CN114348300A - Automatic retractable sun wing unfolding device - Google Patents
Automatic retractable sun wing unfolding device Download PDFInfo
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- CN114348300A CN114348300A CN202210025205.XA CN202210025205A CN114348300A CN 114348300 A CN114348300 A CN 114348300A CN 202210025205 A CN202210025205 A CN 202210025205A CN 114348300 A CN114348300 A CN 114348300A
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- 239000003638 chemical reducing agent Substances 0.000 claims abstract description 17
- 238000004880 explosion Methods 0.000 claims abstract description 10
- 239000002131 composite material Substances 0.000 claims description 7
- 238000000034 method Methods 0.000 claims description 7
- 238000007789 sealing Methods 0.000 claims description 6
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 4
- 239000004917 carbon fiber Substances 0.000 claims description 4
- 238000004804 winding Methods 0.000 claims description 4
- 239000004677 Nylon Substances 0.000 claims description 3
- 239000003822 epoxy resin Substances 0.000 claims description 3
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- 229920000647 polyepoxide Polymers 0.000 claims description 3
- 239000007787 solid Substances 0.000 claims description 3
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- 239000007789 gas Substances 0.000 description 41
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- 239000001307 helium Substances 0.000 description 3
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- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 description 3
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- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 1
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
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- 230000003245 working effect Effects 0.000 description 1
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Abstract
The invention discloses an automatic retractable solar wing spreading device, which is characterized in that a high-pressure gas cylinder, a gas circuit electric explosion valve, a pressure reducer, an electromagnetic valve, an inflation spreading device and a cold air nozzle are sequentially communicated, the inflation valve is used for inflating the high-pressure gas cylinder, the inflation spreading device comprises an annular electromagnet, an inflation strut, a spreading lower plate, a flexible solar panel, a solar panel bracket, a spring system bracket, a self-elevating spring system and an inflation spreading device pipeline, the inflation spreading device pipeline is communicated with the inflation strut through the solar panel bracket, the other end of the inflation strut is fixed with two ends of the spreading lower plate, one end of the flexible solar panel is fixed with the spreading lower plate, the other end of the flexible solar panel is connected into the spring system bracket, and the annular electromagnet is fixed at the support position of the solar panel bracket The satellite launching cost can be greatly reduced, and the satellite launching device is small in storage volume, light in weight and high in reliability.
Description
Technical Field
The invention relates to the technical field of satellite solar panels, in particular to an automatic retractable solar wing unfolding device.
Background
With the continuous development of the aerospace industry, the structure of the spacecraft is more and more complex, and the quality of the spacecraft is more and more large. Conventional spacecraft structures have experienced significant difficulties in development and launch due to limitations in the available space and mass of the vehicle. Therefore, how to sufficiently improve the efficiency of the spacecraft under the condition of limited carrying capacity is an important development direction of the development work of the spacecraft. The existing satellite solar panel is unfolded generally by memory metal, and when the use temperature reaches a certain temperature, the solar panel can be automatically unfolded according to the originally set shape. Or an initiating mechanism is adopted, the solar sailboard is folded before being launched, compressed by a spring and locked by the initiating mechanism. When the sailboard is unfolded, the initiating explosive mechanism obtains an instruction, the explosive bolt is detonated, the locking mechanism is exploded, and the sailboard is unfolded under the action of the spring force. This process seems simple but is a very important step for the satellite to enter into a true working state. All countries have failure cases, and a good satellite becomes a garbage satellite because the solar sailboard cannot be opened. With the increasingly severe environment of space satellites, future satellites should also be recyclable and maneuverable to change orbit. For the satellite with the solar panel which cannot be recovered, the size is large, and the mode of discarding the solar panel to recover the effective load can be adopted. In order to solve the problem of satellite orbit emergency, the solar panel is required to be withdrawn when the orbit is changed by a motor, and the consumed propellant amount is also reduced when the orbit is changed. After all today, where rail refuelling is not possible, the amount of propellant carried is also limited.
The energy sources used by the existing in-orbit spacecraft mainly comprise solar energy, high-pressure gas stored in a pressure container during emission and the like. At present, most of the satellites in all countries in the world use solar energy as a main energy source. In order to be able to work during the launch phase and during the terrestrial shadow (the satellite will have a period of time during its orbit that does not receive sunlight), it is equipped with lithium batteries, called secondary energy. The main payload on the satellite, in particular the transponder part, will consume at least more than 60% of the energy. This requires solar panels to convert solar energy into electrical energy for use and storage. In order to be able to place the satellite in the fairing during the satellite launch and entry phase, the solar panels must not be deployed. So after the satellite and sword are separated, the satellite can be maintained to normally work by virtue of the battery charged on the ground, and the effective load does not work in the period of time. The capacity of the battery is limited and in order for the satellite to actually start working, the solar panel must be deployed as soon as possible to allow the satellite to have autonomous energy supply capability, after which the payload is activated gradually.
At present, the rocket launching cost of the domestic rocket needs about 5-10 million yuan of renminbi, the weight of the flexible solar wing with the same area is reduced by more than 20% compared with that of the rigid solar wing, along with the further development of the technology, the weight of the flexible solar wing with the same area can be reduced by more than 40% even compared with that of the rigid solar wing, and the satellite launching cost can be greatly reduced. The inflatable expansion structure has the advantages of low cost, small storage volume, light weight, high reliability and the like, and can realize the performance which is difficult to achieve by the traditional structure. Therefore, the application of the inflatable expansion structure to various types of spacecrafts becomes a hotspot for space research and development. At present, most of satellites adopt solar panels which are unfolded by utilizing the material characteristics of the solar panels, and the solar panels cannot be opened and closed for the maneuvering orbital transfer and the subsequent satellite recovery.
Disclosure of Invention
Aiming at the defects of the prior art, the invention provides an automatic retractable solar wing unfolding device.
The invention adopts the technical scheme that an automatic retractable solar wing unfolding device comprises a high-pressure gas cylinder, a gas circuit electric explosion valve, a pressure reducer, an electromagnetic valve, an inflation unfolding device and a cold air nozzle which are sequentially communicated, wherein the inflation valve is used for inflating the high-pressure gas cylinder, the inflation unfolding device comprises an annular electromagnet, an inflation strut, an unfolding lower plate, a flexible solar panel, a solar panel bracket, a spring system bracket, a self-lifting spring system and an inflation unfolding device pipeline, the inflation unfolding device pipeline is communicated with the inflation strut through the solar panel bracket, the other end of the inflation strut is fixed with two ends of the unfolding lower plate, one end of the flexible solar panel is fixed with the unfolding lower plate, the other end of the flexible solar panel is connected into the spring system bracket, when in inflation, the inflation strut pulls the flexible solar panel to unfold, the annular electromagnet is fixed at the position of the support of the solar panel support, the annular electromagnet adsorbs the support of the unfolding lower plate after being electrified, the inflatable support is compressed and stored between the solar panel support and the shell of the unfolding lower plate in an uninflated state, the spring system support and the self-lifting spring system are used for adjusting the solar panel to relax and stop at any position, and the flexible solar panel is retracted in the spring system support in an unoperated state of the pipeline of the inflatable unfolding device.
Preferably, the front end of the pressure reducer is provided with a filter, and the back of the pressure reducer is provided with a back pressure sensor of the pressure reducer.
Preferably, the inflatable pillar is made of 40D nylon TPU.
Preferably, the pipeline of the inflation unfolding device comprises an air path plunger, a plunger nut and a sealing rubber ring, wherein the air path plunger is inserted into a threaded hole of the solar panel support and then is screwed into the inner thread of the solar panel support through the plunger nut for fixed connection.
Preferably, aerify the pillar including aerifing the pillar body, aerifing the pillar air cock and aerifing the pillar end cap, aerify the pillar air cock and pass through threaded connection with the solar panel support, aerify the pillar end cap and be solid construction.
Preferably, the inflation valve is arranged at the air source inlet end of the high-pressure air bottle, and the rear end of the high-pressure air bottle is provided with an inflation valve pressure sensor.
Preferably, the high-pressure gas cylinder comprises a lining and a composite layer, the lining is made of an industrial metal material, and the composite layer is formed by winding high-strength carbon fibers and epoxy resin by a wet method and then curing.
The invention has the beneficial effects that: the invention relates to a flexible unfolding device which unfolds a solar panel by using supply air and retracts the solar panel by carrying out secondary air supply. Different from the traditional solar panel, the solar panel has cyclic expansion, and is convenient for satellite recovery and maneuvering orbit transfer. The automatic retractable solar wing unfolding device has the advantages of low cost, capability of greatly reducing satellite launching cost, small storage volume, light weight, high reliability and the like, and can realize the performance which is difficult to achieve by a traditional structure.
Drawings
Fig. 1 is a schematic diagram of an air supply system of an automatic retractable solar wing unfolding apparatus according to the present invention.
Fig. 2 is a structural view of an inflatable unfolding device of an automatic retractable solar wing unfolding device according to the present invention.
FIG. 3 is a piping structure diagram of the inflator according to the present invention.
Fig. 4 is a schematic view of the fixing method of the flexible solar panel and the unfolding lower plate according to the present invention.
FIG. 5 is a view showing the construction of the inflatable strut according to the present invention.
In the figure: 1-a high-pressure gas cylinder, 2-an inflation valve pressure sensor, 3-an inflation valve, 4-a gas path electric explosion valve, 5-a pressure reducer, 6-a pressure reducer rear pressure sensor, 7-an electromagnetic valve, 8-a cold air nozzle, 9-an inflation unfolding device, 10-a filter, 11-a ring electromagnet, 12-an inflation support, 13-an unfolding lower plate, 14-a flexible solar panel, 15-a solar panel support, 16-a spring system support, 17-a self-lifting spring system, 18-an inflation unfolding device pipeline, 18.1-a gas path plunger, 18.2-a plunger nut, 18.3 sealing rubber ring, 12.1-an inflation support body, 12.2-an inflation support air tap and 12.3-an inflation support.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. The components of embodiments of the present invention generally described and illustrated in the figures herein can be arranged and designed in a wide variety of different configurations.
As shown in fig. 2 to 4, a structure of an automatic retractable sun wing unfolding device includes a high-pressure gas cylinder 1, an inflation valve pressure sensor 2, an inflation valve 3, a gas circuit electric explosion valve 4, a pressure reducer 5, a pressure reducer rear pressure sensor 6, an electromagnetic valve 7, a cold air nozzle 8, an inflation unfolding device 9, and a filter 10; the high-pressure gas cylinder 1 is formed by winding an industrial metal lining and carbon fibers. When the gas circuit electric explosion valve works, the gas circuit electric explosion valve 4 is electrified and opened, and gas is discharged through the gas circuit electric explosion valve 4. The high-pressure gas cylinder 1 is composed of a lining and a composite layer, wherein the lining is made of titanium materials and is mainly used for containing and sealing working gas (helium is selected in the system) so as to prevent the working gas from leaking, and a core mold is provided for winding the composite material. The composite layer is formed by curing high-strength carbon fibers and epoxy resin after being wound by a wet method and is mainly used for bearing the internal pressure load generated by gas stored in the gas cylinder. As a gas source for storing high pressure helium; the high-pressure gas cylinder 1 is connected with a four-way pipeline, and the inflation valve 3 is mainly used for inflating the high-pressure gas cylinder 1, so that the gas cylinder has the function of repeated inflation and deflation. The charging valve pressure sensor 2 is a high pressure sensor for detecting the pressure of the high pressure gas source in the high pressure gas cylinder 1. The pressure reducer 5 is used for reducing the pressure of the high-pressure air source to a specified pressure so as to provide a proper pressure for the system. The filter 10 is arranged in front of the pressure reducer 5 to prevent metal fragments generated after the gas circuit electric explosion valve 4 is electrically exploded from entering the pressure reducer 5. The post-decompressor pressure sensor 6 is used to detect the pressure of the gas delivered to the system piping. After the electromagnetic valve 7 is opened, the decompressed gas is filled into the inflation development device 9.
The structure of the inflation unfolding device 9 comprises an annular electromagnet 11, an inflation support 12, an unfolding lower plate 13, a flexible solar panel 14, a solar panel support 15, a spring system support 16, a self-lifting spring system 17 and an inflation unfolding device pipeline 18; the annular electromagnet 11 is fixed at the support position of the solar panel support 15, and absorbs and unfolds the support of the lower plate 13 after being electrified. When the flexible solar panel 14 is not in operation, the flexible solar panel 14 is used for fixing the solar panel, and after the system electromagnetic valve is started, the annular electromagnet 11 is closed, so that the flexible solar panel 14 can be smoothly unfolded after inflation. The inflatable struts 12 are 40D nylon TPU material and are stored in an uninflated state compressed between the solar panel support 15 and the housing of the lower panel 13. The solar panel support 15 has a mounting hole site and can be mounted outside the satellite. The spring system support 16 and the damping device in the self-lifting spring system 17 enable the speed of the flexible solar panel 14 to be kept slow and uniform in the process of retraction and extension, and the speed-adjustable device enables the spring to be automatically stopped when retracted to a set position, so that the flexible solar panel is guaranteed to be stopped on a straight line which is orderly drawn. The solar panel is adjusted to relax within a certain range, and the solar panel can be parked at any position. The flexible solar panel 14 is housed in the spring system support 16 when the inflatable deployment device tubing 18 is not in operation, and the ring electromagnet 11 is de-energized when operation is required. The solenoid valve is opened. The air source enters the pipeline 18 of the inflatable unfolding device and is respectively inflated into the inflatable unfolding device 9, and the inflatable struts 12 are pushed to pull the flexible solar panels 14 to unfold in the unfolding process of the inflatable unfolding devices 9 on the two sides. The pipeline 18 of the inflation unfolding device consists of an air path plunger 18.1, a plunger nut 18.2 and a sealing rubber ring 18.3. The air channel plunger 18.1 is inserted into a threaded hole of the solar panel support 15 and then screwed into the inner thread of the solar panel support 15 through the plunger nut 18.2 to be fixedly connected. The sealing rubber ring 18.3 is used for ensuring the air path tightness. The inflatable support 12 comprises an inflatable support body 12.1, an inflatable support air nozzle 12.2 and an inflatable support plug 12.3, the inflatable support air nozzle 12.2 is in threaded connection with the solar panel support 15, and the inflatable support plug 12.3 is of a solid structure.
The specific operation is as follows: as shown in figure 1, the gas supply system is connected with each unit according to a principle diagram, helium is pressurized through an inflation valve 3 and then is filled into a high-pressure gas cylinder 1, and the gas pressure in the high-pressure gas cylinder 1 can be known through an inflation valve pressure sensor 2. When 35Mpa is reached, the inflation is stopped and the inflation valve 3 is locked. The gas supply system enters a preset orbit along with the satellite in the sky, and the solar panel needs to be unfolded to provide energy for the satellite. At the moment, a detonation instruction is given to the gas circuit electric explosion valve 4, a gas source after detonation flows through the filter 10 and enters the pressure reducer 5 to be decompressed to become 2Mpa gas used by the system, and the pressure sensor 6 behind the pressure reducer records the pressure value in a low-pressure pipeline of the system. And opening the electromagnetic valve 7 to convey the air source to the inflation unfolding device 9, and closing the power supply of the annular electromagnet to release the locking state. Gas enters the inflatable struts 12 through the inflatable deployment device tubes 18. The inflatable pillar 12 pushes the unfolding lower plate 13 to drive the solar panel to be gradually unfolded, and the electromagnetic valve 7 is closed after the solar panel is unfolded. And simultaneously, the sensor detects the pressure of the gas cylinder in the high-pressure gas cylinder 1. When the flexible solar panel 14 needs to be folded, the cold air nozzle 8 is opened, high-pressure gas is automatically discharged to low pressure due to the fact that the space is in a vacuum environment, the flexible solar panel 14 can be rewound and folded under the working action of the self-lifting/self-descending spring system 17, and the cold air nozzle 8 is closed.
The foregoing shows and describes the general principles and broad features of the present invention and advantages thereof. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, which are described in the specification and illustrated only to illustrate the principle of the present invention, but that various changes and modifications may be made therein without departing from the spirit and scope of the present invention, which fall within the scope of the invention as claimed. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (7)
1. An automatic retractable solar wing unfolding device is characterized in that: the high-pressure gas cylinder, the gas circuit electric explosion valve, the pressure reducer, the electromagnetic valve, the inflation unfolding device and the cold air nozzle are sequentially communicated, the inflation valve is used for inflating the high-pressure gas cylinder, the inflation unfolding device comprises an annular electromagnet, an inflation support, an unfolding lower plate, a flexible solar panel, a solar panel support, a spring system support, a self-lifting spring system and an inflation unfolding device pipeline, the inflation unfolding device pipeline is communicated with the inflation support through the solar panel support, the other end of the inflation support is fixed with the two ends of the unfolding lower plate, one end of the flexible solar panel is fixed with the unfolding lower plate, the other end of the flexible solar panel is connected into the spring system support, the inflation support pulls the flexible solar panel to unfold during inflation, the annular electromagnet is fixed at the position of the support of the solar panel support, and adsorbs the support of the unfolding lower plate after being electrified, the inflatable support is compressed and stored between the solar panel support and the shell of the unfolding lower plate in an uninflated state, the spring system support and the self-lifting spring system are used for adjusting the solar panel to relax and stop at any position, and the flexible solar panel is retracted in the spring system support in an unoperated state of the pipeline of the inflatable unfolding device.
2. An automatic retractable solar wing opening device according to claim 1, characterized in that: the front end of the pressure reducer is provided with a filter, and a pressure sensor behind the pressure reducer is arranged.
3. An automatic retractable solar wing opening device according to claim 1, characterized in that: the inflatable support column is made of 40D nylon TPU.
4. An automatic retractable solar wing opening device according to claim 1, characterized in that: the pipeline of the inflating and unfolding device comprises an air path plunger, a plunger nut and a sealing rubber ring, wherein the air path plunger is inserted into a threaded hole of the solar panel support and is fixedly connected with an inner thread of the solar panel support through the plunger nut screwed in.
5. An automatic retractable solar wing opening device according to claim 1, characterized in that: the inflatable support column comprises an inflatable support column body, an inflatable support column air tap and an inflatable support column plug, wherein the inflatable support column air tap is connected with the solar panel support through threads, and the inflatable support column plug is of a solid structure.
6. An automatic retractable solar wing opening device according to claim 1, characterized in that: the inflation valve is arranged at the air source inlet end of the high-pressure air bottle, and the rear end of the high-pressure air bottle is provided with an inflation valve pressure sensor.
7. An automatic retractable solar wing opening device according to claim 1, characterized in that: the high-pressure gas cylinder comprises a lining and a composite layer, wherein the lining is made of industrial metal materials, and the composite layer is formed by winding high-strength carbon fibers and epoxy resin by a wet method and then curing.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210025205.XA CN114348300A (en) | 2022-01-11 | 2022-01-11 | Automatic retractable sun wing unfolding device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210025205.XA CN114348300A (en) | 2022-01-11 | 2022-01-11 | Automatic retractable sun wing unfolding device |
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| CN114348300A true CN114348300A (en) | 2022-04-15 |
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| CN202210025205.XA Pending CN114348300A (en) | 2022-01-11 | 2022-01-11 | Automatic retractable sun wing unfolding device |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117329027A (en) * | 2023-11-28 | 2024-01-02 | 成都志力科技发展有限责任公司 | Telescopic tail nozzle |
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| CN117329027B (en) * | 2023-11-28 | 2024-01-26 | 成都志力科技发展有限责任公司 | Telescopic tail nozzle |
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