CN110979706A - Dual-voltage helicopter power supply system - Google Patents
Dual-voltage helicopter power supply system Download PDFInfo
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- CN110979706A CN110979706A CN201910963106.4A CN201910963106A CN110979706A CN 110979706 A CN110979706 A CN 110979706A CN 201910963106 A CN201910963106 A CN 201910963106A CN 110979706 A CN110979706 A CN 110979706A
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- 238000012423 maintenance Methods 0.000 claims description 10
- 238000010586 diagram Methods 0.000 description 4
- 230000033228 biological regulation Effects 0.000 description 2
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- 230000009286 beneficial effect Effects 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
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Classifications
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- 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
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J9/00—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting
- H02J9/04—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source
- H02J9/06—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source with automatic change-over, e.g. UPS systems
- H02J9/061—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source with automatic change-over, e.g. UPS systems for DC powered loads
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- 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
- B64D2221/00—Electric power distribution systems onboard aircraft
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- Emergency Management (AREA)
- Power Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Stand-By Power Supply Arrangements (AREA)
Abstract
The embodiment of the invention provides a double-voltage helicopter power supply system, which comprises: the system comprises a first power supply system and a second power supply system, wherein the first power supply system comprises a first generator, a first contactor, a generator controller, a first emergency bus bar and an equipment bus bar, and the second power supply system comprises a second generator and a second emergency bus bar; the first generator is connected to a first emergency bus bar through a first contactor, the first emergency bus bar is connected to an equipment bus bar, and the second generator is connected to a second emergency bus bar; the first generator provides a normal working power supply for the airborne equipment; the first emergency bus bar integrates all airborne equipment breakers influencing flight safety; the equipment bus bar integrates all airborne equipment breakers which do not affect flight safety; the first contactor may conduct a path between the first generator to the first emergency bus bar; the second generator provides normal working power for the engine accessories; the second emergency bus bar integrates all engine accessories.
Description
Technical Field
The present application relates to, but is not limited to, the field of aircraft power supply system designs, and more particularly to a helicopter power supply system with dual voltage power supplies.
Background
At present, a large number of light helicopters are available at home and abroad, and the light helicopters are light in weight, so that the selected engines are generally low in power. The existing helicopter usually adopts a single-voltage generator to generate power, usually adopts a 30-volt (V) generator to supply power to airborne equipment, is used in a way of transforming voltage by matching with a transformer, and converts a 30V power supply into a 15V power supply to supply power to engine accessories; or, a high-power 15V generator is adopted to supply power, and a power supply module is configured in each electric device to perform transformation processing.
The power supply system of the power supply system has larger volume, increases the weight of the system and is difficult to meet the power supply requirement of the light helicopter.
Disclosure of Invention
The purpose of the invention is as follows: the embodiment of the invention provides a double-voltage helicopter power supply system, which aims to solve the problems that the power supply system of the power supply system in the prior art is large in size, increases the weight of the system and is difficult to meet the power supply requirement of a light helicopter.
The technical scheme of the invention is as follows:
the embodiment of the invention provides a double-voltage helicopter power supply system, which comprises: the system comprises a first power supply system and a second power supply system, wherein the first power supply system comprises a first generator, a first contactor, a generator controller, a first emergency bus bar and an equipment bus bar which are arranged in a host, and the second power supply system comprises a second generator and a second emergency bus bar which are arranged in the engine; wherein the first generator is connected to the first emergency bus bar through the first contactor, the first emergency bus bar is connected to the equipment bus bar, and the second generator is connected to the second emergency bus bar;
the first generator is configured to provide normal working power supply for the onboard equipment;
the generator controller is used with the first generator and is configured to control and protect the first generator;
the first emergency bus bar configured to integrate all on-board equipment circuit breakers affecting flight safety;
the device bus bar is configured to integrate all airborne device breakers that do not affect flight safety;
the first contactor is configured to conduct a path from the first generator to the first emergency bus bar according to a received control signal, so that the first generator supplies power to an onboard device connected with the first emergency bus bar and the device bus bar;
the second generator configured to provide normal operating power to engine accessories;
the second emergency bus bar configured to integrate all engine accessories.
Optionally, in the dual-voltage helicopter power supply system as described above, the first power supply system further includes: a first emergency power source and a second contactor, the first emergency power source being connected to the first emergency bus bar through the second contactor;
the first emergency power supply is configured to provide an emergency working power supply and a short-time maintenance power supply for the onboard equipment, and the first emergency power supply supplies power to the emergency onboard equipment in an emergency state;
the second contactor is configured to conduct a path from the first emergency power source to the first emergency bus bar according to the received control signal, so that the first emergency power source supplies power to an onboard device connected with the first emergency bus bar.
Optionally, in the dual-voltage helicopter power supply system as described above, the first power supply system further includes: the ground power supply is connected with the ground power socket, and the ground power socket is connected to the first emergency bus bar through the third contactor;
the ground power supply is configured to provide normal maintenance power supply for the onboard equipment through the ground power socket;
the third contactor is configured to conduct a path between the ground power socket and the first emergency bus bar according to a power-on signal, so that the ground power supplies power to the onboard equipment connected with the first emergency bus bar and the equipment bus bar;
when the third contactor is conducted, the first contactor and the second contactor are disconnected.
Optionally, in the dual-voltage helicopter power supply system as described above, the first power supply system further includes: a bus bar contactor connected between the first emergency bus bar and the equipment bus bar;
the bus bar contactor is configured to conduct a path from the first emergency bus bar to the device bus bar according to the received control signal.
Optionally, in the dual-voltage helicopter power supply system as described above, the first power supply system further includes: a shunt connected between the first generator and the first contactor;
the shunt configured to measure an output current of the first generator.
Optionally, in the dual-voltage helicopter power supply system as described above, the second power supply system further includes: a second emergency power supply and a fourth contactor, the second emergency power supply being connected to the second emergency bus bar through the fourth contactor;
the second emergency power supply is configured to provide emergency working power for the engine accessories, and power is supplied to the engine accessories in an emergency state;
the fourth contactor is configured to conduct a path between the second emergency power source to the second emergency bus bar according to the received control signal, so that the second emergency power source supplies power to a transmitter accessory connected to the second emergency bus bar.
Optionally, in the dual-voltage helicopter power supply system as described above, further comprising: control modules connected to the generator controller, the second contactor, the fourth contactor, and the bus bar contactor, respectively;
the control module is configured to send a control signal indicative of opening or closing to a generator controller and a contactor connected thereto.
Optionally, in the dual-voltage helicopter power supply system as described above, further comprising: a display module connected to the first emergency bus bar, the second emergency bus bar, and the shunt, respectively;
the display module is configured to display the voltages of the first emergency bus bar and the second emergency bus bar and the current of the shunt.
Alternatively, in a dual voltage helicopter power system as described above,
the display module is internally provided with a first indicator light for displaying a first generator off-line alarm;
the display module is internally provided with a second indicator light for displaying a first emergency power supply off-line alarm and a third indicator light for displaying a first emergency power supply overtemperature alarm;
and a fourth indicator light for displaying the offline alarm of the second emergency power supply and a fifth indicator light for displaying the overtemperature alarm of the second emergency power supply are arranged in the display module.
The invention has the beneficial effects that: the embodiment of the invention provides a double-voltage helicopter power supply system, which comprises: the system comprises a first power supply system and a second power supply system, wherein the first power supply system comprises a first generator, a first contactor, a generator controller, a first emergency bus bar and an equipment bus bar which are arranged in a host, and the second power supply system comprises a second generator and a second emergency bus bar which are arranged in the engine; wherein the first generator is connected to the first emergency bus bar through the first contactor, the first emergency bus bar is connected to the equipment bus bar, and the second generator is connected to the second emergency bus bar. Through the structural design, the dual-voltage helicopter power supply system is simple in structure, complete in function, highly integrated in components, and high in operability, maintainability and reliability; the device can be applied to unmanned aircrafts and manned aircrafts by matching with different control and display devices.
Drawings
FIG. 1 is a schematic structural diagram of a dual voltage helicopter power system according to an embodiment of the present invention;
fig. 2 is a schematic structural diagram of another dual-voltage helicopter power supply system according to an embodiment of the present invention.
Detailed Description
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. 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.
At present, a large number of low-power engines are available at home and abroad, the engines are mainly provided with 15V direct current generators, and the power supply system of a light helicopter is mainly supplied with power by a 30V direct current generator. Based on the hardware basis of the power supply of the 15V direct current generator and the 30V direct current generator of the engine, a power supply system with a double-voltage power supply system can be configured for the light helicopter.
Fig. 1 is a schematic structural diagram of a dual-voltage helicopter power supply system according to an embodiment of the present invention. The dual-voltage helicopter power supply system provided by the embodiment of the invention can comprise: the system comprises a first power supply system 1 and a second power supply system 2, wherein the first power supply system 1 comprises a first generator 7, a first contactor 6, a generator controller 8, a first emergency bus bar 4 and an equipment bus bar 3 which are arranged in a host, and the second power supply system 2 comprises a second generator 9 and a second emergency bus bar 5 which are arranged in an engine; wherein the first generator 7 is connected to the first emergency bus bar 4 via the first contactor 6, the first emergency bus bar 4 is connected to the equipment bus bar 3, and the second generator 9 is connected to the second emergency bus bar 5.
In the dual-voltage helicopter power supply system provided by the embodiment of the invention, the first generator is configured to provide a normal working power supply for airborne equipment;
a Generator Controller (GCU) connected with the first generator is matched with the first generator for use and is configured to control and protect the first generator;
a first emergency bus bar configured to integrate all on-board equipment circuit breakers affecting flight safety;
a device bus configured to integrate all onboard device breakers that do not affect flight safety;
the first contactor is configured to conduct a path from a first generator to the first emergency bus bar according to the received control signal, so that the first generator supplies power to the on-board equipment connected with the first emergency bus bar and the equipment bus bar;
a second generator configured to provide normal operating power to the engine accessories;
a second emergency bus bar configured to integrate all engine accessories.
Alternatively, the first power supply system is, for example, a 28V power supply system, and the second power supply system is, for example, a 14V power supply system.
Optionally, fig. 2 is a schematic structural diagram of another dual-voltage helicopter power supply system provided in the embodiment of the present invention. On the basis of the structure of the dual-voltage helicopter power supply system shown in fig. 1, in the dual-voltage helicopter power supply system provided by the embodiment of the present invention, the first power supply system 1 further includes: a first emergency power supply 15 and a second contactor 11, the first emergency power supply 15 being connected to the first emergency bus bar 4 through the second contactor 11;
a first emergency power supply 15 configured to provide an emergency operation power supply and a short-time maintenance power supply to the onboard equipment, supplying power to the emergency onboard equipment in an emergency state;
and a second contactor 11 configured to conduct a path between the first emergency power source to the first emergency bus bar according to the received control signal, so that the first emergency power source supplies power to the on-board device connected to the first emergency bus bar.
In the dual-voltage helicopter power supply system shown in fig. 2, the first power supply system may further include: a ground power source (the ground power source is not illustrated in fig. 2), a ground power socket 16 and a third contactor 12, the ground power source is connected with the ground power socket 16, and the ground power socket 16 is connected to the first emergency bus bar 4 through the third contactor 12;
the ground power supply is configured to provide normal maintenance power supply for the airborne equipment through a ground power socket;
a third contactor 12 configured to conduct a path between a ground power socket to the first emergency bus bar according to the power-on signal, so that the ground power supplies power to the on-board device connected to the first emergency bus bar and the device bus bar;
when the third contactor is turned on, the first contactor and the second contactor are turned off, and as can be seen from fig. 2, the third contactor has an interlocking function for the first contactor and the second contactor. In practical application, the machine is provided with ground power supply priority power supply logic, and when the ground power supply supplies power, the first generator and the first emergency power supply cannot be connected with a power grid on the machine.
In the dual-voltage helicopter power supply system shown in fig. 2, the first power supply system 1 may further include: a bus bar contactor 10 connected between the first emergency bus bar 4 and the equipment bus bar 3;
a bus bar contactor 10 configured to conduct a path between the first emergency bus bar to the device bus bar according to the received control signal.
As shown in fig. 2, in the dual-voltage helicopter power supply system, the first power supply system 1 further includes: a shunt 14 connected between the first generator 7 and the first contactor;
a shunt configured to measure an output current of the first generator.
In the dual-voltage helicopter power supply system shown in fig. 2, the second power supply system further includes: a second emergency power supply 17 and a fourth contactor 13, the second emergency power supply being connected to the second emergency bus bar through the fourth contactor;
a second emergency power supply configured to provide emergency operating power to the engine accessory, the engine accessory being powered in an emergency state;
a fourth contactor configured to conduct a path between the second emergency power source to the second emergency bus bar according to the received control signal such that the second emergency power source supplies power to the transmitter accessory connected to the second emergency bus bar.
The dual-voltage helicopter power supply system provided by the embodiment of the invention has the advantages of simple configuration, complete functions, high component integration, and higher operability, maintainability and reliability; the device can be applied to unmanned aircrafts and manned aircrafts by matching with different control and display devices.
In an application example of the above dual-voltage helicopter power supply system provided in the embodiment of the present invention, the first generator may be a 30V dc generator, the second generator may be a 15V generator provided in the engine itself, the first emergency power supply may be a 24V battery, the ground power supply may be a 28V ground power supply, and the second emergency power supply may be a 12V battery.
Brief description of the structure of the power supply system in the above example:
1) the engine is provided with a 300W/15V direct current generator, and a normal working power supply is provided for engine accessories;
2)1 10Ah/12V storage battery is selected to provide an emergency working power supply for the engine accessories, and the emergency power supply time is not less than 30 minutes. In addition, a 12V battery may also be used to start the engine;
3) selecting 1 1800W/30V direct current generator to provide a normal working power supply for airborne equipment, integrating all generator control and protection components into a generator controller, and using the generator controller in cooperation with the 30V direct current generator;
4) 1 10Ah/24V storage battery is selected to provide an emergency working power supply and a short-time maintenance power supply for airborne equipment, and the emergency power supply time is not less than 30 minutes;
5) a 28V ground power socket is arranged on the helicopter and is used for connecting a 28V ground power supply and providing a normal working power supply and a maintenance power supply for the helicopter;
6) A14V emergency bus bar, a 28V emergency bus bar and a 28V equipment bus bar are arranged on the machine. All engine accessories are integrated on a 14V emergency bus bar, all onboard equipment circuit breakers affecting flight safety are integrated on a 28V emergency bus bar, and all onboard equipment circuit breakers not affecting flight safety are integrated on a 28V equipment bus bar.
The above components in the power supply system are described below:
the dual-voltage helicopter power supply system consists of a 15V direct-current generator, a 12V storage battery, a 30V direct-current generator, a generator controller, a 24V storage battery and a 28V ground power supply.
1) 15V DC generator (with engine) with power of 300W
The 300W/15V direct current generator provides a normal working power supply for the engine accessories and supplies power to the engine accessories in a normal state.
2)12V storage battery
The 10Ah/12V storage battery provides an emergency working power supply for the engine accessories, the engine accessories are supplied with power in an emergency state, and the emergency power supply time is not less than 30 minutes. In addition, a 12V battery may also be used to start the engine.
3)30V DC generator with power of 1800W
The 1800W/30V direct current generator provides a normal working power supply for the airborne equipment and supplies power to the airborne equipment in a normal state.
4) Generator controller
The generator controller integrates all generator control and protection components, and is matched with the 30V direct current generator for use, so that the voltage stabilization, regulation, control and protection functions of the generator are realized.
5)24V storage battery
The 10Ah/24V storage battery provides an emergency working power supply and a short-time maintenance power supply for the airborne equipment, the airborne equipment is powered in an emergency state, and the emergency power supply time is not less than 30 minutes.
6)28V ground power supply
The 28V ground power supply provides normal working power supply and maintenance power supply for the airborne equipment through the 28V ground power socket. The ground power supply priority power supply logic is arranged on the machine, and when the 28V ground power supply supplies power, the 30V direct current generator and the 24V storage battery cannot be connected with a power grid on the machine.
Optionally, as shown in fig. 2, the dual-voltage helicopter power supply system provided in the embodiment of the present invention may further include: a control module 18 connected to the generator controller, the second contactor, the fourth contactor, and the bus bar contactor, respectively;
a control module 18 configured to send control signals indicative of opening or closing to the generator controller and contactors connected thereto.
The dual-voltage helicopter power supply system shown in fig. 2 may further include: a display module connected to the first emergency bus bar, the second emergency bus bar, and the shunt, respectively;
a display module configured to display the voltages of the first and second emergency bus bars and the current of the shunt.
In addition, a first indicator light for displaying the off-line alarm of the first generator is arranged in the display module;
a second indicator light for displaying a first emergency power supply off-line alarm and a third indicator light for displaying a first emergency power supply over-temperature alarm are arranged in the display module 19;
and a fourth indicator light for displaying the offline alarm of the second emergency power supply and a fifth indicator light for displaying the overtemperature alarm of the second emergency power supply are arranged in the display module.
The control module is, for example, a control device, and the display module is, for example, a display device.
The dual-voltage helicopter power supply system provided by the embodiment of the invention can be applied to unmanned helicopters and manned helicopters by matching with different control and display devices. The control equipment and the display equipment can be selected according to the positioning and the application of the helicopter, if the helicopter is an unmanned aerial vehicle, the helicopter control system can control, collect and alarm, if the helicopter is an unmanned aerial vehicle, the helicopter can be controlled by a pilot, and the helicopter is collected by a comprehensive display or other equipment and is alarmed by an alarm system. The power supply system mainly controls, collects and alarms as follows:
1)12V battery state control, ground/on signal, ground active. The 12V storage battery is connected to the grid when giving a ground signal, and the 12V storage battery is disconnected when giving an empty signal;
2)30V DC generator state control, ground/on signal, ground active. Judging whether the generator has a grid-connected state or not by the generator controller during the signal of giving the ground, if so, carrying out grid-connected on the 30V generator, and disconnecting the 30V generator during the signal of giving the null;
3)24V battery state control, ground/on signal, ground active. The 24V storage battery is connected to the grid when giving a ground signal, and the 24V storage battery is disconnected when giving an empty signal;
4)28V device bus control, ground/on signal, ground is active. The power supply is supplied to the 28V equipment bus bar during the ground signal, and the power failure is supplied to the 28V equipment bus bar during the null signal;
5) collecting the voltage of a 14V bus bar, simulating signals, and collecting the interval of 0-25V;
6) collecting the voltage of a 28V bus bar, simulating signals, and collecting the interval of 0-50V;
7) collecting the current of a 30V direct current generator, simulating signals, and collecting an interval of 0-100A;
8) the 12V storage battery is off-line and alarms, and the ground/open signal is effective. When the ground signal is output, the 12V storage battery is disconnected, and when the null signal is output, the 12V storage battery is connected to the grid;
9) the 12V storage battery overtemperature alarm, the ground/on signal and the ground are effective. When the ground signal is output, the overtemperature of the 12V storage battery is indicated, and when the null signal is output, the overtemperature of the 12V storage battery is not indicated;
10) the 30V direct current generator is off-line, alarming, ground/open signal and ground is effective. When the ground signal is output, the 30V generator is disconnected from the network, and when the null signal is output, the 30V generator is connected to the network;
11) the 24V storage battery is off-line and is alarmed, and the ground/open signal is effective. When the ground signal is output, the 24V storage battery is disconnected, and when the null signal is output, the 24V storage battery is connected to the grid;
12) the 24V storage battery overtemperature alarm, the ground/open signal and the ground are effective. When the ground signal is output, the over-temperature of the 24V storage battery is shown, and when the null signal is output, the over-temperature of the 24V storage battery is not shown.
The technical indexes of the main products of the double-voltage helicopter power supply system provided by the embodiment of the invention are as follows:
)15V DC generator
Rated power: 300W;
rated current: 20A;
rated voltage: 15V.
2)12V storage battery
Rated capacity: 10 Ah;
rated voltage: 12V;
end discharge voltage: 10V.
3)30V DC generator
Rated power: 1800W;
rated current: 60A;
rated voltage: 30V;
voltage at the voltage regulation point: 28V.
4)24V storage battery
Rated capacity: 10 Ah;
rated voltage: 24V;
end discharge voltage: 20V.
The dual-voltage helicopter power supply system provided by the embodiment of the invention has the advantages of simple structure and complete functions; the control and display components are highly integrated; the operability, the maintainability and the reliability are higher; the device can be applied to unmanned aircrafts and manned aircrafts by matching with different control and display devices.
The foregoing is merely a detailed description of the embodiments of the present invention, and some of the conventional techniques are not detailed. The scope of the present invention is not limited thereto, and any changes or substitutions that can be easily made by those skilled in the art within the technical scope of the present invention will be covered by the scope of the present invention. The protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (9)
1. A dual voltage helicopter power system comprising: the system comprises a first power supply system and a second power supply system, wherein the first power supply system comprises a first generator, a first contactor, a generator controller, a first emergency bus bar and an equipment bus bar which are arranged in a host, and the second power supply system comprises a second generator and a second emergency bus bar which are arranged in the engine; wherein the first generator is connected to the first emergency bus bar through the first contactor, the first emergency bus bar is connected to the equipment bus bar, and the second generator is connected to the second emergency bus bar;
the first generator is configured to provide normal working power supply for the onboard equipment;
the generator controller is used with the first generator and is configured to control and protect the first generator;
the first emergency bus bar configured to integrate all on-board equipment circuit breakers affecting flight safety;
the device bus bar is configured to integrate all airborne device breakers that do not affect flight safety;
the first contactor is configured to conduct a path from the first generator to the first emergency bus bar according to a received control signal, so that the first generator supplies power to an onboard device connected with the first emergency bus bar and the device bus bar;
the second generator configured to provide normal operating power to engine accessories;
the second emergency bus bar configured to integrate all engine accessories.
2. The dual voltage helicopter power system of claim 1 wherein the first power supply regime further comprises: a first emergency power source and a second contactor, the first emergency power source being connected to the first emergency bus bar through the second contactor;
the first emergency power supply is configured to provide an emergency working power supply and a short-time maintenance power supply for the onboard equipment, and the first emergency power supply supplies power to the emergency onboard equipment in an emergency state;
the second contactor is configured to conduct a path from the first emergency power source to the first emergency bus bar according to the received control signal, so that the first emergency power source supplies power to an onboard device connected with the first emergency bus bar.
3. The dual voltage helicopter power system of claim 2 wherein the first power supply regime further comprises: the ground power supply is connected with the ground power socket, and the ground power socket is connected to the first emergency bus bar through the third contactor;
the ground power supply is configured to provide normal maintenance power supply for the onboard equipment through the ground power socket;
the third contactor is configured to conduct a path between the ground power socket and the first emergency bus bar according to a power-on signal, so that the ground power supplies power to the onboard equipment connected with the first emergency bus bar and the equipment bus bar;
when the third contactor is conducted, the first contactor and the second contactor are disconnected.
4. The dual voltage helicopter power system of claim 3 wherein the first power supply regime further comprises: a bus bar contactor connected between the first emergency bus bar and the equipment bus bar;
the bus bar contactor is configured to conduct a path from the first emergency bus bar to the device bus bar according to the received control signal.
5. The dual voltage helicopter power system of claim 4 wherein the first power supply regime further comprises: a shunt connected between the first generator and the first contactor;
the shunt configured to measure an output current of the first generator.
6. The dual voltage helicopter power system of claim 5 wherein the second power supply regime further comprises: a second emergency power supply and a fourth contactor, the second emergency power supply being connected to the second emergency bus bar through the fourth contactor;
the second emergency power supply is configured to provide emergency working power for the engine accessories, and power is supplied to the engine accessories in an emergency state;
the fourth contactor is configured to conduct a path between the second emergency power source to the second emergency bus bar according to the received control signal, so that the second emergency power source supplies power to a transmitter accessory connected to the second emergency bus bar.
7. The dual voltage helicopter power system of claim 6 further comprising: control modules connected to the generator controller, the second contactor, the fourth contactor, and the bus bar contactor, respectively;
the control module is configured to send a control signal indicative of opening or closing to a generator controller and a contactor connected thereto.
8. The dual voltage helicopter power system of claim 6 further comprising: a display module connected to the first emergency bus bar, the second emergency bus bar, and the shunt, respectively;
the display module is configured to display the voltages of the first emergency bus bar and the second emergency bus bar and the current of the shunt.
9. The dual voltage helicopter power system of claim 8,
the display module is internally provided with a first indicator light for displaying a first generator off-line alarm;
the display module is internally provided with a second indicator light for displaying a first emergency power supply off-line alarm and a third indicator light for displaying a first emergency power supply overtemperature alarm;
and a fourth indicator light for displaying the offline alarm of the second emergency power supply and a fifth indicator light for displaying the overtemperature alarm of the second emergency power supply are arranged in the display module.
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| CN201910963106.4A CN110979706B (en) | 2019-10-11 | 2019-10-11 | Dual-voltage helicopter power supply system |
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| CN201910963106.4A CN110979706B (en) | 2019-10-11 | 2019-10-11 | Dual-voltage helicopter power supply system |
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| CN110979706B CN110979706B (en) | 2022-12-30 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
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| CN111756284A (en) * | 2020-06-17 | 2020-10-09 | 江西洪都航空工业集团有限责任公司 | Dual-channel aircraft generator control device with dual-redundancy design |
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| CN114123465B (en) * | 2021-11-19 | 2023-04-11 | 中国直升机设计研究所 | Double-voltage balance emergency power supply system of unmanned helicopter |
| CN114285153A (en) * | 2021-12-27 | 2022-04-05 | 中国航空工业集团公司西安飞机设计研究所 | Universal unmanned conveyor power supply system and method |
| CN114285153B (en) * | 2021-12-27 | 2024-03-19 | 中国航空工业集团公司西安飞机设计研究所 | Power supply system and method for general unmanned conveyor |
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