CN102765490B - Space tethered unfoldable covered surface system - Google Patents
Space tethered unfoldable covered surface system Download PDFInfo
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- CN102765490B CN102765490B CN201210275277.6A CN201210275277A CN102765490B CN 102765490 B CN102765490 B CN 102765490B CN 201210275277 A CN201210275277 A CN 201210275277A CN 102765490 B CN102765490 B CN 102765490B
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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 space technology field, specifically space rope is the deployable plane system that covers, and can be used for the space Large Deployable systems such as space sun shade, spatially masked, spacing reflection mirror, space solar station.
Background technology
The earth outer space is that the new development in science and technology of the mankind and technological advance have brought huge opportunities and challenges.Along with the continuous enhancing of mankind's carrying space ability and the 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 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, as space solar light reflecting mirror, solar rail station, space elevator, space track translator etc.Because mankind's carrier rocket holds the restriction of size, carrying capacity, expensive, the high risk feature of AEROSPACE APPLICATION, the significant difference of ground development environment and space working environment, makes the design of space ultra-large type deployable structure become 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 just gradually too impatient to wait.Earth engineering is the huge artificial climate transformation planning that some scientific research personnel propose for mitigation of global climate warms in recent years.In numerous planning, Comparatively speaking, spacing reflection mirror is one of less preferred planning of quick result, secondary action.
For spacing reflection mirror planning, scientific research personnel has also proposed multiple embodiments conception.One of scheme is to place sunshine reflecting surface in near-earth orbit.American National science association proposed to place on near-earth random orbit the catadioptre that 55,000 single areas are 100 sq ms in 1992; Also someone proposes to generate in near-earth orbit with light satellite the reflection endless belt of similar ring of Saturn, and its total mass reaches 2,000,000,000 tons.Two of scheme is that its total mass exceedes 2,000 ten thousand tons between the earth and the sun, place numerous sunshine reflecting surfaces apart near the Lagrangian points of 1,500,000 kilometers of the earth.Because these scheme technical risks are too large, cost is too high, the cycle is oversize, is interpreted as it is science fiction unavoidably by people.
Space ultra-large type deployable structure, due to its ultralight superthin structure feature and oversize, has the feature of many uniquenesses and faces many new challenges.First being to launch moulding problem, is secondly stability control problem.
Comparatively speaking, existing, relatively feasible various spaces Large Deployable organization plan at present both at home and abroad, its development size is all less than 100 meters, and all too negligible for spatially masked plane system, effect is very micro-.Because its surface density is large, if its size expands, in long-time, the mankind's means of delivery is all difficult to carry its huge quality.In existing document, the known the lightest Large Deployable structure in space is 20 meters of square film solar arrays of the U.S. at present, 4 microns of its film thicknesses, and surface density is 87.5g/m
2.But for the space ultra-large type of 1000 meters of bores is covered plane system, its surface density is still too large.Japan has proposed to involve film surrounding with multi-satellite, build the concept on huge surface, space, enumerate with four each satellites of 1 ton, involve 500 meters of 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, but the moulding of this mode and control, its technical risk is large, and feasibility is poor.
Summary of the invention
The object of the invention is to the deficiency for above-mentioned prior art, it is the deployable plane system that covers that a kind of space rope is provided, by application of weight Gradient Effect, be deployable effective expansion moulding of covering face with the large-scale rope in implementation space, improve the self-stability of track profile.
For achieving the above object, the present invention provides following three kinds of technical schemes:
Technical scheme 1, comprising: puckered ring 4, the 3X of N root flexible drawing rope 1, a 6X perforate connect joint 5 and trailing cable control mechanism 3, and every two collapsible ring bars 4 connect joint 5 by one and connect, and 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, is wound around flexible drawing rope on each rotating disk, controls the rotation direction of N rotating disk 302 by motor 301, makes N root flexible drawing rope 1 flexible, 3≤N≤192;
On each deployable rigid construction, binding has flexible silk screen 8, form M the deployable face 2 that covers, the deployable puckered ring 4 that covers face 2 of composition is divided into n equal portions, in the perforate of equally divided position puckered ring, pass one 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;
Every two coniform space structures share a trailing cable control mechanism 3, 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 Y/2 trailing cable control mechanism and Y the entirety that coniform space structure forms, 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 compositions, conical gear is provided with guide groove 509, and conical gear is fixing with a pair of clamping plate 503,504 by gear wheel shaft 505, the chamber arm at each conical gear two ends is provided with tapped bore 508, and puckered ring 4 is connected with conical gear by this tapped bore.
As preferably, in the cavity of described 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 by stretching of extension spring 6, trailing cable 7 is with the joint 5 that is dynamically connected to move;
In the time 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 centers distances and 1/2 tooth top circle girth sum around the length on a pair of gear;
In the time launching, extension spring 6 is shunk and is driven connected trailing cable 7 to move, and drives a pair of gear to rotate by the transmission of trailing cable 7, in the time that a pair of gear turns over 90 °, is the width between centers of two gears around the contraction in length of the trailing cable 7 on a pair of gear.
Technical scheme 2, comprising: puckered ring 4, the 3X of N root flexible drawing rope 1, a 6X perforate connect joint 5 and trailing cable control mechanism 3, and every two collapsible ring bars 4 connect joint 5 by one and connect, and 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, is wound around flexible drawing rope on each rotating disk, controls the rotation direction of N rotating disk 302 by motor 301, makes N root flexible drawing rope 1 flexible;
On each deployable rigid construction, binding has flexible silk screen 8, form M the deployable face 2 that covers, the deployable puckered ring 4 that covers face 2 of composition is divided into n equal portions, in the perforate of equally divided position puckered ring, pass one 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, it is the each 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 Y trailing cable control mechanism and Y the entirety that coniform space structure forms, wherein, 2≤M≤18, Y >=M, 3≤N≤192,3≤n≤720, X >=1.
Technical scheme 3, comprise: N root flexible drawing rope 1, the puckered ring 4 of 6X perforate, 3X connects joint 5, every two collapsible ring bars 4 connect joint 5 by one and connect, form two deployable rigid constructiones, it is characterized in that: on two deployable rigid constructiones, bind flexible silk screen 8, form upper and lower two deployable faces 2 that cover, the puckered ring 4 that covers face on deployable is divided into N equal portions, pass the perforate of an equally divided position puckered ring with one end of a flexible drawing rope, and kill knot, the flexible drawing rope other end is through the perforate of covering face puckered ring under vertical with the face that above covers, and kill knot, complete successively the threading of N root flexile hauling cable 1, form and cover face the end of as taking upper and lower two, cylindric space structure taking N root flexile hauling cable as bus, wherein, 3≤N≤192, X >=1.
The present invention's tool compared with existing correlation technique has the following advantages:
(1) plane system that covers with trailing cable control mechanism and coniform space structure composition that the present invention proposes more, and the cylindric plane system that covers, application of weight Gradient Effect, can ensure the autonomous stable of whole system track and attitude, making hundred meters of above ultra-large types of space application bore cover face becomes possibility.
(2) three kinds of technical schemes that the present invention proposes, while gathering on ground, application space means of delivery is by its carrying and transmitting effectively.
(3) what the present invention proposed pass through extension spring and the trailing cable band mode of joint motions that is dynamically connected, autonomous expansion and the effectively moulding that can realize hundred meters of above ultra-large types of bore and cover face.
Brief description of the drawings
Fig. 1 is the deployed condition structural representation of the embodiment of the present invention 1;
Fig. 2 is the gathering state schematic diagram of Fig. 1;
Fig. 3 is connection articulation structure schematic diagram of the present invention;
Fig. 4 is that Fig. 3 connects joint and draws state trailing cable in walk path schematic diagram in joint;
Fig. 5 is that Fig. 3 connects joint deployed condition trailing cable walk path schematic diagram in joint;
Fig. 6 is extension spring drive configuration schematic diagram of the present invention;
Fig. 7 is trailing cable control mechanism schematic diagram of the present invention;
Fig. 8 is the deployed condition configuration diagram of the embodiment of the present invention 2;
Fig. 9 is the gathering state structural representation of Fig. 8;
Figure 10 is the deployed condition structural representation of the embodiment of the present invention 3;
Figure 11 is the gathering state structural representation of Figure 10;
Figure 12 is the expansion process schematic diagram of Fig. 1;
Figure 13 is that Figure 12 structure is at the motion change curve that launches a puckered ring in simulation process;
Figure 14 is that Figure 12 structure medium caliber 50m covers face expansion process schematic diagram;
Figure 15 is that Figure 14 structure is at the motion change curve that launches a puckered ring barycenter in simulation process.
Detailed description of the invention
Embodiment 1
With reference to Fig. 1 the present invention by flexible drawing rope 1, cover face 2 and trailing cable control mechanism 3 forms.Cover mask body number M and determine according to designing requirement, span is 2≤M≤18, in this example, chooses upper and lower two and launches bore different faces that cover, and wherein, it is 100m that the face that above covers launches bore, under cover face to launch bore be 50m.
With reference to Fig. 2, each face 2 that covers, adopts puckered ring 4 and is connected joint 5 and forms rigid construction, binds flexible silk screen 8 on rigid construction, and formation is covered face 2.Puckered ring 4 is a plurality of, and concrete number 6X launches bore according to the face that covers and determines, span is X >=1, in this example, covers up and down face puckered ring and all gets 24, totally 48 puckered rings, i.e. X=8.Every two puckered rings 4 connect joint 5 by one and connect, the rigid construction that formation can be drawn in, be launched.By connecting driving and the locking in joint 5, control all puckered rings of rigid construction and be deployed into the masking work state of level by vertical rounding state, then form masking system by traction control mechanism controls flexible drawing rope.All puckered rings 4 of each rigid construction draw on a face of cylinder or drum face, the inside and outside nested placement of the rigid construction of two gatherings.Puckered ring in this rigid construction adopts straight-bar, to obtain high storage rate, or adopts curvilinear rod, with the configuration precision obtaining.The cross section of puckered ring adopts solid section, or adopts hollow section structure, under the prerequisite of proof strength, rigidity, can further alleviate quality.Rigid construction has enough spaces in inside in the time drawing state 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, by a pair of conical gear 501,502 and a pair of clamping plate 503,504 composition, conical gear is provided with guide groove 509, conical gear is by 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 by this tapped bore.The interior placement trailing cable 7 of guide groove 509, this trailing cable is connected with extension spring.When ring bar is deployed into the mode of operation of level by vertical rounding state, and forwarding to after expected angle, locking joint by spring pin 510 and locking hole 511.
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 by stretching of extension spring 6, trailing cable 7 is with the joint 5 that is dynamically connected to move; In the time 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 centers distances and 1/2 tooth top circle girth sum around the length on a pair of gear; In the time launching, extension spring 6 is shunk and is driven connected trailing cable 7 to move, and drives a pair of gear to rotate by the transmission of trailing cable 7, in the time that a pair of gear turns over 90 °, is the width between centers of two gears around the contraction in length of the trailing cable 7 on a pair of gear.
With reference to Fig. 7, described trailing cable control mechanism 3, is made up of motor 301 and rotating disk 302, is wound around flexible drawing rope 1 on each rotating disk, controls the rotation direction of rotating disk 302 by motor 301, makes flexible drawing rope 1 flexible.The concrete number N of flexible drawing rope and rotating disk should consider that the quality of device also ensures to cover face forming requirements, and span is 3≤N≤192, and in this example, 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 example, the puckered ring 4 that composition is covered to face 2 is divided into three equal parts, be n=3, in the perforate of equally divided position puckered ring, pass one 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 coniform space structure, and concrete number Y determines with the number M that covers face according to flexible drawing rope number N, span is Y >=M, in this example, form two coniform space structures, i.e. Y=2.Every two coniform space structures share a trailing cable control mechanism 3, 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 entirety that coniform space structure forms.
On cover face puckered ring and adopt the circular hollow section straight-bar of external diameter 0.03m, internal diameter 0.024m, under cover face puckered ring and adopt the circular hollow section straight-bar of external diameter 0.024m, internal diameter 0.018m, all adopt carbon fibre material.Connect joint and adopt aluminum alloy materials.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 storage rate is 0.008, when gathering, height is 0.054 with the ratio of bore.
Embodiment 2
With reference to Fig. 8, the present invention by flexible drawing rope 1, cover face 2 and trailing cable control mechanism 3 forms.Cover mask body number M and determine according to designing requirement, span is 2≤M≤18, in this example, chooses three and launches the identical face that covers of bore, and wherein, it is 30m that the face that respectively covers launches bore.
With reference to Fig. 9, each face 2 that covers, adopts puckered ring 4 and is connected joint 5 and forms rigid construction, binds flexible silk screen 8 on rigid construction, and formation is covered face 2.Puckered ring 4 is a plurality of, and concrete number 6X launches bore according to the face that covers and determines, span is X >=1, and in this example, three cover face puckered ring and all get 24, totally 72 puckered rings, i.e. X=12.Every two puckered rings 4 connect joint 5 by one and connect, the rigid construction that formation can be drawn in, be launched, by connecting driving and the locking in joint 5, control all puckered rings of rigid construction and be deployed into the masking work state of level by vertical rounding state, then form masking system by traction control mechanism controls flexible drawing rope.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 high storage rate, or by curvilinear rod, with the configuration precision obtaining.Solid section can be used in the cross section of puckered ring, or adopts hollow section structure, under the prerequisite of proof strength, rigidity, can further alleviate quality.Rigid construction has enough spaces in inside in the time drawing state 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, by a pair of conical gear 501,502 and a pair of clamping plate 503,504 composition, conical gear is provided with guide groove 509, conical gear is by 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 by this tapped bore.The interior placement trailing cable 7 of guide groove 509.When ring bar is deployed into the mode of operation of level by vertical rounding state, and forwarding to after expected angle, locking joint by spring pin 510 and locking hole 511.
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 by stretching of extension spring 6, trailing cable 7 is with the joint 5 that is dynamically connected to move; In the time 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 centers distances and 1/2 tooth top circle girth sum around the length on a pair of gear; In the time launching, extension spring 6 is shunk and is driven connected trailing cable 7 to move, and drives a pair of gear to rotate by the transmission of trailing cable 7, in the time that a pair of gear turns over 90 °, is the width between centers of two gears around the contraction in length of the trailing cable 7 on a pair of gear.
With reference to Fig. 7, described traction institute control mechanism 3, is made up of motor 301 and rotating disk 302, is wound around flexible drawing rope on each rotating disk, controls the rotation direction of rotating disk 302 by motor 301, makes flexible drawing rope 1 flexible.The concrete number N of flexible drawing rope and rotating disk should consider that the quality of device also ensures to cover face forming requirements, and span is 3≤N≤192, and in this example, 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 example, the radical of choosing flexible drawing rope 1 is three, and the puckered ring 4 that covers face 2 by composition is divided into three equal parts, passes one 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, and concrete number Y determines with the number M that covers face according to flexible drawing rope number N, span is Y >=M, in this example, form four coniform space structures, i.e. Y=4; Each coniform space structure uses a trailing cable control mechanism 3, it is the each 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 entirety that coniform space structure forms.
Puckered ring adopts 0.02m × 0.01m size, and the straight-bar of the rectangular hollow section of thickness 0.002m is selected carbon fibre material.Connect joint and adopt aluminum alloy materials.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 storage rate is 0.016, when gathering, height is 0.133 with the ratio of bore.
Embodiment 3
With reference to Figure 10, the present invention by flexible drawing rope 1, cover face 2 and flexible silk screen 8 forms.Cover mask body number M and determine according to designing requirement, span is 2≤M≤18, in this example, chooses two and launches the identical face that covers of bore, and wherein, it is 30m that the face that respectively covers launches bore.
With reference to Figure 11, each face 2 that covers, adopts puckered ring 4 and is connected joint 5 and forms rigid construction, binds flexible silk screen 8 on rigid construction, and formation is covered face 2.Puckered ring 4 is a plurality of, and concrete number 6X launches bore according to the face that covers and determines, span is X >=1, in this example, covers up and down face puckered ring and all gets 24, totally 48 puckered rings, i.e. X=8.Every two puckered rings 4 connect joint 5 by one and connect, the rigid construction that formation can be drawn in, be launched, by connecting driving, the locking in joint 5, control all puckered rings of rigid construction and be deployed into the masking work state of level by vertical rounding state, then form masking system by traction control mechanism controls flexible drawing rope.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 high storage rate, also can adopt curvilinear rod, with the configuration precision obtaining.The cross section of puckered ring can adopt solid section, also can adopt hollow section structure, under the prerequisite of proof strength, rigidity, can further alleviate quality.Rigid construction has enough spaces in inside in the time drawing state 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, by a pair of conical gear 501,502 and a pair of clamping plate 503,504 composition, conical gear is provided with guide groove 509, conical gear is by 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 by this tapped bore.The interior placement trailing cable 7 of guide groove 509.When ring bar is deployed into the mode of operation of level by vertical rounding state, and forwarding to after expected angle, locking joint by spring pin 510 and locking hole 511.
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 by stretching of extension spring 6, trailing cable 7 is with the joint 5 that is dynamically connected to move; In the time 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 centers distances and 1/2 tooth top circle girth sum around the length on a pair of gear; In the time launching, extension spring 6 is shunk and is driven connected trailing cable 7 to move, and drives a pair of gear to rotate by the transmission of trailing cable 7, in the time that a pair of gear turns over 90 °, is the width between centers of two gears around the contraction in length of the trailing cable 7 on a pair of gear.
The concrete number N of flexible drawing rope should consider that the quality of device also ensures to cover face forming requirements, and span is 3≤N≤192, and in this example, the radical of flexible drawing rope is six, i.e. N=6.By on cover face puckered ring 4 be divided into six equal portions, pass the perforate of an equally divided position puckered ring with one end of a flexible drawing rope, and kill knot, the flexible drawing rope other end is through the perforate of covering face puckered ring under vertical with the face that above covers, and kill knot, complete successively the threading of six roots of sensation flexile hauling cable 1, form and cover face the end of as, the cylindric space structure taking six roots of sensation flexile hauling cable as bus taking upper and lower two.
Puckered ring adopts 0.02m × 0.01m size, and the straight-bar of the rectangular hollow section of thickness 0.002m is selected carbon fibre material.Connect joint and select aluminum alloy materials.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 storage rate is 0.008, when gathering, height is 0.133 with the ratio of bore.
Single unit system of the present invention is under space environment, and available rope, snap ring mechanism binding, adopt explosive bolt release.Under the rounding state of binding, extension spring is in extended state; Remove after binding, stretching extension spring is shunk, and the trailing cable on gear mesh shortens, and gear mesh drives whole joint to launch under the effect of trailing cable tension force; After expansion puts in place, the registration device on connection joint, by each ring rod lock, covers face device thereby form space Large Deployable.
Effect of the present invention can further illustrate by following simulation result:
Emulation 1
Launch bore as 100m to cover face in the embodiment of the present invention one, under cover face to launch bore be 50m that model is simulation object.
Figure 12 has shown under space environment, the kinetic model of the rigidity supporting structure of this device is by the expansion process analogous diagram of drawing state in and launching, wherein, Figure 12 (a) is the expansion intermediate state in 12 seconds after binding release, on cover puckered ring on face circumference and launch, expand, under cover face and draw in a little cylinder; Figure 12 (b) launched for 150 seconds, and previously vertical puckered ring had all rotated into the cross bar of the level of approaching, above covered face supporting construction and had trended towards moulding; Figure 12 (c) is the expansion intermediate state in 158 seconds after binding release, and the face that above covers launches completely, under cover face and launch, expand; Figure 12 (d) is 250 seconds after binding release, and previously vertical puckered ring had all rotated into the cross bar of the level of approaching, under cover face supporting construction and also trended towards moulding.
In Figure 13 expansion process, the motion change curve of a puckered ring barycenter of emulation, result as shown in figure 13, 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 curling position to complete expanded position.
From Figure 13 (b), can see, puckered ring is first accelerating to slow down in expansion process gradually, until speed becomes zero after launching completely again.
From Figure 13 (c), can see, puckered ring acceleration/accel in expansion process gradually first reduces to increase again, finally becomes zero.
Emulation 2
Cover face as simulation object to launch bore 50m in the embodiment of the present invention one.
Figure 14 shown under space environment, and this kinetic model that covers face is by the expansion process figure that draws state in and launch, and wherein, Figure 14 (a) is the intermediate state of launching for 5 seconds, and puckered ring starts to launch; Figure 14 (b) is the intermediate state of launching for 100 seconds; Figure 14 (c) is the intermediate state of launching for 200 seconds, and puckered ring further launches to horizontal direction.
At expansion bore, 50m covers in face expansion process, the motion change curve of a puckered ring barycenter of emulation, result as shown in figure 15, 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, this puckered ring is launched to desired location gradually by curling position.
From Figure 15 (b), can see, puckered ring, first accelerating to slow down in expansion process gradually, goes to zero gradually again.
From Figure 15 (c), can see, 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 storage rate can reach 0.016, and when gathering, height can reach 0.133 with the ratio of bore.
Can see by above specific embodiment and simulation result, first apparatus of the present invention are feasible, secondly aspect surface density, light weight characteristic is remarkable, again radially there iing superior storage rate with short transverse, and also guaranteed aspect configuration precision, therefore there is good integrated performance index, be significantly better than domestic and international existing relevant programme.
Claims (5)
1. a space rope is the deployable plane system that covers, comprise: puckered ring (4), the 3X of N root flexible drawing rope (1), a 6X perforate connect joint (5) and trailing cable control mechanism (3), every two puckered rings (4) connect joint (5) by 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), on each rotating disk, be wound around flexible drawing rope, control the rotation direction of N rotating disk (302) by motor (301), make N root flexible drawing rope (1) flexible, 3≤N≤192;
On each deployable rigid construction, binding has flexible silk screen (8), form M the deployable face (2) that covers, the deployable puckered ring (4) that covers face (2) of composition is divided into n equal portions, in the perforate of equally divided position puckered ring, pass one 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;
Every two coniform space structures share a trailing cable control mechanism (3), 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 Y/2 trailing cable control mechanism and Y the entirety that coniform space structure forms, 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 formed 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 by 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 by this tapped bore.
3. space according to claim 1 rope is the deployable plane system that covers, it is characterized in that: 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, by stretching of extension spring (6), trailing cable (7) is with joint (5) motion that is dynamically connected;
In the time drawing in, extension spring (6) is in extended state, extension spring (6) is parallel at vertical direction with the chamber arm that connects joint (5), and trailing cable (7) is two gear centers distances and 1/2 tooth top circle girth sum around the length on a pair of gear;
In the time launching, extension spring (6) is shunk and is driven connected trailing cable (7) motion, drive a pair of gear to rotate by the transmission of trailing cable (7), in the time that a pair of gear turns over 90 °, be the width between centers of two gears around the contraction in length of the trailing cable (7) on a pair of gear.
4. a space rope is the deployable plane system that covers, comprise: puckered ring (4), the 3X of N root flexible drawing rope (1), a 6X perforate connect joint (5) and trailing cable control mechanism (3), every two puckered rings (4) connect joint (5) by 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), on each rotating disk, be wound around flexible drawing rope, control the rotation direction of N rotating disk (302) by motor (301), make N root flexible drawing rope (1) flexible;
On each deployable rigid construction, binding has flexible silk screen (8), form M the deployable face (2) that covers, the deployable puckered ring (4) that covers face (2) of composition is divided into n equal portions, in the perforate of equally divided position puckered ring, pass one 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), it is the each 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 Y trailing cable control mechanism and Y the entirety that coniform space structure forms, 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, comprise: N root flexible drawing rope (1), the puckered ring (4) of 6X perforate, 3X connects joint (5), every two puckered rings (4) connect joint (5) by one and connect, form two deployable rigid constructiones, it is characterized in that: on two deployable rigid constructiones, bind flexible silk screen (8), form upper and lower two deployable faces (2) that cover, the puckered ring (4) that covers face on deployable is divided into N equal portions, pass the perforate of an equally divided position puckered ring with one end of a flexible drawing rope, and kill knot, the flexible drawing rope other end is through the perforate of covering face puckered ring under vertical with the face that above covers, and kill knot, complete successively the threading of N root flexile hauling cable (1), form and cover face the end of as taking upper and lower two, cylindric space structure taking N root flexile hauling cable as 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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| GB201520187D0 (en) * | 2015-11-16 | 2015-12-30 | Oxford Space Systems Ltd | Hinge |
| CN105667841B (en) * | 2016-01-29 | 2017-03-29 | 中国人民解放军国防科学技术大学 | For the in-orbit hexagon netting storage method for packing arrested |
| CN107651219B (en) * | 2017-08-30 | 2019-06-18 | 北京控制工程研究所 | A kind of centrifugal conducting wire unfolding mechanism |
| CN113879563B (en) * | 2021-12-06 | 2022-04-12 | 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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|---|---|---|---|---|
| US4030102A (en) * | 1975-10-23 | 1977-06-14 | Grumman Aerospace Corporation | Deployable reflector structure |
| CN101314411A (en) * | 2008-02-01 | 2008-12-03 | 西安电子科技大学 | Shielding surface apparatus with space capable of being expanded |
| CN102011922A (en) * | 2010-12-03 | 2011-04-13 | 西安电子科技大学 | Deployable surface device with fixed truss structure |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5963182A (en) * | 1997-07-07 | 1999-10-05 | Bassily; Samir F. | Edge-supported umbrella reflector with low stowage profile |
| JP3567163B2 (en) * | 2001-01-29 | 2004-09-22 | 独立行政法人 宇宙航空研究開発機構 | Storage and deployment type frame structure |
| US7216995B2 (en) * | 2003-09-10 | 2007-05-15 | Nippon Telegraph And Telephone Corporation | Deployable reflector |
| JP4876941B2 (en) * | 2007-01-31 | 2012-02-15 | 三菱電機株式会社 | Deployable antenna |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4030102A (en) * | 1975-10-23 | 1977-06-14 | Grumman Aerospace Corporation | Deployable reflector structure |
| CN101314411A (en) * | 2008-02-01 | 2008-12-03 | 西安电子科技大学 | Shielding surface apparatus with space capable of being expanded |
| CN102011922A (en) * | 2010-12-03 | 2011-04-13 | 西安电子科技大学 | Deployable surface device with fixed truss structure |
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| JP特开2002-220096A 2002.08.06 |
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