CN105730681B - Plane hydraulic system layout based on power-by-wire energy storage device - Google Patents
Plane hydraulic system layout based on power-by-wire energy storage device Download PDFInfo
- Publication number
- CN105730681B CN105730681B CN201510958685.5A CN201510958685A CN105730681B CN 105730681 B CN105730681 B CN 105730681B CN 201510958685 A CN201510958685 A CN 201510958685A CN 105730681 B CN105730681 B CN 105730681B
- Authority
- CN
- China
- Prior art keywords
- energy
- storage module
- hatch door
- accumulator
- aileron
- 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.)
- Active
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/24—Transmitting means
- B64C13/38—Transmitting means with power amplification
- B64C13/40—Transmitting means with power amplification using fluid pressure
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/24—Transmitting means
- B64C13/38—Transmitting means with power amplification
- B64C13/50—Transmitting means with power amplification using electrical energy
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
- F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
- F15B1/00—Installations or systems with accumulators; Supply reservoir or sump assemblies
- F15B1/02—Installations or systems with accumulators
Abstract
The application is related to a kind of plane hydraulic system layout based on power-by-wire energy storage device, including spoiler aileron accumulator, for driving spoiler steering wheel and aileron steering wheel；Hatch door accumulator, for driving hatch door actuator；Empennage accumulator, for distinguishing driving direction rudder steering wheel and elevator steering wheel；Wherein, spoiler aileron accumulator, hatch door accumulator and empennage accumulator are connected with the fly-by-wire of aircraft, and energy storage or start are carried out for the output order based on fly-by-wire.It is laid out using the plane hydraulic system based on power-by-wire energy storage device of the application, aircraft installed power can be reduced.
Description
Technical field
The application is related to hydraulic system field, particularly a kind of plane hydraulic system cloth based on power-by-wire energy storage device
Office.
Background technology
Plane hydraulic system is one of main mobile system of aircraft.The primary control circuit of present generation aircraft and assisted control system
The control of system and executing agency are used as executing agency all using hydraulic pressure as the energy using hydraulic actuator or hydraulic motor.Aircraft liquid
Pressure system refers to that using fluid as working media on aircraft completing a whole set of of particular manipulation action by oil pressure actuated executing agency fills
Put.To ensure that hydraulic work system is reliable, the reliability of the hydraulic power supply of flight control system, present generation aircraft are particularly improved
It is upper that two sets of (or more sets) separate hydraulic systems are housed mostly.They are referred to as public hydraulic system and power-assisted (manipulation)
Hydraulic system.Hydraulic system such as Boeing 777 airplane is made up of the system that three independent operating pressures are 20.6MPa, as
The energy for control, high lift device, trhrust-reversal device and the takeoff and anding steerable system of flying.For further improve hydraulic system can
Emergent electric oil pump and air sump pump are also parallel with by property, in system, hydraulic system is lost energy when aircraft engine breaks down
During source, by emergent electric oil pump or the emergent air sump pump of stretching hydraulic system can be made to work on.
Plane hydraulic system with lower part generally by being formed：
Voltage supply part：Including main oil pump, emergent oil pump and accumulator.Main oil pump is mounted in the transmission casing of aircraft engine
On, by driven by engine.Accumulator is used to keep whole system stable working.
Executable portion：Including pressurized strut, hydraulic motor and booster.The pressure energy of fluid is converted into machinery by them
Energy.
Control section：For the direction of motion of the fluid flow in control system, pressure and executive component, including pressure
Valve, flow valve, direction valve and servo valve etc..
Slave part：The environmental condition of guarantee system worked well, the element needed for indicating operating status, including fuel tank,
Conduit, oily filter, pressure gauge and radiator etc..
Hydraulic system has advantages below：Weight per unit power is small, system efficiency of transmission is high, simple installation is flexible, inertia
Small, dynamic response is fast, control velocity interval is wide, fluid has lubrication, moving parts not easy to wear in itself.
Hydraulic system is as present generation aircraft primary drive system, for ensureing that aircraft safety flight plays an important role,
Performance, stability, the reliability of hydraulic system directly affect the maneuverability and security of aircraft.In recent years, with the military and people
With the continuous improvement of aeroplane performance, plane hydraulic system has a significant progress in terms of configuration and layout, and aircraft is totally right
Hydraulics weight and volume propose harsher requirement, and this forces plane hydraulic system to develop to high-pressure trend direction.Improve
Hydraulic system pressure can be effectively reduced system weight, reduce aircraft volume, improve system response.
Plane hydraulic system pressure rank is one of most basic parameter of plane hydraulic system.Plane hydraulic system at present
Pressure rank has 21MPa, 28MPa, 35MPa.Currently, the raising of plane hydraulic system pressure rating is all to pass through engine driving
Pump (EDP) output high pressure hydraulic oil realizes that this method has following shortcoming：
Need to develop the Engine Driven Pump (EDP) of high pressure grade, the requirement to EDP is harsher.
Fluid pressure line from EDP to steering wheel is high pressure grade pipeline, and the requirement to pipeline is harsher.
EDP and pipeline needs are high pressure resistant, cause part more thick and heavy, so as to increase aircraft weight.
The content of the invention
The brief overview on the application is given below, so as to provide on the application it is some in terms of basic reason
Solution.It should be appreciated that this general introduction is not the exhaustive general introduction on the application.It is not intended to determine the key of the application
Or pith, nor intended limitation scope of the present application.Its purpose only provides some concepts in simplified form, with
This is as the preamble in greater detail discussed later.
The main purpose of the application is to provide a kind of plane hydraulic system cloth based on power-by-wire energy storage device
Office, it can reduce aircraft installed power.
According to the one side of the application, a kind of plane hydraulic system layout based on power-by-wire energy storage device, including：
Spoiler aileron accumulator, for driving spoiler steering wheel and aileron steering wheel；
Hatch door accumulator, for driving hatch door actuator；
Empennage accumulator, for distinguishing driving direction rudder steering wheel and elevator steering wheel；
Wherein, the fax of the spoiler aileron accumulator, hatch door accumulator and the empennage accumulator with aircraft is grasped
Vertical system connection, energy storage or start are carried out for the output order based on the fly-by-wire.
It is laid out using the plane hydraulic system based on power-by-wire energy storage device of the application, is boosted and stored up by power-by-wire
Energy device improves hydraulic system pressure grade, plane hydraulic system is realized high-pressure trend, the method for realizing high-pressure trend is not to lead to
Cross Engine Driven Pump (EDP) output high pressure hydraulic oil to realize, but boosted close to valve control steering wheel end by power-by-wire
Energy storage device is realized.Also, realize that big transient power is made using the input of small continuous power by power-by-wire boosting energy storage device
It is dynamic, reduce aircraft installed power.
Brief description of the drawings
With reference to the explanation of the embodiment of the present application, can be more readily understood that below in conjunction with the accompanying drawings the application more than and its
Its objects, features and advantages.Part in accompanying drawing is intended merely to show the principle of the application.In the accompanying drawings, identical or similar
Technical characteristic or part will be represented using same or similar reference.
Fig. 1 is a kind of showing for embodiment of the layout of the plane hydraulic system based on power-by-wire energy storage device of the application
It is intended to；
Fig. 2 is a kind of structure chart of embodiment of each energy-storage module in Fig. 1.
Embodiment
Illustrate embodiments herein with reference to the accompanying drawings.Retouched in the accompanying drawing of the application or a kind of embodiment
The element and feature that the element and feature stated can be shown in one or more other accompanying drawings or embodiment are combined.Should
Work as attention, for purposes of clarity, eliminated in accompanying drawing and explanation known to, those of ordinary skill in the art unrelated with the application
Part and processing expression and description.
It is shown in Figure 1, it is that one kind of the layout of the plane hydraulic system based on power-by-wire energy storage device of the application is real
Apply the structure chart 100 of mode.
In the present embodiment, the plane hydraulic system layout based on power-by-wire energy storage device includes the storage of spoiler aileron
Energy device 110, for driving spoiler steering wheel and aileron steering wheel；
Hatch door accumulator 120, for driving hatch door actuator；
Empennage accumulator 130, for distinguishing driving direction rudder steering wheel and elevator steering wheel；
Wherein, the fax of spoiler aileron accumulator 110, hatch door accumulator 120 and empennage accumulator 130 with aircraft is grasped
Vertical system connection, energy storage or start are carried out for the output order based on fly-by-wire.
In one embodiment, spoiler aileron accumulator 110 can include being used to drive left spoiler and port aileron
Left spoiler aileron energy-storage module and right spoiler aileron energy-storage module for driving right spoiler and starboard aileron.
Hatch door accumulator 120 can include being used to drive the left hatch door energy-storage module of left hatch door actuator and for driving the right side
The right hatch door energy-storage module of hatch door actuator.
Empennage accumulator 130 can include for the rudder energy-storage module of driving direction rudder steering wheel and be lifted for driving
The elevator energy-storage module of rudder steering wheel.
In one embodiment, as shown in Fig. 2 each energy-storage module (i.e. left spoiler aileron energy-storage module, right flow-disturbing
Plate aileron energy-storage module, left hatch door energy-storage module, right hatch door energy-storage module, rudder energy-storage module and elevator energy-storage module)
Include motor 1, hydraulic pump 3, accumulator 7 and servo valve 8.
Wherein, motor 1 is connected with the output end of fly-by-wire, and the command signal for being exported based on it controls electricity
The rotating speed of motivation 1.Hydraulic pump 3 is connected to the output shaft of motor 1, for being rotated under the drive of motor 1.
Servo valve 8 includes control terminal, first input end, the second input, the first output end and the second output end.Servo valve
8 are used for based on the external control signal for being input to control terminal while control connection/cut-off of first input end and the first output end
With connection/cut-off of the second input and the second output end.For example, when external control signal instruction servo valve 8 is connected, first is defeated
Enter end to connect with the first output end, the second input connects with the second output end.
Hydraulic pump 3 includes oil-out and oil inlet, and oil-out is connected with the first input end of servo valve 8, and oil inlet is with watching
Take the second input connection of valve 8.The oil-out and oil inlet of hydraulic pump 3 are connected to airborne tank.
Accumulator is connected on the oil circuit between oil-out and first input end.
As a kind of preferred scheme, each energy-storage module can also include being connected to the defeated of oil-out and fly-by-wire
The feedback device 5 gone out between end.
Feedback device is used for the command signal that the output end of the Flow-rate adjustment fly-by-wire based on oil-out exports, from
And control the rotating speed of motor 1.
In one embodiment, feedback device 5 for example can be pressure sensor.
Preferably, each energy-storage module of the application can also include being connected to accumulator 7 and hydraulic pump 3 oil-out it
Between check valve 6.Check valve 6 can prevent the fluid in accumulator 7 from entering in hydraulic pump 3.
Preferably, each energy-storage module of the application can also include being connected to the oil inlet of hydraulic pump 3 and oil-out it
Between safety valve 4.
When the pressure difference of oil inlet and oil-out is more than a predetermined value, safety valve 4 is opened, to avoid whole each energy storage mould
The hypertonia of block.
Each energy-storage module of present embodiment also include be connected to servo valve 8 the first output end and the second output end it
Between hatch door hydraulic motor 9.Hydraulic motor 9 is used for the first output end based on servo valve 8 and the hydraulic pressure of the second output end output
Action is performed to left spoiler aileron, right spoiler aileron, left hatch door, right hatch door, rudder and elevator respectively.
In addition, in one embodiment, each energy-storage module can also include transmission device 2, hydraulic pump 3 fills through transmission
3 output shafts for being connected to motor 1 are put, so as to which the output kinetic energy of motor 1 is transferred into hydraulic pump 3.
In each energy-storage module work of the application, the output end output motor rotary speed instruction letter of fly-by-wire
Number, the size instructed according to motor speed, the rotary work of motor 1, drive hydraulic pump 4 to rotate by transmission mechanism 3, export
Hydraulic oil, high-voltage oil liquid flow to accumulator 7 and servo valve 8 through check valve 6.Pressure before the collection check valve 6 of pressure sensor 5 is anti-
It is fed in the output end of fly-by-wire, forms closed loop, the output end of fly-by-wire is according to the pressure sensing collected
The size of device signal, the size of motor command signal is adjusted in real time, so as to control motor speed in real time.
Finally, hydraulic oil liquid airborne tank provided, by hydraulic pump pressurising to high pressure conditions, accumulator is arrived in storage
In, when hatch door start, accumulator provides transient state big flow.Wherein, it is small continuous power to Energy Accumulator in Plenum Process, and makees
Dynamic process is then big transient power.
Specifically, in thermal energy storage process is pressurized, servo valve 8 is closed, and motor 1 receives the output end of fly-by-wire
Rotary speed instruction signal, start working, drive hydraulic pump 3 to rotate, the hydraulic oil liquid that hydraulic pump 3 provides airborne tank is converted into height
Force feed, by check valve 6, is stored in accumulator 7.Before pressure sensor 5 detects high pressure conditions, motor 1 is kept
Worked under small continuous power state, when pressure sensor 5 detects high pressure conditions, motor 1 reduces rotating speed, keeps extremely low
Idling mode, to maintain system high pressure state.Now, supercharging thermal energy storage process terminates.
During hatch door start, servo valve 8 is opened, and hatch door start needs transient state big flow, is stored in accumulator 7
High-voltage oil liquid abrupt release, to ensure the traffic demand of hatch door start.Now, because the pressure of accumulator 7 discharges, pressure sensor
5 can not detect high pressure conditions, and motor 1 is maintained under small continuous power state and worked again, until accumulator 7 is full of,
Reach high pressure conditions.
The specific completion form of the layout of the plane hydraulic system based on power-by-wire energy storage device of the application is as follows：
Aircraft generator produces electric power, is transmitted by cable from head to tail, when reaching left and right spoiler, left and right flow-disturbing
The spoiler aileron energy storage device of plate configuration produces high-pressure and hydraulic fluid, converts electrical energy into hydraulic energy, is conveyed to left and right flow-disturbing
Plate steering wheel, while it is conveyed to left and right aileron steering wheel.
Electric power continues to transmit toward tail, and when reaching left and right hatch door, the hatch door energy storage device of left and right hatch door configuration produces high pressure
Hydraulic oil liquid, hydraulic energy is converted electrical energy into, be conveyed to hatch door actuator.
Electric power continues to transmit toward tail, when reaching left and right undercarriage, the undercarriage energy storage device production of left and right undercarriage configuration
Raw high-pressure and hydraulic fluid, converts electrical energy into hydraulic energy, is conveyed to left and right undercarriage actuator.
Electric power continues to transmit toward tail, reaches the tail of left and right elevator and rudder, left and right elevator and rudder configuration
Wing energy storage device produces high-pressure and hydraulic fluid, converts electrical energy into hydraulic energy, is conveyed to left and right elevator and rudder；
So far, the plane hydraulic system layout based on power-by-wire boosting energy storage device is completed, passes through each pressure energy storage device
Improve plane hydraulic system pressure rating, plane hydraulic system is realized high-pressure trend, realize the method for high-pressure trend not by
Engine Driven Pump (EDP) output high pressure hydraulic oil is realized, but is stored up being boosted close to valve control steering wheel end by power-by-wire
Can device realization.Also, big transient power start is realized using the input of small continuous power by power-by-wire boosting energy storage device,
Reduce aircraft installed power.
The layout of the plane hydraulic system based on power-by-wire energy storage device of the application, has advantages below：
Plane hydraulic system pressure rating is improved by power-by-wire boosting energy storage device, it is not necessary to Engine Driven Pump
(EDP) aircraft weight, is reduced.
Energy storage device before from aircraft generator to steering wheel is cable, it is not necessary to fluid pressure line, eliminates pipeline vibration
And leakage problem, reduce aircraft weight.
Hydraulic system pressure grade is improved by each energy storage device, plane hydraulic system is realized high-pressure trend, improves rudder
Acc power density, steering wheel size and weight are reduced, so as to reduce aircraft weight.
Power-by-wire boosting energy storage device can utilize the input of small continuous power to realize big transient power start, reduce rudder
The peak flow that machine start needs, so as to reduce aircraft peak flow and installed power.
Some embodiments of the application are described in detail above.Such as one of ordinary skill in the art institute energy
Understand, the whole either any steps or part of the present processes and device, can any computing device (including place
Manage device, storage medium etc.) or the network of computing device in, realized with hardware, firmware, software or combinations thereof,
This is that those of ordinary skill in the art just can be real with their basic programming skill in the case where understanding present context
Existing, therefore be not required to illustrate herein.
It is further clear that when being related to possible peripheral operation in superincumbent explanation, undoubtedly to use
With any computing device be connected any display device and any input equipment, corresponding interface and control program.Sum it up,
Related hardware, software in computer, computer system or computer network and realize each in the preceding method of the application
Hardware, firmware, software or the combinations thereof of kind operation, that is, form the equipment of the application and its each building block.
Therefore, based on above-mentioned understanding, the purpose of the application can also be by running one on any message processing device
Program or batch processing are realized.Described information processing equipment can be known common apparatus.Therefore, the purpose of the application
It can also be realized only by the program product comprising the program code for realizing methods described or equipment is provided.Namely
Say, such program product also forms the application, and the medium of program product also forms this Shen as storage or transmission
Please.Obviously, either transmission medium can be well known by persons skilled in the art or what is developed in the future appoints for the storage
The storage of what type or transmission medium, therefore also It is not necessary to be enumerated at this to various storages or transmission medium.
In the apparatus and method of the application, it is clear that each part or each step are after can decomposing, combine and/or decomposing
Reconfigure.These decompose and/or reconfigured the equivalents that should be regarded as the application.It may also be noted that on performing
The step of stating series of processes can order naturally following the instructions perform in chronological order, but and need not necessarily according to when
Between sequentially perform.Some steps can perform parallel or independently of one another.Meanwhile the application specific embodiment is retouched above
In stating, the feature for describing and/or showing for a kind of embodiment can be in a manner of same or similar one or more
Used in other embodiment, it is combined with the feature in other embodiment, or substitute the feature in other embodiment.
It should be emphasized that term "comprises/comprising" refers to the presence of feature, key element, step or component when being used herein, but simultaneously
It is not excluded for the presence or additional of one or more further features, key element, step or component.
Although the application and its advantage is described in detail it should be appreciated that without departing from by appended claim
Various changes, replacement and conversion can be carried out in the case of the spirit and scope limited.Moreover, the model of the application
Enclose the process described by specification of being not limited only to, equipment, means, the specific embodiment of method and steps.In the art is common
Technical staff will readily appreciate that from present disclosure, can be used and performed and corresponding reality described herein according to the application
Apply the essentially identical function of example or obtain process essentially identical with it result, existing and that future is to be developed, equipment,
Means, method or step.Therefore, appended claim includes such process, equipment, hand in the range of being directed at them
Section, method or step.
Claims (7)
- A kind of 1. plane hydraulic system layout based on power-by-wire energy storage device, it is characterised in that including：Spoiler aileron accumulator, for driving spoiler steering wheel and aileron steering wheel；Hatch door accumulator, for driving hatch door actuator；Empennage accumulator, for distinguishing driving direction rudder steering wheel and elevator steering wheel；Wherein, the spoiler aileron accumulator, the Flight By Wire system of hatch door accumulator and the empennage accumulator with aircraft System connection, energy storage or start are carried out for the output order based on the fly-by-wire；The spoiler aileron accumulator include be used for drive left spoiler and port aileron left spoiler aileron energy-storage module and For driving the right spoiler aileron energy-storage module of right spoiler and starboard aileron；The hatch door accumulator is including for driving the left hatch door energy-storage module of left hatch door actuator and for driving right hatch door to make The right hatch door energy-storage module of dynamic device；The empennage accumulator includes for the rudder energy-storage module of driving direction rudder steering wheel and for driving elevator steering wheel Elevator energy-storage module；The left spoiler aileron energy-storage module, right spoiler aileron energy-storage module, left hatch door energy-storage module, right hatch door energy storage mould Block, rudder energy-storage module and elevator energy-storage module include respectively：Motor, hydraulic pump, accumulator and servo valve；Wherein, the motor is connected with the output end of the fly-by-wire, for based on the fly-by-wire The command signal of output controls the rotating speed of the motor；The hydraulic pump is connected to the output shaft of the motor, for being rotated under motor drive；The servo valve includes control terminal, first input end, the second input, the first output end and the second output end, described to watch Valve is taken to be used for the external control signal based on input to the control terminal while control the first input end and described first defeated Go out the connection/cut-off at end and connection/cut-off of second input and second output end；The hydraulic pump includes oil-out and oil inlet, and the oil-out is connected with the first input end of the servo valve, described Oil inlet is connected with the second input of the servo valve；The accumulator is connected on the oil circuit between the oil-out and the first input end.
- 2. the plane hydraulic system layout according to claim 1 based on power-by-wire energy storage device, it is characterised in that institute State left spoiler aileron energy-storage module, right spoiler aileron energy-storage module, left hatch door energy-storage module, right hatch door energy-storage module, side Respectively further comprised to rudder energy-storage module and elevator energy-storage module：The feedback device being connected between the oil-out and the fly-by-wire；The feedback device is used for the command signal that fly-by-wire described in the Flow-rate adjustment based on the oil-out exports.
- 3. the plane hydraulic system layout according to claim 2 based on power-by-wire energy storage device, it is characterised in that：The feedback device is pressure sensor.
- 4. the layout of the plane hydraulic system based on power-by-wire energy storage device according to claim 1-3 any one, its It is characterised by, the left spoiler aileron energy-storage module, right spoiler aileron energy-storage module, left hatch door energy-storage module, right hatch door Energy-storage module, rudder energy-storage module and elevator energy-storage module respectively further comprise：It is connected to the accumulator and the hydraulic pressure Check valve between the oil-out of pump；The check valve is used to prevent the fluid in the accumulator from entering in the hydraulic pump.
- 5. the plane hydraulic system layout according to claim 4 based on power-by-wire energy storage device, it is characterised in that institute State left spoiler aileron energy-storage module, right spoiler aileron energy-storage module, left hatch door energy-storage module, right hatch door energy-storage module, side Respectively further comprised to rudder energy-storage module and elevator energy-storage module：The hydraulic motor being connected between the first output end of the servo valve and the second output end；The hatch door hydraulic motor is used for the first output end based on the servo valve and the hydraulic pressure difference of the second output end output Action is performed to left spoiler aileron, right spoiler aileron, left hatch door, right hatch door, rudder and elevator.
- 6. the plane hydraulic system layout according to claim 5 based on power-by-wire energy storage device, the left spoiler Aileron energy-storage module, right spoiler aileron energy-storage module, left hatch door energy-storage module, right hatch door energy-storage module, rudder energy storage mould Block and elevator energy-storage module respectively further comprise：The safety valve being connected between the oil inlet and oil-out of the hydraulic pump；The safety valve is used to open when the pressure difference of the oil inlet and the oil-out is more than a predetermined value.
- 7. the plane hydraulic system layout according to claim 6 based on power-by-wire energy storage device, it is characterised in that institute State left spoiler aileron energy-storage module, right spoiler aileron energy-storage module, left hatch door energy-storage module, right hatch door energy-storage module, side Transmission device is respectively further comprised to rudder energy-storage module and elevator energy-storage module；The hydraulic pump is connected to the output shaft of the motor through the transmission device.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2015100913724 | 2015-02-28 | ||
| CN201510091372 | 2015-02-28 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105730681A CN105730681A (en) | 2016-07-06 |
| CN105730681B true CN105730681B (en) | 2018-03-16 |
Family
ID=56296239
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510958685.5A Active CN105730681B (en) | 2015-02-28 | 2015-12-18 | Plane hydraulic system layout based on power-by-wire energy storage device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105730681B (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106828892A (en) * | 2016-11-08 | 2017-06-13 | 北京航空航天大学 | Course of new aircraft electrohydraulic integration hatch door extension and retraction 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 |
| CN107313674B (en) * | 2017-07-07 | 2018-08-14 | 北京航空航天大学 | A kind of electronic supercharging energy storage hatch door actuating system |
| CN110296110B (en) * | 2019-06-14 | 2020-09-22 | 庆安集团有限公司 | Double-energy cabin door transient actuating system |
| 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 |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202213715U (en) * | 2011-09-02 | 2012-05-09 | 北京航空航天大学 | Multi-power configuration of hydraulic energy system of civil airplane |
| GB2510634B (en) * | 2013-02-12 | 2015-03-04 | Ge Aviat Systems Ltd | Methods of monitoring hydraulic fluid levels in an aircraft |
| US9643716B2 (en) * | 2014-04-01 | 2017-05-09 | The Boeing Company | Air vehicle, actuator assembly and associated method of manufacture |
| CN204775999U (en) * | 2015-04-13 | 2015-11-18 | 中国航空工业集团公司沈阳飞机设计研究所 | Servo system of actuating of aircraft fracture formula rudder |
-
2015
- 2015-12-18 CN CN201510958685.5A patent/CN105730681B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN105730681A (en) | 2016-07-06 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105730681B (en) | Plane hydraulic system layout based on power-by-wire energy storage device | |
| CN105620730B (en) | Plane hydraulic system layout based on hydraulic pressure and power-by-wire boosting energy storage device | |
| Van Den Bossche | The A380 flight control electrohydrostatic actuators, achievements and lessons learnt | |
| CN105314128B (en) | A kind of helicopter integrated ground test platform hydraulic control system | |
| CN105620724B (en) | Airplane hydraulic pressure layout system based on hydraulic energy storage device | |
| CN101687544B (en) | Energy build-up aerodynamic braking method and device | |
| CN103569352B (en) | For producing the method for hydraulic power, the application of hybrid power control unit and drive system in aircraft | |
| CN104765312B (en) | Implementation method for reconfigurable aircraft control system | |
| CN204775999U (en) | Servo system of actuating of aircraft fracture formula rudder | |
| CN103803063A (en) | Self-energy feedback type brake apparatus-based airplane braking system and control method thereof | |
| CN101737380B (en) | Electro-hydraulic load simulator with low-pressure oil pump | |
| US11603209B2 (en) | Aviation hydraulic propulsion system utilizing secondary controlled drives | |
| CN106628123A (en) | Distributed airplane flap control system | |
| CN102795344A (en) | Method for powering autonomous drive motors for aircraft | |
| CN103670801A (en) | Multi-redundancy pump control servo mechanism for thrust vector control of liquid oxygen kerosene engine | |
| WO2012021360A1 (en) | Aircraft emergency and backup secondary power apparatus | |
| CN106828892A (en) | Course of new aircraft electrohydraulic integration hatch door extension and retraction system | |
| CN105620752B (en) | New principle hatch door transient state actuating system based on power-by-wire | |
| CN109445402A (en) | A kind of Fuel On Board system is from monitoring to computer control method | |
| CN102458995A (en) | Aircraft having vertical lift system | |
| CN108750125A (en) | A kind of plane lease of liquid electricity combination drive | |
| CN105523174B (en) | A kind of door cylinder separation type hydraulic servo actuator | |
| CN107450307A (en) | A kind of double remaining control methods of undercarriage of Electromechanical Management computer | |
| CN107804453A (en) | The quiet brake pressure linear control method of digital FBW anti-skid brake system (ABS) | |
| CN107235440A (en) | A kind of liquid electricity mixing energy conserving system for lifting mechanism |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |