CN108827377A - Untetheredization measuring system for aircraft - Google Patents
Untetheredization measuring system for aircraft Download PDFInfo
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- CN108827377A CN108827377A CN201810403847.2A CN201810403847A CN108827377A CN 108827377 A CN108827377 A CN 108827377A CN 201810403847 A CN201810403847 A CN 201810403847A CN 108827377 A CN108827377 A CN 108827377A
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- 238000005259 measurement Methods 0.000 claims abstract description 55
- 238000005070 sampling Methods 0.000 claims description 36
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- 230000001360 synchronised effect Effects 0.000 claims description 14
- 230000002000 scavenging effect Effects 0.000 claims description 2
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- 238000005516 engineering process Methods 0.000 description 4
- 230000007613 environmental effect Effects 0.000 description 3
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- 230000008569 process Effects 0.000 description 3
- 230000007958 sleep Effects 0.000 description 3
- 230000002776 aggregation Effects 0.000 description 2
- 238000004220 aggregation Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 2
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- 229910021419 crystalline silicon Inorganic materials 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
- G01D21/00—Measuring or testing not otherwise provided for
- G01D21/02—Measuring two or more variables by means not covered by a single other subclass
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- G—PHYSICS
- G08—SIGNALLING
- G08C—TRANSMISSION SYSTEMS FOR MEASURED VALUES, CONTROL OR SIMILAR SIGNALS
- G08C17/00—Arrangements for transmitting signals characterised by the use of a wireless electrical link
- G08C17/02—Arrangements for transmitting signals characterised by the use of a wireless electrical link using a radio link
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Abstract
The present invention relates to a kind of untetheredization measuring systems for aircraft, including：Several wireless sensor slave modules (10) generate and send the first data according to the measuring signal for acquiring measuring signal in aircraft；Wireless host module (20) is wirelessly connected with the wireless sensor slave module (10), for receiving first data, generates the second data according to first data to form measurement data；Wireless charging transmitter (30) is wirelessly connected with the wireless sensor slave module (10), for charging for the wireless sensor slave module (20).The embodiment of the present invention, realize whole untetheredization of measuring system, save a large amount of wiring space, alleviate weight, significantly simplified installation procedure, reduce because cable contact it is bad caused by probability of malfunction, while also allowing to install more sensor measurement points.
Description
Technical Field
The invention belongs to the field of aerospace testing, and particularly relates to a cableless measuring system for an aircraft.
Background
In the process of carrying out flight tests on the novel spacecraft, measurement of a temperature field, a thermal flow field, a pressure field and the like of a key structure (such as an inner bulkhead, an outer bulkhead, a frame structure and a window body) of the aircraft is one of very important test links, and is also an important basis for force and heat calculation verification of the aircraft in a flight state.
The measurement of force and thermal fields is carried out by obtaining the temperature and mechanical parameter distribution of each part through a large number of sensors and combining data points into a field distribution diagram. Depending on the size of the structure to be measured, it is usually necessary to have hundreds or even thousands of sensors to complete the drawing of the force or thermal field distribution map. The arrangement of such a large number of sensors requires a large number of cables for power supply and multiplex signal transmission, and thousands of cables often fill the entire experimental chamber. This aspect adds weight and reduces the effective test load; on the other hand, the installation and maintenance processes of the cable are very complicated. In particular, in a recent wave-rider aircraft, the problem of insufficient installation space for sensor cables is more pronounced because the cabin is very narrow.
Existing distributed measurement and fieldbus technologies can reduce the overall length of the cable to some extent, but do not completely avoid the presence of cables. Signal cables can be eliminated, but power cables cannot be eliminated, using existing wireless sensor technology. If the battery is used for power supply, the battery is likely to be exhausted in the ground test stage, and the cost for replacing the battery is extremely high, namely according to the aerospace management regulations, the replacement of the battery is regarded as the change of product parts, and the cost for re-doing a whole set of environmental test is likely to be faced.
In summary, the main existing gaps of the existing sensing technologies are shown in: (1) the traditional sensor cable becomes a burden, the weight and the volume of the cable limit the total number of points to be measured, and the measurement resolution of a force thermal field is also limited; (2) due to the particularity of the application industry, the existing wireless sensor technology cannot realize the omission of a power line.
Disclosure of Invention
In order to solve the above problems in the prior art, the present invention provides an untethered measurement system for an aircraft. The technical problem to be solved by the invention is realized by the following technical scheme:
an embodiment of the present invention provides an untethered measurement system for an aircraft, including:
the system comprises a plurality of wireless sensor slave modules, a plurality of wireless sensor slave modules and a plurality of wireless sensor slave modules, wherein the wireless sensor slave modules are used for acquiring measurement signals in an aircraft, and generating and sending first data according to the measurement signals;
the wireless host module is wirelessly connected with the wireless sensor slave module and used for receiving the first data and generating second data according to the first data to form measurement data;
and the wireless charging transmitter is wirelessly connected with the wireless sensor slave module and is used for charging the wireless sensor slave module.
In an embodiment of the present invention, the wireless host module further includes a data storage and forwarding device connected to the wireless host module, and configured to store, record, and forward the measurement data.
In one embodiment of the present invention, the wireless sensor slave module comprises:
a plurality of sensors for collecting the measurement signals;
a wireless slave connected to the sensor for collecting the measurement signal and generating the first data;
and the slave antenna is connected with the wireless slave and is used for sending the first data to the wireless host module.
In one embodiment of the invention, the wireless slave machine is connected with N sensors, wherein N is more than or equal to 1 and less than or equal to 16.
In one embodiment of the present invention, the wireless slave includes: the device comprises a power transmission circuit module, a multi-path ADC sampling converter, an isolation SPI interface, a low-power consumption MCU, a radio frequency transceiver module and a power supply module; wherein,
the transmitting circuit module is connected with the multi-path ADC sampling converter;
the multichannel ADC sampling converter is connected with the isolation SPI interface and the power supply module;
the isolation SPI interface, the low-power consumption MCU, the radio frequency transceiver module and the slave antenna are connected in sequence.
In one embodiment of the present invention, the power supply module includes: the system comprises an isolation power supply, a power supply management module, a battery module and a monocrystalline silicon solar battery; wherein,
the monocrystalline silicon solar cell, the cell module and the power management module are sequentially connected;
the power management module is connected with the low-power-consumption MCU and the radio frequency transceiver module and is used for controlling the power supply of the low-power-consumption MCU and the radio frequency transceiver module;
the power management module is sequentially connected with the isolation power supply and the multichannel ADC sampling converter and used for controlling power supply of the multichannel ADC sampling converter.
In one embodiment of the present invention, the battery module includes: a battery and an energy collection module; wherein,
the monocrystalline silicon solar cell, the energy collecting module and the cell are connected in sequence;
the battery is connected with the power management module and used for supplying power to the wireless slave through the power management module.
In one embodiment of the invention, the wireless slave machine is charged through a weak ambient light energy collection mode and a wireless charging mode.
In one embodiment of the invention, the wireless charging transmitter comprises: the device comprises an input power supply, an isolation/pre-stabilized power supply module, a synchronous switch DC-DC module, a current sampling module, an infrared LED, a temperature management module and a constant current feedback module; wherein,
the input power supply, the isolation/pre-stabilized voltage supply module, the synchronous switch DC-DC module, the current sampling module and the infrared LED are sequentially connected;
the infrared LED is used for outputting light energy to the wireless sensor slave module;
the temperature management module is connected with the infrared LED and used for collecting the temperature of the infrared LED to form a control signal;
the constant current feedback module is connected with the current sampling module and the temperature management module and is used for receiving the sampling signal and the control signal;
the constant current feedback module is connected with the synchronous switch DC-DC module and used for sending the received control signal and the sampling signal to the synchronous switch DC-DC module.
In one embodiment of the present invention, the infrared light emitted from the infrared LED has a wavelength of 850 and 950 nm.
Compared with the prior art, the invention has the beneficial effects that:
1. according to the cableless measuring system provided by the invention, the information transmission between the slave modules and the wireless host of the multi-channel wireless sensor is wireless, the power line is completely omitted and replaced by the wireless charging emitter, so that a large amount of wiring space is saved, the weight is reduced, the installation process is simplified, the fault probability caused by poor contact of cables is reduced, and meanwhile, more sensor measuring points are allowed to be installed.
2. The cableless measurement system provided by the invention enables the multipoint distributed measurement of the temperature, pressure and heat flow field in the narrow cabin body to be more convenient.
3. The cableless measuring system provided by the invention integrates a multi-channel collector, supports direct input of thermocouples and heat flow sensors with various specifications, further reduces the complexity of the system and reduces the total volume.
4. The cableless measurement system provided by the invention is flexible and simple to install, greatly reduces the load volume and the weight of cables, is particularly suitable for measuring a high-density distribution temperature field, a thermal flow field and a stress field of an engine room, a magazine and a test bin section, and can also be applied to distributed measurement in other various severe environments.
Drawings
FIG. 1 is a schematic structural diagram of an untethered measurement system for an aircraft according to an embodiment of the present invention;
FIG. 2 is a schematic structural diagram of a wireless sensor slave module of an untethered measurement system for an aircraft according to an embodiment of the present invention;
FIG. 3 is a schematic structural diagram of a wireless sensor slave module of another cableless measurement system for an aircraft according to an embodiment of the present invention;
fig. 4 is a schematic structural diagram of a wireless charging transmitter of an untethered measurement system for an aircraft according to an embodiment of the present invention;
fig. 5 is a schematic structural diagram of another untethered measurement system for an aircraft according to an embodiment of the present invention.
Detailed Description
The present invention will be described in further detail with reference to specific examples, but the embodiments of the present invention are not limited thereto.
Example one
Referring to fig. 1, fig. 1 is a schematic structural diagram of an untethered measurement system for an aircraft according to an embodiment of the present invention.
An untethered measurement system for an aircraft, comprising:
the plurality of wireless sensor slave modules 10 are used for collecting measurement signals in the aircraft, and generating and sending first data according to the measurement signals;
the wireless host module 20 is wirelessly connected with the wireless sensor slave module 10 and is used for receiving the first data and generating second data according to the first data to form measurement data;
and a wireless charging transmitter 30 wirelessly connected to the wireless sensor slave module 20, for charging the wireless sensor slave module 10.
Further, a data storage and forwarding device 40 is further included, connected to the wireless host module 20, for storing, recording, and forwarding the measurement data.
Further, the wireless sensor slave module 10 includes:
a plurality of sensors 11 for acquiring the measurement signals;
a wireless slave 12 connected to the sensor 11 for collecting the measurement signal and generating the first data;
and the slave antenna 13 is connected with the wireless slave 12 and is used for sending the first data to the wireless master module 20.
Further, the wireless host module 20 includes:
the wireless master 21 is connected with the wireless slave 12 and used for generating second data according to the first data to form measurement data;
and the master antenna 22 is connected with the wireless master 21 and is used for receiving the first data transmitted by the slave antenna 13.
In the cableless measuring system of the present invention, the sensor 11 collects the measuring signal of the measuring field and transmits the measuring signal to the wireless slave 12, wherein the measuring signal may be an analog signal, the wireless slave 12 generates first data after completing the work of transmitting and conditioning the analog signal, digitally sampling, calibrating the graduation meter, etc., and transmits the first data to the wireless master 21, and the wireless master 21 performs communication coordination and data aggregation on the first data and then packages the first data according to a predetermined data format to generate second data to form measuring data.
Further, the plurality of sensors 11 may be collectively provided as one kind or may be provided as a plurality of kinds of sensors at the same time.
Further, the sensor 11 may collect a temperature signal for a temperature sensor, a stress signal for a force sensor, or any sensor that can collect a field signal, which is not limited herein.
The embodiment of the invention not only saves all wiring including a power supply, but also simplifies the system structure, reduces the installation procedures and simultaneously improves the reliability of the system.
Example two
Referring to fig. 1 again, the present embodiment focuses on the detailed description of the important components and the operation principle of the cableless measurement system for an aircraft based on the above-mentioned embodiment.
The present embodiment includes all the contents of the above embodiments, and further, the measurement system further includes: and the data storage and forwarding device 40 is connected with the wireless host 21 and is used for storing, recording and forwarding the measurement data.
Referring to fig. 2, fig. 2 is a schematic structural diagram of a wireless sensor slave module of a cableless measurement system for an aircraft according to an embodiment of the present invention; specifically, the wireless sensor slave module comprises:
a plurality of sensors 11 for acquiring the measurement signals;
a wireless slave 12 connected to the sensor 11 for collecting the measurement signal and generating the first data;
and a slave antenna 13 connected to the wireless slave 12, for transmitting the first data to the wireless master 21 in the wireless master module 20.
As shown in fig. 2, the plurality of sensors 11 are a plurality of independent sensors 1#, 2# … …, and N #;
furthermore, the wireless slave 12 is connected with N sensors 11, wherein N is more than or equal to 1 and less than or equal to 16. Preferably, N ═ 8. The sensors 11 and the corresponding wireless slaves 12 are arranged according to the principle of proximity.
Further, the wireless slave 12 includes: a transmitting circuit module 121, a multi-channel ADC sampling converter 122, an isolation SPI interface 123, a low-power consumption MCU124, a radio frequency transceiver module 125 and a power supply module 126; wherein,
the transmitting circuit module 121 includes a plurality of independent transmitting circuits 1#, 2# … … N #;
the transmitting circuit module 121 is connected to the multi-channel ADC sampling converter 122;
the multichannel ADC sampling converter 122, connected to the isolation SPI interface 123 and the power module 126, is configured to sample multiple channels of signals of the sensor 11 passing through respective transmitting circuits;
the isolation SPI interface 123, the low-power consumption MCU124, the radio frequency transceiver module 125, and the slave antenna 13 are connected in sequence.
Referring to fig. 3, fig. 3 is a schematic structural diagram of a wireless sensor slave module of another cableless measurement system for an aircraft according to an embodiment of the present invention; specifically, the power module 126 includes: an isolated power supply 1261, a power management module 1262, a battery module 1263, a single crystal silicon solar cell 1264; wherein,
the monocrystalline silicon solar cell 1264, the battery module 1263, and the power management module 1262 are connected in sequence;
the power management module 1262 is connected to the low-power consumption MCU124 and the radio frequency transceiver module 125, and is configured to control power supply of the low-power consumption MCU124 and the radio frequency transceiver module 125;
the power management module 1262 is sequentially connected to the isolation power supply 1261 and the multiple ADC sampling converter 122, and is configured to control power supply of the multiple ADC sampling converter 122.
Further, the battery module 1263 includes: a battery 12631 and an energy scavenging module 12632; wherein,
the monocrystalline silicon solar cell 1264, the energy collecting module 12632 and the battery 12631 are connected in sequence;
the battery 12631 is connected to the power management module 1262, and is configured to supply power to the wireless slave 12 through the power management module 1262.
Further, the sensors 11 transmit the measurement signals to the wireless slave 12 via their respective transmission circuits.
The working principle of the wireless slave 12 is as follows: the signals of the multiple paths of sensors 11 are amplified by respective transmitting circuits and then sampled simultaneously by the ADC, the obtained data are sent to the low-power consumption MCU124 through the SPI isolation interface 123 and are temporarily stored in the buffer memory of the low-power consumption MCU124 in sequence according to the sampling sequence, and then the buffer data are periodically packed and sent to the wireless host 21 according to a predetermined protocol with the wireless host 21, and the wireless host 21 performs communication coordination and data aggregation, and then packs and sends to the data storage and forwarding device 40 according to a predetermined data format.
Referring to fig. 4, fig. 4 is a schematic structural diagram of a wireless charging transmitter of an untethered measurement system for an aircraft according to an embodiment of the present invention, specifically, the wireless charging transmitter 30 includes: an input power supply 301, an isolation/pre-stabilized power supply module 302, a synchronous switch DC-DC module 303, a current sampling module 304, an infrared LED 305, a temperature management module 306 and a constant current feedback module 307; wherein,
the input power supply 301, the isolation/pre-stabilized power supply module 302, the synchronous switch DC-DC module 303, the current sampling module 304, and the infrared LED 305 are connected in sequence;
the infrared LED 305 for outputting light energy to the wireless sensor slave module 20;
the temperature management module 306 is connected to the infrared LED 305, and is configured to collect the temperature of the infrared LED 305 to form a control signal;
the constant current feedback module 307 is connected to the current sampling module 304 and the temperature management module 306, and is configured to receive the sampling signal and the control signal;
the constant current feedback module 307 is connected to the synchronous switch DC-DC module 303, and configured to send the received control signal and the received sampling signal to the synchronous switch DC-DC module 303.
Further, the infrared LED 305 emits infrared light with a wavelength of 850nm to 950nm, which is the same as the peak wavelength of the spectral response of the single crystalline silicon solar cell. This is the stage where the single crystal silicon solar cell 1264 is most efficient, and the optical transmission does not generate electromagnetic wave band radiation interference, and therefore does not generate interference to other electronic devices.
In one embodiment, the infrared LED 305 emits infrared light at 940 nm.
The working principle of the wireless charging transmitter 30 is as follows: firstly, the input power supply 301 is input to the pre-voltage stabilization/isolation module 302, the voltage is stabilized at about 28V, then the high-power infrared LED 305 with the wavelength of 940nm is driven to emit infrared rays through the synchronous switch DC-DC module 303, and the current sampling module 304 is driven to make the current be retrieved as the feedback of the synchronous switch DC-DC module 303, so as to realize the constant current driving function;
the temperature management module 306 detects the temperature of the infrared LED 305, and if the temperature exceeds 60 ℃, the constant current value is automatically reduced, thereby performing an overheat derating protection function.
Further, the wireless slave 12 has two charging modes.
The first is a weak ambient energy harvesting mode: the standby state can be maintained for a long time without power shortage by collecting weak light energy in the environment to supplement the self-discharge of the battery 12631.
The monocrystalline silicon solar cell 1264 is responsible for acquiring light energy in the environment, the energy collection module 12632 boosts the voltage and charges the battery 12631, the self-discharge of the battery 12631 can be counteracted as long as weak ambient light exists, and the full-charge state of the battery 12631 is always maintained. The battery 12631 may also be charged quickly by an additional active light source when long periods of operation are required.
The second is a wireless charging mode: in the debugging stage requiring long-term power supply or when quick charging is temporarily required, the wireless charging transmitter 30 is turned on, energy is transferred through 940nm light waves, all the wireless slaves 12 in the cabin are wirelessly charged at the same time, and electromagnetic interference to other electronic equipment is avoided.
Further, the wireless slave 12 may be powered off in a wireless remote control manner during the storage and transportation stage, and is switched back to the low power consumption standby mode, so that the whole system of the wireless slave 12 is in a sleep state most of the time; the sleep state is turned on, and all devices except the low power consumption MCU124 are turned off by the power management module 1262, so that the power consumption of 30 μ a or less on average can be maintained, and the device can stand by for more than 1 year without additional charging even in a dark environment.
Further, each wireless slave 12 supports wireless wake-up, the low power consumption MCU124 wakes up once every 20 seconds, turns on the radio frequency transceiver module 125 to inquire whether a power-on instruction is received, if the power-on instruction is received, powers on all devices through the power management module 1262, and operates according to a predetermined sampling rate, otherwise continues to sleep; after awakening, the sensor 11 and the measuring system can continuously work for more than 10 hours in a full-speed running state, which is enough to complete a flight test task. The measuring system of the embodiment of the invention can achieve the following beneficial effects:
1. the measurement system really realizes the cableless measurement, not only the information transmission between the wireless sensor slave module and the wireless host is wireless, but also the power line is completely saved and is replaced by the wireless charging emitter, thereby not only saving a large amount of wiring space and reducing the weight, but also simplifying the installation procedure and reducing the fault probability caused by poor contact of cables.
2. The wireless charging transmitter in the measuring system adopts 940nm light energy transmission, which is the means with the highest efficiency of the monocrystalline silicon photovoltaic cell, and the light transmission process does not generate electromagnetic wave frequency band radiation interference, thereby not generating interference on other electronic equipment.
3. The measuring system supports deep dormancy and remote wireless awakening, supports environmental energy collection, utilizes weak environmental light energy to charge, and can not be charged for a long time.
EXAMPLE III
Referring to fig. 5, fig. 5 is a schematic structural diagram of another untethered measurement system for an aircraft according to an embodiment of the present invention.
Taking 32-point temperature field measurement on the inner wall of a certain aircraft cabin as an example, the application of the cableless measurement system is described in detail; the cableless measurement system is composed of 4 wireless sensor slave modules 10, 1 wireless host 21, 1 wireless charging transmitter 30 and data storage and forwarding equipment 40. Each sensor 11 is responsible for acquiring 8 paths of nearby thermocouple signals, sampling at fixed time according to a preset sampling rate and sending data to the wireless host 21 through a wireless link; the wireless master 21 is responsible for collecting all data information sent by the wireless slave 12, and sending the data information to the data storage and forwarding device 40 in a time stamp packaging manner. The wireless charging transmitter 30 is installed in the middle of the cabin, and when long-term power supply is needed in the ground test stage, the wireless charging transmitter 30 emits infrared rays with the wavelength of 940nm, irradiates 4 monocrystalline silicon solar cells of the wireless sensor slave module 10 through a direct or diffuse reflection path, and charges the cells in the monocrystalline silicon solar cells.
Compared with the prior art, the embodiment of the invention has obvious advantages, a wiring process is not required in the cabin, a large amount of cable weight and space are saved, the reliability problem of cable joints is avoided, and more sensing nodes can be arranged in a narrow cabin.
The foregoing is a more detailed description of the invention in connection with specific preferred embodiments and it is not intended that the invention be limited to these specific details. For those skilled in the art to which the invention pertains, several simple deductions or substitutions can be made without departing from the spirit of the invention, and all shall be considered as belonging to the protection scope of the invention.
Claims (10)
1. An untethered measurement system for an aircraft, comprising:
the system comprises a plurality of wireless sensor slave modules (10) and a plurality of wireless sensor slave modules, wherein the wireless sensor slave modules are used for acquiring measurement signals in an aircraft, and generating and sending first data according to the measurement signals;
the wireless host module (20) is wirelessly connected with the wireless sensor slave module (10) and is used for receiving the first data and generating second data according to the first data to form measurement data;
the wireless charging transmitter (30) is wirelessly connected with the wireless sensor slave module (10) and is used for charging the wireless sensor slave module (10).
2. The system of claim 1, further comprising a data store-and-forward device (40) coupled to the wireless host module (20) for storing, recording, and forwarding the measurement data.
3. The system according to claim 1, characterized in that said wireless sensor slave module (10) comprises:
a plurality of sensors (11) for acquiring said measurement signals;
a wireless slave (12) connected to the sensor (11) for collecting the measurement signal and generating the first data;
and the slave antenna (13) is connected with the wireless slave (12) and is used for transmitting the first data to the wireless host module (20).
4. System according to claim 3, characterized in that said wireless slave (12) is connected to N said sensors (11), where 1 ≦ N ≦ 16.
5. A system according to claim 3, characterized in that said wireless slave (12) comprises: the device comprises a transmitting circuit module (121), a multi-path ADC sampling converter (122), an isolation SPI interface (123), a low-power consumption MCU (124), a radio frequency transceiving module (125) and a power supply module (126); wherein,
the transmitting circuit module (121) is connected with the multichannel ADC sampling converter (122);
the multichannel ADC sampling converter (122) is connected with the isolation SPI interface (123) and the power supply module (126);
the isolation SPI interface (123), the low-power consumption MCU (124), the radio frequency transceiving module (125) and the slave antenna (13) are sequentially connected.
6. The system of claim 5, wherein the power module (126) comprises: an isolated power supply (1261), a power management module (1262), a battery module (1263), and a single crystal silicon solar cell (1264); wherein,
the monocrystalline silicon solar cell (1264), the battery module (1263) and the power management module (1262) are connected in sequence;
the power management module (1262) is connected with the low-power consumption MCU (124) and the radio frequency transceiver module (125) and is used for controlling the power supply of the low-power consumption MCU (124) and the radio frequency transceiver module (125);
the power management module (1262) is sequentially connected with the isolation power supply (1261) and the multichannel ADC sampling converter (122) and is used for controlling power supply of the multichannel ADC sampling converter (122).
7. The system of claim 6, wherein the battery module (1263) comprises: a battery (12631) and an energy scavenging module (12632); wherein,
the monocrystalline silicon solar cell (1264), the energy collecting module (12632) and the battery (12631) are connected in sequence;
the battery (12631) is connected with the power management module (1262) and is used for supplying power to the wireless slave (12) through the power management module (1262).
8. The system according to claim 6, wherein the wireless slave (12) is charged by a weak ambient light energy gathering mode and a wireless charging mode.
9. The system of claim 1, wherein the wireless charging transmitter (30) comprises: the device comprises an input power supply (301), an isolation/pre-stabilized power supply module (302), a synchronous switch DC-DC module (303), a current sampling module (304), an infrared LED (305), a temperature management module (306) and a constant current feedback module (307); wherein,
the input power supply (301), the isolation/pre-stabilized power supply module (302), the synchronous switch DC-DC module (303), the current sampling module (304) and the infrared LED (305) are sequentially connected;
the infrared LED (305) for outputting light energy to the wireless sensor slave module (20);
the temperature management module (306) is connected with the infrared LED (305) and is used for collecting the temperature of the infrared LED (305) to form a control signal;
the constant current feedback module (307) is connected with the current sampling module (304) and the temperature management module (306) and is used for receiving the sampling signal and the control signal;
the constant current feedback module (307) is connected with the synchronous switch DC-DC module (303) and is used for sending the received control signal and the sampling signal to the synchronous switch DC-DC module (303).
10. The system of claim 9, wherein the infrared LED (305) emits infrared light at a wavelength of 850nm to 950 nm.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109934329A (en) * | 2019-04-18 | 2019-06-25 | 苏州易德龙科技股份有限公司 | A kind of real-time low-consumption wireless transmission counting device for counting production efficiency |
| CN111132059A (en) * | 2019-11-25 | 2020-05-08 | 北京宇航系统工程研究所 | Wireless sensor network system suitable for acquiring flight parameters |
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Application publication date: 20181116 |