CN113708081A - Large-caliber high-flux satellite high-precision foldable reflector - Google Patents
Large-caliber high-flux satellite high-precision foldable reflector Download PDFInfo
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- CN113708081A CN113708081A CN202110832170.6A CN202110832170A CN113708081A CN 113708081 A CN113708081 A CN 113708081A CN 202110832170 A CN202110832170 A CN 202110832170A CN 113708081 A CN113708081 A CN 113708081A
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q15/00—Devices for reflection, refraction, diffraction or polarisation of waves radiated from an antenna, e.g. quasi-optical devices
- H01Q15/14—Reflecting surfaces; Equivalent structures
- H01Q15/16—Reflecting surfaces; Equivalent structures curved in two dimensions, e.g. paraboloidal
- H01Q15/161—Collapsible reflectors
- H01Q15/162—Collapsible reflectors composed of a plurality of rigid panels
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- H01Q1/288—Satellite antennas
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Abstract
一种大口径高通量卫星高精度可折叠反射器，属于卫星反射器技术领域。本发明通过反射面自身的折叠收拢在轨展开，解决了由于卫星平台以及运载工具包络尺寸限制导致的天线反射器口径大小受限的问题；通过高精度、高热稳定性展开定位机构的设计，解决了反射器折叠部分由于展开精度以及在轨高低温变形导致的拼接形面精度较差的问题。本发明3.6m的天线反射器为目前国内首个应用于Ka频段最大口径的高精度星载多波束天线反射器，本发明突破了大口径高精度反射器的设计及制备技术。
A large-diameter high-throughput satellite high-precision foldable reflector belongs to the technical field of satellite reflectors. The invention solves the problem of the limited diameter of the antenna reflector caused by the limitation of the envelope size of the satellite platform and the vehicle through the folding, folding, and on-orbit deployment of the reflecting surface itself; The problem of poor splicing surface accuracy caused by the unfolding accuracy and high and low temperature deformation of the reflector in the folded part of the reflector is solved. The 3.6m antenna reflector of the present invention is the first domestic high-precision space-borne multi-beam antenna reflector with the largest aperture in Ka frequency band, and the invention breaks through the design and preparation technology of large-diameter high-precision reflectors.
Description
Technical Field
The invention relates to a large-caliber high-flux satellite high-precision foldable reflector, and belongs to the technical field of satellite reflectors.
Background
With the rapid increase of the demands of High-speed internet access, airborne communication, remote education, telemedicine, High-definition digital television and the like, the demand of High-Throughput/very High-Throughput Satellite (High/Ultra-High through Satellite-HTS) is increasing. In order to meet the requirements of a new generation of high-flux/very high-flux communication satellite system and support a communication satellite with throughput capacity of Tera-bps magnitude, the ultra-large capacity multi-beam antenna technology and product development are rapidly developed.
High-throughput/very high-throughput communication satellite multi-beam antennas need to meet the following requirements:
1) the need for large aperture antenna reflectors
The broadband communication satellite develops to ultra-large capacity and wide area coverage, and the key technology of the broadband communication satellite is a multi-beam antenna technology matched with the wide area large capacity requirement. When the multi-beam antenna coverage area is fixed, in order to meet the requirement of a high-flux/very high-flux satellite, on one hand, a broadband frequency resource is adopted, and the frequency multiplexing times are increased; on the other hand, it is desirable to have very narrow beams to maximize the number of beams in the coverage area. At present, the wave beam width of a multi-beam antenna successfully applied to the orbit at home and abroad is about 0.6-1.2 degrees, the communication capacity is concentrated in dozens to hundreds of Gbps, and the corresponding reflector caliber is about 1.5-2.6 m; when the satellite communication capacity is increased to be Tera-bps of 500Gbps or even higher, the number of antenna beams reaches hundreds, the beam width is about 0.2-0.4 degrees, the beam width is suitable for the satellite communication capacity, the projection aperture of the reflector reaches about 3.0-5.0 m, and the development of a large-aperture reflector becomes the key of a high-flux/very-high-flux multi-beam antenna technology.
2) Requirement for folding and accommodating function of antenna reflector
The aperture size of the antenna is limited by the size of a communication satellite platform and the envelope size of a rocket fairing, the size of the communication cabin in the width direction (Y direction) of domestic mainstream communication satellite platforms such as DFH-4 and DFH-4E series satellite platforms is 2100mm, a carrier adopts CZ-3B, the net envelope size phi 3650mm of the satellite is allowed, and the size of the maximum width direction of the reflector is required to be smaller than 2200mm according to the layout design requirement of the traditional communication satellite antenna; the dimension of the communication cabin of the DFH-5 satellite platform in the width direction of the east-west cabin plate is 2700mm, the clear envelope dimension of the carrier CZ-5 allowed satellite is phi 4500mm, and for the antenna with the caliber of more than 3m, the platform space also hardly meets the layout requirement of the antenna with the caliber of more than 3 m. Although flexible antennas in China have extremely high storage ratio at present, the high-flux multi-beam antenna receiving working frequency band requires more than 30GHz Ka frequency band, the flexible mesh surface antenna is limited by the problems of working surface metal mesh weaving density, shape surface precision control and the like at present, the problems of directional diagram distortion and large difference loss can be caused by the application of more than 30GHz, and therefore the current international mainstream 3-5 m high-pass satellite large-aperture antenna is mainly designed and applied to a solid surface antenna. The invention provides a high-precision foldable reflector structure in order to meet the requirement of the satellite layout space of a future high-flux large-caliber antenna reflector, wherein the reflector has the functions of folding, storing and unfolding in orbit, namely: the folded reflector is in a folded state when the satellite transmits, the envelope limiting condition of the platform fairing is met, the antenna is unfolded for the second time through the folded part of the reflector after being unfolded in orbit, the unfolded position of the antenna is fixed through the high-precision unfolding positioning mechanism, and the precision requirement of the spliced shape surface of the reflector formed after the folded part is unfolded is guaranteed.
3) The need for high precision, high thermal stability reflectors
The high-flux/very high-flux multi-beam antenna has the characteristics of large number of beams, high gain, narrow beams and the like, and puts higher requirements on indexes such as processing profile precision of a reflector, profile deformation and pointing deviation in high and low temperature environments and the like. The traditional shaped antenna can meet the requirement of electrical performance when the surface accuracy is less than 50 times of the wavelength, has higher requirement on the surface accuracy for high-frequency multi-beam, needs to be better than more than 100 times of the high-frequency wavelength, and has higher requirement on the surface distribution uniformity because the feed sources at different positions of the multi-beam feed source array are different by utilizing the areas of the reflecting surface. The multi-beam antenna reflector is mainly applied to a high-flux satellite with the beam width of 0.2-0.4 degrees, the pointing accuracy change caused by the in-orbit thermal deformation is controlled to be about 0.02-0.04 degrees, otherwise, the marginal gain of a beam coverage area is reduced by at least 2-3 dB, and the C/I performance is deteriorated due to the lifting of an antenna side lobe. Meanwhile, considering that the expansion angle error of the folding part of the reflector in the rail cold and hot environment also has great influence on the overall shape and surface precision of the reflector, an expansion positioning mechanism with high thermal precision and high thermal stability needs to be designed to meet the use requirement of the antenna in the rail environment.
Based on the above requirements, the development of an antenna reflector with a large diameter (3-5 m), foldable storage, high profile precision and high thermal stability is a technical problem which needs to be solved urgently.
Disclosure of Invention
The technical problem solved by the invention is as follows: the defects of the prior art are overcome, the high-flux satellite large-caliber high-precision foldable reflector is provided, and the following technical problems are solved:
(1) the 3.6m antenna reflector is the first high-precision satellite-borne multi-beam antenna reflector applied to the Ka frequency band with the maximum caliber in China at present, and the invention breaks through the design and preparation technology of a large-caliber high-precision reflector;
(2) the problem that the aperture of an antenna reflector is limited due to the limitation of the envelope size of a satellite platform and a carrier is solved by folding and unfolding the reflecting surface on the orbit;
(3) by the design of the unfolding positioning mechanism with high precision and high thermal stability, the problem that the folding part of the reflector has poor precision of the spliced surface due to the unfolding precision and the high and low temperature deformation in orbit is solved;
the technical solution of the invention is as follows: a high-precision foldable reflector for a large-caliber high-flux satellite comprises a main body plate, a foldable plate, a spring unfolding mechanism, an unfolding positioning mechanism and a folding locker;
the folding plates are fixed on two sides of the back plate of the main body plate through the folding locking devices respectively when being folded, the folding locking devices are unlocked when being unfolded, the folding plates are driven to be unfolded through the spring unfolding mechanism, and the unfolding positions and the unfolding angles of the folding plates are limited by the unfolding positioning mechanism, so that the front surfaces of the folding plates and the front surface of the main body plate form a reflecting surface;
the spring unfolding mechanism is a modularized integrated component of a volute spring, a transmission gear train and an escapement mechanism and provides unfolding power with constant rotating speed for the folding plate;
the unfolding positioning mechanism comprises a positioning stop block and a stop pin, the stop block limits an unfolding component arranged on the frame-shaped back frame of the folding plate, the stop pin moves downwards under the action of a compression spring to limit the unfolding locking component in a fixed clamping groove, and the positioning with the unfolding component is realized; the folding locking device fixes the back frame of the folding plate on the main body plate through the locking rod.
Further, the gap between the folding plate and the main body plate is not more than 5 mm.
Furthermore, the folding locker and the folding plate back frame connecting joint are of an integrated structure.
Furthermore, the folding plate is provided with two parallel spring unfolding mechanisms which are respectively arranged at two ends of the reflector in the length direction.
Further, the main body plate comprises a plurality of rectangular pipe fittings, the rectangular pipe fittings form a frame-shaped back frame, and the frame-shaped back frame is connected with the reflecting surface through a plurality of L-shaped angle pieces which are distributed dispersedly.
Further, the material of the frame-type back frame rectangular pipe fitting is a high-modulus M40J epoxy resin system.
Furthermore, a positioning stop block and a stop pin in the unfolding positioning mechanism are made of titanium alloy materials, and an unfolding component in the folding plate is made of carbon fiber composite materials.
Furthermore, the reflecting surfaces of the main body plate and the folding plate are both of honeycomb sandwich structures of the carbon fiber composite material panel aluminum honeycomb core.
Furthermore, the front and rear carbon fiber composite material panels of the main body plate and the folding plate are formed by adopting a sub-block splicing forming method; the sub-block splicing and forming method is particularly a one-way belt local blocking and forming method.
Furthermore, the reflecting surface of the main body plate is formed by splicing eleven honeycombs, the L direction of the central partitioned honeycomb is consistent with the X axis of the long edge of the paraboloid of the reflector, and the W directions of the peripheral partitioned honeycombs are distributed along the center to the peripheral radiation direction; the folded plate is in a long strip shape and is formed by splicing three sub-plates, and the L direction of the honeycomb is consistent with the X axis of the long edge of the paraboloid of the reflector.
Compared with the prior art, the invention has the advantages that:
(1) folding, folding and unfolding design of the large-caliber reflector:
the design methods of blocking, splicing, folding, unfolding, locking and the like of the reflector are provided from the aspects of reflector blocking and splicing technology, reflector folding, unfolding and the like, are suitable for the limitation of the installation size of the cabin plate of the domestic existing satellite platform and the envelope size of the fairing, and meet the requirements of a new generation of high-flux/very high-flux communication satellite system.
(2) The design of the shape surface splicing stability of the antenna in the unfolding state:
by analyzing the principle and the structure size of the reflector unfolding positioning mechanism, sensitive size factors influencing the thermal deformation of the unfolding positioning mechanism in the rail are found, and the unfolding positioning mechanism after optimized design meets the shape surface precision requirement after splicing of the reflectors and the on-rail application under high and low temperatures.
(3) The design and processing method of the large-caliber high-precision reflector comprises the following steps:
the design of high-precision reflecting surfaces and the design of thermal stability are developed from the aspects of sub-block splicing and forming technology of front and rear panels of a reflector, splicing technology of a honeycomb core of the reflector, optimization of a frame type back frame of the reflector and the like, and the manufacturing precision of the reflecting surfaces is met while the in-orbit pointing precision of the antenna is ensured.
Drawings
FIG. 1 is a schematic view of a reflector structure according to the present invention; 1-main body plate; 2. 3-folding the plates 1, 2; 4-spring deployment mechanism; 5, unfolding a positioning mechanism; 6, folding the locking device;
FIG. 2 is a schematic diagram of the reflector of the present invention in a deployed state on a DFH-4E satellite
FIG. 3 is a schematic diagram of the reflector of the present invention in a folded state in a DFH-4E satellite; 7-an antenna locking and releasing device mounted on the satellite platform;
FIG. 4 is a simulation model diagram of the size of the abutted seam of the reflector according to the present invention;
FIG. 5 is a schematic view of the reflector of the present invention in a closed and locked state; 8, locking the angle box, and locking the folding plates (2, 3) to the frame-shaped back frame of the main body plate (1) by matching with the furling locker (6);
FIG. 6 is a schematic view of the integrated design of the folding lock integrated with the joint of the back frame of the folding plate according to the present invention;
FIG. 7 is a schematic view of the spring deployment mechanism of the present invention;
FIG. 8 is a schematic diagram of the movement of the positioning mechanism after the antenna is deployed; 9-positioning stop (one of the parts of the unfolding positioning mechanism); 10-stop pin (one of the deployment positioning mechanism components); 11-unfolding the component (mounted on the folding plate frame type back frame);
FIG. 9 is a schematic view of the deployment positioning mechanism of the present invention;
FIG. 10 is a schematic diagram showing the change of the rotation angle of the unfolding positioning mechanism of the aluminum alloy part along with the size of L2 under the low-temperature working condition of the invention;
FIG. 11 is a schematic view of the deployment positioning mechanism of the present invention after its preferred design;
FIG. 12 is a schematic view of a block molding structure of the reflector of the present invention;
FIG. 13 is a schematic view of a honeycomb core splice of the reflector of the present invention;
FIG. 14 is a schematic view of a frame-type back frame structure according to the present invention.
Detailed Description
In order to better understand the technical solutions, the technical solutions of the present application are described in detail below with reference to the drawings and specific embodiments, and it should be understood that the specific features in the embodiments and examples of the present application are detailed descriptions of the technical solutions of the present application, and are not limitations of the technical solutions of the present application, and the technical features in the embodiments and examples of the present application may be combined with each other without conflict.
The following describes a large-caliber high-throughput satellite high-precision foldable reflector provided by an embodiment of the present application in further detail with reference to the drawings (as shown in fig. 1 to 14).
The invention proposes:
(1) folding, folding and unfolding design of the large-caliber reflector:
the design methods of blocking, splicing, folding, unfolding, locking and the like of the reflector are provided from the aspects of reflector blocking and splicing technology, reflector folding, unfolding scheme design and the like, are suitable for the limitation of the installation size of the cabin plate of the domestic existing satellite platform and the envelope size of the fairing, and meet the requirements of a new generation of high-flux/very high-flux communication satellite system large-aperture antenna reflector.
(2) The design of the shape surface splicing stability of the antenna in the unfolding state: by analyzing the principle and the structure size of the reflector unfolding positioning mechanism, sensitive size factors influencing the thermal deformation of the unfolding positioning mechanism in the rail are found, so that the unfolding positioning mechanism after optimized design meets the shape surface precision requirement after splicing of the reflectors and the on-rail application under high and low temperatures.
(3) The design and processing method of the large-caliber high-precision reflector comprises the following steps: the design of high-precision reflecting surfaces and the design of thermal stability are developed from the aspects of sub-block splicing and forming technology of front and rear panels of a reflector, splicing technology of a honeycomb core of the reflector, optimization of a frame type back frame of the reflector and the like, and the manufacturing precision of the reflecting surfaces is met while the in-orbit pointing precision of the antenna is ensured.
The invention mainly aims at a foldable and storable large-caliber antenna reflector, meets the layout and installation requirements of a satellite platform by folding and furling, and ensures the high precision of the integral shape of the antenna reflector by a high-precision unfolding and positioning mechanism after an on-orbit folding part is unfolded; other improvements to the process of machining reflectors with high dimensional accuracy are associated with certain published documents and patents.
In the solution provided in the embodiment of the present application, the reflector mainly includes five parts, namely a main body plate 1, folding plates 2 and 3 (2 in total, mirror symmetry), a spring unfolding mechanism 4, a unfolding positioning mechanism 5, and a folding lock 6, and a schematic structural diagram of the reflector is shown in fig. 1. The aperture of the unfolded projection of the reflector is 3.6m, the size of the folded reflector is 2.2m, and the size of the folding plate is 0.7m, so that the requirement that the minimum transverse size of the DFH-4 and DFH-4E of the conventional mainstream communication satellite platform is less than or equal to 2.2m is met. Schematic diagrams of the antenna in the layout, the unfolding state and the folding state on the DFH-4E satellite platform are respectively shown in figures 2 and 3, a locking and releasing device 7 used for installing the antenna reflector on the satellite platform is completely positioned within the installation envelope range of a DFH-4E satellite cabin plate, the requirements of a platform installation space are met, and the reflector can also meet the use requirements of a long-focus antenna through the folding design of an unfolding arm.
Because the reflector spliced by the main body plate and the folding plates 1 and 2 has a certain splicing gap at the splicing position, radio frequency performance simulation analysis is specially carried out for determining the influence of the spliced gap on the radio frequency performance of the reflector. When the gap after main part board and folded sheet concatenation is 5mm, according to the simulation analysis result: the splicing gaps between the reflectors only have weak influence on the beam far side lobe performance under the multi-beam application, and the main performance such as gain and cross polarization performance are not obviously changed, so that the block splicing mode of the reflectors can be suitable for folding and folding designs of Ka, Ku and other large-caliber reflectors. The simulation model diagram of the size of the abutted seam of the reflector is shown in figure 4.
Further, in a possible implementation manner, the reflector folding state is locked by a folding locker installed on a reflector back frame, and each folding plate is provided with two folding lockers, as shown in fig. 5, the folding locker is designed by adopting an integrated design of a connection joint with the folding plate back frame, so that the mounting space of the folding locker is saved, and meanwhile, a sufficient unlocking space is provided for the pin pulling and ejecting after the locking rod is cut off, as shown in fig. 6.
The power source of the antenna rotating from the folded state to the unfolded state on the track is a spring unfolding mechanism, each folding plate is provided with two parallel spring unfolding mechanisms which are respectively arranged at two ends of the reflector in the length direction, and by combining the installation layout of two folding lockers, a single folding plate can form a stable 4-point support in a trapezoidal state, so that the first-order base frequency of the reflector is improved.
The fixed end and the output end of the spring unfolding mechanism are respectively arranged on the frame-shaped back frame of the main body plate and the folding plate, the spring unfolding mechanism comprises a volute spiral spring serving as a driving source, a transmission gear train capable of amplifying torsional moment of the spring and an escapement mechanism for controlling output speed of an output shaft, three main components are jointly integrated in the spring unfolding mechanism through modular design, the weight of the mechanism is reduced, and the installation space is saved.
In a mode that can realize, two folded sheets of reflector need cooperate the expansion positioning mechanism under spring deployment mechanism drive to make it stop to preset position, because the folded sheet expandes the space limitedly, the expansion positioning mechanism has adopted the design that integrates, direct mount is in the bottom of spring deployment mechanism, when installing in the expansion part of folded sheet and rotate to the anticipated position, the dog that expandes positioning mechanism carries on spacingly to expanding the part, then the backing pin moves down under compression spring's effect, prescribe the expansion part in fixed draw-in groove, realize with the accurate location of expanding the part (the expansion positioning mechanism after the debugging can realize the accurate location of repeated expansion precision 0.01 °), wherein adopt wedge fit mode between backing pin and the movable part, guarantee that the cooperation of movable part in the draw-in groove is inseparable. Based on the design of the existing 3.6m reflector, the distance between the edge of the folding plate and the center of the rotating shaft of the spring unfolding mechanism is about 800mm, the locking angle deviation of the unfolding positioning mechanism of 0.01 degrees only has the influence of 800 xsin (0.01 degrees) to 0.14mm on the edge displacement of the reflector, the error converted into the root mean square value is smaller, and the requirement of the splicing precision of the antenna after being unfolded in a normal temperature state can be met. The schematic structure diagram of the antenna unfolding process and the unfolding positioning mechanism is shown in fig. 7, and the schematic positioning diagram of the unfolding positioning mechanism is shown in fig. 8.
In order to meet the requirement of maintaining the precision of the unfolding positioning mechanism in a wider temperature range of the rail, the structural size of the unfolding positioning mechanism is analyzed, and size factors influencing the thermal deformation of the unfolding positioning mechanism in the rail are found.
In order to adapt to the minimum size of the antenna expansion envelope, the spatial layout position of the expansion positioning mechanism is determined, the height size H from the rotating shaft to the clamping groove is 97.5mm, the size L1 from the positioning stop dog 9 to the installation position is 48mm, and the calculation is still carried out according to aluminum alloy, so that under the condition that the rail extreme low temperature is-160 ℃, the size of the thermal deformation reduction of the positioning stop dog 9 is as follows:
delta L1 ═ 48X 24e-6 (coefficient of thermal expansion of aluminum alloy). times.180 ℃ (temperature difference from room temperature 20 ℃), 0.2mm
The size of L2 is 0-48 mm, alpha angle is calculated by taking 0.01mm as increment, and the calculation result shows that:
at L2 ═ 0mm, the minimum angle change α min ═ 0.11753 ° (at this time, the displacement of the folded plate edge is 800 × sin (0.11753 °) 1.64mm, and the deformation of the reflector splicing surface due to thermal deformation of the unfolded positioning mechanism is still large).
The schematic diagram of the change of the corner of the aluminum alloy part unfolding and positioning mechanism along with the L2 size under the low-temperature working condition is shown in FIG. 9: initial design size L2-20 mm, α -0.11756 °; the maximum possible design size L2 is 48mm, alpha is 0.11758 degrees, and the size L2 has very weak influence on angle change, so the thermal deformation size Delta L1 of the aluminum alloy positioning block is the most critical sensitive factor.
From the above calculation results, it is found that the L2 size can be increased as much as possible to reduce the L1 size, and the aluminum alloy material can be replaced with a material having a smaller thermal expansion coefficient to reduce the corner error caused by the thermal deformation of the deployment positioning mechanism, and the titanium alloy material having a thermal expansion coefficient of 10e-6/K is used in the present invention. As shown in fig. 8, since the deployed positioning mechanism is used for positioning the positioning pin with a dimension L of 22.7mm, which cannot be changed, L1-22.7-25.3 mm and L2-20 + 22.7-42.7 mm, the titanium alloy positioning pin 9 has a reduced thermal deformation dimension:
delta L1 ═ 25.3X 10e-6 (coefficient of thermal expansion of aluminum alloy). times.180 ℃ (difference in temperature from room temperature to 20 ℃), 0.045mm
Under the working condition, alpha is 0.026447 degrees, the edge of the folding plate generates displacement 800 × sin (0.026447 degrees) 0.369mm, and the requirement of a profile RMS value is considered, so that the requirement of the profile precision after the foldable reflector is unfolded and positioned can be met.
The antenna unfolding positioning mechanism after the optimization design is shown in fig. 11, the stop pin is made of titanium alloy material, and the unfolding component of the antenna for positioning is made of carbon fiber with the thermal expansion coefficient of 2 e-6/K-3 e-6/K.
In a possible implementation mode, the reflector with a projection aperture of 3.6m is an antenna reflector with the largest aperture of the current high-frequency-band high-flux/very high-flux satellite, the structure composition comprises a reflecting surface and a frame-shaped back frame (including an expansion arm), and besides the manufacturing precision of the shape of the reflecting surface meets the technical requirement, the thermal deformation precision of the reflector and the thermal stability of the frame-shaped back frame of the antenna are required to be ensured, and the on-orbit pointing precision of the antenna is ensured.
The method is common in the molding of 1-2 m high-precision reflectors, but in the molding of 3.6m large-caliber reflectors, the problems of bending, warping, wrinkling and the like are easily formed when overlong unidirectional tapes are integrally laid on the molding edges, the laying angle and the molding precision are affected, the stress in the reflecting surface is large after molding, and extra deformation can be generated under the environment of rail extreme temperature to affect the shape surface precision. In order to solve the problems, the sub-block splicing forming scheme is adopted for forming the front and rear panels of the reflector, namely, the conventional long fiber unidirectional tape integral forming mode is replaced by short unidirectional tape local block forming, small sub-blocks are easier to attach a plane structure and a curved surface shape, the accuracy and the quasi-isotropic design of the layer spreading angle of the reflecting surface are ensured, the residual stress in integral forming is reduced, the forming precision and the on-orbit thermal stability of the reflector are improved, and the overall block dividing schematic diagram of the reflecting surface is shown as 12.
The aluminum honeycomb core used by the reflecting surface is also attached to a plane structure to form a curved surface shape, and the integral bending forming of large-area honeycomb can bring great bending stress to influence the forming precision, so that the bending stress of the honeycomb core is also required to be spliced and reduced in the honeycomb core forming process, the pre-curing forming process is increased, and the shape of the cured honeycomb core is kept approximately consistent with the shape of the plane as much as possible. The size of the honeycomb splicing blocks needs to be selected according to the curvature of the reflecting surface and the maximum displacement after bending, the 3.6m reflector is long in focal length and small in curvature of the reflecting surface, so that the reflecting surface of the main body plate is spliced by 11 honeycombs, the direction of a honeycomb L of the middle block 1 is consistent with the long side X axis of the paraboloid of the reflector, and the directions of the surrounding block honeycombs W are distributed along the center to the peripheral radiation direction; the shape of the folding plate is strip-shaped, so that the folding plate is divided into three blocks which are spliced, and the L direction of the honeycomb is also consistent with the X axis of the long edge of the paraboloid of the reflector. A schematic diagram of the reflector honeycomb mosaic is shown in fig. 13.
In a mode that probably realizes, including frame type back of the body frame design scheme, constitute by the connection of rectangle pipe fitting, the material is the M40J epoxy system of high modulus, adopt the processing of the multidirectional fibre winding of machine to form according to accurate isotropic design, the carbon fiber pipe fitting that the winding formed is than the one-way area and spread the technological fibre angle of pasting and be controlled easily, the fillet around the rectangle pipe fitting is difficult for piling up the one-way area that takes place the deformation, therefore change the better product of formation and design parameter matching, thermal stability can obtain better control. The frame type back frame on the main body plate is connected with the reflecting surface through the plurality of L-shaped angle pieces which are dispersedly arranged, when the extreme temperature load of the rail occurs, the deformation of the frame type back frame and the deformation of the reflecting surface can be decoupled through the flexible L-shaped angle pieces, the material of the frame type back frame made of the rectangular pipe fitting formed by winding the carbon fibers is good in uniformity and high in rigidity, the high stability can be kept on the rail, and the high pointing accuracy of the antenna is kept. A schematic structural view of the frame-shaped back frame is shown in fig. 14.
The invention can realize that the projection aperture of the reflecting surface is 3.6m, the size of the reflector is 2.2m after being folded and folded, and the size of the folding plate is 0.7 m.
It will be apparent to those skilled in the art that various changes and modifications may be made in the present application without departing from the spirit and scope of the application. Thus, if such modifications and variations of the present application fall within the scope of the claims of the present application and their equivalents, the present application is intended to include such modifications and variations as well.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
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| CN114914705A (en) * | 2022-07-14 | 2022-08-16 | 北京航天驭星科技有限公司 | Honeycomb tile type portable reflecting surface structure |
| CN115149275A (en) * | 2022-08-29 | 2022-10-04 | 西安空间无线电技术研究所 | Foldable fixed surface antenna reflector and unfolding method |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114384705A (en) * | 2022-01-13 | 2022-04-22 | 北京工业大学 | Super-large-area coaxial laser coherent array light source self-beam-expanding focusing system and preparation method |
| CN114914705A (en) * | 2022-07-14 | 2022-08-16 | 北京航天驭星科技有限公司 | Honeycomb tile type portable reflecting surface structure |
| CN114914705B (en) * | 2022-07-14 | 2022-09-27 | 北京航天驭星科技有限公司 | Honeycomb tile type portable reflecting surface structure |
| CN115149275A (en) * | 2022-08-29 | 2022-10-04 | 西安空间无线电技术研究所 | Foldable fixed surface antenna reflector and unfolding method |
| CN115149275B (en) * | 2022-08-29 | 2023-03-14 | 西安空间无线电技术研究所 | Foldable fixed-surface antenna reflector and unfolding method |
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