CN113532202A - Target drone electrical system and target drone with same - Google Patents
Target drone electrical system and target drone with same Download PDFInfo
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- CN113532202A CN113532202A CN202010294346.2A CN202010294346A CN113532202A CN 113532202 A CN113532202 A CN 113532202A CN 202010294346 A CN202010294346 A CN 202010294346A CN 113532202 A CN113532202 A CN 113532202A
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- lithium ion
- drone
- power
- electrical
- battery pack
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41J—TARGETS; TARGET RANGES; BULLET CATCHERS
- F41J9/00—Moving targets, i.e. moving when fired at
- F41J9/08—Airborne targets, e.g. drones, kites, balloons
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
- B64D27/24—Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
- B64D47/02—Arrangements or adaptations of signal or lighting devices
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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
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Abstract
The invention provides a target drone electrical system and a target drone with the same, wherein the system comprises a low-voltage direct-current power supply system, a lithium ion storage battery pack, a double-wire system power distribution system and an electrical interconnection system, the double-wire system power distribution system comprises an electrical control device, a positive bus bar, a first negative bus bar and a second negative bus bar, the electrical control device is respectively connected with the low-voltage direct-current power supply system and the lithium ion storage battery pack, the electrical control device comprises a control board card and a power board card, the control board card is used for receiving digital signals on a data bus and converting the digital signals into switching values, the power board card is used for receiving the switching values transmitted by the control board card and controlling the control board card to carry out power distribution output according to the switching values, and the electrical interconnection system is respectively connected with the double-wire system power distribution system and a load. By applying the technical scheme of the invention, the technical problems of high development cost and complex design process caused by the adoption of the design process of the military aircraft electrical system to design the target drone in the prior art are solved.
Description
Technical Field
The invention relates to the technical field of small and medium-sized drone, in particular to a drone aircraft electrical system and a drone aircraft with the same.
Background
The target drone is one kind of unmanned aerial vehicle, is mainly used for simulating threat targets such as combat airplanes and missiles, and provides a vivid aerial target for weapon system test and training. The target drone electrical system is responsible for receiving the instructions of the upper computer, supplying power to all systems on the drone according to the time sequence and ensuring that the power supply quality meets the load requirements on the drone. Thus, the design of the electrical system plays a crucial role in the drone to perform its intended function.
The target drone is mainly used for combat readiness training, is directly scrapped after being knocked down, and belongs to consumables. In recent years, with the advent of new weapon systems, troops consume more than 3000 frames of various drone aircraft each year. The electrical system is used as an important guarantee for all systems of the whole unmanned aerial vehicle, and the overall performance of the unmanned aerial vehicle is influenced by the architectural design of the electrical system. If the target drone is designed according to the design flow of the electrical system of the military aircraft, the development cost and the development period of the electrical system of the target drone are increased, and the military expense is greatly increased.
Disclosure of Invention
The invention provides a target drone electrical system and a target drone with the same, and can solve the technical problems of high development cost and complex design process caused by the fact that a military aircraft electrical system design process is adopted to design the target drone in the prior art.
According to an aspect of the invention, there is provided a drone aircraft electrical system comprising: the low-voltage direct-current power supply system is used for providing low-voltage direct current for the target drone; the lithium ion storage battery is used for providing an emergency power supply for the target drone under an emergency condition; the double-wire system power distribution system comprises an electrical control device, a positive bus bar, a first negative bus bar and a second negative bus bar, wherein the electrical control device is respectively connected with a low-voltage direct-current power supply system and a lithium ion storage battery pack, the electrical control device is used for realizing the switching control, the control power distribution and the direct power distribution between the low-voltage direct-current power supply system and the lithium ion storage battery pack, the electrical control device comprises a control board card and a power board card, the control board card is used for receiving digital signals on a data bus and converting the digital signals into switching values, and the power board card is used for receiving the switching values transmitted by the control board card and controlling the control board card to carry out power distribution output according to the switching values; the positive bus bar is arranged in the electric control device, and the low-voltage direct-current power supply system, the lithium ion storage battery pack and the load are connected with the positive bus bar; the first negative bus bar is arranged in the first equipment compartment, the second negative bus bar is arranged in the second equipment compartment, the low-voltage direct-current power supply system, the lithium ion storage battery pack and the load of the first equipment compartment are all connected with the first negative bus bar, and the load of the second equipment compartment is connected with the second negative bus bar; and the electric interconnection system is respectively connected with the double-wire system power distribution system and the load and is used for realizing electric quantity and signal transmission between the double-wire system power distribution system and the load.
Furthermore, the control board card comprises a main control chip and an avionic bus circuit, the main control chip is used for finishing processing of avionic bus signals and sending control signals to the power board card, and the avionic bus circuit is used for finishing receiving of the avionic bus signals and transmitting the avionic bus signals to the main control chip.
Furthermore, the power board card comprises a signal driving element and a power distribution switch, the signal driving element is used for receiving a control signal sent by the main control chip and driving the control signal to a high voltage to ensure that the power distribution switch is reliably conducted, the power distribution switch is used for receiving a driving signal output by the signal driving element and controlling the voltage to be output to a load, and the signal driving element is used for performing positive and negative redundant control on key equipment on the target drone, performing positive and single-way control on important equipment on the target drone and performing positive and negative dual-control redundant control on dangerous goods on the target drone.
Furthermore, the control board card also comprises decoupling capacitors which are arranged on the positive electrode and the negative electrode of the avionics bus interface chip power supply of the control board card.
Furthermore, the power board card also comprises a first discharge capacitor and a second discharge capacitor, the first discharge capacitor is arranged on the positive electrode and the negative electrode of the low-voltage direct-current power supply system, and the second discharge capacitor is arranged on the positive electrode and the negative electrode of the lithium-ion storage battery pack; and/or the electrical control device further comprises a metal shielding plate, and the metal shielding plate is arranged between the control board card and the power board card.
Furthermore, the electric control device also comprises an anti-reverse-filling circuit which is arranged at the input end of the lithium ion storage battery pack.
Further, the low-voltage direct-current power supply system comprises a starting generator, a generator control device and a current transformer, wherein the starting generator is used for driving the generator to work, the current transformer is respectively connected with the generator and the generator control device, the current transformer is used for collecting power generation data of the generator, and the generator control device is used for controlling the output electric quantity of the generator according to the power generation data of the generator; when the generator and the main feeder thereof have ground faults, the current transformer is used for generating pulse voltage proportional to the ground current of the generator and outputting the pulse voltage to the generator control device to protect the generator.
Furthermore, the lithium ion storage battery pack comprises a plurality of 18650 lithium ion single batteries and a heating circuit module, wherein the heating circuit module is respectively connected with the plurality of 18650 lithium ion single batteries, and is used for maintaining the temperature of the plurality of 18650 lithium ion single batteries within a set temperature range; the capacity redundancy of the lithium ion storage battery pack is 30% of the integral of a load electricity utilization curve, and the discharge multiplying power of the lithium ion storage battery pack exceeds 20% of the load electricity utilization transient peak value.
Furthermore, the electric interconnection system comprises a cable and a test interface, the cable comprises a WFRA series insulated super-soft wire, the test interface comprises a bus bar positive and negative interface and a communication bus branch interface, the bus bar positive and negative interface is used for connecting the low-voltage direct-current power supply system and the lithium ion storage battery pack, and the communication bus branch interface is used for testing whether the communication of the avionic bus of the target drone aircraft is normal.
According to another aspect of the present invention, there is provided a drone comprising a drone electrical system and a load, the drone electrical system being as described above, the drone electrical system being for powering the load.
By applying the technical scheme of the invention, the electric system of the target drone is provided, and the electric system of the target drone is provided with a low-voltage direct-current power supply system, a lithium ion storage battery pack, a double-wire system power distribution system and an electric interconnection system, wherein the low-voltage direct-current power supply system and the lithium ion storage battery pack are used for supplying power to a load; in addition, considering that most target drone are made of composite materials, the composite materials are semiconductors, and a drone body cannot be used as a negative line, a double-wire system power distribution system is selected and limited by the structural space of the drone body, a positive bus bar is arranged in an electric control device, and a front equipment cabin and a rear equipment cabin are respectively provided with the negative bus bar, so that the load can be close to the negative conveniently, and the structure and the design flow are simplified; furthermore, through configuring electrical control device to include control integrated circuit board and power integrated circuit board, can realize the control to the distribution through control integrated circuit board and power integrated circuit board, this kind of mode can reduce the inside electromagnetic compatibility influence of equipment, and simple structure has greatly reduced cost and design cycle.
Drawings
The accompanying drawings, which are included to provide a further understanding of the embodiments of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.
FIG. 1 illustrates a functional block diagram of an electric system of a drone provided in accordance with a specific embodiment of the present invention.
Wherein the figures include the following reference numerals:
10. a low voltage DC power supply system; 20. a lithium ion battery pack; 30. a two-wire system power distribution system; 40. an electrical interconnect system.
Detailed Description
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 technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the invention, its application, or uses. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments according to the present application. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, and it should be understood that when the terms "comprises" and/or "comprising" are used in this specification, they specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof, unless the context clearly indicates otherwise.
The relative arrangement of the components and steps, the numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective portions shown in the drawings are not drawn in an actual proportional relationship for the convenience of description. Techniques, methods, and apparatus known to those of ordinary skill in the relevant art may not be discussed in detail but are intended to be part of the specification where appropriate. In all examples shown and discussed herein, any particular value should be construed as merely illustrative, and not limiting. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, further discussion thereof is not required in subsequent figures.
As shown in fig. 1, according to an embodiment of the present invention, there is provided a drone aircraft electrical system, which includes a low-voltage dc power supply system 10, a lithium ion secondary battery pack 20, a two-wire power distribution system 30 and an electrical interconnection system 40, wherein the low-voltage dc power supply system 10 is configured to provide low-voltage dc power to a drone aircraft, the lithium ion secondary battery pack 20 is configured to provide emergency power to the drone aircraft in an emergency situation, the two-wire power distribution system 30 includes an electrical control device, a positive bus bar, a first negative bus bar and a second negative bus bar, the electrical control device is respectively connected with the low-voltage dc power supply system 10 and the lithium ion secondary battery pack 20, the electrical control device is configured to realize power conversion control, power distribution control and direct power distribution between the low-voltage dc power supply system 10 and the lithium ion secondary battery pack 20, the electrical control device includes a control board and a power board, the control board is configured to receive a digital signal on a data bus and convert the digital signal into a switching value, the power board card is used for receiving the switching value transmitted by the control board card and controlling the control board card to carry out power distribution output according to the switching value; the positive bus bar is arranged in the electric control device, and the low-voltage direct-current power supply system 10, the lithium ion storage battery pack 20 and the load are all connected with the positive bus bar; the first negative bus bar is arranged in the first equipment cabin, the second negative bus bar is arranged in the second equipment cabin, the low-voltage direct-current power supply system 10, the lithium ion storage battery pack 20 and the load of the first equipment cabin are all connected with the first negative bus bar, the load of the second equipment cabin is connected with the second negative bus bar, the electrical interconnection system 40 is respectively connected with the double-line system power distribution system 30 and the load, and the electrical interconnection system 40 is used for realizing electric quantity and signal transmission between the double-line system power distribution system 30 and the load.
By applying the configuration mode, the electric system of the target drone is provided, and the electric system of the target drone is provided with a low-voltage direct-current power supply system, a lithium ion storage battery pack, a double-wire system power distribution system and an electric interconnection system, wherein the low-voltage direct-current power supply system and the lithium ion storage battery pack are used for supplying power to a load, the double-wire system power distribution system is used for controlling electric power distributed to the load, and the electric interconnection system is used for realizing electric quantity and signal transmission between the double-wire system power distribution system and the load; in addition, considering that most target drone are made of composite materials, the composite materials are semiconductors, and a drone body cannot be used as a negative line, a double-wire system power distribution system is selected and limited by the structural space of the drone body, a positive bus bar is arranged in an electric control device, and a front equipment cabin and a rear equipment cabin are respectively provided with the negative bus bar, so that the load can be close to the negative conveniently, and the structure and the design flow are simplified; furthermore, through configuring electrical control device to include control integrated circuit board and power integrated circuit board, can realize the control to the distribution through control integrated circuit board and power integrated circuit board, this kind of mode can reduce the inside electromagnetic compatibility influence of equipment, and simple structure has greatly reduced cost and design cycle.
Specifically, in the invention, the control board card comprises a main control chip and an avionic bus circuit, the main control chip is used for processing an avionic bus signal and sending a control signal to the power board card, and the avionic bus circuit is used for receiving the avionic bus signal and transmitting the avionic bus signal to the main control chip.
Further, in the invention, in order to improve the safety of the operation of the devices on the target drone, the control board card may be configured to include a signal driving element and a power distribution switch, the signal driving element is configured to receive a control signal sent by the main control chip and drive the control signal to a high voltage to ensure that the power distribution switch is reliably turned on, the power distribution switch is configured to receive the driving signal output by the signal driving element and control the voltage to be output to a load, and the signal driving element is configured to perform positive redundancy control on power supply to key devices on the target drone, perform positive one-way control on power supply to important devices on the target drone, and perform positive and negative dual redundancy control on hazardous materials on the target drone.
As a specific embodiment of the present invention, the power distribution switch includes a solid state relay and the signal driving element includes an isolation driving module. The design principle of the signal driving element is that the positive redundancy design of power supply is generally carried out on key equipment on the target drone, the positive single-path control of power supply is carried out on important equipment on the target drone, and the positive and negative dual-control redundancy design is carried out on dangerous goods such as initiating explosive devices and the like, so that the safety of an initiating explosive device ignition circuit is improved. Wherein, the key equipment on the target drone generally refers to the equipment of guaranteeing unmanned aerial vehicle flight safety, and important equipment on the target drone generally refers to the equipment of guaranteeing unmanned aerial vehicle executive task.
Further, in the invention, because the positive bus bar is located inside the electrical control device, in order to reduce interference of bus fluctuation on signals, the control board card can be configured to further comprise decoupling capacitors which are arranged on the positive electrode and the negative electrode of the power supply of the avionic bus interface chip of the control board card.
In addition, in the present invention, in order to reduce the interference of the bus fluctuation on the signal, the power board may also be configured to include a first discharge capacitor and a second discharge capacitor, where the first discharge capacitor is disposed on the positive and negative electrodes of the low-voltage dc power supply system 10, and the second discharge capacitor is disposed on the positive and negative electrodes of the lithium-ion battery pack 20. Alternatively, in order to reduce the interference of the bus wave to the signal, the electrical control device may be configured to further include a metal shielding plate, and the metal shielding plate is disposed between the control board card and the power board card.
In order to improve the reliability of power distribution output, in the invention, the electrical control device further comprises an anti-reverse-flow circuit, wherein the anti-reverse-flow circuit is arranged at the input end of the lithium ion storage battery pack 20, so that the current reverse-flow problem caused by a bus switch in a solid output form is prevented, and the reliability of power distribution output is improved.
Further, in the present invention, in order to reduce the cost and simplify the design process, the low voltage dc power supply system 10 may be configured to include a starter generator, a generator control device and a current transformer, the starter generator is used to drive the generator to work, the current transformer is respectively connected to the generator and the generator control device, the current transformer is used to collect the power generation data of the generator, and the generator control device is used to control the output electric quantity of the generator according to the power generation data of the generator; when the generator and the main feeder thereof have ground faults, the current transformer is used for generating pulse voltage proportional to the ground current of the generator and outputting the pulse voltage to the generator control device to protect the generator.
In addition, in the invention, when the low-voltage direct-current power supply system has a fault, the lithium ion storage battery pack can be adopted for emergency power supply. Specifically, in the present invention, considering design cost and simplifying design process, the lithium ion battery pack 20 may be configured to include a plurality of 18650 lithium ion unit cells and a heating circuit module, the heating circuit module is respectively connected to the plurality of 18650 lithium ion unit cells, and the heating circuit module is configured to maintain the temperature of the plurality of 18650 lithium ion unit cells within a set temperature range; the capacity margin of the lithium ion battery pack 20 is 30% of the integral of the load power utilization curve, and the discharge rate of the lithium ion battery pack 20 exceeds 20% of the load power utilization transient peak value.
Further, in the present invention, the primary function of the electrical interconnect system 40 is to connect the various system devices of the drone together as a unit, reliably transmitting commands and signals to coordinate their operations. In the present invention, considering design costs and simplifying the process, the electrical interconnection system 40 can be configured to include cables including WFRA series insulated ultra-flexible wires having a turn radius of only half that of conventional wires and test interfaces. The test interface comprises a bus bar positive and negative interface and a communication bus branch interface, the bus bar positive and negative interface is used for connecting the low-voltage direct-current power supply system 10 and the lithium ion storage battery pack 20, and the communication bus branch interface is used for testing whether the communication of the avionic bus of the drone aircraft is normal. In addition, in the invention, when the cable is installed, the whole machine body structure is fully considered for selecting the separating surface so as to be convenient for subsequent cable production and cable laying as a principle, the selected positions of the separating surface are generally positioned at two sides of the oil tank, the butt joint positions of the left wing and the right wing and the butt joint position of the empennage, and if a certain cable is too complex, the separating surface can be arranged at a proper position so as to be convenient for subsequent processing production.
According to another aspect of the present invention, there is provided a drone comprising a drone electrical system and a load, the drone electrical system being as described above, the drone electrical system being for powering the load.
By applying the configuration mode, the target drone comprises the target drone electrical system, and the target drone electrical system provided by the invention can reduce the cost and the design period on the premise of ensuring the quality of electrical system equipment by designing the low-voltage direct-current power supply system, the lithium ion storage battery pack, the two-wire system power distribution system and the electrical interconnection system, so that the target drone electrical system provided by the invention can be used in the target drone, and the overall performance of the target drone can be ensured to be exerted.
In order to further understand the present invention, the electric system of the drone aircraft provided by the present invention is described in detail below with reference to fig. 1.
As shown in fig. 1, according to an embodiment of the present invention, there is provided a drone aircraft electrical system, which includes a low-voltage dc power supply system 10, a lithium ion secondary battery pack 20, a two-wire power distribution system 30 and an electrical interconnection system 40, wherein the low-voltage dc power supply system 10 is used for supplying low-voltage dc power to a drone aircraft, the lithium ion secondary battery pack 20 is used for supplying emergency power to the drone aircraft in an emergency situation, the two-wire power distribution system 30 is connected to the low-voltage dc power supply system 10 and the lithium ion secondary battery pack 20, respectively, the two-wire power distribution system 30 is used for distributing electric power of the low-voltage dc power supply system 10 and the lithium ion secondary battery pack 20 to a load, the electrical interconnection system 40 is connected to the two-wire power distribution system 30 and the load, in this embodiment, the load includes a flight control system, a recovery system, a fuel system, and a measurement and control system, and the electrical interconnection system 40 is used to transmit electric quantity and signals between the dual-wire system power distribution system 30 and the load.
The low-voltage direct-current power supply system 10 mainly comprises a high-rotation-speed starter generator, a generator control device and a current transformer, wherein the starter generator is used for driving the generator to work, and the rotation speed range of the starter generator is generally 5400r/min to 10000 r/min. The generator control device has the functions of bus bar grounding protection, fault insurance, built-in detection and automatic voltage build-up by secondary start in the air, integrates the functions of voltage regulation, control, protection and the like, and ensures that the equipment has small volume and light weight and has more perfect function through software development. The current transformer is respectively connected with the generator and the generator control device, the current transformer is used for collecting the power generation data of the generator, and the generator control device is used for controlling the output electric quantity of the generator according to the power generation data of the generator; when the generator and the main feeder thereof have ground faults, the current transformer is used for generating pulse voltage proportional to the ground current of the generator and outputting the pulse voltage to the generator control device to protect the generator.
The lithium ion battery pack 20 is configured to include a plurality of 18650 lithium ion battery cells and a warming circuit module, the lithium ion battery cells have the advantages of high specific energy, long service life, less maintenance, short charging time and the like, the nominal voltage is 3.6v, the full-load voltage is 4.2v, and the electricity is considered to be used up when the no-load voltage is discharged to 3.0 v. The number of the battery pack series-parallel single battery packs can be expanded according to the requirement of the actual electricity utilization working condition, the capacity redundancy of the general lithium ion storage battery pack 20 is 30% of the integral of a load electricity utilization curve, and the discharge multiplying power of the lithium ion storage battery pack 20 exceeds 20% of the load electricity utilization transient peak value. The discharge characteristics of the lithium ion battery are greatly influenced by temperature, a heating circuit module needs to be designed in use, the heating circuit module is respectively connected with the 18650 lithium ion single batteries, and the heating circuit module is used for maintaining the temperature of the 18650 lithium ion single batteries within a set temperature range, generally speaking, the temperature of the lithium ion single batteries is 0-25 ℃. The effective capacity of a lithium ion battery increases at low discharge rates and decreases at high discharge rates.
The dual-line power distribution system 30 includes an electrical control device, a positive bus bar, a first negative bus bar, and a second negative bus bar, the electrical control device is connected to the low-voltage dc power supply system 10 and the lithium-ion battery pack 20, and the electrical control device is used to realize power conversion control, control power distribution, and direct power distribution between the low-voltage dc power supply system 10 and the lithium-ion battery pack 20. The positive and negative lines of the double-line system power distribution system 30 are connected to each power supply and electric equipment, the electric control device is usually arranged on a positive circuit and limited by the structural space of the drone aircraft body, the positive bus bar is arranged in the electric control device, and the low-voltage direct-current power supply system 10, the lithium ion storage battery pack 20 and the load are all connected with the positive bus bar; the first negative bus bar is arranged in the first equipment compartment, the second negative bus bar is arranged in the second equipment compartment, the low-voltage direct-current power supply system 10, the lithium ion storage battery pack 20 and the load of the first equipment compartment are all connected with the first negative bus bar, and the load of the second equipment compartment is connected with the second negative bus bar.
In order to reduce the influence of electromagnetic compatibility in equipment, the electrical control device comprises a control board card and a power board card, wherein the control board card is used for receiving digital signals on a data bus and converting the digital signals into switching values to complete self-detection of a power distribution switch, and the power board card is used for receiving the switching values transmitted by the control board card and controlling a control element of the control board card to perform power distribution output according to the switching values. In order to reduce the equipment cost, the power distribution switch is realized by a solid relay. The control board card comprises a main control chip and an avionic bus circuit, the main control chip is used for processing avionic bus signals and sending control signals to the power board card, and the avionic bus circuit is used for receiving the avionic bus signals and transmitting the avionic bus signals to the main control chip. The power integrated circuit board includes signal driver element and distribution switch, signal driver element is used for receiving the control signal that main control chip sent and drives control signal to high-voltage in order to guarantee that distribution switch reliably switches on, distribution switch is used for receiving the drive signal of signal driver element output and control voltage output to the load, signal driver element is used for supplying power just redundant control to the key equipment on the target drone, supply power just single-pass control to the important equipment on the target drone and carry out positive and negative double control redundant control to the hazardous articles on the target drone, with the security that improves priming sytem ignition circuit, signal driver element generally includes keeps apart drive module. Meanwhile, the electrical control device also comprises an anti-reverse-filling circuit which is arranged at the input end of the lithium ion storage battery pack, so that the current reverse-filling problem caused by the adoption of a solid output form of the bus switch is prevented, and the power distribution output reliability is improved.
In addition, because the positive bus bar is positioned in the electrical control device, in order to reduce the interference of bus fluctuation on signals, the electromagnetic compatibility of the product can be improved by adopting the modes of arranging a first leakage capacitor at the positive pole and the negative pole of the low-voltage direct-current power supply system 10, arranging a second leakage capacitor at the positive pole and the negative pole of the lithium ion storage battery pack 20, arranging a metal shielding plate between the control board and the power board, arranging a decoupling capacitor at the positive pole and the negative pole of the avionic bus interface chip power supply of the control board and the like.
The main function of the electrical interconnect system 40 is to connect the various system devices of the drone together and reliably transmit commands and signals to coordinate their operations. In this embodiment, the electrical interconnection system 40 includes a cable and a test interface, and is limited by the space in the cabin of the small and medium target drone, the turning radius of the onboard cable is small, and the cable is preferably made of WFRA series insulated super-flexible wire, and the turning radius of the wire is only half of that of the conventional wire. The test interface comprises a bus bar positive and negative interface and a communication bus branch interface, the bus bar positive and negative interface is used for connecting the low-voltage direct-current power supply system 10 and the lithium ion storage battery pack 20, and the communication bus branch interface is used for testing whether the communication of the avionic bus of the target drone is normal or not, so that the reliable connection of the target drone and ground equipment is facilitated, and the work of target drone testing, software upgrading, technical preparation and the like is completed in a matching manner. In addition, in the invention, when the cable is installed, the whole machine body structure is fully considered for selecting the separating surface so as to be convenient for subsequent cable production and cable laying as a principle, the selected positions of the separating surface are generally positioned at two sides of the oil tank, the butt joint positions of the left wing and the right wing and the butt joint position of the empennage, and if a certain cable is too complex, the separating surface can be arranged at a proper position so as to be convenient for subsequent processing production.
In summary, the present invention provides an electric system of a target drone, which can reduce cost and design period on the premise of ensuring the quality of the electric system equipment by designing a low-voltage dc power supply system, a lithium ion battery pack, a two-wire system power distribution system and an electric interconnection system, and ensure that the overall performance of the target drone is exerted.
In the description of the present invention, it is to be understood that the orientation or positional relationship indicated by the orientation words such as "front, rear, upper, lower, left, right", "lateral, vertical, horizontal" and "top, bottom", etc. are usually based on the orientation or positional relationship shown in the drawings, and are only for convenience of description and simplicity of description, and in the case of not making a reverse description, these orientation words do not indicate and imply that the device or element being referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore, should not be considered as limiting the scope of the present invention; the terms "inner and outer" refer to the inner and outer relative to the profile of the respective component itself.
Spatially relative terms, such as "above … …," "above … …," "above … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial relationship to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if a device in the figures is turned over, devices described as "above" or "on" other devices or configurations would then be oriented "below" or "under" the other devices or configurations. Thus, the exemplary term "above … …" can include both an orientation of "above … …" and "below … …". The device may be otherwise variously oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.
It should be noted that the terms "first", "second", and the like are used to define the components, and are only used for convenience of distinguishing the corresponding components, and the terms have no special meanings unless otherwise stated, and therefore, the scope of the present invention should not be construed as being limited.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. An electric system of a target drone, the electric system of a target drone comprising:
a low voltage DC power supply system (10), the low voltage DC power supply system (10) being configured to provide low voltage DC power to a drone;
a lithium ion battery pack (20), the lithium ion battery pack (20) being used for providing emergency power supply to the target drone in case of emergency;
the double-wire system power distribution system (30), the double-wire system power distribution system (30) comprises an electrical control device, a positive bus bar, a first negative bus bar and a second negative bus bar, the electrical control device is respectively connected with the low-voltage direct-current power supply system (10) and the lithium ion storage battery pack (20), the electrical control device is used for realizing power conversion control, control power distribution and direct power distribution between the low-voltage direct-current power supply system (10) and the lithium ion storage battery pack (20), the electrical control device comprises a control board card and a power board card, the control board card is used for receiving digital signals on a data bus and converting the digital signals into switching values, and the power board card is used for receiving the switching values transmitted by the control board card and controlling the control board card to carry out power distribution output according to the switching values; the positive bus bar is arranged inside the electrical control device, and the low-voltage direct-current power supply system (10), the lithium ion storage battery pack (20) and a load are connected with the positive bus bar; the first negative bus bar is arranged in a first equipment compartment, the second negative bus bar is arranged in a second equipment compartment, the low-voltage direct-current power supply system (10), the lithium-ion storage battery pack (20) and a first equipment compartment load are all connected with the first negative bus bar, and a second equipment compartment load is connected with the second negative bus bar;
the electric interconnection system (40), the electric interconnection system (40) respectively with two-wire system distribution system (30) and load connection, electric interconnection system (40) are used for realizing electric quantity and signal transmission between two-wire system distribution system (30) and the load.
2. The drone electrical system of claim 1, wherein the control board includes a master control chip for completing processing of avionic bus signals and sending control signals to the power board and an avionic bus circuit for completing receipt of avionic bus signals and transmitting the avionic bus signals to the master control chip.
3. The electric system of claim 2, wherein the power board comprises a signal driving element and a power distribution switch, the signal driving element is configured to receive the control signal from the main control chip and drive the control signal to a high voltage to ensure that the power distribution switch is reliably turned on, the power distribution switch is configured to receive the driving signal from the signal driving element and control the voltage to be output to a load, and the signal driving element is configured to perform positive redundancy control on power supply to key devices on the drone aircraft, perform positive one-way control on power supply to important devices on the drone aircraft, and perform positive and negative redundancy control on hazardous materials on the drone aircraft.
4. The drone electrical system of claim 3, wherein the control board further comprises decoupling capacitors disposed on positive and negative poles of an avionics bus interface chip power supply of the control board.
5. The drone electrical system of claim 4, wherein the power board further comprises a first drain capacitor and a second drain capacitor, the first drain capacitor being disposed on the positive and negative poles of the low voltage DC power supply system (10), the second drain capacitor being disposed on the positive and negative poles of the lithium ion battery pack (20); and/or the electric control device further comprises a metal shielding plate, and the metal shielding plate is arranged between the control board card and the power board card.
6. The drone electrical system of claim 1, wherein the electrical control device further comprises an anti-recharge circuit disposed at an input of the lithium ion battery pack (20).
7. The target machine electrical system according to any one of claims 1 to 6, wherein the low voltage DC power supply system (10) comprises a starter generator for driving a generator to operate, a generator control device and a current transformer respectively connected with the generator and the generator control device, the current transformer is used for collecting power generation data of the generator, and the generator control device is used for controlling the output power of the generator according to the power generation data of the generator; when the generator and the main feeder thereof have ground faults, the current transformer is used for generating pulse voltage proportional to the ground current of the generator and outputting the pulse voltage to the generator control device to protect the generator.
8. The target machine electrical system of claim 7, wherein the lithium ion battery pack (20) comprises a plurality of 18650 lithium ion cells and a warming circuit module, the warming circuit module is respectively connected with the plurality of 18650 lithium ion cells, the warming circuit module is used for maintaining the temperature of the plurality of 18650 lithium ion cells in a set temperature range; the capacity redundancy of the lithium ion storage battery pack (20) is 30% of the integral of a load electricity utilization curve, and the discharge multiplying power of the lithium ion storage battery pack (20) exceeds 20% of the load electricity utilization transient peak value.
9. The drone aircraft electrical system of claim 8, wherein the electrical interconnect system (40) includes a cable and a test interface, the cable including WFRA series insulated ultra-flexible wires, the test interface including a bus bar positive and negative interface for connecting the low voltage dc power supply system (10) and the lithium ion battery pack (20) and a communication bus branch interface for testing whether communication of the drone aircraft avionics bus is normal.
10. A drone, characterized in that it comprises a drone electrical system and a load, the drone electrical system being as claimed in any one of claims 1 to 9, the drone electrical system being intended to power the load.
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