CN217805341U - Sun wing spreading guiding and constant force tensioning mechanism - Google Patents
Sun wing spreading guiding and constant force tensioning mechanism Download PDFInfo
- Publication number
- CN217805341U CN217805341U CN202221836855.4U CN202221836855U CN217805341U CN 217805341 U CN217805341 U CN 217805341U CN 202221836855 U CN202221836855 U CN 202221836855U CN 217805341 U CN217805341 U CN 217805341U
- Authority
- CN
- China
- Prior art keywords
- tensioning
- wheel
- constant force
- guiding
- solar
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Landscapes
- Wind Motors (AREA)
Abstract
The application relates to a solar wing spreads guide and constant force straining device, the whole battle array face top and the bottom of solar wing are provided with top load bearing device and bottom load bearing device respectively, guide and constant force straining device include: one end of the guiding mechanism is arranged on the top bearing device of the solar wing array surface, and the other end of the guiding mechanism is arranged on the bottom bearing device, so that the extending direction limiting function is provided for the solar wing array surface when the solar wing array surface is extended; the constant-force tensioning mechanism comprises a tensioning rope and a tensioning wheel assembly which are connected, one end of the tensioning rope is connected with the tensioning wheel assembly, the other end of the tensioning rope is connected with the wing surface at the bottom of the solar wing array surface, and the tensioning wheel assembly is arranged on the bottom bearing device and provides constant tensioning force for the tensioning rope. The scheme of the application can realize the orderly expansion of the in-process of the flexible wing array surface and provide stable tension suitable for thermal deformation, can improve the rigidity and the planeness of the whole wing surface, and has the advantages of simple structure and light weight.
Description
Technical Field
The disclosure relates to the technical field of solar wings, in particular to a solar wing unfolding guide and constant force tensioning mechanism.
Background
In recent years, the energy demand of spacecrafts is gradually increased, and the application of large flexible solar wings is more and more extensive. Because the flexible solar wings are flexibly connected among the plates, the array surfaces of the flexible solar wings are floating due to the fact that the flexible solar wings are free from constraint in the vertical unfolding direction. The flexible wing has low rigidity, and in order to ensure that the array surface does not interfere with the unfolding mechanism and the array surface is stably unfolded in the unfolding process so as to meet the requirements of unfolding fundamental frequency and control strategy implementation, the tensioning of the whole array surface is generally realized by adopting tensioning forces at two ends.
At present, the tensioning devices of some solar wings are complex in structure and heavy in weight, which is a negative factor for the overall aerospace equipment, and improvement or improvement on the tensioning devices is needed.
SUMMERY OF THE UTILITY MODEL
The present disclosure provides a solar wing deployment guide and constant force tensioning mechanism to enable the front surface deployment direction guide and the wing surface tensioning control of the deployment of the solar wing and to make the structure simple.
According to the present disclosure, there is provided a solar wing spreading guiding and constant force tensioning mechanism, the whole front top and bottom of the solar wing being provided with a load bearing device, the guiding and constant force tensioning mechanism comprising:
the guiding mechanism is arranged between the top bearing device and the bottom bearing device of the solar wing array surface and provides an unfolding direction limiting function for the solar wing array surface when the solar wing array surface is unfolded;
the constant-force tensioning mechanism is arranged at the bottom of the solar wing array surface and comprises a tensioning rope and a tensioning wheel assembly which are connected, one end of the tensioning rope is connected with the tensioning wheel assembly, the other end of the tensioning rope is connected with the wing surface at the bottom of the solar wing array surface, and the tensioning wheel assembly provides constant tensioning force for the tensioning rope.
According to this application example embodiment, tensioning wheel subassembly includes take-up pulley, short spring and support arm, the one end of tensioning rope twine in the take-up pulley, the one end of short spring is twined through the support arm, the other end of short spring twines through the take-up pulley and with take-up pulley fixed connection, short spring with the support arm reaches the whole "S" type that is of the winding appearance of take-up pulley.
According to an exemplary embodiment of the application, the short spring comprises one or more stacked spring leaves.
According to an exemplary embodiment of the application, the support arm is a cylinder or a roller having a central axis parallel to the axis of the tensioning wheel.
According to an exemplary embodiment of the application, the short spring is wound through the support arm no more than 1 turn.
According to an example embodiment of the present application, the guide mechanism includes a guide rope, a guide rope wheel assembly, and a tension storage assembly connected with the guide rope wheel assembly and transmitting a tension torque to the guide rope wheel assembly, one end of the guide rope is connected with the guide rope wheel assembly to receive a tension force, and the other end of the guide rope is movably connected to the top carrier through a front surface of the solar wing.
According to this application example embodiment, the guide rope sheave subassembly includes guide rope sheave and pivot wheel, guide rope sheave and pivot wheel coaxial setting, guide rope sheave and pivot wheel all with axle fixed connection, the pivot wheel is used for connecting tension storage component.
According to the embodiment of the application example, the guide rope wheel and the rotating shaft wheel are connected with the shaft through keys, or the end parts of the guide rope wheel and the rotating shaft wheel are in compression connection through nuts, or the square shaft is matched with the square hole.
According to this application example embodiment, tension storage assembly includes storage wheel and fixed moment spiral spring, fixed moment spiral spring's one end fix and wind in the storage wheel is last to store tension, the other end wind the warp the pivot wheel and with pivot wheel fixed connection.
According to the embodiment of the application, the guide mechanism and the constant force tensioning mechanism are respectively provided with a plurality of sets, the sets are arranged at intervals in the transverse direction of the solar wing, and the guide mechanism and the constant force tensioning mechanism in each set are arranged adjacently.
The flexible solar wing can be orderly unfolded along with the guide mechanism in the unfolding process, the unfolding track of the solar wing is controllable, the tensioning mechanism can realize constant force tensioning, the rigidity and the planeness of the whole wing surface can be improved, the flexible solar wing can passively adapt to the thermal deformation of the whole solar wing space, and the flexible solar wing is simple in structure and light in weight.
For a further understanding of the nature and technical content of the invention, reference should be made to the following detailed description and accompanying drawings, which are provided for illustration only and are not intended to limit the scope of the invention.
Drawings
Embodiments of the present disclosure are described in detail below with reference to the accompanying drawings. The accompanying drawings, which are incorporated herein and constitute part of this disclosure, serve to provide a further understanding of the disclosure. The exemplary embodiments of the present disclosure and their description are provided to explain the present disclosure and not to limit the present disclosure. In the drawings:
FIG. 1 shows a schematic structural view of a solar wing and deployment guidance and constant force tensioning mechanism according to an exemplary embodiment of the present application;
FIG. 2 shows a schematic structural diagram of a deployment guidance and constant force tensioning mechanism according to an example embodiment of the present application;
FIG. 3 shows a schematic structural diagram of a constant force tensioning mechanism according to an example embodiment of the present application;
FIG. 4 shows a schematic structural view of a short spring in connection with a tensioner according to an example embodiment of the present application;
fig. 5 shows a schematic structural view of a guide mechanism according to an exemplary embodiment of the present application.
List of reference numerals:
c1 top bearing device 1021 guide rope wheel
10 guide mechanism 103 tension storage assembly
101 guide rope 1031 storage wheel
102 guide sheave assembly 1032 constant-moment scroll spring
20 constant force tensioning mechanism 2022 short spring
201 tensioning rope 2023 support arm
202 tension wheel assembly 2024 screw
2021 tension wheel
Detailed Description
Example embodiments will now be described more fully with reference to the accompanying drawings. Example embodiments may, however, be embodied in many different forms and should not be construed as limited to the embodiments set forth herein; rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the concept of example embodiments to those skilled in the art. The same reference numerals denote the same or similar parts in the drawings, and thus, a repetitive description thereof will be omitted.
The described features, structures, or characteristics may be combined in any suitable manner in one or more embodiments. In the following description, numerous specific details are provided to give a thorough understanding of embodiments of the disclosure. One skilled in the relevant art will recognize, however, that the embodiments of the disclosure can be practiced without one or more of the specific details, or with other means, components, materials, devices, etc. In such cases, well-known structures, methods, devices, implementations, materials, or operations are not shown or described in detail.
The flow charts shown in the drawings are merely illustrative and do not necessarily include all of the contents and operations/steps, nor do they necessarily have to be performed in the order described. For example, some operations/steps may be decomposed, and some operations/steps may be combined or partially combined, so that the actual execution sequence may be changed according to the actual situation.
The terms "first," "second," and the like in the description and claims of the present application and in the foregoing drawings are used for distinguishing between different objects and not for describing a particular sequential order. Furthermore, the terms "include" and "have," as well as any variations thereof, are intended to cover non-exclusive inclusions. For example, a process, method, system, article, or apparatus that comprises a list of steps or elements is not limited to only those steps or elements listed, but may alternatively include other steps or elements not listed, or inherent to such process, method, article, or apparatus.
The application provides a guiding and constant force tensioning mechanism suitable for the flexible solar wing unfolding process. The mechanism uses the constant torque spring to realize the constant tension and the guided configuration, can realize the orderly expansion of the flexible wing and the stable tension adaptive to thermal deformation, and has simple structure and light weight.
Fig. 1 shows a schematic structural diagram of a solar wing and a deployment guidance and constant force tensioning mechanism according to an embodiment of the present application.
The top and bottom of the entire array of solar wings are provided with bearing devices on which support structures Z can be provided to mount the guiding and constant force tensioning mechanisms of the present application. The guiding and constant force tensioning mechanism mainly comprises a guiding mechanism 10 and a constant force tensioning mechanism 20, wherein the guiding mechanism 10 is used for guiding and controlling the unfolding of the wing surfaces of the solar wings, so that the wing surfaces of the solar wings can be unfolded orderly, and the constant force tensioning mechanism 20 is used for effectively tensioning the bottommost solar wings, so that on one hand, the controllable unfolding of proper tensioning can be ensured when the solar wings are unfolded, and on the other hand, the solar wings can adapt to uncertain factors in work such as thermal deformation and the like, so that the solar wings are in proper flatness.
The support structure Z may be provided as desired, such as the illustrated frame structure.
As shown in fig. 1, the solar wing is unfolded by the unfolding mechanism through the top bearing device C1, the whole wing array surface is composed of a plurality of solar wings T, the fixed part of the unfolding guide and constant force tensioning mechanism is arranged at the bottom bearing device C2, and the top bearing device C1 drives the guide rope of the guide mechanism 10 to unfold, so as to guide the solar wings T to unfold in order.
As shown in fig. 2, the guiding mechanism 10 and the constant force tensioning device 20 are installed on the bearing device C2, and when the top bearing device C1 drives the guiding rope to be pulled open in the unfolding process, the guiding rope can produce directional limitation on the unfolding of the solar wing, and there is constant tension on the whole guiding rope under the tensioning action.
Specifically, one end of the guiding mechanism 10 is connected to the top bearing device C1 of the array surface of the solar wing, and the other end is connected to the bottom bearing device C2, so as to provide an unfolding path limiting force to the array surface of the solar wing when the array surface is unfolded, and ensure that the array surface is unfolded in a fixed plane.
The fixed part of the constant force tensioning mechanism 20 is installed at the bearing device C2 at the bottom of the wing surface of the solar wing, and mainly comprises a tensioning rope 201 and a tensioning wheel assembly 202 which are connected, one end of the tensioning rope 201 is connected with the tensioning wheel assembly 202, the other end of the tensioning rope is connected with the wing surface at the bottom of the solar wing array surface, and the tensioning wheel assembly 202 is installed at the bearing device C2 at the bottom to provide constant tensioning force for the tensioning rope 201.
The guide mechanism 10 and the constant force tensioning mechanism 20 may be adjacently disposed as shown in fig. 2.
According to the exemplary embodiment of the present application, as shown in fig. 3, the tension wheel assembly 202 includes a tension wheel 2021, a short spring 2022 and a supporting arm 2023, one end of the tension rope 201 is wound around the tension wheel 2021, one end of the short spring 2022 is wound around the supporting arm 2023, the other end of the short spring 2022 is wound around the tension wheel 2021 and is fixedly connected to the tension wheel 2021, and the wound shape of the short spring 2022, the supporting arm 2023 and the tension wheel 2021 is generally "S" shaped. By the design, when the bottommost sun wing surface at the last stage of deployment is deployed, the tensioning rope 201 is passively pulled open to drive the tensioning wheel 2021 to rotate, and because the tensioning wheel 2021 is connected with the short spring 2022, when the short spring 2022 rotates along with the tensioning wheel 2021, the supporting arm 2023 can cause the short spring 2022 to generate resistance moment, so that the tensioning rope 201 generates a constant tensioning force. When the solar wing is folded, the elastic force on the short spring 2022 is released.
According to an exemplary embodiment of the application, as shown in fig. 4, the short spring 2022 may comprise one or more stacked spring leaves, and may be adjusted according to the required tightening force, or may be provided with more spring leaves if the required force is larger.
According to an exemplary embodiment of the application, the support arm 2023 is a cylinder or roller with a central axis parallel to the axis of the tension wheel 2021. The distance between the supporting arm 2023 and the tensioning wheel 2021 can be adjusted according to the required moment and the size of each structure.
The deformation of the bottom wing surface of the solar wing in the unfolding or working process cannot be too large, if the tensioning mechanism is arranged complicatedly, the tensioning force redundancy can cause the weight of the whole mechanism to be too heavy, so that the tensioning mechanism is arranged for tensioning the wing surface at the bottom of the solar wing, the tensioning function can be achieved, the structure is simple, and the weight is light.
According to an exemplary embodiment of the application, the short spring 2022 is wound on the tension pulley 2021 no more than 1 turn, and the short spring 2022 is wound on the support arm 2023 no more than 1 turn, as shown in fig. 4. One end of the short spring 2022 may be fixed to the tensioning pulley 2021 by a screw 2024, or fixed to the tensioning pulley 2021 by welding, or fixed to the tensioning pulley 2021 by adhesion, and the specific fixing method is not limited to this embodiment. The supporting arm 2023 can make the short spring 2022 store certain strain energy and then produce the resisting moment, and simultaneously the short spring 2022 can superpose different quantity of reeds according to actual production and design state, can produce nearly invariable resisting moment in certain angular dimension.
According to an exemplary embodiment of the present application, as shown in fig. 5, the guide mechanism 10 includes a guide rope 101, a guide rope assembly 102, and a tension storage assembly 103, the tension storage assembly 103 is connected with the guide rope assembly 102 and transmits a tension torque to the guide rope assembly 102, one end of the guide rope 101 is connected with the guide rope assembly 102 to receive the tension force, and the other end of the guide rope 101 is movably connected to the top carrier C1 through the front surface of the sun wing.
According to the exemplary embodiment of the present application, the guide rope pulley assembly 102 includes a guide rope pulley 1021 and a rotation shaft pulley 1022, the guide rope pulley 1021 and the rotation shaft pulley 1022 are coaxially disposed, the guide rope pulley 1021 is used for winding the guide rope 101, both the guide rope pulley 1021 and the rotation shaft pulley 1022 are fixedly connected with the shaft 1023, and the rotation shaft pulley 1022 is used for connecting a tension storage assembly to receive tension.
According to an example embodiment of the present application, the guide sheave 1021 and the rotation shaft sheave 1022 are both keyed to the shaft.
According to an exemplary embodiment of the present application, the tension storage assembly 103 includes a storage wheel 1031 and a constant wrap spring 1032, one end of the constant wrap spring 1032 being fixed and wound around the storage wheel 1031, being previously tensioned on the storage wheel 1031 to store the tension, and the other end being wound around the rotation wheel 1022 and being fixedly connected with the rotation wheel 1022.
Since the total height of the sun's front when deployed and folded is more different, the required range of the deployed length of the guide cord 101 is larger, and therefore a plurality of turns of spring needs to be wound on the storage wheel 1031 to store more energy, so that the guide cord 101 can be rotated on the guide cord wheel 1021 a plurality of turns to release sufficient length or to be tightened.
The constant torque scroll spring 1032 may be a multi-turn coiled spring member.
Above-mentioned design like this, at the expansion in-process for the guiding rope 101 is pulled open passively, and then drives the guiding rope wheel 1021 and rotate, and the pivot wheel 1022 rotates through the realization of being connected between with the guiding rope wheel 1021, because decide the moment scroll spring 1032 and can follow the pivot wheel 1022 and rotate and wind around the pivot wheel 1022, can produce certain resistance moment to the pivot wheel 1022 at the tension of storage wheel 1031 storage, thereby makes the guiding rope 101 produce constant tension.
The guide rope 101 and the tension rope 201 in the present application may be metal or non-metal flexible wires or ropes, such as steel wire ropes, which may be selected according to the needs.
In order to make the whole wing surface stressed evenly, the guiding mechanism and the constant force tensioning mechanism are respectively provided with a plurality of sets, a plurality of sets are arranged at intervals in the transverse direction (X direction shown in figure 1) of the sun wing, and the guiding mechanism and the constant force tensioning mechanism in each set can be arranged adjacently.
According to the exemplary embodiment of the present application, as shown in fig. 1, there are two guiding mechanisms and two constant-force tensioning mechanisms, and each guiding mechanism and each constant-force tensioning mechanism are adjacently disposed near one end of the solar wing at the transverse position. Of course, the specific number and layout can be not limited to this, and can be set according to actual needs.
According to the solar wing unfolding device, the unfolding mechanism can be used for driving the top bearing device C1 to drive the guide rope in the guide mechanism to unfold in the unfolding process of the solar wing, and tension always exists on the guide rope due to the resisting moment of the fixed moment volute spring in the unfolding process, so that the guide effect is generated on the solar wing in the unfolding process; the constant force tensioning mechanism generates a certain resisting moment through the short spring at the last stage of unfolding, and further generates a certain tension through the tensioning rope, and the tension acts on the bottom of the solar wing to enable the whole wing surface to be pulled and flattened and improve the rigidity of the whole wing.
The controllable solar wing unfolding track can be ensured in the unfolding process of the flexible solar wing, and the resistance generated by the guide rope in the unfolding process of the mechanism and relatively unfolded is a constant value; the mechanism can generate constant tension at the last stage of unfolding, and the flexible solar wing is tensioned, so that the rigidity and the flatness of the whole wing surface are improved; in operation, the constant force tensioning mechanism also compensates for airfoil deformation through automatic tracking adjustment of tension.
The scheme that this application provided can realize the guide effect, also can realize the constant force tensioning function simultaneously.
The wing surface tension stabilizing device is simple in structure, safe, reliable and excellent in performance, can effectively achieve the unfolding guiding effect, and can achieve stable wing surface tension under the thermal deformation condition.
Finally, it should be noted that: although the present disclosure has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications may be made to the embodiments described above, or equivalents may be substituted for elements thereof. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present disclosure should be included in the protection scope of the present disclosure.
Claims (10)
1. A sun wing spreading guide and constant force tensioning mechanism, wherein the top and bottom of the entire array of sun wings are provided with a top carrier and a bottom carrier, respectively, the guide and constant force tensioning mechanism comprising:
one end of the guiding mechanism is arranged on the top bearing device of the solar wing array surface, and the other end of the guiding mechanism is arranged on the bottom bearing device, so that the unfolding direction limiting function is provided for the solar wing array surface when the solar wing array surface is unfolded;
the constant-force tensioning mechanism comprises a tensioning rope and a tensioning wheel assembly which are connected, wherein one end of the tensioning rope is connected with the tensioning wheel assembly, the other end of the tensioning rope is connected with the airfoil at the bottom of the solar airfoil surface, and the tensioning wheel assembly is arranged on the bottom bearing device and provides constant tensioning force for the tensioning rope.
2. The solar wing deployment guidance and constant force tensioning mechanism according to claim 1, wherein the tensioning wheel assembly includes a tensioning wheel, a short spring, and a support arm, wherein the one end of the tensioning rope is wound around the tensioning wheel, one end of the short spring is wound around the support arm, the other end of the short spring is wound around the tensioning wheel and is fixedly connected to the tensioning wheel, and the outer shape around which the short spring is wound with the support arm and the tensioning wheel is generally "S" shaped.
3. The solar span opening directing and constant force tensioning mechanism of claim 2 wherein the short spring comprises one or more stacked leaves.
4. The solar span extension guiding and constant force tensioning mechanism of claim 2 wherein the support arm is a cylinder or roller having a central axis parallel to the axis of the tensioning wheel.
5. The solar span opening directing and constant force tensioning mechanism of claim 2 wherein the short spring passes no more than 1 turn around the tensioning wheel.
6. The solar wing deployment guidance and constant force tensioning mechanism of claim 1, wherein the guiding mechanism includes a guiding rope, a guiding sheave assembly, and a tension storage assembly connected to the guiding sheave assembly and transmitting a tensioning torque to the guiding sheave assembly, one end of the guiding rope being connected to the guiding sheave assembly to receive the tensioning force, the other end of the guiding rope being movably connected to the top carrier across the front of the solar wing.
7. The solar wing deployment guidance and constant force tensioning mechanism of claim 6, wherein the guiding sheave assembly comprises a guiding sheave and a rotating shaft wheel, the guiding sheave and the rotating shaft wheel are coaxially disposed, the guiding sheave and the rotating shaft wheel are both fixedly connected to the shaft, and the rotating shaft wheel is used for connecting the tension storage assembly.
8. The solar span opening guide and constant force tensioning mechanism of claim 7 wherein the guide sheave and the rotating shaft sheave are keyed to the shaft, or end-screwed, or square shaft fitted with square hole.
9. The solar spanwise guiding and constant force tensioning mechanism of claim 7, wherein the tension storage assembly includes a storage wheel and a constant force volute spring, one end of the constant force volute spring being fixed to and wound around the storage wheel, storing tension on the storage wheel, and the other end being wound through and fixedly connected to the rotatable shaft wheel.
10. The sun wing spreading guide and constant force tensioning mechanism according to any one of claims 1 to 9 wherein the guide mechanism and the constant force tensioning mechanism are each provided in a plurality of sets, the plurality of sets being spaced apart laterally of the sun wing, the guide mechanism and the constant force tensioning mechanism in each set being located adjacent one another.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221836855.4U CN217805341U (en) | 2022-07-15 | 2022-07-15 | Sun wing spreading guiding and constant force tensioning mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221836855.4U CN217805341U (en) | 2022-07-15 | 2022-07-15 | Sun wing spreading guiding and constant force tensioning mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217805341U true CN217805341U (en) | 2022-11-15 |
Family
ID=83965985
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202221836855.4U Active CN217805341U (en) | 2022-07-15 | 2022-07-15 | Sun wing spreading guiding and constant force tensioning mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217805341U (en) |
-
2022
- 2022-07-15 CN CN202221836855.4U patent/CN217805341U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| JP5503650B2 (en) | Tether processing system and method for flight generator | |
| US8672631B2 (en) | Articulated wind turbine blades | |
| US20140326833A1 (en) | Directionally Controlled Elastically Deployable Roll-Out Array | |
| CN103119729B (en) | For the cable arrangement of the supporting construction of rotating light photovoltaic assembly or similar devices | |
| US9214892B2 (en) | Solar arrays | |
| US8142154B2 (en) | Oscillating energy capture mechanism | |
| US8668455B2 (en) | Turbine wheel | |
| JP6564889B2 (en) | Elastic restraint cable control solar tracking solar generator | |
| JP6165147B2 (en) | Hinge mechanism for deploying and locking solar power generators and reflectors | |
| US20210013830A1 (en) | Articulating Solar Panel Energy Systems, Methods, and Devices | |
| JP5994242B2 (en) | Deployable torque motorization system for space structures | |
| CN102459884A (en) | Rotation blade-type vertical axis wind turbine | |
| KR101503297B1 (en) | Device for applying static dual-axis loads to blade | |
| CN207809816U (en) | Slidingtype mechanism for outspreading sailboard of solar cell | |
| CN217805341U (en) | Sun wing spreading guiding and constant force tensioning mechanism | |
| US8496437B2 (en) | Power transmitting system through cables for airborne wind-type power generation applications | |
| CN104136702B (en) | To be wound up on axle for making material roll and from the device of unwinding axle | |
| JP7411186B2 (en) | Telescopic device | |
| CA2675947C (en) | Oscillating energy capture mechanism | |
| WO2023103473A1 (en) | Method for mounting double-layer linkage closed-loop rope system | |
| JP3231558U (en) | Blades for wind power generators | |
| EP2463516B1 (en) | Aeolian system for converting energy through power wing airfoils | |
| CN110417341A (en) | A kind of single-axis solar tracking bracket | |
| CN214352541U (en) | Mechanical joint structure | |
| CN219009541U (en) | Antiwind mechanism and coiling mechanism |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |