CN105356029A - Planar reflection array antenna based on shape memory polymer composite material hinge and expansion method thereof - Google Patents
Planar reflection array antenna based on shape memory polymer composite material hinge and expansion method thereof Download PDFInfo
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- CN105356029A CN105356029A CN201510756620.2A CN201510756620A CN105356029A CN 105356029 A CN105356029 A CN 105356029A CN 201510756620 A CN201510756620 A CN 201510756620A CN 105356029 A CN105356029 A CN 105356029A
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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
- H01Q1/084—Pivotable antennas
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q19/00—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic
- H01Q19/10—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces
- H01Q19/104—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces using a substantially flat reflector for deflecting the radiated beam, e.g. periscopic antennas
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Abstract
The invention provides a planar reflection array antenna based on a shape memory polymer composite material hinge and an expansion method thereof, belonging to the field of aerospace antenna materials. An existing mechanical or inflatable space extendable antenna structure has the problems of complex mechanical structure, vulnerability and easy damage and high cost. According to the planar reflection array antenna, two curved shape memory polymer laminated plates (2) are fixedly installed between the two fixed end connection pieces (1) of a driving hinge through pressing blocks (12), the two shape memory polymer laminated plates (2) are arranged back to back, and a heating layer (3) is attached to the concave surface of each of the shape memory polymer laminated plates (2). The heating layers (3) drive the shape memory polymer laminated plates (2) such that the shape memory polymer laminated plates (2) become soft, and through a mechanical mode, the shape memory polymer laminated plates (2) are folded to be an O shape or a Z shape. According to the antenna, the impact to a system by driving is small, and an unfolding dramatic impact load is avoided.
Description
Technical field
The present invention relates to a kind of plane reflection array antenna and method of deploying thereof of Shape-based interpolation memory composites hinge.
Background technology
The high speed development of aerospace industry proposes more and more higher requirement to antenna.Because antenna power required is at present higher, the speed of transmission data is larger, therefore the demand of antenna aperture size is also improved gradually, and the bulk of delivery vehicle is limited, therefore this version of deployable antenna can be adopted to reduce space, reduce launch cost.
Traditional space deployable antenna structure adopts the expansion mode of mechanical type or gas-filled type mostly, there is complicated in mechanical structure, is subject to impact failure, high in cost of production shortcoming.Along with the development of shape-memory polymer (ShapeMemoryPolymers, SMPs), there is the intelligent deployed configuration of Shape-based interpolation memory composites (ShapeMemoryPolymerComposites, SMPCs) at present.Due to the feature of the shape memory effect of shape memory polymer composite material and high specific strength thereof, specific stiffness, apply it in deployed configuration, not only effectively to reduce complicated in mechanical structure degree and launch difficulty, and due to the damping of shape memory polymer composite material larger, the expansion of intelligent deployed configuration can be made comparatively mild, alleviate and larger impact is caused to system.
Summary of the invention
The object of the invention is in order to solve existing employing mechanical type or gas-filled type space deployable antenna structure there is complicated in mechanical structure, be easily hit and damage, problem that cost is high, and the plane reflection array antenna that a kind of Shape-based interpolation memory composites hinge drives is proposed.
A kind of plane reflection array antenna of Shape-based interpolation memory composites hinge, it is characterized in that: described plane reflection array antenna comprises one group and drives hinge and a group substrate group, 2-16 substrate in batch is connected with satellite or space station main body by multiple driving hinge, by multiple driving chain connection between substrate in same substrate in batch, and each substrate in batch comprises 2-5 substrate; Each driving hinge comprises two stiff end connectors, by the shape-memory polymer laminate of briquetting fixed installation two panels curved surface between two stiff end connectors, back to setting between two panels shape-memory polymer laminate, the concave surface attachment zone of heating of every plate shape memory polymer laminate, each zone of heating connects power supply; Wherein,
The two ends of each stiff end connector are respectively bare terminal end and socket end, what bare terminal end was relative arranges two panels holding piece, socket end arranges undertaking core, holding piece and curved surface are accepted on core and are arranged installing hole respectively, and curved surface undertaking core has two continuing surfaces matched with shape-memory polymer laminate.
A kind of method of deploying of plane reflection array antenna of Shape-based interpolation memory composites hinge, in the flexible solar battery battle array preparatory stage before transmission, by zone of heating, shape-memory polymer laminate is driven, power supply is that zone of heating is powered, to zone of heating heat temperature raising, and then make the deliquescing of shape-memory polymer laminate, mechanically, O type or Z-type is collapsed into by folding for shape-memory polymer laminate, zone of heating is de-energized afterwards, stop heating, the cooling of shape-memory polymer laminate is hardening, obtain the plane reflection array antenna of folding rounding state, the plane reflection array antenna of rugosity is launched after entering the orbit, give the excitation of shape-memory polymer laminate, after zone of heating heats up again, the shape-memory polymer laminate of folded state deforms, launch to promote plane reflection array antenna gradually to launch, complete expansion process.
Beneficial effect of the present invention is:
The present invention compared with prior art has following beneficial effect: the plane reflection array antenna that Shape-based interpolation memory composites hinge drives has stable motion and the reliable benefit launched in expansion process; Rigidity in Shape-based interpolation memory composites hinge expansion process, intensity are higher, deformation-recovery power is larger, shape retentivity is better, density is low, power and lock function can be rolled into one simultaneously, reduce the complexity of deployable structure, overcome the defect of traditional mechanical space deployable structure and meeting spatial particular/special requirement.In the present invention, the number of substrate can design according to actual demand, and the size of hinge and number can regulate according to the size of substrate and quality.The present invention drives the process of expansion steady, little to the impact of system, specifically avoid the severe impact load of launching to start moment and latter stage, effectively improves the applicability of plane reflection array antenna in all kinds of spacecraft.
Accompanying drawing explanation
Fig. 1 be the present invention relates to drive hinge suit parcel heat-shrink tube time structural representation;
Fig. 2 is the structural representation of the stiff end connector that the present invention relates to;
Fig. 3 is that the present invention is connected with satellite or space station main body, and is the structural representation of closure state;
Fig. 4 is that the present invention is connected with satellite or space station main body, and is the structural representation of deployed condition;
Fig. 5 a is the schematic diagram that original state that operation principle of the present invention relates to fades to the original state of this change procedure of fixed deformation state;
Fig. 5 b be original state that operation principle of the present invention relates to fade to this change procedure of fixed deformation state be warming up to T >=Tt time there is the schematic diagram of external force;
Fig. 5 c be original state that operation principle of the present invention relates to fade to this change procedure of fixed deformation state be cooled to the schematic diagram that T<Tt keeps restraining force;
Fig. 5 d is the schematic diagram that temperature T<Tt that original state that operation principle of the present invention relates to fades to this change procedure of fixed deformation state keeps deformation states;
Fig. 5 e is the schematic diagram being warming up to T >=Tt recoverable force that fixed deformation that operation principle of the present invention relates to returns back to original this change procedure of state;
Fig. 5 f is the schematic diagram that temperature T<Tt that fixed deformation that operation principle of the present invention relates to returns back to original this change procedure of state recovers original state;
Embodiment
Embodiment one:
The plane reflection array antenna of the Shape-based interpolation memory composites hinge of present embodiment, as shown in Figure 1, Figure 3 and Figure 4, described plane reflection array antenna comprises one group and drives hinge 8 and a group substrate group 9,2-16 substrate in batch 9 is connected with satellite or space station main body 10 by multiple driving hinge, connected by multiple driving hinge 8 between substrate 11 in same substrate in batch, and each substrate in batch 9 comprises 2-5 substrate 11; Each driving hinge 8 comprises two stiff end connectors 1, fixedly mounted the shape-memory polymer laminate 2 of two panels curved surface by briquetting 12 between two stiff end connectors 1, back to setting between two panels shape-memory polymer laminate 2, the concave surface attachment zone of heating 3 of every plate shape memory polymer laminate 2, each zone of heating 3 connects power supply 4; Wherein,
The two ends of each stiff end connector 1 are respectively bare terminal end and socket end, what bare terminal end was relative arranges two panels holding piece 6, socket end is arranged accepts core 7, holding piece 6 and curved surface are accepted on core 7 and are arranged installing hole 13 respectively, and curved surface undertaking core 7 has two continuing surfaces matched with shape-memory polymer laminate 2.
One in the making material selection titanium alloy of described stiff end connector 1, aluminium alloy, epoxy matrix composite or cyanate ester based composite material.
Embodiment two:
With embodiment one unlike, the plane reflection array antenna of the Shape-based interpolation memory composites hinge of present embodiment, described in every sheet, the matrix of shape-memory polymer laminate 2 is shape-memory polymer, and the embedding wild phase of inner bag is fibre reinforced composites or particulate reinforced composite; Wherein, the material of wild phase is glass fibre, carbon fiber, aramid fiber, boron fibre, graphite powder, nickel powder or carbon nano-tube; The transition temperature Tt (transitiontemperature) of shape-memory polymer designs by changing material mixture ratio, to meet work requirements, when for high rail work, the transition temperature Tt of shape-memory polymer is for being greater than 170 DEG C, be less than 300 DEG C, when lower than low rail work, the transition temperature Tt of shape-memory polymer is greater than 100 DEG C, is less than 200 DEG C.
Embodiment three:
With embodiment one or two unlike, the plane reflection array antenna of the Shape-based interpolation memory composites hinge of present embodiment, described in every sheet, the cross section of shape-memory polymer laminate 2 is rectangle or circular arc; Wherein, when the cross section of described shape-memory polymer laminate 2 is circular arc, arc chord angle corresponding to circular arc is 90 °-180 °.
Embodiment four:
With embodiment three unlike, the plane reflection array antenna of the Shape-based interpolation memory composites hinge of present embodiment, described zone of heating 3 is the one in embedding resistance wire, the conducting resinl of brushing or the Electric radiant Heating Film of stickup.
Embodiment five:
With embodiment one, two or four unlike, the plane reflection array antenna of the Shape-based interpolation memory composites hinge of present embodiment, when described thermosphere 3 is the Electric radiant Heating Film of pasting, paste the shape-memory polymer laminate 2 outer wrap heat-shrink tube 5 of zone of heating 3, heat-shrink tube 5 outside suit heat-barrier material simultaneously in shape-memory polymer laminate 2 side or aluminium foil, dispel the heat with shape-memory polymer laminate 2 to reduce zone of heating 3.
Embodiment six:
With embodiment five unlike, the plane reflection array antenna of the Shape-based interpolation memory composites hinge of present embodiment, described substrate in batch 9 drives hinge 8 to be connected with satellite or space station main body 10 by 2-6, drives hinge 8 to connect between the substrate 11 in same substrate in batch 9 by 2-6.
Embodiment seven:
With embodiment one, two, four or six unlike, the plane reflection array antenna of the Shape-based interpolation memory composites hinge of present embodiment, adopts the arrangement mode of tandem or parallel connection between the substrate 11 in described same substrate in batch 9.
Embodiment eight:
With embodiment seven unlike, the plane reflection array antenna of the Shape-based interpolation memory composites hinge of present embodiment, sensor installation 14 on each described driving hinge 8, to determine the accuracy and runtime in shape memory polymer composite material hinge expansion process.
Embodiment nine:
A kind of method of deploying utilizing the plane reflection array antenna of the Shape-based interpolation memory composites hinge of above-mentioned any execution mode, in the flexible solar battery battle array preparatory stage before transmission, driven by zone of heating 3 pairs of shape-memory polymer laminates 2, power supply 4 is powered for zone of heating 3, to zone of heating 3 heat temperature raising, and then make shape-memory polymer laminate 2 deliquescing, mechanically, O type or Z-type is collapsed into by folding for shape-memory polymer laminate 2, zone of heating 3 is de-energized afterwards, stop heating, shape-memory polymer laminate 2 cools hardening, obtain the plane reflection array antenna of folding rounding state, the plane reflection array antenna of rugosity is launched after entering the orbit, give shape-memory polymer laminate 2 to encourage, after zone of heating 3 heats up again, the shape-memory polymer laminate 2 of folded state deforms, launch to promote plane reflection array antenna gradually to launch, complete expansion process.The mode heated to zone of heating 3 is directly heating, the heating of embedded resistors silk, the heating of outer painting conducting resinl or paste heated by electrothermal film outward, when outer subsides Electric radiant Heating Film heats, paste the shape-memory polymer laminate 2 outer wrap heat-shrink tube 5 of zone of heating 3, the heat-shrink tube 5 outside suit heat-barrier material simultaneously in shape-memory polymer laminate 2 side or aluminium foil.
Embodiment ten:
With embodiment nine unlike, the method of deploying of the plane reflection array antenna of the Shape-based interpolation memory composites hinge of present embodiment, simultaneously the expansion mode of described plane reflection array antenna is launched by each substrate 11, or substrate 11 classification launches one by one.
The present invention also can have other various embodiments; when not deviating from the present invention's spirit and essence thereof; those skilled in the art are when making various corresponding change and distortion according to the present invention, but these change accordingly and are out of shape the protection range that all should belong to the claim appended by the present invention.
Claims (10)
1. the plane reflection array antenna of a Shape-based interpolation memory composites hinge, it is characterized in that: described plane reflection array antenna comprises one group and drives hinge (8) and a group substrate group (9), 2-16 substrate in batch (9) is connected with satellite or space station main body (10) by multiple driving hinge, connected by multiple driving hinge (8) between substrate (11) in same substrate in batch, and each substrate in batch (9) comprises 2-5 substrate (11); Each driving hinge (8) comprises two stiff end connectors (1), by the shape-memory polymer laminate (2) of briquetting (12) fixed installation two panels curved surface between two stiff end connectors (1), back to setting between two panels shape-memory polymer laminate (2), concave surface attachment zone of heating (3) of every plate shape memory polymer laminate (2), each zone of heating (3) connects power supply (4); Wherein,
The two ends of each stiff end connector (1) are respectively bare terminal end and socket end, what bare terminal end was relative arranges two panels holding piece (6), socket end is arranged accepts core (7), holding piece (6) and curved surface are accepted on core (7) and are arranged installing hole (13) respectively, and curved surface undertaking core (7) has two continuing surfaces matched with shape-memory polymer laminate (2).
2. the plane reflection array antenna of Shape-based interpolation memory composites hinge according to claim 1, it is characterized in that: described in every sheet, the matrix of shape-memory polymer laminate (2) is shape-memory polymer, the embedding wild phase of inner bag is fibre reinforced composites or particulate reinforced composite; Wherein, the material of wild phase is glass fibre, carbon fiber, aramid fiber, boron fibre, graphite powder, nickel powder or carbon nano-tube; When high rail work, the transition temperature Tt of shape-memory polymer, for being greater than 170 DEG C, is less than 300 DEG C, and when lower than low rail work, the transition temperature Tt of shape-memory polymer is greater than 100 DEG C, is less than 200 DEG C.
3. the plane reflection array antenna of Shape-based interpolation memory composites hinge according to claim 1 and 2, is characterized in that: described in every sheet, the cross section of shape-memory polymer laminate (2) is rectangle or circular arc; Wherein, when the cross section of described shape-memory polymer laminate (2) is circular arc, arc chord angle corresponding to circular arc is 90 °-180 °.
4. the plane reflection array antenna of Shape-based interpolation memory composites hinge according to claim 3, is characterized in that: described zone of heating (3) is the one in the conducting resinl of embedding resistance wire, brushing or the Electric radiant Heating Film of stickup.
5. the plane reflection array antenna of the Shape-based interpolation memory composites hinge according to claim 1,2 or 4, it is characterized in that: when described thermosphere (3) is the Electric radiant Heating Film of pasting, paste shape-memory polymer laminate (2) the outer wrap heat-shrink tube (5) of zone of heating (3), heat-shrink tube (5) the outside suit heat-barrier material simultaneously in shape-memory polymer laminate (2) side or aluminium foil.
6. the plane reflection array antenna of Shape-based interpolation memory composites hinge according to claim 5, it is characterized in that: described substrate in batch (9) drives hinge (8) to be connected with satellite or space station main body (10) by 2-6, between the substrate (11) in same substrate in batch (9), drive hinge (8) to connect by 2-6.
7. the plane reflection array antenna of the Shape-based interpolation memory composites hinge according to claim 1,2,4 or 6, is characterized in that: the arrangement mode adopting tandem or parallel connection between the substrate (11) in described same substrate in batch (9).
8. the plane reflection array antenna of Shape-based interpolation memory composites hinge according to claim 7, is characterized in that: the upper sensor installation (14) of each described driving hinge (8).
9. the method for deploying of the plane reflection array antenna of the Shape-based interpolation memory composites hinge described in above-mentioned any claim, it is characterized in that: in the flexible solar battery battle array preparatory stage before transmission, by zone of heating (3), shape-memory polymer laminate (2) is driven, power supply (4) is zone of heating (3) power supply, to zone of heating (3) heat temperature raising, and then make shape-memory polymer laminate (2) deliquescing, mechanically, O type or Z-type is collapsed into by folding for shape-memory polymer laminate (2), zone of heating (3) is de-energized afterwards, stop heating, shape-memory polymer laminate (2) cools hardening, obtain the plane reflection array antenna of folding rounding state, the plane reflection array antenna of rugosity is launched after entering the orbit, give shape-memory polymer laminate (2) excitation, after zone of heating (3) heats up again, the shape-memory polymer laminate (2) of folded state deforms, launch to promote plane reflection array antenna gradually to launch, complete expansion process.
10. the method for deploying of the plane reflection array antenna of Shape-based interpolation memory composites hinge according to claim 9, it is characterized in that: simultaneously the expansion mode of described plane reflection array antenna is launched by each substrate (11), or substrate (11) classification launches one by one.
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| CN109466800A (en) * | 2018-12-29 | 2019-03-15 | 哈尔滨工业大学 | A kind of safeguards system of space development mechanism |
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| CN110510150A (en) * | 2018-05-21 | 2019-11-29 | 哈尔滨工业大学 | A kind of spider web capturing structure and its method for catching based on intelligent composite |
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| CN113276440A (en) * | 2021-05-24 | 2021-08-20 | 哈尔滨工业大学 | Preparation method and unfolding and recycling method of thin-wall column shell structure |
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| CN115246998A (en) * | 2022-08-15 | 2022-10-28 | 北京航空航天大学 | Composite material hinge based on folding and expansion of shape memory composite material control |
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