CN113532202B - 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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- CN113532202B CN113532202B CN202010294346.2A CN202010294346A CN113532202B CN 113532202 B CN113532202 B CN 113532202B CN 202010294346 A CN202010294346 A CN 202010294346A CN 113532202 B CN113532202 B CN 113532202B
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- lithium ion
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- battery pack
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- 229910001416 lithium ion Inorganic materials 0.000 claims abstract description 75
- HBBGRARXTFLTSG-UHFFFAOYSA-N Lithium ion Chemical compound [Li+] HBBGRARXTFLTSG-UHFFFAOYSA-N 0.000 claims abstract description 72
- 238000009826 distribution Methods 0.000 claims abstract description 65
- 238000003860 storage Methods 0.000 claims abstract description 36
- 239000003990 capacitor Substances 0.000 claims description 20
- 238000012360 testing method Methods 0.000 claims description 13
- 238000004891 communication Methods 0.000 claims description 9
- 238000010248 power generation Methods 0.000 claims description 8
- 230000005611 electricity Effects 0.000 claims description 6
- 238000012545 processing Methods 0.000 claims description 6
- 230000008054 signal transmission Effects 0.000 claims description 6
- 229910052751 metal Inorganic materials 0.000 claims description 5
- 239000002184 metal Substances 0.000 claims description 5
- 239000007858 starting material Substances 0.000 claims description 5
- 238000006243 chemical reaction Methods 0.000 claims description 4
- 230000001052 transient effect Effects 0.000 claims description 4
- 238000010792 warming Methods 0.000 claims description 4
- 238000013461 design Methods 0.000 abstract description 21
- 238000011161 development Methods 0.000 abstract description 4
- 238000012938 design process Methods 0.000 abstract description 2
- 238000010438 heat treatment Methods 0.000 description 8
- 230000002265 prevention Effects 0.000 description 6
- 239000002131 composite material Substances 0.000 description 4
- 210000001503 joint Anatomy 0.000 description 4
- 238000004519 manufacturing process Methods 0.000 description 4
- 239000002360 explosive Substances 0.000 description 3
- 230000000977 initiatory effect Effects 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 239000007787 solid Substances 0.000 description 3
- 238000001514 detection method Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 239000004065 semiconductor Substances 0.000 description 2
- 238000012549 training Methods 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 230000033228 biological regulation Effects 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000014509 gene expression Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
Classifications
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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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
- B64D47/02—Arrangements or adaptations of signal or lighting devices
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Charge And Discharge Circuits For Batteries Or The Like (AREA)
Abstract
The application provides an electric system of a target aircraft and the target aircraft with the same, the system comprises a low-voltage direct-current power supply system, a lithium ion storage battery pack, a two-wire system power distribution system and an electric interconnection system, the two-wire system power distribution system comprises an electric control device, a positive bus bar, a first negative bus bar and a second negative bus bar, the electric control device is respectively connected with the low-voltage direct-current power supply system and the lithium ion storage battery pack, the electric 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 perform power distribution output according to the switching values, and the electric interconnection system is respectively connected with the two-wire system power distribution system and a load. By applying the technical scheme of the application, the technical problems of high development cost and complex design process caused by adopting the design flow of the electrical system of the military aircraft to design the target aircraft in the prior art are solved.
Description
Technical Field
The application relates to the technical field of small and medium-sized drones, in particular to a drone electrical system and a drone with the same.
Background
The target drone is used as one of unmanned aircrafts, is mainly used for simulating threat targets such as fighter planes, missiles and the like, and provides a realistic air target for weapon system test and training. The target aircraft electrical system is responsible for receiving an upper computer instruction, supplying power to each system on the aircraft according to a time sequence, and ensuring that the power supply quality meets the requirements of loads on the aircraft. Thus, the design of the electrical system plays a critical role in the target machine performing its intended function.
The target drone is mainly used for combat readiness training, is directly scrapped after knockdown, and belongs to consumables. In recent years, with the continuous advent of new weapon systems, troops consume more than 3000 frames of various targets each year. The electric system is used as an important guarantee of all systems of the whole unmanned aerial vehicle, and the structural design of the electric system influences the overall performance of the unmanned aerial vehicle. If the target aircraft is designed according to the design flow of the electric system of the military aircraft, the development cost and the development period of the electric system of the target aircraft are increased, and the cost of the military aircraft is greatly increased.
Disclosure of Invention
The application provides a target drone electrical system and a target drone with the same, which can solve the technical problems of high development cost and complex design process caused by designing the target drone by adopting a military aircraft electrical system design flow in the prior art.
According to an aspect of the present application, there is provided a target 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 pack is used for providing emergency power supply for the target aircraft under emergency conditions; the double-wire system power distribution system comprises an electric control device, a positive bus bar, a first negative bus bar and a second negative bus bar, wherein the electric control device is respectively connected with the low-voltage direct-current power supply system and the lithium ion storage battery pack, the electric control device is used for realizing power conversion control, power distribution control and direct power distribution between the low-voltage direct-current power supply system and the lithium ion storage battery pack, the electric 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 perform 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 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, the lithium ion storage battery pack and the first equipment cabin load are all connected with the first negative bus bar, and the second equipment cabin load is connected with the second negative bus bar; and the electric interconnection system is respectively connected with the two-wire system power distribution system and the load and is used for realizing electric quantity and signal transmission between the two-wire system power distribution system and the load.
Further, the control board card comprises a main control chip and an avionic bus circuit, wherein the main control chip is used for completing the processing of avionic bus signals and sending control signals to the power board card, and the avionic bus circuit is used for completing the receiving of the avionic bus signals and transmitting the avionic bus signals to the main control chip.
Further, the power board card comprises a signal driving element and a power distribution switch, wherein the signal driving element is used for receiving a control signal sent by the main control chip and driving the control signal to high voltage so as 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 voltage output to a load, and the signal driving element is used for carrying out power supply positive redundancy control on key equipment on the target drone, power supply positive single-way control on the important equipment on the target drone and positive and negative double-control redundancy control on dangerous articles on the target drone.
Further, the control board card also comprises a decoupling capacitor, and the decoupling capacitor is arranged at the anode and the cathode of the avionics bus interface chip power supply of the control board card.
Further, the power board card further comprises a first discharge capacitor and a second discharge capacitor, wherein the first discharge capacitor is arranged at the positive electrode and the negative electrode of the low-voltage direct-current power supply system, and the second discharge capacitor is arranged at 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 arranged between the control board card and the power board card.
Further, the electric control device further comprises a reverse-filling prevention circuit, and the reverse-filling prevention circuit 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 line thereof have ground faults, the current transformer is used for generating pulse voltage which is proportional to the ground current of the generator and outputting the pulse voltage to the generator control device so as to protect the generator.
Further, 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 the heating circuit module is used for maintaining the temperatures of the plurality of 18650 lithium ion single batteries in a set temperature range; the capacity redundancy of the lithium ion storage battery pack is 30% of the integral of the load electricity consumption curve, and the discharge rate of the lithium ion storage battery pack exceeds 20% of the load electricity consumption transient state peak value.
Further, the electrical interconnection system comprises a cable and a test interface, wherein the cable comprises WFRA series insulated super-soft wires, the test interface comprises a bus positive interface and a bus branch interface, the bus positive interface and the bus positive interface are used for connecting a low-voltage direct-current power supply system and a lithium ion storage battery pack, and the bus branch interface is used for testing whether communication of a target aircraft avionics bus is normal or not.
According to another aspect of the present application there is provided a drone comprising a drone electrical system as described above and a load, the drone electrical system being for powering the load.
By means of the technical scheme, the target aircraft electrical system is provided, and the low-voltage direct-current power supply system, the lithium ion storage battery pack, the double-wire system power distribution system and the electrical interconnection system are arranged, so that 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, the electrical interconnection system is used for realizing electric quantity and signal transmission between the double-wire system power distribution system and the load, the system constitution can be simplified on the premise that the equipment quality of the electrical system is guaranteed, and cost and design period are reduced; in addition, the target aircraft is mostly made of a composite material, the composite material is a semiconductor, and the machine body cannot be used as a negative line, so that a double-wire power distribution system is selected and used, the positive bus bar is limited by the structural space of the machine body of the target aircraft, the positive bus bar is arranged in the electric control device, and the negative bus bars are respectively arranged in the front equipment cabin and the rear equipment cabin, so that the load is conveniently and closely connected with the negative bus bar, and the structure and the design flow are simplified; moreover, through configuring the electric control device to include control panel card and power board card, can realize the control to the distribution through control panel card and power board card, this kind of mode can reduce the inside electromagnetic compatibility influence of equipment, simple structure has greatly reduced cost and design cycle.
Drawings
The accompanying drawings, which are included to provide a further understanding of embodiments of the application and are incorporated in and constitute a part of this specification, illustrate embodiments of the application and together with the description serve to explain the principles of the application. It is evident that the drawings in the following description are only some embodiments of the present application and that other drawings may be obtained from these drawings without inventive effort for a person of ordinary skill in the art.
Fig. 1 shows a functional block diagram of a target aircraft electrical system provided in accordance with an embodiment of the application.
Wherein the above 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, without conflict, the embodiments of the present application and features of the embodiments may be combined with each other. The following description of the embodiments of the present application will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present application, but not all embodiments. The following description of at least one exemplary embodiment is merely exemplary in nature and is in no way intended to limit the application, its application, or uses. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.
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 exemplary embodiments according to the present application. As used herein, the singular is also intended to include the plural unless the context clearly indicates otherwise, and furthermore, it is to be understood that the terms "comprises" and/or "comprising" when used in this specification are taken to specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof.
The relative arrangement of the components and steps, numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present application unless it is specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective parts shown in the drawings are not drawn in actual scale for convenience of description. Techniques, methods, and apparatus known to one of ordinary skill in the relevant art may not be discussed in detail, but should be considered part of the specification where appropriate. In all examples shown and discussed herein, any specific values should be construed as merely illustrative, and not a limitation. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numerals and letters denote like items in the following figures, and thus once an item is defined in one figure, no further discussion thereof is necessary in subsequent figures.
As shown in fig. 1, according to an embodiment of the present application, there is provided a target electric system including a low voltage dc power supply system 10, a lithium ion battery pack 20, a two-wire power distribution system 30, and an electric interconnection system 40, the low voltage dc power supply system 10 for supplying low voltage dc power to the target, the lithium ion battery pack 20 for supplying emergency power to the target in an emergency situation, the two-wire power distribution system 30 including an electric control device, a positive bus bar, a first negative bus bar, and a second negative bus bar, the electric control device being connected to the low voltage dc power supply system 10 and the lithium ion battery pack 20, respectively, the electric control device for performing power conversion, control distribution, and direct distribution between the low voltage dc power supply system 10 and the lithium ion battery pack 20, the electric control device including a control board card for receiving digital signals on the data bus and converting the digital signals into switching amounts, and a power board card for receiving switching amounts transmitted by the cards and controlling the control board card to perform power distribution output according to the switching amounts; 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 first equipment cabin load are all connected with the first negative bus bar, the second equipment cabin load is connected with the second negative bus bar, the electrical interconnection system 40 is respectively connected with the two-wire 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 two-wire system power distribution system 30 and the load.
By means of the configuration mode, the target aircraft electrical system is provided, and the low-voltage direct-current power supply system, the lithium ion storage battery pack, the double-wire system power distribution system and the electrical interconnection system are arranged, so that 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, the electrical interconnection system is used for realizing electric quantity and signal transmission between the double-wire system power distribution system and the load, the system constitution can be simplified on the premise that the equipment quality of the electrical system is guaranteed, and cost and design period are reduced; in addition, the target aircraft is mostly made of a composite material, the composite material is a semiconductor, and the machine body cannot be used as a negative line, so that a double-wire power distribution system is selected and used, the positive bus bar is limited by the structural space of the machine body of the target aircraft, the positive bus bar is arranged in the electric control device, and the negative bus bars are respectively arranged in the front equipment cabin and the rear equipment cabin, so that the load is conveniently and closely connected with the negative bus bar, and the structure and the design flow are simplified; moreover, through configuring the electric control device to include control panel card and power board card, can realize the control to the distribution through control panel card and power board card, this kind of mode can reduce the inside electromagnetic compatibility influence of equipment, simple structure has greatly reduced cost and design cycle.
Specifically, in the application, the control board comprises a main control chip and an avionic bus circuit, wherein the main control chip is used for completing the processing of avionic bus signals and sending control signals to the power board, and the avionic bus circuit is used for completing the receiving of avionic bus signals and transmitting the avionic bus signals to the main control chip.
Further, in order to improve the safety of the operation of the equipment on the target aircraft, the control board card can be configured to comprise a signal driving element and a power distribution switch, wherein 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 so as 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 carrying out power supply forward redundancy control on key equipment on the target aircraft, power supply forward one-way control on the important equipment on the target aircraft and positive and negative double control redundancy control on dangerous articles on the target aircraft.
As a specific embodiment of the application, the power distribution switch comprises a solid state relay and the signal driving element comprises an isolated driving module. The design principle of the signal driving element is generally to perform power supply positive redundancy design on key equipment on the target aircraft, perform power supply positive single-path control on the important equipment on the target aircraft, and perform positive and negative double-control redundancy design on dangerous articles such as initiating explosive devices so as to improve the safety of an initiating explosive device ignition circuit. The key equipment on the target plane generally refers to equipment for ensuring the flight safety of the unmanned aerial vehicle, and the important equipment on the target plane generally refers to equipment for ensuring the unmanned aerial vehicle to execute tasks.
Further, in the application, since 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 a decoupling capacitor, and the decoupling capacitor is arranged at the positive electrode and the negative electrode of the avionics bus interface chip power supply of the control board card.
In addition, in order to reduce the interference of bus fluctuation on signals, the power board card can also be configured to comprise a first bleeder capacitor and a second bleeder capacitor, wherein the first bleeder capacitor is arranged at the positive electrode and the negative electrode of the low-voltage direct-current power supply system 10, and the second bleeder capacitor is arranged at the positive electrode and the negative electrode of the lithium ion storage battery pack 20. Alternatively, in order to reduce interference of bus fluctuation with signals, the electrical control device may also be configured to further include a metal shielding plate disposed between the control board card and the power board card.
In order to improve the reliability of the distribution output, in the application, the electric control device further comprises a reverse-filling prevention circuit, wherein the reverse-filling prevention circuit is arranged at the input end of the lithium ion storage battery pack 20, so that the problem of reverse filling of current caused by a bus switch in a solid output form is prevented, and the reliability of the distribution output is improved.
Further, in the present application, in order to reduce the cost and simplify the design flow, the low-voltage dc power supply system 10 may be configured to include a starter generator for driving the generator to operate, a generator control device and a current transformer connected to the generator and the generator control device, respectively, the current transformer being used for collecting the power generation data of the generator, the generator control device being 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 line thereof have ground faults, the current transformer is used for generating pulse voltage which is proportional to the ground current of the generator and outputting the pulse voltage to the generator control device so as to protect the generator.
In addition, in the application, when the low-voltage direct-current power supply system fails, the lithium ion storage battery pack can be used for emergency power supply. Specifically, in the present application, considering design cost and simplified design flow, the lithium ion battery pack 20 may be configured to include a plurality of 18650 lithium ion battery cells and a heating circuit module, where the heating circuit module is respectively connected to the plurality of 18650 lithium ion battery cells, and the heating circuit module is used to maintain the temperatures of the plurality of 18650 lithium ion battery cells in a set temperature range; the capacity redundancy of the lithium ion battery pack 20 is 30% of the integral of the load electricity consumption curve, and the discharge rate of the lithium ion battery pack 20 exceeds 20% of the load electricity consumption transient peak value.
Further, in the present application, the main function of the electrical interconnection system 40 is to connect the various system devices on the target machine together in a unit, and reliably transmit commands and signals to coordinate them. In the present application, electrical interconnect system 40 may be configured to include cables and test interfaces, the cables including WFRA series insulated ultra-flexible wires having a turn radius of only half that of conventional wires, in view of design costs and simplified flow. The test interface comprises a bus positive and negative interface and a communication bus branch interface, wherein the bus 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 avionics bus of the target aircraft is normal. In addition, in the application, when the cable is installed, the whole machine body structure is fully considered in the selection of the separating surface so as to be convenient for the subsequent cable production and cable laying as a principle, the selected position of the separating surface is generally positioned at the two sides of the oil tank, the butt joint positions of the left wing and the right wing and the butt joint positions of the tail wings, and in addition, if a certain cable is too complicated, the separating surface can be arranged at a proper position so as to be convenient for the subsequent processing production.
According to another aspect of the present application there is provided a drone comprising a drone electrical system as described above and a load, the drone electrical system being for powering the load.
By applying the configuration mode, the target aircraft comprises the target aircraft electrical system, and the cost and the design period can be reduced on the premise of ensuring the equipment quality of the electrical system by designing the low-voltage direct-current power supply system, the lithium ion storage battery pack, the two-wire power distribution system and the electrical interconnection system, so that the whole performance of the target aircraft can be ensured to be exerted by using the target aircraft electrical system in the target aircraft.
For a further understanding of the present application, a detailed description of the target aircraft electrical system provided by the present application is provided below in connection with fig. 1.
As shown in fig. 1, according to an embodiment of the present application, there is provided an electrical system for a target aircraft, the electrical system for a target aircraft including a low voltage dc power supply system 10, a lithium ion battery pack 20, a two-wire power distribution system 30 and an electrical interconnection system 40, the low voltage dc power supply system 10 being configured to supply low voltage dc power to the target aircraft, the lithium ion battery pack 20 being configured to supply emergency power to the target aircraft in an emergency situation, the two-wire power distribution system 30 being connected to the low voltage dc power supply system 10 and the lithium ion battery pack 20, respectively, the two-wire power distribution system 30 being configured to distribute electrical power from the low voltage dc power supply system 10 and the lithium ion battery pack 20 to a load, the electrical interconnection system 40 being connected to the two-wire power distribution system 30 and the load, respectively, in this embodiment, the load including a flight control system, a recovery system, a fuel system and a measurement and control system, the electrical interconnection system 40 being configured to enable power and signal transmission between the two-wire 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 of the starter generator is generally in the range of 5400r/min to 10000r/min. The generator control device has the functions of bus bar grounding protection, fault protection, in-machine detection and automatic voltage establishment for secondary air starting, integrates the functions of voltage regulation, control, protection and the like, and has the advantages of small equipment size, light weight and 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 line thereof have ground faults, the current transformer is used for generating pulse voltage which is proportional to the ground current of the generator and outputting the pulse voltage to the generator control device so as 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, where the lithium ion battery cells have the advantages of high specific energy, long life, less maintenance, short charging time, etc., the nominal voltage is 3.6v, the full charge voltage is 4.2v, and it is generally considered that the power is exhausted when the no-load voltage is placed at 3.0 v. The number of the series-parallel single battery packs of the battery pack can be expanded according to the requirement of the actual power utilization working condition, the capacity redundancy of the lithium ion battery pack 20 is generally 30% of the integral of the load power utilization curve, and the discharge multiplying power of the lithium ion battery pack 20 exceeds 20% of the load power utilization transient peak value. The discharge characteristic of the lithium ion battery is greatly affected by temperature, a heating circuit module is required to be designed in use and is respectively connected with a plurality of 18650 lithium ion single batteries, the heating circuit module is used for maintaining the temperature of the 18650 lithium ion single batteries in a set temperature range, and generally, the temperature of the lithium ion single batteries is between 0 ℃ and 25 ℃. The effective capacity of lithium ion batteries increases at low discharge rates and decreases at high discharge rates.
The two-wire system power distribution system 30 comprises an electric control device, a positive bus bar, a first negative bus bar and a second negative bus bar, wherein the electric control device is respectively connected with the low-voltage direct-current power supply system 10 and the lithium ion storage battery pack 20, and is used for realizing power conversion control, power distribution control and direct power distribution between the low-voltage direct-current power supply system 10 and the lithium ion storage battery pack 20. Positive and negative wires of the two-wire system power distribution system 30 are connected to each power supply and electric equipment, an electric control device is usually arranged on a positive circuit and limited by the structural space of a target aircraft body, a positive bus bar is arranged in the electric control device, and the low-voltage direct-current power supply system 10, the lithium ion battery pack 20 and a load are 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 first equipment cabin load are all connected with the first negative bus bar, and the second equipment cabin load is connected with the second negative bus bar.
In order to reduce the electromagnetic compatibility influence inside the equipment, the electric 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, the self-detection of the power distribution switch is completed, 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 equipment cost, the distribution switch is realized by using a solid relay. The control board card comprises a main control chip and an avionic bus circuit, wherein the main control chip is used for completing the processing of avionic bus signals and sending control signals to the power board card, and the avionic bus circuit is used for completing the receiving of the avionic bus signals and transmitting the avionic bus signals to the main control chip. The power board card comprises a signal driving element and a power distribution switch, wherein the signal driving element is used for receiving a control signal sent by a main control chip and driving the control signal to high voltage so as 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, the signal driving element is used for carrying out power supply positive redundancy control on key equipment on a target aircraft, carrying out power supply positive one-way control on important equipment on the target aircraft and carrying out positive and negative double control redundancy control on dangerous articles on the target aircraft so as to improve the safety of an initiating explosive device ignition circuit, and the signal driving element generally comprises an isolation driving module. Meanwhile, the electric control device further comprises a reverse-filling prevention circuit, the reverse-filling prevention circuit is arranged at the input end of the lithium ion storage battery pack, the current reverse-filling problem caused by the fact that a bus switch adopts a solid-state output mode is prevented, and the distribution output reliability is improved.
In addition, because the positive bus bar is positioned in the electric control device, in order to reduce the interference of bus fluctuation on signals, the method of arranging a first discharge capacitor at the positive electrode and the negative electrode of the low-voltage direct-current power supply system 10, arranging a second discharge capacitor at the positive electrode and the negative electrode of the lithium ion storage battery pack 20, arranging a metal shielding plate between the control board card and the power board card, arranging a decoupling capacitor at the positive electrode and the negative electrode of the avionics bus interface chip power supply of the control board card and the like can be adopted, so that the electromagnetic compatibility of products is improved.
The primary function of the electrical interconnect system 40 is to connect the various system devices on the drone together in a unit, reliably transmitting commands and signals to coordinate their operation. In this embodiment, the electrical interconnect system 40 includes cables and test interfaces, limited by space in the medium and small target cabins, with small on-board cable turning radii, preferably WFRA series insulated ultra-flexible wires with turning radii that are only half of conventional wires. The test interface comprises a bus positive and negative interface and a communication bus branch interface, wherein the bus 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, the communication bus branch interface is used for testing whether communication of the aerial electric bus of the target aircraft is normal or not, the target aircraft is convenient to reliably connect with ground equipment, and work such as target aircraft test, software upgrading and technical preparation is completed in a matched mode. In addition, in the application, when the cable is installed, the whole machine body structure is fully considered in the selection of the separating surface so as to be convenient for the subsequent cable production and cable laying as a principle, the selected position of the separating surface is generally positioned at the two sides of the oil tank, the butt joint positions of the left wing and the right wing and the butt joint positions of the tail wings, and in addition, if a certain cable is too complicated, the separating surface can be arranged at a proper position so as to be convenient for the subsequent processing production.
In summary, the application provides a target aircraft electrical system, which is designed for a low-voltage direct-current power supply system, a lithium ion battery pack, a two-wire power distribution system and an electrical interconnection system, so that the cost and the design period can be reduced on the premise of ensuring the quality of electrical system equipment, and the overall performance of the target aircraft can be ensured.
In the description of the present application, it should be understood that the azimuth or positional relationships indicated by the azimuth terms such as "front, rear, upper, lower, left, right", "lateral, vertical, horizontal", and "top, bottom", etc., are generally based on the azimuth or positional relationships shown in the drawings, merely to facilitate description of the present application and simplify the description, and these azimuth terms do not indicate and imply that the apparatus or elements referred to must have a specific azimuth or be constructed and operated in a specific azimuth, and thus should not be construed as limiting the scope of protection of the present application; the orientation word "inner and outer" refers to inner and outer relative to the contour of the respective component itself.
Spatially relative terms, such as "above … …," "above … …," "upper surface at … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial location relative 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 in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "above" or "over" other devices or structures would then be oriented "below" or "beneath" the other devices or structures. Thus, the exemplary term "above … …" may include both orientations of "above … …" and "below … …". The device may also be positioned in other different ways (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.
In addition, the terms "first", "second", etc. are used to define the components, and are only for convenience of distinguishing the corresponding components, and the terms have no special meaning unless otherwise stated, and therefore should not be construed as limiting the scope of the present application.
The above description is only of the preferred embodiments of the present application and is not intended to limit the present application, but various modifications and variations can be made to the present application by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application should be included in the protection scope of the present application.
Claims (10)
1. A drone electrical system, the drone electrical system 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 the drone;
a lithium ion battery (20), the lithium ion battery (20) being configured to provide emergency power to the drone in an emergency situation;
the system comprises a two-wire power distribution system (30), wherein the two-wire power distribution system (30) comprises an electric control device, a positive bus bar, a first negative bus bar and a second negative bus bar, the electric control device is respectively connected with the low-voltage direct-current power supply system (10) and the lithium ion storage battery pack (20), the electric control device is used for realizing power conversion control, power distribution control and direct power distribution between the low-voltage direct-current power supply system (10) and the lithium ion storage battery pack (20), the electric 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 perform 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 (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 in the first equipment cabin are all connected with the first negative bus bar, and the load in the second equipment cabin is connected with the second negative bus bar;
and the electrical interconnection system (40) is respectively connected with the two-wire 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 two-wire system power distribution system (30) and the load.
2. The drone electrical system of claim 1, wherein the control board card includes a main control chip for completing processing of avionics bus signals and sending control signals to the power board card, and avionics bus circuitry for completing receipt of avionics bus signals and transmitting the avionics bus signals to the main control chip.
3. The target aircraft electrical system of claim 2, wherein 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 so as to ensure reliable conduction of the power distribution switch, the power distribution switch is used for receiving a driving signal output by the signal driving element and controlling voltage output to a load, and the signal driving element is used for performing power supply positive redundancy control on key equipment on the target aircraft, power supply positive single-way control on important equipment on the target aircraft and positive and negative double-control redundancy control on dangerous articles on the target aircraft.
4. The drone electrical system of claim 3, wherein the control board card further comprises a decoupling capacitor disposed at an anode and a cathode of an avionics bus interface chip power supply of the control board card.
5. The drone electrical system of claim 4, wherein the power board card further comprises a first bleed capacitor and a second bleed capacitor, the first bleed capacitor being disposed at the positive and negative poles of the low voltage dc power supply system (10), the second bleed capacitor being disposed at the positive and negative poles of the lithium ion battery pack (20); and/or the electrical control device further comprises a metal shielding plate, wherein 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-reverse-fill circuit disposed at an input of the lithium ion battery pack (20).
7. The target aircraft electrical system according to any one of claims 1 to 6, wherein the low voltage direct current power supply system (10) comprises a starter generator for driving a generator to operate, a generator control device and a current transformer connected to the generator and the generator control device, respectively, the current transformer being used for collecting power generation data of the generator, the generator control device being 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 line thereof have ground faults, the current transformer is used for generating pulse voltage which is proportional to the ground current of the generator and outputting the pulse voltage to the generator control device so as to protect the generator.
8. The drone electrical system of claim 7, wherein the lithium ion battery pack (20) includes a plurality of 18650 lithium ion cells and a warming circuit module, the warming circuit module being respectively connected to the plurality of 18650 lithium ion cells, the warming circuit module being configured to maintain temperatures 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 the load electricity consumption curve, and the discharge multiplying power of the lithium ion storage battery pack (20) exceeds 20% of the load electricity consumption transient state peak value.
9. The drone electrical system of claim 8, wherein the electrical interconnect system (40) includes a cable including a WFRA series insulated ultra-flexible wire and a test interface including a bus bar positive and negative interface for connecting the low voltage dc power system (10) and the lithium ion battery pack (20) and a communication bus branch interface for testing whether communication of the drone avionics bus is normal.
10. A drone comprising 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 for powering the load.
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