CN218829187U - Unmanned vehicles electrical system and unmanned vehicles - Google Patents
Unmanned vehicles electrical system and unmanned vehicles Download PDFInfo
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- CN218829187U CN218829187U CN202223085059.4U CN202223085059U CN218829187U CN 218829187 U CN218829187 U CN 218829187U CN 202223085059 U CN202223085059 U CN 202223085059U CN 218829187 U CN218829187 U CN 218829187U
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Abstract
The utility model discloses an unmanned vehicles electrical system and unmanned vehicles. The unmanned aerial vehicle electrical system comprises: a power supply device and a power consumption device; wherein: the power supply equipment comprises a power supply control unit, a first power supply management unit, a second power supply management unit, a third power supply management unit, a first power supply distribution unit and a second power supply distribution unit; the first power supply distribution unit is powered by a power supply control unit and a second power supply management unit together, and the second power supply distribution unit is powered by a power supply control unit and a third power supply management unit together; the electric equipment comprises critical equipment and non-critical equipment; the key equipment adopts the first power distribution unit and the second power distribution unit to supply power together, and the non-key equipment adopts the first power management unit to supply power. Thus, a safe equipment power supply can still be provided for the unmanned aerial vehicle when part of the unmanned aerial vehicle has a fault.
Description
Technical Field
The utility model relates to an unmanned vehicles field especially relates to an unmanned vehicles electrical system and unmanned vehicles.
Background
At present, unmanned aerial vehicle's application is increasingly extensive, can be applied to and take a picture in the air, make a video recording and general commodity circulation transportation.
However, the existing unmanned aerial vehicle generally adopts a single battery, and the endurance of the unmanned aerial vehicle cannot be estimated, and other risks possibly existing in the battery cannot be predicted, so that insufficient endurance or faults may occur. The battery fails and the unmanned aerial vehicle loses power, resulting in crash.
Therefore, there is a need to provide a new electrical system for an unmanned aerial vehicle that can still provide a safe device power supply for the unmanned aerial vehicle to meet the safety requirements of the unmanned aerial vehicle when some components of the unmanned aerial vehicle fail.
SUMMERY OF THE UTILITY MODEL
An embodiment of the utility model provides an unmanned vehicles electrical system and unmanned vehicles aims at solving the battery of present unmanned vehicles and can't estimate unmanned vehicles's continuation of the journey and other risks that the battery probably exists are announced in advance, probably takes place to continue a journey not enough or break down, leads to unmanned vehicles will lose power, leads to the problem of crash.
In order to solve the technical problem, an embodiment of the utility model provides an unmanned vehicles electrical system, unmanned vehicles electrical system includes: the power supply equipment is electrically connected with the electric equipment; wherein:
the power supply equipment comprises a power supply control unit, a first power supply management unit, a second power supply management unit, a third power supply management unit, a first power supply distribution unit and a second power supply distribution unit; wherein the first power distribution unit is powered by the power control unit and the second power management unit together, and the second power distribution unit is powered by the power control unit and the third power management unit together;
the electric equipment comprises critical equipment and non-critical equipment; the key equipment adopts the first power distribution unit and the second power distribution unit to supply power together, and the non-key equipment adopts the first power management unit to supply power.
Optionally, the power control unit is mounted at the tail of a bottom bin of the unmanned aerial vehicle.
Optionally, the first power management unit, the second power management unit, and the third power management unit are mounted side-by-side on a floor of a rear tail bin of the unmanned aerial vehicle.
Optionally, the first power distribution unit and the second power distribution unit are mounted in a tail bin of an unmanned aerial vehicle.
Optionally, the critical equipment comprises important critical equipment and general critical equipment; the first power distribution unit provides power for all key equipment including the important key equipment and the general key equipment; the second power distribution unit provides power for the important key equipment.
Optionally, the first power distribution unit is commonly powered by the power control unit and the second power management unit, and includes: the outputs of the second power supply management unit and the power supply control unit are connected in parallel through a diode to supply power for the first power supply distribution unit.
Optionally, the power supply logic of the first power distribution unit is:
when the power supply control unit is short-circuited, the second power supply management unit supplies power to the first power supply distribution unit;
when the second power supply management unit is short-circuited, the power supply control unit supplies power to the first power supply distribution unit;
when only the second power supply management unit is started and power electricity is not started, the first power supply distribution unit is independently powered by the second power supply management unit; after the power electricity is started, when the second power management unit and the power control unit are normal, if the voltage of the second power management unit is higher, the second power management unit can supply power preferentially, when the voltage of the second power management unit is reduced to be consistent with the voltage of the power control unit along with the discharge of the second power management unit, the second power management unit and the power control unit can supply power together, and when the voltage is lower than the power control unit along with the further discharge of the second power management unit, the power control unit can supply power independently; if the voltage of the power supply control unit is higher than that of the second power supply management unit from the beginning, the power supply control unit supplies power alone, and the power of the second power supply management unit cannot be consumed.
Optionally, the second power distribution unit is commonly powered by the power control unit and the third power management unit, and includes: the outputs of the power supply control unit and the third power supply management unit are connected in parallel through a diode to supply power for the second power supply distribution unit.
Optionally, the power supply logic of the second power distribution unit is:
when the power supply control unit is short-circuited, the third power supply management unit supplies power to the second power supply distribution unit;
when the third power supply management unit is short-circuited, the power supply control unit supplies power to the second power supply distribution unit;
when only the third power supply management unit is started and power electricity is not started, the second power supply distribution unit is independently powered by the third power supply management unit; after power electricity is started, when the third power management unit and the power control unit are both normal, if the voltage of the third power management unit is higher, the third power management unit can supply power preferentially, when the voltage of the third power management unit is reduced to be consistent with the voltage of the power control unit along with the discharge of the third power management unit, the third power management unit and the power control unit can supply power together, and when the voltage is lower than that of the power control unit along with the further discharge of the third power management unit, the power control unit can supply power independently; if the voltage of the power supply control unit is higher than that of the third power supply management unit from the beginning, the power supply control unit supplies power alone all the time, and the power of the third power supply management unit cannot be consumed.
Accordingly, an embodiment of a second aspect of the present invention provides an unmanned aerial vehicle, the unmanned aerial vehicle includes an embodiment of the first aspect of the present invention the unmanned aerial vehicle electrical system.
Compared with the prior art, the unmanned aerial vehicle electrical system and the unmanned aerial vehicle provided by the embodiment of the utility model have the advantages that the unmanned aerial vehicle electrical system comprises power supply equipment and electric equipment; the power supply equipment comprises a power supply control unit, a first power supply management unit, a second power supply management unit, a third power supply management unit, a first power supply distribution unit and a second power supply distribution unit; wherein the first power distribution unit is powered by the power control unit and the second power management unit together, and the second power distribution unit is powered by the power control unit and the third power management unit together; the electric equipment comprises critical equipment and non-critical equipment; the key equipment adopts the first power distribution unit and the second power distribution unit to supply power together, and the non-key equipment adopts the first power management unit to supply power. Therefore, when part of components of the unmanned aerial vehicle (particularly the unmanned manned aircraft) are in fault, a safe equipment power supply can still be provided for the aircraft, meanwhile, the possible risks of the battery in the power management unit and the possible risks of the power distribution unit can be fed back in time, when the risks exist in the power management unit or the power distribution unit, an emergency risk avoiding basis can be provided for cluster management of the automatic driving and intelligent command and dispatching center, and the requirement that intelligent traffic provides a low-air short-distance traffic transportation solution can be met. Therefore, the problem that the battery of the existing unmanned aerial vehicle cannot estimate the endurance of the unmanned aerial vehicle and forecast other risks possibly existing in the battery, insufficient endurance or failure can occur, and the unmanned aerial vehicle loses power and crashes can be solved.
Drawings
One or more embodiments are illustrated by way of example in the accompanying drawings which correspond to and are not to be construed as limiting the embodiments, in which elements having the same reference numeral designations represent like elements throughout, and in which the drawings are not to be construed as limiting in scale unless otherwise specified.
FIG. 1 is a schematic diagram of an electrical system for an unmanned aerial vehicle according to the present invention;
FIG. 2 is a detailed structural schematic diagram of an electrical system of an unmanned aerial vehicle provided by the present invention;
FIG. 3 is a schematic view of the positioning of the components of an electrical system of an unmanned aerial vehicle within the unmanned aerial vehicle provided by the present invention;
FIG. 4 is a schematic view of the positioning of the components of an unmanned aerial vehicle electrical system within an unmanned aerial vehicle provided by the present invention;
fig. 5 is a schematic diagram illustrating a position of a power battery assembly in an electrical system of an unmanned aerial vehicle provided by the present invention;
fig. 6 is a schematic view of a position of a cabin display unit in an electrical system of an unmanned aerial vehicle in the unmanned aerial vehicle provided by the present invention;
fig. 7 is a schematic structural diagram of an unmanned aerial vehicle provided by the present invention.
Reference numerals:
electrical 1 power supply device 11 for unmanned aerial vehicle
System for controlling a power supply
First power management unit 111 and second power management unit 112
Third Power management Unit 113 first Power distribution Unit 114
Second power distribution unit 115 power cell assembly 121
Flight control unit 122 magnetic compass barometer unit 123
Unmanned aerial vehicle 100
Detailed Description
In order to facilitate understanding of the present invention, the present invention will be described in more detail with reference to the accompanying drawings and specific embodiments. It will be understood that when an element is referred to as being "secured to" another element, it can be directly on the other element or intervening elements may be present. When an element is referred to as being "connected" to another element, it can be directly connected to the other element or intervening elements may be present. The terms "upper", "lower", "inner", "outer", "bottom", and the like as used herein are used in the description to indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are used only for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus should not be construed as limiting the present invention. Furthermore, the terms "first," "second," "third," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. The terminology used in the description of the invention herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used herein, the term "and/or" includes any and all combinations of one or more of the associated listed items.
Furthermore, the technical features mentioned in the different embodiments of the invention described below can be combined with each other as long as they do not conflict with each other.
In one embodiment, as shown in fig. 1, the present invention provides an unmanned aerial vehicle electrical system, the unmanned aerial vehicle electrical system 1 comprising: the power supply device 11 is electrically connected with the electric equipment 12, and the power supply device 11 provides electrical control for the electric equipment 12; wherein:
the Power supply device 11 includes a Power Control Unit (PCU) 116, a first Power Management Unit (PMU) 111, a second Power management Unit 112, a third Power management Unit 113, a first Power Distribution Unit (PDU) 114, and a second Power Distribution Unit 115; wherein the first power distribution unit 114 is commonly powered by the power control unit 116 and the second power management unit 112, and the second power distribution unit 115 is commonly powered by the power control unit 116 and the third power management unit 113;
the powered devices 12 include critical devices and non-critical devices; the critical device uses the first power distribution unit 114 and the second power distribution unit 115 to supply power together, and the non-critical device uses the first power management unit 111 to supply power.
In the present embodiment, by providing an unmanned aerial vehicle electrical system for an unmanned aerial vehicle, the unmanned aerial vehicle electrical system comprises a power supply device and a power-consuming device; the power supply equipment comprises a power supply control unit, a first power supply management unit, a second power supply management unit, a third power supply management unit, a first power supply distribution unit and a second power supply distribution unit; wherein the first power distribution unit is powered by the power control unit and the second power management unit together, and the second power distribution unit is powered by the power control unit and the third power management unit together; the electric equipment comprises critical equipment and non-critical equipment; the key equipment adopts the first power distribution unit and the second power distribution unit to supply power together, and the non-key equipment adopts the first power management unit to supply power. Therefore, when part of components of the unmanned aerial vehicle (particularly the unmanned manned aircraft) are in fault, a safe equipment power supply can still be provided for the aircraft, meanwhile, the possible risks of the battery in the power management unit and the possible risks of the power distribution unit can be fed back in time, when the risks exist in the power management unit or the power distribution unit, an emergency risk avoiding basis can be provided for cluster management of the automatic driving and intelligent command and dispatching center, and the requirement that intelligent traffic provides a low-air short-distance traffic transportation solution can be met. Therefore, the problem that the battery of the existing unmanned aerial vehicle cannot estimate the endurance of the unmanned aerial vehicle and forecast other risks possibly existing in the battery, insufficient endurance or failure can occur, and the unmanned aerial vehicle loses power and crashes can be solved.
In one embodiment, the powered device 12 includes critical devices and non-critical devices; the critical device uses the first power distribution unit 114 and the second power distribution unit 115 to supply power together, and the non-critical device uses the first power management unit 111 to supply power.
Specifically, as shown in fig. 2 to 6, the key devices include important key devices and general key devices; the important key devices include a power battery assembly 121, a Flight Control Unit (FCU) 122, and a magnetic Compass Barometer Unit (CBU) 123 of the unmanned aerial vehicle. Wherein:
the power battery assembly 121 is used for providing a power supply for the unmanned aerial vehicle. In this embodiment, as shown in fig. 5, the unmanned aerial vehicle 121 includes 12 sets of power battery assemblies, and is installed in a 3 × 4 arrangement in the bottom cabin of the unmanned aerial vehicle. The battery management unit and the power protection device in the power battery assembly 121 use a power supply of 10V-30V to supply power. The electricity consumption requirement of the single-group power battery pack for a 10V-30V power supply is 3.8W, and the total power supply requirement of the 12 groups of power battery packs is 45.6W.
The flight control unit 122 is an information processing and control center of the unmanned aerial vehicle.
And the magnetic compass barometer unit 123 is used for measuring the yaw angle and the height of the unmanned aerial vehicle.
In this embodiment, as shown in fig. 3 and 4, the unmanned aerial vehicle electrical system 1 includes a disk barometer unit 123 and three flight control units (FCU 1, FCU2, FCU 3), where FCU1 is mounted in a shark fin at the top of the unmanned aerial vehicle, FCU2 is mounted on the cockpit floor of the unmanned aerial vehicle, and FCU3 is mounted on the tailbay bulkhead of the unmanned aerial vehicle. The flight control unit and the disk barometer unit are powered by 18-35V voltage, wherein the power consumption of the FCU1 is 5W, the FCU2 and the disk barometer unit share the same power supply, the total power consumption is 7W, and the power consumption of the FCU3 is 5.6W.
As shown in fig. 2 to 6, the general key device includes one of the following devices: pan-tilt assembly 124, radar altimeter 125, onboard router 126, bus recorder 127, and cockpit display unit 128. Wherein:
the holder assembly 124 is configured to photograph the surrounding environment of the unmanned aerial vehicle, and monitor the flight environment of the unmanned aerial vehicle. As shown in fig. 4, the pan-tilt assembly 124 is installed below the bottom of the front section of the unmanned aerial vehicle, the pan-tilt assembly 124 includes a camera and a pan-tilt for controlling and stabilizing the direction of the camera, the pan-tilt assembly is powered by a power supply of 18-35V, and the power consumption during operation is 28W.
The radar altimeter 125, which measures the height of the unmanned aerial vehicle to the ground, is mounted outside the bottom of the vehicle, as shown in fig. 4. In an embodiment, the radar altimeter 125 is a compact type K-band altimeter radar, adopts a 24GHz-ISM band, has a measurement accuracy of 2cm, is powered by a 9-36V power supply, and has a power consumption of 2.1W during operation.
The onboard router 126 is connected between the components in the unmanned aerial vehicle, and is used for information interaction between the components. The onboard router 126 is powered by 9-36V voltage, and the power consumption is 7W during operation.
The bus recorder 127 is configured to record CAN data on each CAN (Controller Area Network) bus of the unmanned aerial vehicle, and is installed on a floor of a tail bin of the unmanned aerial vehicle. The bus recorder 127 is powered by a power supply of 18-35V, and the power consumption is 2.8W during working.
The cockpit display unit 128 is configured to interact with the passengers to provide the passengers with status information of the unmanned aerial vehicle. As shown in FIG. 6, the cockpit display unit 128 is installed at the front position of the cockpit of the unmanned aerial vehicle, and uses 18-35V power supply, and the power consumption during operation is 14W.
The non-critical devices include environmental devices such as lights, sounds, and the like.
In a preferred embodiment, as shown in fig. 2, the electric device further includes a Central Control Unit (CCU) 129, where the central Control unit 129 is electrically connected to the first power management unit 111 and is powered by the first power management unit 111. The central control unit 129 is used for controlling the power supply of the non-critical devices in a unified manner, that is, the power supply of the non-critical devices including the environmental devices such as lights and sounds is controlled by the central control unit 129 in a unified manner.
In one embodiment, the power supply apparatus 11 includes a power control unit 116 and a first power management unit 111, a second power management unit 112, a third power management unit 113, a first power distribution unit 114, and a second power distribution unit 115.
Specifically, the power control unit 116 is configured to convert a power supply on the unmanned aerial vehicle into equipment power, provide a 24V power supply for the electric equipment after the power battery is turned on, and provide a higher layer of power supply guarantee for an electrical system of the unmanned aerial vehicle.
As shown in fig. 3, the power control unit 116 is installed at the rear of the bottom bay of the unmanned aerial vehicle.
The input of the power control unit 116 is from a power supply, and is stepped down to a 24V device through a DC/DC (Direct Current to Direct Current) power supply, a communication interface of the power control unit 116 is connected to an ALLCAN bus, and self-state information such as Current, voltage and the like is reported through CAN communication of the ALLCAN bus.
The ALLCAN bus is connected with a flight control system, a power battery assembly, a power management unit and other equipment.
The power supply of the power supply control unit 116 adopts a 5A fuse as a protection device, which can ensure that the power supply is safe when the power supply control unit 116 fails. The output of the power control unit 116 adopts a 12A fuse and a backflow prevention circuit, so that when a short circuit occurs inside the power control unit 116, backflow current cannot occur, and the safety of the power supply of the electric equipment cannot be influenced.
The first power management unit 111, the second power management unit 112, and the third power management unit 113 are configured to provide power for all the electric devices connected thereto and ensure power supply safety of the electric devices.
As shown in fig. 3, the first power management unit 111, the second power management unit 112, and the third power management unit 113 are installed side by side on the floor of the rear tail bin of the unmanned aerial vehicle.
The first power management unit 111, the second power management unit 112, and the third power management unit 113 support external key signal on output, and communication interfaces thereof are connected to an ALLCAN bus, and report self-state information such as current and voltage through CAN communication of the ALLCAN bus.
The first power management unit 111, the second power management unit 112 and the third power management unit 113 have the same data monitoring and alarming capabilities, can acquire data such as temperature, current and electric quantity of the battery in real time and monitor various data, and generate three different levels of warning for the data with risks according to the severity of the risks. And for serious deviation from a normal threshold or fault, alarm locking logic is defined, once a certain item of data exceeds a locking threshold, the alarm is always locked in a state of primary alarm and cannot be automatically removed, and the alarm must be manually intervened to carry out maintenance confirmation and then is removed by sending a removing command, so that the safety of charging, discharging and flying is ensured.
The power-on signal lines of the first power management unit 111, the second power management unit 112 and the third power management unit 113 are connected in parallel and connected to the power-on button on the cockpit display unit 128. When the power-on button is pressed for more than 1 second, the first power management unit 111, the second power management unit 112, and the third power management unit 113 all turn on the discharge MOS and start to discharge to the outside. At this point all the electrical consumers, including flight control unit 122 and power cell assembly 121, have begun to operate. At this point, the power may be turned on by a power button on the ground control station, or on the cockpit display unit 128. After the power supply is turned on, the power supply control unit 116 starts to work to provide power backup for the whole battery system.
When the unmanned aerial vehicle needs to be shut down, a power electricity shut-down command is issued through the ground control station, the power electricity is shut down first, the power supply control unit 116 stops outputting immediately, then a power supply management unit shut-down command is issued through the ground control station, and the outputs of the first power supply management unit 111, the second power supply management unit 112 and the third power supply management unit 113 are shut down.
The power electricity closing command and the power management unit closing command are divided into two commands, and the second command is required to be received within 3 seconds after the first command is received to be effective, so that the possibility of mistaken closing can be effectively reduced.
The first power management unit 111, the second power management unit 112, the third power management unit 113, and the power control unit 116 all have CAN communication capabilities, the first power management unit 111, the second power management unit 112, the third power management unit 113, and the power control unit 116 are all connected to the flight control unit 122 through an ALLCAN bus, and CAN send information such as own input voltage, output current, temperature, and alarm to the flight control unit 122 through the CAN bus, and meanwhile, the flight control unit 122 CAN forward the information to a ground station through a data link for display, so as to be referred to by a remote unit.
In one embodiment, the first power distribution unit 114 and the second power distribution unit 115 are used for supplying power to the key devices of the electric devices.
As shown in fig. 3, the first power distribution unit 114 and the second power distribution unit 115 are installed in the tail bin of the unmanned aerial vehicle.
The first power distribution unit 114 is used for providing power for all critical devices including the important critical device and the general critical device of the electric equipment. The second power distribution unit 115 is used for providing power for the important key equipment of the electric equipment.
The first power distribution unit 114 is commonly powered by the power control unit 116 and the second power management unit 112. Specifically, the first power distribution unit 114 is electrically connected to the power control unit 116 and the second power management unit 112, respectively, and the power control unit 116 and the second power management unit 112 jointly supply power to the first power distribution unit 114.
The output of the first power distribution unit 114 is protected by a fuse of 2A specification, and each of the on-circuit devices is connected to the power supply inside the first power distribution unit 114 through a separate fuse. When a certain electric equipment breaks down to generate large current, the electric equipment can be cut off by the fuse, the safety of a power bus is protected, the fuse is detachable, and the replacement is convenient. Therefore, when any one electric device is short-circuited, other electric devices are not affected.
Specifically, the power supply logic of the first power distribution unit 114 is as follows:
the first power distribution unit 114 provides power supply and protection for all key devices on the unmanned aerial vehicle, and power sources of the first power distribution unit 114 are the second power management unit 112 and the power control unit 116, wherein the second power management unit 112 and the power control unit 116 both have a backflow prevention function, so that current backflow can be effectively prevented. The outputs of the second power management unit 112 and the power control unit 116 are connected in parallel through diodes, so that input backup and seamless switching can be realized.
When the power control unit 116 is short-circuited, the second power management unit 112 can supply power to the first power distribution unit 114, and due to the existence of the diode and the backflow prevention circuit, the electric energy of the second power management unit 112 can be prevented from flowing back to the power control unit 116 through the first power distribution unit 114, so that the power supply of the first power distribution unit 114 is prevented from being failed integrally.
When the second power management unit 112 is short-circuited, the power control unit 116 supplies power to the first power distribution unit 114, and due to the existence of the diode and the backflow prevention circuit, the electric energy of the power control unit 116 can be prevented from flowing backwards to the second power management unit 112 through the first power distribution unit 114, so that the power supply of the first power distribution unit 114 is prevented from being wholly failed.
Therefore, whether the second power management unit 112 or the power control unit 116 fails, it can be ensured that the power supply requirements of all the electric devices connected to the first power distribution unit 114 can be met.
When only the second power management unit 112 is turned on and the power supply is not turned on, the first power distribution unit 114 is supplied with power by the second power management unit 112 alone. After the power supply is turned on, because the second power management unit 112 and the power control unit 116 are connected in parallel through a diode, when the second power management unit 112 and the power control unit 116 are both normal, if the voltage of the second power management unit 112 is higher, the second power management unit 112 can supply power preferentially, when the voltage of the second power management unit 112 is reduced to be consistent with the voltage of the power control unit 116 as the second power management unit 112 discharges, the second power management unit 112 and the power control unit 116 supply power together, and when the voltage is lower than the power control unit 116 as the second power management unit 112 further discharges, the power control unit 116 supplies power alone. If the voltage of the power control unit 116 is higher than that of the second power management unit 112 from the beginning, the power control unit 116 alone supplies power all the time, the power of the second power management unit 112 will not be consumed, and it can be ensured that the second power management unit 112 has enough power to ensure the power supply safety of the equipment power in an emergency.
In one embodiment, the second power distribution unit 115 is commonly powered by the power control unit 116 and the third power management unit 113, and is used for providing power for the important key devices of the electric devices.
Specifically, the second power distribution unit 115 is electrically connected to the power control unit 116 and the third power management unit 113, respectively, and the power control unit 116 and the third power management unit 113 jointly supply power to the second power distribution unit 115.
The output of the second power distribution unit 115 is protected by a fuse of 2A specification, and each piece of circuit-using equipment is connected to the power supply inside the second power distribution unit 115 through a separate fuse. When a certain electric equipment breaks down to generate large current, the electric equipment can be cut off by the fuse, the safety of a power bus is protected, the fuse is detachable, and the replacement is convenient. Therefore, when any one electric device is short-circuited, other electric devices are not affected.
Specifically, the power supply logic of the second power distribution unit 115 is as follows:
the second power distribution unit 115 provides power supply and protection for the important key devices of the electric devices on the unmanned aerial vehicle, and the power sources of the second power distribution unit 115 are the third power management unit 113 and the power control unit 116. The third power management unit 113 and the power control unit 116 both have a backflow prevention function, so that current backflow can be effectively prevented. The outputs of the power control unit 116 and the third power management unit 113 are connected in parallel through a diode, so that input backup and seamless switching can be realized.
When the power control unit 116 is short-circuited, the third power management unit 113 can supply power to the second power distribution unit 115, and due to the existence of the diode and the backflow prevention circuit, the electric energy of the third power management unit 113 can be prevented from flowing backwards to the power control unit 116 through the second power distribution unit 115, so that the power supply of the second power distribution unit 115 is prevented from being failed wholly.
When the third power management unit 113 is short-circuited, the power control unit 116 can supply power to the second power distribution unit 115, and due to the existence of the diode and the backflow prevention circuit, the electric energy of the power control unit 116 can be prevented from flowing backwards to the third power management unit 113 through the second power distribution unit 115, so that the power supply of the second power distribution unit 115 is prevented from being failed wholly.
Therefore, it can be ensured that the power supply requirements of all the electric devices connected to the second power distribution unit 115 can be met regardless of the failure of the third power management unit 113 or the power control unit 116.
When only the third power management unit 113 is turned on and power is not turned on, the second power distribution unit 115 is supplied with power solely from the third power management unit 113. After the power supply is turned on, because the third power management unit 113 and the power control unit 116 are connected in parallel through a diode, when the third power management unit 113 and the power control unit 116 are both normal, if the voltage of the third power management unit 113 is higher, the third power management unit 113 preferentially supplies power, when the voltage of the third power management unit 113 is reduced to be consistent with the voltage of the power control unit 116 as the third power management unit 113 discharges, the third power management unit 113 and the power control unit 116 supply power together, and when the voltage is lower than the power control unit 116 as the third power management unit 113 further discharges, the power control unit 116 supplies power alone. If the voltage of the power control unit 116 is higher than that of the third power management unit 113 from the beginning, the power control unit 116 alone supplies power all the time, the power of the third power management unit 113 will not be consumed, and it can be ensured that the third power management unit 113 has enough power to ensure the power supply safety of the equipment power in an emergency.
Based on the same concept, in one embodiment, as shown in fig. 7, the present invention provides an unmanned aerial vehicle 100, where the unmanned aerial vehicle 100 includes the unmanned aerial vehicle electrical system 1 according to any of the above embodiments.
In this embodiment, the electrical system 1 of the unmanned aerial vehicle is the same as the electrical system 1 of the unmanned aerial vehicle described in any one of the embodiments, and specific structures and functions may refer to the electrical system 1 of the unmanned aerial vehicle described in any one of the embodiments, which is not described herein again.
In this embodiment, by providing an unmanned aerial vehicle comprising an unmanned aerial vehicle electrical system comprising a power supply and a powered device; the power supply equipment comprises a power supply control unit, a first power supply management unit, a second power supply management unit, a third power supply management unit, a first power supply distribution unit and a second power supply distribution unit; wherein the first power distribution unit is powered by the power control unit and the second power management unit together, and the second power distribution unit is powered by the power control unit and the third power management unit together; the electric equipment comprises critical equipment and non-critical equipment; the key equipment adopts the first power distribution unit and the second power distribution unit to supply power together, and the non-key equipment adopts the first power management unit to supply power. Therefore, when parts of the unmanned aerial vehicle (especially the unmanned manned aircraft) are in failure, a safe equipment power supply can still be provided for the aircraft, meanwhile, the possible risks of the battery in the power management unit and the possible risks of the power distribution unit can be fed back in time, when the power management unit or the power distribution unit has the risks, an emergency risk avoiding basis can be provided for cluster management of the automatic driving and intelligent command and dispatching center, and the requirement of providing a low-air short-distance transportation solution for intelligent transportation can be met. Therefore, the problem that the battery of the existing unmanned aerial vehicle cannot estimate the endurance of the unmanned aerial vehicle and forecast other possible risks of the battery, insufficient endurance or faults can occur, and the unmanned aerial vehicle loses power and is crashed can be solved.
It should be noted that the above unmanned aerial vehicle embodiment and the unmanned aerial vehicle electrical system embodiment belong to the same concept, and specific implementation processes thereof are described in detail in the unmanned aerial vehicle electrical system embodiment, and technical features in the unmanned aerial vehicle electrical system embodiment are applicable to the above unmanned aerial vehicle embodiments, and are not described herein again.
It should be noted that, in this document, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrases "comprising a component of' 8230; \8230;" does not exclude the presence of another like element in a process, method, article, or apparatus that comprises the element.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; within the idea of the invention, also technical features in the above embodiments or in different embodiments can be combined, steps can be implemented in any order, and there are many other variations of the different aspects of the invention as described above, which are not provided in detail for the sake of brevity; although the present invention has been described in detail with reference to the foregoing embodiments, it should be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; such modifications or substitutions do not depart from the scope of the invention in its corresponding aspects.
Claims (8)
1. An unmanned aerial vehicle electrical system, comprising: the power supply equipment is electrically connected with the electric equipment; wherein:
the power supply equipment comprises a power supply control unit, a first power supply management unit, a second power supply management unit, a third power supply management unit, a first power supply distribution unit and a second power supply distribution unit; wherein the first power distribution unit is powered by the power control unit and the second power management unit together, and the second power distribution unit is powered by the power control unit and the third power management unit together;
the electric equipment comprises critical equipment and non-critical equipment; the key equipment adopts the first power distribution unit and the second power distribution unit to supply power together, and the non-key equipment adopts the first power management unit to supply power.
2. The unmanned aerial vehicle electrical system of claim 1, wherein the power supply control unit is mounted aft of a bottom bay of the unmanned aerial vehicle.
3. The unmanned aerial vehicle electrical system of claim 1, wherein the first power management unit, the second power management unit, and the third power management unit are mounted side-by-side on a floor of a aft bay of the unmanned aerial vehicle.
4. The unmanned aerial vehicle electrical system of claim 1, wherein the first power distribution unit and the second power distribution unit are mounted at a tail bin of the unmanned aerial vehicle.
5. The unmanned aerial vehicle electrical system of claim 1, wherein the critical equipment comprises critical equipment and general critical equipment; the first power distribution unit provides power for all key equipment including the important key equipment and the general key equipment; the second power distribution unit provides power for the important and critical equipment.
6. The unmanned aerial vehicle electrical system of claim 1, wherein the first power distribution unit is powered by both the power control unit and the second power management unit, comprising: the outputs of the second power supply management unit and the power supply control unit are connected in parallel through a diode to supply power for the first power supply distribution unit together.
7. The unmanned aerial vehicle electrical system of claim 1, wherein the second power distribution unit is commonly powered by the power control unit and the third power management unit, comprising: the outputs of the power supply control unit and the third power supply management unit are connected in parallel through a diode to supply power for the second power supply distribution unit together.
8. An unmanned aerial vehicle comprising an unmanned aerial vehicle electrical system as claimed in any one of claims 1 to 7.
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| CN202223085059.4U CN218829187U (en) | 2022-11-17 | 2022-11-17 | Unmanned vehicles electrical system and unmanned vehicles |
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| CN202223085059.4U CN218829187U (en) | 2022-11-17 | 2022-11-17 | Unmanned vehicles electrical system and unmanned vehicles |
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