CN111756435A - Power and signal transmission system - Google Patents
Power and signal transmission system Download PDFInfo
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- CN111756435A CN111756435A CN202010646167.0A CN202010646167A CN111756435A CN 111756435 A CN111756435 A CN 111756435A CN 202010646167 A CN202010646167 A CN 202010646167A CN 111756435 A CN111756435 A CN 111756435A
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- 230000008054 signal transmission Effects 0.000 title claims abstract description 29
- 238000006243 chemical reaction Methods 0.000 claims abstract description 106
- 230000003287 optical effect Effects 0.000 claims abstract description 52
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- 239000013307 optical fiber Substances 0.000 claims description 12
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- 230000005693 optoelectronics Effects 0.000 claims description 2
- 238000005516 engineering process Methods 0.000 abstract description 15
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- 238000010586 diagram Methods 0.000 description 5
- 230000005684 electric field Effects 0.000 description 4
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- 238000005299 abrasion Methods 0.000 description 3
- 239000003990 capacitor Substances 0.000 description 3
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- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 2
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- 238000003199 nucleic acid amplification method Methods 0.000 description 2
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Classifications
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B7/00—Radio transmission systems, i.e. using radiation field
- H04B7/14—Relay systems
- H04B7/15—Active relay systems
- H04B7/185—Space-based or airborne stations; Stations for satellite systems
- H04B7/1851—Systems using a satellite or space-based relay
- H04B7/18515—Transmission equipment in satellites or space-based relays
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J50/00—Circuit arrangements or systems for wireless supply or distribution of electric power
- H02J50/10—Circuit arrangements or systems for wireless supply or distribution of electric power using inductive coupling
- H02J50/12—Circuit arrangements or systems for wireless supply or distribution of electric power using inductive coupling of the resonant type
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J50/00—Circuit arrangements or systems for wireless supply or distribution of electric power
- H02J50/20—Circuit arrangements or systems for wireless supply or distribution of electric power using microwaves or radio frequency waves
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J50/00—Circuit arrangements or systems for wireless supply or distribution of electric power
- H02J50/30—Circuit arrangements or systems for wireless supply or distribution of electric power using light, e.g. lasers
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B10/00—Transmission systems employing electromagnetic waves other than radio-waves, e.g. infrared, visible or ultraviolet light, or employing corpuscular radiation, e.g. quantum communication
- H04B10/40—Transceivers
Abstract
The invention discloses a power and signal transmission system, which is used for transmitting power and signals between a satellite rotating part and a satellite body. The signal transmission subsystem comprises a rotating part photoelectric conversion subsystem arranged on the satellite rotating part, a satellite body photoelectric conversion subsystem arranged on the satellite body and an optical slip ring, and the power transmission subsystem adopts a radio transmission technology to transmit a primary power supply of the satellite body to the satellite rotating part.
Description
Technical Field
The invention relates to the technical field of aerospace, in particular to a power and signal transmission system.
Background
With the rapid development of the internet of things and the mobile internet technology, the low-orbit satellite constellation is coming to a brand new development climax. Various types of satellites are increasingly demanded, wherein some satellites are provided with rotating parts, such as satellite solar cell array SADA driving mechanisms, satellite-borne scanning antennas, space moving target optical monitoring systems, new-system electronic detection systems, space manipulators and the like, and therefore, the demands of the rotating mechanisms are also increasingly widespread.
The conductive slip ring is a key component for power and signal transmission between a traditional satellite rotating component and a satellite body, and is mainly used for energy supply of the satellite rotating component and signal transmission between the rotating component and the satellite body. Therefore, the reliability and lifetime of the conductive slip ring often determine the reliability and lifetime of the satellite. The conventional conductive slip ring is a contact type mechanical rotating structure, as shown in fig. 1, and mainly comprises a shaft assembly 101, a brush holder assembly 102, a housing 103, an outer cover 104, and a bearing 105, and the slip ring forms signal transmission channels of loops by performing mechanical friction on corresponding loops such as a signal loop, a power loop, a ground loop, and the like on the shaft assembly 101 through brush wires or brush wire bundles on the brush holder assembly 102.
At present, the application of the space conductive slip ring abroad reaches the level of tens of millions of revolutions, the application life of the space conductive slip ring in China also reaches the level of millions, but the satellite with high requirements on the rotating speed and the number of revolutions is obviously insufficient, and in the in-orbit running period of the satellite, along with the increase of the load of a rotating part, the abrasion speed of a slip ring coating is firstly reduced and then increased, the generated abrasion chips can reduce the insulation performance of the slip ring to cause vacuum discharge, the reliability of electric contact is continuously reduced at the end of the service life, so that the energy of the whole satellite is reduced, and the service life of the satellite is influenced.
Disclosure of Invention
To solve some or all of the problems in the prior art, the present invention provides a power and signal transmission system for transmitting energy and signals between a satellite rotating component and a satellite body, comprising:
a signal transmission subsystem comprising:
an electro-optical conversion transmitting module respectively arranged on the satellite rotating part and the satellite
The body is used for modulating signals to be transmitted to optical signals with different wavelengths;
a photoelectric conversion receiving module respectively arranged on the satellite rotation part and the satellite
The body is used for receiving optical signals and restoring the optical signals into corresponding signals; to be provided with
And
an optical slip ring connected with the satellite rotating part and the satellite body through optical fibers respectively for
Transmitting an optical signal; and
and the power transmission subsystem adopts a radio transmission technology to transmit the primary power supply of the satellite body to the satellite rotating part.
Furthermore, the electro-optical conversion emission module comprises a radio frequency light conversion emission module, a digital light conversion emission module, an RS422 light conversion emission module, an RS485 light conversion emission module and a CAN light conversion emission module.
Further, the radio frequency light conversion transmitting module comprises a preposed low noise amplifier, an electro-optical converter and an automatic power and temperature controller.
Further, the photoelectric conversion receiving module comprises a radio frequency light conversion receiving module, a digital light conversion receiving module, an RS422 light conversion receiving module, an RS485 light conversion receiving module, and a CAN light conversion receiving module.
Further, the rf-to-ir receiving module includes an optical path adaptor, an optoelectronic converter, an optical power detection and bias controller, and a post-amplifier.
Furthermore, the signal transmission subsystem further comprises a calibration light path transmitting module arranged on the satellite body and a calibration light path receiving module arranged on the satellite rotating component.
Furthermore, the signal transmission subsystem further comprises a wavelength division multiplexing module respectively arranged between the optical fiber and the satellite rotating part and between the optical fiber and the satellite body.
The invention provides a power and signal transmission system, which is used for transmitting energy and signals between a satellite rotating part and a satellite body. The non-contact transmission method replaces the traditional contact type mechanical conductive slip ring transmission, so that the power and the signal transmission time between the satellite rotating part and the body can be effectively prolonged, and the service life of the satellite with the rotating part is further prolonged.
Drawings
To further clarify the above and other advantages and features of embodiments of the present invention, a more particular description of embodiments of the present invention will be rendered by reference to the appended drawings. It is appreciated that these drawings depict only typical embodiments of the invention and are therefore not to be considered limiting of its scope. In the drawings, the same or corresponding parts will be denoted by the same or similar reference numerals for clarity.
FIG. 1 shows a schematic diagram of a prior art conductive slip ring;
fig. 2 is a schematic diagram of a power and signal transmission system according to an embodiment of the present invention;
FIG. 3 is a signal interaction diagram of a power and signal transmission system according to an embodiment of the present invention; and
fig. 4 is a schematic diagram illustrating the principle of rf signal to optical signal transmission according to an embodiment of the present invention.
Detailed Description
In the following description, the present invention is described with reference to examples. One skilled in the relevant art will recognize, however, that the embodiments may be practiced without one or more of the specific details, or with other alternative and/or additional methods, materials, or components. In other instances, well-known structures, materials, or operations are not shown or described in detail to avoid obscuring aspects of the invention. Similarly, for purposes of explanation, specific numbers, materials and configurations are set forth in order to provide a thorough understanding of the embodiments of the invention. However, the invention is not limited to these specific details. Further, it should be understood that the embodiments shown in the figures are illustrative representations and are not necessarily drawn to scale.
Reference in the specification to "one embodiment" or "the embodiment" means that a particular feature, structure, or characteristic described in connection with the embodiment is included in at least one embodiment of the invention. The appearances of the phrase "in one embodiment" in various places in the specification are not necessarily all referring to the same embodiment.
It should be noted that the embodiment of the present invention describes the process steps in a specific order, however, this is only for the purpose of illustrating the specific embodiment, and does not limit the sequence of the steps. Rather, in various embodiments of the present invention, the order of the steps may be adjusted according to process adjustments.
Aiming at the problem that the service life of satellite energy and signal transmission is limited due to mechanical abrasion of the traditional conductive slip ring, the invention provides a power and signal transmission system which adopts a non-contact mode to transmit power and signals. The solution of the invention is further described below with reference to the accompanying drawings of embodiments.
Fig. 2 is a schematic diagram of a power and signal transmission system according to an embodiment of the present invention. As shown in fig. 2, a power and signal transmission system for transmitting energy and signals between a satellite rotating component and a satellite body includes a signal transmission subsystem and a power transmission subsystem.
The signal transmission subsystem is used for signal transmission, wherein the signals comprise radio frequency signals, digital signals, CAN bus signals of interaction between a satellite computer and a rotating component, RS422 signals and the like, and the signal transmission subsystem comprises:
the rotating component photoelectric conversion subsystem 201 is arranged on a satellite rotating component, and comprises a radio frequency photoelectric conversion module 011, a digital photoelectric conversion module 012, an RS422 photoelectric conversion module 013, an RS485 photoelectric conversion module 014, a CAN photoelectric conversion module 015, and the like, wherein each photoelectric conversion module comprises an electro-optical conversion transmitting module and a photoelectric conversion receiving module, in an embodiment of the present invention, as shown in fig. 3, the rotating component photoelectric conversion 201 comprises a radio frequency light conversion transmitting module 211, a digital light conversion transmitting module 212, an RS422 light conversion transmitting module 213, an RS485 light conversion transmitting module 214, a CAN light conversion transmitting module 215, a radio frequency light conversion receiving module 216, a digital light conversion receiving module 217, an RS422 light conversion receiving module 218, an RS light conversion receiving module 219, a CAN light conversion receiving module 2110, wherein the radio frequency light conversion transmitting module 211, the digital light conversion transmitting module 212, the rf light conversion receiving module 485, the CAN light conversion receiving module 2110, The RS422 light conversion transmitting module 213, the RS485 light conversion transmitting module 214, and the CAN light conversion transmitting module 215 modulate a radio frequency signal, a digital signal, and an RS422 signal, an RS485 signal, and a CAN bus signal of the interaction between the house computer and the rotating component, respectively, onto optical signals of different wavelengths, and transmit the optical signals to the satellite body, and the radio frequency light conversion receiving module 216, the digital light conversion receiving module 217, the RS422 light conversion receiving module 218, the RS485 light conversion receiving module 219, and the CAN light conversion receiving module 2110 receive the optical signals transmitted from the satellite body, respectively, and restore the optical signals to corresponding signals. In order to transmit optical signals through optical fibers, in an embodiment of the present invention, the optical-to-electrical conversion 201 of the rotating component further includes a wavelength division multiplexing module 2112. In addition, in still another embodiment of the present invention, the rotating member photoelectric conversion 201 further includes a calibration optical path receiving module 2111;
the satellite body photoelectric conversion subsystem 202 is disposed on a satellite body, and includes a radio frequency photoelectric conversion module 021, a digital photoelectric conversion module 022, an RS422 photoelectric conversion module 023, an RS485 photoelectric conversion module 024, a CAN photoelectric conversion module 025, and the like, wherein each photoelectric conversion module includes an photoelectric conversion transmitting module and a photoelectric conversion receiving module, in an embodiment of the present invention, as shown in fig. 3, the satellite body photoelectric conversion 202 includes a radio frequency light conversion transmitting module 221, a digital light conversion transmitting module 222, an RS422 light conversion transmitting module 223, an RS485 light conversion transmitting module 224, a CAN light conversion transmitting module 225, a radio frequency light conversion receiving module 226, a digital light conversion receiving module 227, an RS422 light conversion receiving module 228, an RS485 light conversion receiving module 229, and a CAN light conversion receiving module 2210, wherein the radio frequency light conversion transmitting module 221, the digital light conversion transmitting module 222, the RS422 light conversion transmitting module 223, the CAN light conversion receiving module 2210, the rf light conversion transmitting module 221, the digital light conversion transmitting module, The RS485 light conversion transmitting module 224 and the CAN light conversion transmitting module 225 respectively modulate a radio frequency signal, a digital signal, and an RS422 signal, an RS485 signal, and a CAN bus signal of a house computer interacting with a rotating component onto optical signals of different wavelengths, and transmit the optical signals to a satellite rotating component, and the radio frequency light conversion receiving module 226, the digital light conversion receiving module 227, the RS422 light conversion receiving module 228, the RS485 light conversion receiving module 229, and the CAN light conversion receiving module 2210 respectively receive the optical signals transmitted from the satellite rotating component, and restore the optical signals to corresponding signals. To transmit optical signals through optical fibers, in one embodiment of the invention, the satellite body photoelectric conversion 202 further comprises a wavelength division multiplexing module 2212. In addition, in another embodiment of the present invention, the satellite body photoelectric conversion 202 further includes a calibration optical path transmitting module 2211; and
the optical slip ring 203 is respectively connected with the satellite rotating part and the satellite body through optical fibers and is used for transmitting optical signals; the electric/optical-optical/electric conversion is a technical key link of a satellite rotating part adopting an optical slip ring rotating technology, and the performance of photoelectric conversion directly influences key indexes of a system such as bandwidth, noise, phase and the like. Because the pure optical link has high noise, it needs to make noise optimization design on the optical-electrical link, therefore, in an embodiment of the present invention, as shown in fig. 4, the RF-to-optical transmitting module includes a pre-lna 411, an electro-optical converter 412 and an automatic power and temperature controller 413, the RF signal enters the inside of the device through the RF interface on the panel of the optical transmitter, is converted into a microwave optical signal output after impedance matching, low noise amplification and electro-optical/optical conversion, and is transmitted to the optical receiving end through the optical fiber and the smooth ring, the RF-to-optical receiving module includes an optical path adapter 421, an electro-optical converter 422, an optical power detection and bias controller 423 and a post-amplifier 424, the microwave optical signal transmitted to the optical receiving end through the optical fiber and the smooth ring enters the inside of the optical receiver through the optical adapter, and is transmitted through the optical path adapter, the optical path adaptation, the optical/electrical, And outputting the required microwave signal after post amplification.
The Power transmission subsystem transmits a primary Power supply of the satellite body to the satellite rotating part by adopting a Wireless Power Transfer (WPT) technology. The wireless power transmission technology includes microwave wireless power transmission, laser wireless power transmission and the like, and the ground common wireless power transmission technology mainly includes three types: electric field coupling, magnetic field coupling, and electromagnetic radiation:
the electric field coupling type WPT technology is used for realizing wireless transmission of electric energy through an interactive electric field generated between polar plates at a certain distance, belongs to a near field WPT technology, and improves the voltage on a coupling capacitor through compensating the resonance of a network inductor and the coupling capacitor, so that the interactive electric field intensity between the polar plates is enhanced, a larger displacement current is formed on a smaller coupling capacitor, and the wireless transmission of the electric energy between the polar plates is realized. The receiving and transmitting coil needs to be accurately aligned and the two polar plates need to be relatively static, so the method is not suitable for being used on a satellite rotating mechanism;
the magnetic field coupling type WPT technology is a near field WPT technology which takes a high-frequency alternating magnetic field as a carrier and transmits higher power at a medium-short distance with higher efficiency, and when the mutual inductance between coils is larger, the quality factor of the coils is higher, and the transmission efficiency of a system is higher. The electromagnetic induction type WPT technology realizes wireless transmission of electric energy by utilizing magnetic field coupling between a primary side and a secondary side of a loose coupling transformer. When the distance between two satellite compartments is short (in the range of tens of centimeters to tens of centimeters), the wireless energy transmission rate can reach about 90 percent, but the method has higher requirements on the space position relation between the primary side and the secondary side of the coupling transformer, and if a dislocation phenomenon exists, the efficiency is rapidly reduced. If the method is used for energy transmission between two satellite cabins, the coupling primary coil and the coupling secondary coil are required to be fixed at rotating shafts of the two cabins, certain constraint limitation is imposed on the structure and installation of the coils, and the coupling coil and the installation position thereof are solved, so that the method can be applied to wireless energy supply of the satellite rotating cabin with the power consumption of hundreds of watts; and
the electromagnetic Microwave WPT (MPT) technology is a technology that can realize high-Power, relatively long-distance wireless Power transmission by using microwaves, i.e., electromagnetic waves having a frequency of 300MHz to 300GHz, as a carrier of electric Power. In one embodiment of the invention, electromagnetic microwave WPT technology is chosen for wireless energy transfer, as shown in fig. 2: the microwave power source 241 firstly converts the primary power source of the satellite into microwave energy, and the microwave energy is directionally transmitted to a far end by the transmitting antenna 242; the microwave energy is then transmitted through a free space at a distance, captured by a rectifying antenna 243 on the satellite rotating component, and converted into direct current electric energy by a rectifying circuit 244 to be supplied to each single machine of the satellite rotating component as input of a primary power supply, wherein the primary power supply of the satellite is electric energy of a satellite sailboard and a lithium battery.
The schemes in the embodiments of the present invention all use non-contact schemes, and specifically, the process of performing information interaction between a satellite body and a rotating component by using the schemes in the embodiments of the present invention is as follows:
firstly, signals for transmitting information comprise digital signals, radio frequency signals, CAN bus signals of a star computer and rotating parts, RS422 signals and the like, and the signals are interacted through an optical slip ring: each signal to be interacted needs to be modulated to different wavelengths lambda through corresponding electro-optical conversion transmitting modules1～λm+nThen all these wavelengths are lambda1～λm+nThe optical signals are connected to the optical fiber after wavelength division multiplexing, transmitted to the other end through a smooth ring and then recovered into corresponding signals through a corresponding photoelectric conversion receiving module; and
secondly, a primary power supply of the satellite body supplies an energy power signal to the rotating part, and a microwave power source firstly converts electric energy of a satellite sailboard and a lithium battery into microwave energy and carries out directional emission to a far end from an emission antenna; then the microwave energy is transmitted through a distance of free space and captured by a rectifying antenna on the satellite rotating part, and is converted into direct current electric energy which is provided for each single machine of the satellite rotating part to be used as the input of a primary power supply.
While various embodiments of the present invention have been described above, it should be understood that they have been presented by way of example only, and not limitation. It will be apparent to persons skilled in the relevant art that various combinations, modifications, and changes can be made thereto without departing from the spirit and scope of the invention. Thus, the breadth and scope of the present invention disclosed herein should not be limited by any of the above-described exemplary embodiments, but should be defined only in accordance with the following claims and their equivalents.
Claims (8)
1. A power and signal transmission system for transmitting power and signals between a satellite rotating member and a satellite body, comprising:
a signal transmission subsystem comprising:
the rotating part photoelectric conversion subsystem is arranged on the satellite rotating part and comprises an electro-optical conversion transmitting module and a photoelectric conversion receiving module;
the satellite body photoelectric conversion subsystem is arranged on the satellite body and comprises an electro-optical conversion transmitting module and a photoelectric conversion receiving module; and
the optical slip ring is connected with the rotating part photoelectric conversion subsystem and the satellite body photoelectric conversion subsystem through optical fibers respectively, and is configured to be capable of transmitting optical signals; and
a power transmission subsystem configured to transmit the primary power of the satellite body to the satellite rotating member by radio transmission.
2. The system of claim 1, wherein the electro-optical conversion transmitting module comprises a radio frequency light conversion transmitting module, a digital light conversion transmitting module, an RS422 light conversion transmitting module, an RS485 light conversion transmitting module and a CAN light conversion transmitting module.
3. The system of claim 2, wherein the rf-to-lrf module comprises a pre-lna, an electro-optic transducer, and an automatic power, temperature controller.
4. The system of claim 1, wherein the optical-to-electrical conversion receiving module comprises a radio frequency to optical receiving module, a digital to optical receiving module, an RS422 to optical receiving module, an RS485 to optical receiving module, and a CAN to optical receiving module.
5. The system of claim 4, wherein the RF-to-optical receiving module comprises an optical path adapter, an optoelectronic converter, an optical power detection and bias controller, and a post-amplifier.
6. The system of claim 1, wherein the signal transmission subsystem further comprises a calibration optical path transmitting module disposed on the satellite body, and a calibration optical path receiving module disposed on the satellite rotating member.
7. The system of claim 1, wherein the signal transmission subsystem further comprises two wavelength division multiplexing modules disposed between the optical fiber and the satellite rotating component and between the optical fiber and the satellite body, respectively.
8. The system of claim 1, wherein the power delivery subsystem comprises a microwave power source, a transmitting antenna, a rectifying antenna, and a rectifying circuit, wherein the microwave power source and the transmitting antenna are disposed on the satellite body, and the rectifying antenna and the rectifying circuit are disposed on the satellite rotating component.
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| CN202010646167.0A CN111756435A (en) | 2020-07-07 | 2020-07-07 | Power and signal transmission system |
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| CN202010646167.0A CN111756435A (en) | 2020-07-07 | 2020-07-07 | Power and signal transmission system |
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