CN102030110B - Clamp device for involutory processing of anti-interference airplane fuselage and wings intersection point - Google Patents
Clamp device for involutory processing of anti-interference airplane fuselage and wings intersection point Download PDFInfo
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- CN102030110B CN102030110B CN201010526069XA CN201010526069A CN102030110B CN 102030110 B CN102030110 B CN 102030110B CN 201010526069X A CN201010526069X A CN 201010526069XA CN 201010526069 A CN201010526069 A CN 201010526069A CN 102030110 B CN102030110 B CN 102030110B
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Abstract
The invention relates to a clamp device for involutory processing of an anti-interference airplane fuselage and wings intersection point, which comprises a front section clamp assembly, a back section clamp assembly, a connecting assembly and an accessory, wherein the front section clamp assembly and the back section clamp assembly are connected together through the connecting assembly and then connected and fixed together with airplane fuselage hangers and airplane wing hangers through the connecting assembly and the accessory. In the invention, the clamp device is applied to the field of involutory assembling processing of the anti-interference airplane fuselage and airplane wings intersection point for the first time; the airplane wings and the airplane fuselage hangers are clamped and fixed together through the device to form a stable processing environment, therefore, the stability of the assembling processing of an airplane is greatly improved, the processing quality is ensured, the processing efficiency is enhanced at the same time, the processing cost is reduced, and the important insurance for involutory processing of the anti-interference airplane fuselage and airplane wings intersection point is provided. The clamp device has better practical value and wide application prospect in the technical field of aviation.
Description
Technical field
The present invention relates to a kind of grip device that is applicable to the involutory processing of aircraft, more particularly, be based on a kind of anti-interference airframe, the involutory processing clamp device of wing intersection point of space structure and simulation analysis, be applied to the involutory assembling processing of the special intersection points of labyrinth such as airframe, wing band muscle, beam, belong to the aircraft manufacturing technical field.
Background technology
In the aircraft manufacturing field, when especially fighter plane is made, after fuselage, the machine-shaping of wing difference, owing to make and assembly error, need again involutory processing.The mode that adopts at present is manual align reaming, and fuselage, wing after posture adjustment latch on the carriage is involutory, are extracted locating dowel pin out respectively, carry out involutory processing, and the location that relies in the processing conducts oneself with dignity to keep by fuselage, wing.This kind mode can not have large force of cut, otherwise very easily causes the positioning of fuselage, wing, causes involutory not the going up in position, hole of being processed at last.This has restricted the application of process technology greatly, and the assembling process-cycle of the aircraft that seriously lagged behind, the while can't ensure the crudy of aircraft.
The development of processing realistic situation and opportunity of combat of new generation needs us that a kind of practicable airframe, the involutory processing clamp device of wing intersection point are provided, and to guarantee aircraft stablizing in involutory processing, improves work efficiency, guarantees crudy.Muscle, girder construction and the joint of while airframe, some intersection point place complexity of wing, high locked bolts etc. are also had higher requirement to the profile of airframe, the involutory processing clamp device of wing intersection point, produce interference with airframe, wing to avoid anchor clamps in installation, fixation procedure.
Summary of the invention
1, purpose: the purpose of this invention is to provide a kind of anti-interference airframe, the involutory processing clamp device of wing intersection point, it is used for guaranteeing the stability of course of processing airframe, the special position of intersecting point of wing, makes the course of processing efficient, and is reliable.
Anti-airframe, the involutory processing unit (plant) of wing of interfering of this kind adopts software CATIAV5R17 to become figure, and places the aircraft digital-to-analogue to carry out space motion emulation, guarantees rational in infrastructurely, adopts simultaneously Mechanics Simulation, guarantees that stiffness meets the requirements.
2, technical scheme: a kind of anti-interference airframe of the present invention, the involutory processing clamp device of wing intersection point, it is by by anchor clamps leading portion assembly 1, anchor clamps back segment assembly 2, coupling assembling and annex consist of, the position annexation is therebetween: anchor clamps leading portion assembly 1 and anchor clamps back segment assembly 2 link together by coupling assembling, are connected and fixed by coupling assembling and annex and fuselage auricle 51, wing auricle 52 again.With reference to accompanying drawing Fig. 1, Fig. 2.
Described anchor clamps leading portion assembly 1 comprises anchor clamps leading portion matrix 11, anchor clamps leading portion cushion block 12, and cover 13 at the bottom of the anchor clamps leading portion, leading cover compresses screw 14.The position annexation is therebetween: 2 anchor clamps leading portion cushion blocks 12 are screwed in anchor clamps leading portion matrix 11 inboards, the bottom outlet 113 that cover 13 is compressed into anchor clamps leading portion matrix 11 at the bottom of the anchor clamps leading portion, its both ends of the surface respectively with anchor clamps leading portion matrix 11 inside and outside end face.2 leading covers compress screw 14 and are screwed on anchor clamps leading portion matrix 11 outer faces.
This anchor clamps leading portion matrix 11 is seen Fig. 3, Fig. 2, and it is bow-shaped structural, and arc boss is worn in its inner, and boss is used for reducing fuselage housing screw 33 extension elongations, improves screw in compression intensity, and arcuate structure is used for preventing interfering with wing auricle 52.Upper and lower end face respectively has a trapezoidal form hole, can be used for observing machining status and chip removal, for guaranteeing Joint strenght, this coboundary, trapezoidal form hole is no more than the inner end surface of anchor clamps leading portion matrix 11, the line parallel of cutting sth. askew of this trapezoidal hypotenuse boundary line, trapezoidal form hole and the chamfering of cutting sth. askew; The crossbeam of upper and lower end face respectively has 2 pin-and-hole through holes 111,3 tie bolt tapped bore through holes 112; Its side has 1 bottom outlet through hole 113,2 leading covers to compress 115,3 of 114,2 housing screw tapped bore of screw thread blind hole through holes and support 116,2 stretching screw through holes 117 of jackscrew tapped through hole; Inner end surface has 2 tappedes blind hole 118.See Fig. 3 b, near the another side of fuselage position three sections steps chamfering of cutting sth. askew is arranged, epimere chamfering section 119 is avoided interfering with fuselage auricle entablatrance 513, its section form is L-shaped, stage casing chamfering section 120 is avoided interfering with fuselage auricle diagonal bar 514, its section form is rectangular, and hypomere chamfering section 121 is avoided interfering with fuselage auricle cross sill 515, and its section form is L-shaped.This anchor clamps leading portion matrix 11, material adopts the Lc4 superduralumin, is issued to the lightweight effect in the proof strength prerequisite.This anchor clamps leading portion cushion block 12, its profile are that the lower end is screw thread, and the upper end is cylindric, are milled with two side channels at cylindrical end and are convenient to install.Anchor clamps leading portion cushion block 12 is tightened on anchor clamps leading portion matrix 11 inner side ends by tapped blind hole 118.Its quantity is 2.Cover 13 at the bottom of this anchor clamps leading portion, its profile is that boring is cylindric, and wall thickness is 5mm, and the two ends inside circumference has 2 * 45 ° of chamferings, is convenient to install.Overlap 13 external diameters and anchor clamps leading portion matrix side bottom outlet 113 internal diameter interference fit at the bottom of the anchor clamps leading portion, cover at the bottom of the anchor clamps leading portion 13 squeezed into bottom outlet 113, make overlap at the bottom of the anchor clamps leading portion 13 both ends of the surface respectively with anchor clamps leading portion matrix 11 inside and outside end face.Material adopts the T12A carbon tool steel.This leading cover compresses screw 14, and the large head of a nail is cylindric, has interior hex slot on it.Being used for processing used leading cover is fixed in cover 13 at the bottom of the anchor clamps leading portion.
Described anchor clamps back segment assembly 2 comprises anchor clamps back segment matrix 21, anchor clamps back segment cushion block 22, cover 23 at the bottom of the anchor clamps back segment, rear guide pin bushing housing screw 24.The position annexation is therebetween: 2 anchor clamps back segment cushion blocks 22 are screwed in anchor clamps back segment matrix 21 inboards, the bottom outlet 213 that cover 23 is compressed into anchor clamps back segment matrix 21 at the bottom of the anchor clamps back segment, its both ends of the surface respectively with anchor clamps back segment matrix 21 inside and outside end face.Guide pin bushing housing screw 24 is screwed on anchor clamps back segment matrix 21 outer faces after 2.
This anchor clamps back segment matrix 21 is seen Fig. 4, Fig. 2, and it also is bow-shaped structural, and arc boss is worn in its inner, and boss is used for reducing fuselage housing screw 33 extension elongations, improves screw in compression intensity, and arcuate structure is used for preventing interfering with wing auricle 52.Upper and lower end face respectively has a rectangle form hole, can be used for observing machining status and chip removal; The crossbeam of upper and lower end face respectively has 2 pin-and-hole through holes 211,3 tie bolt through holes 212; 215,3 of 214,2 housing screw tapped through holees of guide pin bushing housing screw tapped blind hole supported 216,2 stretching screw through holes 217 of jackscrew tapped through hole after there were 1 bottom outlet through hole 213,2 in the side; Inner end surface has 2 tappedes blind hole 218.This anchor clamps back segment matrix 21, material adopts the Lc4 superduralumin, is issued to the lightweight effect in the proof strength prerequisite.This anchor clamps back segment cushion block 22:, its profile is the lower end screw thread, the upper end is cylindric, for the ease of installing, mills out two side channels.Anchor clamps back segment cushion block 22 is tightened on anchor clamps back segment matrix 21 inner side ends by tapped blind hole 218.Its quantity is 2.Cover 23 at the bottom of this anchor clamps back segment, it is cylindric that its profile is boring, and wall thickness is 5mm, and the two ends inside circumference has 2 * 45 ° of chamferings, is convenient to install.Overlap 23 external diameters and anchor clamps back segment matrix side bottom outlet 213 internal diameter interference fit at the bottom of the anchor clamps back segment, cover at the bottom of the anchor clamps back segment 23 squeezed into bottom outlet 213, make overlap at the bottom of the anchor clamps back segment 23 both ends of the surface respectively with anchor clamps back segment matrix 21 inside and outside end face.Material adopts the T12A carbon tool steel.Guide pin bushing housing screw 24 after being somebody's turn to do, the large head of a nail, cylindric, have interior hex slot on it.Be used for to process and overlap in 23 at the bottom of used rear guide pin bushing is pressed abd fixed on the anchor clamps back segment.
Above-mentioned " leading cover compresses screw 14 " and " rear guide pin bushing housing screw 24 ", its front guide pin bushing and rear guide pin bushing are the parts adjacent with this device, are connected with this device by housing screw.
Described coupling assembling comprises that 33,6 groups of wings of 32,4 groups of fuselage housing screws of 31,6 groups of tie bolts of 4 groups of pins support 36,4 nuts 37 of 35,4 pressing plates of 34,4 groups of stretching screws of jackscrew.Be symmetrically distributed on anchor clamps leading portion assembly 1 and the anchor clamps back segment assembly 2.This pin 31:
Long 40mm straight pin is used for anchor clamps leading portion matrix 11 and anchor clamps back segment matrix 21 are aligned, the anti-shearing.The hexagonal stainless steel bolt is used for anchor clamps leading portion matrix 11 and anchor clamps back segment matrix 21 are linked together in the long 50mm of this tie bolt 32:M10.The hexagonal stainless steel screw is used for anchor clamps leading portion matrix 11 in the long 90mm of this fuselage housing screw 33:M12, and anchor clamps back segment matrix 21 tightens together with fuselage auricle 51.This wing supports hexagonal jackscrew in the long 60mm of jackscrew 34:M12, contacts support machine wing lug sheet 52 with wing auricle 52 outer faces.The long 110mm outer-hexagonal of this stretching screw 35:M10 stainless steel screw, screw head inner end surface and pressing plate 36 step trough end contacts, the screw afterbody is screwed with nut 37.This pressing plate 36: be the cuboid with two-layer ladder strip hole, head contacts with wing auricle 52 inner side ends, the middle part step trough is embedded with stretching screw 35 ailheads, and afterbody contacts with anchor clamps leading portion cushion block 12 or anchor clamps back segment cushion block 22, is stretching screw 35 and wing auricle 52 transition connecting apparatus.This nut 37:M10 is screwed in stretching screw 35 afterbodys.
Described annex is pad, and this pad is the bending aluminum strip, and anti-interference need cut part, adds in fuselage housing screw 33 and fuselage auricle 51 outer face contact positions, and the housing screw end stays impression at fuselage auricle end face when preventing the application of force.
3, advantage and effect: a kind of anti-interference airframe of the present invention, the involutory processing clamp device of wing intersection point have following advantage:
(1) clamp structure is optimized processing, interferes with fuselage, wing generation when having avoided some specific position to install and fix.
(2) first with fixture application in involutory assembling processing, conventional airframe, the involutory processing of wing have been changed without stationary fixture, the unsettled present situation of the course of processing, airframe, the involutory processing clamp device of wing intersection point and airframe, wing form closed loop power stream, make operating force become internal force, greatly improved the stability of aircraft state in the course of processing.
(3) adopt anti-airframe, the involutory processing clamp device of wing intersection point of interfering, airframe, wing fixing are in stable condition, add and can adopt larger cutting-in man-hour, and having greatly reduced machining needs knife bar quantity, has improved work efficiency.
(4) airframe, the involutory processing clamp device of wing intersection point are through checking, and dynamic and static rigidity is stable in the fastening course of processing, and product processing quality can be guaranteed fully.
(5) use of airframe, the involutory processing clamp device of wing intersection point has been saved tooling cost so that machining process is simplified greatly.
Description of drawings
Fig. 1 is the external structure scheme drawing of a kind of anti-interference airframe of the present invention, the involutory processing clamp device of wing intersection point
Fig. 2 is Fig. 1 explosive view
Fig. 3 is anchor clamps leading portion basal body structure scheme drawing of the present invention
Fig. 3 a is that isometric view is looked on an anchor clamps leading portion basal body structure left side
Fig. 3 b is that isometric view is looked on the anchor clamps leading portion basal body structure right side
Fig. 4 is anchor clamps back segment basal body structure scheme drawing of the present invention
Fig. 5 is airframe, wing intersection point place auricle structural representation
Fig. 5 a is fuselage auricle structural representation
Fig. 5 b is wing auricle structural representation
Among the figure: 1. anchor clamps leading portion assembly 11. anchor clamps leading portion matrixes 111. pin-and-hole through holes 112. tapped through holees
113. bottom outlet through hole 114. tappedes blind hole 115. tapped through holees 116. tapped through holees 117. through holes
118. tapped blind hole 119. epimere chamferings 120. stage casing chamferings 121. hypomere chamferings 12. anchor clamps leading portion cushion blocks
Compress screw 13. overlap 14. leading covers at the bottom of the anchor clamps leading portion
2. anchor clamps back segment assembly 21. anchor clamps leading portion matrixes 211. pin-and-hole through holes 212. through holes 213. bottom outlet through holes
214. tapped blind hole 215. tapped through holees 216. tapped through holees 217. through holes 218. tappedes blind hole
22. overlap 24. rear guide pin bushing housing screws at the bottom of the anchor clamps back segment cushion block 23. anchor clamps back segments
36. pressing plate 37. nuts
41. anchor clamps leading portion pad 42. anchor clamps back segment pads
51. fuselage auricle 511. front surfaces 512. rear surfaces 513. fuselage auricle entablatrances, 514. fuselage auricle diagonal bars
515. fuselage auricle cross sill
52. wing auricle 521. front auricle outer face 522. rear auricle outer face 523. inner end surfaces
The specific embodiment
Below in conjunction with accompanying drawing this device is further specified.
See also Fig. 1, Fig. 2, Fig. 3, Fig. 4, shown in Figure 5, a kind of anti-interference airframe of the present invention, the involutory processing clamp device of wing intersection point are by segment body assembly 1 before the anchor clamps, segment body assembly 2 behind the anchor clamps, coupling assembling and annex four parts consist of.The position annexation is therebetween: anchor clamps leading portion assembly 1 and anchor clamps back segment assembly 2 link together by coupling assembling, are connected and fixed by coupling assembling and annex and fuselage auricle 51, wing auricle 52 again.
1. anchor clamps leading portion assembly 1 is by anchor clamps leading portion matrix 11, and anchor clamps leading portion cushion block 12, cover 13 at the bottom of the anchor clamps leading portion, leading cover compress screw 14 and consist of.2 anchor clamps leading portion cushion blocks 12 are connected to anchor clamps leading portion matrix 11 inboards by tapped blind hole 118, bottom outlet 113 interference fit of cover 13 and anchor clamps leading portion matrix 11 at the bottom of the anchor clamps leading portion, its magnitude of interference is 0.03mm, by vice with the anchor clamps leading portion at the bottom of cover 13 squeeze into anchor clamps leading portion matrix bottom outlet 113, make overlap at the bottom of the anchor clamps leading portion 13 both ends of the surface respectively with anchor clamps leading portion matrix 11 inside and outside end face.2 leading covers compress screw 14 and are screwed in the tapped blind hole 114 of anchor clamps leading portion matrix 11 outer faces.
2. anchor clamps back segment assembly 2 is by anchor clamps back segment matrix 21, anchor clamps back segment cushion block 22, and cover 23 at the bottom of the anchor clamps back segment, rear guide pin bushing housing screw 24 consists of.2 anchor clamps back segment cushion blocks 22 are connected to anchor clamps back segment matrix 21 inboards by tapped blind hole 218, bottom outlet 213 interference fit of cover 23 and anchor clamps back segment matrix 21 at the bottom of the anchor clamps back segment, its magnitude of interference is 0.03mm, by vice with the anchor clamps back segment at the bottom of cover 23 squeeze into anchor clamps back segment matrix bottom outlet 213, make overlap at the bottom of the anchor clamps back segment 23 both ends of the surface respectively with anchor clamps back segment matrix 21 inside and outside end face.Guide pin bushing housing screw 24 is screwed in the tapped blind hole 214 of anchor clamps back segment matrix 21 outer faces after 2.
3. anchor clamps leading portion assembly 1 connects into an integral body with anchor clamps back segment assembly 2 by 4 groups of pins 31 and 6 groups of tie bolts 32.Pin 31 passes the pin-and-hole through hole 211 of segment body assembly 2 behind the pin-and-hole through hole 111 of segment body matrix 11 before the anchor clamps and the anchor clamps, and the pin-and-hole position is aligned, and then with anchor clamps leading portion matrix 11 and anchor clamps back segment matrix 21 axial location.Tie bolt 32 usefulness outer hexagonal spanners are tightened, and pass respectively the through hole 212 of anchor clamps back segment matrix 21 and the tapped through hole 112 of anchor clamps leading portion matrix 11, and segment body matrix before the anchor clamps 11 and anchor clamps back segment matrix 21 are fixed together.
4. anchor clamps leading portion pad 41 hangs over anchor clamps leading portion matrix 11 the inners and wears on the arc boss, and anchor clamps back segment pad 42 hangs over anchor clamps back segment matrix 21 the inners and wears on the arc boss.2 groups of fuselage housing screws 33 pass 2 groups of tapped through holees 115 of anchor clamps leading portion matrix 11, are pressed on the anchor clamps leading portion pad 41, and anchor clamps leading portion pad 41 contacts with fuselage auricle 51 front surfaces 511; 2 groups of fuselage housing screws 33 pass 2 groups of tapped through holees 215 of anchor clamps back segment matrix 21, are pressed on the anchor clamps back segment pad 42, and anchor clamps back segment pad 42 contacts with fuselage auricle 51 rear surfaces 512.Anchor clamps leading portion matrix 11 and the fuselage housing screw 33 usefulness outer hexagonal spanners on the anchor clamps back segment matrix 12 are tightened after symmetry tightens in advance, and anchor clamps leading portion assembly 1 is fixed on the fuselage auricle 51 with anchor clamps back segment assembly 2.
5.3 the group wing supports 3 groups of tapped through holees 116 that jackscrew 34 passes anchor clamps leading portion matrix 11, is pressed on the front auricle outer face 521 of wing auricle 52; 3 groups of wings support 3 groups of tapped through holees 116 that jackscrew 34 passes anchor clamps back segment matrix 12, are pressed on the rear auricle outer face 522 of wing auricle 52, tighten in advance with outer hexagonal spanner.
6.2 group stretching screw 35 passes two groups of through holes 117 of anchor clamps leading portion matrix 11, screw head is imbedded in the pressing plate 36, and screw head inner end surface and pressing plate 36 step trough end contacts, screw afterbody through hole 117 from the anchor clamps leading portion matrix 11 stretches out, and is screwed with nut 37.Pressing plate 36 heads contact with wing auricle 52 inner side ends 523, and afterbody contacts with anchor clamps leading portion cushion block 12; 2 groups of stretching screws 35 pass two groups of through holes 217 of anchor clamps back segment matrix 21, and screw head is imbedded in the pressing plate 36, and screw head inner end surface and pressing plate 36 step trough end contacts, screw afterbody through hole 217 from the anchor clamps back segment matrix 21 stretches out, and is screwed with nut 37.Pressing plate 36 heads contact with wing auricle 52 inner end surfaces 523, and afterbody contacts with anchor clamps back segment cushion block 22.Tighten in advance all stretching screw nuts 37 with interior hexagon socket spanner, anchor clamps leading portion assembly 1 is fixed on the wing auricle 52 with anchor clamps back segment assembly 2.
7. successively wing is supported jackscrew 34 with deciding torque wrench, fuselage housing screw 33, stretching screw 35 is decided power and is tightened, decide the power value and be respectively 2NM, 20NM, 15NM, so far whole airframe, the involutory processing clamp device of wing intersection point and airframe, wing auricle fixedly clamping finish, can carry out following process.Whole installing and fixing in the process; should note: epimere chamfering 119 is avoided interfering with fuselage auricle entablatrance 513; stage casing chamfering 120 is avoided interfering with fuselage auricle diagonal bar 514, and hypomere chamfering 121 is avoided interfering with fuselage auricle cross sill 515, with protection fuselage, wing structure integraty.
The invention discloses a kind of anti-interference airframe, the involutory processing clamp device of wing intersection point, domesticly first grip device to be applied to airframe, the involutory assembling manufacture field of wing intersection point, and consider that labyrinth affects anchor clamps, by this device with aircraft wing, some specific position auricle of fuselage grips together, form stable processing environment, greatly expanded the range of use of anchor clamps, improved the stability of processing, crudy is guaranteed, brought up to simultaneously work efficiency, save tooling cost, be the labyrinth airframe, the involutory processing of wing intersection point provides important leverage.
Claims (5)
1. an airframe, the involutory processing clamp device of wing intersection point, it is characterized in that: it is by anchor clamps leading portion assembly (1), anchor clamps back segment assembly (2), coupling assembling and annex consist of, anchor clamps leading portion assembly (1) and anchor clamps back segment assembly (2) link together by coupling assembling, are connected and fixed by coupling assembling and annex and fuselage auricle (51), wing auricle (52) again;
Described anchor clamps leading portion assembly (1) comprises anchor clamps leading portion matrix (11), anchor clamps leading portion cushion block (12), and cover (13) at the bottom of the anchor clamps leading portion, leading cover compresses screw (14); 2 anchor clamps leading portion cushion blocks (12) are screwed in anchor clamps leading portion matrix (11) inboard, cover (13) is compressed into the bottom outlet (113) of anchor clamps leading portion matrix (11) at the bottom of the anchor clamps leading portion, its both ends of the surface respectively with the inside and outside end face of anchor clamps leading portion matrix (11), 2 leading covers compress screws (14) and are screwed on anchor clamps leading portion matrix (11) outer face; This anchor clamps leading portion matrix (11) is bow-shaped structural, and arc boss is worn in its inner, and boss is used for reducing fuselage housing screw (33) extension elongation, improves screw in compression intensity, and arcuate structure is used for preventing from interfering with wing auricle (52); Upper and lower end face respectively has a trapezoidal form hole, can be used for observing machining status and chip removal, for guaranteeing Joint strenght, this coboundary, trapezoidal form hole is no more than the inner end surface of anchor clamps leading portion matrix (11), the line parallel of cutting sth. askew of this trapezoidal hypotenuse boundary line, trapezoidal form hole and the chamfering of cutting sth. askew; The crossbeam of upper and lower end face respectively has 2 pin-and-hole through holes (111), 3 tie bolt tapped bore through holes (112), there is 1 bottom outlet (113) anchor clamps leading portion matrix (11) side, 2 leading covers compress screw thread blind hole (114), 2 housing screw tapped bore through holes (115), 3 are supported jackscrew tapped through hole (116), and 2 stretching screw through holes (117), inner end surface have 2 tappedes blind hole (118); Anchor clamps leading portion matrix (11) has three sections steps chamfering of cutting sth. askew near the another side of fuselage position, epimere chamfering section (119) is avoided interfering with fuselage auricle entablatrance (513), its section form is L-shaped, stage casing chamfering section (120) is avoided interfering with fuselage auricle diagonal bar (514), its section form is rectangular, hypomere chamfering section (121) is avoided interfering with fuselage auricle cross sill (515), and its section form is L-shaped; This anchor clamps leading portion cushion block (12), its profile is that the lower end is screw thread, and the upper end is cylindric, is milled with two side channels at cylindrical end and is convenient to install, anchor clamps leading portion cushion block (12) is tightened on anchor clamps leading portion matrix (11) inner side end by tapped blind hole (118), and its quantity is 2; Cover (13) at the bottom of this anchor clamps leading portion, its profile is that boring is cylindric, and wall thickness is 4-6mm, and the two ends inside circumference has 2 * 45 ° of chamferings, is convenient to install; Cover (13) external diameter and anchor clamps leading portion matrix side bottom outlet (113) internal diameter interference fit at the bottom of the anchor clamps leading portion, cover (13) at the bottom of the anchor clamps leading portion is squeezed into bottom outlet (113), make at the bottom of the anchor clamps leading portion cover (13) both ends of the surface respectively with the inside and outside end face of anchor clamps leading portion matrix (11); This leading cover compresses screw (14), and the large head of a nail is cylindric, has interior hex slot on it, is used for processing used leading cover and is fixed in cover (13) at the bottom of the anchor clamps leading portion;
Described anchor clamps back segment assembly (2) comprises anchor clamps back segment matrix (21), anchor clamps back segment cushion block (22), cover (23) at the bottom of the anchor clamps back segment, rear guide pin bushing housing screw (24); 2 anchor clamps back segment cushion blocks (22) are screwed in anchor clamps back segment matrix (21) inboard, cover (23) is compressed into the bottom outlet (213) of anchor clamps back segment matrix (21) at the bottom of the anchor clamps back segment, its both ends of the surface respectively with the inside and outside end face of anchor clamps back segment matrix (21); Guide pin bushing housing screw (24) is screwed on anchor clamps back segment matrix (21) outer face after 2; This anchor clamps back segment matrix (21), it also is bow-shaped structural, and arc boss is worn in its inner, and boss is used for reducing fuselage housing screw (33) extension elongation, improves screw in compression intensity, and arcuate structure is used for preventing from interfering with wing auricle (52); Upper and lower end face respectively has a rectangle form hole, can be used for observing machining status and chip removal; The crossbeam of upper and lower end face respectively has 2 pin-and-hole through holes (211), 3 tie bolt through holes (212); There is 1 bottom outlet through hole (213) side, guide pin bushing housing screw tapped blind hole (214) after 2, and 2 housing screw tapped through holees (215), 3 are supported jackscrew tapped through holees (216), 2 stretching screw through holes (217); Inner end surface has 2 tappedes blind hole (218); This anchor clamps back segment cushion block (22), its profile is the lower end screw thread, the upper end is cylindric, for the ease of installing, mills out two side channels; Anchor clamps back segment cushion block (22) is tightened on anchor clamps back segment matrix (21) inner side end by tapped blind hole (218), and its quantity is 2; Cover (23) at the bottom of this anchor clamps back segment, it is cylindric that its profile is boring, and wall thickness is 4-6mm, and the two ends inside circumference has 2 * 45 ° of chamferings, is convenient to install; Cover (23) external diameter and anchor clamps back segment matrix side bottom outlet (213) internal diameter interference fit at the bottom of the anchor clamps back segment, cover (23) at the bottom of the anchor clamps back segment is squeezed into bottom outlet (213), make at the bottom of the anchor clamps back segment cover (23) both ends of the surface respectively with the inside and outside end face of anchor clamps back segment matrix (21); Guide pin bushing housing screw (24) after being somebody's turn to do, the large head of a nail, cylindric, have interior hex slot on it, be used for processing and overlap in (23) at the bottom of used rear guide pin bushing is pressed abd fixed on the anchor clamps back segment;
Described coupling assembling comprises 4 groups of pins (31), 6 groups of tie bolts (32), and 4 groups of fuselage housing screws (33), 6 groups of wings support jackscrew (34), 4 groups of stretching screws (35), 4 pressing plates (36), 4 nuts (37); Be symmetrically distributed on anchor clamps leading portion assembly (1) and the anchor clamps back segment assembly (2); This pin (31) is
Long 40mm straight pin is used for anchor clamps leading portion matrix (11) and anchor clamps back segment matrix (21) are aligned, the anti-shearing; This tie bolt (32) is hexagonal stainless steel bolt in the long 50mm of M10, is used for anchor clamps leading portion matrix (11) and anchor clamps back segment matrix (21) are linked together; This fuselage housing screw (33) is hexagonal stainless steel screw in the long 90mm of M12, is used for anchor clamps leading portion matrix (11), anchor clamps back segment matrix (21) are tightened together with fuselage auricle (51); It is hexagonal jackscrew in the long 60mm of M12 that this wing supports jackscrew (34), contacts support machine wing lug sheet (52) with wing auricle (52) outer face; This stretching screw (35) is the long 110mm outer-hexagonal of M10 stainless steel screw, screw head inner end surface and pressing plate (36) step trough end contact, and the screw afterbody is screwed with nut (37); This pressing plate (36) is the cuboid with two-layer ladder strip hole, head contacts with wing auricle (52) inner side end, the middle part step trough is embedded with stretching screw (35) ailhead, afterbody contacts with anchor clamps leading portion cushion block (12), anchor clamps back segment cushion block (22), is stretching screw (35) and wing auricle (52) transition connecting apparatus; This nut (37) is the M10 nut, is screwed in stretching screw (35) afterbody;
Described annex is pad, and this pad is the bending aluminum strip, and anti-interference need cut part, adds in fuselage housing screw (33) and fuselage auricle (51) outer face contact position, and the housing screw end stays impression at fuselage auricle end face when preventing the application of force.
2. a kind of airframe according to claim 1, the involutory processing clamp device of wing intersection point is characterized in that: this anchor clamps leading portion matrix (11), material adopts the Lc4 superduralumin, is issued to the lightweight effect in the proof strength prerequisite.
3. a kind of airframe according to claim 1, the involutory processing clamp device of wing intersection point is characterized in that: this anchor clamps back segment matrix (21), material adopts the Lc4 superduralumin, is issued to the lightweight effect in the proof strength prerequisite.
4. a kind of airframe according to claim 1, the involutory processing clamp device of wing intersection point is characterized in that: cover (13) at the bottom of this anchor clamps leading portion, material employing T12A carbon tool steel.
5. a kind of airframe according to claim 1, the involutory processing clamp device of wing intersection point is characterized in that: cover (23) at the bottom of this anchor clamps back segment, material employing T12A carbon tool steel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201010526069XA CN102030110B (en) | 2010-10-25 | 2010-10-25 | Clamp device for involutory processing of anti-interference airplane fuselage and wings intersection point |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201010526069XA CN102030110B (en) | 2010-10-25 | 2010-10-25 | Clamp device for involutory processing of anti-interference airplane fuselage and wings intersection point |
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| CN102030110A CN102030110A (en) | 2011-04-27 |
| CN102030110B true CN102030110B (en) | 2013-03-20 |
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| CN102020022A (en) * | 2011-01-26 | 2011-04-20 | 北京航空航天大学 | Clamp device for carrying out opposite-closing processing on intersection points of fuselage and aerofoils of airplane |
| CN109277718B (en) * | 2018-12-14 | 2024-01-05 | 太仓金硕智控设备有限公司 | Automatic welding production line for steel grating |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6141848A (en) * | 1997-06-28 | 2000-11-07 | The Boeing Company | Contoured stringer/clip drilling |
| KR20060026199A (en) * | 2004-09-20 | 2006-03-23 | 한국항공우주산업 주식회사 | Aircraft skid |
| CN101081641A (en) * | 2006-05-30 | 2007-12-05 | 空中客车德国有限公司 | Assemblage for hanger bracket with engine |
| CN201040362Y (en) * | 2006-12-18 | 2008-03-26 | 燕山大学 | Multi-paw centering clamping system |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| ITTO20060518A1 (en) * | 2006-07-14 | 2008-01-15 | Alenia Aeronautica Spa | METHOD, EQUIPMENT AND PLANT FOR THE MANUFACTURE OF SHELL STRUCTURES |
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6141848A (en) * | 1997-06-28 | 2000-11-07 | The Boeing Company | Contoured stringer/clip drilling |
| KR20060026199A (en) * | 2004-09-20 | 2006-03-23 | 한국항공우주산업 주식회사 | Aircraft skid |
| CN101081641A (en) * | 2006-05-30 | 2007-12-05 | 空中客车德国有限公司 | Assemblage for hanger bracket with engine |
| CN201040362Y (en) * | 2006-12-18 | 2008-03-26 | 燕山大学 | Multi-paw centering clamping system |
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| CN102030110A (en) | 2011-04-27 |
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