CN102050409B - Hoisting system of large-sized extensible antenna - Google Patents
Hoisting system of large-sized extensible antenna Download PDFInfo
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- CN102050409B CN102050409B CN 201010575012 CN201010575012A CN102050409B CN 102050409 B CN102050409 B CN 102050409B CN 201010575012 CN201010575012 CN 201010575012 CN 201010575012 A CN201010575012 A CN 201010575012A CN 102050409 B CN102050409 B CN 102050409B
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- deployable antenna
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Abstract
The invention discloses a hoisting system for a large-sized extensible antenna, and in particular relates to a ground testing system for the extensible antenna. The hoisting system provided by the invention mainly solves the problem that the existing testing system can not simulate the space zero gravity extension for the extensible antenna in the ground stimulation. The system provided by the invention comprises a lifting rod (1), a positioning cable (2), a supporting cable (3), a hoisting ring (4), a pulling cable (5) and a counter weight (6), wherein the supporting cable (3) is an equilateral polygon parallel to the opening surface of the extensible antenna (7); the hoisting ring (4) is arranged in each cross position of the radially arranged positioning cable (2) and supporting cable (3); the pulling cable (5) passes through the hoisting ring (4) and is respectively connected with the counter weight (6) and the extensible antenna (7); and one end of the positioning cable (2) is connected with the upper end of the lifting rod (1), and the other end of the positioning cable and the other end of the lifting rod are fixed with the ground so as to form a circular conical surface extensible supporting structure with the lifting rod (1) as the center. The hoisting system provided by the invention is convenient in gravity unloading, is not limited by the testing space and can be used for the ground extension test of the extensible antenna.
Description
Technical field
The invention belongs to field of mechanical technique, specifically a kind of Lift-on/Lift-off System is mainly used in the ground spreading test that spaceborne ring rib can be opened up antenna, also can be applicable to ground spreading test and the ground interim sunshade of the deployable antenna of other types.
Background technology
Along with the development of space communications technique with to the demand of survey of deep space, antenna aperture is increasing, because the carrying capacity of satellite and carry the restriction in space, spaceborne deployable antenna arises at the historic moment.The general spaceborne antenna of opening up all has the three kinds of states of deployed condition that draw attitude, the transition condition from the gathering attitude to the centre of deployed condition in, keep being locked as mode of operation, but because complicated space environment, make general simulation result be difficult to reach the requirement of the high reliability of compellent deployable antenna.In case launch in space unsuccessfully, cost will be very huge.Therefore, the deployment characteristics of large-scale spaceborne deployable antenna, surface accuracy need to be verified by ground experiment.Yet ground environment and space environment difference are very large, and topmost is exactly gravity environment.Because the ground gravity environment originally can just may be opened up not open on ground in the structure that space launches, even may cause structural damage.The large-scale spaceborne antenna of opening up generally is made of a plurality of joints and connecting rod, and flexibility is larger, therefore in the ground spreading test, need take the mode of multiple spot unloading when carrying out gravity unloading.But the ground spreading experimental set-up need to design according to structure, expansion mode, expansion path of motion, antenna aperture and the remaining operational space of deployable antenna, just can reach the purpose of unloading part gravity or whole gravity.
Existing testing technique normally hang on top ceiling by hoist cable on the one or more system points on the test specimen comes the gravity of test specimen structure itself is compensated.
Imperial court helps in the ground validation 33-34 page or leaf of the large-scale grating reflector mechanical characteristics of paper that communication was delivered with observing and controlling fourth phase calendar year 2001 and has introduced a kind of gravitational compensation method, the method is that the magnetcisuspension slider is hung on the top ceiling, by reduction at the intermittence level friction of displacement pickup control top ceiling and slider, use the power sensor of Direct Current Motor and control hoist cable tension force and offset the weight of antenna.The method has two open defects: must hang on indoorly, it is limited to use height and span; Since used motor, the power sensor, and all inconveniences of receipts are installed, debug and removed to the complex devices such as displacement pickup.
Road ripple, Tao Guoliang, Liu Wu are at the paper zero gravity of journal of Zhejiang university the 5th phase the 43rd curly hair table in 2009 a kind of gravitational compensation method of having simulated the exploitation of pneumatic suspension and Introduction of key techniques, the method is that in the vertical direction hangs one without the friction cylinder, cylinder one side is led to atmosphere, opposite side links to each other with storage tank by large-diameter pipeline, by the pressure in the pressure valve on the pipeline control cylinder cavity volume make the power that acts on the piston all the time with the gravitational equilibrium of test specimen.The method also has three large defectives: the method is merely able to realize the motion of in the vertical direction, can't satisfy the requirement of the Comlex-locus of deployable antenna; The method can't satisfy the test requirements document of the large flexible needs multiple spot unloading of subjects; Manufacturing cost without the friction cylinder is too high.
Although varied take spaceborne deployable antenna as main ground experiment expanding unit, the good Large Deployable device of overall characteristic is actually rare.
Summary of the invention
The object of the invention is to overcome deficiency and the defective that above-mentioned prior art exists, a kind of Large deployable antenna Lift-on/Lift-off System of the space constraint that is not put to the test is provided, to reach reduction experimentation cost, realize large-scale spaceborne multiple spot unloading of opening up antenna, be convenient to Fast Installation and dismounting, satisfy deployable antenna to the integrated performance index requirement of Comlex-locus.
The technical thought of the purpose of this realization invention is: adopt lifting bar as centre strut and highly support, offset antenna gravity by the suitable counterweight of cable traction, and utilize the compound movement of the flexible tracking antenna of rope, the multiple spot unloading is finished in the combination of registration wire, suspension ring, counterweight and the supporting cables of plural number, thereby makes deployable antenna launch to put in place under the connection joint torsion spring propulsive effort effect of self in gravity environment.Whole system comprises: the trailing cable of plural number, counterweight, a plurality of registration wire, a supporting cables and a lifting bar; Supporting cables is equilateral polygon, the parallel actinal surface top that is positioned at deployable antenna, and the registration wire radial array, the point of crossing place of each registration wire and supporting cables is provided with suspension ring; Trailing cable passes suspension ring one end and is connected with counterweight, and the other end is connected with deployable antenna; One end of registration wire is connected with the upper end of lifting bar, and the other end of registration wire and lifting bar is fixed with ground, forms the circular conical surface expansion supporting construction centered by lifting bar.
Described lifting bar, the circular sleeves different by the multistage diameter connect to form, and consist of stretching structure, to realize elongating upon deployment as the centre strut of whole system and highly to support, draw in when not using; The length of the stretching of this lifting bar height and registration wire is adjustable, with adapt to different bores, burnt directly than the operating needs of deployable antenna.
Described registration wire for the steel strand that the steel wire strand gummed forms, is strained by carrying capstan winch during use.
Described supporting cables adopts breaking elongation less than 4% Kev stay cord, and this supporting cables and registration wire are bound at its point of crossing place.
Described suspension ring pass registration wire and are blocked by supporting cables, and with anti-fall, the distance of suspension ring and center mast is greater than launching fully on the aft antenna and the point of connection of the trailing cable distance to center mast.
The present invention has following advantage:
The present invention is owing to use the lifting bar that can be fixed in ground as the centre strut of system and highly support, the restriction in the space that is not put to the test.
(1) the present invention is owing to be provided with suspension ring at the crossover location of registration wire and supporting cables, and all above the deployable antenna actinal surface, therefore can conveniently realize the multiple spot unloading of deployable antenna by trailing cable and counterweight.
(2) the present invention is owing to use adjustable for height lifting bar and length-adjustable registration wire, therefore different bores and burnt footpath than the expansion test of antenna all can carry out in same pilot system, and it be not necessary for different bores and burnt footpath than antenna build different pilot systems, therefore reduced experimentation cost.
(3) the present invention since the distance of the suspension ring that are positioned at deployable antenna actinal surface top and center mast greater than on the antenna with the point of connection of the trailing cable distance to center mast, therefore be easy to utilize the flexible drawing rope that passes suspension ring to satisfy the requirement of deployable antenna complexity expansion path of motion.
Test results shows: the present invention can make deployable antenna configuration precision under the ground gravity environment reach gratifying technical index, and is convenient to install and remove receipts.
Description of drawings
Fig. 1 is the integral structure scheme drawing that the present invention draws attitude in;
Fig. 2 is the integral structure scheme drawing of deployed condition of the present invention;
Fig. 3 is hanging position rope of the present invention and the mutual scheme drawing of suspension ring;
Fig. 4 is the rounding state scheme drawing of deployable antenna under apparatus of the present invention of bore 20m;
Fig. 5 is the deployed condition scheme drawing of deployable antenna under apparatus of the present invention of bore 20m;
Fig. 6 is the rounding state scheme drawing of the deployable flexible sunshade of bore 30m;
Fig. 7 is the deployed condition scheme drawing of the deployable flexible sunshade of bore 30m;
Fig. 8 is the deployable antenna deployed condition emulation scheme drawing of 10m bore;
Fig. 9 is the deployable antenna deployed condition emulation scheme drawing of 20m bore.
The specific embodiment
Such as Fig. 1, shown in Figure 2, the present invention includes: lifting bar 1, registration wire 2, supporting cables 3, suspension ring 4, trailing cable 5 and counterweight 6.Wherein, the number of lifting bar 1 and supporting cables 3 is single; Registration wire 2, suspension ring 4, trailing cable 5, the number of counterweight 6 is a plurality of, its concrete number deployable antenna profile precision and antenna aperture as required selected, the number that for example uses in the deployable antenna example of 10m bore is 6, and the number that uses in the deployable antenna example of 20m bore is 12.Lifting bar 1 is formed by connecting by the different circular sleeve of multistage diameter, according to using needs to may be elongated to the arbitrary height position.Registration wire 2 adopts steel strand, and anti-axial elongation has again certain flexibility largely.What supporting cables 3 and trailing cable 5 adopted is the Kev tow of breaking elongation＜4%.What suspension ring 4 adopted is lighter weight and smooth annulus, and quality can be ignored in the whole system calculation of parameter.What counterweight 6 adopted is plumb aligner.
During connection, lifting bar 1 lower end is fixed on the ground, and keep stable; The upper end of registration wire 2 links to each other with the upper end of lifting bar 1, lower end and the ground of registration wire 2 are fixed, and the capstan winch tension by carrying, so just can make the two ends of the lifting bar 1 of centre strut effect all be in stationary state, become the stable height of whole system and support, and then the circular conical surface that forms centered by lifting bar 1 launches supporting construction; Because it is adjustable that the length of the elongation of lifting bar 1 height and registration wire 2 is, therefore different bores and burnt footpath than the expansion test of antenna can in same system, carry out, and do not need to re-construct new pilot system; Supporting cables 3 is one section self-enclosed Kev tow, and when after the binding of the relevant position of the position of a plurality of even five equilibriums on the supporting cables 3 and every registration wire 2, supporting cables 3 just forms the equilateral polygon of a level attitude at spatial altitude.As shown in Figure 3, suspension ring 4 pass registration wire 2 and above supporting cables 3, and like this, suspension ring 4 can be distributed in because the screens effect of supporting cables 3 is not glided on each summit of the equilateral polygon that this supporting cables 3 forms.Therefore, the length of supporting cables 3 determines the position of suspension ring 4.The principle that the length of supporting cables 3 is selected is to make suspension ring 4 launch rear haulage rope and antenna connector to the distance of lifting bar to the distance of lifting bar 1 greater than antenna, so just can make counterweight 6 play the effect of gravity unloading by the trailing cable 5 that passes suspension ring 4.The length of trailing cable 5 need satisfy antenna 7 launch fully after counterweight 6 do not touch ground.Because counterweight 6 has been carried out gravity unloading by 4 pairs of deployable antennas of suspension ring 7, therefore, deployable antenna 7 just can launch under self joint torsion spring propulsive effort after release, because the joint of deployable antenna 7 carries lockout mechanism, just can self-locked after expansion puts in place.Fig. 1 is the situation that the ring rib deployable antenna 7 of 10m bore draws under native system, and Fig. 2 is the situation after the ring rib deployable antenna 7 of 10m bore launches under this Lift-on/Lift-off System smoothly.
Such as Fig. 4, shown in Figure 5, be pilot system in the deployable antenna of 20m bore, because the bore of deployable antenna increases, its flexible increase, therefore need the unloading point of more number more to satisfy the requirement of precision of expansion, increased according to actual needs the number of registration wire 2, suspension ring 4, trailing cable 5 and counterweight 6, be increased to 12 by 6, the effect of multiple spot unloading during with the increase deployed condition, thus realized that more the ground gravity of high-precision requirement launches test.
Structure and parameter of the present invention can require according to the bore that the single unit system reflecting surface launches to determine, below provide several different instances, but be not limited to these examples.
Example 1, the expansion of the deployable antenna of bore 10m under apparatus of the present invention.
The rounding state of this device as shown in Figure 1, deployed condition is as shown in Figure 2.
Center mast adopts the mobile liftable bar, and height is 12 meters after stretching; 6 registration wires are used in test, locate long 17 meters of rustling sound for every, become 45 degree with lifting bar; The Kev that length is 42.43m draws supporting cables; 6 suspension ring; 6 Kevlar trailing cables; Launching the aft antenna summit is 1 meter according to the lifting bar bottom; Antenna weighs 24 kilograms, 4.5 kilograms of each counterweights; The burnt footpath of the ring rib deployable antenna of this 10m bore is than being 0.5.
Reflecting surface under this device is carried out simulation analysis, find that maximum distortion appears on the ring, maximum distortion is 15mm, and the surperficial root-mean-square error (RMS error) RMS that reaches is 6mm, as seen unloads effect or ideal.
Example 2, the expansion of the deployable antenna of bore 20m under apparatus of the present invention.
The gathering attitude of this device is equipped with the deployed condition of rope net as shown in Figure 5 as shown in Figure 4.
Center mast adopts fixedly lifting bar, highly is 20m after stretching; Because antenna aperture is larger, in order to guarantee deployable antenna profile precision, here adopt the more unloading point of more number, except the unloading of antenna loop rib junction, also in the unloading of ring joint, 12 registration wires have been adopted altogether, what use equally is steel strand, strain stretching rear become with the center lifting bar 36.87 degree, the every long 25m of registration wire after launching with capstan winch; Accordingly, use 12 trailing cables, adopted equally the kevlar fiber material; 12 suspension ring; 12 counterweights; Antenna aperture 20m, burnt footpath is than being 0.5, on the summit according to ground 3m, 84 kilograms of gross weights, 9 kilograms of each counterweights.
Reflecting surface under this device is carried out simulation analysis, and maximum distortion appears on the rib, and maximum distortion is 12mm.The surperficial root-mean-square error (RMS error) RMS that can reach is 6mm.As seen in the situation that bore strengthens, the number of suitable increase trailing cable can reach the precision higher than example 1.
Example 3, the deployable flexible sunshade of bore 30m.
The gathering attitude of this device as shown in Figure 6, deployed condition is as shown in Figure 7.
More than several examples the present invention is not constituted any limitation.According to the antenna aperture needs of reality and the needs of test accuracy, can select the lifting bar of different length, both can for electronic also can be for manual, both can for mobile also can be for fixing; The angle of reasonable Arrangement trailing cable, number and length, the number of suspension ring, the size of counterweight, the length of supporting cables all can be set according to actual needs.
Effect of the present invention can further specify according to following simulation example:
Take the first example of the present invention as simulation object.
Fig. 8 has showed under the gravity environment on ground, the deformation of the rigid backbone of deployable antenna under native system.If operating frequency of antenna is 1Ghz, wavelength X is 300mm, and take the surperficial root-mean-square error (RMS error) RMS of 0.02 λ as the calculating standard, then the RMS of the 6mm of this simulation example can meet the demands; Calculate standard take 3 λ as maximum distortion, then the 15mm of this simulation example also can meet the demands.Illustrate that this device can reach the operating needs at 1G and following frequency of operation.
Take the second example of the present invention as simulation object.
Fig. 9 has showed under the gravity environment on ground, the deformation of the rigid backbone of deployable antenna under native system.If operating frequency of antenna is 1Ghz, wavelength X is 300mm, and take the RMS of 0.02 λ as the calculating standard, then the RMS of the 6mm of this simulation example can meet the demands; Calculate standard take 3 λ as maximum distortion, then the 12mm of this simulation example also can meet the demands.Illustrate that this device can reach the operating needs of 1G and following frequency of operation.
Even above simulation example presentation of results is under the ground gravity environment, large-scale spaceborne ring rib deployable antenna also can launch on ground, and can reach gratifying profile precision.This pilot system adopts simple test equipment, admirably in ground simulation the deployable antenna of agravic environment of space from drawing to the process of launching in, overall characteristic is good.
Claims (7)
1. Large deployable antenna Lift-on/Lift-off System, comprising: the trailing cable of plural number and counterweight is characterized in that: also comprise a plurality of registration wires (2), a supporting cables (3) and a lifting bar (1); Supporting cables (3) is equilateral polygon, the parallel actinal surface top that is positioned at deployable antenna (7), and registration wire (2) radial array, the point of crossing place of each registration wire and supporting cables is provided with suspension ring (4); Trailing cable (5) passes suspension ring (4) one ends and is connected with counterweight (6), and the other end is connected with deployable antenna (7); One end of registration wire (2) is connected with the upper end of lifting bar (1), and the other end of registration wire and lifting bar is fixed with ground, forms the circular conical surface expansion supporting construction centered by lifting bar (1);
The length of described supporting cables (3) determines the position of suspension ring (4), the principle that its length is selected is to make suspension ring (4) launch rear haulage rope and antenna connector to the distance of lifting bar, so that counterweight (6) plays the effect of gravity unloading by the trailing cable (5) that passes suspension ring (4) to the distance of lifting bar (1) greater than antenna.
2. deployable antenna Lift-on/Lift-off System according to claim 1, it is characterized in that: lifting bar (1) is connected to form by the different circular sleeve of multistage diameter, consist of stretching structure, to realize extending upon deployment as the centre strut of whole system and highly to support, draw in when not using.
3. deployable antenna Lift-on/Lift-off System according to claim 1 is characterized in that: the steel strand that registration wire (2) forms for the steel wire strand gummed, during use by carrying the capstan winch tension.
4. deployable antenna Lift-on/Lift-off System according to claim 1 is characterized in that: supporting cables (3) and registration wire (2) are in its point of crossing place binding.
5. deployable antenna Lift-on/Lift-off System according to claim 1 is characterized in that: supporting cables (3) adopts breaking elongation less than 4% Kev stay cord.
6. deployable antenna Lift-on/Lift-off System according to claim 1, it is characterized in that: suspension ring (4) pass registration wire (2) and are blocked by supporting cables (3), with anti-fall, the distance of suspension ring (4) and lifting bar (1) is greater than launching fully on the aft antenna and the point of connection of the trailing cable distance to lifting bar (1).
7. deployable antenna Lift-on/Lift-off System according to claim 1 is characterized in that: the stretching height of lifting bar (1) and the length of registration wire (2) are adjustable, with adapt to different bores, burnt directly than the operating needs of deployable antenna.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010575012 CN102050409B (en) | 2010-12-06 | 2010-12-06 | Hoisting system of large-sized extensible antenna |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010575012 CN102050409B (en) | 2010-12-06 | 2010-12-06 | Hoisting system of large-sized extensible antenna |
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| CN102050409A CN102050409A (en) | 2011-05-11 |
| CN102050409B true CN102050409B (en) | 2013-03-20 |
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| CN 201010575012 Expired - Fee Related CN102050409B (en) | 2010-12-06 | 2010-12-06 | Hoisting system of large-sized extensible antenna |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107246862B (en) * | 2017-05-19 | 2020-01-07 | 上海宇航系统工程研究所 | Gravity balance method for ground test of heavy satellite-borne deployable antenna |
| CN108708929B (en) * | 2018-05-11 | 2019-10-22 | 西安空间无线电技术研究所 | A kind of spaceborne loop aerial constant force discharge mechanism and method |
| CN110304550B (en) * | 2019-07-15 | 2020-07-28 | 西安工业大学 | Active suspension device and suspension method of antenna structure |
| CN113219261B (en) * | 2021-03-29 | 2022-06-24 | 西安电子科技大学 | Modular deployable antenna ground deployment test system, control method and application |
| CN113371235B (en) * | 2021-05-31 | 2022-07-22 | 哈尔滨工业大学 | Active and passive combined suspension type double-layer motion platform and using method |
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