CN102765490A - Space tethered unfoldable covered surface system - Google Patents
Space tethered unfoldable covered surface system Download PDFInfo
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- CN102765490A CN102765490A CN2012102752776A CN201210275277A CN102765490A CN 102765490 A CN102765490 A CN 102765490A CN 2012102752776 A CN2012102752776 A CN 2012102752776A CN 201210275277 A CN201210275277 A CN 201210275277A CN 102765490 A CN102765490 A CN 102765490A
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Abstract
The invention discloses a space tethered unfoldable covered surface system which mainly solves the problems of difficult unfolded formation and poor stability in the prior art. The space tethered unfoldable covered surface system comprises soft traction cables (1), a traction cable control mechanism (3), folded rings (4) and connection joints (5). Soft screen meshes (8) are bonded on rigid structures formed by the folded ring and the connection joints to form covered surfaces (2), and the soft traction cables (1) are connected with the covered surfaces (2) and the traction cable control mechanism (3) which controls the soft traction cables (1) to stretch out and draw back. Tension springs (6) and traction cables (7) are arranged in the folded rings (4), the tension springs (6) are stretched out when the folded rings (4) are folded, and when the folded rings (4) are unfolded, the tension springs (6) draw back, and the traction cables (7) are shortened. Under the effect of the tension of the traction cables, the connection joints (5) are unfolded to enable the covered surfaces to be unfolded into a horizontal working state from a vertical folded state, and the folded rings are locked through positioning devices on the connection joints (5). The space tethered unfoldable covered surface system has the advantages of being low in surface density, high in configuration actuary, large in storage rate and stable in posture, and can serve as an unfoldable screening device in the space.
Description
Technical field
The invention belongs to the space technology field, specifically is that space rope is the deployable plane system that covers, and can be used for the large-scale deployable systems in space such as space sun shade, spatially masked, spacing reflection mirror, space solar station.
Background technology
The earth outer space has brought huge opportunities and challenges for human new development in science and technology and technological advance.Along with the continuous enhancing of human carrying space ability and the continuous development of space technology, the application of space ultra-large type deployable structure is brought into schedule gradually.Space ultra-large type deployable structure has direct application prospect in the space communtication field, and has produced huge economic and social benefit.Space ultra-large type deployable structure also has tempting application prospect in other field, like space solar light reflecting mirror, solar rail station, space elevator, space track translator etc.Because human carrier rocket holds the restriction of size, carrying capacity; Expensive, the high risk characteristics of AEROSPACE APPLICATION; The significant difference of ground development environment and space working environment, what make space ultra-large type deployable structure is designed to one of gordian technique of following AEROSPACE APPLICATION.
It is the mathematical fact that global climate system warms, and mitigation of global climate warms and becomes too impatient to wait just gradually.Earth engineering is the huge artificial climate transformation planning that proposes for mitigation of global climate warms of some scientific research personnel in recent years.In numerous planning, Comparatively speaking, spacing reflection mirror is one of less preferred planning of quick result, secondary action.
To spacing reflection mirror planning, the scientific research personnel has also proposed the multiple embodiments conception.One of scheme is to place the sunshine reflecting surface at LEO.American National science association proposed on the near-earth random orbit, to place 55,000 single areas the catadioptre that is 100 sq ms in 1992; Also the someone proposes to generate the reflection endless belt of similar ring of Saturn with light satellite at LEO, and its total mass reaches 2,000,000,000 tons.Two of scheme is that its total mass is above 2,000 ten thousand tons between the earth and the sun, apart from placing numerous sunshine reflecting surfaces near the Lagrangian points of 1,500,000 kilometers of the earth.Because these scheme technical risks are too big, cost is too high, the cycle is oversize, is interpreted as it is science fiction by people unavoidably.
Space ultra-large type deployable structure has many distinct feature and faces many new challenges owing to its ultralight superthin structure characteristics and oversize.At first being to launch the moulding problem, secondly is the Stability Control problem.
Comparatively speaking, domestic and international existing, the feasible relatively at present large-scale deployable structure scheme in various spaces, its development size is all less than 100 meters, and it is all too negligible to be used for spatially masked plane system, and effect is very little.Because its surface density is big, if its size enlarges, means of delivery human in long-time all is difficult to carry its huge quality.In existing document, the known the lightest large-scale deployable structure in space is 20 meters square film solar arrays of the U.S. at present, 4 microns of its film thicknesses, and surface density is 87.5g/m
2But for the space ultra-large type of 1000 meters of bores was covered plane system, its surface density was still too big.Japan has proposed to involve around the film with multi-satellite, makes up the notion on huge surface, space, has enumerated with four satellites of 1 ton respectively; Involve 500 meters square films of size, film thickness is 5 microns, and quality is 2.5 tons; And the simulation analysis that has carried out dynamic control; Yet the moulding of this mode and control, its technical risk is big, and feasibility is poor.
Summary of the invention
The objective of the invention is to deficiency to above-mentioned prior art; It is the deployable plane system that covers that a kind of space rope is provided; Through the application of weight Gradient Effect, be deployable effective expansion moulding of covering face with the large-scale rope in implementation space, improve the autonomous stability of track profile.
For realizing above-mentioned purpose, the present invention provides following three kinds of technical schemes:
Trailing cable control mechanism 3 is made up of motor 301 and N rotating disk 302, twines the flexible drawing rope on each rotating disk, through the rotation direction of N rotating disk 302 of motor 301 controls, makes N root flexible drawing rope 1 flexible, 3≤N≤192;
On each deployable rigid construction, bind flexible silk screen 8 is arranged; Constitute M the deployable face 2 that covers; Be divided into the n equal portions with forming the deployable puckered ring 4 that covers face 2, in the perforate of equally divided position puckered ring, pass an end of flexible drawing rope 1, and kill knot; The other end of flexible drawing rope 1 is wrapped on the rotating disk of trailing cable control mechanism, forms Y coniform space structure;
The shared trailing cable control mechanism 3 of per two coniform space structures, promptly each the flexible drawing rope 1 in two coniform space structures is wrapped in respectively on each rotating disk of same trailing cable control mechanism 3; The integral body that formation is made up of Y/2 trailing cable control mechanism and the individual coniform space structure of Y, wherein, 2≤M≤18; Y>=M; 3≤N≤192,3≤n≤720, X>=1.
As preferably, described connection joint 5 is by a pair of conical gear 501,502 and a pair of clamping plate 503; 504 form; Conical gear is provided with guide groove 509, and conical gear is fixed through gear wheel shaft 505 and a pair of clamping plate 503,504; The chamber arm at each conical gear two ends is provided with tapped bore 508, and puckered ring 4 is connected with conical gear through this tapped bore.
As preferably, be placed with trailing cable 7 and extension spring 6 in the cavity of described puckered ring 4, trailing cable 7 is killed knot with extension spring 6 and is connected, and through stretching of extension spring 6, trailing cable 7 drives and connects joint 5 motions;
When drawing in, extension spring 6 is in extended state, and extension spring 6 is parallel at vertical direction with the chamber arm that connects joint 5, and trailing cable 7 is two gear center distances and 1/2 tooth top circle girth sum around the length on a pair of gear;
When launching, extension spring 6 is shunk and is driven trailing cable 7 motions that link to each other, and the transmission through trailing cable 7 drives a pair of gear and rotates, and when a pair of gear rotation was crossed 90 °, the contraction in length of the trailing cable 7 on a pair of gear was the width between centers of two gears.
Trailing cable control mechanism 3 is made up of motor 301 and N rotating disk 302, twines the flexible drawing rope on each rotating disk, through the rotation direction of N rotating disk 302 of motor 301 controls, makes N root flexible drawing rope 1 flexible;
Bind on each deployable rigid construction flexible silk screen 8 is arranged; Constitute M the deployable face 2 that covers; Be divided into the n equal portions with forming the deployable puckered ring 4 that covers face 2, in the perforate of equally divided position puckered ring, pass an end of flexible drawing rope 1, and kill knot; The other end of flexible drawing rope 1 is wrapped on the rotating disk of trailing cable control mechanism, forms Y coniform space structure;
Each coniform space structure uses a trailing cable control mechanism 3, and promptly each the flexible drawing rope 1 in each coniform space structure is wrapped on each rotating disk of a trailing cable control mechanism 3; These trailing cable control mechanism tractions connect, and form by Y trailing cable control mechanism and Y the integral body that coniform space structure is formed, wherein; 2≤M≤18, Y>=M, 3≤N≤192; 3≤n≤720, X>=1.
The present invention compares with existing correlation technique has following advantage:
(1) plane system that covers with trailing cable control mechanism and coniform space structure composition of the present invention's proposition more; And the cylindric plane system that covers; The application of weight Gradient Effect; Can guarantee the autonomous stable of total system track and attitude, making the ultra-large type of SPACE APPLICATION bore more than hundred meters cover face becomes possibility.
(2) three kinds of technical schemes of the present invention's proposition, when drawing on ground, the application space means of delivery is with its carrying and emission effectively.
(3) extension spring of pass through that the present invention proposes drives the mode that is connected joint motions with trailing cable, can realize that the ultra-large type of bore more than hundred meters cover autonomous expansion and effective moulding of face.
Description of drawings
Fig. 1 is the deployed condition structural representation of the embodiment of the invention 1;
Fig. 2 is the gathering attitude scheme drawing of Fig. 1;
Fig. 3 is a connection articulation structure scheme drawing of the present invention;
Fig. 4 is that Fig. 3 connects the joint and draws the attitude trailing cable in and in the joint, walk the path scheme drawing;
Fig. 5 is that Fig. 3 connects joint deployed condition trailing cable and in the joint, walks the path scheme drawing;
Fig. 6 is an extension spring drive configuration scheme drawing of the present invention;
Fig. 7 is a trailing cable control mechanism scheme drawing of the present invention;
Fig. 8 is the deployed condition configuration diagram of the embodiment of the invention 2;
Fig. 9 is the gathering attitude structural representation of Fig. 8;
Figure 10 is the deployed condition structural representation of the embodiment of the invention 3;
Figure 11 is the gathering attitude structural representation of Figure 10;
Figure 12 is the expansion process scheme drawing of Fig. 1;
Figure 13 is the motion change curve of Figure 12 structure puckered ring in launching simulation process;
Figure 14 is that Figure 12 structure medium caliber 50m covers face expansion process scheme drawing;
Figure 15 is the motion change curve of Figure 14 structure puckered ring barycenter in launching simulation process.
The specific embodiment
With reference to Fig. 1 the present invention by flexible drawing rope 1, cover face 2 and trailing cable control mechanism 3 is formed.Cover mask body number M and confirm that according to designing requirement span is 2≤M≤18, in this instance, choose up and down two and launch the different faces that cover of bore, wherein, on cover face to launch bore be 100m, it is 50m that the face that covers down launches bore.
With reference to Fig. 2, each covers face 2, adopts puckered ring 4 and is connected joint 5 formation rigid constructiones, on rigid construction, binds flexible silk screen 8, constitutes the face 2 that covers.Puckered ring 4 is a plurality of, and concrete number 6X launches bore according to the face that covers and confirms that span is X >=1, in this instance, covers the face puckered ring up and down and all gets 24, totally 48 puckered rings, i.e. X=8.Per two puckered rings 4 connect joint 5 through one and connect the rigid construction that formation can be drawn in, launched.Through connecting the driving and the locking in joint 5, all puckered rings of control rigid construction are deployed into the masking work state of level by vertical rounding state, form masking system by traction control mechanism controls flexible drawing rope again.All puckered rings 4 of each rigid construction draw on a face of cylinder or drum face nested placement inside and outside the rigid construction of two gatherings in.Puckered ring in this rigid construction adopts straight-bar, to obtain the high rate of taking in, perhaps adopts curvilinear rod, with the configuration precision that obtains.Solid section is adopted in the cross section of puckered ring, perhaps adopts the hollow section structure, under the prerequisite of proof strength, rigidity, can further alleviate quality.Rigid construction has enough spaces in inside when drawing attitude in, can hold relevant rope net, silk screen or thin film flexible structure.
With reference to Fig. 3, Fig. 4 and Fig. 5, described connection joint 5 is by a pair of conical gear 501; 502 form with a pair of clamping plate 503,504, and conical gear is provided with guide groove 509; Conical gear is through gear wheel shaft 505 and a pair of clamping plate 503; 504 is fixing, and the chamber arm at each conical gear two ends is provided with tapped bore 508, and puckered ring 4 is connected with conical gear through this tapped bore.Place trailing cable 7 in the guide groove 509, this trailing cable links to each other with extension spring.When the ring bar is deployed into the mode of operation of level by vertical rounding state, and after forwarding expected angle to, through spring pin 510 and locking hole 511 locking joints.
With reference to Fig. 6, in the cavity of puckered ring 4, be placed with trailing cable 7 and extension spring 6, trailing cable 7 is killed knot with extension spring 6 and is connected, and through stretching of extension spring 6, trailing cable 7 drives and connects joint 5 motions; When drawing in, extension spring 6 is in extended state, and extension spring 6 is parallel at vertical direction with the chamber arm that connects joint 5, and trailing cable 7 is two gear center distances and 1/2 tooth top circle girth sum around the length on a pair of gear; When launching, extension spring 6 is shunk and is driven trailing cable 7 motions that link to each other, and the transmission through trailing cable 7 drives a pair of gear and rotates, and when a pair of gear rotation was crossed 90 °, the contraction in length of the trailing cable 7 on a pair of gear was the width between centers of two gears.
With reference to Fig. 7, described trailing cable control mechanism 3 is made up of motor 301 and rotating disk 302, twines flexible drawing rope 1 on each rotating disk, through the rotation direction of motor 301 control rotating disks 302, makes flexible drawing rope 1 flexible.The quality of the concrete number N considered device of flexible drawing rope and rotating disk also guarantees to cover face moulding requirement, and span is 3≤N≤192, and in this instance, the radical of flexible drawing rope and the number of rotating disk are six, i.e. N=6.
Choose the isodisperse of puckered ring according to the radical of flexible drawing rope 1, span is 3≤n≤720, in this instance; The puckered ring 4 that composition is covered face 2 is divided into three equal parts, i.e. n=3 passes an end of flexible drawing rope 1 in the perforate of equally divided position puckered ring; And kill knot, the other end of flexible drawing rope 1 is wrapped on the rotating disk of trailing cable control mechanism, forms coniform space structure; Concrete number Y confirms that with the number M that covers face span is Y>=M, in this instance according to flexible drawing rope number N; Form two coniform space structures, i.e. Y=2.The shared trailing cable control mechanism 3 of per two coniform space structures; I.e. each flexible drawing rope 1 in two coniform space structures; Be wrapped in respectively on each rotating disk of same trailing cable control mechanism 3, form by a trailing cable control mechanism and two integral body that coniform space structure is formed.
On cover the pipe cross section straight-bar that the face puckered ring adopts external diameter 0.03m, internal diameter 0.024m, cover the pipe cross section straight-bar that the face puckered ring adopts external diameter 0.024m, internal diameter 0.018m down, all adopt carbon fibre material.Connect the joint and adopt aluminum alloy materials.Then whole apparatus structure draws in the cylinder of Φ 0.8m * 5.4m, and its quality is less than 20Kg, and surface density is less than 0.03Kg/m
2, radially the rate of taking in is 0.008, height is 0.054 with the ratio of bore during gathering.
With reference to Fig. 8, the present invention by flexible drawing rope 1, cover face 2 and trailing cable control mechanism 3 is formed.Cover mask body number M and confirm that according to designing requirement span is 2≤M≤18, in this instance, choose three and launch the identical face that covers of bore, wherein, it is 30m that the face that respectively covers launches bore.
With reference to Fig. 9, each covers face 2, adopts puckered ring 4 and is connected joint 5 formation rigid constructiones, on rigid construction, binds flexible silk screen 8, constitutes the face 2 that covers.Puckered ring 4 is a plurality of, and concrete number 6X launches bore according to the face that covers and confirms that span is X >=1, and in this instance, three cover the face puckered ring and all get 24, totally 72 puckered rings, i.e. X=12.Per two puckered rings 4 connect joint 5 through one and connect; The rigid construction that formation can be drawn in, launched; Through connecting the driving and the locking in joint 5; Control rigid construction all puckered rings are deployed into the masking work state of level by vertical rounding state, form masking system by traction control mechanism controls flexible drawing rope again.All puckered rings 4 of each rigid construction draw on a face of cylinder or drum face, and the rigid construction of three gatherings is placed from top to bottom successively.Puckered ring in this rigid construction adopts straight-bar, to obtain the high rate of taking in, perhaps uses curvilinear rod, with the configuration precision that obtains.Solid section can be used in the cross section of puckered ring, perhaps adopts the hollow section structure, under the prerequisite of proof strength, rigidity, can further alleviate quality.Rigid construction has enough spaces in inside when drawing attitude in, can hold relevant rope net, silk screen or thin film flexible structure.
With reference to Fig. 3, Fig. 4 and Fig. 5, described connection joint 5 is by a pair of conical gear 501; 502 form with a pair of clamping plate 503,504, and conical gear is provided with guide groove 509; Conical gear is through gear wheel shaft 505 and a pair of clamping plate 503; 504 is fixing, and the chamber arm at each conical gear two ends is provided with tapped bore 508, and puckered ring 4 is connected with conical gear through this tapped bore.Place trailing cable 7 in the guide groove 509.When the ring bar is deployed into the mode of operation of level by vertical rounding state, and after forwarding expected angle to, through spring pin 510 and locking hole 511 locking joints.
With reference to Fig. 6, described extension spring drive configuration is placed with trailing cable 7 and extension spring 6 in the cavity of puckered ring 4, and trailing cable 7 is killed knot with extension spring 6 and is connected, and through stretching of extension spring 6, trailing cable 7 drives and connects joint 5 motions; When drawing in, extension spring 6 is in extended state, and extension spring 6 is parallel at vertical direction with the chamber arm that connects joint 5, and trailing cable 7 is two gear center distances and 1/2 tooth top circle girth sum around the length on a pair of gear; When launching, extension spring 6 is shunk and is driven trailing cable 7 motions that link to each other, and the transmission through trailing cable 7 drives a pair of gear and rotates, and when a pair of gear rotation was crossed 90 °, the contraction in length of the trailing cable 7 on a pair of gear was the width between centers of two gears.
With reference to Fig. 7, described traction institute control mechanism 3 is made up of motor 301 and rotating disk 302, twines the flexible drawing rope on each rotating disk, through the rotation direction of motor 301 control rotating disks 302, flexible drawing rope 1 is stretched.The quality of the concrete number N considered device of flexible drawing rope and rotating disk also guarantees to cover face moulding requirement, and span is 3≤N≤192, and in this instance, the radical of flexible drawing rope and the number of rotating disk are nine, i.e. N=9.
According to the isodisperse of puckered ring, span is 3≤n≤720, can choose the radical of flexible drawing rope 1.In this instance, the radical of choosing flexible drawing rope 1 is three, is about to form the puckered ring 4 that covers face 2 and is divided into three equal parts; In the perforate of equally divided position puckered ring, pass an end of flexible drawing rope 1, and kill knot, the other end of flexible drawing rope 1 is wrapped on the rotating disk of trailing cable control mechanism; Form coniform space structure, concrete number Y confirms that with the number M that covers face span is Y >=M according to flexible drawing rope number N; In this instance, form four coniform space structures, i.e. Y=4; Each coniform space structure uses a trailing cable control mechanism 3; It is each the flexible drawing rope 1 in each coniform space structure; Be wrapped on each rotating disk of a trailing cable control mechanism 3; These trailing cable control mechanism tractions connect, and form by four trailing cable control mechanisms and four integral body that coniform space structure is formed.
Puckered ring adopts 0.02m * 0.01m size, and the straight-bar in the rectangle hollow cross section of thickness 0.002m is selected carbon fibre material.Connect the joint and adopt aluminum alloy materials.Then whole device draws in the cylinder of Φ 0.25m * 4.0m, and its quality is less than 30Kg, and surface density is less than 0.03Kg/m
2, radially the rate of taking in is 0.016, height is 0.133 with the ratio of bore during gathering.
With reference to Figure 10, the present invention by flexible drawing rope 1, cover face 2 and flexible silk screen 8 is formed.Cover mask body number M and confirm that according to designing requirement span is 2≤M≤18, in this instance, choose two and launch the identical face that covers of bore, wherein, it is 30m that the face that respectively covers launches bore.
With reference to Figure 11, each covers face 2, adopts puckered ring 4 and is connected joint 5 formation rigid constructiones, on rigid construction, binds flexible silk screen 8, constitutes the face 2 that covers.Puckered ring 4 is a plurality of, and concrete number 6X launches bore according to the face that covers and confirms that span is X >=1, in this instance, covers the face puckered ring up and down and all gets 24, totally 48 puckered rings, i.e. X=8.Per two puckered rings 4 connect joint 5 through one and connect; The rigid construction that formation can be drawn in, launched; Through connecting driving, the locking in joint 5; Control rigid construction all puckered rings are deployed into the masking work state of level by vertical rounding state, form masking system by traction control mechanism controls flexible drawing rope again.All puckered rings 4 of each rigid construction draw on a face of cylinder or drum face, and the rigid construction of two gatherings is placed from top to bottom successively.Puckered ring in this rigid construction can adopt straight-bar, to obtain the high rate of taking in, also can adopt curvilinear rod, with the configuration precision that obtains.Solid section can be adopted in the cross section of puckered ring, also can adopt the hollow section structure, under the prerequisite of proof strength, rigidity, can further alleviate quality.Rigid construction has enough spaces in inside when drawing attitude in, can hold relevant rope net, silk screen or thin film flexible structure.
With reference to Fig. 3, Fig. 4 and Fig. 5, described connection joint 5 is by a pair of conical gear 501; 502 form with a pair of clamping plate 503,504, and conical gear is provided with guide groove 509; Conical gear is through gear wheel shaft 505 and a pair of clamping plate 503; 504 is fixing, and the chamber arm at each conical gear two ends is provided with tapped bore 508, and puckered ring 4 is connected with conical gear through this tapped bore.Place trailing cable 7 in the guide groove 509.When the ring bar is deployed into the mode of operation of level by vertical rounding state, and after forwarding expected angle to, through spring pin 510 and locking hole 511 locking joints.
With reference to Fig. 6, described extension spring drive configuration is placed with trailing cable 7 and extension spring 6 in the cavity of puckered ring 4, and trailing cable 7 is killed knot with extension spring 6 and is connected, and through stretching of extension spring 6, trailing cable 7 drives and connects joint 5 motions; When drawing in, extension spring 6 is in extended state, and extension spring 6 is parallel at vertical direction with the chamber arm that connects joint 5, and trailing cable 7 is two gear center distances and 1/2 tooth top circle girth sum around the length on a pair of gear; When launching, extension spring 6 is shunk and is driven trailing cable 7 motions that link to each other, and the transmission through trailing cable 7 drives a pair of gear and rotates, and when a pair of gear rotation was crossed 90 °, the contraction in length of the trailing cable 7 on a pair of gear was the width between centers of two gears.
The quality of the concrete number N considered device of flexible drawing rope also guarantees to cover face moulding requirement, and span is 3≤N≤192, and in this instance, the radical of flexible drawing rope is six, i.e. N=6.With on cover face puckered ring 4 be divided into six equal portions; Pass the perforate of an equally divided position puckered ring with an end of a flexible drawing rope, and kill knot, the flexible drawing rope other end pass with on cover the vertical following perforate of covering the face puckered ring of face; And kill knot; Accomplish the threading of six roots of sensation flexible drawing rope 1 successively, form with up and down two to cover face be the end, be the cylindric space structure of bus with six roots of sensation flexible drawing rope.
Puckered ring adopts 0.02m * 0.01m size, and the straight-bar in the rectangle hollow cross section of thickness 0.002m is selected carbon fibre material.Connect the joint and select aluminum alloy materials.Then whole device draws in the cylinder of Φ 0.25m * 4.0m, and its quality is less than 20Kg, and surface density is less than 0.03Kg/m
2, radially the rate of taking in is 0.008, height is 0.133 with the ratio of bore during gathering.
Single unit system of the present invention is under space environment, and the explosive bolt release is adopted in available rope, snap ring mechanism binding.Under the rounding state of binding, extension spring is in extended state; After removing binding, the stretching extension spring is shunk, and the trailing cable on gear mesh shortens, and gear mesh drives whole joint and launches under the effect of trailing cable tension force; After expansion put in place, the registration device that connects on the joint encircled rod lock with each, thereby formed the large-scale deployable face device that covers in space.
Effect of the present invention can further specify through following simulation result:
To launch bore be 100m to cover face in the embodiment of the invention one, and it is that the model of 50m is a simulation object that the face that covers down launches bore.
Figure 12 has showed under space environment; The kinetic model of the rigidity supporting structure of this device is by drawing the expansion process analogous diagram that attitude is launched in; Wherein, Figure 12 (a) is the expansion intermediate state in 12 seconds after the binding release, on cover that puckered ring launches, expands on the face circumference, the face that covers down draws in a little cylinder; Figure 12 (b) launched for 150 seconds, and previous vertical puckered ring had all rotated into the cross bar near level, on cover the face supporting construction and trended towards moulding; Figure 12 (c) is the expansion intermediate state in 158 seconds after the binding release, on cover face and launch fully, time cover face to launch, expand; Figure 12 (d) is 250 seconds after the binding release, and previous vertical puckered ring has all rotated into the cross bar near level, and covering the face supporting construction has also trended towards moulding down.
In Figure 13 expansion process; The motion change curve of a puckered ring barycenter of emulation; The result is shown in figure 13, and wherein, Figure 13 (a) is the displacement changing curve of this puckered ring barycenter; Figure 13 (b) is the speed change curves of this puckered ring barycenter, and Figure 13 (c) is the acceleration change curve of this puckered ring barycenter.
From Figure 13 (a), can see, this puckered ring by the curling position to complete expanded position.
Can see that from Figure 13 (b) puckered ring is quickening earlier to slow down in the expansion process gradually again, becomes zero until launching back speed fully.
Can see that from Figure 13 (c) puckered ring acceleration/accel in expansion process gradually reduces earlier to increase again, becomes zero at last.
Covering face with expansion bore 50m in the embodiment of the invention one is simulation object.
Figure 14 has showed that under space environment this kinetic model that covers face is by drawing the expansion process figure that attitude is launched in, and wherein, Figure 14 (a) is an intermediate state of launching for 5 seconds, and puckered ring begins to launch; Figure 14 (b) is an intermediate state of launching for 100 seconds; Figure 14 (c) is an intermediate state of launching for 200 seconds, and puckered ring further launches to horizontal direction.
50m covers in the face expansion process at the expansion bore; The motion change curve of a puckered ring barycenter of emulation; The result is shown in figure 15, and wherein, Figure 15 (a) is the displacement changing curve of this puckered ring barycenter; Figure 15 (b) is the speed change curves of this puckered ring, and Figure 15 (c) is the acceleration change curve of this puckered ring.
From Figure 15 (a), can see that this puckered ring is launched to desired location by the curling position gradually.
Can see that from Figure 15 (b) puckered ring goes to zero quickening earlier to slow down in the expansion process gradually gradually again.
Can see that from Figure 15 (c) puckered ring acceleration/accel in expansion process gradually reduces gradually, and goes to zero.
Above simulation result shows integral structure of the present invention can be under space environment smoothly, launch reposefully, and compare with existing domestic and international scheme, its surface density can reach 0.03Kg/m
2, radially the rate of taking in can reach 0.016, and height can reach 0.133 with the ratio of bore during gathering.
Can see through above specific embodiment and simulation result; Apparatus of the present invention at first are feasible; Secondly the light weight characteristic is remarkable aspect surface density, radially with short transverse the superior rate of taking in is being arranged all once more, and also guaranteed aspect the configuration precision; Therefore the excellent comprehensive performances index is arranged, significantly be superior to existing relevant programme both at home and abroad.
Claims (5)
1. a space rope is the deployable plane system that covers; Comprise: the puckered ring (4) of N root flexible drawing rope (1), a 6X perforate, 3X connection joint (5) and trailing cable control mechanism (3); Per two puckered rings (4) connect joint (5) through one and connect; Form M deployable rigid construction, it is characterized in that:
Trailing cable control mechanism (3) is made up of motor (301) and N rotating disk (302), twines the flexible drawing rope on each rotating disk, through the rotation direction of motor (301) N rotating disk of control (302), makes N root flexible drawing rope (1) flexible, 3≤N≤192;
On each deployable rigid construction, bind flexible silk screen (8) is arranged; Constitute M the deployable face (2) that covers; To form the deployable puckered ring (4) that covers face (2) and be divided into the n equal portions, and in the perforate of equally divided position puckered ring, pass an end of flexible drawing rope (1), and kill knot; The other end of flexible drawing rope (1) is wrapped on the rotating disk of trailing cable control mechanism, forms Y coniform space structure;
Per shared trailing cable control mechanisms of two coniform space structures (3), promptly each the flexible drawing rope (1) in two coniform space structures is wrapped in respectively on each rotating disk of same trailing cable control mechanism (3); The integral body that formation is made up of Y/2 trailing cable control mechanism and the individual coniform space structure of Y, wherein, 2≤M≤18; Y>=M; 3≤N≤192,3≤n≤720, X>=1.
2. space according to claim 1 rope is the deployable plane system that covers; It is characterized in that: connect joint (5) and form by a pair of conical gear (501,502) and a pair of clamping plate (503,504); Conical gear is provided with guide groove (509); Conical gear is fixing through gear wheel shaft (505) and a pair of clamping plate (503,504), and the chamber arm at each conical gear two ends is provided with tapped bore (508), and puckered ring (4) is connected with conical gear through this tapped bore.
3. space according to claim 1 rope is the deployable plane system that covers; It is characterized in that: be placed with trailing cable (7) and extension spring (6) in the cavity of puckered ring (4); Trailing cable (7) is killed knot with extension spring (6) and is connected; Through stretching of extension spring (6), trailing cable (7) drives and connects joint (5) motion;
When drawing in, extension spring (6) is in extended state, and extension spring (6) is parallel at vertical direction with the chamber arm that connects joint (5), and trailing cable (7) is two gear center distances and 1/2 tooth top circle girth sum around the length on a pair of gear;
When launching; Extension spring (6) is shunk and is driven trailing cable (7) motion that links to each other; Transmission through trailing cable (7) drives a pair of gear and rotates, and when a pair of gear rotation was crossed 90 °, the contraction in length of the trailing cable (7) on a pair of gear was the width between centers of two gears.
4. a space rope is the deployable plane system that covers; Comprise: the puckered ring (4) of N root flexible drawing rope (1), a 6X perforate, 3X connection joint (5) and trailing cable control mechanism (3); Per two puckered rings (4) connect joint (5) through one and connect; Form M deployable rigid construction, it is characterized in that:
Trailing cable control mechanism (3) is made up of motor (301) and N rotating disk (302), twines the flexible drawing rope on each rotating disk, through the rotation direction of motor (301) N rotating disk of control (302), makes N root flexible drawing rope (1) flexible;
Bind on each deployable rigid construction flexible silk screen (8) is arranged; Constitute M the deployable face (2) that covers; To form the deployable puckered ring (4) that covers face (2) and be divided into the n equal portions, and in the perforate of equally divided position puckered ring, pass an end of flexible drawing rope (1), and kill knot; The other end of flexible drawing rope (1) is wrapped on the rotating disk of trailing cable control mechanism, forms Y coniform space structure;
Each coniform space structure uses a trailing cable control mechanism (3), and promptly each the flexible drawing rope (1) in each coniform space structure is wrapped on each rotating disk of a trailing cable control mechanism (3); These trailing cable control mechanism tractions connect, and form by Y trailing cable control mechanism and Y the integral body that coniform space structure is formed, wherein; 2≤M≤18, Y>=M, 3≤N≤192; 3≤n≤720, X>=1.
5. a space rope is the deployable plane system that covers, and comprising: the puckered ring (4) of N root flexible drawing rope (1), a 6X perforate, a 3X connection joint (5), and per two puckered rings (4) connect joint (5) through one and connect; Form two deployable rigid constructiones, it is characterized in that: on two deployable rigid constructiones, bind flexible silk screen (8), constitute two deployable faces (2) that cover up and down; The puckered ring that covers face on deployable (4) is divided into the N equal portions, passes the perforate of an equally divided position puckered ring, and kill knot with an end of a flexible drawing rope; The flexible drawing rope other end pass with on cover the vertical following perforate of covering the face puckered ring of face; And kill knot, accomplish the threading of N root flexible drawing rope (1) successively, form with up and down two to cover face be the end; With N root flexible drawing rope is the cylindric space structure of bus; Wherein, 3≤N≤192, X>=1.
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| CN201210275277.6A CN102765490B (en) | 2012-08-03 | 2012-08-03 | Space tethered unfoldable covered surface system |
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| CN201210275277.6A CN102765490B (en) | 2012-08-03 | 2012-08-03 | Space tethered unfoldable covered surface system |
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| WO2017085455A1 (en) * | 2015-11-16 | 2017-05-26 | Oxford Space Systems Limited | Hinge |
| CN107651219A (en) * | 2017-08-30 | 2018-02-02 | 北京控制工程研究所 | A kind of centrifugal wire development mechanism |
| CN113879563A (en) * | 2021-12-06 | 2022-01-04 | 沈阳中科新宇空间智能装备有限公司 | Double-module extensible tensioning integral structure with self-extensible folding hinge |
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