CN105071012A - Spatially extendible annular tensioning integrated antenna mechanism - Google Patents
Spatially extendible annular tensioning integrated antenna mechanism Download PDFInfo
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- CN105071012A CN105071012A CN201510446461.6A CN201510446461A CN105071012A CN 105071012 A CN105071012 A CN 105071012A CN 201510446461 A CN201510446461 A CN 201510446461A CN 105071012 A CN105071012 A CN 105071012A
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Abstract
The invention provides a spatially extendible annular tensioning integrated antenna mechanism, relates to antenna mechanisms, and solves the problems that a present extendible annular antenna needs lots of mechanical connection in the folding and unfolding process and further causes high total weight and low unfolding reliability. A main-end fixation member is fixedly connected with one end of a main-end connecting tube via a pin, the other end of the main-end connecting tube is fixedly connected with one end of a carbon fiber tube, two bar-shaped openings are formed in the sidewall of the main-end connecting tube along the length direction, two locking flat springs are arranged correspondingly at the positions of the bar-shaped openings, a drive spring is placed in the carbon fiber tube, an annular groove is formed in the middle portion of a guiding slide block circumferentially, when the antenna mechanism is unfolded, the lower portion of the locking flat springs are clamped in the annular groove of the guiding slide block, the lower end of the guiding slide block is connected with a slide block screw, the guiding slide block is placed at the upper end of the driving spring, an auxiliary-end fixation piece is fixedly connected with the other end of the carbon fiber tube via an auxiliary-end connecting piece, and the amount of tensioning integrated rods is an even number. The antenna mechanism is used in the field of wireless communication.
Description
Technical field
The present invention relates to a kind of telescopic antenna mechanism, be specifically related to the deployable annular stretching integral antenna mechanism in a kind of space, belong to satellite wireless communication field.
Background technology
Along with the development of mankind's space cause, large-scale antenna all plays an important role in multiple-task, as fields such as earth observation, survey of deep space, radio astronomys, in telecommunication, played leading role especially, therefore the maximization of antenna becomes the study hotspot of deployable antenna.In order to meet the capacity requirement of reflector, large aperture antenna must make extensible form.This deployable antenna has very high requirement to mechanism, thermal environment and radio frequency, but also will meet expansion reliability, is therefore a challenging many-sided design problem.Although the Large Deployable loop aerial of current application can realize launching function, but comprise a large amount of interconnective rigid member, which results in and need a large amount of mechanical connections in the process launched and draw in, and these mechanical connections not only increase total quality, and greatly reduce the reliability of expansion, become the bottleneck of deployable antenna large scale development.
To sum up, existing deployable loop aerial comprises a large amount of interconnective rigid member, in the process launched and draw in, need a large amount of mechanical connections, causes total quality reliability that is large and that launch low.
Summary of the invention
The present invention solves existing deployable loop aerial to need a large amount of mechanical connections in the process launched and draw in, causes the problem that total quality reliability that is large and that launch is low, and then provides a kind of space deployable annular stretching integral antenna mechanism.
The present invention solves the problems of the technologies described above the technical scheme taked to be:
The deployable annular stretching integral antenna mechanism in space of the present invention comprises middle tensioning apparatus, delayed release device, many stretching integral rod members and Duo Gen side tension cords;
Middle tensioning apparatus comprises tensioning spring and two thin slices, and two thin slices be arranged in parallel up and down, and tensioning spring is vertically arranged between the two sheets;
Described delayed release device comprises two band damping slowly-releasing pulleys;
Every root stretching integral rod member comprises end suspension ring, main side firmware, main side tube connector, guide shoe, slide block screw, driving spring, carbon fiber pipe, secondary end connection, secondary end firmware and two stay springs, main side firmware is affixed by one end of pin and main side tube connector, end suspension ring are threaded on the firmware of main side, the other end of main side tube connector and one end of carbon fiber pipe affixed, the sidewall of main side tube connector is processed with two strip gabs along its length, each strip gab place correspondence is provided with a stay spring, driving spring is positioned at carbon fiber pipe, the middle part of guide shoe is processed with annular groove along its circumference, when antenna mechanism is launched, the bottom of stay spring is installed on the annular groove place of guide shoe, the lower end of guide shoe is connected with slide block screw, guide shoe is positioned at the upper end of driving spring, secondary end firmware is packed in the other end of carbon fiber pipe by secondary end connection, the quantity of stretching integral rod member is even number,
Many side tension cords comprise the fast rope of control, lower control speed rope, multiple saddle rope, multiple oblique cord, multiple limits rope, multiple perpendicular rope and multiple middle side tension cords;
Many stretching integral rod members are along the circumferential direction arranged, wherein the stretching integral rod member of half along the circumferential direction tilts uniform setting clockwise, remaining half stretching integral rod member along the circumferential direction tilts uniform setting counterclockwise, the end suspension ring of the stretching integral rod member be obliquely installed clockwise are arranged upward, the end suspension ring of the stretching integral rod member be obliquely installed counterclockwise are arranged down, main side firmware and secondary the end between firmware of two stretching integral rod members of adjacent same rotation direction are connected with a perpendicular rope, firmware is held through secondary successively in one end of perpendicular rope, driving spring is connected with the lower end of guide shoe, a Gen Biansuo is connected with between two main side firmwares of two stretching integral rod members of adjacent same rotation direction, end suspension ring successively through clockwise stretching integral rod member are the fast rope of upper control, end suspension ring successively through counterclockwise stretching integral rod member are the fast rope of lower control, the fast rope of upper control and lower control speed rope are wrapped on corresponding band damping slowly-releasing pulley, main side firmware and secondary the end between firmware of two stretching integral rod members of adjacent different rotation direction are connected with an oblique cord, a saddle rope is connected with between two secondary end firmwares of two stretching integral rod members of adjacent different rotation direction, middle tensioning apparatus is positioned at the center of many stretching integral rod members, the main side firmware of each stretching integral rod member be obliquely installed clockwise and side tension cords in the middle of be connected with between the thin slice of top, the main side firmware of each stretching integral rod member be obliquely installed counterclockwise and side tension cords in the middle of be connected with between the thin slice of below.
The present invention has following beneficial effect:
The deployable annular stretching integral antenna mechanism in space of the present invention is only made up of stretching integral rod member and rope, and compared with existing sky thread stretching mechanism, quality reduces greatly, and bore is larger, and its light-weighted advantage is more obvious;
The deployable annular stretching integral antenna mechanism in space of the present invention does not need motor to drive, driving spring provides power for expansion of the present invention and gathering action, launches that motion is simple, reliability is high, and it is simple that mechanism structure is received in exhibition, launch to control simply, antenna launches to have synchronism;
The present invention also has rigidity in expansion process, has strainer to improve entire physical rigidity, make day Line stiffness secure and can realize steady expansion after expansion terminates;
Antenna mechanism Stability Analysis of Structures of the present invention, can ensure high surface accuracy, has good antenna mechanism performance;
Antenna of the present invention is only made up of bar and rope, has very little gathering volume, can realize high gathering rate, draws rigidity in greatly, is convenient to transport, can saves upper payload space of firing a rocket;
Structure of the present invention adopts the processing and manufacturing of space flight common used material, rich material resources, and processing technology is ripe, and material therefor density is little, and stiffness is large, effectively can alleviate the weight of mechanism.
Accompanying drawing explanation
Fig. 1 is the overall structure stereogram (horizontal positioned) of the deployable annular stretching integral antenna mechanism deployed condition in space of the present invention, Fig. 2 is the overall structure stereogram (vertically placing) of the deployable annular stretching integral antenna mechanism deployed condition in space of the present invention, Fig. 3 is the main cutaway view of stretching integral rod member 32 in the specific embodiment of the invention one, Fig. 4 is the A portion enlarged drawing of Fig. 3, Fig. 5 is the B portion enlarged drawing of Fig. 3, Fig. 6 is the overall structure vertical view of the deployable annular stretching integral antenna mechanism rounding state in space of the present invention, Fig. 6 is the overall structure vertical view of the deployable annular stretching integral antenna mechanism rounding state in space of the present invention, Fig. 7 is the overall structure shaft side figure of the deployable annular stretching integral antenna mechanism rounding state in space of the present invention, Fig. 8 is the structural representation of middle tensioning apparatus 30 in the specific embodiment of the invention one, Fig. 9 is the stereogram with damping slowly-releasing pulley 23 in embodiment one.
Embodiment
Embodiment one: as shown in Fig. 1 ~ 9, the deployable annular stretching integral antenna mechanism in space of present embodiment comprises middle tensioning apparatus 30, delayed release device 31, many stretching integral rod members 32 and Duo Gen side tension cords;
Middle tensioning apparatus 30 comprises tensioning spring 20 and two thin slices, 19, two thin slices about 19 be arranged in parallel, and tensioning spring 20 is vertically arranged between two thin slices 19;
Described delayed release device 31 comprises two band damping slowly-releasing pulleys 23;
Every root stretching integral rod member 32 comprises end suspension ring 1, main side firmware 3, main side tube connector 4, guide shoe 7, slide block screw 8, driving spring 10, carbon fiber pipe 11, secondary end connection 12, secondary end firmware 13 and two stay springs 6, main side firmware 3 is affixed by one end of pin and main side tube connector 4, end suspension ring 1 are threaded on main side firmware 3, the other end of main side tube connector 4 and one end of carbon fiber pipe 11 affixed, the sidewall of main side tube connector 4 is processed with along its length two strip gab 4-1, each strip gab place correspondence is provided with a stay spring 6, driving spring 10 is positioned at carbon fiber pipe 11, the middle part of guide shoe 7 is processed with annular groove 7-1 along its circumference, when antenna mechanism is launched, the bottom of stay spring 6 is installed on the annular groove 7-1 place of guide shoe 7, the lower end of guide shoe 7 is connected with slide block screw 8, guide shoe 7 is positioned at the upper end of driving spring 10, secondary end firmware 13 is packed in the other end of carbon fiber pipe 11 by secondary end connection 12, the quantity of stretching integral rod member 32 is even number,
Many side tension cords comprise the fast rope of control 24, the fast rope of lower control 25, multiple saddle rope 14, multiple oblique cord 15, multiple limits rope 16, multiple perpendicular rope 17 and multiple middle side tension cords 18;
Many stretching integral rod members 32 are along the circumferential direction arranged, the wherein stretching integral rod member 32 of the half along the circumferential direction uniform setting of inclination clockwise, remaining half stretching integral rod member 32 is the uniform setting of inclination counterclockwise along the circumferential direction, the end suspension ring 1 of the stretching integral rod member 32 be obliquely installed clockwise are arranged upward, the end suspension ring 1 of the stretching integral rod member 32 be obliquely installed counterclockwise are arranged down, main side firmware 3 and secondary the end between firmware 13 of two stretching integral rod members 32 of adjacent same rotation direction are connected with a perpendicular rope 17, firmware 13 is held through secondary successively in one end of perpendicular rope 17, driving spring 10 is connected with the lower end of guide shoe 7, a limit rope 17 is connected with between two main side firmwares 3 of two stretching integral rod members 32 of adjacent same rotation direction, end suspension ring 1 successively through clockwise stretching integral rod member 32 are the fast rope 24 of upper control, end suspension ring 1 successively through counterclockwise stretching integral rod member 32 are the fast rope 25 of lower control, the fast rope of upper control 24 and the fast rope 25 of lower control are wrapped on corresponding band damping slowly-releasing pulley 23, main side firmware 3 and secondary the end between firmware 13 of two stretching integral rod members 32 of adjacent different rotation direction are connected with an oblique cord 15, a saddle rope 14 is connected with between two secondary end firmwares 13 of two stretching integral rod members 32 of adjacent different rotation direction, middle tensioning apparatus 30 is positioned at the center of many stretching integral rod members 32, the main side firmware 3 of each stretching integral rod member 32 be obliquely installed clockwise and side tension cords 18 in the middle of be connected with between the thin slice 19 of top, the main side firmware 3 of each stretching integral rod member 32 be obliquely installed counterclockwise and side tension cords 18 in the middle of be connected with between the thin slice 19 of below.
Lens barrel bore of the present invention can expand according to actual needs, and the quantity of the basic bar of stretching integral specifically can be determined according to the concrete size of antenna and bore.
Embodiment two: as shown in Figure 3 and Figure 4, described in present embodiment, described two strip gab 4-1 are symmetricly set on main side tube connector 4, and two stay springs 6 are symmetricly set on two strip gab 4-1 places of main side tube connector 4.Design like this, have locking efficiency high, coupling mechanism force is symmetrical, and locking is reliable advantage steadily.Other composition and annexation identical with embodiment one.
Embodiment three: as shown in Figure 3 and Figure 4, described in present embodiment, described stretching integral rod member 32 also comprises end nut 2, and described end nut 2 is threaded on end suspension ring 1.Design like this, can the dismounting adjustment of implementation structure, and provides path for the installation of inner components.Other composition and annexation identical with embodiment one or two.
Embodiment four: as shown in Figure 3 and Figure 4, the described stretching integral rod member 32 of present embodiment also comprises slider nut 9, and described slider nut 9 is threaded on slide block screw 8.Design like this, adjusts by the screw-in depth of adjustment slide block screw 8 and the pretightning force of position to driving spring 10 of slider nut 9, changes the initial energy storage capacity of driving spring 10, thus obtain the actuating force of different size.Other composition and annexation identical with embodiment three.
Operation principle:
Under initial condition, antenna body is in rounding state, and in stretching integral rod member 32, the elastic potential energy of driving spring 10 is maximum, and under the restriction of the fast rope of upper control 24 and the fast rope of lower control 25, have very large internal stress in rope, whole antenna body is in the stable state of tensioning.
During expansion, releasing device 31 works, antenna body launches, the stress that the fast rope of upper control 24 and the fast rope 25 of lower control store is discharged, the fast rope of upper control 24 and lower control fast rope 25 length increase, interior one section of stretching integral rod member 32 is contracted under the tensioning function of perpendicular rope 17 driving spring 10 in stretching integral rod member 32, driving spring 10 drives guide shoe 7 to move along a straight line in stretching integral rod member 32, until two stay springs 6 are stuck in the annular groove 7-1 place of guide shoe 7, namely guide shoe 7 is by the bayonet locking of two stay springs 6, whole annular stretching integral antenna aperture increases, highly reduce, achieve the function that perpendicular rope 17 orientation reduces designated length, ensure that perpendicular rope 17, when tension, reverse play does not occur simultaneously, by the release of the fast rope of upper control 24 and the fast rope 25 of lower control, perpendicular rope 17 length is reduced to the shortest and realizes the locking of guide shoe 7 in bar, achieves and converts from drawing the continuous morphology launched, and in the process of expansion, this antenna mechanism stable equilibrium constantly.Antenna mechanism is launched completely, achieves the support to reflecting surface.
Claims (4)
1. the deployable annular stretching integral antenna mechanism in space, described stretching integral antenna mechanism comprises middle tensioning apparatus (30), delayed release device (31), many stretching integral rod members (32) and many side tension cords;
Middle tensioning apparatus (30) comprises tensioning spring (20) and two thin slices (19), two thin slices (19) be arranged in parallel up and down, and tensioning spring (20) is vertically arranged between two thin slices (19);
Described delayed release device (31) comprises two bands damping slowly-releasing pulley (23);
Every root stretching integral rod member (32) comprises end suspension ring (1), main side firmware (3), main side tube connector (4), guide shoe (7), slide block screw (8), driving spring (10), carbon fiber pipe (11), secondary end connection (12), secondary end firmware (13) and two stay springs (6), main side firmware (3) is affixed with one end of main side tube connector (4) by pin (5), end suspension ring (1) screw thread is on main side firmware (3), the other end of main side tube connector (4) and one end of carbon fiber pipe (11) affixed, the sidewall of main side tube connector (4) is processed with along its length two strip gabs (4-1), each strip gab place correspondence is provided with a stay spring (6), driving spring (10) is positioned at carbon fiber pipe (11), the middle part of guide shoe (7) is processed with annular groove (7-1) along its circumference, when antenna mechanism is launched, the bottom of stay spring (6) is installed on annular groove (7-1) place of guide shoe (7), the lower end of guide shoe (7) is connected with slide block screw (8), guide shoe (7) is positioned at the upper end of driving spring (10), secondary end firmware (13) is packed in the other end of carbon fiber pipe (11) by secondary end connection (12), the quantity of stretching integral rod member (32) is even number,
Many side tension cords comprise the fast rope of control (24), the fast rope of lower control (25), multiple saddle rope (14), multiple oblique cord (15), multiple limits rope (16), multiple perpendicular rope (17) and multiple middle side tension cords (18);
Many stretching integral rod members (32) are along the circumferential direction arranged, the wherein stretching integral rod member (32) of the half along the circumferential direction uniform setting of inclination clockwise, remaining half stretching integral rod member (32) is the uniform setting of inclination counterclockwise along the circumferential direction, the end suspension ring (1) of the stretching integral rod member (32) be obliquely installed clockwise are arranged upward, the end suspension ring (1) of the stretching integral rod member (32) be obliquely installed counterclockwise are arranged down, main side firmware (3) and secondary the end between firmware (13) of two stretching integral rod members (32) of adjacent same rotation direction are connected with a perpendicular rope (17), firmware (13) is held through secondary successively in one end of perpendicular rope (17), driving spring (10) is connected with the lower end of guide shoe (7), a Gen Biansuo (17) is connected with between two main side firmwares (3) of two stretching integral rod members (32) of adjacent same rotation direction, end suspension ring (10) successively through clockwise stretching integral rod member (32) are the fast rope of upper control (24), end suspension ring (1) successively through counterclockwise stretching integral rod member (32) are the fast rope of lower control (25), the fast rope of upper control (24) and the fast rope of lower control (25) are wrapped on corresponding band damping slowly-releasing pulley (23), main side firmware (3) and secondary the end between firmware (13) of two stretching integral rod members (32) of adjacent different rotation direction are connected with an oblique cord (15), a saddle rope (14) is connected with between two secondary ends firmware (13) of two stretching integral rod members (32) of adjacent different rotation direction, middle tensioning apparatus (30) is positioned at the center of many stretching integral rod members (32), side tension cords (18) in the middle of being connected with one between the main side firmware (3) of each stretching integral rod member (32) be obliquely installed clockwise and the thin slice (19) being positioned at top, side tension cords (18) in the middle of being connected with one between the main side firmware (3) of each stretching integral rod member (32) be obliquely installed counterclockwise and the thin slice (19) being positioned at below.
2. the deployable annular stretching integral antenna mechanism in space according to claim 1, it is characterized in that: described two strip gabs (4-1) are symmetricly set on main side tube connector (4), two stay springs (6) are symmetricly set on two strip gabs (4-1) place of main side tube connector (4).
3. the deployable annular stretching integral antenna mechanism in space according to claim 1 and 2, it is characterized in that: described stretching integral rod member (32) also comprises end nut (2), and described end nut (2) is threaded on end suspension ring (1).
4. the deployable annular stretching integral antenna mechanism in space according to claim 3, it is characterized in that: described stretching integral rod member (32) also comprises slider nut (9), and described slider nut (9) is threaded on slide block screw (8).
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| CN201510446461.6A CN105071012B (en) | 2015-07-27 | 2015-07-27 | The deployable annular tensioning integrated antenna mechanism in space |
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Cited By (10)
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| CN105977648A (en) * | 2016-07-15 | 2016-09-28 | 哈尔滨工业大学 | Shear fork coordinated type annular space deployable antenna mechanism |
| CN106910976A (en) * | 2017-05-02 | 2017-06-30 | 湖北文理学院 | Light-duty automatic Quick extension folded antenna bar |
| CN107453017A (en) * | 2017-07-24 | 2017-12-08 | 西安电子科技大学 | A kind of space plane film antenna deployable mechanism |
| CN108528762A (en) * | 2018-04-13 | 2018-09-14 | 哈尔滨工业大学 | A kind of stretching type can open up space bay section skeleton structure |
| CN108767421A (en) * | 2018-06-28 | 2018-11-06 | 哈尔滨工业大学（威海） | A kind of space deployable antenna supporting mechanism |
| CN109586000A (en) * | 2018-11-23 | 2019-04-05 | 哈尔滨工程大学 | A kind of annular tensioning entirety deployable structure of centre-drive |
| CN110304550A (en) * | 2019-07-15 | 2019-10-08 | 西安工业大学 | A kind of the active suspension apparatus and suspension system of antenna structure |
| CN110416741A (en) * | 2019-07-19 | 2019-11-05 | 同济大学 | A kind of ring tension elastic rib Deployable antenna structure |
| US11081775B2 (en) | 2017-01-31 | 2021-08-03 | Oxford Space Systems Limited | Actuating support member |
| CN114575461A (en) * | 2022-03-16 | 2022-06-03 | 中山大学 | Nested annular tensioning integral structure spliced in modularization mode |
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| CN105977648B (en) * | 2016-07-15 | 2018-10-02 | 哈尔滨工业大学 | A kind of scissor coordinated type annular space deployable antenna mechanism |
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| CN108767421A (en) * | 2018-06-28 | 2018-11-06 | 哈尔滨工业大学（威海） | A kind of space deployable antenna supporting mechanism |
| CN109586000A (en) * | 2018-11-23 | 2019-04-05 | 哈尔滨工程大学 | A kind of annular tensioning entirety deployable structure of centre-drive |
| CN109586000B (en) * | 2018-11-23 | 2020-07-14 | 哈尔滨工程大学 | Central-driven annular tensioning integral expandable structure |
| CN110304550A (en) * | 2019-07-15 | 2019-10-08 | 西安工业大学 | A kind of the active suspension apparatus and suspension system of antenna structure |
| CN110416741A (en) * | 2019-07-19 | 2019-11-05 | 同济大学 | A kind of ring tension elastic rib Deployable antenna structure |
| CN114575461A (en) * | 2022-03-16 | 2022-06-03 | 中山大学 | Nested annular tensioning integral structure spliced in modularization mode |
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