CN112467712B - Low-voltage power supply system of ultra-light helicopter - Google Patents
Low-voltage power supply system of ultra-light helicopter Download PDFInfo
- Publication number
- CN112467712B CN112467712B CN202011213111.2A CN202011213111A CN112467712B CN 112467712 B CN112467712 B CN 112467712B CN 202011213111 A CN202011213111 A CN 202011213111A CN 112467712 B CN112467712 B CN 112467712B
- Authority
- CN
- China
- Prior art keywords
- contactor
- storage battery
- generator
- bus bar
- unloading
- 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
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 claims abstract description 30
- 229910052744 lithium Inorganic materials 0.000 claims abstract description 30
- 238000010248 power generation Methods 0.000 claims description 10
- 239000007858 starting material Substances 0.000 claims description 3
- HBBGRARXTFLTSG-UHFFFAOYSA-N Lithium ion Chemical compound [Li+] HBBGRARXTFLTSG-UHFFFAOYSA-N 0.000 claims 2
- 229910001416 lithium ion Inorganic materials 0.000 claims 2
- 238000000034 method Methods 0.000 abstract description 5
- 238000010586 diagram Methods 0.000 description 1
Images
Classifications
-
- 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
- H02J1/00—Circuit arrangements for DC mains or DC distribution networks
-
- 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
- H02J1/00—Circuit arrangements for DC mains or DC distribution networks
- H02J1/10—Parallel operation of DC sources
-
- 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)
- Power Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Business, Economics & Management (AREA)
- Emergency Management (AREA)
- Charge And Discharge Circuits For Batteries Or The Like (AREA)
Abstract
The invention belongs to the technical field of aircraft power supply system design, and discloses an ultra-light helicopter low-voltage power supply system, which comprises: 1200VA alternating-current generator, power converter, lithium storage battery, 250VA alternating-current generator, rectifier, direct current distribution control box, distribution panel box; wherein, a generator contactor, a storage battery contactor and a connecting unloading contactor are arranged in the direct current distribution control box; a generator bus bar PP2, an unloading bus bar PP3, a storage battery bus bar PP1, a control switch and an alarm indicator lamp are arranged in the distribution board box; the atypical aviation power supply system (low voltage 28VDC and high voltage 270 VDC) is adopted, the ground power supply system is eliminated, and the starting and control process of the engine is completed by the storage battery system.
Description
Technical Field
The invention belongs to the technical field of aircraft power supply system design, and particularly relates to a low-voltage power supply system of an ultra-light helicopter.
Background
The ultra-light helicopter is a 500 kg-grade ultra-light civil helicopter, the selected engine control system adopts a low-voltage 14V direct-current power system, and the aviation low-voltage power supply is generally a 28V direct-current power supply. If a typical aviation low-voltage 28V direct-current power supply system is adopted, a power generation system and a storage battery system with two different voltages need to be designed simultaneously, so that the configuration of the power supply system is complicated, and the weight of the whole helicopter is increased.
Disclosure of Invention
In view of the problems in the background art, the invention aims to provide a low-voltage power supply system of an ultra-light helicopter, which adopts atypical aviation power supply systems (low voltage 28VDC and high voltage 270 VDC), cancels a ground power supply system, and completes the starting and control process of an engine by a storage battery system.
In order to achieve the purpose, the invention adopts the following technical scheme to realize.
A low voltage power supply system for an ultra-light helicopter, said system comprising: 1200VA AC generator 1, power converter 2, lithium battery 3, 250VA AC generator 4, rectifier 5, direct current distribution control box 6, distribution board box 10;
wherein, a generator contactor 7, a storage battery contactor 8 and a connecting unloading contactor 9 are arranged in the direct current distribution control box 6;
a generator bus bar PP2, an unloading bus bar PP3, a storage battery bus bar PP1, a control switch 11 and an alarm indicator lamp 12 are arranged in the distribution board box 10;
the 1200VA alternating-current generator 1 and the power converter 2 are used for rectifying and outputting 14V direct-current power to be used by electric equipment on a generator bus bar PP2 and an unloading bus bar PP 3;
the lithium storage battery pack 3 is used for outputting a 14V direct-current power supply to be used by electric equipment on the storage battery bus bar PP 1;
a 250VA AC generator 4 and a rectifier 5, which is used for rectifying and outputting 14V DC power to charge the lithium storage battery 3.
The technical scheme of the invention has the characteristics and further improvements that:
(1) One end of the storage battery contactor 8 is connected to the positive end of the lithium storage battery pack 3, the other end of the storage battery contactor is connected to the control switch 11, and the storage battery contactor 8 is controlled to be switched on/off through the on/off of the control switch 11;
when the main contact of the storage battery contactor 8 is normally in an open position, when the storage battery contactor 8 acts and is attracted, one end of the main contact of the storage battery contactor 8 is connected with the lithium storage battery pack 3, and the other end of the main contact of the storage battery contactor 8 is connected with the 14V storage battery bus bar PP1, so that the lithium storage battery pack 3 is connected with the 14V storage battery bus bar PP 1;
when the auxiliary contact of the storage battery contactor 8 is normally connected with the ground at one end, and the alarm indicator lamp 12 is connected with the other end, when the storage battery contactor 8 acts and is attracted, the alarm indicator lamp 12 is disconnected with the ground.
(2) One end of the generator contactor 7 is grounded, the other end of the generator contactor is connected to the control end of the power converter 2, and a ground/on signal is output to the power converter 2 through the control switch 11, so that the output end of the power converter is controlled to control a signal, and the pull-in/pull-out of the generator contactor 7 is controlled;
when the generator contactor 7 acts and is attracted, one end of the generator contactor is connected to the power output end of the power converter 2, and the other end of the generator contactor is connected to the 14V generator bus bar PP2, so that the power output end of the power converter is connected with the 14V generator bus bar PP 2;
when the generator contactor 7 acts and is attracted, one end of the auxiliary contact is grounded, and the other end of the auxiliary contact is connected to the unloading contactor 9, so that the unloading contactor 9 is controlled to be connected.
(3) One end of the connected unloading contactor 9 is connected with the motor bus bar PP2, the other end of the connected unloading contactor is connected with the auxiliary contact of the motor contactor 7, when the generator contactor 7 is in a normal state, the connected unloading contactor 9 is in a normal state, and when the generator contactor 7 acts and is attracted, the auxiliary contact of the generator contactor 7 sends a ground signal to one end of the connected unloading contactor 9, so that the connected unloading contactor 9 is controlled to act and attract;
when the connecting and unloading contactor 9 is in a normal state, one end of a main contact of the connecting and unloading contactor 9 is connected with the generator bus bar PP2, the other end of the main contact of the connecting and unloading contactor 9 is connected with the 14V storage battery bus bar PP1, when the connecting and unloading contactor 9 acts and is absorbed, one end of the main contact of the connecting and unloading contactor 9 is connected with the generator bus bar PP2, and the other end of the main contact of the connecting and unloading contactor is connected with the unloading bus bar PP 3;
when the connecting and unloading contactor 9 is in a normal state, one end of the auxiliary contact of the connecting and unloading contactor 9 is grounded, the other end of the auxiliary contact of the connecting and unloading contactor 9 is connected with the alarm indicator lamp 12, and when the connecting and unloading contactor 9 acts and is attracted, one end of the auxiliary contact of the connecting and unloading contactor 9 is grounded, and the other end of the auxiliary contact of the connecting and unloading contactor 9 is disconnected.
(4) The 1200VA alternator 1 is used to power the power converter 2.
(5) The 250VA alternating-current generator 4 is connected with the rectifier 5; and the starter motor and the rectifier 5 are connected to the output end of the lithium battery pack 3 in parallel.
(6) When the power supply system is in a normal power supply state, the control switch controls the generator contactor 7 and the storage battery contactor 8 to be attracted;
the 1200VA alternating-current generator 1 rectifies and outputs 14V direct-current power to the generator bus bar PP2 and the unloading bus bar PP3 through the power converter 2 to supply power, and the 250VA alternating-current generator 4 rectifies and outputs 14V direct-current power to the storage battery bus bar PP1 through the rectifier 5 to supply power and charges the 12V/15Ah lithium storage battery pack 3; the battery bus bar PP1 and the generator bus bar PP2 are independent of each other in a normal power supply state.
(7) When the power supply system is in an emergency power supply state, the generator contactor 7 is in a disconnection state;
when a 14V direct-current power generation system composed of the 1200VA alternating-current generator 1 and the power converter 2 has a fault, the connecting unloading contactor 9 acts for closing, the load on the unloading bus bar PP3 stops supplying power, and the generator bus bar PP2 supplies emergency power through the storage battery bus bar PP1 through the normally closed contact of the connecting unloading contactor 9.
(8) When the 14V DC power generation system composed of the 250VA AC generator 4 and a rectifier 5 fails, the storage battery bus bar PP1 is supplied with emergency power by the 12V/15Ah lithium storage battery 3.
(9) When the power supply system is in a starting power supply state, the control switch controls the storage battery contactor 8 to suck; when the engine is started, the 12V/15Ah lithium storage battery 3 supplies power to the storage battery bus bar PP1 and the generator bus bar PP2 at the same time, the engine control system supplies power to the storage battery bus bar PP1, and the rest emergency loads are supplied power to the generator bus bar PP 2; and after the starting is finished, switching on a direct current power generation system on the machine so as to switch into a normal power supply state.
The invention provides a low-voltage power supply system of an ultra-light helicopter, which adopts an atypical aviation power supply system (low voltage 28VDC and high voltage 270 VDC), cancels a ground power supply system, and completes the starting and control process of an engine by a storage battery system.
Drawings
Fig. 1 is a schematic block diagram of a low-voltage power supply system of an ultra-light helicopter according to an embodiment of the present invention.
Detailed Description
An embodiment of the present invention provides an ultra-light helicopter low-voltage power supply system, as shown in fig. 1, the system includes: 1200VA AC generator 1, power converter 2, lithium battery group 3, 250VA AC generator 4, rectifier 5, DC distribution control box 6, distribution board box 10.
Wherein, a generator contactor 7, a storage battery contactor 8 and a connecting unloading contactor 9 are arranged in the direct current distribution control box 6;
a generator bus bar PP2, an unloading bus bar PP3, a storage battery bus bar PP1, a control switch 11 and an alarm indicator lamp 12 are arranged in the distribution board box 10;
the 1200VA alternating-current generator 1 and the power converter 2 are used for rectifying and outputting 14V direct-current power to be used by electric equipment on a generator bus bar PP2 and an unloading bus bar PP 3;
the lithium storage battery 3 is used for outputting a 14V direct-current power supply to be used by electric equipment on the storage battery bus bar PP 1;
a 250VA AC generator 4 and a rectifier 5, which is used for rectifying and outputting 14V DC power to charge the lithium storage battery 3.
In particular, the method comprises the following steps of,
(1) One end of the storage battery contactor 8 is connected to the positive end of the lithium storage battery pack 3, the other end of the storage battery contactor is connected to the control switch 11, and the storage battery contactor 8 is controlled to be closed/opened through the on/off of the control switch 11;
when the main contact of the storage battery contactor 8 is normally in an open position, when the storage battery contactor 8 acts and is attracted, one end of the main contact of the storage battery contactor 8 is connected with the lithium storage battery pack 3, and the other end of the main contact of the storage battery contactor 8 is connected with the 14V storage battery bus bar PP1, so that the lithium storage battery pack 3 is connected with the 14V storage battery bus bar PP 1;
when the auxiliary contact of the storage battery contactor 8 is normal, one end of the auxiliary contact is connected with the ground, the other end of the auxiliary contact is connected with the alarm indicator lamp 12, and when the storage battery contactor 8 acts and is absorbed, the alarm indicator lamp 12 is disconnected with the ground.
(2) One end of the generator contactor 7 is grounded, the other end of the generator contactor is connected to the control end of the power converter 2, and a ground/on signal is output to the power converter 2 through the control switch 11, so that the output end of the power converter is controlled to control a signal, and the pull-in/pull-out of the generator contactor 7 is controlled;
when the generator contactor 7 acts and is attracted, one end of the generator contactor is connected to the power output end of the power converter 2, and the other end of the generator contactor is connected to the 14V generator bus bar PP2, so that the power output end of the power converter is connected with the 14V generator bus bar PP 2;
when the generator contactor 7 acts and is attracted, one end of the auxiliary contact is grounded, and the other end of the auxiliary contact is connected to the unloading contactor 9, so that the unloading contactor 9 is controlled to be connected.
(3) One end of the connected unloading contactor 9 is connected with the motor bus bar PP2, the other end of the connected unloading contactor is connected with the auxiliary contact of the motor contactor 7, when the generator contactor 7 is in a normal state, the connected unloading contactor 9 is in a normal state, and when the generator contactor 7 acts and is attracted, the auxiliary contact of the generator contactor 7 sends a ground signal to one end of the connected unloading contactor 9, so that the connected unloading contactor 9 is controlled to act and attract;
when the connecting and unloading contactor 9 is in a normal state, one end of a main contact of the connecting and unloading contactor 9 is connected with the generator bus bar PP2, the other end of the main contact of the connecting and unloading contactor 9 is connected with the 14V storage battery bus bar PP1, when the connecting and unloading contactor 9 acts and is attracted, one end of the main contact of the connecting and unloading contactor 9 is connected with the generator bus bar PP2, and the other end of the main contact of the connecting and unloading contactor is connected with the unloading bus bar PP 3;
when the connecting and unloading contactor 9 is in a normal state, one end of an auxiliary contact of the connecting and unloading contactor 9 is grounded, the other end of the auxiliary contact is connected with the alarm indicator lamp 12, and when the connecting and unloading contactor 9 acts and is absorbed, one end of the auxiliary contact of the connecting and unloading contactor 9 is grounded, and the other end of the auxiliary contact is disconnected.
(4) The 1200VA alternator 1 is used to power the power converter 2.
(5) The 250VA alternating-current generator 4 is connected with the rectifier 5; and the starter motor and the rectifier 5 are connected to the output end of the lithium storage battery 3 in parallel.
(6) When the power supply system is in a normal power supply state, the control switch controls the generator contactor 7 and the storage battery contactor 8 to be attracted;
the 1200VA alternating-current generator 1 rectifies and outputs 14V direct-current power to the generator bus bar PP2 and the unloading bus bar PP3 through the power converter 2 to supply power, and the 250VA alternating-current generator 4 rectifies and outputs 14V direct-current power to the storage battery bus bar PP1 through the rectifier 5 to supply power and charges the 12V/15Ah lithium storage battery pack 3; the battery bus bar PP1 and the generator bus bar PP2 are independent of each other in a normal power supply state.
(7) When the power supply system is in an emergency power supply state, the generator contactor 7 is in a disconnection state;
when a 14V direct-current power generation system composed of the 1200VA alternating-current generator 1 and the power converter 2 has a fault, the connecting unloading contactor 9 acts for closing, the load on the unloading bus bar PP3 stops supplying power, and the generator bus bar PP2 supplies emergency power through the storage battery bus bar PP1 through the normally closed contact of the connecting unloading contactor 9.
(8) When the 14V DC power generation system composed of the 250VA AC generator 4 and a rectifier 5 fails, the storage battery bus bar PP1 is supplied with emergency power by the 12V/15Ah lithium storage battery 3.
(9) When the power supply system is in a starting power supply state, the control switch controls the storage battery contactor 8 to suck; when the engine is started, the 12V/15Ah lithium storage battery 3 supplies power to the storage battery bus bar PP1 and the generator bus bar PP2 at the same time, the engine control system supplies power to the storage battery bus bar PP1, and the rest emergency loads are supplied power to the generator bus bar PP 2; and after the starting is finished, switching on a direct current power generation system on the machine, and thus, switching into a normal power supply state.
The invention provides a low-voltage power supply system of an ultra-light helicopter, which adopts atypical aviation power supply systems (low voltage 28VDC and high voltage 270 VDC), cancels a ground power supply system, and finishes the starting and control process of an engine by a storage battery system.
Claims (10)
1. A low-voltage power supply system for an ultra-light helicopter, said system comprising: the power supply comprises a 1200VA alternating-current generator (1), a power converter (2), a lithium storage battery pack (3), a 250VA alternating-current generator (4), a rectifier (5), a direct-current distribution control box (6) and a distribution board box (10);
wherein, a generator contactor (7), a storage battery contactor (8) and a connecting unloading contactor (9) are arranged in the direct current distribution control box (6);
a generator bus bar PP2, an unloading bus bar PP3, a storage battery bus bar PP1, a control switch (11) and an alarm indicator lamp (12) are arranged in the distribution board box (10);
the 1200VA alternating-current generator (1) and the power converter (2) are used for rectifying and outputting 14V direct-current power to be used by electric equipment on a generator bus bar PP2 and an unloading bus bar PP 3;
the lithium storage battery pack (3) is used for outputting a 14V direct-current power supply to be used by electric equipment on the storage battery bus bar PP 1;
the lithium ion battery pack comprises a 250VA alternating current generator (4) and a rectifier (5) which is used for rectifying and outputting a 14V direct current power supply to charge the lithium ion battery pack (3).
2. The low-voltage power supply system of the ultra-light helicopter of claim 1,
one end of the storage battery contactor (8) is connected to the positive end of the lithium storage battery pack (3), the other end of the storage battery contactor is connected to the control switch (11), and the storage battery contactor (8) is controlled to be closed/opened through the on/off of the control switch (11);
when the main contact of the storage battery contactor (8) is normally in an open position, when the storage battery contactor (8) acts and is attracted, one end of the main contact of the storage battery contactor (8) is connected with the lithium storage battery pack (3), and the other end of the main contact of the storage battery contactor (8) is connected with the 14V storage battery bus bar PP1, so that the lithium storage battery pack (3) is connected with the 14V storage battery bus bar PP 1;
when the auxiliary contact of the storage battery contactor (8) is normal, one end of the auxiliary contact is connected with the ground, the other end of the auxiliary contact is connected with the alarm indicating lamp (12), and when the storage battery contactor (8) acts and is attracted, the alarm indicating lamp (12) is disconnected with the ground.
3. A low-voltage power supply system for an ultra-light helicopter according to claim 2,
one end of the generator contactor (7) is grounded, the other end of the generator contactor is connected to the control end of the power converter (2), and a ground/open signal is output to the power converter (2) through the control switch (11), so that the output end of the power converter is controlled to control a signal, and the pull-in/pull-out of the generator contactor (7) is controlled;
when the generator contactor (7) acts and is attracted, one end of the generator contactor is connected to the power output end of the power converter (2), and the other end of the generator contactor is connected to the 14V generator bus bar PP2, so that the power output end of the power converter is connected with the 14V generator bus bar PP 2;
when the auxiliary contact of the generator contactor (7) is normally connected with one end of the ground and the other end of the ground, the alarm indicator lamp is connected to one end of the auxiliary contact, and when the generator contactor (7) acts and is attracted, one end of the auxiliary contact is connected with the ground and the other end of the auxiliary contact is connected to the connected unloading contactor (9), so that the connected unloading contactor (9) is controlled.
4. A low-voltage power supply system for an ultra-light helicopter according to claim 3,
one end of the connected unloading contactor (9) is connected with the motor bus bar PP2, the other end of the connected unloading contactor is connected with an auxiliary contact of the motor contactor (7), when the generator contactor (7) is in a normal state, the connected unloading contactor (9) is in a normal state, and when the generator contactor (7) acts and is attracted, the auxiliary contact of the generator contactor (7) sends a ground signal to one end of the connected unloading contactor (9), so that the connected unloading contactor (9) is controlled to act and attract;
when the connecting unloading contactor (9) is in a normal state, one end of a main contact of the connecting unloading contactor (9) is connected with the generator bus bar PP2, the other end of the main contact of the connecting unloading contactor is connected with the 14V storage battery bus bar PP1, when the connecting unloading contactor (9) acts and is attracted, one end of the main contact of the connecting unloading contactor (9) is connected with the generator bus bar PP2, and the other end of the main contact of the connecting unloading contactor is connected with the unloading bus bar PP 3;
when the connected unloading contactor (9) is in a normal state, one end of an auxiliary contact of the connected unloading contactor (9) is grounded, the other end of the auxiliary contact of the connected unloading contactor is connected with the alarm indicator lamp (12), and when the connected unloading contactor (9) acts and is attracted, one end of the auxiliary contact of the connected unloading contactor (9) is grounded, and the other end of the auxiliary contact of the connected unloading contactor is disconnected.
5. The low-voltage power supply system of the ultra-light helicopter of claim 1,
the 1200VA alternating-current generator (1) is used for supplying power to the power converter (2).
6. The low-voltage power supply system of the ultra-light helicopter of claim 1,
the 250VA alternating-current generator (4) is connected with the rectifier (5); and the starter and the rectifier (5) are connected to the output end of the lithium storage battery pack (3) in parallel.
7. The low-voltage power supply system of the ultra-light helicopter of claim 4,
when the power supply system is in a normal power supply state, the control switch controls the generator contactor (7) and the storage battery contactor (8) to be attracted;
the 1200VA alternating-current generator (1) rectifies and outputs 14V direct-current power to supply power to the generator bus bar PP2 and the unloading bus bar PP3 through the power converter (2), and the 250VA alternating-current generator (4) rectifies and outputs 14V direct-current power to supply power to the storage battery bus bar PP1 through the rectifier (5) and charges the 12V/15Ah lithium storage battery pack (3); the battery bus bar PP1 and the generator bus bar PP2 are independent of each other in a normal power supply state.
8. The low-voltage power supply system of the ultra-light helicopter of claim 4,
when the power supply system is in an emergency power supply state, the generator contactor (7) is in a disconnection state;
when a 14V direct-current power generation system composed of the 1200VA alternating-current generator (1) and the power converter (2) has a fault, the connecting unloading contactor (9) acts to close, the load on the unloading bus bar PP3 stops supplying power, and the generator bus bar PP2 supplies emergency power through the storage battery bus bar PP1 through the normally closed contact of the connecting unloading contactor (9).
9. The low-voltage power supply system of the ultra-light helicopter of claim 8,
when a 14V direct-current power generation system consisting of a 250VA alternating-current generator (4) and a rectifier (5) fails, the storage battery bus bar PP1 is supplied with emergency power by a 12V/15Ah lithium storage battery pack (3).
10. A low-voltage power supply system for an ultra-light helicopter according to claim 4,
when the power supply system is in a starting power supply state, the control switch controls the storage battery contactor (8) to be closed; when the engine is started, a 12V/15Ah lithium storage battery pack (3) supplies power to a storage battery bus bar PP1 and a generator bus bar PP2 at the same time, an engine control system supplies power to the storage battery bus bar PP1, and the rest emergency loads are supplied power to the generator bus bar PP 2; and after the starting is finished, switching on a direct current power generation system on the machine, and thus, switching into a normal power supply state.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011213111.2A CN112467712B (en) | 2020-11-03 | 2020-11-03 | Low-voltage power supply system of ultra-light helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011213111.2A CN112467712B (en) | 2020-11-03 | 2020-11-03 | Low-voltage power supply system of ultra-light helicopter |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112467712A CN112467712A (en) | 2021-03-09 |
| CN112467712B true CN112467712B (en) | 2023-04-11 |
Family
ID=74835038
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011213111.2A Active CN112467712B (en) | 2020-11-03 | 2020-11-03 | Low-voltage power supply system of ultra-light helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112467712B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114123475B (en) * | 2021-11-03 | 2023-06-23 | 哈尔滨哈飞航空工业有限责任公司 | Self-adaptive control power distribution system and method |
| CN114172251B (en) * | 2021-11-12 | 2023-11-21 | 天津航空机电有限公司 | Small and medium-sized unmanned helicopter power distribution system |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1472113A (en) * | 2002-08-02 | 2004-02-04 | 洪 章 | Helicopper |
| GB201319585D0 (en) * | 2013-11-06 | 2013-12-18 | Ge Aviat Systems Ltd | Electrical power system for an aircraft |
| CN104659900A (en) * | 2013-11-25 | 2015-05-27 | 中国直升机设计研究所 | Power supply system of unmanned helicopter |
| 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 |
| CN109149552A (en) * | 2018-09-25 | 2019-01-04 | 南京麦格安倍电气科技有限公司 | A kind of aircraft battery plays the pressure limiting device in motor-car |
| CN211374922U (en) * | 2019-12-23 | 2020-08-28 | 北京汽车集团越野车有限公司 | Automobile range extender testing system and automobile |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA3090325A1 (en) * | 2018-02-08 | 2019-08-15 | Vita Inclinata Technologies, Inc. | Suspended load stability systems and methods |
-
2020
- 2020-11-03 CN CN202011213111.2A patent/CN112467712B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1472113A (en) * | 2002-08-02 | 2004-02-04 | 洪 章 | Helicopper |
| GB201319585D0 (en) * | 2013-11-06 | 2013-12-18 | Ge Aviat Systems Ltd | Electrical power system for an aircraft |
| CN104627377A (en) * | 2013-11-06 | 2015-05-20 | 通用电气航空系统有限公司 | Electrical power system for an aircraft |
| CN104659900A (en) * | 2013-11-25 | 2015-05-27 | 中国直升机设计研究所 | Power supply system of unmanned helicopter |
| 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 |
| CN109149552A (en) * | 2018-09-25 | 2019-01-04 | 南京麦格安倍电气科技有限公司 | A kind of aircraft battery plays the pressure limiting device in motor-car |
| CN211374922U (en) * | 2019-12-23 | 2020-08-28 | 北京汽车集团越野车有限公司 | Automobile range extender testing system and automobile |
Also Published As
| Publication number | Publication date |
|---|---|
| CN112467712A (en) | 2021-03-09 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US20220037894A1 (en) | High reliability hybrid energy storage system | |
| CN206544473U (en) | Electric car electric power system | |
| CN105102318B (en) | Boat with electric drive | |
| US9401597B2 (en) | Method and device for discharging an intermediate circuit of a power supply network | |
| CN107963040B (en) | Battery pack device, operating method for battery pack device, and vehicle | |
| KR20120062956A (en) | High voltage system of electric vehicles | |
| CN105790364A (en) | Electrical system of internal-combustion-engine powered vehicle and power supply method thereof | |
| US20200042062A1 (en) | Dynamically configurable energy storage unit | |
| CN112467712B (en) | Low-voltage power supply system of ultra-light helicopter | |
| CN105790365A (en) | Electrical system of internal-combustion-engine powered vehicle and power supply method thereof | |
| CN109193726A (en) | Engineering vehicular lithium ion battery energy storage system | |
| CN105270192B (en) | Distance increasing unit for pure electric automobile | |
| CN104901406B (en) | A kind of blood-collecting car power supply system and the blood-collecting car using the system | |
| US11581744B2 (en) | Electrical architecture of an aircraft | |
| CN117962675B (en) | Ordered charging control device of charging pile, charging pile and charging system | |
| CN207977741U (en) | aircraft DC power supply system | |
| CN119275989A (en) | A power distribution system architecture and power distribution method for a dual-engine unmanned aerial vehicle | |
| CN114083986A (en) | Automobile high-voltage controller capable of independently controlling upper power supply and control method thereof | |
| CN212435420U (en) | Inside and outside uninterrupted power switching circuit of airship, power supply system and airship | |
| CN205440011U (en) | A increase journey ware for pure electric vehicles | |
| CN220066917U (en) | Control circuit and control system | |
| CN217010421U (en) | Environment-friendly ship battery system based on electric power maintenance stability | |
| CN119133659B (en) | Marine energy storage system and discharge method thereof | |
| CN221162612U (en) | Electric control system of vehicle and vehicle | |
| CN216959380U (en) | Energy storage battery protection system for taking electricity through battery direct current side |
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 |