CN106688334B - Redundance type low-voltage direct electricity generation system - Google Patents
Redundance type low-voltage direct electricity generation system Download PDFInfo
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- CN106688334B CN106688334B CN200710083618.9A CN200710083618A CN106688334B CN 106688334 B CN106688334 B CN 106688334B CN 200710083618 A CN200710083618 A CN 200710083618A CN 106688334 B CN106688334 B CN 106688334B
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Abstract
A kind of redundance type low-voltage direct electricity generation system for unmanned vehicle, it is divided into power supply A and power supply B, main power circuits of the power supply A as aircraft, redundancy backups of the power supply B as power supply A, power supply B can be switched to moment when power supply A breaks down, it is ensured that the power supply of aircraft main power circuit.User can select using power supply A or power supply B to be working power by monitoring and control loop to main power circuit simultaneously.Redundance type DC power generation system provided by the present invention substantially increases the reliability of aircraft electric power system, reduces system cost by the design of switching circuit；The monitoring and control loop user having simultaneously can flexibly select power supply, easy to operate, practical.Can be widely applied to the low pressure 28V DC power generation system in the fields such as Aeronautics and Astronautics, industry.
Description
Technical field
The invention belongs to a kind of low-voltage direct electricity generation system for unmanned vehicle, its redundancy is mainly characterized by
The power supply mode of formula and user can policer operation convenience and reliability.
Background technology
Unmanned vehicle typically uses low pressure 28V DC power-supply systems.Unmanned vehicle power-supply system is on ground
Electric energy is provided to all electrical equipments of flying platform and mission payload platform in test and flight course, must
There must be the function of the generation and conversion and electric energy transmission and distribution of electric energy.Unmanned vehicle electric power system is in nothing
Belong to highly important subsystem in people's aerocraft system, its importance index is generally 10 (10 is maximum),
Electric power system must overall process reliably working do not allow for the generation of instant cut-off phenomenon.
The direct current that conventional unmanned vehicle DC power generation system is typically dragged using independent sustainer at present
Magneto is as main frame, and redundant power is dragged using subsidiary engine or using many independent AC permanent magnet hairs
The form that motor parallel is powered, in order to pursue the reliable working time, often the big weight of generator volume is high.With
Further expanding for current unmanned vehicle mission profile, the increase of requirement during to voyage and boat drastically.
Therefore developing a kind of reliability height, small volume, lightweight DC power generation system seems very important.
Current rectifier power source belongs to the technology of relatively maturation, because a large amount of DC-DC power modules are (straight
Circulate direct current) use, can greatly simplify design cycle and technical risk.But 28V dc sources electricity
The input range of source module is generally 18~36V, and due to aero-engine, to be generally operational in the range of speeds wider
Scope, therefore the voltage range after rectification can typically exceed 36V, not have at present for the input voltage more than 36V
There is suitable power module to choose, often using the method for reduction generator output AC voltage value, but
Easily causing can not normally electrify in the case of the slow-speed of revolution.
Therefore the problem of modular power source input voltage range is also one critically important is solved.
In summary, solve rectifier power source input superpressure and improve power-supply system reliability, mitigate power supply chi
Very little weight becomes very urgent.
The content of the invention
The technology of the present invention solves problem mainly for asking that current unmanned vehicle low-voltage power generating system is present
Topic, proposes a kind of high reliability, high performance redundance type low-voltage direct electricity generation system, is loaded according to unmanned plane
The requirement such as characteristic and use environment condition, the weight of unmanned plane is directed to reference to current unmanned plane power-supply system feature etc.
Measure volume feature and design；Simultaneously current modular power source input superpressure is solved by discharging clamp circuit design
Problem.
Implementer's case of the present invention is a kind of redundance type low-voltage direct generating system for unmanned vehicle
System, the system includes the AC permanent-magnetic generator 1 of two groups of public rotors, two independent rectifier circuits
2a, 2b, two independent filter capacitor 3a, 3b, two independent input filter circuit 4a, 4b, two
Individual independent release clamp circuit 5a, 5b, power control circuit 6, two independent DC power supplier 7a,
7b, two independent output filter circuit 8a, 8b, diode 9, automatic switch-over circuit 10；Two groups public
The alternating current that the AC permanent-magnetic generator 1 of one rotor is exported, respectively through rectifier circuit 2a, 2b and filter
Be direct current after ripple electric capacity 3a, 3b, but mains ripple is very big, by input filter circuit 4a, 4b it
Direct current is sent to DC power supplier 7a, 7b afterwards, by output filter circuit 8a, 8b produce power supply A and
Diode 9 is accessed before power supply B, wherein power supply A, and power supply B passes through automatic switch-over circuit 10 and power supply A
It is connected；Clamp circuit 5a, 5b are discharged by voltage detecting circuit 41, drive circuit 42, three FETs
43 compositions, the input voltage range for improving DC power supplier 7a, 7b；Power control circuit 6 is used
Manually controlled in described redundance type low-voltage direct electricity generation system；Power supply B as power supply A redundancy
Under backup, normal operation, power supply A and power supply B are respectively to respective load supplying, in power supply A hairs
In the case of raw failure, realize power supply B to be switched on power supply A by automatic switch-over circuit 10 and work, and
And the electrical equipment on power supply B disconnects automatically；Simultaneously user can manually control selections use power supply A or
Power supply B is working power.
The advantage of the present invention compared with prior art is as follows：
(1) generator uses the AC permanent-magnetic generator of a public rotor, saves bulk；Using
The mode of dual pulley transmission, improves efficiency and reliability.
(2) AC-DC conversion is carried out by the way of rectifier bridge adds DC power module so that system
It is easily achieved and power quality is good.
(3) redundancy realizes that power supply B can be realized and automatically switches to power supply A paths, substantially increases power supply A
Power supply reliability.
(4) power supply possesses outside control function, can conveniently realize the control of power-supply system, and user is easy to operate.
(5) the release clamp circuit that design is realized can effectively improve the input range of DC power supplier, pole
It is big to extend generator output amplitude, improve the operating frequency range of power-supply system correspondence engine.
Brief description of the drawings
Fig. 1 is overall theory diagram of the invention
It is wherein the AC permanent-magnetic generator of 1 two groups of public rotors；2 be rectifier circuit；3 be filtering
Electric capacity；4 be input filter circuit；5 be release clamp circuit；6 be power control circuit；7 be direct current
Source module；8 be output filter circuit；9 be diode；10 be automatic switch-over circuit.(explanation：Each portion
Above point dimeric figure for a, below figure for b)
Fig. 2 is the electric generator structure figure of common rotor
Wherein 21 be dual pulley；22 be one group of wound stator；23 be another group of wound stator；24 be public affairs
Rotor magnetic steel.
Fig. 3 is the theory diagram of power control circuit
Wherein 31 be user control signal；32 be signal conversion circuit.
Fig. 4 is the theory diagram of release clamp circuit
Wherein 41 voltage detecting circuits；42 be drive circuit；43 be release circuit.
Embodiment
As shown in figure 1, generator 1 of the electric energy of redundance type low-voltage direct electricity generation system by one group of common rotor
Produce, its output form is that three-phase virtual value is 16~32V alternating currents, by rectifier circuit 2a, 2b
With the direct current after filter capacitor 3a, 3b for 17.6~38.6V or so, but mains ripple is very big；By
Direct current is sent to DC power supplier 7a, 7b after input filter circuit 4a, 4b；By exporting filtered electrical
Road 8a and 8b access two poles before producing power supply A (28.5V) and power supply B (28V), wherein power supply A respectively
Pipe 9, and power supply B is connected by automatic switch-over circuit 10 with power supply A.
As seen from Figure 1, redundance type low-voltage direct electricity generation system is made up of power supply A and power supply B altogether, its
Middle power supply B is as power supply A backup, and under normal operation, power supply A and power supply B are respectively to respective
Load supplying；In the case where power supply A breaks down, automatic switch-over circuit 10 is by relay group into its line
Circle power-off, its K1A and K1B switches are disconnected to normally closed by normally opened, realize that power supply B is switched on power supply A
Work, and the electrical equipment on power supply B disconnects automatically.Generally, power supply A accesses is all to close
Key is loaded, and is not allowed power-off, by Redundancy Designs of the power supply B as power supply A, is improved and used on power supply A
The power supply reliability of electric equipment.
Can be obtained by analyzing us, the Redundancy Design of the electricity generation system mainly by two sets of independent rectifications and
DC translation circuit is obtained.
As Fig. 2 indicates the product structure of the AC permanent-magnetic generator 1 of two groups of public rotors, due to normal
Engine only one of which output shaft is advised, therefore generally only connects a generator；Conventional method is to use
One generator of main shaft drives, then drives the form of another or two generators from a random
Obtain redundancy and the backup of generator unit.The AC permanent-magnetic generator 1 of two groups of public rotors of the present invention
For double-generator mechanical series structure, by swashing that public permanent-magnet steel and associated magnetic circuit are constituted on the component of rotor 24
Magnetic assembly, two identical stators 22,23 components are separated with middle casing, the exchange of two groups of public rotors
Magneto is fastened together with 4 M6 bolts, and belt pulley 21 ensures power with axle using plane key joint
Transmission.Wherein 21 are connected using dual pulley with the output shaft of engine.The exchange of two groups of public rotors
The structure type of magneto 1 preferably make use of the main output shaft of engine, improve the compact of structure
Degree, and redundancy and the backup of generator are obtained, achieve higher reliability.
Power supply redundancy control can realize automatic switchover and manually switch two kinds of control modes.For automatic
Switch when broken down for power supply A, as shown in Fig. 1 automatic switch-over circuits 10.In general,
If in the case that the electricity generation system working time is longer, user can be according to the service condition of electricity generation system, profit
Manually switching mode realizes that power supply A and power supply B selection is used or is used alternatingly.As shown in figure 3,
The principle of switching circuit is indicated in figure.It utilizes the distant control function of DC power supplier, the control of user input
Signal 31 processed every after isolation, then is sent to by Amplification and insulation the control end of DC power supplier by light
ON+/ON- realizes being switched on and off for DC power supplier 7a, 7b.Combination control can be achieved in control, and
B work that power supply A work B does not work, power supply A does not work, power supply A, B work and not worked and (examine
Repair state) four kinds of mode of operations.Under normal operating conditions, power supply A and B can not work simultaneously, use
Any idle situation of power supply A and B only may be selected when selecting in family.
The problem of other one big technical problem of the solution of the present invention is DC power supplier input superpressure, because
The aero-engine range of speeds is very wide, and maximum speed is one times of minimum speed, due to the linear pass of generator
System, after rectification to module 7 input voltage be 17.6~38.6V, and the nominal voltage of conventional modules be 18~
36V, has exceeded the input range of module, works long hours and easily causes the damage of module 7；Conventional rectification electricity
The mode of reduction minimum speed correspondence alternating voltage is taken in source, can so cause in the slow-speed of revolution input voltage very
To 16V is less than, there will be no output voltage for this egf block.The present invention is ingenious to have used MOS's to cut-off function,
By the electric energy loss of superpressure part in the heat loss of metal-oxide-semiconductor.As shown in figure 4,41 be voltage detecting electricity
Road, when module input voltage is higher than 36V, drive circuit 42 can open three FETs 43 and work,
It is heat energy by unnecessary voltage conversion.Because the work of the engine general short time less than 30S is operated in maximum
Under speed conditions, so the time more than 36V input voltages is generally less than 30S, therefore metal-oxide-semiconductor can be with short
Time service heat loss state, otherwise overlong time can cause puncturing for metal-oxide-semiconductor 43.
In summary, the present invention different from conventional Redundancy Design by providing a kind of redundance type low-voltage direct
Electricity generation system, and automatic switchover can be realized and manually control two working methods to improve the reliability of system
Property；Power supply quality is improved by the use of input and output filter circuit and DC power supplier；In addition, also
The problem of solving for DC power supplier input voltage superpressure, greatly improves the work of power-supply system
Scope and adaptability.Under the system bulk, it is lightweight, powerful flexibly, simple and convenient user operation, reliability
Property high, low cost can be widely popularized and applied in the electric power system of various unmanned vehicle.
Claims (5)
1. a kind of redundance type low-voltage direct electricity generation system, it is characterised in that：The system includes two groups public one
The AC permanent-magnetic generator (1) of rotor, two independent rectifier circuits (2a, 2b), two are independent
Filter capacitor (3a, 3b), two independent input filter circuits (4a, 4b), two independent release pincers
Position circuit (5a, 5b), power control circuit (6), two independent DC power suppliers (7a, 7b),
Two independent output filter circuits (8a, 8b), diode (9), automatic switch-over circuit (10)；
The alternating current of AC permanent-magnetic generator (1) output of two groups of public rotors, respectively through rectification
It is direct current after bridge circuit (2a, 2b) and filter capacitor (3a, 3b), but mains ripple is very big, warp
Direct current is sent to DC power supplier (7a, 7b) after crossing input filter circuit (4a, 4b), by defeated
Go out filter circuit (8a, 8b) and produce access diode (9) before power supply A and power supply B, wherein power supply A,
And power supply B is connected by automatic switch-over circuit (10) with power supply A；
Discharge clamp circuit (5a, 5b) be located at input filter circuit (4a, 4b) and DC power supplier (7a,
It is in parallel with input filter circuit (4a, 4b) and DC power supplier (7a, 7b) between 7b), by electricity
Pressure detection circuit (41), drive circuit (42), three FET (43) compositions, for improving direct current
The input voltage range of power module (7a, 7b)；
Power control circuit (6) is used to manually control described redundance type low-voltage direct electricity generation system；
Power supply B as power supply A redundancy backup, under normal operation, power supply A and power supply B difference
It is real by automatic switch-over circuit (10) in the case where power supply A breaks down to respective load supplying
Existing power supply B, which is switched on power supply A, to work, and the electrical equipment on power supply B disconnects automatically；While user
Can control selections the use of power supply A or power supply B be manually working power.
2. a kind of redundance type low-voltage direct electricity generation system according to claim 1, it is characterised in that：
During using manually switching, DC power supplier (7a, 7b) distant control function, user input make use of
Control signal (31) by light every after isolation, then be sent to by Amplification and insulation the control of DC power supplier
End ON+/ON- realizes being switched on and off for DC power supplier (7a, 7b).
3. a kind of redundance type low-voltage direct electricity generation system according to claim 1, it is characterised in that：
Described automatic switch-over circuit (10) is by relay group into the case where power supply A breaks down, automatically
The coil blackout of switching circuit (10), the K1A and K1B of automatic switch-over circuit (10) are switched by normally opened
It is disconnected to normally closed, realizes power supply B to be switched on power supply A and work.
4. two groups public one of a kind of redundance type low-voltage direct electricity generation system for described in claim 1
The AC permanent-magnetic generator of rotor, including belt pulley (21), two identical stators (22,23), rotors
(24), it is characterised in that：Its structure type preferably make use of the main output shaft of engine, using double hairs
Excitatory group be made up of on electromechanics cascaded structure, rotor (24) component public permanent-magnet steel and associated magnetic circuit
Part, two identical stator (22,23) components are separated with middle casing, the exchange of two groups of public rotors
Magneto is fastened together with 4 M6 bolts, and belt pulley (21) is ensured with axle using plane key joint
Power is transmitted；Its middle belt pulley (21) is connected using dual pulley with the output shaft of engine.
5. a kind of raising dc source of redundance type low-voltage direct electricity generation system for described in claim 1
The method of module input voltage range, it is characterised in that：Function is cut-off using MOS, by superpressure part
Electric energy loss in the heat loss of metal-oxide-semiconductor, when module input voltage be higher than 36V when, drive circuit (42)
Three FETs (43) work opened, is heat energy by unnecessary voltage conversion.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200710083618.9A CN106688334B (en) | 2007-12-17 | 2007-12-17 | Redundance type low-voltage direct electricity generation system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200710083618.9A CN106688334B (en) | 2007-12-17 | 2007-12-17 | Redundance type low-voltage direct electricity generation system |
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| Publication Number | Publication Date |
|---|---|
| CN106688334B true CN106688334B (en) | 2012-05-16 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN200710083618.9A Active CN106688334B (en) | 2007-12-17 | 2007-12-17 | Redundance type low-voltage direct electricity generation system |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109633559A (en) * | 2018-11-26 | 2019-04-16 | 西南电子技术研究所（中国电子科技集团公司第十研究所） | Phased-array radar TR component power supply |
| CN109742843A (en) * | 2018-12-27 | 2019-05-10 | 中国空间技术研究院 | A kind of power supply and distribution Reconfigurable Control system and method towards mass flight validation |
| CN109980641A (en) * | 2019-04-11 | 2019-07-05 | 重庆川仪控制系统有限公司 | A kind of DCS control system power supply and DCS control system |
| CN111756284A (en) * | 2020-06-17 | 2020-10-09 | 江西洪都航空工业集团有限责任公司 | Dual-channel aircraft generator control device with dual-redundancy design |
| CN113339281A (en) * | 2021-06-24 | 2021-09-03 | 中国原子能科学研究院 | Nuclear power supply electromagnetic pump parallel drive controller |
-
2007
- 2007-12-17 CN CN200710083618.9A patent/CN106688334B/en active Active
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109633559A (en) * | 2018-11-26 | 2019-04-16 | 西南电子技术研究所（中国电子科技集团公司第十研究所） | Phased-array radar TR component power supply |
| CN109742843A (en) * | 2018-12-27 | 2019-05-10 | 中国空间技术研究院 | A kind of power supply and distribution Reconfigurable Control system and method towards mass flight validation |
| CN109742843B (en) * | 2018-12-27 | 2021-02-09 | 中国空间技术研究院 | Power supply and distribution reconfigurable control system and method for batched flight verification |
| CN109980641A (en) * | 2019-04-11 | 2019-07-05 | 重庆川仪控制系统有限公司 | A kind of DCS control system power supply and DCS control system |
| CN111756284A (en) * | 2020-06-17 | 2020-10-09 | 江西洪都航空工业集团有限责任公司 | Dual-channel aircraft generator control device with dual-redundancy design |
| CN113339281A (en) * | 2021-06-24 | 2021-09-03 | 中国原子能科学研究院 | Nuclear power supply electromagnetic pump parallel drive controller |
| CN113339281B (en) * | 2021-06-24 | 2022-07-01 | 中国原子能科学研究院 | Nuclear power supply electromagnetic pump parallel drive controller |
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