CN109050878A - A kind of continuous variable camber structure of aircraft and its distributing drive control method - Google Patents
A kind of continuous variable camber structure of aircraft and its distributing drive control method Download PDFInfo
- Publication number
- CN109050878A CN109050878A CN201810863361.7A CN201810863361A CN109050878A CN 109050878 A CN109050878 A CN 109050878A CN 201810863361 A CN201810863361 A CN 201810863361A CN 109050878 A CN109050878 A CN 109050878A
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- China
- Prior art keywords
- sma
- aircraft
- continuous variable
- hinge
- rib joint
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- 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.)
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/44—Varying camber
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/36—Structures adapted to reduce effects of aerodynamic or other external heating
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/44—Varying camber
- B64C3/50—Varying camber by leading or trailing edge flaps
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C2009/005—Ailerons
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention belongs to technical field of aerospace, specifically related to a kind of aircraft wing leading edge, the structure and its distributing drive control method of rear and the continuous variable camber of wing tip, the continuous variable camber structure of aircraft of the invention includes SMA, it is respectively used to for being attached at the edge for being located at the adjacent two rib joint of hinge the same side, and SMA connection heating power supplies and with the plastic cement seal of tube, plastic pipe connects cooling compressor, one angular transducer is installed on each hinge, SMA have shape memory function, heating meeting refresh memory state is carried out to it, contraction distortion is presented, in low temperature, lengthening deformation and length shapes can be kept fixed under external force, it is heated by the SMA silk to side, the SMA silk of the other side lives cooling gas cooling by plastic pipe, realize whole rib joint to the inclined of side Turn.
Description
Technical field
The invention belongs to technical field of aerospace, and in particular to continuously bent to a kind of aircraft wing leading edge, rear and wing tip
The structure and its distributing drive control method of degree.
Background technique
These control surfaces such as droope snoot, trailing edge flap, aileron and the winglet of application aboard at present, pass through it
Yaw motion increases maximum lift coefficient, improves the aeroperformance of aircraft, manipulates airplane motion posture.
The control surface of existing aircraft is connected on wing by hinge or sliding rail, is existed obviously not between control surface and wing
Continuous break and scale gap, easily separate when air-flow passes through, and largely influence the pneumatic efficiency of aircraft, and cause
Wing is buffeted, and the flight manipulation quality of aircraft is reduced.
Summary of the invention
The continuous variable camber structure of aircraft of the invention and its distributing drive control method, are able to solve existing aircraft handling
Face pneumatic efficiency decline, the discontinuous problem of shape in deflection.
A kind of continuous variable camber structure of aircraft, including wing leading edge flaps, trailing edge flap, aileron and winglet, it is special
Sign is, the continuous variable camber structure of aircraft further include:
At least two are located in the same horizontal plane the rib joint of setting, between two adjacent rib joints
Two rib joints are attached by medium position by hinge, can be around between the rib joint of adjacent two
The hinge planar rotates predetermined angular；
SMA, the edge for being respectively used to be located at the adjacent two rib joint of described hinge the same side carries out
Connection, and the SMA connection heating power supply and with the plastic cement seal of tube, the plastic pipe connection cools down compressor；
Angular transducer is mounted on the hinge.
Preferably, the rib joint is 3~5.
Preferably, the SMA silk braid is in the plastic pipe.
A kind of distributing drive control method of the continuous side camber structure of aircraft, comprising:
The rib joint instruction that side deflects thereto described in data acquisition TT&C system input control at least two, is surveyed
Cooling compressor described in control system drive imports cooling gas into the plastic tube of the other side, is powered to the SMA silk of pre-deflection side
Heating, the angular transducer acquires the drift angle between the two neighboring rib joint, while acquiring observing and controlling to the data
System feedback deflection angle realizes deflection.
The utility model has the advantages that
The continuous variable camber structure of aircraft of the invention and its distributing drive control method are more by the driving of wing alloy
The servo-actuated rib of grade, implements fairing continuous deflection, and by temperature, displacement and angular transducer, constantly signal is fed back, and realizes and closes to morely
The accurate control of control surface deflection mechanism is saved, there is the features such as effect is directly efficient, and control response is rapid, rudder face structure and main wing box
Covering is connected, and shape fairing is continuous, does not have opposite joint scale, and drag reduction lift-rising income is obvious, reduction aircraft aerodynamic drag 20%,
Improve 50% or more Stealth Fighter.
Detailed description of the invention
Fig. 1 is the control surface schematic diagram of the continuous variable camber structure of aircraft of the invention；
Fig. 2 is the scheme of installation of angular transducer of the invention on the hinge of rib joint；
Fig. 3 is the flow chart for driving the continuous variable camber structure of aircraft to turn to B lateral deviation in the embodiment of the present invention；
Fig. 4 is the flow chart for driving the continuous variable camber structure of aircraft to turn to A lateral deviation in the embodiment of the present invention；
Wherein, 1- rib joint, 2- hinge, 3- angular transducer, 4-SMA, 5- plastic tube.
Specific embodiment
In order to enable structure and its method of the invention is more easily understood, below with reference to attached drawing and specific embodiment
Further detailed description.
In the description of the present invention, it is to be understood that, term " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom" "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown, is merely for convenience of description of the present invention and simplification of the description, rather than the dress of indication or suggestion meaning
It sets or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as protecting the present invention
The limitation of range.
It is the continuous variable camber structure of aircraft of the invention, including wing leading edge flaps, trailing edge flap, pair such as Fig. 1 and Fig. 2
The wing and winglet, which is characterized in that the continuous variable camber structure of aircraft further include:
At least two are located in the same horizontal plane the rib joint 1 of setting, between two adjacent rib joints 1 in
Two rib joints are attached by portion position by hinge 2, between two adjacent rib joints 1 can around hinge 2 flat
Predetermined angular is rotated in face；
SMA silk 4 is respectively used to for being attached at the edge for being located at the adjacent two rib joint 1 of 2 the same side of hinge,
And SMA silk 4 connects heating power supply and is sealed with plastic pipe 5, plastic pipe 5 connects cooling compressor, and SMA have shape memory function
Can, it is restored to memory state when heated, presentation contraction distortion contraction distortion and can be protected under the effect of external force in low temperature
Hold regular length shape.
Angular transducer 3 is mounted on hinge 2, can acquire the deflection angle of every level-one rib joint.
It is preferably in the present invention, rib joint 1 is 3~5；SMA silk 4 is embedded in plastic pipe 5.
A kind of distributing drive control method of the continuous side camber structure of aircraft, comprising:
In data acquisition at least two rib joint 1 of the TT&C system input control instruction that side deflects thereto, observing and controlling
The cooling compressor of system drive imports cooling gas into the plastic tube 5 of the other side, to 4 electrified regulation of SMA silk of pre-deflection side,
Angular transducer 3 acquires the drift angle between two neighboring rib joint 1, while feeding back deflection angle to data acquisition TT&C system
Degree realizes deflection.
Embodiment one
Such as Fig. 3, the instruction turned to B lateral deviation, the cooling compression of TT&C system driving are inputted in data acquisition TT&C system (PXI)
Machine imports cooling gas, the temperature conditions of temperature acquisition card real-time monitoring A side SMA thread, when temperature reaches into the plastic tube of the side A
When sufficiently low, triggering solenoid valve opens heating power supply, and to the SMA silk electrified regulation of the side B, the SMA silk temperature of the side B is increased, and leads
The SMA silk contraction distortion of the side B is caused, 1 around hinge 2 of rib joint of every level-one is rotated to the side B, and the side A SMA is forced to elongate, angle
Sensor 3 acquires the drift angle between every level-one rib joint 1, while feeding back deflection angle to data acquisition TT&C system (PXI),
Realize that structure is deflected to the fairing of the side B.
Embodiment two
Such as Fig. 4, the instruction turned to A lateral deviation, the cooling compression of TT&C system driving are inputted in data acquisition TT&C system (PXI)
Machine imports cooling gas, the temperature conditions of temperature acquisition card real-time monitoring B side SMA thread, when temperature reaches into the plastic tube of the side B
When sufficiently low, triggering solenoid valve opens heating power supply, and to the SMA silk electrified regulation of the side A, the SMA silk temperature of the side A is increased, and leads
The SMA silk contraction distortion of the side A is caused, 1 around hinge 2 of rib joint of every level-one is rotated to the side A, and the side B SMA is forced to elongate, angle
Sensor 3 acquires the drift angle between every level-one rib joint 1, while feeding back deflection angle to data acquisition TT&C system (PXI),
Realize that structure is deflected to the fairing of the side A.
Finally it is noted that the above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations.To the greatest extent
Present invention has been described in detail with reference to the aforementioned embodiments for pipe, those skilled in the art should understand that: it is still
It is possible to modify the technical solutions described in the foregoing embodiments, or part of technical characteristic is equally replaced
It changes；And these are modified or replaceed, the essence for technical solution of various embodiments of the present invention that it does not separate the essence of the corresponding technical solution
Mind and range.
Claims (4)
1. a kind of continuous variable camber structure of aircraft, including wing leading edge flaps, trailing edge flap, aileron and winglet, feature
It is, the continuous variable camber structure of aircraft further include:
At least two are located in the same horizontal plane the rib joint (1) of setting, between two adjacent rib joints (1)
Medium position, two rib joints are attached by hinge (2), the rib joint (1) of adjacent two it
Between can planar rotate predetermined angular around the hinge (2)；
It SMA (4), is respectively used to that the edge of the adjacent two rib joint (1) of the hinge (2) the same side will be located at
It is attached, and SMA described (4) connect heating power supply and sealed with plastic pipe (5), the cooling pressure of plastic pipe (5) connection
Contracting machine；
Angular transducer (3) is mounted on the hinge (2).
2. the continuous variable camber structure of aircraft according to claim 1, which is characterized in that the rib joint (1) is 3~5
It is a.
3. the continuous variable camber structure of aircraft according to claim 1, which is characterized in that SMA described (4) are embedded in described
In plastic pipe (5).
4. a kind of distributing drive control method of the continuous side camber structure of aircraft characterized by comprising
Rib joint (1) instruction that side deflects thereto described in data acquisition TT&C system input control at least two, is surveyed
It controls cooling compressor described in system drive and imports cooling gas into the plastic tube (5) of the other side, to the SMA silk of pre-deflection side
(4) electrified regulation, the angular transducer (3) acquire the drift angle between the two neighboring rib joint (1), while to described
Data acquire TT&C system and feed back deflection angle, realize deflection.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810863361.7A CN109050878A (en) | 2018-08-01 | 2018-08-01 | A kind of continuous variable camber structure of aircraft and its distributing drive control method |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201810863361.7A CN109050878A (en) | 2018-08-01 | 2018-08-01 | A kind of continuous variable camber structure of aircraft and its distributing drive control method |
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| CN109050878A true CN109050878A (en) | 2018-12-21 |
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| CN201810863361.7A Pending CN109050878A (en) | 2018-08-01 | 2018-08-01 | A kind of continuous variable camber structure of aircraft and its distributing drive control method |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110143272A (en) * | 2019-05-30 | 2019-08-20 | 中国人民解放军海军工程大学 | A kind of device of control aircraft combined operation face gap flowing |
| CN110304269A (en) * | 2019-07-17 | 2019-10-08 | 北京航空航天大学 | A kind of controllable clamp structure of intellectual material driving control surface deflection |
| CN110329491A (en) * | 2019-07-29 | 2019-10-15 | 吉林大学 | Deformable wing and its deformation control method based on marmem driving |
| CN110654530A (en) * | 2019-11-01 | 2020-01-07 | 北京航空航天大学 | Variable camber wing structure with deformation feedback |
| CN111717368A (en) * | 2020-07-01 | 2020-09-29 | 电子科技大学 | Flexible wing structure based on shape memory alloy and manufacturing method thereof |
| CN111874265A (en) * | 2020-08-25 | 2020-11-03 | 中国科学院微小卫星创新研究院 | Satellite-borne running mechanism driving device and control method thereof |
| CN111907694A (en) * | 2020-06-22 | 2020-11-10 | 哈尔滨工业大学(深圳)(哈尔滨工业大学深圳科技创新研究院) | Wing trailing edge and wing with variable camber |
| CN114275142A (en) * | 2022-01-13 | 2022-04-05 | 北京机电工程研究所 | Wing surface with continuously variable trailing edge camber |
| CN114291287A (en) * | 2022-01-13 | 2022-04-08 | 北京机电工程研究所 | Design method of wing surface with continuously variable trailing edge |
| CN114348239A (en) * | 2022-01-24 | 2022-04-15 | 北京航空航天大学 | Control surface rib frame structure driven by shape memory alloy and capable of continuously and automatically deflecting |
| EP4119440A1 (en) * | 2021-07-16 | 2023-01-18 | BAE SYSTEMS plc | Control surface actuation |
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| CN101693467A (en) * | 2009-10-13 | 2010-04-14 | 南京航空航天大学 | Self-adapting morphing trailing edge based on SMA |
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| CN107444617A (en) * | 2017-07-13 | 2017-12-08 | 北京航空航天大学 | A kind of variable adaptive wing structure of camber |
| CN107628228A (en) * | 2017-08-28 | 2018-01-26 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of leading edge of a wing continuously bent structure |
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| CN101693467A (en) * | 2009-10-13 | 2010-04-14 | 南京航空航天大学 | Self-adapting morphing trailing edge based on SMA |
| CN102951286A (en) * | 2011-08-16 | 2013-03-06 | 波音公司 | Variable camber fluid-dynamic body utilizing optimized smart materials |
| CN104121745A (en) * | 2014-07-04 | 2014-10-29 | 南京航空航天大学 | Tube-in-tube type cooling system and experimental method for SMA driver |
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Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110143272A (en) * | 2019-05-30 | 2019-08-20 | 中国人民解放军海军工程大学 | A kind of device of control aircraft combined operation face gap flowing |
| CN110304269A (en) * | 2019-07-17 | 2019-10-08 | 北京航空航天大学 | A kind of controllable clamp structure of intellectual material driving control surface deflection |
| CN110304269B (en) * | 2019-07-17 | 2021-09-14 | 北京航空航天大学 | Controllable clamp structure for intelligent material driving control surface to deflect |
| CN110329491A (en) * | 2019-07-29 | 2019-10-15 | 吉林大学 | Deformable wing and its deformation control method based on marmem driving |
| CN110654530A (en) * | 2019-11-01 | 2020-01-07 | 北京航空航天大学 | Variable camber wing structure with deformation feedback |
| CN111907694A (en) * | 2020-06-22 | 2020-11-10 | 哈尔滨工业大学(深圳)(哈尔滨工业大学深圳科技创新研究院) | Wing trailing edge and wing with variable camber |
| CN111907694B (en) * | 2020-06-22 | 2022-02-22 | 哈尔滨工业大学(深圳)(哈尔滨工业大学深圳科技创新研究院) | Wing trailing edge and wing with variable camber |
| CN111717368A (en) * | 2020-07-01 | 2020-09-29 | 电子科技大学 | Flexible wing structure based on shape memory alloy and manufacturing method thereof |
| CN111717368B (en) * | 2020-07-01 | 2024-04-02 | 电子科技大学 | Flexible wing structure based on shape memory alloy and manufacturing method thereof |
| CN111874265A (en) * | 2020-08-25 | 2020-11-03 | 中国科学院微小卫星创新研究院 | Satellite-borne running mechanism driving device and control method thereof |
| EP4119440A1 (en) * | 2021-07-16 | 2023-01-18 | BAE SYSTEMS plc | Control surface actuation |
| CN114275142A (en) * | 2022-01-13 | 2022-04-05 | 北京机电工程研究所 | Wing surface with continuously variable trailing edge camber |
| CN114291287A (en) * | 2022-01-13 | 2022-04-08 | 北京机电工程研究所 | Design method of wing surface with continuously variable trailing edge |
| CN114275142B (en) * | 2022-01-13 | 2023-08-25 | 北京机电工程研究所 | Continuous variable trailing edge camber airfoil |
| CN114348239A (en) * | 2022-01-24 | 2022-04-15 | 北京航空航天大学 | Control surface rib frame structure driven by shape memory alloy and capable of continuously and automatically deflecting |
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Application publication date: 20181221 |
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