CN205675229U

CN205675229U - Folding wing

Info

Publication number: CN205675229U
Application number: CN201620324195.XU
Authority: CN
Inventors: 及兰平; 王旭
Original assignee: Individual
Current assignee: Individual
Priority date: 2016-04-05
Filing date: 2016-04-05
Publication date: 2016-11-09
Anticipated expiration: 2026-04-05

Abstract

The utility model is a kind of " folding wing ", mainly by: the part such as wing support frame, slide rail, Diaphragm-braced rib, covering, wing movement device is constituted, the wing that can be folded by a kind of wing support frame of enforcement and wing cover, when realizing that storage parked by aircraft, wing draws in and folds, take less space, after aircraft lift-off, wing launches, wing area expands therewith, formation can produce lift, the wing undertaking load, to support that aircraft flies in the air, it is mainly used in, with the aircraft compared with low velocity flight, belonging to aviation field.

Description

Folding wing

Technical field:

The utility model is a kind of " folding wing ", mainly by wing support frame, slide rail, Diaphragm-braced rib, illiteracy The part such as skin, wing movement device is constituted, for the aircraft compared with low velocity flight, belonging to aviation field.

Background technology:

Wing is the vitals of aviation aircraft, and the major function of wing is to produce lift, to support aircraft at sky Middle flight, present wing is mainly collectively constituted by wing inner support skeleton and skin, and inner support skeleton is by longitudinal and horizontal To the truss that beam formed shape is fixing, in order to maintain wing profile shape, stayed surface covering, to bear the pneumatic lotus that covering transmits Carry；Skin is in order to maintain wing profile, by wing aerodynamic power transmission to wing support frame.

Existing Fixed Wing AirVehicle wing area is substantially constant, and it is also unalterable that wing shapes one are sized, Hence in so that Fixed Wing AirVehicle takies bigger space when ground is parked, take up room to reduce, some aircraft Wing can be partially folded, such as the carrier-borne aircraft of aircraft carrier；Some small aircrafts, for the space taking when reducing storage, are adopted Rotating with wing and mode that fuselage is overlapping, rotary expansion again during flight, such as some SUAVs；But these methods all can not Change wing area, also limited by many conditions, it is impossible to be widely used.Use prior art, it is impossible to make Fixed Wing AirVehicle: Both when parking, storing, wing can be drawn in folding minimizing to take up room, can expand at expansion wing under state of flight again Area, enables wing to produce enough lift, to support that aircraft flies in the air.

Utility model content:

The purpose of this utility model is: the wing that can be folded by a kind of wing support frame of enforcement and wing cover, When realizing that storage parked by aircraft, wing draws in and folds, and takies less space, and after aircraft lift-off, wing launches, wing area with Expansion, formed can produce lift, the wing undertaking load, to support that aircraft flies in the air.

The utility model mainly by: the wing support frame of folding, slide rail, Diaphragm-braced rib, covering, wing can be drawn in The part such as movement device is constituted,

Further, wing support frame is the truss of triangle, by different, the highly different longitudinal beam of some root length degree And transverse beam, an and slide rail, by being hinged and the mode of being slidably connected is constituted, this truss in order to maintain wingpiston and Section shape, support Diaphragm-braced rib and skin, bear the pneumatic load that covering transmits；A wherein long longitudinal beam Being leading edge of a wing beam, a longest transverse beam is trailing edge beam, and slide rail is the wing root beam of wing, and slide rail is connected to aircraft On.

Further, slide rail is the wing root beam of wing, connects aircraft body and wing triangular truss, and slide block is can edge The parts that sliding-rail groove slides, the wing root end of leading edge of a wing beam is hingedly connected on the fixture of slide rail front end, can be around pin joint Rotate, it is impossible to slide along slide rail.Other each nodes of triangular truss wing root end are hingedly connected on the corresponding each slide block of slide rail, slide block Can be slided along slide rail by after wing movement device active force, thus change the length on triangular truss wing root limit, drive three Dihedral truss deforms, and changes shape and the area of triangle, it is achieved wing-folding, the purpose of expansion.

Further, for make wing support frame fold after can be parallel with fuselage, reduce further and take up room, Gu Locking member and each slide block flex outward out the fixing galianconism determining length in proportion, the fixing galianconism length hinged with leading edge of a wing beam The longest, the fixing galianconism length hinged with trailing edge beam is the shortest, each node of triangular truss wing root end, is hingedly connected to corresponding On the fixing galianconism of slide block.

Further, leading edge of a wing beam utilizes leading edge of a wing thickness and width, is fabricated to meet the shape of aerodynamic force, can Enough increasing its intensity, can keeping again the aerodynamic configuration that the leading edge of a wing is good, the wing root end of leading edge beam extends to machine again from pin joint In body, wing root front end can be made to have preferable aerodynamic configuration, the constraint of fuselage can also be utilized to strengthen leading edge beam bending resistance, antitorque energy Power.

Further, trailing edge beam utilizes thickness and the width of trailing edge, is fabricated to the triangle with sufficient intensity The base of shape truss.The wing tip position of trailing edge beam wing tip position and leading edge beam is articulated and connected, and wing root position is hingedly connected to slide rail Slide block on.

Further, transverse beam and longitudinal beam are in triangular truss, mutually each other along wing thickness direction upper-lower position hinge Connect in succession, the termination of each beam be connected to leading edge beam, trailing edge beam, on sliding-rail sliding.

Further, Diaphragm-braced rib is the parts constituting wing vertical section aerodynamic configuration, is simultaneously connected with wing-folding Covering, many group Diaphragm-braced ribs support covering and constitute airfoil outer surface by this aerodynamic configuration, often organize Diaphragm-braced rib all by upper, Lower two roots are constituted, and two roots lay respectively at the upper and lower surface of wing triangular truss, before often organizing Diaphragm-braced rib End and leading edge of a wing beam are articulated and connected, and the rear end of two roots links together, and after wing launches, Diaphragm-braced rib is overlapped on wing The upper and lower surface of triangular truss, sends pneumatic for the wing cover bearing load to wing support frame.

Further, wing cover is connected to wing ribs, is attached to the leading edge of a wing and wing ribs surface, wing Covering is Collapsible soft material, and material should have the characteristics such as lightweight, thickness is thin, tensile strength is high, stretcher strain is little, work as machine The wing draws in when folding, and wing cover draws folding therewith in, and after wing launches, wing cover is at wing triangular truss and wing Launch under the stretching of ribs, tighten, form airfoil outer surface, utilize the tension force of wing cover material to bear what aerodynamic force brought Load.

Further, wing movement device is the mechanism making wing launch or fold, and the form of this device makes with it Relevant by state, if for the purpose of reduction takes up room when folded wing is only to deposit, before using, wing is launched, can use Manually launch or launch with machinery；If wing launches after aircraft lift-off, umbrella can be used to pull expansion, or machinery Device pulls expansion；If aircraft is reused, after flight completes landing, can use and manually fold or be folded mechanically.

A kind of folding wing, mainly by wing support frame, slide rail, Diaphragm-braced rib, wing cover, wing action dress Put composition, it is characterized in that: wing support frame can fold and drive Diaphragm-braced rib and skin synchronization action, it is achieved machine Wingfold, the purpose of expansion.Wing support frame is the truss of triangle, by different, the highly different longitudinal direction of some root length degree Beam and transverse beam and a slide rail, by being hinged and the mode of being slidably connected is constituted, this truss in order to maintain wingpiston and Section shape, support Diaphragm-braced rib and skin, bear the pneumatic load that covering transmits；A wherein long longitudinal beam Being leading edge of a wing beam, a longest transverse beam is trailing edge beam, and slide rail is the wing root beam of wing, and slide rail connects aircraft originally Body and wing triangular truss, slide block is the parts that can slide along sliding-rail groove, and the wing root end of leading edge of a wing beam is hingedly connected to sliding On the fixture of rail front end, can rotate around pin joint, it is impossible to slide along slide rail.Triangular truss other nodes of wing root end are hinged Being connected on the slide block of slide rail, slide block can be slided along slide rail by after wing movement device active force, thus changes triangle The length on truss wing root limit, drives triangular truss deformation, changes shape and the area of triangle, it is achieved wing-folding, expansion Purpose.

Brief description:

The utility model is discussed in detail below in conjunction with the accompanying drawings.

The fully deployed plane of Fig. 1 wing support frame；

Fig. 2 wing support frame folds plane completely；

Fig. 3 wing support frame partly launches plane；

Fig. 4 a nodal plane figure；

Fig. 5 a node 1-1 profile；

Fig. 6 b nodal plane figure；

Fig. 7 b node 2-2 profile；

Fig. 8 c nodal plane figure；

Fig. 9 c node 3-3 profile；

Figure 10 A-A profile；

Single line bar schematic diagram under Figure 11 wing support frame completely folded state；

Single line bar schematic diagram under Figure 12 wing support frame half deployed condition；

Single line bar schematic diagram under Figure 13 wing support frame its fully unfolded position；

The fully deployed plane perspective view of Figure 14 wing；

Figure 15 wing partly launches plane perspective；

Figure 16 wing folds plane perspective view completely；

Figure 17 wing B-B profile；

The 4-4 profile of Figure 18 B-B section；

Aircraft plane perspective view under Figure 19 wing completely folded state；

Aircraft plane perspective view under Figure 20 wing half deployed condition；

Aircraft plane perspective view under Figure 21 wing its fully unfolded position；

Aircraft plane under Figure 22 wing completely folded state；

Aircraft plane under Figure 23 wing half deployed condition；

Aircraft plane under Figure 24 wing its fully unfolded position；

Single line bar schematic diagram under Figure 25 galianconism rotary wing support frame completely folded state；

Single line bar schematic diagram under Figure 26 galianconism rotary wing support frame half deployed condition；

Single line bar schematic diagram under Figure 27 galianconism rotary wing support frame its fully unfolded position；

A kind of folding wing unmanned plane emission process schematic diagram of Figure 28；

Accompanying drawing is numbered:

1 transverse beam；2 longitudinal beams；3 leading edge of a wing beams；4 trailing edge beams；5 slide rails； 6 fix connector；7 slide blocks；8 Diaphragm-braced ribs；9 Diaphragm-braced rib tail point slide blocks (tail point slide block)；

10 coverings；11 wing movement devices；

Detailed description of the invention:

The utility model realizes its utility model mesh by implementing techniques below measure.

Fig. 1 is the folding wing support frame plane of a pair expansion, and Fig. 2 is that wing support frame folds plane completely Figure, Fig. 3 is that wing support frame partly launches plane.Wing support frame mainly by: support frame, the cunning of folding can be drawn in The part such as rail, wing movement device is constituted,

Wing support frame is different by calculating the length determining by some, highly different transverse beams the 1st, longitudinal beam 2 and Leading edge of a wing beam the 3rd, trailing edge beam 4, slide rail the 5th, fix connector the 6th, slide block 7 by being hinged and being slidably connected mode, structure Become triangular truss as shown in Figure 1.This truss is in order to maintain plane and section shape, support Diaphragm-braced rib and the table of wing Face covering, bear the pneumatic load that covering transmits.

Slide rail 5 has a following functions:

1st, it is connector between wing triangular truss and aircraft body；

2nd, connect and retrain slide block 7 so that it is can only move along slide rail；

3rd, it is the wing root beam of wing triangular truss；

Slide rail 5 connects aircraft body and wing triangular truss, and the wing root end of leading edge of a wing beam 3 is hingedly connected to fix On the galianconism of connector 6, can rotate around pin joint, it is impossible to slide (see Fig. 4, Fig. 5) along slide rail 5.Triangular truss wing root end Other each nodes, are hingedly connected on the galianconism of corresponding slide block 7, and slide block 7 is by can after wing movement device 11 active force Slide along slide rail 5, change the length of triangular truss wing root beam, drive triangular truss with the pin joint of fixing connector 6 Centered on, draw in along slide rail 5 or launch, thus changing shape and the area (see Fig. 2, Fig. 3) of triangle, it is achieved wing-folding, The purpose launched.(connected mode of slide rail, slide block, slide rail and slide block has various ways, and the utility model has been only exemplified by a kind of shape Formula).

For making the wing support frame can be parallel with fuselage after folding, reduce further and take up room, fixing connector 6 Stretching out by calculating the galianconism determining length to both sides with slide block 7, each node is articulated and connected (see figure with triangular truss wing root end 4th, Fig. 5, Fig. 6, Fig. 7, Fig. 8, Fig. 9).

Figure 10 is the A-A profile of wing support frame, and this figure presents the position between each beam of wing support frame and closes System, wherein:

Leading edge of a wing beam 3 utilizes leading edge of a wing thickness and width, is fabricated to meet aerodynamic shape, can either increase Its intensity, can keep again the aerodynamic configuration that the leading edge of a wing is good, by the wing root end of leading edge beam 3 from fixing connector 6 pin joint again Extend to, in fuselage (see Fig. 1, Fig. 4, Fig. 5), wing root front end can be made to have preferable aerodynamic configuration, the constraint of fuselage can also be utilized Strengthen leading edge beam bending resistance, anti-twisting property.

Trailing edge beam 4 utilizes thickness and the width of trailing edge, is fabricated to have the triangular truss of sufficient intensity Base.The wing tip position of trailing edge beam 4 wing tip position and leading edge beam 3 is articulated and connected, and wing root position is hingedly connected to the galianconism of slide block 7 Upper (Fig. 1, Fig. 2, Fig. 3, Fig. 8, Fig. 9).

Transverse beam 1 and longitudinal beam 2, in triangular truss, are articulated and connected along wing thickness direction upper-lower position mutually each other, The termination of each beam be connected to leading edge beam, trailing edge beam, on sliding-rail sliding.

Figure 11, Figure 12, Figure 13 use the form of single line bar apparent illustrate wing triangular truss motion principle, figure 11 is the single line bar schematic diagram under wing support frame completely folded state；Figure 12 is under wing support frame half deployed condition Single line bar schematic diagram；Figure 13 is the single line bar schematic diagram under wing support frame its fully unfolded position.

Figure 14 is the wingpiston perspective view after launching, and Figure 15 is the wingpiston perspective view of half expansion, and Figure 16 is complete The wingpiston perspective view folding.

In figure, Diaphragm-braced rib the 8th, Diaphragm-braced rib tail point slide block 9 (hereinafter referred to as: tail point slide block) is to constitute wing to indulge disconnected The parts of face aerodynamic configuration, covering 10 is the outer surface of wing.

Figure 17 is the B-B profile of Figure 14, figure illustrates wing support frame, Diaphragm-braced rib the 8th, tail point slide block the 9th, cover Relation between skin 10.Wherein, Diaphragm-braced rib 8 mainly has the effect that

1st, constitute and keep wing vertical section aerodynamic configuration；

2nd, connecting and support covering 10, constraint covering 10 presses the path motion of design when wing-folding and expansion,

3rd, under the drive of wing support frame, covering 10 is tightened so that it is aerodynamic force can be born；

4th, accept the pneumatic load of covering 10 transmission, and pass to wing support frame；

Figure 18 is the 4-4 profile of Figure 17, shows the relation between tail point slide block 9 and wing ribs the 8th, covering 10.

Tail point slide block 9 is the slidably prolongation of Diaphragm-braced rib, mainly has the effect that

1 and Diaphragm-braced rib 8 collectively form and keep wing vertical section aerodynamic configuration；

2nd, in the constraint lower slider of Diaphragm-braced rib 8, can extend or shorten the length of Diaphragm-braced rib, so that cover Skin 10 can slide along Diaphragm-braced rib 8, with the stretching to covering 10 when adaline wingfold and expansion action.

Many group Diaphragm-braced ribs support covering and constitute airfoil outer surface, often organize Diaphragm-braced rib all by upper and lower two roots Constituting, two roots lay respectively at the upper and lower surface of wing triangular truss, often organize front end and the wing of Diaphragm-braced rib Leading edge beam 3 is articulated and connected, and the rear end of two roots links together, and after wing launches, Diaphragm-braced rib 8 is overlapped on wing triangle The upper and lower surface of truss, sends pneumatic for the wing cover bearing load to wing support frame (Figure 17).Indulge to construct wing Section pneumatic profile, length trailing edge the to be exceeded beam 4 of Diaphragm-braced rib 8 afterbody, thus bring the advantage that: Diaphragm-braced The length that rib increases defines the wing area of increase.

Wing cover 10 is connected to Diaphragm-braced rib the 8th, tail point slide block 9, is attached to leading edge of a wing beam 3 and wing ribs table Face, forms airfoil outer surface (Figure 17).Wing cover 10 is Collapsible soft material, material should have lightweight, thickness is thin, anti- The characteristics such as tensile strength is high, stretcher strain is little, when wing draws in and folds, wing cover 10 draws folding therewith in, when wing launches After, wing cover 10 launches under the stretching of wing triangular truss and wing ribs, tightens, and forms airfoil outer surface, profit Bear aerodynamic load with the tension force of wing cover material.

Wing movement device 11 is mechanism, the concrete form of this device and its use shape making wing launch or fold State is relevant, if for the purpose of when folded wing is only to deposit, reduction takes up room, before using launches wing, can use artificial Launch or launch with machinery；If wing launches after aircraft lift-off, umbrella can be used to pull expansion, or mechanical device Pull expansion, or umbrella pulls expansion to add the modes such as mechanical device tension；If aircraft is reused, after aircraft landing, Wing can use and manually fold or be folded mechanically.Wing movement device 11 as required, can be placed in slide rail front end or slide rail Rear end, in accompanying drawing, the wing movement device 11 of display is a kind of rear-mounted schematic diagram.

Figure 19, Figure 20, Figure 21 illustrate " folding wing " being arranged on a body from folding completely, to half exhibition Opening, to fully deployed perspective view, Figure 19 performance is that aircraft shows at storage state and pre-flight state, Figure 20 Be the state that wing gradually spreads out after aircraft flight, Figure 21 performance is that the fully deployed rear aircraft of aircraft wing is normal The state of flight.

Figure 22, Figure 23, Figure 24 illustrate " folding wing " being arranged on a body from folding completely, to half exhibition Opening, to fully deployed plan view, Figure 22 performance is that aircraft shows at storage state and pre-flight state, Figure 23 Be the state that in aircraft flight, wing gradually spreads out, Figure 24 performance be that the fully deployed rear aircraft of aircraft wing is normal The state of flight.

Wing support frame has two kinds of forms, wing support frame described above, and galianconism and slide block 7 are integrated, slide block 7 Along slide rail 5 slide when, galianconism will not rotate.Another kind of wing-folding skeleton is as shown in Figure 25, Figure 26, Figure 27: slide block 7 He Galianconism is not one, and galianconism is longitudinal beam 2 and the extension of leading edge beam 3, and the top of galianconism is hingedly connected to fixing connector 6 He Slide block 7 center position, when slide block 7 moves along slide rail 5, drives triangular truss, is fixing with the prolongation galianconism of leading edge beam 3 It centered on pin joint on connector 6, is deformed along slide rail 5, it is achieved the purpose folding, launching, at slide block 7 sliding process In, galianconism, as the extension of beam, rotates with beam.

Expansion of the present utility model:

Based on same principle, the utility model can either be used for aircraft wing, it is also possible to is applied to aircraft vertical tail The wing and tailplane.

The slide rail 5 being given in described above is one, simultaneously slide rail and the wing root beam as both sides wing, based on former equally Reason, slide rail 5 can be also two, is placed in aircraft fuselage both sides, respectively the wing slide rail of homonymy and wing root beam.

The utility model has a following major advantage:

1st, there is same pair of wing to require to produce shape, the function of area change according to using.

2nd, the wing volume after folding, much smaller than the wing volume after expansion, for after aircraft, makes aircraft reduce storage Deposit, launch required space, therefore, it is possible to realize that aircraft stores to launch integration, possess greater flexibility.

3rd, after aircraft lift-off, folded wing launches, and wing area increases several times, can produce bigger lift, carrying Bigger load, increases the ability of aircraft.

4th, can be used for the aircraft of variety classes, different size.

The utility model purposes:

The utility model can be implemented in many fields, for example；

1st, hovercar automobile wing when normal road draws in and is folded in above roof of the vehicle, and automobile takes off When, wing launches, forms sufficiently large wing area, produces enough lift, supports automobile flight.

2nd, the restriction of the restriction due to volume for the existing individual lift device of individual lift device and mode of taking off, it is difficult to peace The installation wing, required lift is provided by engine completely, thus results in that fuel consumption is big, the time for lift off is short.And folded wing application In individual lift device, wing-folding, expansion wing horizontal flight after lift-off can be made in takeoff phase, provided a part by wing Lift, it is possible to reduce the consumption of fuel, increases aircraft voyage.

3rd, small-sized have people's aircraft.

4th, unmanned plane stores at ordinary times, transports, and can be stored in after unmanned plane wing-folding in launching tube, during use Directly being launched by launching tube, after aircraft lift-off, wing launches, and produces enough lift, supports unmanned plane during flying.This kind of mode Can be applicable to land, marine vessel, underwater submarine.

Aircraft wing stored collapsed in aircraft cabin, is carried aircraft to appointment by aircraft by mode of the 5th, dropping Spatial domain is dropped, and after aircraft air-drop, wing launches, and produces enough lift, supports aircraft flight.

Embodiment scheme:

What Figure 28 showed is a kind of employing unmanned plane of the present utility model, launches from storage, transmitting, lift-off, wing, just arrives The often process schematic of flight.

Claims

1. a folding wing, mainly by wing support frame, Diaphragm-braced rib, covering, wing movement device is constituted, and it is special Levy and be: wing support frame is by transverse beam (1), longitudinal beam (2), leading edge of a wing beam (3), trailing edge beam (4), slide rail (5), solid Determining connector (6), slide block (7), by being hinged and being slidably connected mode, triangle truss, this triangular truss is subject to After the active force of wing movement device (11), can move along slide rail (5) centered on the pin joint of fixing connector (6), from And change shape and the area of triangular truss, drive wing ribs (8), covering (10) the synchronization fortune being connected with it simultaneously Dynamic, it is achieved the folding of wing, expansion.

2. folding wing according to claim 1, is characterized in that: slide rail (5) connects aircraft fuselage, and by fixing Connector (6) and slide block (7) connect wing triangular truss, and slide rail (5) is the wing root beam of wing triangular truss, slide block (7) Can be slided along slide rail (5) by after the active force of wing movement device (11), thus change wing triangular truss wing root beam Length, and then change shape and the area of wing triangular truss.

3. folding wing according to claim 1, is characterized in that: for make wing support frame fold after can and fuselage Parallel, reduce further and take up room, fixing connector (6) and slide block (7) stretch out to both sides and determine length by calculating Galianconism, each node is articulated and connected with triangular truss wing root end.

4. folding wing according to claim 1, is characterized in that: Diaphragm-braced rib (8) constitutes and keeps wing vertical disconnected Face aerodynamic configuration, often organizes Diaphragm-braced rib and is all made up of upper and lower two roots, and two roots lay respectively at the upper of wing triangular truss Surface and lower surface, often organize the front end of Diaphragm-braced rib and leading edge of a wing beam (3) be articulated and connected, and the rear end of two roots is connected to Together, many group Diaphragm-braced ribs connect and support covering composition airfoil outer surface,.

5. folding wing according to claim 1, is characterized in that: also include tail point slide block (9), and tail point slide block (9) is The slidably prolongation of Diaphragm-braced rib, can extend in the constraint lower slider of Diaphragm-braced rib (8) or shorten Diaphragm-braced The length of rib, so that covering (10) can slide along Diaphragm-braced rib (8), with when adaline wingfold and expansion action pair The stretching of covering (10).

6. folding wing according to claim 1, is characterized in that: covering (10) is connected to Diaphragm-braced rib (8), tail point Slide block (9), is attached to leading edge of a wing beam (3) and Diaphragm-braced rib (8) surface, forms airfoil outer surface, and covering (10) is for rolling over Folded soft material.

7. folding wing according to claim 1, is characterized in that: wing movement device (11) be make wing launch or The mechanism folding, the concrete form of this device is relevant with its use state, reduces and take up room when folded wing is only to deposit For the purpose of, before using, wing is launched, artificial expansion can be used or launch with machinery；After aircraft lift-off, wing launches, Umbrella can be used to pull expansion, mechanical device to pull expansion, umbrella to pull expansion to add the modes such as mechanical device tension.

8. folding wing according to claim 1, is characterized in that: galianconism is fixed on fixing slide block (6) and slide block (7) Face, when wing action wing support frame deforms, galianconism does not rotates.

9. folding wing according to claim 1, is characterized in that: galianconism is longitudinal beam (2) and the prolongation of leading edge beam (3) Section, the top of galianconism is hingedly connected to fixing connector (6) and slide block (7) center position, when slide block (7) is transported along slide rail (5) When dynamic, drive triangular truss, centered on the prolongation galianconism of leading edge beam (3) pin joint on fixing connector (6), along sliding Rail (5) is deformed, it is achieved the purpose folding, launching, in slide block (7) sliding process, galianconism is as the extension of beam, with beam Rotate together.