CN103661922B - A kind of servo control mechanism electricity consumption combustion gas mixing power set - Google Patents
A kind of servo control mechanism electricity consumption combustion gas mixing power set Download PDFInfo
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- CN103661922B CN103661922B CN201210320268.4A CN201210320268A CN103661922B CN 103661922 B CN103661922 B CN 103661922B CN 201210320268 A CN201210320268 A CN 201210320268A CN 103661922 B CN103661922 B CN 103661922B
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- combustion gas
- pressure
- control mechanism
- servo control
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Abstract
The invention belongs to a kind of servo control mechanism electricity consumption combustion gas mixing power set, be specifically related to one and be applied particularly to carry-on servo control mechanism.A kind of servo control mechanism electricity consumption combustion gas mixing power set, it includes motor drive controller, and motor drive controller is connected with the pressure sensor of electrodynamic pump and accumulator by cable respectively.It is an advantage of the invention that, it can provide the electric hydaulic energy and combustion gas hydraulic energy source both power sources simultaneously, the electric hydaulic energy can meet for a long time, small-power and long-time ground measurement condition, and combustion gas hydraulic pressure and electric hydaulic hybrid power can meet short time, high-power flight operating mode.
Description
Technical field
The invention belongs to a kind of servo control mechanism electricity consumption combustion gas mixing power set, be specifically related to one and specifically should
For carry-on servo control mechanism.
Background technology
Servo control mechanism is the general designation of the executing agency's subsystem to flying vehicles control, and typical case's application is aircraft
Rudder face wave control.In some aircraft, existing long-time, the small-power operating mode of servo control mechanism, also
There are short time, high-power operating mode.Thus, the power set to servo control mechanism it is also proposed new requirement.
Currently for for the servomechanism system that relatively high power and/or freedom of motion are more, electro-hydraulic side
Case usually becomes preferred version because of flexible layout.For power set, the electrodynamic pump with battery as power
Scheme can work the long period, but power is less than normal；Combustion gas hydraulic energy source scheme power with combustion gas as power
Relatively big, but the working time is the shortest.
Summary of the invention
It is an object of the invention to provide a kind of electric combustion gas mixing power dress of servo control mechanism on aircraft
Put, long-time, small-power flight operating mode and long-time ground measurement condition can be met, it is possible to meet short
Time, high-power flight operating mode, and provide peak power by accumulators double during high operating mode, improve the energy
The efficiency of device, reduces source energy consumption.
The present invention is achieved in that a kind of servo control mechanism electricity consumption combustion gas mixing power set, and it includes electricity
Machine drives controller, and motor drive controller is respectively by cable and electrodynamic pump and the pressure sensing of accumulator
Device connects, and the high-pressure outlet of electrodynamic pump is connected with the entrance of check valve, and fuel gas source is connected with turbine, turbine
Being connected with decelerator, decelerator is connected with hydraulic pump, and the high-pressure outlet of hydraulic pump connects with the entrance of check valve
Connecing, the outlet of check valve and check valve connects, with filter, accumulator, overflow valve and high-voltage safety
The entrance of valve connects, and accumulator is connected with fuel tank, and fuel tank is connected with low-pressure safety valve, fuel tank also with overflow
The outlet of valve and the outlet of high-pressure safety valve connect, the low-pressure inlet of electrodynamic pump and the low press-in of hydraulic pump
Mouth connects.
It is an advantage of the invention that it can provide the electric hydaulic energy and combustion gas hydraulic energy source both simultaneously
Power source, the electric hydaulic energy can meet for a long time, small-power and long-time ground measurement condition,
Combustion gas hydraulic pressure and electric hydaulic hybrid power can meet short time, high-power flight operating mode.
Accompanying drawing explanation
Fig. 1 is a kind of servo control mechanism electricity consumption combustion gas mixing power set schematic diagram provided by the present invention.
In figure, 1 motor drive controller, 2 electrodynamic pumps, 3 fuel gas sources, 4 turbines, 5 decelerators, 6 liquid
Press pump, 7 accumulators, 8 low-pressure safety valves, 9 overflow valves, 10 fuel tanks, 11 high-pressure safety valves, 12 is single
To valve, 13 check valves, 14 filters.
Detailed description of the invention
The present invention is described in detail with specific embodiment below in conjunction with the accompanying drawings:
A kind of servo control mechanism electricity consumption combustion gas mixing power set it include energy source device in set two set hydraulic powers
The energy: a set of electric hydaulic energy, a set of combustion gas hydraulic energy source, the two set energy share fuel tank 10, accumulation of energy
Device 7 and other hydraulic services.Energy source device also includes the energy with motor drive controller as core simultaneously
Energy hole management loop.
A kind of servo control mechanism electricity consumption combustion gas mixing power set, it includes motor drive controller 1, motor
Controller 1 is driven to be connected with the pressure sensor of electrodynamic pump 2 and accumulator 7 by cable respectively, electronic
The high-pressure outlet of pump 2 is connected with the entrance of check valve 12, and fuel gas source 3 is connected with turbine 4, turbine 4 with
Decelerator 5 connects, and decelerator 5 is connected with hydraulic pump 6, the high-pressure outlet of hydraulic pump 6 and check valve 13
Entrance connect, the outlet of check valve 12 and check valve 13 connects, with filter 14, accumulator 7,
The entrance of overflow valve 9 and high-pressure safety valve 11 connects, and accumulator 7 is connected with fuel tank 10, fuel tank 10
Be connected with low-pressure safety valve 8, fuel tank 10 also with the outlet of overflow valve 9 and going out of high-pressure safety valve 11
Mouth connects, and the low-pressure inlet of electrodynamic pump 2 and the low-pressure inlet of hydraulic pump 6 connect.
Source energy controls management loop using energy source device high pressure as controlled quentity controlled variable, when load flow causes greatly
Energy high-pressure less than setting value (when low operating mode 8MPa, high operating mode 34MPa, drive and control of electric machine
Device 1 controls electrodynamic pump 2 and runs up, and supplements high-voltage oil liquid；When energy high-pressure is higher than or reaches to set
During definite value, servo controller 1 controls electrodynamic pump 2 low-speed running (the most supplementary servo valve internal leakage loss stream
Amount even shut down, reduce electrodynamic pump 2 flow output, with this realize the unidirectional variable speed of electrodynamic pump 2,
Pressure on Energy carries out electric hydaulic source energy according to the mode that loading demand stepping is arranged and controls management.
During low operating mode, system pressure is determined by electrodynamic pump 2 closed-loop control, accumulator 7 initial inflated gas pressure
Being 4 ~ 5MPa, electrodynamic pump 2 is by controlling the unidirectional change of direct current brushless motor speed by system pressure control
At 8MPa, accumulator provides peak power for servo control mechanism.During high operating mode, fuel gas source 3 is lighted a fire, and drives
Turbine 4 High Rotation Speed, is worked by the decelerator 5 rear drive hydraulic pump 6 that slows down, and system pressure is by overflow
Valve 9 will control at 35MPa.When system pressure decreases below 34MPa due to underfed, electronic
The motor speed of pump 2 raises, and supplements flow for system, it is provided that system peak power together with accumulator 7,
Double accumulators when thus accumulator 7 and electrodynamic pump 2 form high operating mode.The high-voltage safety pressure of system by
High-pressure safety valve 11 sets, low-voltage safety pressure is set by low-pressure safety valve 8.
According to the present invention, when servo control mechanism is in low operating mode, electrodynamic pump is by controlling the unidirectional of motor speed
Variation control system pressure, exports small-power, and the peak power of system is provided by an accumulator, meets
Long-time small-power flight operating mode and long-time ground measurement condition requirement；Servo control mechanism is in high operating mode
Time, servo control mechanism carries fuel gas source igniting, gas driven turbine High Rotation Speed, drives liquid by decelerator
Press pump works, and now system pressure is by overflow valve control, and electrodynamic pump now is by driver control, with
Accumulator forms double accumulator together provides the peak power of system.Short time, high-power flight can be met
Working condition requirement.
Claims (1)
1. servo control mechanism electricity consumption combustion gas mixing power set, it is characterised in that: it includes that motor drives
Controller (1), motor drive controller (1) is respectively by cable and electrodynamic pump (2) and the pressure of accumulator (7)
Force snesor connects, and the high-pressure outlet of electrodynamic pump (2) and the entrance of the first check valve (12) connect, combustion gas
Source (3) is connected with turbine (4), and turbine (4) is connected with decelerator (5), decelerator (5) and hydraulic pump (6)
Connecting, the high-pressure outlet of hydraulic pump (6) and the entrance of the second check valve (13) connect, the first check valve (12)
Outlet with the second check valve (13) connects, the outlet of the second check valve (13) and filter (14), accumulation of energy
The entrance of device (7), overflow valve (9) and high-pressure safety valve (11) connects, accumulator (7) and fuel tank (10)
Connecting, fuel tank (10) is connected with low-pressure safety valve (8), fuel tank (10) also with the outlet of overflow valve (9) and
The outlet of high-pressure safety valve (11) connects, the low-pressure inlet of electrodynamic pump (2) and the low-pressure inlet of hydraulic pump (6)
Connect.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210320268.4A CN103661922B (en) | 2012-08-31 | 2012-08-31 | A kind of servo control mechanism electricity consumption combustion gas mixing power set |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210320268.4A CN103661922B (en) | 2012-08-31 | 2012-08-31 | A kind of servo control mechanism electricity consumption combustion gas mixing power set |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103661922A CN103661922A (en) | 2014-03-26 |
| CN103661922B true CN103661922B (en) | 2016-08-31 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210320268.4A Active CN103661922B (en) | 2012-08-31 | 2012-08-31 | A kind of servo control mechanism electricity consumption combustion gas mixing power set |
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| Country | Link |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106224329B (en) * | 2016-09-08 | 2018-02-13 | 北京精密机电控制设备研究所 | A kind of integrated electric Hydrauservo System |
| JP2018094969A (en) * | 2016-12-08 | 2018-06-21 | 住友精密工業株式会社 | Eha system of aircraft landing gear |
| CN108284947B (en) * | 2017-12-13 | 2021-11-02 | 中航(成都)无人机***股份有限公司 | Aircraft braking system based on pressure accumulation energy storage |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1094124A (en) * | 1993-04-18 | 1994-10-26 | 隋喜顺 | Double-acting engine |
| CN1066405C (en) * | 1995-09-15 | 2001-05-30 | 国家航空工业公司 | Process and device for control of rudder of aircraft |
| CN1902389A (en) * | 2003-10-27 | 2007-01-24 | 联合工艺公司 | Hybrid engine accessory power system |
| CN201110220Y (en) * | 2007-08-16 | 2008-09-03 | 靳北彪 | Outside inflatable engine |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102007021748B4 (en) * | 2007-05-09 | 2019-12-12 | Liebherr-Aerospace Lindenberg Gmbh | Drive system for a vault-variable aircraft wing |
-
2012
- 2012-08-31 CN CN201210320268.4A patent/CN103661922B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1094124A (en) * | 1993-04-18 | 1994-10-26 | 隋喜顺 | Double-acting engine |
| CN1066405C (en) * | 1995-09-15 | 2001-05-30 | 国家航空工业公司 | Process and device for control of rudder of aircraft |
| CN1902389A (en) * | 2003-10-27 | 2007-01-24 | 联合工艺公司 | Hybrid engine accessory power system |
| CN201110220Y (en) * | 2007-08-16 | 2008-09-03 | 靳北彪 | Outside inflatable engine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103661922A (en) | 2014-03-26 |
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