CN110979706B - Dual-voltage helicopter power supply system - Google Patents
Dual-voltage helicopter power supply system Download PDFInfo
- Publication number
- CN110979706B CN110979706B CN201910963106.4A CN201910963106A CN110979706B CN 110979706 B CN110979706 B CN 110979706B CN 201910963106 A CN201910963106 A CN 201910963106A CN 110979706 B CN110979706 B CN 110979706B
- Authority
- CN
- China
- Prior art keywords
- bus bar
- emergency
- power supply
- contactor
- generator
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 230000009977 dual effect Effects 0.000 claims description 11
- 238000012423 maintenance Methods 0.000 claims description 10
- 238000010586 diagram Methods 0.000 description 4
- 238000013461 design Methods 0.000 description 2
- 230000009466 transformation Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000033228 biological regulation Effects 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 102200142069 rs2577154 Human genes 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
-
- 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
-
- 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
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Business, Economics & Management (AREA)
- Emergency Management (AREA)
- Power 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 application relates to the field of aircraft power supply system design, in particular to a helicopter power supply system with a dual-voltage power supply system.
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, and is matched with a transformer to be used in a voltage transformation way, so that a 30V power supply is converted 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 an 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 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 supply 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 an 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 obtained by a person skilled in the art without making any creative effort based on the embodiments in the present invention, belong to the protection scope of the present invention.
At present, a large number of low-power engines are arranged at home and abroad, the engines are mostly provided with 15V direct-current generators, and the power supply system of the light helicopter is mostly supplied with power by 30V direct-current generators. 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;
a first contactor configured to conduct a path between a first generator to a first emergency bus bar according to a received control signal, such that the first generator supplies power to an on-board device connected to the first emergency bus bar and a device bus bar;
a second generator configured to provide normal operating power to the engine accessories;
a second emergency bus 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 an onboard power grid.
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 accessories, the engine accessories 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 structure, 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 provides a normal working power supply 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) 1 1800W/30V direct-current generator is selected to provide a normal working power supply for airborne equipment, and all generator control and protection components are integrated into a generator controller to be matched with the 30V direct-current generator for use;
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 double-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;
and 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 current divider.
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 warning of the second emergency power supply and a fifth indicator light for displaying the overtemperature warning 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 signals as follows:
1) 12V battery state control, ground/on signal, ground active. When a ground signal is given, the 12V storage battery is connected to the grid, and when an empty signal is given, the 12V storage battery is disconnected;
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 a signal, 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 30V DC generator off-line alarm, ground/on signal, ground active. 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 24V off-line warning, ground/on signal, ground active. 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 24V battery over-temperature alarm, ground/on signal, ground active. 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: 10Ah;
rated voltage: 12V;
end discharge voltage: 10V.
3) 30V DC generator
Rated power: 1800W;
rated current: 60A;
rated voltage: 30V;
voltage at the voltage regulating point: 28V.
4) 24V storage battery
Rated capacity: 10Ah;
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 modifications 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 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 that affect 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;
the first emergency bus bar and the equipment bus bar in the first power supply system are used for providing a first power supply voltage of the double-voltage helicopter power system, and the second emergency bus bar in the second power supply system is used for providing a second power supply voltage of the double-voltage helicopter power system.
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 connected to the first emergency bus bar through the second contactor;
the first emergency power supply is configured to provide emergency working power supply and short-time maintenance power supply for the onboard equipment, and power is supplied 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 airborne 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 an onboard device connected with the first emergency bus bar and the device 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 between 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,
a first indicator light for displaying a first generator off-line alarm is arranged in the display module;
the display module is internally provided with a second indicator light for displaying the off-line alarm of the first emergency power supply and a third indicator light for displaying the overtemperature alarm of the first emergency power supply;
and a fourth indicator light for displaying the offline warning of the second emergency power supply and a fifth indicator light for displaying the overtemperature warning of the second emergency power supply are arranged in the display module.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910963106.4A CN110979706B (en) | 2019-10-11 | 2019-10-11 | Dual-voltage helicopter power supply system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910963106.4A CN110979706B (en) | 2019-10-11 | 2019-10-11 | Dual-voltage helicopter power supply system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110979706A CN110979706A (en) | 2020-04-10 |
| CN110979706B true CN110979706B (en) | 2022-12-30 |
Family
ID=70081871
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910963106.4A Active CN110979706B (en) | 2019-10-11 | 2019-10-11 | Dual-voltage helicopter power supply system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110979706B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111756284B (en) * | 2020-06-17 | 2024-07-16 | 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 |
| 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 |
| 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 |
Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH07274594A (en) * | 1994-03-28 | 1995-10-20 | Mitsubishi Heavy Ind Ltd | Safety device for output voltage switching mechanism in generation set |
| SE9703548D0 (en) * | 1997-09-30 | 1997-09-30 | Asea Brown Boveri | Electric power plant |
| JP2002027637A (en) * | 2000-07-04 | 2002-01-25 | Sumitomo Wiring Syst Ltd | Circuit unit for high-voltage electrical junction box |
| DE102010001333A1 (en) * | 2010-01-28 | 2011-08-18 | Airbus Operations GmbH, 21129 | Method and device for providing an on-board AC voltage in an aircraft |
| CN102402721A (en) * | 2010-09-15 | 2012-04-04 | 波音公司 | Electrical load management system |
| CN103587707A (en) * | 2013-11-15 | 2014-02-19 | 中航飞机股份有限公司西安飞机分公司 | Power supply system of electronic flight instruments |
| CN104184195A (en) * | 2014-09-09 | 2014-12-03 | 北京航空航天大学 | Power supply system for improving reliability and maintainability of unmanned helicopter |
| CN105024452A (en) * | 2015-08-11 | 2015-11-04 | 中国航空工业集团公司西安飞机设计研究所 | DC uninterrupted power supply method and line |
| CN107187582A (en) * | 2017-07-31 | 2017-09-22 | 中国商用飞机有限责任公司 | Flap board operating handle |
| CN107264812A (en) * | 2016-04-08 | 2017-10-20 | 陕西飞机工业（集团）有限公司 | A kind of emergent redundance power supply circuit of aircraft |
| CN107612115A (en) * | 2017-08-07 | 2018-01-19 | 中国航空工业集团公司沈阳飞机设计研究所 | Airborne lithium battery group is thrown and moves back power grid control method and control device |
| CN107910860A (en) * | 2017-12-01 | 2018-04-13 | 中国直升机设计研究所 | A kind of single-shot Helicopter Electrical Power system |
| CN107910948A (en) * | 2017-12-01 | 2018-04-13 | 中国直升机设计研究所 | It is a kind of to be used to reduce device and Helicopter Electrical Power system that helicopter turns the electric time |
| CN108288853A (en) * | 2018-04-04 | 2018-07-17 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Aircraft DC power supply system and method for supplying power to |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2882200B1 (en) * | 2005-02-17 | 2015-05-01 | Hispano Suiza Sa | ELECTRICAL POWER SUPPLY FOR GAS TURBINE AIRCRAFT ENGINE EQUIPMENT |
| FR2907762B1 (en) * | 2006-10-27 | 2009-12-18 | Airbus France | SYSTEM FOR GENERATING, CONVERTING, DISTRIBUTING AND ELECTRIC STARTING ABOARD AN AIRCRAFT |
| JP5511939B2 (en) * | 2012-12-19 | 2014-06-04 | 日立オートモティブシステムズ株式会社 | Engine starter |
| CN104852067B (en) * | 2015-04-17 | 2017-04-26 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Airplane power generation system based on fuel cell |
-
2019
- 2019-10-11 CN CN201910963106.4A patent/CN110979706B/en active Active
Patent Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH07274594A (en) * | 1994-03-28 | 1995-10-20 | Mitsubishi Heavy Ind Ltd | Safety device for output voltage switching mechanism in generation set |
| SE9703548D0 (en) * | 1997-09-30 | 1997-09-30 | Asea Brown Boveri | Electric power plant |
| JP2002027637A (en) * | 2000-07-04 | 2002-01-25 | Sumitomo Wiring Syst Ltd | Circuit unit for high-voltage electrical junction box |
| DE102010001333A1 (en) * | 2010-01-28 | 2011-08-18 | Airbus Operations GmbH, 21129 | Method and device for providing an on-board AC voltage in an aircraft |
| CN102402721A (en) * | 2010-09-15 | 2012-04-04 | 波音公司 | Electrical load management system |
| CN103587707A (en) * | 2013-11-15 | 2014-02-19 | 中航飞机股份有限公司西安飞机分公司 | Power supply system of electronic flight instruments |
| CN104184195A (en) * | 2014-09-09 | 2014-12-03 | 北京航空航天大学 | Power supply system for improving reliability and maintainability of unmanned helicopter |
| CN105024452A (en) * | 2015-08-11 | 2015-11-04 | 中国航空工业集团公司西安飞机设计研究所 | DC uninterrupted power supply method and line |
| CN107264812A (en) * | 2016-04-08 | 2017-10-20 | 陕西飞机工业（集团）有限公司 | A kind of emergent redundance power supply circuit of aircraft |
| CN107187582A (en) * | 2017-07-31 | 2017-09-22 | 中国商用飞机有限责任公司 | Flap board operating handle |
| CN107612115A (en) * | 2017-08-07 | 2018-01-19 | 中国航空工业集团公司沈阳飞机设计研究所 | Airborne lithium battery group is thrown and moves back power grid control method and control device |
| CN107910860A (en) * | 2017-12-01 | 2018-04-13 | 中国直升机设计研究所 | A kind of single-shot Helicopter Electrical Power system |
| CN107910948A (en) * | 2017-12-01 | 2018-04-13 | 中国直升机设计研究所 | It is a kind of to be used to reduce device and Helicopter Electrical Power system that helicopter turns the electric time |
| CN108288853A (en) * | 2018-04-04 | 2018-07-17 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Aircraft DC power supply system and method for supplying power to |
Non-Patent Citations (2)
| Title |
|---|
| 全桥隔离型直直变换电源电路设计;吴少石等;《信息系统工程》;20180320(第03期);全文 * |
| 通航飞机直流电源系统原理及常见故障分析;任可;《航空制造技术》;20150415(第07期);全文 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110979706A (en) | 2020-04-10 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102336275B (en) | For the method for airplane emergency electrical management | |
| CN110979706B (en) | Dual-voltage helicopter power supply system | |
| CN107910860B (en) | Power supply system of single-engine helicopter | |
| EP3743974A1 (en) | Electrical powering or drive system for a motor in an electrically driven aircraft | |
| CN104184195B (en) | A kind of electric power system promoting depopulated helicopter reliability and maintainability | |
| CN112327162A (en) | System and method for collecting working current of airplane direct current generator | |
| CN113036894B (en) | Solar unmanned aerial vehicle electrical system architecture | |
| CN114172251B (en) | Small and medium-sized unmanned helicopter power distribution system | |
| CN111181209B (en) | Unmanned aerial vehicle multichannel power management system | |
| CN210490540U (en) | High-reliability tethered unmanned aerial vehicle airborne power supply control system | |
| CN110825150A (en) | Unmanned aerial vehicle is with digital power supply unit who has distribution function | |
| CN107910948B (en) | Device for reducing helicopter power conversion time and helicopter power system | |
| CN211529030U (en) | Unmanned aerial vehicle is with digital power supply unit who has distribution function | |
| RU204798U1 (en) | Aviation mobile generating unit APA-5DM-100 | |
| RU2232109C1 (en) | Method of electric power supply for on-board systems of flying vehicle | |
| CN209767233U (en) | Unmanned aerial vehicle power supply unit and unmanned aerial vehicle | |
| CN212085877U (en) | Large-scale unmanned aerial vehicle power supply redundancy system | |
| CN211296308U (en) | High-power supply system of light high-mobility chassis vehicle-mounted laser weapon system | |
| US20220144444A1 (en) | Aircraft propulsion system | |
| CN112311084A (en) | Power supply system of fixed-wing unmanned aerial vehicle | |
| CN111682644A (en) | Power management system based on manned and unmanned modification | |
| EP3840167A1 (en) | Power supply units for aircrafts | |
| CN213846326U (en) | Power limit protection device of staying unmanned aerial vehicle system | |
| CN113532202B (en) | Target drone electrical system and target drone with same | |
| CN210517882U (en) | Staying unmanned aerial vehicle power supply system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |