CN106314765A - Energy recovery type aircraft undercarriage extension and retraction hydraulic system - Google Patents
Energy recovery type aircraft undercarriage extension and retraction hydraulic system Download PDFInfo
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- CN106314765A CN106314765A CN201510354206.9A CN201510354206A CN106314765A CN 106314765 A CN106314765 A CN 106314765A CN 201510354206 A CN201510354206 A CN 201510354206A CN 106314765 A CN106314765 A CN 106314765A
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- accumulator
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Abstract
The invention relates to an aircraft undercarriage hydraulic system, in particular to an energy recovery type aircraft undercarriage extension and retraction hydraulic system. The hydraulic system comprises a hydraulic oil tank (1), a hydraulic pump (3), a check valve (4), a pressure accumulator (7) and an airplane wheel (16). The hydraulic pump (3) is connected with the airplane wheel (16) through a transmission mechanism and connected with the pressure accumulator (7) through the check valve (4). The check valve (4) and the pressure accumulator (7) communicate with an undercarriage pressure supply pipeline. According to the system, the technical problem that original technical systems are high in weight, short in service and poor in economic efficiency is solved.
Description
Technical field
The present invention relates to a kind of Hydraulic System for Aircraft Landing Gear, particularly to a kind of energy recovery type
Undercarriage folding and unfolding hydraulic system.
Background technology
In existing undercarriage folding and unfolding hydraulic system, general employing is driven by the engine
Throttle grverning hydraulic system, provides hydraulic energy by Engine driven Hydraulic Pump for undercarriage control
Source, this construction weight is big, and structure is complicated, and energy loss is serious.This mode has 3 drawbacks:
(1) provided hydraulic energy source by Engine driven Hydraulic Pump for undercarriage control, have bigger
Energy loss, add the burden of electromotor.
(2) in aircraft cruising phase, it is not necessary to carry out undercarriage control, now, at hydraulic pump
In idling conditions, add the loss of hydraulic pump.
(3) in the aircraft taxi stage, wheel rotates the energy produced and loses completely, economy
Poor.
Summary of the invention
The technical problem to be solved in the present invention: propose one length in service life, simple in construction, one-tenth
This is low, it is simple to integrated energy recovery type undercarriage folding and unfolding hydraulic system.
Technical scheme: described hydraulic system include hydraulic oil container 1, hydraulic pump 3,
Check valve 4, accumulator 7 and wheel 16, hydraulic pump 3 is with wheel 16 by drive mechanism even
Connecing, hydraulic pump 3 is connected with accumulator 7, at check valve 4 and accumulator 7 by check valve 4
Between with undercarriage voltage supply pipeline connection.
As a kind of improvement of the technical program, described hydraulic pump 3 is also associated with standby simultaneously
Motor 14, is provided with pressure switch 15, pressure switch between check valve 4 and accumulator 7
15 are connected with standby motor 14.
As a kind of improvement of the technical program, accumulator 7 is by relief valve 6 and hydraulic oil container
1 connection.
Beneficial effects of the present invention: 1, energy recovery type undercarriage folding and unfolding hydraulic system is used
The energy produced when wheel rotates is accumulator pressurising, is provided for undercarriage control by accumulator
Hydraulic energy source, decreases the energy loss of aircraft.
2, without by Engine driven Hydraulic Pump, alleviating the burden of electromotor.
3, mainly hydraulic energy source is provided by accumulator rather than hydraulic pump for undercarriage control,
Hydraulic pump, without remaining idle state when off position, decreases the loss of hydraulic pump.
4, this system is provided with the motor that pressure switch controls, not enough in accumulator function or send out
During raw fault, can carry out undercarriage control by motor-driven hydraulic pumps, add system can
By property.
5, pressure transducer detection system pressure it is equipped with, it is ensured that system it will be seen that accumulator fills
The real time information of system pressure when pressure situation and undercarriage control.
6, this system structure is simple, it is simple to Integration Design.
Accompanying drawing explanation
Fig. 1 is the schematic diagram of the present invention；
In figure: 1 is hydraulic oil container, 2 is oil filter, and 3 is hydraulic pump, and 4 is check valve, and 5 are
Stop valve, 6 is relief valve, and 7 is accumulator, and 8 is pressure transducer, and 9 is bi-bit bi-pass electricity
Magnet valve, 10 is overflow valve, and 11 is three position four-way electromagnetic valve, and 12 is choke valve, and 13 for rising and falling
Frame retractable actuating cylinder, 14 is motor, and 15 is pressure switch, and 16 is wheel.
Detailed description of the invention
Below in conjunction with the accompanying drawings the present invention is elaborated.
As it is shown in figure 1, described hydraulic system includes: fuel tank 1, hydraulic filter 2, hydraulic pump
3, check valve 4, stop valve 5, relief valve 6, accumulator 7, pressure transducer 8, two
Two-way electromagnetic valve 9, overflow valve 10, three position four-way electromagnetic valve 11, choke valve 12, undercarriage
Retractable actuating cylinder 13, motor 14, pressure switch 15, wheel 16, is characterized in that, hydraulic pump
The drive shaft of 3 connects respectively at wheel 16 and motor 14, hydraulic pump 3 oil absorbing end and filtration
Device 2 one end connects, and the other end of filter 2 connects the hydraulic oil container 1 of aircraft, hydraulic pump 3
Pressure output is connected with one end of check valve 4, the other end of check valve 4 respectively with stop valve
One end of 5 connects with the oil-in of pressure transducer 8 and two-position two-way solenoid valve 9 respectively, cuts
Only the other end of valve 5 oil-in with accumulator 7 and relief valve 6 respectively is connected, relief valve 6
Drain tap and hydraulic oil container 1 connect, the oil-out of two-position two-way solenoid valve 9 respectively with overflow
The P mouth of the oil-in of valve 10, pressure switch 15 and three position four-way electromagnetic valve 11 connects, and three
The T mouth of position four-way solenoid valve 11 drain tap and fuel tank 1 with overflow valve 10 respectively connects, and three
One end of the A mouth of position four-way solenoid valve 11 and choke valve 12 connects, another of choke valve 12
End is connected with the oil-in of undercarriage control pressurized strut 13, the B mouth of three position four-way electromagnetic valve 11
Connect with the oil return opening of undercarriage control pressurized strut 13.
Energy recovery type undercarriage folding and unfolding hydraulic system pressure is from quantitative hydraulic pump 2, fixed
The drive shaft of amount hydraulic pump 2 connects in output shaft and the wheel 16 of motor 14, and wheel 16 revolves
Driving hydraulic pump 3 when turning is accumulator 7 pressurising, when pressurising pressure exceedes the setting of relief valve 6
During pressure, relief valve 6 is opened, and system pressure reduces, thus protects this hydraulic system.Work as machine
When wheel 16 stops the rotation, hydraulic pump 3 quits work, and accumulator 7 Plenum Process terminates；When
When flight control system sends gear up or puts down instruction, two-position two-way solenoid valve 9 is connected, and three
Position four-way solenoid valve 11 is changed to packing up or extended position, the hydraulic energy source of accumulator 7 release
By stop valve 5, two-position two-way solenoid valve 9, three position four-way electromagnetic valve 11 and choke valve 12
Enter undercarriage control pressurized strut 13, complete gear up or put down action, release
After, two-position two-way solenoid valve 9 disconnects, and three position four-way electromagnetic valve 11 conversion is to middle position；This is
System can be adjusted by the unlatching pressure of the flow of regulation choke valve 12 and overflow valve 10 and rise and fall
The time that frame is packed up or put down；Wherein stop valve 5 is in normal open state, when system maintenance,
Close stop valve 5, it is to avoid in system, hydraulic oil liquid flows out；Pressure transducer 8 monitors liquid constantly
Pressure system pressure；Pressure switch 15 monitors system pressure, when system pressure is less than setting value,
Pressure switch 15 is opened, and sends the signal of telecommunication, starts motor 14, for accumulator 7 pressurising.
Claims (3)
1. an energy recovery type undercarriage folding and unfolding hydraulic system, is characterized by: described
Hydraulic system include hydraulic oil container (1), hydraulic pump (3), check valve (4), accumulator (7)
With wheel (16), hydraulic pump (3) is connected by drive mechanism with wheel (16), hydraulic pump
(3) it is connected with accumulator (7), at check valve (4) and accumulator by check valve (4)
(7) with undercarriage voltage supply pipeline connection between.
A kind of energy recovery type undercarriage folding and unfolding hydraulic pressure the most according to claim 1
System, is characterized by: described hydraulic pump (3) is also associated with standby motor (14) simultaneously,
Pressure switch (15), pressure switch are installed between check valve (4) and accumulator (7)
(15) it is connected with standby motor (14).
A kind of energy recovery type undercarriage folding and unfolding hydraulic pressure the most according to claim 1
System, is characterized by: accumulator (7) is by relief valve (6) with hydraulic oil container (1) even
Logical.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510354206.9A CN106314765A (en) | 2015-06-24 | 2015-06-24 | Energy recovery type aircraft undercarriage extension and retraction hydraulic system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510354206.9A CN106314765A (en) | 2015-06-24 | 2015-06-24 | Energy recovery type aircraft undercarriage extension and retraction hydraulic system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106314765A true CN106314765A (en) | 2017-01-11 |
Family
ID=57728828
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510354206.9A Pending CN106314765A (en) | 2015-06-24 | 2015-06-24 | Energy recovery type aircraft undercarriage extension and retraction hydraulic system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106314765A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106945824A (en) * | 2017-05-09 | 2017-07-14 | 昊翔电能运动科技(昆山)有限公司 | A kind of unmanned plane undercarriage and method of rising and falling |
| CN109334960A (en) * | 2018-11-29 | 2019-02-15 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of rotation pressure supply device and the undercarriage with it |
| CN109515696A (en) * | 2018-12-29 | 2019-03-26 | 南通华夏飞机工程技术股份有限公司 | A kind of undercarriage folding and unfolding hydraulic system |
| CN112173088A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Combined pressure accumulator with flow rate control function and hydraulic brake system |
| EP3848279A1 (en) * | 2020-01-09 | 2021-07-14 | Goodrich Corporation | Systems for harvesting rotational wheel energy for landing gear retraction |
-
2015
- 2015-06-24 CN CN201510354206.9A patent/CN106314765A/en active Pending
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106945824A (en) * | 2017-05-09 | 2017-07-14 | 昊翔电能运动科技(昆山)有限公司 | A kind of unmanned plane undercarriage and method of rising and falling |
| CN109334960A (en) * | 2018-11-29 | 2019-02-15 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of rotation pressure supply device and the undercarriage with it |
| CN109334960B (en) * | 2018-11-29 | 2021-10-01 | 中国航空工业集团公司沈阳飞机设计研究所 | Rotary pressure supply device and aircraft landing gear with same |
| CN109515696A (en) * | 2018-12-29 | 2019-03-26 | 南通华夏飞机工程技术股份有限公司 | A kind of undercarriage folding and unfolding hydraulic system |
| CN109515696B (en) * | 2018-12-29 | 2023-10-31 | 南通华夏飞机工程技术股份有限公司 | Hydraulic system for retraction and extension of undercarriage |
| EP3848279A1 (en) * | 2020-01-09 | 2021-07-14 | Goodrich Corporation | Systems for harvesting rotational wheel energy for landing gear retraction |
| US11981447B2 (en) | 2020-01-09 | 2024-05-14 | Goodrich Corporation | Systems for harvesting rotational wheel energy for landing gear retraction |
| EP4393816A3 (en) * | 2020-01-09 | 2024-09-04 | Goodrich Corporation | Systems for harvesting rotational wheel energy for landing gear retraction |
| CN112173088A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Combined pressure accumulator with flow rate control function and hydraulic brake system |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20170111 |