CN219313058U - Unmanned aerial vehicle distribution device and terminal equipment - Google Patents

Abstract

The utility model relates to the technical field of aviation electricity and discloses an unmanned aerial vehicle power distribution device and terminal equipment. This unmanned aerial vehicle power distribution device includes: the device comprises a power supply module, an acquisition module, a communication interface, a control module and a control interface module; the unmanned aerial vehicle power distribution device is connected with the unmanned aerial vehicle through the communication interface, and is connected with a plurality of electric equipment in the unmanned aerial vehicle through the control interface module; the control module is respectively connected with the communication interface, the control interface module, the power supply module and the acquisition module; the power module, the acquisition module and the control interface module are sequentially connected. The self-adaptive power supply capacity of the unmanned aerial vehicle power distribution device is effectively improved.

Description

Unmanned aerial vehicle distribution device and terminal equipment

Technical Field

The utility model relates to the technical field of aviation electrical, in particular to an unmanned aerial vehicle power distribution device and terminal equipment.

Background

Along with unmanned aerial vehicle's application is more and more extensive, especially unmanned aerial vehicle logistics distribution and the appearance of manned trip mode all impels each big unmanned aerial vehicle enterprise to accelerate to mix and move unmanned aerial vehicle overall arrangement, carries out the research and development of middle-size large-scale pure electric and mixed unmanned aerial vehicle on schedule, this has put forward higher requirement to unmanned aerial vehicle distribution device's self-adaptation power supply ability.

At present, the weight of the unmanned aerial vehicle directly influences the carrying capacity and the cruising ability of the aircraft, so that the unmanned aerial vehicle has strict requirements on the weight and the size of each device. As the flight control computer of unmanned aerial vehicle core equipment, receive weight and size restriction equally, output control signal port quantity is limited, however, current unmanned aerial vehicle power supply device does not consider how to practice thrift flight control computer's interface resource, its self-adaptation power supply capacity has very big defect, most unmanned aerial vehicle power supply device only is applicable to pure unmanned aerial vehicle power supply system, only supply power through single lithium cell group, and carry out power supply control to avionics through flight control computer's signal generally, and then the holistic control signal of unmanned aerial vehicle is not enough problem has been caused. In addition, because the data transmission, the image transmission, the automatic driving, the video and other electric equipment in the unmanned aerial vehicle have multiple power supply demands, in other words, different electric equipment in the unmanned aerial vehicle have different power supply demands, the existing unmanned aerial vehicle power supply device cannot output various voltage systems, and further cannot meet the power supply demands of all the electric equipment in the unmanned aerial vehicle, and cannot detect the voltage and the current output to the electric equipment, so that whether the output voltage and the current are abnormal or not cannot be judged.

In summary, the existing unmanned aerial vehicle power supply device has the technical problem of poor adaptive power supply capability.

Disclosure of Invention

The utility model mainly aims to provide an unmanned aerial vehicle power distribution device and terminal equipment, and aims to improve the self-adaptive power supply capacity of the unmanned aerial vehicle power distribution device.

To achieve the above object, the present utility model provides an unmanned aerial vehicle power distribution device, including: the device comprises a power supply module, an acquisition module, a communication interface, a control module and a control interface module;

the unmanned aerial vehicle power distribution device is connected with the unmanned aerial vehicle through the communication interface, and is connected with a plurality of electric equipment in the unmanned aerial vehicle through the control interface module;

the control module is respectively connected with the communication interface, the control interface module, the power supply module and the acquisition module;

the power module, the acquisition module and the control interface module are sequentially connected.

Optionally, the unmanned aerial vehicle includes: a generator power supply and an avionic battery;

the generator power supply and the avionics battery are respectively connected with the power supply module and used for providing required voltage for each electric equipment, wherein the required voltage refers to input voltage corresponding to each electric equipment.

Optionally, the power module includes: the device comprises an input power acquisition unit, a parallel power unit, a secondary power conversion unit and an output switch unit;

the input power supply acquisition unit is connected with the secondary power supply conversion unit through the parallel power supply unit;

the input power supply acquisition unit is connected with the output switch unit.

Optionally, the input power supply acquisition unit includes: the device comprises a first current sensor, a second current sensor, a generator power supply filtering subunit and an avionics battery filtering subunit;

the generator power supply filtering subunit is connected with the first current sensor, and the avionics battery filtering subunit is connected with the second current sensor.

Optionally, the parallel electric unit includes a first diode combination circuit and a second diode combination circuit, wherein the first diode combination circuit and the second diode combination circuit are the same.

Optionally, the first diode combining circuit includes: a first diode and a second diode;

the anode of the first diode is connected with the anode of the second diode, and the cathode of the first diode is connected with the cathode of the second diode.

Optionally, the secondary power conversion unit includes: the first resistor, the second resistor, the first capacitor, the second capacitor, the third capacitor, the inductor and the secondary power supply conversion subunit;

the first end of the first capacitor is connected with the first end of the inductor, the second end of the inductor is connected with the first end of the second capacitor, and the second end of the first capacitor is respectively grounded with the second end of the second capacitor;

the junction of the second end of the inductor and the first end of the second capacitor is connected with the first end of the secondary power conversion subunit;

the second end of the secondary power supply conversion subunit is connected with the first end of the first resistor;

the intersection point of the second end of the first resistor and the first end of the second resistor is connected with the third end of the secondary power conversion subunit respectively;

the connection terminal between the second end of the second resistor and the second end of the third capacitor is grounded.

Optionally, the output switch unit includes: the third resistor, the fourth resistor, the fifth resistor, the fourth capacitor and the switch subunit;

the first end of the switch subunit is connected with the third resistor, the intersection point of the connection of the fourth resistor and the fifth resistor is connected with the second end of the switch subunit, and the fourth resistor is connected with the fourth capacitor;

the fourth capacitor is grounded, and the fifth resistor is grounded.

Optionally, the switch subunit is a high-side switch, a relay or an MOS transistor.

In addition, to achieve the above purpose, the present utility model also provides a terminal device, which includes the unmanned aerial vehicle power distribution device as described in any one of the above.

The unmanned aerial vehicle power distribution device of the utility model comprises: the device comprises a power supply module, an acquisition module, a communication interface, a control module and a control interface module; the unmanned aerial vehicle power distribution device is connected with the unmanned aerial vehicle through a communication interface, and is connected with a plurality of electric equipment in the unmanned aerial vehicle through a control interface module; the control module is respectively connected with the communication interface, the control interface module, the power module and the acquisition module; the power module, the acquisition module and the control interface module are connected in sequence.

The unmanned aerial vehicle power distribution device is different from a traditional unmanned aerial vehicle power supply device mode, and after the unmanned aerial vehicle power distribution device is connected with a flight control computer in an unmanned aerial vehicle through a communication interface, the unmanned aerial vehicle power distribution device can further perform power distribution control on a plurality of electric equipment in the unmanned aerial vehicle, and interface resources of the flight control computer are effectively saved. And then the unmanned aerial vehicle power distribution device is connected with a plurality of electric equipment in the unmanned aerial vehicle through the control interface module, namely, the control interface module outputs a plurality of power supply voltages which respectively correspond to the electric equipment in the unmanned aerial vehicle, so that the technical problem that the conventional unmanned aerial vehicle power distribution device cannot output a plurality of voltage systems is effectively solved, and the self-adaptive power supply capacity of the unmanned aerial vehicle power distribution device is further improved.

Drawings

FIG. 1 is a schematic view of an embodiment of a power distribution device for a drone of the present utility model;

FIG. 2 is a functional block diagram of a drone power distribution apparatus of the present utility model;

FIG. 3 is a block diagram of a system involved in the unmanned aerial vehicle power distribution apparatus of the present utility model;

fig. 4 is a schematic circuit diagram of an input power collection unit in the unmanned aerial vehicle power distribution device of the present utility model;

fig. 5 is a schematic circuit diagram of a secondary power conversion unit in the unmanned aerial vehicle power distribution device of the present utility model;

fig. 6 is a schematic circuit diagram of an output switching unit in the unmanned aerial vehicle power distribution device of the present utility model.

Reference numerals illustrate:

reference numerals	Name of the name	Reference numerals	Name of the name
				10	Unmanned aerial vehicle distribution device	A10	Power supply module
A20	Acquisition module	A30	Communication interface
				A40	Control module	A50	Control interface module
20	Unmanned plane	201	Electric equipment
				A101	Input power supply acquisition unit	A102	Parallel electric unit
A103	Secondary power supply conversion unit	A104	Output switch unit
				A1011	First current sensor	A1012	Second current sensor
A1013	Generator power supply filtering subunit	A1014	Avionics battery filtering subunit
				R1	First resistor	R2	Second resistor
C1	First capacitor	C2	Second capacitor
				C3	Third capacitor	L	Inductance
A1031	Secondary power supply conversion subunit	R3	Third resistor
				R4	Fourth resistor	R5	Fifth resistor
C4	Fourth capacitor	D1	First diode
				D2	Second diode

The achievement of the objects, functional features and advantages of the present utility model will be further described with reference to the accompanying drawings, in conjunction with the embodiments.

Detailed Description

It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the present application.

The following description of the embodiments of the present application will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are only some, but not all, of the embodiments of the present application. All other embodiments, which can be made by one of ordinary skill in the art based on the embodiments herein without making any inventive effort, are intended to be within the scope of the present application.

It should be noted that all directional indicators (such as up, down, left, right, front, and rear … …) in the embodiments of the present application are merely used to explain the relative positional relationship, movement, etc. between the components in a specific posture (as shown in the drawings), and if the specific posture is changed, the directional indicator is correspondingly changed.

In the present application, unless explicitly specified and limited otherwise, the terms "coupled," "secured," and the like are to be construed broadly, and for example, "secured" may be either permanently attached or removably attached, or integrally formed; can be mechanically or electrically connected; either directly or indirectly, through intermediaries, or both, may be in communication with each other or in interaction with each other, unless expressly defined otherwise. The specific meaning of the terms in this application will be understood by those of ordinary skill in the art as the case may be.

In addition, descriptions such as those related to "first," "second," and the like, are provided for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated in this application. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include at least one such feature. In addition, the technical solutions of the embodiments may be combined with each other, but it is necessary to base that the technical solutions can be realized by those skilled in the art, and when the technical solutions are contradictory or cannot be realized, the combination of the technical solutions should be regarded as not exist and not within the protection scope of the present application.

The utility model provides an unmanned aerial vehicle power distribution device.

In an embodiment of the present utility model, referring to fig. 1, fig. 1 is a schematic structural diagram of an embodiment of a unmanned aerial vehicle power distribution device 10 of the present utility model, where the unmanned aerial vehicle power distribution device 10 includes: the device comprises a power supply module A10, an acquisition module A20, a communication interface A30, a control module A40 and a control interface module A50;

the unmanned aerial vehicle power distribution device 10 is connected with the unmanned aerial vehicle 20 through the communication interface A30, and the unmanned aerial vehicle power distribution device 10 is connected with a plurality of electric equipment 201 in the unmanned aerial vehicle 20 through a control interface module A50;

in this embodiment, the unmanned aerial vehicle power distribution device 10 is connected with the flight control computer in the unmanned aerial vehicle 20 through the communication interface a30, and then the control interface module a50 can be directly controlled through the unmanned aerial vehicle power distribution device 10, then the unmanned aerial vehicle power distribution device 10 can be connected with a plurality of electric devices 201 in the unmanned aerial vehicle 20 through the control interface module a50, in addition, the unmanned aerial vehicle power distribution device 10 can also be connected with a plurality of electric devices 201 through the control interface module a 50.

Note that the communication interface a30 includes, but is not limited to, a CAN bus communication interface, an RS232 communication interface, an RS422 communication interface, and an RS458 communication interface. For example, the unmanned aerial vehicle power distribution device 10 of the present utility model communicates with the flight control computer in the unmanned aerial vehicle 20 through the CAN bus communication interface, in other words, the unmanned aerial vehicle power distribution device 10 and the flight control computer communicate by using the CAN bus, where the CAN bus has the advantages of long transmission distance, strong interference immunity, high transmission speed, many connection nodes, and the like. Then control interface module A50 (i.e., output control port) is controlled according to unmanned aerial vehicle distribution device, has reduced the use quantity of flight control computer interface in unmanned aerial vehicle 20, avoids changing the flight control computer because of interface quantity problem, has reduced research and development cost and cycle.

The control interface module a50 includes, but is not limited to, a power input interface, a primary power interface, and a secondary power interface. The power input interface, the communication control interface, the primary power interface and the secondary power interface are respectively connected with the connectors corresponding to each other, in other words, the unmanned aerial vehicle power distribution device is provided with 4 independent connectors, so that the power input interface, the communication control interface, the primary power interface and the secondary power interface are divided, the technical problem that the conventional unmanned aerial vehicle power distribution device does not divide the interfaces for the output of various voltage systems is effectively solved, and the cable crosslinking in the system is reduced.

The control module A40 is respectively connected with the communication interface A30, the control interface module A50, the power supply module and the acquisition module;

in this embodiment, referring to fig. 2, fig. 2 is a functional block diagram of the unmanned aerial vehicle power distribution apparatus according to the present utility model. The control module A40 is respectively in communication connection with the communication interface A30, the control interface module A50, the power supply module A10 and the acquisition module A20.

It should be noted that the control module a40 includes, but is not limited to, an MCU microprocessor, an ARM processor, an FPGA programmable logic device, and an X86 processor.

The acquisition module a20 includes an output power acquisition unit, configured to acquire an adaptive power source corresponding to each electric device, for example, DC24V, DC V and DC8V.

The power module A10, the acquisition module A20 and the control interface module A50 are sequentially connected.

In this embodiment, referring to fig. 2, the power module a10, the acquisition module a20, and the control interface module a50 are sequentially connected in communication.

In summary, the unmanned aerial vehicle power distribution device of the present utility model includes: the device comprises a power supply module A10, an acquisition module A20, a communication interface A30, a control module A40 and a control interface module A50; the unmanned aerial vehicle power distribution device is connected with the unmanned aerial vehicle through a communication interface A30, and is connected with a plurality of electric equipment in the unmanned aerial vehicle through a control interface module A50; the control module A40 is respectively connected with the communication interface A30, the control interface module A50, the power supply module A10 and the acquisition module A20; the power module A10, the acquisition module A20 and the control interface module A50 are sequentially connected.

The unmanned aerial vehicle power distribution device is different from a traditional unmanned aerial vehicle power supply device mode, and after the unmanned aerial vehicle power distribution device is connected with a flight control computer in an unmanned aerial vehicle through a communication interface A30, the unmanned aerial vehicle power distribution device can further perform power distribution control on a plurality of electric equipment in the unmanned aerial vehicle, and interface resources of the flight control computer are effectively saved. And then the unmanned aerial vehicle power distribution device is connected with a plurality of electric equipment in the unmanned aerial vehicle through the control interface module A50, namely, the control interface module A50 outputs a plurality of power supply voltages which meet respective corresponding requirements of each electric equipment in the unmanned aerial vehicle, so that the technical problem that the conventional unmanned aerial vehicle power distribution device cannot output a plurality of voltage systems is effectively solved, and the self-adaptive power supply capacity of the unmanned aerial vehicle power distribution device is further improved.

Further, in still another embodiment of the unmanned aerial vehicle power distribution device of the present utility model, the unmanned aerial vehicle 20 includes: a generator power supply and an avionic battery;

the generator power supply and the avionics battery are respectively connected with the power supply module a10 and are used for providing a required voltage for each electric equipment 201, wherein the required voltage refers to an input voltage corresponding to each electric equipment 201.

In this embodiment, the power module a10 further includes a dual power input interface, i.e. a first power input interface and a second power input interface, wherein the voltage provided by the generator power is input to the power module a10 through the first power input interface, and the voltage provided by the avionics battery is input to the power module a10 through the second power input interface.

In the embodiment, after the generator power supply and the avionic battery are provided to the power supply module A10 by adopting the dual power input interface, the filtering treatment is respectively carried out on the generator power supply and the avionic battery in the power supply module A10, and then the filtering treatment is input through the parallel power unit, so that the technical problems that the traditional unmanned aerial vehicle power supply device only supports the power supply of a pure battery system and the cruising ability is poor are effectively solved, and the power distribution requirement of the hybrid composite wing unmanned aerial vehicle power supply system on the airborne electric equipment is met.

Further, in some possible embodiments, the power module a10 includes: an input power acquisition unit A101, a parallel power unit A102, a secondary power conversion unit A103 and an output switch unit A104;

the input power acquisition unit A101 is connected with the secondary power conversion unit A103 through the parallel power unit A102;

in this embodiment, referring to fig. 3, fig. 3 is a system block diagram related to the unmanned aerial vehicle power distribution apparatus of the present utility model. The input power supply acquisition unit A101 is connected with the parallel electric unit A102 to form an avionics bus bar, wherein external key equipment in the unmanned aerial vehicle is powered through the avionics bus bar or the external key electric equipment is directly powered. In addition, the input power acquisition unit A101 can also be connected with the secondary power conversion unit A103 through the parallel power unit A102 to form a secondary power bus bar, wherein the secondary power bus bar is used for directly supplying power to electric equipment in the unmanned aerial vehicle or directly supplying power to external electric equipment.

It should be noted that the input power source acquisition unit a101 may include a first current sensor a1011, a second current sensor a1012, a generator power source filtering subunit a1013, and an avionics battery filtering subunit a1014.

In a specific embodiment, avionics power is provided by an avionics bus bar, referring to fig. 4, fig. 4 is a schematic circuit diagram related to an input power collection unit of the unmanned aerial vehicle power distribution device according to the present utility model, where generator power input through a first power input interface is filtered by a generator power filtering subunit a1013, then flows through a first current sensor a1011 to monitor the generator power, and then is input through a parallel power unit a 102; in addition, after the avionics battery input through the second power input interface is filtered through the avionics battery filtering subunit a1014, the avionics battery is monitored through the second current sensor a1012, and then input through the parallel unit a102, wherein the input of the avionics power through the parallel unit can be understood as the sum of the voltages of the generator power supply and the avionics battery; it is also understood to include only the voltage provided by the avionics battery (i.e., the generator is not operating).

The input power acquisition unit A101 is connected with the output switch unit A104.

In this embodiment, the generator power supply inputs the voltage provided by the generator power supply to the input power supply acquisition unit a101 through the first power supply input interface for filtering processing, and then inputs the voltage to the output switch unit a104, that is, the generator power supply is connected with the output switch unit a104 through the input power supply acquisition unit a101 to form a main bus bar, wherein the power is directly supplied to general electric equipment in the unmanned aerial vehicle or is directly supplied to external general electric equipment through the main bus bar.

In this embodiment, the bus bar design mode is adopted in the utility model, and the bus bar design mode is divided into a main bus bar, an avionics battery bus bar, a secondary power bus bar and the like, wherein the main bus bar supplies power to general equipment or load equipment, and the avionics battery bus bar supplies power to key equipment. When the generator stops working, the unmanned aerial vehicle power distribution device automatically cuts off the power supply of the main bus bar through the output switch unit A104, and a flight control computer in the unmanned aerial vehicle is not needed to participate in control, so that the complexity of the system is reduced, the electric quantity is saved, and the flight time is increased.

Further, in other possible embodiments, the input power acquisition unit a101 includes: a first current sensor a1011, a second current sensor a1012, a generator power filtering subunit a1013, and an avionics battery filtering subunit a1014;

the generator power filtering subunit a1013 is connected to the first current sensor a1011, and the avionics battery filtering subunit a1014 is connected to the second current sensor a 1012.

The first current sensor a1011 and the second current sensor a1012 refer to a detection device. In this embodiment, the first current sensor a1011 and the second current sensor a1012 perform overcurrent early warning protection on the unmanned aerial vehicle power distribution device 10, so that the safety of the unmanned aerial vehicle power distribution device 10 is further improved.

Further, in some possible embodiments, the parallel power unit a102 includes a first diode combination and a second diode combination, wherein the first diode combination and the second diode combination are the same.

In the embodiment, the utility model adopts a diode combination way to support the simultaneous power supply of the avionic battery and the generator, so that the endurance time of the unmanned aerial vehicle is longer, and the reliability of the system is further improved.

It should be noted that, the present utility model adopts diode combination (i.e., the first diode combination and the second diode combination) for the power input of the avionics battery and the generator, and may also use MOS transistors or integrated circuits for replacement.

Further, in other possible embodiments, the first diode combination includes: a first diode D1 and a second diode D2;

the anode of the first diode D1 is connected with the anode of the second diode D2, and the cathode of the first diode D1 is connected with the cathode of the second diode D2.

Further, in some possible embodiments, the secondary power conversion unit a103 includes: the first resistor R1, the second resistor R2, the first capacitor C1, the second capacitor C2, the third capacitor C3, the inductor L and the secondary power conversion subunit A1031;

the first end of the first capacitor C1 is connected with the first end of the inductor L, the second end of the inductor L is connected with the first end of the second capacitor C2, and the second end of the first capacitor C1 is respectively grounded with the second end of the second capacitor C2;

the junction of the second end of the inductor L and the first end of the second capacitor C2 is connected to the first end of the secondary power conversion subunit a1031;

the second end of the secondary power conversion subunit a1031 is connected with the first end of the first resistor R1;

an intersection point of the second end of the first resistor R1 and the first end of the second resistor R2, and a third end of the secondary power conversion subunit a1031 are respectively connected with the first end of the third capacitor C3;

the connection terminal between the second end of the second resistor R2 and the second end of the third capacitor C3 is grounded.

In this embodiment, referring to fig. 5, fig. 5 is a schematic circuit diagram of a secondary power conversion unit in the unmanned aerial vehicle power distribution device according to the present utility model. Because the current unmanned aerial vehicle power supply voltage system increases, unmanned aerial vehicle power distribution device 10 designs by secondary power conversion unit a103, and this secondary power conversion unit a103 carries out the secondary conversion to input voltage (i.e. generator power and avionics battery's voltage sum, avionics battery provided voltage and generator provided voltage) in order to satisfy airborne consumer voltage demand. The voltage output by the secondary power supply conversion unit A103 is adjustable, namely, the airborne equipment with different voltages can be adapted by adjusting the resistance parameters, so that the subsequent research and development cost and period are reduced. For example, the steering engine is mainly powered by DC24V, DC V and DC8V.

It should be noted that, the resistance parameters of the first resistor R1 and the second resistor R2 may be adjusted, and are not constant.

Further, in other possible embodiments, the output switch unit a104 includes: the third resistor R3, the fourth resistor R4, the fifth resistor R5, the fourth capacitor C4 and the switch subunit;

the first end of the switch subunit is connected with the third resistor R3, the intersection point of the connection of the fourth resistor R4 and the fifth resistor R5 is connected with the second end of the switch subunit, and the fourth resistor R4 is connected with the fourth capacitor C4;

the fourth capacitor C4 is grounded, and the fifth resistor R5 is grounded.

In this embodiment, referring to fig. 6, fig. 6 is a schematic circuit diagram of an output switch unit in the unmanned aerial vehicle power distribution apparatus of the present utility model. When unmanned aerial vehicle 20 carries out flight mission, when needs control the on-vehicle consumer, can control the power supply of on-vehicle consumer through output switch unit A104, can also monitor the electric current size of on-vehicle consumer simultaneously, if the electric current of on-vehicle consumer is unusual, then indicate that on-vehicle consumer appears unusual, improved distribution system's integrated level and security.

Further, in other possible embodiments, the switch subunit is a high-side switch, a relay, or a MOS transistor.

Further, in yet another embodiment, the unmanned aerial vehicle power distribution device includes at least 2 temperature sensors, and the unmanned aerial vehicle power distribution device is an onboard system power distribution device, and heating is unavoidable. According to the unmanned aerial vehicle power distribution device, 2 temperature sensors can be added, the temperature condition of power distribution equipment is monitored in real time, and when the set temperature threshold value is reached, the temperature condition is reported to a flight control computer in advance for early warning. When early warning appears, in time reduce unmanned aerial vehicle distribution device's output and open the forced air cooling fan and cool down, great improvement the security.

Further, in another embodiment, the sources of the voltage and current collection and control model of the utility model are unmanned aerial vehicle power distribution devices, and can also be flight control computers.

In summary, first, the unmanned aerial vehicle power distribution device 10 and the flight control computer in the utility model adopt CAN bus communication, and the unmanned aerial vehicle power distribution device 10 performs power distribution control, so that interface resources of the flight control computer are saved, connecting cables in the system are reduced, the integration level is higher, and the subsequent research and development cost and period are reduced. Secondly, the utility model adopts a diode combination way or an MOS tube or an integrated circuit way to support the simultaneous power supply of the avionic battery and the generator, thereby enabling the unmanned aerial vehicle to have longer endurance time and higher reliability; on the other hand, the utility model also adopts the high-side switch with feedback to control output, thereby improving the integration level and the safety of the system. In addition, the built-in secondary power supply conversion unit A103 can be more suitable for the situation that the current unmanned aerial vehicle power system is increased, and has better compatibility. In other words, the present utility model improves the self-adaptive capabilities of unmanned aerial vehicle power distribution devices.

In addition, the application also provides terminal equipment. The terminal equipment provided by the embodiment of the utility model can be applied to the unmanned aerial vehicle power distribution device.

The foregoing description is only of the preferred embodiments of the present application and is not intended to limit the scope of the claims, and all equivalent structural changes made in the present application and the accompanying drawings or direct/indirect application in other related technical fields are included in the scope of the present application.

Claims (10)

1. Unmanned aerial vehicle power distribution device, its characterized in that, unmanned aerial vehicle power distribution device includes: the device comprises a power supply module, an acquisition module, a communication interface, a control module and a control interface module;

the unmanned aerial vehicle power distribution device is connected with the unmanned aerial vehicle through the communication interface, and is connected with a plurality of electric equipment in the unmanned aerial vehicle through the control interface module;

the control module is respectively connected with the communication interface, the control interface module, the power supply module and the acquisition module;

the power module, the acquisition module and the control interface module are sequentially connected.

2. The unmanned aerial vehicle power distribution device of claim 1, wherein the unmanned aerial vehicle comprises: a generator power supply and an avionic battery;

the generator power supply and the avionics battery are respectively connected with the power supply module and used for providing required voltage for each electric equipment, wherein the required voltage refers to input voltage corresponding to each electric equipment.

3. The unmanned aerial vehicle power distribution device of claim 1, wherein the power module comprises: the device comprises an input power acquisition unit, a parallel power unit, a secondary power conversion unit and an output switch unit;

the input power supply acquisition unit is connected with the secondary power supply conversion unit through the parallel power supply unit;

the input power supply acquisition unit is connected with the output switch unit.

4. The unmanned aerial vehicle power distribution device of claim 3, wherein the input power acquisition unit comprises: the device comprises a first current sensor, a second current sensor, a generator power supply filtering subunit and an avionics battery filtering subunit;

the generator power supply filtering subunit is connected with the first current sensor, and the avionics battery filtering subunit is connected with the second current sensor.

5. The unmanned aerial vehicle power distribution device of claim 3, wherein the power combining unit comprises a first diode combination and a second diode combination, wherein the first diode combination and the second diode combination are the same.

6. The unmanned aerial vehicle power distribution device of claim 5, wherein the first diode combining comprises: a first diode and a second diode;

the anode of the first diode is connected with the anode of the second diode, and the cathode of the first diode is connected with the cathode of the second diode.

7. The unmanned aerial vehicle power distribution device of claim 3, wherein the secondary power conversion unit comprises: the first resistor, the second resistor, the first capacitor, the second capacitor, the third capacitor, the inductor and the secondary power supply conversion subunit;

the first end of the first capacitor is connected with the first end of the inductor, the second end of the inductor is connected with the first end of the second capacitor, and the second end of the first capacitor is respectively grounded with the second end of the second capacitor;

the junction of the second end of the inductor and the first end of the second capacitor is connected with the first end of the secondary power conversion subunit;

the second end of the secondary power supply conversion subunit is connected with the first end of the first resistor;

the intersection point of the second end of the first resistor and the first end of the second resistor is connected with the third end of the secondary power conversion subunit respectively;

the connection terminal between the second end of the second resistor and the second end of the third capacitor is grounded.

8. The unmanned aerial vehicle power distribution device of claim 3, wherein the output switching unit comprises: the third resistor, the fourth resistor, the fifth resistor, the fourth capacitor and the switch subunit;

the first end of the switch subunit is connected with the third resistor, the intersection point of the connection of the fourth resistor and the fifth resistor is connected with the second end of the switch subunit, and the fourth resistor is connected with the fourth capacitor;

the fourth capacitor is grounded, and the fifth resistor is grounded.

9. The unmanned aerial vehicle power distribution device of claim 8, wherein the switch subunit is a high-side switch, relay, or MOS transistor.

10. A terminal device, characterized in that it comprises a drone power distribution apparatus according to any one of claims 1-9.

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