CN101710732B - Unmanned helicopter continuous voltage-stabilizing power supply system with engine air restarting function - Google Patents
Unmanned helicopter continuous voltage-stabilizing power supply system with engine air restarting function Download PDFInfo
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- CN101710732B CN101710732B CN2009102375383A CN200910237538A CN101710732B CN 101710732 B CN101710732 B CN 101710732B CN 2009102375383 A CN2009102375383 A CN 2009102375383A CN 200910237538 A CN200910237538 A CN 200910237538A CN 101710732 B CN101710732 B CN 101710732B
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- electromagnetic relay
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- control box
- distribution network
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E40/00—Technologies for an efficient electrical power generation, transmission or distribution
- Y02E40/40—Arrangements for reducing harmonics
Abstract
The invention relates to an unmanned helicopter continuous voltage-stabilizing power supply system with an engine air restarting function, which comprises at least one generator, at least one generator control box, a distribution network, at least one equipment battery, at least one starting battery, a second electromagnetic relay, a third electromagnetic relay and a main control box, wherein the generator is driven by an unmanned helicopter engine to supply voltage; the generator control box is connected with the generator; the distribution network is connected to the generator through a transmission line to receive the voltage generated by the generator; the equipment battery is connected to the distribution network through the transmission line; the starting battery is connected to the distribution network through a first electromagnetic relay; the second electromagnetic relay is used for switching on or switching off the connection of the generator control box and the distribution network; the third electromagnetic relay is used for switching on or switching off a starter; and the main control box is connected with the first electromagnetic relay, the second electromagnetic relay and the third electromagnetic relay, receives the instruction of an airborne management computer connected with the main control box, and amplifies the current to drive each electromagnetic relay.
Description
Technical field
The present invention relates to the supply of electric power of unmanned plane, particularly depopulated helicopter low-voltage DC supply system.Refer in particular to unmanned helicopter continuous voltage-stabilizing power supply system with restarting function in the engine air.
Background technology
The depopulated helicopter electric power system need guarantee stable, continued power in the whole flight course, and great fluctuation process appearred in the line voltage on any not permission of moment machine.In case and the helicopter engine flame-out in flight need be reset; Electric current moment increases during starting, and the about 70A of amplification (decide on different helicopters) causes on the machine pressure drop of grid excessive, and the airborne equipment instantaneous loss of pressure can make the flight control system inefficacy of whole depopulated helicopter when serious, thus the generation major accident.Present depopulated helicopter electric power system design adopts the method for super capacitor auxiliary power supply to evade to above-mentioned situation, the voltage fall in the time of can partly improving starting, but still there is serious disturbance in whole airborne equipment line voltage.
Summary of the invention
The purpose of this invention is to provide a kind of unmanned helicopter continuous voltage-stabilizing power supply system with restarting function in the engine air, ELIMINATION OF ITS INTERFERENCE when adopting physically-isolated method that actuating motor is moved has in essence improvement to the power supply security of unmanned helicopter-mounted electronic system.
The present invention is a kind of unmanned helicopter continuous voltage-stabilizing power supply system with restarting function in the engine air, and this system comprises:
At least one generator provides voltage by the depopulated helicopter motor driven;
At least one generator control box is connected with described generator, is used for keeping the generator output voltage value at setting range;
Power distribution network, it is connected to generator to accept the voltage that described generator produces by supply line;
At least one equipment storage battery, it is connected to power distribution network by supply line, does not power to airborne equipment when generator is worked;
At least one starting battery is the starter power supply during starting, after starting is finished, is connected to power distribution network by first electromagnetic relay;
This first electromagnetic relay is used for being switched on or switched off being connected of starting battery and power distribution network;
One second electromagnetic relay is used for being switched on or switched off being connected of generator control box and power distribution network;
One the 3rd electromagnetic relay is used for being switched on or switched off starter;
A master control box is connected with above-mentioned first electromagnetic relay, second electromagnetic relay, the 3rd electromagnetic relay, is used for receiving the instruction of the airborne supervisory computer that is connected with this master control box, and electric current is amplified to drive electromagnetic relay.
Wherein, described first electromagnetic relay is a normally closed relay.
Wherein, described second electromagnetic relay, the 3rd electromagnetic relay are normally opened relay.
During starting, starting battery and power distribution network disconnect, and starting battery is the starter power supply separately, and the equipment storage battery is the airborne equipment power supply.After starting is finished, starting battery is connected to power distribution network, powers for airborne equipment, or accept the charging of generator with the equipment storage battery with the equipment storage battery, and the voltage fluctuation that brings of balancing generator voltage instability.
Advantage of the present invention is:
The first, during starting starting battery and power distribution network are disconnected, avoided starting of the influence of the starting current of instantaneous increase to power distribution network on the machine, the excessive problem of power distribution network voltage fluctuation has guaranteed aerial engine health restarting when having overcome starting;
The second, after starting is finished, starting battery is connected to power distribution network, with the equipment storage battery, when generator failure or heavy load, power to airborne equipment.Improve electric power storage, the power supply capacity of storage battery, increased the capacity of storage battery.
Description of drawings
Fig. 1 is that the discrete depopulated helicopter electric power system of starter, generator is switched schematic diagram;
Fig. 2 is that the depopulated helicopter electric power system of starting/generator one is switched schematic diagram;
Fig. 3 is a master control box schematic internal view.
Embodiment
Figure 1 shows that the electric power system of certain light-duty depopulated helicopter, starter and generator are two separate equipment in this example.
Starting battery 110, socket 111 are connected to distribution mains 206 by distribution wire 210 and normally closed relay 114.114 select normally closed relay to be herein, only when starting, need to disconnect, select normally closed relay can save electric energy because this relay is closure state under most time.Socket 111 connects external power source, is used for the boost charge and engine 101 ground starts of storage battery 108,110.In order to guarantee the capacity of starting battery 110, under the situation that surface condition allows,, after starting is finished, throw off ground power supply with the ground power supply starting.
Ground remote control start-up function basic procedure:
1, if use ground power supply that ground power supply is connected to socket 111, connects power devices switch 150,151,152,153 etc.;
2, send " starting " by ground control station and order to supervisory computer 141, supervisory computer 141 is forwarded to master control box 109 with " starting " order.Master control box 109 at first disconnects normally closed relay 114, connects normally opened relay 113 then, connects starter 103, and is 107 power supplies of starting booster.During the engine start, magneto (not drawing among Fig. 1) can not produce enough voltage and finish igniting, and starting booster 107 utilizes starting battery 110 to come the magneto output voltage is carried out supercharging.
3, after the engine start, ground control station sends " starting is finished " and orders to supervisory computer 141, and master control box 109 disconnects normally opened relay 113, and starter 103 is thrown off with engine 101.Throw off ground power supply if use ground power supply this moment.
4, master control box 109 will often be opened electromagnetic relay 112 connections, and generator 102 begins generating.By generator control box 104 monitoring power distribution network voltages, controlling generator 102 output voltages in real time is set point.Master control box 109 is connected to distribution mains 206 with normally closed relay 114 closures with starting battery 110, carries out boost charge, perhaps is the airborne equipment power supply with equipment storage battery 108.
Aforesaid operations is just finished the handoff functionality of starting battery 110 behind engine 101 prestarts.After being the instruction that receives supervisory computer 141, the external operation of above-mentioned master control box 109 carries out.
After engine 101 startings are finished, produce high-tension ignition, no longer need the power supply of depopulated helicopter power distribution network by self driving magneto.
In the flight course,, promptly switch to restarting mode in the engine air aloft in case supervisory computer 141 is found engine cut-off.Supervisory computer 141 is sent to master control box 109 with the corresponding command.Master control box 109 cuts off normally closed relay 114 at this moment, disconnects normally opened relay 112, connects normally opened relay 113, and engine 101 is reset.After starting is finished, disconnect normally opened relay 113, supervisory computer 141 returns to normal mode, and master control box 109 is with normally closed relay 114, normally opened relay 112 closures.
Embodiment 2
Figure 2 shows that the electric power system of certain heavy depopulated helicopter, starter and generator are same equipment in this example.
Other parts and Fig. 1 are similar among Fig. 2, repeat no more herein.
The starting flow process is: disconnect normally closed relay 114 by master control box 109 earlier, normally opened relay 112 and 113 is connected in control then.After starting is finished, starting/generator control box 122 will start/and generator 120 is converted into generating state, exports electric energy to power distribution network.Relay 112,113 is kept closed, closed normally closed relay 114.
Fig. 3 is primary control box 109 schematic internal view in embodiment 1 and the embodiment 2, expansion DO port when being used for computer DO port deficiency.Primary control box 109 carries out communication by RS422 interface 134 and supervisory computer 141, according to receiving order, with the connecting and disconnecting of control normally opened relay 112,113, normally closed relay 114 by the connecting and disconnecting of single-chip microcomputer 130 by DO port controlling solid-state relay 131,132,133.
Claims (3)
1. unmanned helicopter continuous voltage-stabilizing power supply system with restarting function in the engine air, it is characterized in that: this system comprises:
At least one generator provides voltage by the depopulated helicopter motor driven;
At least one generator control box is connected with described generator, is used for keeping the generator output voltage value at setting range;
Power distribution network, it is connected to generator to accept the voltage that described generator produces by supply line;
At least one equipment storage battery, it is connected to power distribution network by supply line, does not power to airborne equipment when generator is worked;
At least one starting battery is the starter power supply during starting, after starting is finished, is connected to power distribution network by first electromagnetic relay; This first electromagnetic relay is used for being switched on or switched off being connected of starting battery and power distribution network;
One second electromagnetic relay is used for being switched on or switched off being connected of generator control box and power distribution network;
One the 3rd electromagnetic relay is used for being switched on or switched off starter;
A master control box is connected with above-mentioned first electromagnetic relay, second electromagnetic relay and the 3rd electromagnetic relay, and receives the instruction of the airborne supervisory computer that is connected with this master control box, and electric current is amplified to drive electromagnetic relay.
2. the unmanned helicopter continuous voltage-stabilizing power supply system with restarting function in the engine air according to claim 1 is characterized in that: described first electromagnetic relay is a normally closed relay.
3. the unmanned helicopter continuous voltage-stabilizing power supply system with restarting function in the engine air according to claim 1 is characterized in that: described second electromagnetic relay and the 3rd electromagnetic relay are normally opened relay.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009102375383A CN101710732B (en) | 2009-11-11 | 2009-11-11 | Unmanned helicopter continuous voltage-stabilizing power supply system with engine air restarting function |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009102375383A CN101710732B (en) | 2009-11-11 | 2009-11-11 | Unmanned helicopter continuous voltage-stabilizing power supply system with engine air restarting function |
Publications (2)
| Publication Number | Publication Date |
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| CN101710732A CN101710732A (en) | 2010-05-19 |
| CN101710732B true CN101710732B (en) | 2011-11-16 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN2009102375383A Expired - Fee Related CN101710732B (en) | 2009-11-11 | 2009-11-11 | Unmanned helicopter continuous voltage-stabilizing power supply system with engine air restarting function |
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Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101879942B (en) * | 2010-06-25 | 2012-11-21 | 北京航空航天大学 | Helicopter rotor wing automatic clutch control system with safety protection function |
| CN102097752B (en) * | 2010-12-30 | 2013-02-13 | 江苏兆胜空调有限公司 | Direct-current distribution panel for helicopter |
| CN102602535A (en) * | 2012-04-05 | 2012-07-25 | 唐粮 | Double-engine rotor unmanned aerial vehicle system |
| CN104184195B (en) * | 2014-09-09 | 2016-11-09 | 北京航空航天大学 | A kind of electric power system promoting depopulated helicopter reliability and maintainability |
| RU182061U1 (en) * | 2017-11-07 | 2018-08-02 | Акционерное общество "Корпорация "Стратегические пункты управления" АО "Корпорация "СПУ - ЦКБ ТМ" | Power supply device |
| CN107910948B (en) * | 2017-12-01 | 2021-05-07 | 中国直升机设计研究所 | Device for reducing helicopter power conversion time and helicopter power system |
| 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 |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN2645320Y (en) * | 2003-09-11 | 2004-09-29 | 威海广泰空港设备股份有限公司 | Electric power unit for airplane |
| EP1218636B1 (en) * | 1999-10-01 | 2005-07-27 | Bell Helicopter Textron Inc. | Redundant electrical dc power system for aircraft |
| CN101202454A (en) * | 2006-11-23 | 2008-06-18 | 伊斯帕诺-絮扎公司 | An electrical power supply for an aircraft |
| CN101410298A (en) * | 2006-04-04 | 2009-04-15 | 法国空中客车公司 | Device and method for generating a back-up electricity supply on board an aircraft |
-
2009
- 2009-11-11 CN CN2009102375383A patent/CN101710732B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1218636B1 (en) * | 1999-10-01 | 2005-07-27 | Bell Helicopter Textron Inc. | Redundant electrical dc power system for aircraft |
| CN2645320Y (en) * | 2003-09-11 | 2004-09-29 | 威海广泰空港设备股份有限公司 | Electric power unit for airplane |
| CN101410298A (en) * | 2006-04-04 | 2009-04-15 | 法国空中客车公司 | Device and method for generating a back-up electricity supply on board an aircraft |
| CN101202454A (en) * | 2006-11-23 | 2008-06-18 | 伊斯帕诺-絮扎公司 | An electrical power supply for an aircraft |
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| CN101710732A (en) | 2010-05-19 |
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