CN112478146A - Design method for electrical system of unmanned helicopter - Google Patents
Design method for electrical system of unmanned helicopter Download PDFInfo
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- CN112478146A CN112478146A CN202011429714.6A CN202011429714A CN112478146A CN 112478146 A CN112478146 A CN 112478146A CN 202011429714 A CN202011429714 A CN 202011429714A CN 112478146 A CN112478146 A CN 112478146A
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- 238000013461 design Methods 0.000 title claims abstract description 39
- 238000000034 method Methods 0.000 title claims abstract description 36
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims abstract description 34
- 230000036541 health Effects 0.000 claims abstract description 22
- 238000004891 communication Methods 0.000 claims abstract description 19
- 230000005540 biological transmission Effects 0.000 claims description 11
- 238000005259 measurement Methods 0.000 claims description 6
- 241000251468 Actinopterygii Species 0.000 claims description 3
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 claims description 3
- 239000003990 capacitor Substances 0.000 claims description 3
- 238000001514 detection method Methods 0.000 claims description 3
- 230000010365 information processing Effects 0.000 claims description 3
- 239000007788 liquid Substances 0.000 claims description 3
- 229910052744 lithium Inorganic materials 0.000 claims description 3
- 238000010248 power generation Methods 0.000 claims description 3
- 230000009466 transformation Effects 0.000 claims description 3
- 238000012544 monitoring process Methods 0.000 claims description 2
- 230000003044 adaptive effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000008054 signal transmission Effects 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/24—Transmitting means
- B64C13/38—Transmitting means with power amplification
- B64C13/50—Transmitting means with power amplification using electrical energy
-
- 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
- B64D41/00—Power installations for auxiliary purposes
-
- 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
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
-
- 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
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D2045/0085—Devices for aircraft health monitoring, e.g. monitoring flutter or vibration
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Mechanical Engineering (AREA)
- Automation & Control Theory (AREA)
- Navigation (AREA)
Abstract
The invention provides a design method of an unmanned helicopter electrical system, which comprises an electrical system design method, wherein the electrical system design method comprises a power supply manager, a standby storage battery, a generator and a rectification module, an external power supply, a night navigation lamp, a health management system, a load, a data link communication system, a flight control system, a steering control system and an accelerator steering engine.
Description
Technical Field
The invention relates to the field of unmanned helicopter equipment, in particular to a design method of an unmanned helicopter electrical system.
Background
With the development of adaptive control technology, the adaptive flight of the unmanned helicopter has been widely researched all over the world, the unmanned helicopter has many advantages that the unmanned fixed-wing aircraft does not have, and has unique flight performance and use value, the unmanned helicopter flight control system is a typical nonlinear, strong-coupling, multivariable and multi-drive system, all variables influence the flight attitude, flight direction, flight height and flight speed of the unmanned helicopter, the stable boundary of the unmanned helicopter flight control system is greatly changed along with the change of flight conditions, at present, the small unmanned helicopter is more and more widely applied, various autonomous flight control systems are frequently appeared, but the electrical system is not perfect in architecture, inconvenient to use and single in function.
Disclosure of Invention
The invention aims to provide a design method of an electric system of an unmanned helicopter, aiming at solving the problems in the background technology, and the design method is a general design method of the electric system of the unmanned helicopter during use and can design the electric system according to the overall requirement.
In order to achieve the purpose, the invention is realized by the following technical scheme: a design method of an electric system of an unmanned helicopter comprises an electric system design method, wherein the electric system design method comprises a power supply manager, a standby storage battery, a generator and rectification module, an external power supply, a night navigation lamp, a health management system, a load, a data link communication system, a flight control system, a steering control system and an accelerator steering engine, the electric system design method mainly comprises three parts of a power supply, power transmission and distribution and electric equipment, the power supply and the power transmission and distribution are combined and collectively called as a power supply system, the power supply system has the function of providing electric energy meeting preset design requirements for each electric system or equipment of the airplane, the electric energy comprises enough electric capacity and reliable power transmission and distribution and ensures that the power supply quality meets the requirements, the generator and the rectification module process the generated three-phase alternating current through a rectifier, a filter capacitor and a voltage regulator and then send the three-phase alternating current to a main bus bar, the power supply manager SSPC outputs 28V direct current, wherein the 28V direct current supplies power for a flight control system, a data link communication system, a load, a rudder control system, an accelerator steering engine, a health management system and a night navigation lamp.
As a preferred embodiment of the present invention, the power supply includes a power manager, a backup battery, a generator and rectifier module, and an external power supply, the generator and rectifier module is a main power supply, and the backup battery is an onboard lithium battery.
As a preferred embodiment of the invention, the flight control system comprises a flight control computer, a vertical gyro, an inertial measurement unit, a digital magnetic field machine, an air data sensor, a radio altimeter and a GPS receiver.
In a preferred embodiment of the present invention, the flight control computer is a core of the whole information processing exchange, the GPS receiver provides information such as the position and the velocity of the aircraft to the flight control computer, and the inertial measurement unit provides the attitude information of the aircraft to the flight control computer.
As a preferred embodiment of the invention, the rudder control system comprises a swash plate steering engine 1, a swash plate steering engine 2, a swash plate steering engine 3 and a tail steering engine, the rudder control system adopts a 1-to-4 design, the rudder control system and the flight control system adopt an RS422 communication mode, the steering engine system controls 4 paths of steering engines through PWM signals, the health management system has the functions of signal acquisition and health task management, and the health management system and the flight control system adopt a CAN bus communication mode and CAN monitor the functions of rotating speed, engine temperature, oil quantity surplus and the like in real time.
As a preferred embodiment of the present invention, the power manager mainly includes power generation, power transformation, power distribution, and emergency power sources, the data link communication system (8) includes a C-band and a U-band, the U-band includes a U-wave antenna 1 and a U-wave antenna 2, and the C-band includes a C-wave antenna 1 and a C-wave antenna 2.
As a preferred embodiment of the invention, the load comprises a photoelectric hanging cabin, an SAR, an electric detection system, a fire control system and a fish fork, and the health management system (6) comprises an ECU, a rotating speed, a temperature, a liquid level, a generator start-stop function and a vehicle extinguishing function.
The invention has the beneficial effects that: the invention relates to a design method of an unmanned helicopter electrical system, which comprises a power supply manager; a standby storage battery; a generator and a rectifier module; an external power supply; a night navigation light; a health management system; loading; a data link communication system; a flight control system; a rudder control system; an accelerator steering engine.
1. The design method of the unmanned helicopter electrical system is a design method of a general unmanned helicopter electrical system, the electrical system can be designed according to the overall requirement, the system can reliably work in any flight state, and the average fault interval time can meet the overall requirement of an airplane.
2. The power supply characteristic of the design method of the electric system of the unmanned helicopter meets the requirements of all electric systems; the input of each power utilization system also can not ensure that the power supply characteristic exceeds the regulation of relevant standards or detailed specifications of models, and the signal transmission among the systems on the unmanned aerial vehicle is ensured.
3. According to the design method of the unmanned helicopter electrical system, when a main power supply fails, the power transmission and distribution network ensures that the power supply of emergency electric equipment is ensured, and the power transmission and distribution network ensures that the unmanned helicopter can be powered by an external power supply when in a ground debugging state or a flight preparation state before flight.
Drawings
Fig. 1 is a schematic structural diagram of a power supply and distribution principle of an unmanned helicopter electrical system design method according to the present invention;
FIG. 2 is a schematic structural diagram of a signal system of the method for designing an electrical system of an unmanned helicopter according to the present invention;
in the figure: 1. a power manager; 2. a standby storage battery; 3. a generator and a rectifier module; 4. an external power supply; 5. a night navigation light; 6. a health management system; 7. loading; 8. a data link communication system; 9. a flight control system; 10. a rudder control system; 11. an accelerator steering engine.
Detailed Description
In order to make the technical means, the creation characteristics, the achievement purposes and the effects of the invention easy to understand, the invention is further described with the specific embodiments.
Referring to fig. 1 and fig. 2, the present invention provides a technical solution: a design method for an electric system of an unmanned helicopter comprises the electric system design method and is characterized in that: the design method of the electric system comprises a power supply manager 1, a standby storage battery 2, a generator and rectification module 3, an external power supply 4, a night navigation lamp 5, a health management system 6, a load 7, a data link communication system 8, a flight control system 9, a rudder control system 10 and an accelerator steering engine 11, the design method of the electric system mainly comprises three parts of a power supply, power transmission and distribution and power utilization equipment, the combination of the power supply and the power transmission and distribution is called as a power supply system, the power supply system has the function of providing electric energy meeting the preset design requirements for each power utilization system or equipment of an airplane, the electric energy comprises enough electric capacity and reliable power transmission and distribution and ensures that the power supply quality meets the requirements, the generator and rectification module 3 sends the three-phase alternating current to a main bus bar of the power supply manager 1 after being processed by a rectifier, a filter capacitor and a voltage regulator, and the power supply manager 1SSPC, wherein the 28V direct current supplies power for a flight control system 9, a data link communication system 8, a load 7, a rudder control system 10, an accelerator steering engine 11, a health management system 6 and a night navigation lamp 5.
The electric equipment statistical table is as follows:
| serial number | Electric equipment name | Number of devices | Maximum power consumption (W) | Average power consumption (W) |
| 1 | Flight control system | 1 | ||
| 2 | Data link communication system | 1 | ||
| 3 | |
3 | ||
| 4 | Throttle steering engine | 1 | ||
| 5 | Task load system | 1 | ||
| 6 | Health management system | 1 | ||
| Total up to |
Watch 1
In a preferred embodiment of the present invention, the power supply includes a power manager 1, a backup battery 2, a generator and rectifier module 3, and an external power supply 4, the generator and rectifier module 3 is a main power supply, and the backup battery 2 is an onboard lithium battery.
Power source capacity analysis table-power supply load table is as follows:
watch two
The power capacity analysis-load working time statistical table is as follows:
watch III
As a preferred embodiment of the invention, the flight control system 9 comprises a flight control computer, a vertical gyro, an inertial measurement unit, a digital magnetic field machine, an atmospheric data sensor, a radio altimeter and a GPS receiver.
In a preferred embodiment of the present invention, the flight control computer is a core of the whole information processing exchange, the GPS receiver provides information such as the position and the velocity of the aircraft to the flight control computer, and the inertial measurement unit provides the attitude information of the aircraft to the flight control computer.
As a preferred embodiment of the invention, the rudder control system 10 comprises a swash plate steering engine 1, a swash plate steering engine 2, a swash plate steering engine 3 and a tail steering engine, the rudder control system 10 adopts a 1-to-4 design, the rudder control system 10 and the flight control system 9 adopt an RS422 communication mode, the steering engine system 10 controls 4 paths of steering engines through PWM signals, the health management system 6 has the functions of signal acquisition and health task management, and the health management system 6 and the flight control system 9 adopt a CAN bus communication mode, so that the functions of monitoring the rotating speed, the engine temperature, the oil quantity surplus and the like in real time CAN be realized.
As a preferred embodiment of the present invention, the power manager 1 mainly includes power generation, power transformation, power distribution, and emergency power supply, the data link communication system 8 includes a C-band and a U-band, the U-band includes a U-wave antenna 1 and a U-wave antenna 2, and the C-band includes a C-wave antenna 1 and a C-wave antenna 2.
As a preferred embodiment of the invention, the load 7 comprises a photoelectric hanging cabin, an SAR, an electric detection system, a fire control system and a fish fork, and the health management system 6 comprises an ECU, a rotating speed, a temperature, a liquid level, a generator start-stop function and a vehicle extinguishing function.
While there have been shown and described what are at present considered the fundamental principles and essential features of the invention and its advantages, it will be apparent to those skilled in the art that the invention is not limited to the details of the foregoing exemplary embodiments, but is capable of other specific forms without departing from the spirit or essential characteristics thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.
Furthermore, it should be understood that although the present description refers to embodiments, not every embodiment may contain only a single embodiment, and such description is for clarity only, and those skilled in the art should integrate the description, and the embodiments may be combined as appropriate to form other embodiments understood by those skilled in the art.
Claims (7)
1. A design method for an electric system of an unmanned helicopter comprises the electric system design method and is characterized in that: the design method of the electric system comprises a power supply manager (1), a standby storage battery (2), a generator and rectification module (3), an external power supply (4), a night navigation lamp (5), a health management system (6), a load (7), a data link communication system (8), a flight control system (9), a rudder control system (10) and an accelerator steering engine (11), the design method of the electric system mainly comprises three parts of a power supply, power transmission and distribution and electric equipment, the power supply and the power transmission and distribution are combined to be a power supply system, the power supply system has the function of providing electric energy meeting the preset design requirements for each electric system or equipment of an airplane, the electric energy comprises enough electric capacity and reliable power transmission and distribution and ensures that the power supply quality meets the requirements, the generator and rectification module (3) sends the generated three-phase alternating current to a main bus bar of the power supply manager (1) after being processed by a rectifier, a filter capacitor and a voltage, the power supply manager (1) SSPC outputs 28V direct current, wherein the 28V direct current supplies power for the flight control system (9), the data link communication system (8), the load (7), the rudder control system (10), the accelerator steering engine (11), the health management system (6) and the night navigation lamp (5).
2. The method of claim 2, wherein the method further comprises: the power supply comprises a power supply manager (1), a standby storage battery (2), a generator and rectification module (3) and an external power supply (4), the generator and rectification module (3) is a main power supply, and the standby storage battery (2) is an onboard lithium battery.
3. The design method of the electric system of the unmanned helicopter of claim 1, characterized in that: the flight control system (9) comprises a flight control computer, a vertical gyro, an inertial measurement unit, a digital magnetic field machine, an atmospheric data sensor, a radio altimeter and a GPS receiver.
4. The design method of the electric system of the unmanned helicopter of claim 1, characterized in that: the flight control computer is the core of the whole information processing and exchanging, the GPS receiver provides the position, the speed and other information of the airplane to the flight control computer, and the inertial measurement unit provides the attitude information of the airplane to the flight control computer.
5. The design method of the electric system of the unmanned helicopter of claim 1, characterized in that: the steering control system (10) comprises a swash plate steering engine 1, a swash plate steering engine 2, a swash plate steering engine 3 and a tail steering engine, the steering control system (10) adopts a 1-to-4 design, the steering control system (10) and a flight control system (9) adopt an RS422 communication mode, the steering engine system (10) controls 4 paths of steering engines through PWM signals, the health management system (6) has the functions of signal acquisition and health task management, the health management system (6) and the flight control system (9) adopt a CAN bus communication mode, and the functions of monitoring the rotating speed, the engine temperature, the oil quantity residue and the like in real time are achieved.
6. The design method of the electric system of the unmanned helicopter of claim 1, characterized in that: the power supply manager (1) mainly comprises a power generation, power transformation, power distribution and emergency power supply, the data link communication system (8) comprises a C wave band and a U wave band, the U wave band comprises a U wave antenna 1 and a U wave antenna 2, and the C wave band comprises a C wave antenna 1 and a C wave antenna 2.
7. The design method of the electric system of the unmanned helicopter of claim 1, characterized in that: the load (7) comprises a photoelectric hanging cabin, an SAR, an electric detection system, a fire control system and a fish fork, and the health management system (6) comprises an ECU, a rotating speed, a temperature, a liquid level, a generator start-stop function and a vehicle extinguishing function.
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| CN202011429714.6A CN112478146A (en) | 2020-12-09 | 2020-12-09 | Design method for electrical system of unmanned helicopter |
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| CN202011429714.6A CN112478146A (en) | 2020-12-09 | 2020-12-09 | Design method for electrical system of unmanned helicopter |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114056553A (en) * | 2021-12-03 | 2022-02-18 | 航天神舟飞行器有限公司 | Medium-sized freight unmanned helicopter system |
| CN114069831A (en) * | 2021-12-02 | 2022-02-18 | 北京机电工程研究所 | Aircraft power supply voltage stabilization power supply control method |
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| CN114069831A (en) * | 2021-12-02 | 2022-02-18 | 北京机电工程研究所 | Aircraft power supply voltage stabilization power supply control method |
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| CN114056553A (en) * | 2021-12-03 | 2022-02-18 | 航天神舟飞行器有限公司 | Medium-sized freight unmanned helicopter system |
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