CN111682644A - Power management system based on manned and unmanned modification - Google Patents
Power management system based on manned and unmanned modification Download PDFInfo
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- CN111682644A CN111682644A CN202010512702.3A CN202010512702A CN111682644A CN 111682644 A CN111682644 A CN 111682644A CN 202010512702 A CN202010512702 A CN 202010512702A CN 111682644 A CN111682644 A CN 111682644A
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- monitoring unit
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- power
- load monitoring
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- 238000012986 modification Methods 0.000 title claims abstract description 17
- 230000004048 modification Effects 0.000 title claims abstract description 17
- 238000012544 monitoring process Methods 0.000 claims abstract description 76
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims abstract description 48
- 230000005611 electricity Effects 0.000 claims abstract description 13
- 238000001514 detection method Methods 0.000 claims abstract description 11
- 238000004891 communication Methods 0.000 claims abstract description 8
- 238000012545 processing Methods 0.000 claims description 9
- 238000006243 chemical reaction Methods 0.000 claims description 4
- 230000008878 coupling Effects 0.000 claims description 3
- 238000010168 coupling process Methods 0.000 claims description 3
- 238000005859 coupling reaction Methods 0.000 claims description 3
- 238000012423 maintenance Methods 0.000 claims description 3
- 230000002950 deficient Effects 0.000 claims 2
- 238000010586 diagram Methods 0.000 description 4
- 238000000034 method Methods 0.000 description 3
- 238000013461 design Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000009420 retrofitting Methods 0.000 description 1
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Classifications
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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
- H02J13/00—Circuit arrangements for providing remote indication of network conditions, e.g. an instantaneous record of the open or closed condition of each circuitbreaker in the network; Circuit arrangements for providing remote control of switching means in a power distribution network, e.g. switching in and out of current consumers by using a pulse code signal carried by the network
- H02J13/00002—Circuit arrangements for providing remote indication of network conditions, e.g. an instantaneous record of the open or closed condition of each circuitbreaker in the network; Circuit arrangements for providing remote control of switching means in a power distribution network, e.g. switching in and out of current consumers by using a pulse code signal carried by the network characterised by monitoring
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02H—EMERGENCY PROTECTIVE CIRCUIT ARRANGEMENTS
- H02H7/00—Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions
- H02H7/22—Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions for distribution gear, e.g. bus-bar systems; for switching devices
-
- 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
- H02J13/00—Circuit arrangements for providing remote indication of network conditions, e.g. an instantaneous record of the open or closed condition of each circuitbreaker in the network; Circuit arrangements for providing remote control of switching means in a power distribution network, e.g. switching in and out of current consumers by using a pulse code signal carried by the network
- H02J13/00006—Circuit arrangements for providing remote indication of network conditions, e.g. an instantaneous record of the open or closed condition of each circuitbreaker in the network; Circuit arrangements for providing remote control of switching means in a power distribution network, e.g. switching in and out of current consumers by using a pulse code signal carried by the network characterised by information or instructions transport means between the monitoring, controlling or managing units and monitored, controlled or operated power network element or electrical equipment
- H02J13/00016—Circuit arrangements for providing remote indication of network conditions, e.g. an instantaneous record of the open or closed condition of each circuitbreaker in the network; Circuit arrangements for providing remote control of switching means in a power distribution network, e.g. switching in and out of current consumers by using a pulse code signal carried by the network characterised by information or instructions transport means between the monitoring, controlling or managing units and monitored, controlled or operated power network element or electrical equipment using a wired telecommunication network or a data transmission bus
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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
- H02J9/00—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting
- H02J9/04—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source
- H02J9/06—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source with automatic change-over, e.g. UPS systems
- H02J9/08—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source with automatic change-over, e.g. UPS systems requiring starting of a prime-mover
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D2221/00—Electric power distribution systems onboard aircraft
-
- 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
- H02J2310/00—The network for supplying or distributing electric power characterised by its spatial reach or by the load
- H02J2310/40—The network being an on-board power network, i.e. within a vehicle
- H02J2310/44—The network being an on-board power network, i.e. within a vehicle for aircrafts
Landscapes
- Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Computer Networks & Wireless Communication (AREA)
- Aviation & Aerospace Engineering (AREA)
- Business, Economics & Management (AREA)
- Emergency Management (AREA)
- Remote Monitoring And Control Of Power-Distribution Networks (AREA)
Abstract
The invention relates to the technical field of electrical systems of general aircrafts, and discloses a power management system based on unmanned modification of an unmanned aerial vehicle, which comprises: the equipment obtains electric power from each power supply of the airplane through a power supply cable and reasonably distributes the electric power to other equipment for power supply, and is connected with the flight control computer through a communication cable so as to receive a control signal of the flight control computer and upload a detection return value to the flight control computer. The system can send the current electricity utilization information, working state, switching state and other information of the equipment to the flight control computer, so that the flight control computer can make a definite judgment according to the current equipment state and control each equipment through the load monitoring unit, and the equipment safety is improved; meanwhile, the load monitoring unit can perform current-limiting protection, overcurrent restarting and the like on the power consumption of the equipment, and the same working state controlled by the fuse when the driver drives by a man machine is achieved.
Description
Technical Field
The invention relates to the technical field of electrical systems of general airplanes, in particular to a power management system based on unmanned modification of a man-machine.
Background
With the rapid development of the current social logistics industry, fast and efficient logistics ways are being pursued by large logistics enterprises, and airplane transportation is just an efficient substitute. The P-750XL general airplane of Pacific Aerospace company in New Zealand is very suitable for branch line transportation in logistics industry due to the characteristics of short take-off and landing distance, heavy load weight and long effective range.
The manned aircraft has high operation cost and large limitation on operation conditions due to weather factors, so the current situation can be greatly improved by unmanned modification of the manned aircraft. And the power management of the system is the premise that the airborne equipment can work normally.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: aiming at the existing problems, the power management system based on the man-machine unmanned modification is provided.
The technical scheme adopted by the invention is as follows: a power management system based on unmanned modification of human machines comprises: the system comprises at least one power supply system load monitoring unit, a flight control computer and a power supply system, wherein the load monitoring unit is used for providing power for the aircraft equipment, monitoring the power utilization condition of each piece of equipment and sending the power utilization condition to the flight control computer;
the flight control computer judges the equipment required to be used according to the working requirement of the airplane and outputs a switching instruction to the load monitoring unit;
the aircraft power supply is used for providing power for flight, ground and emergency of the aircraft.
Furthermore, the load monitoring unit does not serve as a power supply, and the power consumption of the load monitoring unit is from the airplane power supply; the load monitoring unit is connected with the flight control computer through a cable, the cable comprises a power supply cable and a communication cable, the power supply cable is used for supplying power to the flight control computer by the load monitoring unit, and the communication cable is used for receiving an instruction of the flight control computer by the load monitoring unit and sending the power supply condition of the airplane equipment to the flight control computer; the load monitoring unit is connected with the aircraft equipment through a power supply cable.
Further, a plurality of aircraft devices are connected to the load monitoring unit.
Further, the aircraft power supply includes:
the external power supply is used for supplying power to all equipment in the ground maintenance stage or the ground starting stage of the airplane;
the generator is used for providing electricity for the whole-airplane equipment after the starting of the airplane engine is finished;
and the onboard battery is used for providing emergency electricity for the whole aircraft equipment when the aircraft generator does not generate electricity or outputs electricity correctly.
Furthermore, the load monitoring unit can work normally when any one power supply is switched on, and the phenomenon of power failure or restarting is not generated when the power supply is switched.
Further, the load monitoring unit includes:
the isolated power supply conversion unit is used for converting the airplane power supply into the power consumption required by the work of the load monitoring unit;
the power supply detection unit is used for detecting the current and voltage condition of the airplane power supply;
the non-switching equipment power distribution unit is used for providing power supply and protection functions for all aircraft equipment which does not need to be switched on and off;
the switch type equipment power distribution unit is used for providing power supply and protection functions for all airplane equipment needing to be switched;
the monitoring unit is used for collecting all detection quantities including switching state quantity, voltage and current;
the data processing unit is used for processing and forwarding all the quantities detected by the monitoring unit;
the data recording unit is used for storing all the data processed by the data processing unit;
and the bus interface is used for electrically coupling the load monitoring unit with the flight control computer.
Further, the flight control computer is used for providing switching judgment for the switch equipment of the whole machine in the system, and sending the instruction to the load monitoring unit to control the on-off of the switch equipment.
Furthermore, the flight control computer also needs to receive parameters such as the power supply condition of the aircraft equipment detected by the load monitoring unit, and judge, forward and store the parameters.
Further, when the flight control computer judges that a problem occurs in the detection signal from the load monitoring unit, an instruction for alarming and switching off the power supply of the problem equipment should be sent to the load monitoring unit in time.
Further, an application model of the power management system based on human-computer unmanned modification is an AT200 unmanned aerial vehicle modified by taking P-750XL produced by Pacific Aerospace of New Zealand as a prototype.
Compared with the prior art, the beneficial effects of adopting the technical scheme are as follows:
(1) the aircraft equipment is powered by the load monitoring unit, and the current power utilization information, the working state, the switching state and other information of the equipment can be sent to the flight control computer, so that the flight control computer can make clear judgment according to the current equipment state and control each equipment through the load monitoring unit, and the equipment safety is improved.
(2) The load monitoring unit can perform current-limiting protection, overcurrent restarting and the like on the power consumption of equipment, and the same working state controlled by a fuse when the driver drives by a man-machine is achieved.
Drawings
Fig. 1 is a schematic diagram of a power management system modified by a human-machine unmanned system according to the invention.
Fig. 2 is a schematic diagram of a functional module of a load monitoring unit of the power supply system.
Reference numerals: 100-aircraft power supply; 101-an external power supply; 102-a generator; 103-on-board battery; 200-a load monitoring unit; 201-an isolated power conversion unit; 202-power detection unit; 203-non-switching type equipment power distribution; 204-switching class equipment power distribution; 205-a monitoring unit; 206-a data processing unit; 207-data recording unit; 208-bus interface 300-flight control computer; 400-aircraft equipment.
Detailed Description
The invention provides a power management system based on manned and unmanned modification, which supplies power to aircraft equipment through a load monitoring unit, sends information such as the power consumption condition and the switching state of the equipment to a flight control computer, and the flight control computer makes a clear judgment according to the current aircraft requirement and the equipment state and outputs an instruction to the load monitoring unit, thereby accurately controlling the use of the equipment and protecting a circuit.
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present disclosure will be described in further detail below with reference to specific embodiments and the accompanying drawings. It should be emphasized that the following description is merely exemplary in nature and is not intended to limit the scope of the disclosure or its applications.
In one exemplary embodiment of the invention, a power management system based on human-machine unmanned retrofitting is provided. In this embodiment, the application model of the power management system to be modified without human is an AT200 unmanned aerial vehicle modified by using P-750XL available man-machine as a prototype, which is produced by Pacific Aerospace, new zealand.
Fig. 1 is a schematic diagram of a power management system modified by a human-machine unmanned system according to an embodiment of the invention. As shown in fig. 1, the power management system includes:
an aircraft power supply 100 that provides flight, ground, and emergency power for the aircraft;
a load monitoring unit 200 that supplies power to the aircraft device 400 and monitors the power consumption status of each device and sends it to the flight control computer;
and the flight control computer 300 is used for judging the equipment required to be used according to the working requirement of the airplane and outputting a switching instruction to the load monitoring unit.
Fig. 2 is a schematic diagram of a functional module of a load monitoring unit of a power supply system modified by unmanned or unmanned operation according to an embodiment of the present invention. As shown in fig. 2, the power supply system load monitoring unit function module includes:
the isolated power supply conversion unit 201 is used for converting the airplane power supply into the power consumption required by the work of the load monitoring unit;
a power supply detection unit 202 for detecting a current-voltage condition of the aircraft power supply;
the non-switching equipment power distribution 203 is used for providing functions of power supply, protection and the like for all aircraft equipment which does not need to be subjected to switching control;
the switch type equipment power distribution 204 is used for providing functions of power supply, protection and the like for all airplane equipment needing to be switched;
a monitoring unit 205 for collecting all detection quantities including switching state quantity, voltage, current, and the like;
a data processing unit 206, configured to process and forward all the quantities detected by the monitoring unit;
a data recording unit 207 for saving all the data processed by the data processing unit;
a bus interface 208 for electrically coupling the load monitoring unit and the flight control computer.
The following describes each component of the power management system with the human-machine unmanned modification in the embodiment in detail.
The load monitoring unit 200 does not generate power by itself, and its own power usage or power supply to the aircraft equipment is from the aircraft power supply 400.
The load monitoring unit 200 is electrically coupled to the flight control computer 300 through a cable, wherein the cable includes a power supply cable and a communication cable.
The power supply cable is used for the load monitoring unit 200 to supply power to the flight control computer 300, and the communication cable is used for the load monitoring unit 200 to receive instructions from the flight control computer 300 and to send information such as power supply conditions and switch states of the aircraft equipment to the flight control computer 300.
The aircraft devices 400 that are powered by the load monitoring unit 200 are electrically coupled thereto by power cables.
In a cable connecting the load monitoring unit 200 and the flight control computer 300, at least 14 pins are required to be connected with both devices, wherein 4 pins are used for power supply, and 10 pins are used for communication.
The load monitoring unit 200 may be connected to a plurality of devices, and these devices may all obtain functions such as overcurrent protection, output current limiting, disconnection reconnection, and the like through the load monitoring unit 200 and may transmit their own power consumption information to the flight control computer 300 through the load monitoring unit 200.
the external power supply 101 is used for supplying power to all equipment in the ground maintenance stage or the ground starting stage of the airplane;
the generator 102 is used for providing electricity for all-airplane equipment after the airplane engine finishes starting;
and the onboard battery 103 is used for providing emergency electricity for all-aircraft equipment when the aircraft generator does not generate electricity or outputs electricity correctly.
The load monitoring unit 200 should work normally when connected to any one of the airplane power supplies, and no power failure or restart occurs when the power supplies are switched.
The load monitoring unit 200 has the following functions: the power supply of the connected equipment can be met; the power supply state of the connected equipment can be monitored; information of the connected devices can be uploaded to the flight control computer 300; can receive the instruction of the flight control computer 300 and operate according to the instruction.
The flight control computer 300 should determine the use of the whole aircraft equipment according to the current aircraft state and task requirements, and send instructions to the load monitoring unit 200 to control the on/off of the aircraft equipment.
The flight control computer 300 should be able to receive parameters such as the power supply condition of the aircraft equipment, the switch state and the like from the load monitoring unit 200, and determine, forward and store the parameters.
When judging that the detection signal from the load monitoring unit 200 is faulty, the flight control computer 300 should send an alarm to the load monitoring unit 200 in time and turn off the power supply of the faulty device.
So far, the examples of the present disclosure have been described in detail with reference to the accompanying drawings. From the above description, those skilled in the art should clearly recognize that the power management system of the present disclosure is based on an unmanned and unmanned modification.
It is to be noted that, in the attached drawings or in the description, the implementation modes not shown or described are all the modes known by the ordinary skilled person in the field of technology, and are not described in detail. Further, the above definitions of the various elements and methods are not limited to the various specific structures, shapes or arrangements of parts mentioned in the examples, which may be easily modified or substituted by those of ordinary skill in the art.
In summary, in the power management system based on the manned and unmanned modification, the load monitoring unit supplies power to the aircraft equipment, and sends information such as the power utilization condition and the switching state of the equipment to the flight control computer, and the flight control computer makes a clear judgment according to the current aircraft requirement and the equipment state and outputs an instruction to the load monitoring unit, so that the use of the equipment is accurately controlled and the circuit can be protected.
Furthermore, the word "comprising" does not exclude the presence of elements or steps not listed in a claim. The word "a" or "an" preceding an element does not exclude the presence of a plurality of such elements.
In addition, unless steps are specifically described or must occur in sequence, the order of the steps is not limited to that listed above and may be changed or rearranged as desired by the desired design. The embodiments described above may be mixed and matched with each other or with other embodiments based on design and reliability considerations, i.e., technical features in different embodiments may be freely combined to form further embodiments.
Similarly, it should be appreciated that in the foregoing description of exemplary embodiments of the disclosure, various features of the disclosure are sometimes grouped together in a single embodiment, figure, or description thereof for the purpose of streamlining the disclosure and aiding in the understanding of one or more of the various disclosed aspects. However, the disclosed method should not be interpreted as reflecting an intention that: that is, the claimed disclosure requires more features than are expressly recited in each claim. Rather, as the following claims reflect, disclosed aspects lie in less than all features of a single foregoing disclosed embodiment. Thus, the claims following the detailed description are hereby expressly incorporated into this detailed description, with each claim standing on its own as a separate embodiment of this disclosure.
The above-mentioned embodiments are intended to illustrate the objects, aspects and advantages of the present disclosure in further detail, and it should be understood that the above-mentioned embodiments are only illustrative of the present disclosure and are not intended to limit the present disclosure, and any modifications, equivalents, improvements and the like made within the spirit and principle of the present disclosure should be included in the scope of the present disclosure.
Claims (10)
1. A power management system based on human-machine unmanned modification is characterized by comprising:
the system comprises at least one power supply system load monitoring unit, a flight control computer and a power supply system, wherein the load monitoring unit is used for providing power for the aircraft equipment, monitoring the power utilization condition of each piece of equipment and sending the power utilization condition to the flight control computer;
the flight control computer judges the equipment required to be used according to the working requirement of the airplane and outputs a switching instruction to the load monitoring unit;
the aircraft power supply is used for providing power for flight, ground and emergency of the aircraft.
2. The power management system based on the manned and unmanned aerial vehicle is modified according to claim 1, wherein the load monitoring unit does not serve as a power supply per se, and the power consumption of the load monitoring unit is derived from an aircraft power supply;
the load monitoring unit is connected with the flight control computer through a cable;
the cable comprises a power supply cable and a communication cable, wherein the power supply cable is used for supplying power to the flight control computer by the load monitoring unit;
the communication cable is used for the load monitoring unit to receive the instruction of the flight control computer and send the power supply condition of the airplane equipment to the flight control computer;
the load monitoring unit is connected with the aircraft equipment through a power supply cable.
3. The system of claim 2, wherein a plurality of aircraft devices are connected to the load monitoring unit.
4. The system of claim 1, wherein the aircraft power supply comprises an external power supply, a generator, and an onboard battery;
the external power supply is used for supplying power to all equipment in the ground maintenance stage or the ground starting stage of the airplane;
the generator is used for providing electricity for the whole-airplane equipment after the starting of the airplane engine is completed;
the onboard battery is used for providing emergency electricity for the whole aircraft equipment when the aircraft generator does not generate electricity or outputs electricity correctly.
5. The power management system based on manned and unmanned modification of claim 4, wherein the load monitoring unit can work normally when connected with any one of the aircraft power supplies, and the load monitoring unit does not generate power failure or restart phenomenon when the power supplies are switched.
6. The system of claim 1, wherein the load monitoring unit comprises:
the isolated power supply conversion unit is used for converting the airplane power supply into the power consumption required by the work of the load monitoring unit;
the power supply detection unit is used for detecting the current and voltage condition of the airplane power supply;
the non-switching equipment power distribution unit is used for providing power supply and protection functions for all aircraft equipment which does not need to be switched on and off;
the switch type equipment power distribution unit is used for providing power supply and protection functions for all airplane equipment needing to be switched;
the monitoring unit is used for collecting all detection quantities including switching state quantity, voltage and current;
the data processing unit is used for processing and forwarding all the quantities detected by the monitoring unit;
the data recording unit is used for storing all the data processed by the data processing unit;
and the bus interface is used for electrically coupling the load monitoring unit with the flight control computer.
7. The power management system based on the manned and unmanned modification is characterized in that the flight control computer provides switching judgment for the switching equipment on the airplane and realizes on-off control of the switching equipment by sending instructions to the load unit.
8. The system of claim 1, wherein the flight control computer receives the power supply condition of the aircraft device detected by the load monitoring unit, and determines, forwards and stores the power supply condition.
9. The system of claim 8, wherein when the flight control computer determines that the power supply condition of the aircraft device is not satisfactory, the flight control computer immediately sends an alarm to the load monitoring unit and turns off the power supply of the defective device when determining that the detection signal is defective.
10. The power management system based on manned and unmanned modification of any one of claims 1-9, wherein the power management system is of an application model of AT200 unmanned aerial vehicle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010512702.3A CN111682644A (en) | 2020-06-08 | 2020-06-08 | Power management system based on manned and unmanned modification |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010512702.3A CN111682644A (en) | 2020-06-08 | 2020-06-08 | Power management system based on manned and unmanned modification |
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| Publication Number | Publication Date |
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| CN111682644A true CN111682644A (en) | 2020-09-18 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202010512702.3A Pending CN111682644A (en) | 2020-06-08 | 2020-06-08 | Power management system based on manned and unmanned modification |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2022183659A1 (en) * | 2021-03-02 | 2022-09-09 | 广东汇天航空航天科技有限公司 | Switching circuit, switching circuit control method, and aircraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203111521U (en) * | 2013-01-15 | 2013-08-07 | 中国航空工业集团公司西安飞机设计研究所 | Four-channel aircraft power supply system information synthesis configuration |
| CN104659900A (en) * | 2013-11-25 | 2015-05-27 | 中国直升机设计研究所 | Power supply system of unmanned helicopter |
| CN109038535A (en) * | 2017-06-08 | 2018-12-18 | 北京德知航创科技有限责任公司 | Unmanned plane Distribution Management System |
| CN110884657A (en) * | 2018-12-21 | 2020-03-17 | 苏州律点信息科技有限公司 | Unmanned aerial vehicle power control system |
-
2020
- 2020-06-08 CN CN202010512702.3A patent/CN111682644A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203111521U (en) * | 2013-01-15 | 2013-08-07 | 中国航空工业集团公司西安飞机设计研究所 | Four-channel aircraft power supply system information synthesis configuration |
| CN104659900A (en) * | 2013-11-25 | 2015-05-27 | 中国直升机设计研究所 | Power supply system of unmanned helicopter |
| CN109038535A (en) * | 2017-06-08 | 2018-12-18 | 北京德知航创科技有限责任公司 | Unmanned plane Distribution Management System |
| CN110884657A (en) * | 2018-12-21 | 2020-03-17 | 苏州律点信息科技有限公司 | Unmanned aerial vehicle power control system |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2022183659A1 (en) * | 2021-03-02 | 2022-09-09 | 广东汇天航空航天科技有限公司 | Switching circuit, switching circuit control method, and aircraft |
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Application publication date: 20200918 |