CN105730681A - Airplane hydraulic system layout based on power-by-wire energy storage device - Google Patents
Airplane hydraulic system layout based on power-by-wire energy storage device Download PDFInfo
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- CN105730681A CN105730681A CN201510958685.5A CN201510958685A CN105730681A CN 105730681 A CN105730681 A CN 105730681A CN 201510958685 A CN201510958685 A CN 201510958685A CN 105730681 A CN105730681 A CN 105730681A
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- 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
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- 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
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- 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
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- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fluid-Pressure Circuits (AREA)
Abstract
The invention relates to an airplane hydraulic system layout based on a power-by-wire energy storage device. The layout comprises spoiler flap accumulators used for driving spoiler steering engines and flap steering engines, cabin door accumulators used for driving cabin door actuators, and empennage accumulators used for driving rudder steering engines and elevating rudder steering engines, wherein the spoiler flap accumulators, the cabin door accumulators and the empennage accumulators are all connected with a fly-by-wire operation system of an airplane and used for storing energy or acting based on output commands of the fly-by-wire operation system. By the adoption of the airplane hydraulic system layout based on the power-by-wire energy storage device, the installed power of the airplane can be reduced.
Description
Technical field
The application relates to hydraulic system field, particularly a kind of plane hydraulic system layout based on power-by-wire energy storage device.
Background technology
Plane hydraulic system is one of main mobile system of aircraft.The primary control circuit of present generation aircraft and the control of secondary control system and actuator are all using hydraulic pressure as the energy, using hydraulic actuator or hydraulic motor as actuator.Plane hydraulic system refers to fluid for working media on aircraft, completes the package unit of particular manipulation action by oil pressure actuated actuator.For ensureing that hydraulic work system is reliable, particularly improve the reliability of the hydraulic power supply of flight control system, present generation aircraft overlaps, equipped with two, the hydraulic system that (or overlapping) is separate mostly.They are called 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, handles the energy of system as flight control, high lift device, trhrust-reversal device and takeoff and anding.For improving the reliability of hydraulic system further, system is also parallel with emergent electric oil pump and air sump pump, when aircraft engine break down make hydraulic system lose the energy time, can by emergent electric oil pump or stretch out emergent air sump pump and make hydraulic system work on.
Plane hydraulic system is generally formed by with lower part:
For laminate section: include main oil pump, emergent oil pump and accumulator.Main oil pump is contained on the transmission casing of aircraft engine, by driven by engine.Accumulator is used for keeping whole system stable working.
Perform part: include pressurized strut, hydraulic motor and booster.By them, the pressure of fluid can be converted to mechanical energy.
Control part: 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: ensureing the environmental condition of system worked well, the element needed for indicating operating status, including fuel tank, conduit, oil filter, Pressure gauge and radiator etc..
Hydraulic system has the advantage that weight per unit power is little, system transfers efficiency high, simple installation is flexible, inertia is little, dynamic response is fast, control velocity interval width, fluid itself have lubrication, moving parts not easy to wear.
Hydraulic system is as present generation aircraft primary drive system, and for ensureing that aircraft safety flight plays an important role, the performance of hydraulic system, stability, reliability directly affect maneuverability and the safety of aircraft.In recent years, along with improving constantly of dual-use aeroplane performance, plane hydraulic system has had significant progress in configuration and layout, and hydraulics weight and volume are proposed harsher requirement by overall aircraft, and this forces plane hydraulic system to develop to high-pressure trend direction.Improve hydraulic system pressure and 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.The pressure rank of current plane hydraulic system has 21MPa, 28MPa, 35MPa.Currently, the raising of plane hydraulic system pressure rating is all export high pressure hydraulic oil by Engine Driven Pump (EDP) to realize, and this method exists following shortcoming:
Need to develop the Engine Driven Pump (EDP) of high pressure grade, the requirement of EDP is harsher.
Fluid pressure line from EDP to steering wheel is high pressure grade pipeline, and the requirement of pipeline is harsher.
EDP and pipeline need high pressure resistant, cause that part is more thick and heavy, thus increasing aircraft weight.
Summary of the invention
Brief overview about the application given below, in order to the basic comprehension in some of the application is provided.Should be appreciated that this general introduction is not that the exhaustive about the application is summarized.It is not intended to determine the key of the application or pith, neither intended limitation scope of the present application.It is only intended to and provides some concept in simplified form, in this, as the preamble in greater detail discussed after a while.
One main purpose of the application is in that to provide a kind of plane hydraulic system layout based on power-by-wire energy storage device, and it can reduce aircraft installed power.
One side according to the application, a kind of plane hydraulic system layout based on power-by-wire energy storage device, including:
Spoiler aileron accumulator, is used for driving spoiler steering wheel and aileron steering wheel；
Hatch door accumulator, is used for driving hatch door actuator；
Empennage accumulator, for driving direction rudder steering wheel and elevator steering wheel respectively；
Wherein, described spoiler aileron accumulator, hatch door accumulator and described empennage accumulator are all connected with the fly-by-wire of aircraft, carry out energy storage or start for the output order based on described fly-by-wire.
Adopt the plane hydraulic system layout based on power-by-wire energy storage device of the application, hydraulic system pressure grade is improved by power-by-wire boosting energy storage device, plane hydraulic system is made to realize high-pressure trend, the method realizing high-pressure trend exports the realization of high pressure hydraulic oil not by Engine Driven Pump (EDP), but is being realized by power-by-wire boosting energy storage device near valve control steering wheel end.Further, utilize the input of little continuous power to realize big transient power start by power-by-wire boosting energy storage device, reduce aircraft installed power.
Accompanying drawing explanation
With reference to below in conjunction with the accompanying drawing explanation to the embodiment of the present application, the above and other objects, features and advantages of the application can be more readily understood that.Parts in accompanying drawing are intended merely to the principle illustrating the application.In the accompanying drawings, same or similar technical characteristic or parts will adopt same or similar accompanying drawing labelling to represent.
Fig. 1 is the schematic diagram of a kind of embodiment of the plane hydraulic system layout based on power-by-wire energy storage device of the application；
Fig. 2 is the structure chart of a kind of embodiment of each energy-storage module in Fig. 1.
Detailed description of the invention
Embodiments herein is described with reference to the accompanying drawings.Can combine with the element shown in one or more other accompanying drawing or embodiment and feature at the element described in the accompanying drawing of the application or a kind of embodiment and feature.It should be noted that, for purposes of clarity, accompanying drawing and eliminate expression and the description of unrelated with the application, parts known to persons of ordinary skill in the art and process in illustrating.
Shown in Figure 1, for structure Figure 100 of a kind of embodiment of the plane hydraulic system layout based on power-by-wire energy storage device of the application.
In the present embodiment, the plane hydraulic system layout based on power-by-wire energy storage device includes spoiler aileron accumulator 110, is used for driving spoiler steering wheel and aileron steering wheel；
Hatch door accumulator 120, is used for driving hatch door actuator；
Empennage accumulator 130, for driving direction rudder steering wheel and elevator steering wheel respectively；
Wherein, spoiler aileron accumulator 110, hatch door accumulator 120 and empennage accumulator 130 are all connected with the fly-by-wire of aircraft, carry out energy storage or start for the output order based on fly-by-wire.
In one embodiment, spoiler aileron accumulator 110 can include for driving the left spoiler aileron energy-storage module of left spoiler and port aileron and for driving the right spoiler aileron energy-storage module of right spoiler and starboard aileron.
Hatch door accumulator 120 can include for driving the left hatch door energy-storage module of left hatch door actuator and for driving the right hatch door energy-storage module of right hatch door actuator.
Empennage accumulator 130 can include the rudder energy-storage module for driving direction rudder steering wheel and for driving the elevator energy-storage module of elevator steering wheel.
In one embodiment, as in figure 2 it is shown, each energy-storage module (i.e. 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) all includes motor 1, hydraulic pump 3, accumulator 7 and servo valve 8.
Wherein, motor 1 is connected with the outfan of fly-by-wire, for controlling the rotating speed of motor 1 based on the command signal of its output.Hydraulic pump 3 is connected to the output shaft of motor 1, for rotating under driving at motor 1.
Servo valve 8 includes controlling end, first input end, the second input, the first outfan and the second outfan.Servo valve 8 is for connecting/cut-off based on what be input to that the external control signal controlling end controls the connection/cut-off of first input end and the first outfan and the second input and the second outfan simultaneously.Such as, when external control signal instruction servo valve 8 is connected, first input end and the connection of the first outfan, the second input and the second outfan connect.
Hydraulic pump 3 includes oil-out and oil-in, and oil-out is connected with the first input end of servo valve 8, and oil-in is connected with the second input of servo valve 8.Oil-out and the oil-in 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 version, each energy-storage module can also include the feedback device 5 being connected between oil-out and the outfan of fly-by-wire.
Feedback device is for the command signal of the outfan output of the Flow-rate adjustment fly-by-wire based on oil-out, thus controlling the rotating speed of motor 1.
In one embodiment, feedback device 5 can be such as pressure transducer.
Preferably, each energy-storage module of the application can also include the check valve 6 that is connected between the oil-out of accumulator 7 and hydraulic pump 3.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 the relief valve 4 that is connected between oil-in and the oil-out of hydraulic pump 3.
When the pressure reduction of oil-in and oil-out is more than a predetermined value, relief valve 4 is opened, to avoid the hypertonia of whole each energy-storage module.
Each energy-storage module of present embodiment also includes the hatch door hydraulic motor 9 being connected between the first outfan of servo valve 8 and the second outfan.Hydraulic motor 9 is used for the hydraulic pressure of the first outfan based on servo valve 8 and the output of the second outfan respectively to left spoiler aileron, right spoiler aileron, left hatch door, right hatch door, rudder and elevator execution action.
Additionally, in one embodiment, each energy-storage module can also include actuating device 2, and hydraulic pump 3 is connected to the output shaft of motor 1 through actuating device 3, thus the output kinetic energy of motor 1 is transferred to hydraulic pump 3.
When each energy-storage module of the application works, the outfan output motor rotary speed instruction signal of fly-by-wire, size according to motor speed instruction, motor 1 rotary work, hydraulic pump 4 is driven to rotate by drive mechanism 3, output hydraulic oil, high-voltage oil liquid flows to accumulator 7 and servo valve 8 through check valve 6.Pressure transducer 5 gathers the pressure feedback before check valve 6 in the outfan of fly-by-wire, form closed loop, the outfan of the fly-by-wire size according to the pressure sensor signal collected, adjusts the size of motor command signal, in real time thus controlling motor speed in real time.
Finally, the hydraulic oil liquid provided by airborne tank, by hydraulic pump pressurising to high pressure conditions, storage is in accumulator, and when hatch door start, accumulator provides the big flow of transient state.Wherein, being little continuous power to Energy Accumulator in Plenum Process, start process is then big transient power.
Specifically, in supercharging thermal energy storage process, servo valve 8 cuts out, motor 1 receives the outfan rotary speed instruction signal of fly-by-wire, starts working, and drives hydraulic pump 3 to rotate, hydraulic pump 3 converts the hydraulic oil liquid that airborne tank provides to hydraulic oil, and through check valve 6, storage is in accumulator 7.Before pressure transducer 5 detects high pressure conditions, motor 1 is maintained under little continuous power state and works, and when pressure transducer 5 detects high pressure conditions, motor 1 reduces rotating speed, keeps extremely low idling mode, maintains system high pressure state.Now, supercharging thermal energy storage process terminates.
In hatch door start process, servo valve 8 is opened, and hatch door start needs the big flow of transient state, is stored in the high-voltage oil liquid abrupt release in accumulator 7, ensures the traffic demand of hatch door start.Now, because accumulator 7 earth pressure release, pressure transducer 5 can not detect that high pressure conditions, motor 1 are again maintained under little continuous power state and work, until accumulator 7 is full of, reaches high pressure conditions.
It is as follows that the plane hydraulic system layout based on power-by-wire energy storage device of the application specifically completes form:
Aircraft generator produces electric power, transmits to tail from head through cable, when arriving left and right spoiler, the spoiler aileron energy storage device of left and right spoiler configuration produces high-pressure and hydraulic fluid, convert electrical energy into hydraulic energy, flow to left and right spoiler steering wheel, be delivered simultaneously to left and right aileron steering wheel.
Electric power continues toward tail transmission, and when arriving left and right hatch door, the hatch door energy storage device of left and right hatch door configuration produces high-pressure and hydraulic fluid, converts electrical energy into hydraulic energy, flows to hatch door actuator.
Electric power continues toward tail transmission, and when arriving left and right undercarriage, the undercarriage energy storage device of left and right undercarriage configuration produces high-pressure and hydraulic fluid, converts electrical energy into hydraulic energy, flows to left and right undercarriage actuator.
Electric power continues toward tail transmission, arrives left and right elevator and rudder, and the empennage energy storage device of left and right elevator and rudder configuration produces high-pressure and hydraulic fluid, converts electrical energy into hydraulic energy, flows to left and right elevator and rudder；
So far, complete the plane hydraulic system layout based on power-by-wire boosting energy storage device, plane hydraulic system pressure rating is improved by each pressure energy storage device, plane hydraulic system is made to realize high-pressure trend, the method realizing high-pressure trend exports the realization of high pressure hydraulic oil not by Engine Driven Pump (EDP), but is being realized by power-by-wire boosting energy storage device near valve control steering wheel end.Further, utilize the input of little continuous power to realize big transient power start by power-by-wire boosting energy storage device, reduce aircraft installed power.
The plane hydraulic system layout based on power-by-wire energy storage device of the application, has the advantage that
Improve plane hydraulic system pressure rating by power-by-wire boosting energy storage device, it is not necessary to Engine Driven Pump (EDP), reduce aircraft weight.
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, reduces aircraft weight.
Improve hydraulic system pressure grade by each energy storage device, make plane hydraulic system realize high-pressure trend, improve steering gear power density, reduce steering wheel size and weight, thus reducing aircraft weight.
Power-by-wire boosting energy storage device can utilize the input of little continuous power to realize big transient power start, reduces the peak flow that steering wheel start needs, thus reducing aircraft peak flow and installed power.
Above some embodiments of the application are described in detail.As one of ordinary skill in the art can be understood, whole or any steps of the present processes and device or parts, can in any computing equipment (including processor, storage medium etc.) or the network of computing equipment, realized with hardware, firmware, software or their combination, this is that those of ordinary skill in the art use their basic programming skill can be achieved with when understanding present context, therefore need to not illustrate at this.
It is further clear that, time superincumbent explanation relates to possible peripheral operation, to use any display device and any input equipment, corresponding interface and control program that are connected with any computing equipment undoubtedly.Sum it up, related hardware in computer, computer system or computer network, software and the hardware of various operations in realizing the preceding method of the application, firmware, software or their combination, namely constitute the equipment of the application and each building block thereof.
Therefore, based on above-mentioned understanding, the purpose of the application can also be realized by one program of operation or batch processing on any messaging device.Described messaging device can be known common apparatus.Therefore, the purpose of the application can also only by providing the program product comprising the program code realizing described method or equipment to realize.It is to say, such program product also constitutes the application, and the medium storing or transmitting such program product also constitutes the application.Obviously, described storage or transmission medium can be well known by persons skilled in the art, or any kind of storage developed in the future or transmission medium, various storages or transmission medium enumerated at this so also without necessity.
In the equipment and method of the application, it is clear that each parts or each step reconfigure after can decomposing, combine and/or decomposing.These decompose and/or reconfigure the equivalents that should be regarded as the application.It may also be noted that the step performing above-mentioned series of processes can order naturally following the instructions perform in chronological order, but it is not required to necessarily perform sequentially in time.Some step can perform parallel or independently of one another.Simultaneously, herein above in the description of the application specific embodiment, the feature described for a kind of embodiment and/or illustrate can use in one or more other embodiment in same or similar mode, combined with the feature in other embodiment, or substitute the feature in other embodiment.
It should be emphasized that term " include/comprise " refers to the existence of feature, key element, step or assembly herein when using, but it is not precluded from the existence of one or more further feature, key element, step or assembly or additional.
Although having described the application and advantage thereof in detail it should be appreciated that various change, replacement and conversion can be carried out when without departing from the spirit and scope being defined by the claims appended hereto.And, scope of the present application is not limited only to the specific embodiment of the process described by description, equipment, means, method and steps.One of ordinary skilled in the art will readily appreciate that from present disclosure, can use process, equipment, means, method or step that perform the function essentially identical to corresponding embodiment described herein or obtain the result essentially identical with it, that existing and future is to be developed according to the application.Therefore, appended claim is directed in their scope to include such process, equipment, means, method or step.
Claims (9)
1. the plane hydraulic system layout based on power-by-wire energy storage device, it is characterised in that including:
Spoiler aileron accumulator, is used for driving spoiler steering wheel and aileron steering wheel；
Hatch door accumulator, is used for driving hatch door actuator；
Empennage accumulator, for driving direction rudder steering wheel and elevator steering wheel respectively；
Wherein, described spoiler aileron accumulator, hatch door accumulator and described empennage accumulator are all connected with the fly-by-wire of aircraft, carry out energy storage or start for the output order based on described fly-by-wire.
2. the plane hydraulic system layout based on power-by-wire energy storage device according to claim 1, it is characterised in that:
Described spoiler aileron accumulator includes for driving the left spoiler aileron energy-storage module of left spoiler and port aileron and for driving the right spoiler aileron energy-storage module of right spoiler and starboard aileron；
Described hatch door accumulator includes for driving the left hatch door energy-storage module of left hatch door actuator and for driving the right hatch door energy-storage module of right hatch door actuator；
Described empennage accumulator includes the rudder energy-storage module for driving direction rudder steering wheel and for driving the elevator energy-storage module of elevator steering wheel.
3. the plane hydraulic system layout based on power-by-wire energy storage device according to claim 2, it is characterized in that, described 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 include respectively:
Motor, hydraulic pump, accumulator and servo valve；
Wherein,
Described motor is connected with the outfan of described fly-by-wire, for the rotating speed of the command signal described motor of control of the output based on described fly-by-wire；
Described hydraulic pump is connected to the output shaft of described motor, for rotating under driving at described motor；
Described servo valve includes controlling end, first input end, the second input, the first outfan and the second outfan, described servo valve for based on the external control signal of input to described control end control simultaneously described first input end and described first outfan connect/end with described second input and described second outfan connect/cut-off；
Described hydraulic pump includes oil-out and oil-in, and described oil-out is connected with the first input end of described servo valve, and described oil-in is connected with the second input of described servo valve；
Described accumulator is connected on the oil circuit between described oil-out and described first input end.
4. the plane hydraulic system layout based on power-by-wire energy storage device according to claim 3, it is characterized in that, described 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 feedback device between described oil-out and described fly-by-wire；
Described feedback device is for based on the command signal of fly-by-wire output described in the Flow-rate adjustment of described oil-out.
5. the plane hydraulic system layout based on power-by-wire energy storage device according to claim 4, it is characterised in that:
Described feedback device is pressure transducer.
6. the plane hydraulic system layout based on power-by-wire energy storage device according to claim 3-5 any one, it is characterized in that, described 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 check valve between the oil-out of described accumulator and described hydraulic pump；
Described check valve enters in described hydraulic pump for preventing the fluid in described accumulator.
7. the plane hydraulic system layout based on power-by-wire energy storage device according to claim 6, it is characterized in that, described 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 hydraulic motor between the first outfan of described servo valve and the second outfan；
Described hatch door hydraulic motor is used for the hydraulic pressure of the first outfan based on described servo valve and the output of the second outfan respectively to left spoiler aileron, right spoiler aileron, left hatch door, right hatch door, rudder and elevator execution action.
8. the plane hydraulic system layout based on power-by-wire energy storage device according to claim 7, described 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 relief valve between oil-in and the oil-out of described hydraulic pump；
Described relief valve is for opening when the pressure reduction of described oil-in and described oil-out is more than a predetermined value.
9. the plane hydraulic system layout based on power-by-wire energy storage device according to claim 8, it is characterized in that, described 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 actuating device；
Described hydraulic pump is connected to the output shaft of described motor through described actuating device.
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| 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 |
| 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 |
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