CN210297322U - Unmanned aerial vehicle machine carries power management device - Google Patents
Unmanned aerial vehicle machine carries power management device Download PDFInfo
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- CN210297322U CN210297322U CN201921677177.XU CN201921677177U CN210297322U CN 210297322 U CN210297322 U CN 210297322U CN 201921677177 U CN201921677177 U CN 201921677177U CN 210297322 U CN210297322 U CN 210297322U
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02E60/10—Energy storage using batteries
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Abstract
The application discloses unmanned aerial vehicle machine carries power management device, the device includes: the power supply comprises a shell, a printed circuit board and a power supply, wherein the printed circuit board and the power supply are fixed in the shell; the shell comprises a power management device shell and a battery shell, and the power management device shell and the battery shell are separable structures; the printed circuit board fixed in the shell is arranged on the shell of the power management device and comprises a power management module and a control circuit; the power supply comprises a battery, a heating circuit, a heating sheet and a charging control panel; the heating circuit, the heating sheet and the charging control board are arranged on the battery. The utility model provides an airborne power supply management device only needs to change the battery part, has saved cost of maintenance.
Description
Technical Field
The utility model relates to a power management technical field, concretely relates to unmanned aerial vehicle machine carries power management device.
Background
A power Management unit (pmu) is a highly centralized and portable power Management solution. The device is integrated in a single package, so that higher battery conversion efficiency, lower power consumption and fewer components are realized to adapt to reduced board level space. PMU provides reliable and stable power supply for each subassembly of unmanned aerial vehicle, obtains more and more extensive use in the unmanned aerial vehicle product, helps reducing entire system's consumption to through reducing the energy consumption of subassembly when idle, make the unmanned aerial vehicle battery can have longer live time. The interface that is connected with external equipment is integrated on the printed circuit board in the PMU, is equipped with the interface aviation plug that corresponds with the interface on the PMU casing.
In the existing power management device, a power management part is separated from an emergency power supply (battery), and the structure is required to be dismantled for battery maintenance. After the battery is charged and maintained, the battery is assembled, so that the size is large, and the maintenance cost is high.
SUMMERY OF THE UTILITY MODEL
In view of the above-mentioned defect or not enough among the prior art, it is expected to provide an unmanned aerial vehicle machine carries power management device, can reduce the space and occupy, more is applicable to on the unmanned aerial vehicle.
In a first aspect, the utility model provides an unmanned aerial vehicle machine carries power management device, the device includes:
the power supply, the shell and the printed circuit board fixed in the shell;
the shell comprises a power management device shell and a battery shell, and the power management device shell and the battery shell are separable structures;
the printed circuit board fixed in the shell is arranged on the shell of the power management device and comprises a power management module and a control circuit;
the power supply comprises a battery, a heating circuit, a heating sheet and a charging control panel; the heating circuit, the heating sheet and the charging control board are arranged on the battery.
Optionally, the apparatus further comprises: emergency standby power supply equipment;
the emergency standby power supply equipment is electrically connected with the power supply conversion module.
Optionally, the power management module in the apparatus includes: the device comprises a power conversion module, an output monitoring module, a battery management module and a microprocessor;
the power conversion module is electrically connected with the input power supply;
one end of the output monitoring module is electrically connected with the servo actuating system, the main equipment and the load equipment respectively;
the microprocessor is electrically connected with the flight control computer;
the battery management module is electrically connected with the microprocessor;
optionally, the input power supply includes: ground direct current power supply, airborne generator direct current power supply and emergency direct current power supply.
The utility model provides an airborne power management device, simple structure has broken through current power management device the control unit and has separately designed with the battery. The power management device and a circuit part for charging and discharging the battery are designed in a unified mode, so that the whole design is compact. And the shell of the battery part is separately designed, so that the shell is convenient to process, the shell of the whole machine does not need to be replaced when the battery and the heating plate which are used for a long time are replaced, and only the battery part needs to be replaced, so that the maintenance cost is saved.
Drawings
Other features, objects and advantages of the present application will become more apparent upon reading of the following detailed description of non-limiting embodiments thereof, made with reference to the accompanying drawings in which:
fig. 1 is a schematic structural diagram of an airborne power management device of an unmanned aerial vehicle according to an embodiment of the present invention;
fig. 2 is a schematic structural diagram of a system architecture of an onboard power management device of an unmanned aerial vehicle according to an embodiment of the present invention;
fig. 3 is a schematic structural diagram of a power management module according to an embodiment of the present invention;
fig. 4 is a schematic structural diagram of an emergency power module according to an embodiment of the present invention.
In the figure, 1-battery shell, 2-power management device shell, 3-printed circuit board, 4-power management module, 5-control circuit, 6-power supply, 7-battery, 8-heating circuit, 9-heating sheet and 10-charging control board.
Detailed Description
The present application will be described in further detail with reference to the following drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the relevant invention and not restrictive of the invention. It should be noted that, for convenience of description, only the portions related to the present invention are shown in the drawings.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.
In the description of the present invention, the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "inner", "outer", etc. indicate orientations or positional relationships illustrated in the drawings, and are only for convenience of description of the present invention, and do not indicate or imply that the device or element referred to must have a particular orientation, and therefore, should not be construed as limiting the scope of the present invention.
In the description of the present invention, it should be noted that unless otherwise specified and limited, the terms "connected" and "connected" should be interpreted broadly, such as for example as a fixed connection, but also as an integral connection; may be directly connected or indirectly connected through an intermediate. The specific meaning of the above terms in the present invention can be specifically understood by those skilled in the art.
In the existing battery management device, a power management part is separated from an emergency power supply (battery), and the structure is required to be dismantled for battery maintenance. After the battery is charged and maintained, the battery is assembled, so that the size is large and the maintenance cost is high.
The embodiment of the utility model provides a based on prior art's defect, designed integral type machine and carried power management device, be convenient for on the less unmanned aerial vehicle of installation volume. The battery charging can be completed under the condition that the battery is not disassembled, and the voltage and current sampling is carried out on the three paths of input voltages. The power management system can manage the power and provide an emergency power, and adopts a design of being in a same shape with a machine body so as to reduce the installation volume. The two modules are interconnected through cables and connectors and are installed in a power supply cabin of the airplane.
In a first aspect, the utility model provides an airborne power management device for an unmanned aerial vehicle, which comprises a power supply, a shell and a printed circuit board fixed in the shell;
the shell comprises a power management device shell and a battery shell, and the power management device shell and the battery shell are separable structures; the printed circuit board fixed in the shell is arranged on the shell of the power management device and comprises a power management module and a control circuit;
the power supply comprises a battery, a heating circuit, a heating sheet and a charging control panel; the heating circuit, the heating sheet and the charging control board are arranged on the battery.
Specifically, figure 1 is the utility model discloses an unmanned aerial vehicle machine carries power management device's schematic structure diagram of embodiment. This unmanned aerial vehicle machine carries power management device's structure can include two-layer shell, battery case 1 and power management device shell 2, includes printed circuit board 3 and power 6 in power management device shell 2. The power supply 6 includes a battery 7, and a heating circuit 8, a heating sheet 9, and a charging control board 10 provided on the battery 7.
Optionally, the unmanned aerial vehicle machine carries power management device that this application embodiment provided still includes: emergency standby power supply equipment; the emergency standby power supply equipment is electrically connected with the power supply conversion module. Referring to fig. 2, it is a schematic structural diagram of a power management module according to an embodiment of the present invention.
Optionally, the unmanned aerial vehicle machine carries power management device that this application embodiment provided still includes: the power management module includes: the device comprises a power conversion module, an output monitoring module, a battery management module and a microprocessor; the power conversion module is electrically connected with the input power supply; one end of the output monitoring module is electrically connected with the servo actuating system, the main equipment and the load equipment respectively; the microprocessor is electrically connected with the flight control computer; the battery management module is electrically connected with the microprocessor.
Specifically, under normal operating conditions, the radio station on the flight control computer can open the emergency power switch through the instruction, and at this moment, the emergency power is in the exportable state, guarantees to provide the required emergency power of flight. After the flight is finished, the flight control computer can close the end emergency power switch through the instruction, and emergency power output is turned off, and no power output exists, so that the emergency power can not be over-discharged.
It can be understood that a microprocessor is designed in the power management module, and the processor is responsible for the functions of input power state signal acquisition, output power state signal acquisition, emergency power management, communication between the power management module and the flight control computer and the like. The microprocessor can report the power state to the flight control computer through the RS232 communication interface, and can also receive the instruction issued by the flight control computer through the communication interface. And the microprocessor controls the on-off of the emergency power supply, the charging of the emergency power supply, the on-off of the load power supply and the like according to the instruction of the flight control computer.
Optionally, the input power supply includes: ground direct current power supply, airborne generator direct current power supply and emergency direct current power supply. Referring to fig. 3, it is a schematic diagram of a functional structure of a power management module according to an embodiment of the present invention.
Specifically, the power management module can complete 3 input power sources: input monitoring of the ground DC power supply DC28V, the on-board generator DC28V, and the emergency DC power supply DC25.9V. The three input power sources can be automatically switched, and the on-board generator direct-current power source DC28V and the on-board generator direct-current power source DC56V are switched to output. The output monitoring module is responsible for output monitoring of two power supplies (DC28V and DC 56V). The battery management module can be communicated with the flight control computer, and the microprocessor is electrically connected with the flight control computer.
It can be understood that the work flow of power management may be that the dc power is first monitored for input, and after switching and converting the circuit, the circuit is used to monitor the input power. And judging whether any path has a fault according to the voltage state of the input direct current power supply, and carrying out turn-off processing on the input power supply with the fault. The switching of the power supply is carried out according to the sequence of the ground power supply, the generator power supply and the emergency power supply, and the priority is from high to low. First, a power supply with a high priority is used, and when the power supply with the high priority "fails", the switching circuit selects an input power supply with the next priority and outputs the selected input power supply to the subsequent circuit.
The input direct current power supply is sent to the post-stage power supply conversion circuit for power supply conversion after passing through the monitoring and switching circuit. The power supply conversion circuit adopts a DC-DC conversion technology, and can output two paths of direct current power supplies for later-stage equipment.
Referring to fig. 4, it is a schematic structural diagram of an emergency power module according to an embodiment of the present invention.
When the ground power supply is not available and the power supply of the generator is abnormal, the power supply management module cuts off the power supply of the generator, and an emergency power supply is needed to supply power.
The emergency power supply module is responsible for providing an emergency power supply, and the module can complete functions of storage battery charging and discharging management, storage battery temperature control and the like. The storage battery can adopt 7 strings of lithium polymer batteries, and the single storage battery is 3.7@15 AH. The nominal voltage of the assembled storage battery is 25.9V, the full rush voltage is 29.4V, and the minimum discharge protection voltage is 18.9V. Under the condition that ground power supplies power, the emergency power supply module can adopt the ground power to charge the storage battery, and the storage battery charging and discharging tube is finished by the charging and discharging protection circuit.
The normal working process of the emergency power supply module is as follows: under normal conditions, a power supply is input into the power supply management module. Respectively a ground power supply, a generator power supply and an emergency power supply. The power supplies are P1 (ground power supply), P2 (generator power supply), P3 (emergency power supply) from high to low in priority, and the three power supplies can be switched seamlessly from high to low in priority. A high level power supply is preferably used as an input. When the ground power supply at the input port of the power supply management module is disconnected, the input power supply is switched to the power supply of the generator; when the power supply of the generator at the input port of the power management module is disconnected, the input power supply is switched to use an emergency power supply.
And when the power is on in the initial state, the emergency power supply is in a disconnected state in the default state. The engine is first started using a ground power supply that simultaneously supplies power to the back-end devices via a power management module. And starting the flight control computer in the rear-stage equipment, and sending a control instruction to the on-off switch of the storage battery channel to switch on the storage battery channel. After the engine is started stably, the engine drives the generator to generate electricity. When the flight test starts, the ground power supply is removed, and at the moment, the input power supply of the power management module is switched to the power supply of the generator, so that the power supply of the subsequent test is ensured. And when the normal flight test is finished, the flight control computer sends a shutdown instruction to the engine and sends a 'turn-off' instruction to the on-off switch of the storage battery channel, and the test is finished.
If an abnormal condition occurs, the following processing can be carried out: if the engine is stopped during flight, the generator has no power output. And at the moment, the input power supply of the power supply management module is switched to the storage battery, and meanwhile, the flight control computer monitors the power supply fault reported by the power supply module and judges that the fault reason is that the generator has no power supply to output according to the fault code. At the moment, the flight control computer sends a load power supply turn-off control instruction to cut off the power supply of the load equipment, then follow-up landing and other processes are executed, after landing, the flight control computer sends a turn-off instruction to the on-off switch of the storage battery channel to cut off the power supply of the storage battery, and the test is finished.
The technical scheme of the utility model beneficial effect lies in: the input power supply is accurately monitored and switched in real time, secondary power supply conversion is completed, the communication with the master control equipment is realized, and the emergency power supply is managed. The power management module and the emergency storage battery module are independent design modules, and the convenient maintenance testability of the independent modules is fully considered during design.
The above description is only a preferred embodiment of the application and is illustrative of the principles of the technology employed. It will be appreciated by a person skilled in the art that the scope of the invention as referred to in the present application is not limited to the embodiments with a specific combination of the above-mentioned features, but also covers other embodiments with any combination of the above-mentioned features or their equivalents without departing from the inventive concept. For example, the above features may be replaced with (but not limited to) features having similar functions disclosed in the present application.
Claims (4)
1. An unmanned aerial vehicle machine carries power management device, its characterized in that, the device includes:
the power supply, the shell and the printed circuit board fixed in the shell;
the shell comprises a power management device shell and a battery shell, and the power management device shell and the battery shell are separable structures;
the printed circuit board fixed in the shell is arranged on the shell of the power management device and comprises a power management module and a control circuit;
the power supply comprises a battery, a heating circuit, a heating sheet and a charging control panel; the heating circuit, the heating sheet and the charging control board are arranged on the battery.
2. The apparatus of claim 1, further comprising: emergency standby power supply equipment;
the emergency standby power supply equipment is electrically connected with the power supply conversion module.
3. The apparatus of claim 1, wherein:
the power management module includes: the device comprises a power conversion module, an output monitoring module, a battery management module and a microprocessor;
the power conversion module is electrically connected with the input power supply;
one end of the output monitoring module is electrically connected with the servo actuating system, the main equipment and the load equipment respectively;
the microprocessor is electrically connected with the flight control computer;
the battery management module is electrically connected with the microprocessor.
4. The apparatus of claim 3, wherein: the input power supply includes: ground direct current power supply, airborne generator direct current power supply and emergency direct current power supply.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921677177.XU CN210297322U (en) | 2019-10-09 | 2019-10-09 | Unmanned aerial vehicle machine carries power management device |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201921677177.XU CN210297322U (en) | 2019-10-09 | 2019-10-09 | Unmanned aerial vehicle machine carries power management device |
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| CN210297322U true CN210297322U (en) | 2020-04-10 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112201878A (en) * | 2020-09-11 | 2021-01-08 | 中国航空工业集团公司成都飞机设计研究所 | Ground and air combined heating method for lithium ion battery of airplane |
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2019
- 2019-10-09 CN CN201921677177.XU patent/CN210297322U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112201878A (en) * | 2020-09-11 | 2021-01-08 | 中国航空工业集团公司成都飞机设计研究所 | Ground and air combined heating method for lithium ion battery of airplane |
| CN112201878B (en) * | 2020-09-11 | 2023-07-21 | 中国航空工业集团公司成都飞机设计研究所 | Heating method for combining ground and air of lithium ion battery of airplane |
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