CN111129689B - Vibration reduction component of large-scale self-unfolding satellite antenna - Google Patents
Vibration reduction component of large-scale self-unfolding satellite antenna Download PDFInfo
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- CN111129689B CN111129689B CN202010031018.3A CN202010031018A CN111129689B CN 111129689 B CN111129689 B CN 111129689B CN 202010031018 A CN202010031018 A CN 202010031018A CN 111129689 B CN111129689 B CN 111129689B
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/005—Damping of vibrations; Means for reducing wind-induced forces
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/08—Means for collapsing antennas or parts thereof
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/12—Supports; Mounting means
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/27—Adaptation for use in or on movable bodies
- H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
- H01Q1/288—Satellite antennas
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Abstract
The invention discloses a vibration reduction component of a large self-expansion satellite antenna, which aims to solve the problem of profile accuracy errors caused by vibration in the expansion process and the posture adjustment process after the expansion of the conventional expansion antenna mechanism. Comprises a multi-finger-flap friction damper, a self-resetting elastic support friction damper, an elastic driving hinge and a satellite structure rod piece. The multi-finger-lobe friction damper controls the transverse vibration of the satellite unfolding antenna, comprises a multi-finger-lobe rod, and is tightly pressed on the structural rod piece through an adjustable pressing ring. The self-resetting elastic support friction damper controls axial vibration and comprises metal rubber, a guide rod, an SMA traction wire and an outer sleeve. The elastic driving hinge provides unfolding power through a volute spring, and the unfolding speed and the synchronism are controlled through gears. The satellite structure rod is fixedly connected with other components to ensure the integrity of the unfolded antenna. The invention is used for satellite and space detectors.
Description
Technical Field
The invention relates to the technical field of satellite flexible unfolding mechanisms, in particular to a vibration damping component of a large-scale self-unfolding satellite antenna, and belongs to the technical field of space equipment and equipment.
Background
The development of mobile communication satellites, astronomical detection satellites, geosynchronous observation satellites, military reconnaissance satellites and the like which are provided with large-caliber antennas is a core technology for establishing high-resolution earth observation systems, space-based earth observation and detection systems and other important special items. With the development of satellite technology, large flexible self-expanding antennas gradually develop to two technical characteristics of large expansion size and high profile precision, and the design requirements are higher and higher. Due to the limitation of the payload of the carrier rocket and the size of the fairing, the large satellite unfolding antenna is sent into the space in a folded and compressed state, and is unfolded to be in a required geometric configuration after reaching a preset orbit. Because it is very difficult to improve the profile accuracy and stability of the large-size unfolding antenna, higher requirements are put on the design of the large-size flexible self-unfolding antenna structure and the control stability and control accuracy of the unfolding process. In recent years, research on vibration control methods for satellite-deployed antennas has become one of the focus problems in the field of aerospace science and technology research.
The structural form of the satellite antenna continuously changes in the unfolding process, and the satellite antenna is a typical multi-degree-of-freedom multi-mode system and has complex time-varying characteristics. And the satellite antenna has the characteristics of large size, weak rigidity, low natural frequency, density and the like after being unfolded, coupling vibration is very easy to occur during posture regulation, the unfolded profile precision of the antenna is reduced, the service life of the antenna is prolonged, and therefore an effective vibration control mechanism is needed for control. At present, two main ideas of the research on controlling the vibration of the satellite antenna comprise structural design optimization and external damper control. The design optimization method comprises the steps of obtaining modal performance parameters of the antenna structure by establishing a dynamic model of the antenna structure, finding a component of the antenna which is easy to resonate with a star body, and avoiding the modal resonance of the star body and the antenna by optimizing the scheme of the antenna structure. The method has been studied with high efficiency at home and abroad, and obtains remarkable effect, but the method can not fundamentally solve the difficult problems that the structure optimization and the control strategy are difficult to accurately make due to the time-varying antenna shape in the process of unfolding the antenna, and can not ensure the stability when the antenna is acted by external interference in the whole unfolding process. Therefore, the design of the vibration control system with simple structure and reliable control has important significance for ensuring the stability of the satellite antenna during the unfolding and the profile precision after the unfolding.
Disclosure of Invention
Aiming at the problem of coupling vibration easily generated during the unfolding process of a satellite unfolding antenna and during posture adjustment after the unfolding process, the invention designs a structural rod component, which achieves the vibration suppression effect by adding two friction damper energy dissipation and vibration absorption components into a supporting rod of the satellite.
The technical scheme adopted by the invention is as follows: the vibration reduction component of the large-scale self-unfolding satellite antenna comprises a support rod piece, a multi-finger-flap friction damper, a self-resetting axial damper and a folding and unfolding hinge, wherein the self-resetting axial damper comprises: the support rod piece is used as a basic structural piece and is respectively connected with the self-resetting axial damper and the folding and unfolding hinge, is used as a base body of the multi-finger flap damper and is connected with the multi-finger flap damper through the outer ring locking ring. The multi-finger-flap damper adopts a carbon fiber multi-finger-flap thin-wall circular section structure made of the same material as the support rod piece, the root part of one end of the damping structure is not split and is fixedly connected with the hinged end of the unfolding component, and the rest part of the damping structure is of a multi-finger-flap structure and is pre-pressed on the outer wall of the unfolding component through a locking ring. When the amplitude of the bending vibration generated by the unfolding component reaches a certain value, the finger flap and the inner wall of the unfolding component generate micro-sliding friction and energy dissipation. The self-resetting axial damper consists of an outer sleeve, a damping energy dissipation element, a shape memory alloy wire and a guide shaft. The metal rubber is used as a damping energy dissipation element, when the expansion component vibrates axially, the outer sleeve of the axial damper can extrude the metal rubber, after the metal rubber deforms, the inner metal wires can rub against each other to generate energy dissipation, the sleeve is wound with the shape memory alloy, the reset force in a non-vibration state and the pretightening force of the metal rubber are provided for the axial damper, when the vibration is finished, the stress of the shape memory alloy wires and the stress of the metal rubber are balanced, the axial damper is enabled to recover the initial size under the combined action, and the profile precision and the axial rigidity of the satellite antenna are guaranteed. The folding hinge consists of a volute spiral spring, a synchronous gear, a rotating body, a connecting body and a rotating shaft. The volute spiral spring drives the folding hinge to realize that the antenna unfolding mechanism is unfolded from a folded state, and the synchronous gear ensures the stability and the synchronism of the unfolding process of the antenna unfolding mechanism.
A vibration damping member of a large self-expanding satellite antenna is characterized in that: the device comprises a self-resetting axial damper, two multi-finger-flap friction dampers, a folding and unfolding hinge assembly and two structural rod pieces; the middle part of the vibration reduction component is provided with a self-resetting axial damper, two ends of the self-resetting axial damper are connected with two structural rods, the two multi-finger-flap dampers are respectively sleeved on the two structural rods, the non-flap-splitting part is fixed at one end of the structural rods connected with the self-resetting axial damper, the flap-splitting part is tightly pressed on the structural rods through three outer ring locking rings, and one end of one structural rod, which is not connected with the self-resetting axial damper, is connected with a folding and unfolding hinge assembly.
Each multi-finger-flap damper consists of an outer ring locking ring, a multi-finger-flap pressing plate and a structural rod piece; the multi-finger flap pressing plate is of a multi-finger flap thin-wall circular section structure, the root part of one end of the damping structure is not split and is fixedly connected with the hinged end of the unfolding component, the rest part of the damping structure is of a multi-finger flap structure, the multi-finger flap structure is pre-pressed on the outer wall of the unfolding component through the outer ring locking ring, the number of the outer ring locking rings is three initially, and the number of the outer ring locking rings is adjusted according to different actual states.
Each self-resetting axial damper consists of an outer sleeve, a damping energy dissipation element, a shape memory alloy wire and a guide shaft; the two outer sleeves are in butt joint, annular metal rubber is used as a damping energy dissipation element and penetrates through and is fixed between the two outer sleeves through a guide shaft, a boss is arranged outside the inner wall of each outer sleeve, a through hole is formed outside the boss, and the shape memory alloy wire penetrates through the bosses of the outer sleeves and is wound on the two outer sleeves. One end of the guide shaft is fixed on a boss of one outer sleeve, and the other end of the guide shaft penetrates through the other outer sleeve and is in clearance fit with the boss of the outer sleeve.
Each folding and unfolding hinge component consists of a volute spiral spring, a synchronous gear, a rotating body, a connecting body and a rotating shaft. The two synchronous gears are arranged in parallel, the rotating bodies are fixed on the inner sides of the synchronous gears, and the rotating shafts penetrate through the connecting bodies, the rotating bodies and the synchronous gears. The inner end of the spiral spring is fixed on the rotating shaft, and the outer end of the spiral spring is fixed on the rotating body. The two rotating bodies are respectively fixedly connected with the two radial rib components.
The structural rod piece is made of carbon fiber composite materials.
The multi-finger flap pressing plate is made of carbon fiber composite materials, and the outer ring locking ring is made of rubber materials.
The outer sleeve and the guide shaft are made of carbon fiber composite materials, and the damping energy dissipation element is made of metal rubber materials.
The rotating body, the fixing body, the connecting body, the retainer, the rotating shaft and the synchronous gear are all made of carbon fiber composite materials, and the volute spiral spring is made of shape memory alloy or titanium alloy.
The invention has the beneficial effects that:
1. the self-resetting axial damper in the structural rod component controls the axial vibration of the deployable antenna supporting rod component, and can be self-reset to the initial size in a non-vibration state, so that the axial vibration of the deployable antenna can be inhibited, and the profile accuracy of the deployable antenna can be ensured.
2. The invention controls the transverse vibration of the expandable antenna supporting rod through the multi-finger-lobe damper in the structural rod component, has simple structure and reliable work, can effectively inhibit the transverse vibration of the expandable component, improves the profile precision of the antenna and prolongs the service life of the antenna.
3. The structural rod component designed by the invention has the advantages of simple mechanism, small additional mass, reliable work, small volume after being folded and high storage rate, and can ensure the light weight requirement of the unfolded antenna.
4. The rod component with the designed structure has the characteristics of wide suppression frequency band and large energy dissipation, and has quick response to vibration and good effectiveness.
5. The rod component with the designed structure has an adjustable function, and the threshold value of the friction force can be controlled by adjusting the pre-tightening force of the self-resetting axial damper and the multi-finger-lobe friction damper so as to inhibit the vibration of the satellite antenna in different states.
6. The structural rod piece assembly designed by the invention adopts a modular design, can be conveniently disassembled and replaced, selects parts with different parameters according to different use environments, and has strong expansibility and strong adaptability.
7. The structural rod component designed by the invention is not limited to a satellite antenna unfolding mechanism, and can be applied to other rod structures needing vibration control.
Drawings
Fig. 1 is a schematic view of a vibration damping member of a large self-expanding satellite antenna according to the present invention after being deployed by a radial rib antenna deployment mechanism.
Fig. 2 is a schematic diagram of the vibration damping member of the large self-unfolding satellite antenna according to the present invention after being folded by the unfolding mechanism of the radial rib antenna.
Fig. 3 is a schematic view of the vibration reduction structure of the large self-expanding satellite antenna of the present invention.
Fig. 4 is a schematic structural view of a self-resetting axial damper of a vibration reduction member of a large self-expanding satellite antenna according to the present invention.
Fig. 5 is a structural cross-sectional view of a self-resetting axial damper of a vibration reduction member of a large self-deploying satellite antenna of the present invention.
Fig. 6 is a schematic structural view of a multi-finger-lobe damper of a vibration damping member of a large self-expanding satellite antenna according to the present invention.
Fig. 7 is a schematic view of the folding and unfolding mechanism of the vibration reduction member of the large self-unfolding satellite antenna according to the present invention.
Fig. 8 is a schematic view of an end folding and unfolding mechanism for a vibration reduction member of a large self-unfolding satellite antenna according to the present invention.
Fig. 9 is a schematic view of the bottom folding mechanism of the vibration reduction member of the large self-expanding satellite antenna of the present invention.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings and examples.
The first embodiment is as follows: the vibration damping structure of a large self-expanding satellite antenna according to the present invention will be described by taking a radially ribbed satellite antenna as an example, which is described with reference to fig. 1 to 9. The vibration reduction component of the large-scale self-unfolding satellite antenna comprises four parts, namely a self-resetting axial damper 1, a multi-finger-lobe friction damper 2, a folding and unfolding hinge component 3 and a support rod piece 12; the support rod 12 is used as a basic structural member and is respectively connected with the self-reset axial damper 1 and the folding and unfolding hinge assembly 3, and is used as a base body of the multi-finger flap pressing plate 11 and is connected with the multi-finger flap pressing plate 11 through the outer ring locking ring 10 to jointly form the multi-finger flap friction damper 2. The vibration reduction components of the large self-expanding satellite antenna are sequentially connected to form a radial rib component A. The root of the radial rib component A is unfolded through the retainer mechanism 18, the unfolded radial rib component A is an umbrella rib-shaped antenna structure body, the number of the radial rib components A is six, the radial rib components A are arranged at equal angles according to six directions and extend outwards, the self-resetting axial dampers 1 and the folding and unfolding hinge components 3 are arranged in a staggered mode and connected with the support rod 12, and the multi-finger-lobe friction damper 2 covers the support rod 12. The end folding hinge 5 controls the antenna support rod to be unfolded at the end and locked after being unfolded by 90 degrees. The root folding hinge 4 controls the root of the antenna to be unfolded through a hexagonal retainer 18 uniformly divided at an angle of 60 degrees and is locked after being unfolded at an angle of 90 degrees. The present embodiment provides elastic potential energy as power for the satellite antenna to unfold through the spiral spring 15.
The second embodiment is as follows: as described with reference to fig. 4 and 5, the self-resetting axial damper 1 of the present embodiment is composed of an outer sleeve 8, a metal rubber 9, a shape memory alloy wire 7, and a guide shaft 19. The two outer sleeves 8 are butted, the annular metal rubber 9 is used as a damping energy dissipation element and is fixedly penetrated between the two outer sleeves through a guide shaft 19, and the guide shaft 19 can ensure the radial rigidity and the vibration direction of the damper. The shape memory alloy wire 7 has super-elastic mechanical property, axial pre-tightening force is provided for the metal rubber 9 of the axial damper 1 by winding the shape memory alloy wire on the two outer sleeves 8, when vibration occurs, the vibration can cause the relative position between the two outer sleeves 8 to change, so that the metal rubber 9 is stretched or compressed, and the thin metal wires in the metal rubber 9 rub with each other to generate energy consumption to inhibit the vibration. When the vibration is finished, the pretightening force generated by the extension of the shape memory alloy wire 7 is balanced with the elastic force generated by the compression of the metal rubber 9, so that the axial damper 1 is restored to the initial shape, and the shape precision of the axial direction is kept. In addition, the axial rigidity of the self-resetting axial damper assembly is ensured by the combined action of the shape memory alloy wire 7 and the metal rubber 9.
The third concrete implementation mode: as described with reference to fig. 3 and 6, the multi-finger-flap friction damper 2 of the present embodiment uses a carbon fiber multi-finger-flap thin-walled circular cross-sectional structure made of the same material as the support rod 12 as the multi-finger-flap pressing plate 11, the root of one end of the damping structure is not split and is fixedly connected to the hinged end of the expansion member, and the rest is a multi-finger-flap structure, and is pre-pressed on the outer wall of the expansion member by the outer ring locking ring 10. When the supporting rod 12 vibrates transversely, because the multi-finger-flap press plate 11 and the structural rod 6 have different vibration deformation sizes, relative displacement can be generated between the multi-finger-flap press plate and the structural rod 6, and the outer locking ring 11 applies friction force to the multi-finger-flap friction damper 2 through pretightening force, so that friction energy consumption can be generated between the finger flaps and the supporting rod 12, and vibration is suppressed. When the vibration is finished, the support rod 12 can be restored to the original shape because the elastic deformation force generated by the deformation of the support rod is larger than the pretightening force, and the structural precision is ensured.
Fourth embodiment referring to fig. 3 and 7, the folding hinge 3 of the present embodiment includes a spiral spring 15, a synchronizing gear 17, a rotating body 13, a coupling body 20, and a rotating shaft 14. The spiral spring 15 drives the folding hinge to realize that the antenna unfolding mechanism is unfolded from a folding state, and the synchronous gear 17 ensures the stability and the synchronism of the unfolding process of the antenna unfolding mechanism. The support rod 12 of the satellite antenna is fixedly connected with the rotating bodies 13, and when the rotating bodies on the two sides are unfolded for 90 degrees respectively, the rotating bodies are locked, so that the radial rib component A is maintained at 180 degrees after being unfolded.
The fifth concrete implementation mode: as described with reference to fig. 3 and 8, the end portion folding hinge 5 of the present embodiment is composed of a rotating body 13, a spiral spring 15, a rotating shaft 14, and a fixed body 16. The end folding hinge 5 is required to be folded for 90 degrees and then locked to support a satellite reflecting surface cable net, so that the end folding hinge is designed to rotate at a single side, the other side of the end folding hinge is fixed, the radial rib component A is fixedly connected with the rotating body 13 through the supporting rod 12, unfolding power is provided through the volute spiral spring 15, the rotating body 13 is tightly pressed on the fixing body 16 through sufficient pretightening force after the end folding hinge is unfolded, and the precision of the unfolded molded surface is ensured.
The sixth specific implementation mode: as described with reference to fig. 3 and 9, the base folding hinge 4 of the present embodiment is composed of the holder 18, the rolling element 13, the spiral spring 15, and the rotating shaft 14. The retainer 18 extends outwards in six directions and is arranged at equal angles, the radial rib assemblies A are respectively controlled to expand in six directions, the radial rib assemblies are fixedly connected with the rotating body 13 through the supporting rod 12 and are locked after being expanded for 90 degrees, and the radial rib assemblies are tightly pressed on the retainer 18 through the volute spiral spring 15, so that the profile accuracy of the expanded antenna is ensured.
Claims (5)
1. A vibration damping member of a large self-expanding satellite antenna is characterized in that: the device comprises a self-resetting axial damper, two multi-finger-flap friction dampers, a folding and unfolding hinge assembly and two support rods; the middle part of the vibration reduction component is provided with a self-resetting axial damper, two ends of the self-resetting axial damper are connected with two supporting rod pieces, two multi-finger-flap friction dampers are respectively sleeved on the two supporting rod pieces, the non-flap part is fixed at one end of the supporting rod piece connected with the self-resetting axial damper, the flap part is tightly pressed on the supporting rod pieces through three outer ring locking rings, and one end of one supporting rod piece, which is not connected with the self-resetting axial damper, is connected with a folding and unfolding hinge assembly;
each multi-finger-flap friction damper consists of an outer ring locking ring, a multi-finger-flap pressing plate and a support rod piece; the multi-finger flap pressing plate is of a multi-finger flap thin-wall circular section structure, the root part of one end of the multi-finger flap friction damper is not split and is fixedly connected with the hinged end of the unfolding component, the rest part of the damping structure is of a multi-finger flap structure, the multi-finger flap structure is pre-pressed on the outer wall of the unfolding component through an outer ring locking ring, the number of the outer ring locking rings is three initially, and the number of the outer ring locking rings is adjusted according to different actual states;
each self-resetting axial damper consists of an outer sleeve, a damping energy dissipation element, a shape memory alloy wire and a guide shaft; the two outer sleeves are butted, annular metal rubber serving as a damping energy dissipation element passes through and is fixed between the two outer sleeves through a guide shaft, a boss is arranged outside the inner wall of each outer sleeve, a through hole is formed outside the boss, and the shape memory alloy wire passes through the bosses of the outer sleeves and is wound on the two outer sleeves; one end of the guide shaft is fixed on a boss of one outer sleeve, and the other end of the guide shaft penetrates through the other outer sleeve and is in clearance fit with the boss of the outer sleeve;
each folding and unfolding hinge component consists of a volute spiral spring, a synchronous gear, a rotating body, a connecting body and a rotating shaft; the two synchronous gears are arranged in parallel, the inner sides of the synchronous gears are fixedly provided with rotating bodies, and the rotating shafts penetrate through the connecting bodies, the rotating bodies and the synchronous gears; the inner end of the volute spiral spring is fixed on the rotating shaft, and the outer end of the volute spiral spring is fixed on the rotating body; the two rotating bodies are respectively fixedly connected with the two radial rib components.
2. The vibration damping structure of a large self-expanding satellite antenna according to claim 1, wherein: the support rod is made of carbon fiber composite materials.
3. The vibration damping structure of a large self-expanding satellite antenna according to claim 1, wherein: the multi-finger flap pressing plate is made of carbon fiber composite materials, and the outer ring locking ring is made of rubber materials.
4. The vibration damping structure of a large self-expanding satellite antenna according to claim 1, wherein: the outer sleeve and the guide shaft are made of carbon fiber composite materials, and the damping energy dissipation element is made of metal rubber materials.
5. The vibration damping structure of a large self-expanding satellite antenna according to claim 1, wherein: the rotating body, the fixing body, the connecting body, the retainer, the rotating shaft and the synchronous gear are all made of carbon fiber composite materials, and the volute spiral spring is made of shape memory alloy or titanium alloy.
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| CN202010031018.3A CN111129689B (en) | 2020-01-13 | 2020-01-13 | Vibration reduction component of large-scale self-unfolding satellite antenna |
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| CN113484878B (en) * | 2021-08-19 | 2023-12-05 | 北京云恒科技研究院有限公司 | Beidou navigation signal receiving equipment |
| CN114408218B (en) * | 2022-02-15 | 2024-05-28 | 长沙天仪空间科技研究院有限公司 | Control system of space expandable mechanism |
| CN114430100B (en) * | 2022-02-15 | 2023-10-13 | 长沙天仪空间科技研究院有限公司 | Satellite-borne antenna unfolding control system |
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