CN118008996A - Variable damping variable stiffness and broadband parallel vibration isolation system for spacecraft control moment gyro - Google Patents
Variable damping variable stiffness and broadband parallel vibration isolation system for spacecraft control moment gyro Download PDFInfo
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- CN118008996A CN118008996A CN202311836639.9A CN202311836639A CN118008996A CN 118008996 A CN118008996 A CN 118008996A CN 202311836639 A CN202311836639 A CN 202311836639A CN 118008996 A CN118008996 A CN 118008996A
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- 238000013016 damping Methods 0.000 title claims abstract description 107
- 238000002955 isolation Methods 0.000 title claims abstract description 78
- 239000007788 liquid Substances 0.000 claims abstract description 50
- 230000007704 transition Effects 0.000 claims abstract description 39
- 230000000712 assembly Effects 0.000 claims description 20
- 238000000429 assembly Methods 0.000 claims description 20
- 238000003466 welding Methods 0.000 claims description 18
- 239000000835 fiber Substances 0.000 claims description 16
- 238000003754 machining Methods 0.000 claims description 14
- 238000007789 sealing Methods 0.000 claims description 12
- 239000012530 fluid Substances 0.000 claims description 7
- 230000003014 reinforcing effect Effects 0.000 claims description 7
- 229920002545 silicone oil Polymers 0.000 claims description 7
- 238000004804 winding Methods 0.000 claims description 3
- 238000003491 array Methods 0.000 claims description 2
- 230000002146 bilateral effect Effects 0.000 claims 1
- 238000010586 diagram Methods 0.000 description 10
- 230000007547 defect Effects 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 2
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000007613 environmental effect Effects 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 239000010720 hydraulic oil Substances 0.000 description 1
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Abstract
The invention discloses a spacecraft control moment gyro variable damping variable stiffness and broadband parallel vibration isolation system, and relates to the technical field of vibration isolation and noise reduction of spacecrafts. The vibration isolator comprises variable damping variable stiffness liquid vibration isolators, a vibration isolator transition support, a base, a locking and releasing device, a push rod and an annular connecting plate, wherein the four variable damping variable stiffness liquid vibration isolators are obliquely and symmetrically distributed between the annular connecting plate and the base to form a symmetrical parallel vibration isolation system, the upper end of each liquid vibration isolator is connected with the lower mounting surface of the annular connecting plate through the transition support through screws, and the lower end of each liquid vibration isolator is connected with the base through the transition support through screws. The invention protects the control moment gyro at the active section, inhibits the micro-vibration of the control moment gyro at the on-orbit section, improves the working quality of the precise effective load in the spacecraft cabin, and reduces the contribution of the micro-vibration of the control moment gyro to the noise level in the cabin.
Description
Technical Field
The invention belongs to the field of vibration isolation and noise reduction of spacecrafts, and particularly relates to a variable-damping variable-stiffness broadband parallel vibration isolation system of a spacecraft control moment gyro.
Background
The control moment gyro is a high-inertia high-rotation-speed precise execution part for controlling the gesture of a spacecraft, and vibration isolation is needed. On the other hand, the control moment gyro vibration isolator and the system have high performance and environmental adaptability because the control moment gyro faces a random, broadband and low-frequency energy-based large-amplitude environment in the transmitting stage and faces a random, broadband and high-frequency energy-based small-amplitude environment in the track section.
The prior spacecraft control moment gyro vibration isolation technical scheme can be generally divided into two main types: the vibration isolation configuration generally adopts a parallel or Steward platform mode to realize multi-degree-of-freedom vibration isolation. In the passive vibration isolation mode, a bellows fluid damper schematic diagram with a fixed damping hole is proposed by a patent document CN210526884U for vibration isolation of a control moment gyro, vibration isolation modes of a transverse groove spring inner sleeve damper are proposed by both patent documents CN106005484B and CN110566630B, and a complex mechanical support technology for a control moment gyro cluster vibration isolation system is mainly described by a patent document CN 110803306B. In the passive vibration isolation mode, the vibration isolation bandwidth is limited due to the fact that the damping mode is fixed or single.
In order to improve the performance of the passive vibration isolator, three-parameter vibration isolators have been proposed in european patent documents EP0623763B1, EP2518366B1 and chinese patent document CN104632989B, CN104389943B, and the vibration isolation performance of the three-parameter vibration isolator is significantly improved in the high frequency band, but not in the low frequency band, particularly in the formant region, as compared with the two-parameter vibration isolator.
In order to improve the defects of the passive vibration isolator or system in the frequency width, especially in the low frequency band, a scheme of adopting active and passive integrated vibration isolation is proposed and studied, for example, patent document CN103587724B, CN106286692B, CN105000201B proposes an integrated vibration isolation scheme of superposing piezoelectric actuators by passive vibration isolation elements, and patent document CN115897837a proposes a vibration isolator scheme of superposing voice coil motor actuators by bellows liquid damping. The active and passive integrated vibration isolator or system has the obvious defects of needing to be provided with equipment such as a power supply, a sensor, a controller and the like in the space engineering, which obviously increases the complexity of the vibration isolation system and reduces the reliability.
In summary, to develop a broadband vibration isolation system with high reliability and environmental adaptability, which can efficiently inhibit the vibration and impact of a spacecraft control moment gyro, the key technical problems to be solved include:
1. The high-performance vibration isolation system firstly needs to have a high-performance vibration isolation device, and the existing vibration isolation device is generally fixed in damping and rigidity, so that the vibration isolator is not environment-adaptive and limited in vibration isolation bandwidth, and therefore the vibration isolator with adaptability and variable damping and rigidity needs to be designed.
2. The modern spacecraft mainly develops towards the large-scale and manned directions, so that the control moment gyro is generally large in specification, the vibration isolation system is adopted in the active section to bear the load, the reliability problem is obvious, and a locking mode is adopted in the active section, so that the vibration isolation system of the control moment gyro is required to have certain compression flexibility in the active section, the unlocking release impact of the control moment gyro can be relieved at first in an on-orbit section, then the micro-vibration generated by the control moment gyro can be effectively restrained in the normal working stage of the control moment gyro, and the influence of the micro-vibration of the control moment gyro on the working quality or noise level of a precise effective load in a cabin is avoided.
The present invention has been made in view of this.
Disclosure of Invention
The invention aims to solve the technical problem of overcoming the defects of the prior art and providing a variable damping variable stiffness broadband parallel vibration isolation system for a spacecraft control moment gyro.
In order to solve the technical problems, the invention adopts the basic conception of the technical scheme that:
A variable-damping variable-rigidity broadband parallel vibration isolation system for a spacecraft control moment gyro comprises variable-damping variable-rigidity liquid vibration isolators, vibration isolator transition supports, a base, locking and releasing devices, ejector rods and annular connecting plates, wherein the four variable-damping variable-rigidity liquid vibration isolators are obliquely and symmetrically distributed between the annular connecting plates and the base to form a symmetrical parallel vibration isolation system, the upper end of each liquid vibration isolator is connected with the lower mounting surface of the annular connecting plate through the transition support through screws, and the lower end of each liquid vibration isolator is connected with the base through the transition support through screws; the two locking and releasing devices are symmetrically distributed on two sides of the annular connecting plate, the upper ends of the two locking and releasing devices are connected with the lower mounting surface of the annular connecting plate through screws, and the lower ends of the two locking and releasing devices are connected with the mounting bracket of the locking and releasing device on the base through screws; the two ejector rods are symmetrically distributed on the other two sides of the annular connecting plate, the lower ends of the two ejector rods are connected with the ejector rod mounting brackets on the base through screws, the upper ends of the two ejector rods are free ends, when the locking and releasing device is in a locking state, the upper ends of the ejector rods are in contact with the annular connecting plate, and when the locking and releasing device is in a releasing state, a certain gap exists between the upper ends of the ejector rods and the annular connecting plate; the upper mounting surface of the annular connecting plate is connected with four mounting lug plates of the control moment gyro through screws.
Optionally, the variable damping variable stiffness liquid vibration isolator comprises a piston assembly, a main bellows assembly, a secondary bellows assembly, a main and secondary bellows connecting flange, a sealing ring, silicone oil, a machined spring assembly, an upper connecting piece, a middle connecting piece and a lower connecting piece, wherein the two sets of main bellows assemblies are distributed above and below the piston assembly and are connected with the piston assembly through a first flange of the main bellows assemblies by bolts and nuts, and the sealing ring is arranged between the two sets of main bellows assemblies and the piston assembly; the first flanges of the two sets of auxiliary bellows assemblies are respectively connected with the second flanges of the two sets of main bellows assemblies by bolts and nuts through the two sets of main and auxiliary bellows connecting flanges, and sealing rings are respectively arranged between each set of main bellows assemblies and the connecting flanges and between the connecting flanges and the auxiliary bellows assemblies; the upper part and the lower part of the piston component form symmetrical sealed cavities, each sealed cavity is divided into a main cavity corresponding to the main bellows component, a buffer cavity corresponding to the auxiliary bellows component, and a fluid channel which is formed between the auxiliary bellows component and the main and auxiliary bellows connecting flanges and is used for connecting the main cavity with the buffer cavity, and silicone oil is filled in the sealed cavities on the upper part and the lower part of the piston component to serve as a working medium.
Optionally, two sets of middle connecting pieces in the variable damping variable stiffness liquid vibration isolator are respectively connected with the main and auxiliary corrugated pipe connecting flanges above and below the piston assembly by bolts and nuts at the upper ends and the lower ends, so that the two middle connecting pieces are arranged symmetrically left and right; the upper connecting piece is positioned above the middle connecting piece, the middle part of the upper connecting piece is connected with the piston assembly through a screw, and the lower part of the upper connecting piece is connected with a clamping ring in the machined spring assembly through a screw; the lower connecting piece is positioned below the middle connecting piece, and the upper part of the lower connecting piece is connected with a main and auxiliary corrugated pipe connecting flange positioned below the piston assembly through bolts and nuts; the machining spring assembly is positioned in the lower connecting piece, the lower end of the machining spring assembly is connected with the lower connecting piece through a screw, and the clamping ring at the upper end of the machining spring assembly is connected with the lower part of the upper connecting piece through a screw.
Optionally, the piston assembly in the variable damping variable stiffness liquid vibration isolator comprises a piston, a fixed damping hole, a low-frequency valve and a high-frequency valve, wherein the fixed damping hole is processed in the middle of the piston and is used as a main damping hole, and the aspect ratio of the main damping hole accords with the category of thick-wall small holes, namely 0.5< l/d is less than or equal to 4; the low-frequency valve comprises a low-frequency valve core, a low-frequency valve core spring and a low-frequency valve seat, the low-frequency valve core is positioned at the middle position of the two low-frequency valve core springs, the low-frequency valve is in a normally open mode, and when the upper part and the lower part vibrate, working medium can bidirectionally pass through the low-frequency valve; the high-frequency valve comprises a high-frequency valve core, a high-frequency valve core spring and a high-frequency valve seat, wherein the high-frequency valve core is pressed on the valve port by one high-frequency valve core spring, the high-frequency valve is in a normally closed mode, and when the piston vibrates up and down, working medium can only pass through the high-frequency valve from one direction, so that the high-frequency valve is required to be arranged in pairs, and the two valves are oppositely arranged in the piston; the low-frequency valves and the high-frequency valves are circumferentially and uniformly distributed or symmetrically distributed around the fixed damping hole, and the number and valve parameters of the low-frequency valves and the high-frequency valves can be optimally configured and designed according to the requirements of a specific vibration isolation system.
Optionally, the main bellows assembly in the variable damping variable stiffness liquid vibration isolator comprises a main bellows, a main bellows first flange and a main bellows second flange, preferably, the first flange and the second flange are in 90-degree dislocation design in azimuth, and the main bellows is connected with the first flange and the second flange in a welding mode; the secondary bellows assembly comprises a secondary bellows, a secondary bellows first flange, a secondary bellows second flange and a volume adjusting end cover, wherein the volume adjusting end cover is positioned above the secondary bellows and is connected with the secondary bellows second flange through screws, and a sealing ring is arranged between the volume adjusting end cover and the secondary bellows second flange; the auxiliary corrugated pipe is connected with the first flange and the second flange through welding.
Optionally, in the variable damping variable stiffness liquid vibration isolator, the machining spring assembly comprises a machining spring and a clamping ring, the machining spring adopts a transverse groove spring form, in a natural state, a clamping ring force acting part is positioned at a middle position in a clamping groove at the upper part of the transverse groove spring, gaps between the upper surface and the lower surface of the clamping ring and the transverse groove spring are equal, and the gap amount is optimized according to the condition of the vibration isolation system.
Optionally, the mechanical model of the variable damping variable stiffness liquid vibration isolator is composed of a variable damping three-parameter damper mechanical model and a two-stage stiffness element with a clearance element in parallel.
Optionally, the base comprises a bottom plate, a side coaming, a panel, reinforcing ribs, a mandril mounting bracket and a locking and releasing device mounting bracket, wherein the side coaming is positioned between the bottom plate and the panel, the side coaming, the bottom plate and the panel are all designed into rectangles, the lower end of the side coaming is connected with the bottom plate and the upper end of the side coaming is connected with the panel in a welding mode, and reinforcing rib arrays are welded between the side coaming and the bottom plate and between the side coaming and the panel; the two locking and releasing device mounting brackets are symmetrically distributed on two sides of a panel on the base, the lower ends of the two locking and releasing device mounting brackets are connected with the panel on the base in a welding mode, and mounting holes connected with the locking and releasing devices are designed on the upper parts of the two locking and releasing device mounting brackets; preferably, the two ejector rod mounting brackets are symmetrically distributed on the other two sides of the panel on the base, the lower ends of the two ejector rod mounting brackets are connected with the panel on the base in a welding mode, and mounting hole sites connected with the ejector rods are designed on the upper parts of the two ejector rod mounting brackets.
Optionally, the locking and releasing device adopts a hot cutting unlocking mode with low impact, and mainly comprises a lower supporting block, a fiber rope loop, a hot knife assembly and an upper supporting block, wherein the lower supporting block is connected with a locking and releasing device mounting bracket on the base through a screw, and the upper supporting block is connected with a lower mounting surface of the annular connecting plate through a screw; the fiber rope loop is formed by winding a high-strength fiber rope between an upper supporting block and a lower supporting block in a state that the vibration isolation system is compressed, so that locking force for controlling the moment gyro is formed; the hot knife component is connected with the lower supporting block and is propped against the two sides of the fiber rope loop, and after the satellite orbit entering system starts an unlocking signal, the hot knife component is electrified and heated to generate high temperature, so that the fiber rope loop is cut, and the control moment gyro is unlocked and released.
Optionally, the annular connecting plate is provided with hole sites which are connected with four mounting lug plates of the control moment gyro through threads on the upper mounting surface, and hole sites which are respectively connected with four vibration isolator transition brackets and two locking and releasing devices through threads are arranged on the lower mounting surface; the vibration isolator transition support comprises a support side plate and a support bottom plate, and the support side plate is connected with the support bottom plate in a welding mode; each variable damping variable stiffness liquid vibration isolator is provided with an upper vibration isolator transition bracket and a lower vibration isolator transition bracket, wherein a side plate of the upper transition bracket is connected with the upper end of the vibration isolator through a screw, a bottom plate of the upper transition bracket is connected with a lower mounting surface of an annular connecting plate through a screw, a side plate of the lower transition bracket is connected with the lower end of the vibration isolator through a screw, and a bottom plate of the lower transition bracket is connected with a panel on a base through a screw.
After the technical scheme is adopted, compared with the prior art, the invention has the following beneficial effects, and of course, any product for implementing the invention does not necessarily need to achieve all the following advantages at the same time:
The variable damping variable stiffness liquid vibration isolator in the vibration isolation system adopts a corrugated pipe structure mode, so that the vibration isolator not only can adapt to and meet the compression requirement of the control moment gyro in a locking state, but also can efficiently relieve the impact energy of the control moment gyro when the control moment gyro is unlocked and released at an on-track section, and can obviously inhibit the micro-vibration of the control moment gyro after the control moment gyro is put into normal work.
The technical scheme provided by the invention provides a variable damping variable stiffness broadband parallel vibration isolation system for a spacecraft control moment gyro, the control moment gyro is protected in an active section, micro-vibration of the control moment gyro is restrained in an on-orbit section, the working quality of a precise effective load in a spacecraft cabin is improved, and the contribution of the micro-vibration of the control moment gyro to the noise level in the cabin is reduced.
The following describes the embodiments of the present invention in further detail with reference to the accompanying drawings.
Drawings
The drawings in the following description are only examples of embodiments from which other drawings may be derived by those skilled in the art without the exercise of inventive faculty. In the drawings:
FIG. 1 is a schematic diagram of an assembly of a spacecraft control moment gyro variable damping variable stiffness, broadband parallel vibration isolation system and a control moment gyro of the invention.
Fig. 2 is a schematic diagram of an assembly of the spacecraft control moment gyro variable damping variable stiffness and broadband parallel vibration isolation system.
Fig. 3 is an external axial view of a variable damping and variable stiffness liquid vibration isolator in a spacecraft control moment gyro variable damping and variable stiffness broadband parallel vibration isolation system.
Fig. 4 is a top view of a variable damping and variable stiffness liquid vibration isolator in a spacecraft control moment gyro variable damping and variable stiffness broadband parallel vibration isolation system.
FIG. 5 is a cross-sectional view A-A of FIG. 4 in the "spacecraft control moment gyro damping variable stiffness, broadband parallel vibration isolation system" of the present invention.
Fig. 6 is a top view of a piston assembly of a variable damping and variable stiffness liquid vibration isolator in a "spacecraft control moment gyroscopic damping and variable stiffness broadband parallel vibration isolation system" of the present invention.
FIG. 7 is a cross-sectional view B-B of FIG. 6 in the "spacecraft control moment gyro damping variable stiffness, broadband parallel vibration isolation system" of the present invention.
FIG. 8 is a cross-sectional view C-C of FIG. 6 in a "spacecraft control moment gyro damping variable stiffness, broadband parallel vibration isolation system" of the present invention.
Fig. 9 is a schematic structural diagram of a main bellows assembly of a variable damping and variable stiffness liquid vibration isolator in a "spacecraft control moment gyro variable damping and variable stiffness broadband parallel vibration isolation system" of the present invention.
Fig. 10 is a schematic structural diagram of a secondary bellows assembly of a variable damping and variable stiffness liquid vibration isolator in a "spacecraft control moment gyro variable damping and variable stiffness broadband parallel vibration isolation system" of the present invention.
Fig. 11 is a schematic structural view of a connection flange of a main corrugated pipe and a secondary corrugated pipe of a variable-damping variable-stiffness liquid vibration isolator in a spacecraft control moment gyro variable-damping variable-stiffness broadband parallel vibration isolation system.
Fig. 12 is a schematic structural view of a machined spring assembly of a variable damping and variable stiffness liquid vibration isolator in a "spacecraft control moment gyroscopic damping and variable stiffness, broadband parallel vibration isolation system" of the present invention.
Fig. 13 is a schematic diagram of a mechanical model of a variable damping and variable stiffness liquid vibration isolator in a spacecraft control moment gyro variable damping and variable stiffness broadband parallel vibration isolation system compared with a mechanical model of an existing two-parameter and three-parameter vibration isolator.
Fig. 14 is a schematic diagram showing the comparison of the vibration transfer rate curve of the variable damping and variable stiffness liquid vibration isolator in the spacecraft control moment gyro variable damping and variable stiffness broadband parallel vibration isolation system with the vibration transfer rate curve of the prior two-parameter and three-parameter vibration isolator.
Fig. 15 is an external axial side view of a base in the spacecraft control moment gyro variable damping variable stiffness broadband parallel vibration isolation system of the present invention.
Fig. 16 is an assembly schematic diagram of a locking and releasing device in a spacecraft control moment gyro variable damping variable stiffness broadband parallel vibration isolation system of the present invention.
Fig. 17 is a schematic distribution diagram of an annular connecting plate structure and mounting holes on a lower mounting surface of the annular connecting plate structure of the spacecraft control moment gyro damping variable stiffness broadband parallel vibration isolation system.
Fig. 18 is an assembly schematic diagram of the ejector rod in the spacecraft control moment gyro variable damping variable stiffness broadband parallel vibration isolation system.
FIG. 19 is an isometric view of a transition bracket of a variable damping and variable stiffness liquid vibration isolator in a spacecraft control moment gyro variable damping and variable stiffness broadband parallel vibration isolation system;
in the drawings, the list of components represented by the various numbers is as follows:
1. A variable damping variable stiffness liquid vibration isolator; 11. an upper connecting piece; 12. an intermediate connection; 13. a lower connecting piece; 14. the secondary bellows assembly comprises a secondary bellows assembly body 141, a secondary bellows assembly 142, a secondary bellows first flange 143, a secondary bellows second flange 144 and a volume adjusting end cover; 15. a main bellows and auxiliary bellows connecting flange; 16. a seal ring; 17. a main bellows assembly 171, a main bellows 172, a main bellows first flange 173, a main bellows second flange; 18. the piston assembly, 181, the piston, 182, fixed damping hole; 183. a low frequency valve 1831, a low frequency valve core, 1832, a low frequency valve core spring, 1833, a low frequency valve seat; 184. a high frequency valve 1841, a high frequency valve core, 1842, a high frequency valve core spring, 1843 and a high frequency valve seat; 19. machining a spring assembly 191, machining a spring, 192 and a clamping ring; 1011. a lower buffer chamber 1012, an upper buffer chamber 1021, a lower fluid passage 1022, an upper fluid passage 1031, a lower main chamber 1032, an upper main chamber 104, silicone oil; 2. a base, 21, a bottom plate; 22. reinforcing ribs, 23, side walls, 24, a panel, 25 ejector rod mounting brackets, 26 and locking and releasing device mounting brackets; 3. the locking and releasing device comprises a locking and releasing device 31, a lower supporting block 32, a hot knife assembly 33, a fiber rope loop 34 and an upper supporting block; 4. the annular connecting plate, 41, the control moment gyro mounting hole site, 42, the locking and releasing device mounting hole site, 43 and the mounting hole site of the vibration isolator transition bracket; 5. a push rod; 6. the vibration isolator is provided with a transition bracket 61, bracket side plates 62 and a bracket bottom plate; 7. controlling a moment gyro; 8. mechanical model of two parameter vibration isolator; 9. a mechanical model of the three-parameter vibration isolator; 10. a mechanical model of a variable damping and variable stiffness liquid vibration isolator.
It should be noted that these drawings and the written description are not intended to limit the scope of the inventive concept in any way, but to illustrate the inventive concept to those skilled in the art by referring to the specific embodiments.
Description of the embodiments
The invention will now be described in further detail with reference to the accompanying drawings.
Referring to fig. 1-19, in this embodiment, a variable damping, variable stiffness and broadband parallel vibration isolation system for a spacecraft control moment gyro is provided, which includes a variable damping, variable stiffness liquid vibration isolator 1, a vibration isolator transition support 6, a base 2, a locking and releasing device 3, a push rod 5 and an annular connecting plate 4.
Referring to fig. 1,2, 15 and 18, four variable damping and variable stiffness liquid vibration isolators 1 are obliquely and symmetrically distributed between an annular connecting plate 4 and a base 2 to form a symmetrical parallel vibration isolation system, the upper end of each liquid vibration isolator 1 is connected with the lower mounting surface of the annular connecting plate 4 through a transition bracket 6 by a screw, and the lower end is connected with the base 2 through the transition bracket 6 by a screw; the two locking and releasing devices 3 are symmetrically distributed on two sides of the annular connecting plate 4, the upper ends of the two locking and releasing devices are connected with the lower mounting surface of the annular connecting plate 4 through screws, and the lower ends of the two locking and releasing devices are connected with the locking and releasing device mounting brackets 26 on the base 2 through screws; the two ejector rods 5 are symmetrically distributed on the other two sides of the annular connecting plate 4, the lower ends of the two ejector rods are connected with the ejector rod mounting brackets 25 on the base 2 through screws, the upper ends of the two ejector rods are free ends, when the locking and releasing device 3 is in a locking state, the upper ends of the ejector rods 5 are in contact with the annular connecting plate 4, and when the locking and releasing device 3 is in a releasing state, a certain gap exists between the upper ends of the ejector rods 5 and the annular connecting plate 4; the upper mounting surface of the annular connecting plate 4 is connected with four mounting lug plates of the control moment gyro 7 through screws. The protection scope is not limited to the vibration isolation configuration described above, but all vibration isolation configurations based on the components described above are within the protection scope.
Referring to fig. 3, 4, 5 and 11, the variable damping and variable stiffness liquid vibration isolator 1 comprises a piston assembly 18, a main bellows assembly 17, a secondary bellows assembly 14, a main and secondary bellows connecting flange 15, a sealing ring 16, silicone oil 104, a machined spring assembly 19, an upper connecting member 11, a middle connecting member 12 and a lower connecting member 13. The two sets of main bellows assemblies 17 are distributed above and below the piston assembly 18, and are connected with the piston assembly 18 through bolts and nuts by the first flange 172, and sealing rings 16 are arranged between the two sets of main bellows assemblies 17 and the piston assembly 18; the first flanges 142 of the two sets of the secondary bellows assemblies 14 are respectively connected with the second flanges 173 of the two sets of the primary bellows assemblies 17 by bolts and nuts through the two sets of the primary and secondary bellows connecting flanges 15, and sealing rings 16 are respectively arranged between each set of the primary bellows assemblies 17 and the primary and secondary bellows connecting flanges 15 and between the primary and secondary bellows connecting flanges 15 and the secondary bellows assemblies 14. Thus, in the above assembly, symmetrical sealed pockets are formed above and below the piston assembly 18. The upper sealed volume is divided into an upper main chamber 1032 corresponding to the main bellows assembly 18, an upper buffer chamber 1012 corresponding to the sub-bellows assembly 14, and an upper fluid passage 1022 formed between the sub-bellows assembly 14 and the main and sub-bellows connecting flange 15, connecting the upper main chamber 1032 and the upper buffer chamber 1012; the lower sealed vessel is divided into a lower main chamber 1031 corresponding to the main bellows assembly 18, a lower buffer chamber 1011 corresponding to the sub bellows assembly 14, and a lower fluid passage 1021 formed between the sub bellows assembly 14 and the main and sub bellows connecting flange 15, connecting the lower main chamber 1031 and the lower buffer chamber 1011. The working medium 104 is filled in the sealed cavities above and below the piston assembly 18, but the working medium is not limited to silicone oil, and other hydraulic oil and mechanical lubricating oil with stable physical characteristics in a wide temperature range are all within a protection range.
Referring to fig. 3, 4, 5 and 12, in the variable damping and variable stiffness liquid vibration isolator 1, two sets of intermediate connectors 12 are respectively connected with main and auxiliary bellows connecting flanges 15 on and under a piston assembly 18 at the upper and lower ends thereof by bolts and nuts, so as to be arranged symmetrically left and right; the upper connecting piece 11 is arranged above the middle connecting piece 12, the middle part of the upper connecting piece is connected with the piston assembly 18 through a screw, and the lower part of the upper connecting piece is connected with a clamping ring 192 in the machined spring assembly 19 through a screw; the lower connecting piece 13 is positioned below the middle connecting piece 12, and the upper part of the lower connecting piece is connected with a main bellows connecting flange 15 positioned below the piston assembly 18 through bolts and nuts; the machined spring assembly 19 is positioned inside the lower connector 13, and has its lower end screwed to the lower connector 13 and its upper end snap ring 192 screwed to the lower portion of the upper connector 11. Other possible designs and arrangements based on the above elements are within the scope of the invention.
Referring to fig. 6, 7 and 8, in the variable damping variable stiffness liquid vibration isolator 1, a piston assembly 8 includes a piston 181, a fixed damping orifice 182, a low frequency valve 183 and a high frequency valve 184. A fixed damping hole 182 is processed in the middle of the piston 181 and is used as a main damping hole, and the length-diameter ratio of the main damping hole accords with the category of thick-wall small holes, namely, 0.5< l/d is less than or equal to 4; the low-frequency valve 183 comprises a low-frequency valve core 1831, a low-frequency valve core spring 1832 and a low-frequency valve seat 1833, the low-frequency valve core 1831 is positioned in the middle of the two low-frequency valve core springs 1832, the low-frequency valve 183 is in a normally open mode, and when the piston 181 vibrates up and down, the working medium 104 can bidirectionally pass through the low-frequency valve 183; the high-frequency valve 184 includes a high-frequency valve core 1841, a high-frequency valve core spring 1842 and a high-frequency valve seat 1843, the high-frequency valve core 1841 is pressed on the valve port by one high-frequency valve core spring 1842, the high-frequency valve 184 is in a normally closed mode, when the piston 181 vibrates up and down, the working medium 104 can only pass through the high-frequency valve 184 from one direction, so that the high-frequency valve 184 must be arranged in pairs, and two valves are oppositely arranged in the piston 181; preferably, the plurality of low-frequency valves 183 and the plurality of high-frequency valves 184 are circumferentially and uniformly distributed or symmetrically distributed around the fixed damping hole 182, and the number and the valve parameters of the low-frequency valves 183 and the high-frequency valves 184 can be optimally configured and designed according to the requirements of a specific vibration isolation system. However, the protection scope is not limited to the above-mentioned form, and in some cases, the fixed damping hole can also adopt a thin-wall small hole with the length-diameter ratio l/d less than or equal to 0.5, and other feasible arrangement forms of the fixed damping hole, the low-frequency valve and the high-frequency valve on the piston are all within the protection scope.
Referring to fig. 9 and 10, the main bellows assembly 17 includes a main bellows 171, a main bellows first flange 172, and a main bellows second flange 173, where the main bellows first flange 172 and the main bellows second flange 173 are in 90 ° dislocation design in azimuth, so that the overall design of the liquid vibration isolator is facilitated, and the main bellows 171, the main bellows first flange 172, and the main bellows second flange 173 are all connected by welding; the secondary bellows assembly 14 comprises a secondary bellows 141, a secondary bellows first flange 142, a secondary bellows second flange 143 and a volume adjusting end cover 144, the volume adjusting end cover 144 is located above the secondary bellows 141 and is connected with the secondary bellows second flange 143 through screws, a sealing ring 16 is arranged between the volume adjusting end cover 144 and the secondary bellows second flange 143, and the secondary bellows 141 is connected with the first flange 142 and the second flange 143 through welding. But other possible designs of misalignment based on other possible angles of the above elements are within the scope of protection.
Referring to fig. 12, the machined spring assembly 19 includes a machined spring 191 and a snap ring 192. The machined spring 191 is in a form of a transverse groove spring, and in a natural state, the force-exerting part of the clamping ring 192 is positioned in the middle position of the clamping groove at the upper part of the transverse groove spring 191, the gaps between the upper surface and the lower surface of the clamping ring and the transverse groove spring 191 are equal, and the gap amount can be optimally designed according to the condition of a specific vibration isolation system. But other forms of machined springs, such as pattern springs, coil springs, etc., are within the scope of protection.
Referring to fig. 15, the base 2 includes a bottom plate 21, side panels 23, a panel 24, a reinforcing rib 22, a carrier mounting bracket 25, and a locking and releasing device mounting bracket 26, wherein the side panels 23 are located in the middle of the bottom plate 21 and the panel 24, the side panels 23, the bottom plate 21 and the panel 24 are all designed to be rectangular, the lower ends of the side panels 23 are connected with the bottom plate 21 and the upper ends of the side panels 24 in a welding manner, and an array of reinforcing ribs 22 is welded between the side panels 23 and the bottom plate 21 and between the side panels 23 and the panel 24; the two locking and releasing device mounting brackets 26 are symmetrically distributed on two sides of the panel 24 on the base 2, the lower ends of the two locking and releasing device mounting brackets are connected with the panel 24 on the base 2 in a welding mode, and mounting hole sites connected with the locking and releasing devices 3 are designed on the upper parts of the two locking and releasing device mounting brackets 26; the two ejector rod mounting brackets 25 are symmetrically distributed on the other two sides of the panel 24 on the base 2, the lower ends of the two ejector rod mounting brackets are connected with the panel 24 on the base 2 in a welding mode, and mounting hole sites connected with the ejector rods 5 are designed on the upper parts of the two ejector rod mounting brackets 25. But other possible designs and other possible connection ways based on the above elements are within the scope of protection.
Referring to fig. 16, the locking and releasing device 3 adopts a thermal cutting unlocking mode with low impact, and mainly comprises a lower supporting block 31, a fiber rope loop 33, a thermal knife assembly 32 and an upper supporting block 34, wherein the lower supporting block 31 is connected with a locking and releasing device mounting bracket 26 on the base 2 through screws, and the upper supporting block 34 is connected with a lower mounting surface of the annular connecting plate 4 through screws; the fiber rope loop 33 is formed by winding a high-strength fiber rope between the upper supporting block 34 and the lower supporting block 31 in a state that the vibration isolation system is compressed, so as to form a locking force for the control moment gyro 7; the hot knife assembly 32 is connected with the lower supporting block 31 and is propped against the two sides of the fiber rope loop 33, when the satellite orbit entering system starts an unlocking signal, the hot knife assembly 32 is electrified and heated to generate high temperature, thereby cutting the fiber rope loop 33 and unlocking and releasing the control moment gyro 7. The protection scope is not limited to the hot cutting unlocking mode, structure or material, and any other feasible locking and releasing mode, structure or material such as a fire, shape memory alloy drive and the like is within the protection scope.
Referring to fig. 17, the annular connecting plate 4 has a hole 41 on its upper mounting surface, which is screwed with four mounting lugs of the moment control gyro 7, and a hole 42 on its lower mounting surface, which is screwed with two locking and releasing devices 3, and a hole 43 on its lower mounting surface, which is screwed with four vibration isolator transition brackets 6.
Referring to fig. 19, 1 and 2, the transition bracket 6 of the vibration isolator comprises a bracket side plate 61 and a bracket bottom plate 62, and the bracket side plate 61 and the bracket bottom plate 62 are connected in a welding mode; each variable damping and variable stiffness liquid vibration isolator 1 is provided with an upper vibration isolator transition bracket 6 and a lower vibration isolator transition bracket 6, wherein a side plate 61 of the upper transition bracket 6 is connected with the upper end of the vibration isolator 1 through screws, a bottom plate 62 of the upper transition bracket 6 is connected with the lower mounting surface of the annular connecting plate 4 through screws, a side plate 61 of the lower transition bracket 6 is connected with the lower end of the vibration isolator 1 through screws, and a bottom plate 62 of the lower transition bracket 6 is connected with the panel 24 on the base 2 through screws. But other possible mounting hole designs and other possible connection modes are within the protection scope.
Referring to fig. 13 and 14, the mechanical model 10 of the variable damping variable stiffness liquid vibration isolator 1 is composed of a variable damping three-parameter vibration isolator mechanical model connected in parallel with a two-stage stiffness element with a clearance element. The mechanical model is within the scope of the present invention. Compared with the existing mechanical model 8 of the two-parameter vibration isolator and the mechanical model 9 of the three-parameter damper, the vibration isolator not only provides the damping with adaptability and variability, but also provides the rigidity with adaptability and variability; on the other hand, as the fixed damping hole 182 is designed in the piston 181 of the liquid vibration isolator 1 and a plurality of frequency valves 183 and 184 are overlapped, the vibration transmission rate of the vibration isolator 1 in a low frequency band, particularly in a formant region, is obviously reduced by the low frequency valve 183, and the vibration transmission rate is further reduced by the high frequency valve 184 in a high frequency band, so that the hydraulic damping device has adaptability and excellent performance in a wide frequency band; meanwhile, a machined spring 191 with excellent linearity is designed as the second-stage rigidity, so that the invention can adapt to the vibration and impact environments of the control moment gyro 7 at different stages.
The embodiment described with reference to fig. 1 to 19 provides a variable damping, variable stiffness and broadband parallel vibration isolation system for a spacecraft control moment gyro 7, protects the control moment gyro in an active section, suppresses micro-vibration of the control moment gyro in an on-orbit section, improves the working quality of a precise payload in a spacecraft cabin, and reduces the contribution of the micro-vibration of the control moment gyro to the noise level in the cabin.
What is not described in detail in this specification is prior art known to those skilled in the art.
The present invention is not limited to the above embodiments, and any person who can learn the structural changes made under the teaching of the present invention can fall within the scope of the present invention if the present invention has the same or similar technical solutions. The technology, shape, and construction parts of the present invention, which are not described in detail, are known in the art.
Claims (10)
1. A spacecraft control moment gyro variable damping variable stiffness and broadband parallel vibration isolation system comprises: the variable damping variable stiffness liquid vibration isolator comprises a variable damping variable stiffness liquid vibration isolator transition support, a base, a locking and releasing device, an ejector rod and an annular connecting plate, and is characterized in that: four variable damping variable stiffness liquid vibration isolators are obliquely and symmetrically distributed between the annular connecting plate and the base to form a symmetrical parallel vibration isolation system, the upper end of each liquid vibration isolator is connected with the lower mounting surface of the annular connecting plate through a transition bracket by a screw, and the lower end of each liquid vibration isolator is connected with the base through the transition bracket by a screw; the two locking and releasing devices are symmetrically distributed on two sides of the annular connecting plate, the upper ends of the two locking and releasing devices are connected with the lower mounting surface of the annular connecting plate through screws, and the lower ends of the two locking and releasing devices are connected with the mounting bracket of the locking and releasing device on the base through screws; the two ejector rods are symmetrically distributed on the other two sides of the annular connecting plate, the lower ends of the two ejector rods are connected with the ejector rod mounting brackets on the base through screws, the upper ends of the two ejector rods are free ends, when the locking and releasing device is in a locking state, the upper ends of the ejector rods are in contact with the annular connecting plate, and when the locking and releasing device is in a releasing state, a certain gap exists between the upper ends of the ejector rods and the annular connecting plate; the upper mounting surface of the annular connecting plate is connected with four mounting lug plates of the control moment gyro through screws.
2. The spacecraft control moment gyro variable damping variable stiffness broadband parallel vibration isolation system is characterized in that a piston assembly, a main bellows assembly, a secondary bellows assembly, a main and secondary bellows connecting flange, a sealing ring, silicone oil, a machined spring assembly, an upper connecting piece, a middle connecting piece and a lower connecting piece are arranged above and below the piston assembly, the two sets of main bellows assemblies are connected with the piston assembly through a first flange of the main bellows assemblies through bolts and nuts, and the sealing rings are arranged between the two sets of main bellows assemblies and the piston assembly; the first flanges of the two sets of auxiliary bellows assemblies are respectively connected with the second flanges of the two sets of main bellows assemblies by bolts and nuts through the two sets of main and auxiliary bellows connecting flanges, and sealing rings are respectively arranged between each set of main bellows assemblies and the connecting flanges and between the connecting flanges and the auxiliary bellows assemblies; the upper part and the lower part of the piston component form symmetrical sealed cavities, each sealed cavity is divided into a main cavity corresponding to the main bellows component, a buffer cavity corresponding to the auxiliary bellows component, and a fluid channel which is formed between the auxiliary bellows component and the main and auxiliary bellows connecting flanges and is used for connecting the main cavity with the buffer cavity, and silicone oil is filled in the sealed cavities on the upper part and the lower part of the piston component to serve as a working medium.
3. The variable damping variable stiffness and broadband parallel vibration isolation system for the spacecraft control moment gyro according to claim 2, wherein the upper ends and the lower ends of two sets of middle connecting pieces in the variable damping variable stiffness liquid vibration isolator are respectively connected with a main bellows connecting flange and a secondary bellows connecting flange which are positioned above and below a piston assembly by bolts and nuts to form bilateral symmetry arrangement; the upper connecting piece is positioned above the middle connecting piece, the middle part of the upper connecting piece is connected with the piston assembly through a screw, and the lower part of the upper connecting piece is connected with a clamping ring in the machined spring assembly through a screw; the lower connecting piece is positioned below the middle connecting piece, and the upper part of the lower connecting piece is connected with a main and auxiliary corrugated pipe connecting flange positioned below the piston assembly through bolts and nuts; the machining spring assembly is positioned in the lower connecting piece, the lower end of the machining spring assembly is connected with the lower connecting piece through a screw, and the clamping ring at the upper end of the machining spring assembly is connected with the lower part of the upper connecting piece through a screw.
4. The spacecraft control moment gyro variable damping variable stiffness broadband parallel vibration isolation system is characterized in that a piston assembly in a variable damping variable stiffness liquid vibration isolator comprises a piston, a fixed damping hole, a low-frequency valve and a high-frequency valve, wherein the middle part of the piston is provided with the fixed damping hole as a main damping hole, and the length-diameter ratio of the main damping hole accords with the category of thick-wall small holes, namely 0.5< l/d is less than or equal to 4; the low-frequency valve comprises a low-frequency valve core, a low-frequency valve core spring and a low-frequency valve seat, the low-frequency valve core is positioned at the middle position of the two low-frequency valve core springs, the low-frequency valve is in a normally open mode, and when the upper part and the lower part vibrate, working medium can bidirectionally pass through the low-frequency valve; the high-frequency valve comprises a high-frequency valve core, a high-frequency valve core spring and a high-frequency valve seat, wherein the high-frequency valve core is pressed on the valve port by one high-frequency valve core spring, the high-frequency valve is in a normally closed mode, and when the piston vibrates up and down, working medium can only pass through the high-frequency valve from one direction, so that the high-frequency valve is required to be arranged in pairs, and the two valves are oppositely arranged in the piston; the low-frequency valves and the high-frequency valves are circumferentially and uniformly distributed or symmetrically distributed around the fixed damping hole, and the number and valve parameters of the low-frequency valves and the high-frequency valves can be optimally configured and designed according to the requirements of a specific vibration isolation system.
5. The spacecraft control moment gyro variable damping variable stiffness and broadband parallel vibration isolation system according to claim 2, wherein the main bellows assembly in the variable damping variable stiffness liquid vibration isolator comprises a main bellows, a main bellows first flange and a main bellows second flange, preferably, the first flange and the second flange are in 90-degree dislocation design in azimuth, and the main bellows is connected with the first flange and the second flange in a welding mode; the secondary bellows assembly comprises a secondary bellows, a secondary bellows first flange, a secondary bellows second flange and a volume adjusting end cover, wherein the volume adjusting end cover is positioned above the secondary bellows and is connected with the secondary bellows second flange through screws, and a sealing ring is arranged between the volume adjusting end cover and the secondary bellows second flange; the auxiliary corrugated pipe is connected with the first flange and the second flange through welding.
6. The variable damping variable stiffness broadband parallel vibration isolation system for the spacecraft control moment gyro according to claim 2, wherein in the variable damping variable stiffness liquid vibration isolator, a machining spring assembly comprises a machining spring and a clamping ring, the machining spring is in the form of a transverse groove spring, in a natural state, a clamping ring force part is positioned at the middle position in a clamping groove at the upper part of the transverse groove spring, gaps between the upper surface and the lower surface of the clamping ring are equal to those between the transverse groove spring and the clamping ring, and the gap amount is optimized according to the condition of the vibration isolation system.
7. The spacecraft control moment gyro variable damping variable stiffness and broadband parallel vibration isolation system according to any one of claims 1-6, wherein the mechanical model of the variable damping variable stiffness liquid vibration isolator is composed of a three-parameter damper mechanical model with damping only, and a two-stage stiffness element with a clearance element is connected in parallel.
8. The spacecraft control moment gyro variable damping variable stiffness broadband parallel vibration isolation system is characterized in that a base comprises a bottom plate, side panels, a panel, reinforcing ribs, a mandril mounting bracket and a locking and releasing device mounting bracket, wherein the side panels are positioned between the bottom plate and the panel, the side panels, the bottom plate and the panel are all designed into rectangles, the lower ends of the side panels are connected with the bottom plate and the upper ends of the side panels in a welding mode, and reinforcing rib arrays are welded between the side panels and the bottom plate and between the side panels and the panel; the two locking and releasing device mounting brackets are symmetrically distributed on two sides of a panel on the base, the lower ends of the two locking and releasing device mounting brackets are connected with the panel on the base in a welding mode, and mounting holes connected with the locking and releasing devices are designed on the upper parts of the two locking and releasing device mounting brackets; preferably, the two ejector rod mounting brackets are symmetrically distributed on the other two sides of the panel on the base, the lower ends of the two ejector rod mounting brackets are connected with the panel on the base in a welding mode, and mounting hole sites connected with the ejector rods are designed on the upper parts of the two ejector rod mounting brackets.
9. The spacecraft control moment gyro variable damping variable stiffness broadband parallel vibration isolation system is characterized in that a locking and releasing device adopts a hot cutting unlocking mode with low impact characteristics, and mainly comprises a lower supporting block, a fiber rope loop, a hot knife assembly and an upper supporting block, wherein the lower supporting block is connected with a locking and releasing device mounting bracket on a base through screws, and the upper supporting block is connected with a lower mounting surface of an annular connecting plate through screws; the fiber rope loop is formed by winding a high-strength fiber rope between an upper supporting block and a lower supporting block in a state that the vibration isolation system is compressed, so that locking force for controlling the moment gyro is formed; the hot knife component is connected with the lower supporting block and is propped against the two sides of the fiber rope loop, and after the satellite orbit entering system starts an unlocking signal, the hot knife component is electrified and heated to generate high temperature, so that the fiber rope loop is cut, and the control moment gyro is unlocked and released.
10. The variable damping variable stiffness broadband parallel vibration isolation system for the spacecraft control moment gyro according to claim 1, wherein the annular connecting plate is provided with hole sites which are in threaded connection with four mounting ear plates of the control moment gyro on an upper mounting surface and hole sites which are in threaded connection with four vibration isolator transition brackets and two locking and releasing devices respectively on a lower mounting surface; the vibration isolator transition support comprises a support side plate and a support bottom plate, and the support side plate is connected with the support bottom plate in a welding mode; each variable damping variable stiffness liquid vibration isolator is provided with an upper vibration isolator transition bracket and a lower vibration isolator transition bracket, wherein a side plate of the upper transition bracket is connected with the upper end of the vibration isolator through a screw, a bottom plate of the upper transition bracket is connected with a lower mounting surface of an annular connecting plate through a screw, a side plate of the lower transition bracket is connected with the lower end of the vibration isolator through a screw, and a bottom plate of the lower transition bracket is connected with a panel on a base through a screw.
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| US5305981A (en) * | 1991-10-31 | 1994-04-26 | Honeywell Inc. | Multiaxis vibration isolation system |
| US20140312198A1 (en) * | 2013-04-17 | 2014-10-23 | Honeywell International Inc. | Isolators including damper assemblies having variable annuli and spacecraft isolation systems employing the same |
| CN106005484A (en) * | 2016-05-18 | 2016-10-12 | 北京空间飞行器总体设计部 | Vibration reduction and insulation device for parallel truss-type control moment gyros |
| CN212718003U (en) * | 2020-07-09 | 2021-03-16 | 赛洛克流体设备成都有限公司 | Bellows subassembly and pneumatic normally closed bellows valve of heavy-calibre |
| CN113104239A (en) * | 2021-04-23 | 2021-07-13 | 中国科学院微小卫星创新研究院 | Thermal cutting unlocking device and installation unlocking method |
| CN113803396A (en) * | 2021-09-10 | 2021-12-17 | 中国空间技术研究院 | Controllable variable rigidity and variable damping vibration isolation device |
| CN114718988A (en) * | 2022-03-31 | 2022-07-08 | 北京控制工程研究所 | Satellite flywheel vibration isolator based on flexible frame body |
| CN115750663A (en) * | 2022-10-27 | 2023-03-07 | 北京微纳星空科技有限公司 | Vibration isolation device of control moment gyro and control moment gyro |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5305981A (en) * | 1991-10-31 | 1994-04-26 | Honeywell Inc. | Multiaxis vibration isolation system |
| US20140312198A1 (en) * | 2013-04-17 | 2014-10-23 | Honeywell International Inc. | Isolators including damper assemblies having variable annuli and spacecraft isolation systems employing the same |
| CN106005484A (en) * | 2016-05-18 | 2016-10-12 | 北京空间飞行器总体设计部 | Vibration reduction and insulation device for parallel truss-type control moment gyros |
| CN212718003U (en) * | 2020-07-09 | 2021-03-16 | 赛洛克流体设备成都有限公司 | Bellows subassembly and pneumatic normally closed bellows valve of heavy-calibre |
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| CN113803396A (en) * | 2021-09-10 | 2021-12-17 | 中国空间技术研究院 | Controllable variable rigidity and variable damping vibration isolation device |
| CN114718988A (en) * | 2022-03-31 | 2022-07-08 | 北京控制工程研究所 | Satellite flywheel vibration isolator based on flexible frame body |
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