CN106828892A - Course of new aircraft electrohydraulic integration hatch door extension and retraction system - Google Patents
Course of new aircraft electrohydraulic integration hatch door extension and retraction system Download PDFInfo
- Publication number
- CN106828892A CN106828892A CN201710079850.9A CN201710079850A CN106828892A CN 106828892 A CN106828892 A CN 106828892A CN 201710079850 A CN201710079850 A CN 201710079850A CN 106828892 A CN106828892 A CN 106828892A
- Authority
- CN
- China
- Prior art keywords
- hydraulic
- hatch door
- door actuator
- aircraft
- works
- 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.)
- Pending
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/16—Fairings movable in conjunction with undercarriage elements
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/18—Operating mechanisms
- B64C25/22—Operating mechanisms fluid
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/18—Operating mechanisms
- B64C25/24—Operating mechanisms electric
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Power-Operated Mechanisms For Wings (AREA)
Abstract
The disclosure discloses a kind of aircraft door extension and retraction system, and the system includes the local integrated electro-hydraulic bag being made up of motor, hydraulic pump, check valve, accumulator, safety valve, and local integrated electro-hydraulic bag also includes reversal valve and hatch door actuator.The system critical piece is concentrated near aircraft door, only need to be from airborne power supply outgoing cable, you can drive system works.The disclosure is forward-looking with good practicality, and hydraulic power source is substituted using power supply, greatly reduces aircraft on-board systems pipeline quantity, improves aircraft payload；The disclosure also has preferable Reliability And Maintainability.Because hatch door actuating system is integrated near aircraft door, parts are few, and fault rate is low, and dismounting is easy in highly integrated module design, easy to maintenance.The disclosure utilizes accumulator charging, increases system moment service behaviour.The electrical equipment controllability such as motor and reversal valve is high simultaneously, is easy to control.
Description
Technical field
The disclosure belongs to aircraft Actuator technique field, and in particular to a kind of aircraft door extension and retraction system.
Background technology
At present, aircraft door folding and unfolding actuator system concentrates hydraulic power source as the energy using airborne, by hydraulic long-pipe
Road is transferred near undercarriage.Nearby system is various and redundance is backed up for undercarriage, including cabin door lock, recovery spring
Deng device, nearby pipe-line layout is complicated to cause undercarriage, and number of parts is numerous.
With the development of aircraft technology, power-by-wire technology will be one of following main direction of studying, aircraft airborne system
System electrohydraulic integration is, from hydraulic on-board systems to the excessive of fax mobile system, to substitute multiple-energy-source using unification power supply and mix
The airborne energy, mobile system energy utilization rate is greatly improved with reliability.Aircraft door system is used as important airborne start
Device system, current technology is more ripe, is widely used, but is the absence of development space.
The content of the invention
Based on this, the disclosure discloses a kind of aircraft door extension and retraction system, and the system includes：Local integrated electro-hydraulic bag,
Reversal valve and hatch door actuator；
The local integrated electro-hydraulic bag is used to provide power source for the hatch door extension and retraction system, and under the drive of motor
Output hydraulic oil, drives the flexible work of hatch door actuator.
The reversal valve is used to control the flow direction of hydraulic oil, works in hatch door actuator and stretches out or contraction-like
State；
The hatch door actuator is used for open and close undercarriage hatch door.
The disclosure has the advantages that：
(1) disclosure is forward-looking substitutes hydraulic power source with good practicality using power supply, greatly reduces aircraft airborne
System pipeline quantity, improves aircraft payload
(2) disclosure has preferable Reliability And Maintainability.Due to hatch door actuating system, to be integrated in aircraft door attached
Closely, parts are few, and fault rate is low, and dismounting is easy in highly integrated module design, easy to maintenance.
(3) disclosure has good system dynamic and controllability.Using accumulator charging, increase system
Moment service behaviour.The electrical equipment controllability such as motor and reversal valve is high simultaneously, is easy to control.
Brief description of the drawings
Fig. 1 is a kind of aircraft door extension and retraction system principle schematic diagram. of the disclosure；
Fig. 2 is a kind of schematic layout pattern of aircraft door extension and retraction system of the disclosure；
Fig. 3 is that the system of the disclosure works in fluid when stretching out state and flows to schematic diagram；
Fig. 4 is that fluid flows to schematic diagram when the system of the disclosure works in contraction state.
Specific embodiment
Son is described further to the disclosure with reference to the accompanying drawings and examples.
In one embodiment, the disclosure discloses a kind of aircraft door extension and retraction system, and the system includes：It is local electro-hydraulic
One bag, reversal valve and hatch door actuator；
The local integrated electro-hydraulic bag is used to provide power source for the hatch door extension and retraction system, and under the drive of motor
Output hydraulic oil, drives the flexible work of hatch door actuator.
The reversal valve is used to control the flow direction of hydraulic oil, works in hatch door actuator and stretches out or contraction-like
State；
The hatch door actuator is used for open and close undercarriage hatch door.
In the present embodiment, the present disclosure proposes by the use of airborne power supply as power resources, collect near driving aircraft door
Into electrohydraulic integration actuating system, complete hatch door draw-in and draw-off function, substitute the existing all-hydraulic hatch door extension and retraction system of aircraft.
The invention aims to reduce aircraft door extension and retraction system hydraulic redundancy pipeline, increase aircraft payload, improve system
Reliability.
In one embodiment, the local integrated electro-hydraulic bag includes：Motor, hydraulic pump, check valve, accumulator, safety
Valve；
The motor belt motor hydrodynamic pressure pump blade rotation, makes hydraulic pump works；
The hydraulic pump rotates under the drive of motor, and from low pressure hydraulic fluid port oil suction, high pressure hydraulic fluid port oil extraction is that the system is defeated
Go out required high-voltage oil liquid.
The check valve is used to prevent fluid from reversely flowing into hydraulic pump from hatch door actuator.
The accumulator be used for storage energy, and for work in the system zero-time release store energy with
Overcome the rest inertia power of aircraft door；
The safety valve is used to, when the operating pressure of hydraulic pump in integrated electro-hydraulic bag is more than rated value, turn on off-load, makes
The high pressure hydraulic fluid port of hydraulic pump, the conducting of low pressure hydraulic fluid port so that unnecessary operating pressure flows to low pressure hydraulic fluid port from high pressure hydraulic fluid port.
More excellent, the accumulator is additionally operable to supplement fluid for system.
In the present embodiment, it is as shown in Figure 1 by motor, hydraulic pump, check valve, accumulator, safety valve constitute it is local
Integrated electro-hydraulic bag, also reversal valve and hatch door actuator.As Fig. 2, system critical piece are concentrated near aircraft door, only need
From airborne power supply outgoing cable, you can drive system works.When aircraft door needs work, airborne power supply is carried for whole system
Power supply power, motor work drives hydraulic pump output hydraulic oil, flows through check valve.By controlling the port position of reversal valve, control
The flow direction of hydraulic oil, makes hatch door actuator work in the state stretched out or shrink.The effect of accumulator is storage in figure
Energy, in the energy of the zero-time release storage of system work, overcomes the rest inertia power of hatch door；Accumulator is also promising simultaneously
System supplements the function of fluid；When operating pressure or flow are more than rated value, safety valve conducting off-load, it is ensured that system safety
Operation.
In one embodiment, when reversal valve works in left position, hatch door actuator works in the state of stretching out；
When commutator works in right position, hatch door actuator works in contraction state；
When commutator is in middle position, hatch door actuator is in self-locking state.
In this embodiment, as Fig. 3 represents that reversal valve works in left position, hatch door actuator works in the state of stretching out, i.e. hatch door
The flow direction of fluid in opening process；Fig. 4 represents that reversal valve works in right position, and hatch door actuator works in contraction state, i.e.,
The flow direction of fluid in hatch door closing course.When system does not work, the connection with airborne power supply is cut off, during reversal valve is in
Position, hatch door actuator is in self-locking state.
Here the description of the disclosure and application are illustrative, are not wishing to for the scope of the present disclosure to be limited in above-described embodiment
In.The deformation and change of embodiments disclosed herein are possible, real for the ordinary skill of those this areas is any
The replacement and equivalent various parts for applying example are known.Art technology is any it is noted that not departing from the disclosure
Spirit or essential characteristics in the case of, various substitutions and modifications are all possible.Therefore, the disclosure should not be limited to embodiment
Disclosure of that, the claimed scope of the disclosure is defined by the scope that claims are defined.
Claims (4)
1. a kind of aircraft door extension and retraction system, it is characterised in that the system includes：Local integrated electro-hydraulic bag, reversal valve and cabin
Door actuator；
The local integrated electro-hydraulic bag is used to provide power source for the hatch door extension and retraction system, and is exported under the drive of motor
Hydraulic oil, drives the flexible work of hatch door actuator.
The reversal valve is used to control the flow direction of hydraulic oil, works in hatch door actuator and stretches out or contraction state；
The hatch door actuator is used to be turned on or off undercarriage hatch door.
2. system according to claim 1, it is characterised in that the local integrated electro-hydraulic bag includes：Motor, hydraulic pump,
Check valve, accumulator, safety valve；
The motor belt motor hydrodynamic pressure pump blade rotation, makes hydraulic pump works；
The hydraulic pump rotates under the drive of motor, and from low pressure hydraulic fluid port oil suction, high pressure hydraulic fluid port oil extraction is the system output institute
The high-voltage oil liquid for needing.
The check valve is used to prevent fluid from reversely flowing into hydraulic pump from hatch door actuator.
The accumulator be used for storage energy, and for work in the system zero-time release store energy to overcome
The rest inertia power of aircraft door；
The safety valve is used to, when the operating pressure of hydraulic pump in integrated electro-hydraulic bag is more than rated value, turn on off-load, makes hydraulic pressure
The high pressure hydraulic fluid port of pump, the conducting of low pressure hydraulic fluid port so that unnecessary operating pressure flows to low pressure hydraulic fluid port from high pressure hydraulic fluid port.
3. system according to claim 2, it is characterised in that：The accumulator is additionally operable to supplement fluid for system.
4. system according to claim 1, it is characterised in that：When reversal valve works in left position, the work of hatch door actuator
In the state of stretching out；
When commutator works in right position, hatch door actuator works in contraction state；
When commutator is in middle position, hatch door actuator is in self-locking state.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610977530 | 2016-11-08 | ||
| CN2016109775300 | 2016-11-08 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106828892A true CN106828892A (en) | 2017-06-13 |
Family
ID=59128813
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710079850.9A Pending CN106828892A (en) | 2016-11-08 | 2017-02-15 | Course of new aircraft electrohydraulic integration hatch door extension and retraction system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106828892A (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107217940A (en) * | 2017-07-07 | 2017-09-29 | 北京航空航天大学 | A kind of hydraulic booster energy storage hatch door actuating system |
| CN107313674A (en) * | 2017-07-07 | 2017-11-03 | 北京航空航天大学 | A kind of electronic supercharging energy storage hatch door actuating system |
| CN107816279A (en) * | 2017-09-12 | 2018-03-20 | 陕西飞机工业（集团）有限公司 | A kind of transporter cargo hold gate is low shake make an uproar than control system |
| CN108984917A (en) * | 2018-07-20 | 2018-12-11 | 北京航空航天大学 | Large aircraft flies control actuating system intelligent design and evaluation method |
| CN109515694A (en) * | 2018-03-16 | 2019-03-26 | 陕西飞机工业（集团）有限公司 | A kind of control system being automatically prevented from the non-mandatory unlatching of undercarriage door |
| CN110296110A (en) * | 2019-06-14 | 2019-10-01 | 庆安集团有限公司 | A kind of Dual-energy source hatch door transient state actuating system |
| CN110985331A (en) * | 2019-12-02 | 2020-04-10 | 北京航空航天大学 | Intelligent pump and active disturbance rejection control method thereof |
| CN111089088A (en) * | 2019-12-27 | 2020-05-01 | 中国航空工业集团公司沈阳飞机设计研究所 | Multi-mechanism series connection motion coordination control loop |
| CN114278626A (en) * | 2021-12-23 | 2022-04-05 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Airborne emergency hydraulic system and method for electric pressurization energy storage flow compensation |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1705585A (en) * | 2002-10-22 | 2005-12-07 | 波音公司 | Electric-based secondary power system architectures for aircraft |
| CN103953244A (en) * | 2014-04-25 | 2014-07-30 | 哈尔滨飞机工业集团有限责任公司 | Hydraulic control mechanism for cabin door of plane |
| CN105620752A (en) * | 2015-02-28 | 2016-06-01 | 北京航空航天大学 | Power-by-wire-based new-principle cabin door transient actuating system |
| CN105620730A (en) * | 2015-02-28 | 2016-06-01 | 北京航空航天大学 | Airplane hydraulic system layout based on hydraulic and power-by-wire boosting and energy storing devices |
| CN105730681A (en) * | 2015-02-28 | 2016-07-06 | 北京航空航天大学 | Airplane hydraulic system layout based on power-by-wire energy storage device |
-
2017
- 2017-02-15 CN CN201710079850.9A patent/CN106828892A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1705585A (en) * | 2002-10-22 | 2005-12-07 | 波音公司 | Electric-based secondary power system architectures for aircraft |
| CN103953244A (en) * | 2014-04-25 | 2014-07-30 | 哈尔滨飞机工业集团有限责任公司 | Hydraulic control mechanism for cabin door of plane |
| CN105620752A (en) * | 2015-02-28 | 2016-06-01 | 北京航空航天大学 | Power-by-wire-based new-principle cabin door transient actuating system |
| CN105620730A (en) * | 2015-02-28 | 2016-06-01 | 北京航空航天大学 | Airplane hydraulic system layout based on hydraulic and power-by-wire boosting and energy storing devices |
| CN105730681A (en) * | 2015-02-28 | 2016-07-06 | 北京航空航天大学 | Airplane hydraulic system layout based on power-by-wire energy storage device |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107313674A (en) * | 2017-07-07 | 2017-11-03 | 北京航空航天大学 | A kind of electronic supercharging energy storage hatch door actuating system |
| CN107217940B (en) * | 2017-07-07 | 2018-06-22 | 北京航空航天大学 | A kind of hydraulic booster energy storage hatch door actuating system |
| CN107217940A (en) * | 2017-07-07 | 2017-09-29 | 北京航空航天大学 | A kind of hydraulic booster energy storage hatch door actuating system |
| CN107816279A (en) * | 2017-09-12 | 2018-03-20 | 陕西飞机工业（集团）有限公司 | A kind of transporter cargo hold gate is low shake make an uproar than control system |
| CN107816279B (en) * | 2017-09-12 | 2020-01-14 | 陕西飞机工业（集团）有限公司 | Control system for low vibration noise ratio of cargo hold gate of conveyor |
| CN109515694B (en) * | 2018-03-16 | 2022-04-19 | 陕西飞机工业（集团）有限公司 | Control system for automatically preventing non-instruction opening of landing gear cabin door |
| CN109515694A (en) * | 2018-03-16 | 2019-03-26 | 陕西飞机工业（集团）有限公司 | A kind of control system being automatically prevented from the non-mandatory unlatching of undercarriage door |
| CN108984917A (en) * | 2018-07-20 | 2018-12-11 | 北京航空航天大学 | Large aircraft flies control actuating system intelligent design and evaluation method |
| CN110296110A (en) * | 2019-06-14 | 2019-10-01 | 庆安集团有限公司 | A kind of Dual-energy source hatch door transient state actuating system |
| CN110985331A (en) * | 2019-12-02 | 2020-04-10 | 北京航空航天大学 | Intelligent pump and active disturbance rejection control method thereof |
| CN111089088A (en) * | 2019-12-27 | 2020-05-01 | 中国航空工业集团公司沈阳飞机设计研究所 | Multi-mechanism series connection motion coordination control loop |
| CN114278626A (en) * | 2021-12-23 | 2022-04-05 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Airborne emergency hydraulic system and method for electric pressurization energy storage flow compensation |
| CN114278626B (en) * | 2021-12-23 | 2023-11-07 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Onboard emergency hydraulic system and method for electric supercharging energy storage flow compensation |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106828892A (en) | Course of new aircraft electrohydraulic integration hatch door extension and retraction system | |
| CN103072687B (en) | Take-off and landing device, aircraft and the method implemented by take-off and landing device | |
| CN103459857B (en) | The fluid pressure drive device of Work machine | |
| CN105570237B (en) | A kind of double redundancy electromechanical static pressure servo mechanism | |
| RU2544251C2 (en) | Aircraft control system | |
| CN103803063A (en) | Self-energy feedback type brake apparatus-based airplane braking system and control method thereof | |
| US20090242694A1 (en) | Hydraulic system for aircraft | |
| CN102733442B (en) | Gyration energy recycling system of hydraulic excavator | |
| CN104328817B (en) | A kind of energy-recuperation system | |
| US20180245565A1 (en) | Control system for submersible electric motor drive control | |
| CN105620730B (en) | Plane hydraulic system layout based on hydraulic pressure and power-by-wire boosting energy storage device | |
| CN105620752A (en) | Power-by-wire-based new-principle cabin door transient actuating system | |
| CN203428881U (en) | Hydraulic control system of cantilever crane or ladder frame | |
| CN105730681A (en) | Airplane hydraulic system layout based on power-by-wire energy storage device | |
| CN105366040A (en) | Double-switch-valve-based self-powdering brake apparatus and system | |
| CN110701116B (en) | Closed pump control system with safety reset and safety reset method thereof | |
| CN105365801A (en) | Apparatus and method for controlling a hydraulic brake of an aircraft | |
| CN107313674A (en) | A kind of electronic supercharging energy storage hatch door actuating system | |
| CN105620724B (en) | Airplane hydraulic pressure layout system based on hydraulic energy storage device | |
| CN106314765A (en) | Energy recovery type aircraft undercarriage extension and retraction hydraulic system | |
| CN103669462A (en) | Mixed-type hydraulic device | |
| CN105015316A (en) | Hydraulic hybrid power transmission system with self-adaption switching function | |
| CN109185284A (en) | Electric hydrostatic actuator system control method with energy recycling system | |
| CN105605038B (en) | A kind of suitable load energy regenerating electricity hydrostatic actuating system | |
| CN102530784A (en) | Work arm hydraulic system of high-altitude operation vehicle and high-altitude operation vehicle with the hydraulic system |
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 | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20170613 |
|
| RJ01 | Rejection of invention patent application after publication |