CN109334949A - A kind of morphing can be changed the shape control system and method for camber trailing edge formations - Google Patents
A kind of morphing can be changed the shape control system and method for camber trailing edge formations Download PDFInfo
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- CN109334949A CN109334949A CN201810989388.0A CN201810989388A CN109334949A CN 109334949 A CN109334949 A CN 109334949A CN 201810989388 A CN201810989388 A CN 201810989388A CN 109334949 A CN109334949 A CN 109334949A
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- axle sleeve
- master control
- cable wire
- stake
- support shaft
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- 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
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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
- B64C13/26—Transmitting means without power amplification or where power amplification is irrelevant
- B64C13/28—Transmitting means without power amplification or where power amplification is irrelevant mechanical
- B64C13/30—Transmitting means without power amplification or where power amplification is irrelevant mechanical using cable, chain, or rod mechanisms
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/28—Leading or trailing edges attached to primary structures, e.g. forming fixed slots
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Automation & Control Theory (AREA)
- Flexible Shafts (AREA)
- Piles And Underground Anchors (AREA)
Abstract
The invention discloses shape control systems and method that a kind of morphing can be changed camber trailing edge formations, and wherein design method is easy to operate by driving cable wire directly to carry out deformation driving to variable camber trailing edge formations, are easy to implement.Using distributed driving method in method of the invention, is driven using bracing cable from rear edge surface distribution, the complex deformation of rear may be implemented.Have in the deformation, carrying of structure type and have great advantage, and force-transfer characteristic is good.
Description
Technical field:
The invention belongs to field of airplane structure, and in particular to a kind of morphing can be changed the shape of camber trailing edge formations
Control system and method.
Background technique:
The driving of deformable structure is one of the research hotspot of variant technology, driving device target to have it is light-weight, point
The features such as cloth is high-effect, be easy to control, response quickly.
The driving element to efficient and light weight energy and distributed driving design method have conducted extensive research both at home and abroad.Distribution
Formula driving structure shares the mode of load by using multiple drivers, effectively alleviates construction weight, can really realize
The deformation of continuous and derivable.
By the design requirement of analysis-driven device, the invention proposes a kind of morphings can be changed camber trailing edge formations
Shape control method.Since to can be changed the deformation of camber trailing edge formations complex for variant aircraft, using bracing cable from edge airfoil surface
Distribution driving, makes rear that can continuously change shape with fairing.The shape control method is easy to implement, and is had good
Force-transfer characteristic.
Summary of the invention:
The present invention can be changed the shape control problem of camber trailing edge formations for variant aircraft, and proposing a kind of morphing can
The shape control system and method for variable camber trailing edge formations, using master control cable wire and close to edge airfoil surface bracing cable to rear
Distributed driving is carried out, the drive scheme of variable camber trailing edge formations is optimized, it is intended to it is simpler with operating, it is more convenient for
The method of realization makes rear fairing continuously change shape.
The present invention adopts the following technical scheme: a kind of morphing can be changed the shape control system of camber trailing edge formations, it will
Shape control system is extended to m subregion is divided into, and is provided with master control cable wire on every segment boundary of m subregion, close to upper following table
Face master control cable wire quantity is respectively m+1, has n segment in each subregion, is disposed with bracing cable on each segment, close to upper following table
N bracing cable is respectively arranged in face, is disposed with support shaft in rear starting point, and m+1 connection master control steel is evenly arranged in the support shaft
First axle sleeve of rope is evenly arranged the second axle sleeve of n connection bracing cable, connection according to the position of bracing cable in each subregion
The highs and lows of the first axle set anchor ring of master control cable wire process a raised cylindrical stake, cylindrical stake side respectively
Hole is got through, for across master control cable wire and bracing cable, production to have sliding nest in support shaft, along diameter on the first axle sleeve, the second axle sleeve
To the pin for being longer than half bush wall thickness is put into, slide pin in sliding nest.
It further, further include displacement coordination system, displacement coordination system is made of m short beam, each subregion is corresponding
One short beam.
Further, it is respectively placed with a pin at the left and right sides a quarter circumference of cylindrical stake, supported
The position that each pin is corresponded on axis outer surface circumferentially makes sliding nest, the cross sectional shape of the sliding nest and the section shape of pin
Shape is identical.
The present invention also adopts the following technical scheme that a kind of morphing can be changed the shape control method of camber trailing edge formations,
Steps are as follows:
(1) support shaft chooses aluminium alloy extrusions, is thick-walled tube, and length is equal to rear and extends the length to deformable region
The outer surface processing of degree, support shaft is smooth, to cooperate with the first axle sleeve, the second axle sleeve；
(2) first axle sleeves, the second axle sleeve are thick-walled tube, choose aluminium alloy extrusions, connect the first axle sleeve of master control cable wire
It is equally spaced and is evenly arranged in the first shaft room of every two in the second axle sleeve in support shaft, connecting bracing cable, two neighboring
There are identical gap, the first axle sleeve, the inner surface processing of the second axle sleeve are smooth for one axle sleeve, the second shaft room, the first axle sleeve,
The highs and lows of second axle sleeve anchor ring are each to make a call to a diameter less than the first axle sleeve, the counterbore of the second sleeve width, passes through
Cylindrical stake is fixed on the first axle sleeve, on the second axle sleeve by screw, close to the position root of upper surface on the side of cylindrical stake
A through-hole is made a call to according to the size of master control cable wire or bracing cable, is used to across master control cable wire or bracing cable；
(3) using cylindrical stake as symmetry axis on the first axle sleeve, the second axle sleeve, the left and right sides of cylindrical stake four/
The pin for being longer than half bush wall thickness is radially respectively placed at one circumference, corresponds to each pin on support shaft outer surface
Position circumferentially makes sliding nest, and the cross sectional shape of sliding nest is identical as the cross sectional shape of pin；
(4) displacement coordination system is a flute profile short beam, and the top surface of short beam is beaten elliptical aperture according to the position of cylindrical stake, made
Each cylindrical stake can extend there through, the axial direction of elliptical long edge first axle set, the second axle sleeve, elliptical long side length
It is determined by rear deformation extent, bond length is equal to cylindrical stake diameter, and apical side height is no more than in cylindrical stake for wearing master
The hole of control cable wire and bracing cable is correspondingly connected at the cylindrical stake of master control cable wire at the both ends of short beam, highly should be intermediate altitude
Half, and the short beam of two neighboring by stages cooperates here, retains top half on one side, retains lower half portion on one side；
(5) master control cable wire and bracing cable are fixed in rear core plate end, and core plate is fixed in the bracing cable close to upper surface of the airfoil
Lower surface is fixed on the upper surface of core plate close to the bracing cable of wing lower surface.
The invention has the following beneficial effects:
(1) design method of the invention is grasped by driving cable wire directly to carry out deformation driving to variable camber trailing edge formations
Make simply, to be easy to implement.
(2) it using distributed driving method in method of the invention, is driven using bracing cable from rear edge surface distribution, it can be with
Realize the complex deformation of rear.Have in the deformation, carrying of structure type and have great advantage, and force-transfer characteristic is good.
Detailed description of the invention:
Fig. 1 is the main view for the shape control system that morphing of the present invention can be changed camber trailing edge formations.
Fig. 2 is the top view for the shape control system that morphing of the present invention can be changed camber trailing edge formations.
Fig. 3 is the side view for the shape control system that morphing of the present invention can be changed camber trailing edge formations.
Fig. 4 is axle sleeve schematic diagram.
Fig. 5 is the sliding nest schematic diagram of axis.
Fig. 6 is displacement coordination system short beam schematic diagram.
Specific embodiment:
The present invention will be further described below with reference to the drawings.
Morphing of the present invention can be changed the shape control system of camber trailing edge formations using master control cable wire and close to the rear wing
The bracing cable distribution on type surface drives variable camber trailing edge formations.For the complex deformation for meeting rear, by rear deformable region
It extends to m subregion is divided into, in the same direction, reversed or differential deflection may be implemented in m by stages.To meet to rear complex deformation
Control also extends shape control system to m subregion is divided into, and master control cable wire 1, patch are arranged on every segment boundary of m subregion
Nearly upper and lower surface master control cable wire quantity is respectively m+1.There is n segment in each subregion, bracing cable 2, patch are arranged on each segment
Nearly upper and lower surface respectively arranges n bracing cable.Shape control system schematic diagram is as shown in Figure 1.
Arrange that a support shaft 3 is evenly arranged m+1 in support shaft 3 according to the position of master control cable wire 1 in rear starting point
First axle sleeve 4 of a connection master control cable wire 1.According to the position of bracing cable 2, n connection bracing cable 2 is evenly arranged in each subregion
The second axle sleeve 5.The highs and lows for connecting 4 anchor ring of the first axle sleeve of master control cable wire 1 process a raised circle respectively
Hole is got through in cylindricality stake, cylindrical stake side, for across master control cable wire 1.Hole is got through in cylindrical stake side, for across bracing cable 2.
First axle sleeve 4, the schematic diagram of the second axle sleeve 5 are as shown in Figure 2.
To complete the positioning in support shaft 3 of the first axle sleeve 4, the second axle sleeve 5, sliding nest 6 is made in support shaft 3, the
It is radially put into the pin 7 for being longer than half bush wall thickness on one axle sleeve 4, the second axle sleeve 5, slides pin 7 in sliding nest 6, to protect
Circumferential deflection can be generated without axial displacement relative to support shaft 3 by demonstrate,proving the first axle sleeve 4, the second axle sleeve 5.In view of symmetrical
Property, using cylindrical stake as symmetry axis, a pin 7 is respectively placed at the left and right sides a quarter circumference of cylindrical stake.?
The position that each pin is corresponded on 3 outer surface of support shaft circumferentially makes sliding nest 6, as shown in Figure 3.The length of sliding nest 6 is by rear
Edge deformation angle determines that the cross sectional shape of sliding nest 6 is identical as the cross sectional shape of pin 7.
Utilize deformable transition between 2 displacement coordination of bracing cable and adjacent sectors of each subregion of the guarantee of displacement coordination system 8
Naturally, to allow, rear is in the same direction, reversed or differential deflection.Displacement coordination system is made of m short beam (as shown in Figure 4),
Each subregion corresponds to a short beam.With the two legs of a flute profile short beam by the cylindrical stake of the axle sleeve of a subregion from two sides
It fixes, elliptical aperture is beaten at the position of each Correspondent cy linder shape stake in the top surface of short beam, passes through cylindrical stake corresponding ellipse
Circular hole, in each subregion, when the first axle sleeve 4 deflection of both ends connection master control cable wire, it is ensured that the bracing cable 2 in subregion
Compatibility of deformation.Short beam apical side height is no more than in cylindrical stake for wearing the hole of master control cable wire 1 and bracing cable 2.In connection master control steel
At the cylindrical stake of rope 1, i.e. the both ends height of short beam should be the half of intermediate altitude, and the short beam of two neighboring by stages is herein
Place's cooperation, retains top half on one side, retains lower half portion on one side, to realize that two neighboring by stages transition is natural.
Master control cable wire 1 and bracing cable 2 are fixed on rear.By manipulating master control cable wire 1, control rear deformation.Manipulate master control
Cable wire 1 makes the first axle sleeve 4 for connecting master control cable wire deflect, and the second axle sleeve of connection bracing cable is driven by displacement coordination system
5 deflections, then bracing cable 2 generates displacement, and generates the contrary of displacement close to the bracing cable of upper and lower surface 2, to make rear
Deflection.It is required according to rear deformed shape, distributes the deflection angle of each master control cable wire 1, reach the various modifications requirement of rear.
Morphing of the present invention can be changed the shape control method of camber trailing edge formations, and steps are as follows:
One section of wing is selected, aerofoil profile is NACA0012 aerofoil profile.The variable tangential overall length 400mm of camber rear.It extends to centre
600mm sections of cambers are variable.The shape control system of variable camber rear is arranged in inside the wing structure before the back rest.
(1) support shaft 3 chooses aluminium alloy extrusions, is thick-walled tube, and length is equal to rear and extends the length to deformable region
Degree.Diameter is determined by local aerofoil profile height and the first axle sleeve 4,5 size of the second axle sleeve.Diameter should be as far as possible under enabled condition
Greatly.The outer surface of support shaft 3 need to process it is smooth, so as to the first axle sleeve 4, the second axle sleeve 5 cooperation.
(2) first axle sleeves 4, the second axle sleeve 5 are also thick-walled tube, choose aluminium alloy extrusions.Connect the first of master control cable wire
Axle sleeve 4 is equally spaced between the second axle sleeve 5 in support shaft 3, connecting bracing cable is evenly arranged in the first axle sleeve of every two 4.Phase
There are identical minim gaps between adjacent two the first axle sleeves 4, the second axle sleeve 5.First axle sleeve 4, the second axle sleeve 5 inner surface need to add
Work is smooth.A diameter is made a call to much smaller than sleeve width the highs and lows of the first axle sleeve 4,5 anchor ring of the second axle sleeve are each
Counterbore is fixed on cylindrical stake on axle sleeve by screw.Position on the side of cylindrical stake close to upper surface is according to master
Control cable wire 1 or the size of bracing cable 2 make a call to a through-hole, are used to across master control cable wire 1 or bracing cable 2.
(3) divide using cylindrical stake as symmetry axis in the left and right sides of cylindrical stake four on the first axle sleeve 4, the second axle sleeve 5
One of radially respectively place the pin 7 for being longer than half bush wall thickness at circumference.Each pin is corresponded on 3 outer surface of support shaft
The position of nail circumferentially makes sliding nest 6, and the length of sliding nest 6 is determined by rear deformation angle, the cross sectional shape and pin 7 of sliding nest 6
Cross sectional shape it is identical.
(4) displacement coordination system 8 is a flute profile short beam, and elliptical aperture is beaten according to the position of cylindrical stake in the top surface of short beam,
Extend there through each cylindrical stake.Elliptical long edge first axle covers the axial direction of the 4, second axle sleeve 5, elliptical long side
Length is determined that bond length is equal to cylindrical stake diameter by rear deformation extent, and apical side height, which is no more than in cylindrical stake, to be used for
Wear the hole of master control cable wire 1 and bracing cable 2.It at the both ends of short beam, is correspondingly connected at the cylindrical stake of master control cable wire, highly should be intermediate
The half of height, and the short beam of two neighboring by stages cooperates here, retains top half on one side, retains lower half on one side
Point.
(5) master control cable wire 1 and bracing cable 2 are fixed in rear core plate end.Core plate is fixed in bracing cable 2 close to upper surface of the airfoil
Lower surface, the upper surface of core plate is fixed on close to the bracing cable 2 of wing lower surface.
Since trailing edge is extended to intermediate 600mm sections of variable camber, so taking shaft length is 600mm.To drive system
It is grouped, along axial 600mm, every 150mm arranges a driving cable wire, uniformly distributed 9 bracing cables between every two drivings cable wire.Driving
Cable wire and bracing cable are arranged on same axis, and axis is thick-walled tube, internal diameter 48mm, outer diameter 64mm.
In order to enable to drive cable wire and bracing cable array arrangement, and by cable wire and opened on upper lower aerofoil, axis
Line position is evenly distributed with axle sleeve, and every 15mm arranges one, sleeve width 14mm, internal diameter 64mm, and outer diameter 80mm refers both to diameter herein,
There is the gap 1mm per adjacent two shaft room.Two raised cylindrical stakes are processed in each axle sleeve anchor ring the highest point and the lowest point, directly
Diameter 6mm, high 10mm, stake is interior to perforate, and wears the hole bore dia 2mm of cable wire, wears the bore dia 0.5mm of bracing cable, the hole heart is located at cylinder pile
At the downward 2mm in upper surface.Cable wire and bracing cable are each passed through the aperture of cylinder pile, and cable wire one end knots in rear core plate end, separately
One end is pierced by from cylinder stake holes for manipulating, and bracing cable one end knots in rear core plate end, and the hole of cylindrical stake is fixed in one end.
Short beam the overall length 162mm, thick 1mm, wide 10mm of displacement coordination system.According to the height of cylindrical stake, among short beam
The high 6mm in part, high 3mm, both ends director 7.5mm at the cylinder pile of both ends connection cable wire, and one end retains top half, one end
Retain lower half portion.15 ° are integrally deflected down by rear in this present embodiment, cylindrical stake does not generate axial direction relative to elliptical aperture
Displacement, therefore elliptical aperture need to only be longer than the diameter of cylindrical stake along the axial length.Enabling elliptical aperture long axis length is 10mm, and short axle is long
Degree is 6mm.
It is l that airfoil trailing edge, which is bent the tangential length of neutral surface, and upper and lower surface length is l0, can be changed the tangential beginning of camber rear
Place's aerofoil profile height is h0.If it is α that rear rudder face, which deflects down angle, then can be calculated by the cosine law, after deflection on rear
Length surface is
If rear deflects down angle when being α, the drive shaft turns angle in shape control system is β, is positive clockwise.
The distance in the axle center Kong Xinyu is R at perforation in cylindrical stake0.Then
By taking NACA0012 aerofoil profile as an example, rudder face small angle deflection simplifies NACA0012 aerofoil profile, replaces song with straight line
Line, rear chord length c=400mm, aerofoil profile upper and lower surface length is l0=402mm can be changed the tangential beginning aerofoil profile of camber rear
Height is h0=46mm.Since NACA0012 aerofoil profile is symmetrical airfoil, rear chord length is to be bent the tangential length of neutral surface.Rear
Deflect down 15 °.L' then can be calculated by formula 10=414mm.
The distance R in the axle center Kong Xinyu at the cylindrical stake perforation of shape control system0=48mm, calculates, β=14.3 °.
I.e. when drive shaft rotates clockwise 14.3 °, corresponding rear deflects down 15 °.
In this way, the shape control system of design drives displacement coordination system that bracing cable is made to generate displacement by driving cable wire, from
And rear fairing is made continuously to change shape, and it is easy to operate, it is easy to implement.
The above is only a preferred embodiment of the present invention, it is noted that for the ordinary skill people of the art
It for member, can also make several improvements without departing from the principle of the present invention, these improvement also should be regarded as of the invention
Protection scope.
Claims (4)
1. the shape control system that a kind of morphing can be changed camber trailing edge formations, it is characterised in that: by shape control system edge
It opens up to m subregion is divided into, master control cable wire (1) is provided on every segment boundary of m subregion, close to upper and lower surface master control cable wire number
Amount is respectively m+1, has n segment in each subregion, bracing cable (2) are disposed on each segment, respectively arrange n close to upper and lower surface
Bracing cable, is disposed with support shaft (3) in rear starting point, m+1 connection master control cable wire is evenly arranged on the support shaft (3)
(1) the first axle sleeve (4) is evenly arranged the second of n connection bracing cable (2) according to the position of bracing cable (2) in each subregion
Axle sleeve (5), the highs and lows for connecting the first axle sleeve (4) anchor ring of master control cable wire (1) process a raised circle respectively
Hole is got through in cylindricality stake, cylindrical stake side, for across master control cable wire (1) and bracing cable (2), production to have cunning on support shaft (3)
Nest (6) is radially put into the pin (7) for being longer than half bush wall thickness on the first axle sleeve (4), the second axle sleeve (5), pin (7) is made to exist
Sliding in sliding nest (6).
2. the shape control system that morphing as described in claim 1 can be changed camber trailing edge formations, it is characterised in that: also wrap
It includes displacement coordination system (8), displacement coordination system (8) is made of m short beam, the corresponding short beam of each subregion.
3. the shape control system that morphing as described in claim 1 can be changed camber trailing edge formations, it is characterised in that: in circle
A pin (7) is respectively placed at the left and right sides a quarter circumference of cylindricality stake, it is corresponding every on support shaft (3) outer surface
The position of one pin circumferentially makes sliding nest (6), and the cross sectional shape of the sliding nest (6) is identical as the cross sectional shape of pin (7).
4. the shape control method that a kind of morphing can be changed camber trailing edge formations, it is characterised in that: steps are as follows:
(1) support shaft (3) chooses aluminium alloy extrusions, is thick-walled tube, and length is equal to rear and extends the length to deformable region,
The outer surface processing of support shaft (3) is smooth, to cooperate with the first axle sleeve (4), the second axle sleeve (5)；
(2) first axle sleeves (4), the second axle sleeve (5) are thick-walled tube, choose aluminium alloy extrusions, connect the first axle of master control cable wire
Set (4), which is equally spaced, is evenly arranged in the first axle sleeve of every two (4) in the second axle sleeve (5) on support shaft (3), connecting bracing cable
Between, between two neighboring first axle sleeve (4), the second axle sleeve (5) there are identical gap, the first axle sleeve (4), the second axle sleeve (5)
Inner surface processing is smooth, makes a call to a diameter and is less than the highs and lows of the first axle sleeve (4), the second axle sleeve (5) anchor ring are each
Cylindrical stake is fixed on the first axle sleeve (4), the second axis by screw by the counterbore of the first axle sleeve (4), the second axle sleeve (5) width
It covers on (5), the position on the side of cylindrical stake close to upper surface makes a call to one according to the size of master control cable wire (1) or bracing cable (2)
A through-hole is used to across master control cable wire (1) or bracing cable (2)；
(3) divide using cylindrical stake as symmetry axis in the left and right sides of cylindrical stake four on the first axle sleeve (4), the second axle sleeve (5)
One of radially respectively place the pin (7) for being longer than half bush wall thickness at circumference, corresponded on support shaft (3) outer surface each
The position of a pin circumferentially makes sliding nest (6), and the cross sectional shape of sliding nest (6) is identical as the cross sectional shape of pin (7)；
(4) displacement coordination system (8) is a flute profile short beam, and the top surface of short beam is beaten elliptical aperture according to the position of cylindrical stake, made
Each cylindrical stake can extend there through, elliptical long edge first axle set (4), the second axle sleeve (5) axial direction, elliptical length
Edge lengths are determined that bond length is equal to cylindrical stake diameter by rear deformation extent, and apical side height, which is no more than in cylindrical stake, to be used
It is correspondingly connected at the cylindrical stake of master control cable wire, highly answers at the both ends of short beam in the hole for wearing master control cable wire (1) and bracing cable (2)
Short beam for the half of intermediate altitude, and two neighboring by stages cooperates here, retains top half on one side, retains on one side
Half part；
(5) master control cable wire (1) and bracing cable (2) are fixed in rear core plate end, and core is fixed in the bracing cable (2) close to upper surface of the airfoil
The lower surface of plate is fixed on the upper surface of core plate close to the bracing cable (2) of wing lower surface.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201810989388.0A CN109334949B (en) | 2018-08-28 | 2018-08-28 | Shape control system and method for variable camber trailing edge structure of morphing wing |
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| CN112278238A (en) * | 2019-07-26 | 2021-01-29 | 香港城市大学深圳研究院 | Wing and aircraft that can warp in succession |
| CN113232828A (en) * | 2021-05-31 | 2021-08-10 | 南京航空航天大学 | Deflection control mechanism of deformable structure of supersonic aircraft head |
| CN113232828B (en) * | 2021-05-31 | 2022-04-22 | 南京航空航天大学 | Deflection control mechanism of deformable structure of supersonic aircraft head |
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