase the structural damping to attenuate the vibration response of a system on the premise of high rigidity and small additional mass of the system.
In order to achieve the above purpose, the invention provides the following technical scheme:
the invention discloses a high-rigidity high-damping satellite platform configuration, which comprises:
a satellite-rocket docking ring for docking with a rocket adapter;
one side of the mounting plate is fixedly connected with the satellite-rocket butt joint ring, and the other side of the mounting plate is fixedly connected with an optical load plate which bears optical loads;
damping layers are laid on the outer surface of the optical load plate and the outer wall of the satellite-rocket butt joint ring;
and a restraint layer is laid on the outer surface of the damping layer.
Further, the mounting plate comprises a butt plate, a partition plate, an outer plate and the optical load plate;
one side of the butt joint plate is fixedly connected with the satellite and rocket butt joint ring, and the other side of the butt joint plate is fixedly connected with the baffle plate with a groined structure;
the side of the partition board far away from the butt joint board is fixedly connected with the optical load board;
the outer plate comprises four plates and is arranged around the partition plate.
Further, the butt joint plate the baffle the planking and the optics load board is aluminium honeycomb sandwich panel, aluminium honeycomb sandwich panel unit equipment fixing position and rigidity are strengthened the equal pre-buried piece that buries in position.
Further, the embedded parts comprise a first embedded part and a second embedded part;
the first embedded part is a beam or a sealing edge beam embedded part;
the first embedded part is arranged at the position where the rigidity of the aluminum honeycomb sandwich plate is enhanced;
the second embedded part is embedded in the installation position of the single machine equipment of the aluminum honeycomb sandwich plate;
further, the first embedded part is a T700, T800, M40 or M50 carbon fiber embedded part;
the second embedded part is made of magnesium or magnesium-lithium alloy.
Further, the damping layer is made of butyl rubber or silicon rubber;
the restraint layer is made of aluminum alloy, magnesium alloy or a honeycomb plate.
In the technical scheme, the high-rigidity high-damping satellite platform structure provided by the invention is provided;
has the beneficial effects that;
compared with the prior art, the high-rigidity high-damping satellite platform structure designed by the invention has the following advantages:
1. the partition plates are of a # -shaped structure, the platform cabin is divided into nine single cabin bodies which are regularly distributed, single equipment in the cabin can be conveniently mounted, the structural space utilization rate is high, meanwhile, the platform configuration is flat, the platform configuration height is remarkably reduced, the integral mass center of the satellite is reduced, and the structural rigidity is increased;
2. the butt joint plate, the partition plate, the outer plate and the optical load plate are all aluminum honeycomb sandwich plates, the aluminum honeycomb sandwich plates have the performances of high specific strength and specific rigidity and strong designability, and in addition, a first embedded part and a second embedded part are embedded in the butt joint plate, the partition plate, the outer plate and the optical load plate at the installation position and the rigidity strengthening position of the single-machine equipment;
the first embedded parts are T700, T800, M40 or M50 carbon fiber beam and edge sealing beam embedded parts, so that the rigidity of the platform structure is obviously improved, and meanwhile, the structural damping is effectively improved and the lightweight design of the platform structure is facilitated;
the second embedded part is made of magnesium or magnesium-lithium alloy, and compared with the aluminum alloy embedded part with high density and poor damping performance, the second embedded part is made of magnesium or magnesium-lithium alloy, so that the quality of the platform structure can be further reduced, and the effect of increasing the structural damping is achieved;
3. the damping layer and the constraint layer are sequentially laid on the outer surface of the optical load plate and the outer wall of the satellite-rocket butt joint ring, the structural damping of the platform is increased through constraint damping processing, and the structural damping and the vibration response of each component of the damping system are effectively increased on the premise that the system is high in rigidity and small in additional mass.
Drawings
In order to more clearly illustrate the embodiments of the present application or technical solutions in the prior art, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments described in the present invention, and other drawings can be obtained by those skilled in the art according to the drawings.
FIG. 1 is an exploded schematic view of a high-rigidity high-damping satellite platform configuration disclosed by the invention;
FIG. 2 is a schematic diagram of a distribution embodiment of a high-rigidity high-damping satellite platform configuration mounting plate embedded part disclosed by the invention;
FIG. 3 is a front view of a satellite and rocket docking ring of a high-rigidity high-damping satellite platform configuration disclosed by the invention;
FIG. 4 is a cross-sectional view of a satellite-rocket docking ring with a high-rigidity and high-damping satellite platform configuration, disclosed by the invention;
FIG. 5 is a partial schematic view of FIG. 4;
fig. 6 is a schematic structural diagram of a damping layer laid on an optical load plate of a high-rigidity high-damping satellite platform configuration disclosed by the invention.
Fig. 7 is a partial schematic view of fig. 6.
Description of reference numerals:
1. a satellite-rocket docking ring; 2. a butt plate; 3. a partition plate; 4. an outer plate; 5. a load plate; 501. a first embedded part; 502. a second embedded part; 6. a damping layer; 7. and a constraining layer.
Detailed Description
In order to make the technical solutions of the present invention better understood, those skilled in the art will now describe the present invention in further detail with reference to the accompanying drawings.
As shown in fig. 1;
a satellite-rocket docking ring 1 for docking with a rocket adapter;
one side of the mounting plate is fixedly connected with the satellite-rocket butt joint ring 1, the other side of the mounting plate is fixedly connected with an optical load plate 5, and the optical load plate 5 bears optical loads;
damping layers 6 are laid on the outer surface of the optical load plate 5 and the outer wall of the satellite-rocket docking ring 1;
the outer surface of the damping layer 6 is coated with a restraint layer 7.
Preferably, the damping layer 6 is made of butyl rubber or silicon rubber;
the restraint layer 7 is made of aluminum alloy, magnesium alloy or honeycomb plate.
Specifically, one side of a satellite-rocket docking ring 1 is docked with a rocket adapter, the other side of the satellite-rocket docking ring 1 is fixedly connected with a mounting plate, the side of the mounting plate, which is far away from the satellite-rocket docking ring 1, is fixedly connected with an optical load plate 5, a damping layer 6 and a constraint layer 7 are sequentially paved on the outer surface of the optical load plate 5 and the outer wall of the satellite-rocket docking ring 1, the damping layer 6 and the constraint layer 7 are used for realizing constraint damping treatment to increase the structural damping of the platform, and the structural damping and the vibration response of each component of the damping system are effectively increased on the premise that the system is;
preferably, the mounting plate comprises a butt plate 2, a partition plate 3, an outer plate 4 and an optical load plate 5;
one side of the butt joint plate 2 is fixedly connected with the satellite and rocket butt joint ring 1, and the other side is fixedly connected with a baffle plate 3 with a groined structure;
the side of the partition board 3 far away from the butt joint board 2 is fixedly connected with an optical load board 5;
the outer panel 4 includes four pieces and is disposed around the partition 3.
Specifically, as shown in fig. 1, a butt plate 2 is fixedly connected with a satellite and rocket butt ring 1 to bear the whole satellite, a partition plate 3 is fixedly connected to the middle of the side, away from the satellite and rocket butt ring 1, of the butt plate 2, the partition plate 3 is of a # -shaped structure formed by splicing eight partition plates in a split mode, and the platform cabin is divided into nine single cabin bodies with regular distribution through the partition plate 3 with the # -shaped structure, so that single-machine equipment in the cabin can be conveniently installed, the structural space utilization rate is high, and meanwhile, the platform configuration is flat in design, the platform configuration height is remarkably reduced, the integral mass center of the satellite is reduced, and the structural rigidity is increased;
an optical load plate 5 is covered on the side of the partition plate 3 far away from the butt joint plate 2 in a sealing manner, a damping layer 6 and a restraint layer 7 are sequentially laid on the surface of the optical load plate 5 far away from the side of the partition plate 3, outer plates 4 are fixedly connected to four side surfaces of the butt joint plate 2, the partition plate 3 and the optical load plate 5, and solar wings are installed through the outer plates 4;
preferably, the butt joint plate 2, the partition plate 3, the outer plate 4 and the optical load plate 5 are all aluminum honeycomb sandwich plates, embedded parts are embedded in the installation positions and the rigidity strengthening positions of single-machine equipment of the aluminum honeycomb sandwich plates, and the butt joint plate 2, the partition plate 3, the outer plate 4 and the optical load plate 5 have the performances of high specific strength, high specific rigidity and strong designability through the aluminum honeycomb sandwich plates;
preferably, the embedded parts comprise a first embedded part 501 and a second embedded part 502;
the first embedded part 501 is a beam or edge banding beam embedded part;
a first embedded part 501 is arranged at the position where the rigidity of the aluminum honeycomb sandwich plate is enhanced;
a second embedded part 502 is embedded in the installation position of the single-machine equipment of the aluminum honeycomb sandwich plate;
preferably, the first embedded part 501 is a T700, T800, M40 or M50 carbon fiber embedded part, which significantly increases the rigidity of the platform configuration structure, and simultaneously, effectively increases the structural damping and is beneficial to the lightweight design of the platform configuration;
the second embedded part 502 is a magnesium or magnesium-lithium alloy embedded part, and by utilizing the characteristics of small density, high specific strength and good damping performance of the magnesium or magnesium-lithium alloy, compared with an aluminum alloy embedded part with large density and poor damping performance, the quality of the platform configuration can be further reduced, and the effect of increasing the structural damping is achieved;
in the technical scheme, the high-rigidity high-damping satellite platform configuration assembling method provided by the invention comprises the following steps:
step 1: firstly, laying a damping layer 6 on the outer wall of the satellite-rocket docking ring 1 and the outer surface of the optical load plate 5, and laying a constraint layer 7 on the upper surface of the damping layer 6;
step 2: fixedly connecting the satellite and rocket butt joint ring 1 with the butt joint plate 2;
and step 3: fixedly connecting the partition boards 3 with the butt-joint boards 2 to form a platform cabin, wherein the platform cabin is divided into nine single cabin bodies with regular distribution by the partition boards 3 with the groined structure;
and 4, step 4: mounting the optical load plate 5 on the optical load plate 5 mounting surface formed by the spacer 3;
and 5: after the single-machine equipment of each subsystem in the platform cabin is installed, the outer plate 4 is installed finally, and the platform is configured to form a closed structure.
Has the advantages that:
1. the partition plates are of a # -shaped structure, the platform cabin is divided into nine single cabin bodies which are regularly distributed, single equipment in the cabin can be conveniently mounted, the structural space utilization rate is high, meanwhile, the platform configuration is flat, the platform configuration height is remarkably reduced, the integral mass center of the satellite is reduced, and the structural rigidity is increased;
2. the butt joint plate, the partition plate, the outer plate and the optical load plate are all aluminum honeycomb sandwich plates, the aluminum honeycomb sandwich plates have the performances of high specific strength and specific rigidity and strong designability, and in addition, a first embedded part and a second embedded part are embedded in the butt joint plate, the partition plate, the outer plate and the optical load plate at the installation position and the rigidity strengthening position of the single-machine equipment;
the first embedded parts are T700, T800, M40 or M50 carbon fiber beam and edge sealing beam embedded parts, so that the rigidity of the platform structure is obviously improved, and meanwhile, the structural damping is effectively improved and the lightweight design of the platform structure is facilitated;
the second embedded part is made of magnesium or magnesium-lithium alloy, and compared with the aluminum alloy embedded part with high density and poor damping performance, the second embedded part is made of magnesium or magnesium-lithium alloy, so that the quality of the platform structure can be further reduced, and the effect of increasing the structural damping is achieved;
3. the damping layer and the constraint layer are sequentially laid on the outer surface of the optical load plate and the outer wall of the satellite-rocket butt joint ring, the structural damping of the platform is increased through constraint damping processing, and the structural damping and the vibration response of each component of the damping system are effectively increased on the premise that the system is high in rigidity and small in additional mass.
While certain exemplary embodiments of the present invention have been described above by way of illustration only, it will be apparent to those of ordinary skill in the art that the described embodiments may be modified in various different ways without departing from the spirit and scope of the invention. Accordingly, the drawings and description are illustrative in nature and should not be construed as limiting the scope of the invention.
Claims (6)
1. A high stiffness high damping satellite platform configuration, comprising:
a satellite-rocket docking ring (1) for docking with a rocket adapter;
one side of the mounting plate is fixedly connected with the satellite-rocket docking ring (1), the other side of the mounting plate is fixedly connected with an optical load plate (5), and the optical load plate (5) bears optical loads;
damping layers (6) are laid on the outer surface of the optical load plate (5) and the outer wall of the satellite-rocket butt joint ring (1);
and a restraint layer (7) is laid on the outer surface of the damping layer (6).
2. The high stiffness high damping satellite platform configuration of claim 1;
the mounting plate comprises a butt plate (2), a partition plate (3), an outer plate (4) and the optical load plate (5);
one side of the butt joint plate (2) is fixedly connected with the satellite-rocket butt joint ring (1), and the other side of the butt joint plate is fixedly connected with the baffle plate (3) with a groined structure;
the side of the clapboard (3) far away from the butt joint plate (2) is fixedly connected with the optical load plate (5);
the outer plate (4) comprises four blocks and is arranged around the partition plate (3).
3. A high stiffness high damping satellite platform configuration according to claim 2;
butt joint plate (2) baffle (3) planking (4) and optics load board (5) are aluminium honeycomb sandwich panel, aluminium honeycomb sandwich panel unit equipment fixing position and rigidity strengthen the equal pre-buried piece that has of position.
4. A high stiffness high damping satellite platform configuration according to claim 3;
the embedded parts comprise a first embedded part (501) and a second embedded part (502);
the first embedded part (501) is a beam or edge banding beam embedded part;
the first embedded part (501) is arranged at the position where the rigidity of the aluminum honeycomb sandwich plate is enhanced;
the second embedded part (502) is embedded in the installation position of the single aluminum honeycomb sandwich plate device.
5. The high stiffness high damping satellite platform configuration of claim 4;
the first embedded part (501) is a T700, T800, M40 or M50 carbon fiber embedded part;
the second embedded part (502) is a magnesium or magnesium-lithium alloy embedded part.
6. The high stiffness high damping satellite platform configuration of claim 1;
the damping layer (6) is made of butyl rubber or silicon rubber;
the restraint layer (7) is made of aluminum alloy, magnesium alloy or a honeycomb plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011578709.1A CN112607057A (en) | 2020-12-28 | 2020-12-28 | High-rigidity high-damping satellite platform structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011578709.1A CN112607057A (en) | 2020-12-28 | 2020-12-28 | High-rigidity high-damping satellite platform structure |
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| CN112607057A true CN112607057A (en) | 2021-04-06 |
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| CN202011578709.1A Pending CN112607057A (en) | 2020-12-28 | 2020-12-28 | High-rigidity high-damping satellite platform structure |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113022888A (en) * | 2021-05-28 | 2021-06-25 | 北京最终前沿深空科技有限公司 | Satellite structure and satellite assembly method |
| CN113911396A (en) * | 2021-09-30 | 2022-01-11 | 北京空间飞行器总体设计部 | Secondary modular structure with adjustable connection and mounting and dismounting method thereof |
| WO2023161719A1 (en) * | 2022-02-25 | 2023-08-31 | Network Access Associates Limited | Space vehicle and method for manufacture thereof |
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2020
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113022888A (en) * | 2021-05-28 | 2021-06-25 | 北京最终前沿深空科技有限公司 | Satellite structure and satellite assembly method |
| CN113022888B (en) * | 2021-05-28 | 2021-08-10 | 北京最终前沿深空科技有限公司 | Satellite structure and satellite assembly method |
| CN113911396A (en) * | 2021-09-30 | 2022-01-11 | 北京空间飞行器总体设计部 | Secondary modular structure with adjustable connection and mounting and dismounting method thereof |
| WO2023161719A1 (en) * | 2022-02-25 | 2023-08-31 | Network Access Associates Limited | Space vehicle and method for manufacture thereof |
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Application publication date: 20210406 |