CA1198322A - Method for shaping panels by bending operation, in particular panels for planking aircraft fuselage, and apparatus for implementing such method - Google Patents
Method for shaping panels by bending operation, in particular panels for planking aircraft fuselage, and apparatus for implementing such methodInfo
- Publication number
- CA1198322A CA1198322A CA000412907A CA412907A CA1198322A CA 1198322 A CA1198322 A CA 1198322A CA 000412907 A CA000412907 A CA 000412907A CA 412907 A CA412907 A CA 412907A CA 1198322 A CA1198322 A CA 1198322A
- Authority
- CA
- Canada
- Prior art keywords
- ribs
- jaw
- panels
- stiffening
- set forth
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
Links
- 238000000034 method Methods 0.000 title claims abstract description 13
- 238000007493 shaping process Methods 0.000 title claims abstract description 11
- 238000005452 bending Methods 0.000 title claims abstract description 10
- 230000003014 reinforcing effect Effects 0.000 claims abstract description 4
- 239000000969 carrier Substances 0.000 claims description 11
- 239000000463 material Substances 0.000 claims description 5
- 229910052751 metal Inorganic materials 0.000 claims description 5
- 239000002184 metal Substances 0.000 claims description 5
- 230000007935 neutral effect Effects 0.000 claims description 4
- 230000009849 deactivation Effects 0.000 claims 1
- 229920000136 polysorbate Polymers 0.000 claims 1
- 239000012530 fluid Substances 0.000 description 5
- 229910052782 aluminium Inorganic materials 0.000 description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 2
- 238000005422 blasting Methods 0.000 description 2
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000005096 rolling process Methods 0.000 description 2
- 230000008094 contradictory effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 230000010339 dilation Effects 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000003801 milling Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D47/00—Making rigid structural elements or units, e.g. honeycomb structures
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D11/00—Bending not restricted to forms of material mentioned in only one of groups B21D5/00, B21D7/00, B21D9/00; Bending not provided for in groups B21D5/00 - B21D9/00; Twisting
- B21D11/20—Bending sheet metal, not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/20—Integral or sandwich constructions
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Moulding By Coating Moulds (AREA)
- Shaping Metal By Deep-Drawing, Or The Like (AREA)
- Bending Of Plates, Rods, And Pipes (AREA)
Abstract
Abstract.
A method is disclosed for bending panels which are pro-vided with reinforcing stiffening ribs. The bending is caused by upsetting or elongating the ribs by means of an apparatus which engages the ribs at points which are spaced a predetermined distance from the panel skin.
The invention is in particular applicable to the shaping of aircraft fuselage planks.
A method is disclosed for bending panels which are pro-vided with reinforcing stiffening ribs. The bending is caused by upsetting or elongating the ribs by means of an apparatus which engages the ribs at points which are spaced a predetermined distance from the panel skin.
The invention is in particular applicable to the shaping of aircraft fuselage planks.
Description
3~
BACKGROUND OE' THE INVENTION
The present invention rela-tes to a method -for shaping panels, in particular aircraft fuselage skin sections, by means of bending. Such panels consist of a material which is elastically and plastically deformable, and in case of aircraEt fuselage skin sections, is preferably of aluminum.
Aircraft, whether military or civil, must meet ex-treme requirements. Nevertheless, their manufacture should not involve excessive cost. These somewhat contradictory criteria apply in particular to the manufacture of curved skin sections or panels used for the fuselage, the wings, and other parts of aircraft.
Recent developments in the design of aircraft have resulted in panels or skin sections having an outer skin portion and rein-forcing ribs or so-called "stringers" as integrally formed members.
By means of modern milling machines, panels having at each point calculated minimum dimensions oE skin, ribs and, as the case may be, additional fins intersecting the ribs, may be manufactured of solid aluminum sheet material.
Considerable problems, however, exist in the shaping oE
such integral panels to a curvature provided in accordance with a given pattern; the combination of skin, ribs, and fins intersecting -the ribs, renders these panels very stiff and resistant to de-formation.
Several methods are known by which such panels may be shaped: stretch-drawing, ball blasting, rolling,and whipping.
However, these processes involve difficulties when applied to in-tegral panels.
33~Z
Stretch-drawing results in locally inappropriate deformations unless very expensive apparatus is provided. Ball blasting is suitable only iE the skin thickness exceeds a pre-determined minimum to allow for the necessary skin dilation.
Rolling and whipping are sub~ect to limitations as to the shapes which may be obtained; in particular, there are problems with non-cylindrical or spherically curved workpieces, and this is particularly true when the ribs and fins of the panel have difEerent height dimensions.
SUM~IAR~ OF THE INVENTION
According to one aspect of the inven-tion there is provided a method for shaping panels made of a plastically de-formable material having both a skin portion and a plurality of intersecting stiffening and secondary ribs on one surface of said skin portion, comprising the steps of transmit-tiny force along said stiffening ribs to plastically vary the length thereof, said force being transmitted to a s-tiffening rib by engaging the stiffening rib and applying force at the points of intersection between said stiffening and secondary ribs at a prede-termined distance spaced ourwardly from said skin portion whereby said skin portion is subjected to bending forces without substantial tensioning or crushing stresses being imparted thereto.
According to another aspect of the invention there is provided an apparatus for the deformation of sheet metal provided with reinforcing ribs extending perpendicularly from one sheet metal surface thereof and extending in a direction in which a curvature of the sheet is to be made, means -to alter the length of ~3 ~ t~ 2 said ribs to vary the curvature of said sheet me-tal comprising:
at least two pairs of clamping jaws adapted to engage respectively one of said ribs at spaced apart points, adjustmen-t means associated with at least one of said pairs of clamping jaws for adjusting the distance by which said points are spaced apart, power drive means for moving said jaw pairs relative to one another, and stop means for limiting said rela-tive movement.
BRIEF DESCRIPTION OF THE DRAWINGS
Figure 1 illustrates isometrically an example oE a panel to be brought to the shape shown by means of the method of the present invention, Figure 2 is a schematized sectional view of a preferred embodiment of the apparatus of the invention, Figure 3 is a part of a plan view of the apparatus shown in Figure 2, Figure 4a and 4b illustrate, respectively, two positions of the gripping elements when engaging ribs of the panel, the illustration being substantially in the plane indicated IV-IV in Figure 1, Figure 5 is a diagram illustrating the strain distribution in the panel, F`igure 6 is a longitudinal section of an auxiliary device to be combined with the appratus, and Figure 7 is a plan view of the device shown in Figure 6.
DESCRIPTION OF A PREFERRED EMBODIMENT
Figure 1 illustrates, as an example, a panel 1 shaped in accordance with the teachings of the present invention. It is a B
3~
part of an aircraft wing and comprises an outer con-tiguous skin
BACKGROUND OE' THE INVENTION
The present invention rela-tes to a method -for shaping panels, in particular aircraft fuselage skin sections, by means of bending. Such panels consist of a material which is elastically and plastically deformable, and in case of aircraEt fuselage skin sections, is preferably of aluminum.
Aircraft, whether military or civil, must meet ex-treme requirements. Nevertheless, their manufacture should not involve excessive cost. These somewhat contradictory criteria apply in particular to the manufacture of curved skin sections or panels used for the fuselage, the wings, and other parts of aircraft.
Recent developments in the design of aircraft have resulted in panels or skin sections having an outer skin portion and rein-forcing ribs or so-called "stringers" as integrally formed members.
By means of modern milling machines, panels having at each point calculated minimum dimensions oE skin, ribs and, as the case may be, additional fins intersecting the ribs, may be manufactured of solid aluminum sheet material.
Considerable problems, however, exist in the shaping oE
such integral panels to a curvature provided in accordance with a given pattern; the combination of skin, ribs, and fins intersecting -the ribs, renders these panels very stiff and resistant to de-formation.
Several methods are known by which such panels may be shaped: stretch-drawing, ball blasting, rolling,and whipping.
However, these processes involve difficulties when applied to in-tegral panels.
33~Z
Stretch-drawing results in locally inappropriate deformations unless very expensive apparatus is provided. Ball blasting is suitable only iE the skin thickness exceeds a pre-determined minimum to allow for the necessary skin dilation.
Rolling and whipping are sub~ect to limitations as to the shapes which may be obtained; in particular, there are problems with non-cylindrical or spherically curved workpieces, and this is particularly true when the ribs and fins of the panel have difEerent height dimensions.
SUM~IAR~ OF THE INVENTION
According to one aspect of the inven-tion there is provided a method for shaping panels made of a plastically de-formable material having both a skin portion and a plurality of intersecting stiffening and secondary ribs on one surface of said skin portion, comprising the steps of transmit-tiny force along said stiffening ribs to plastically vary the length thereof, said force being transmitted to a s-tiffening rib by engaging the stiffening rib and applying force at the points of intersection between said stiffening and secondary ribs at a prede-termined distance spaced ourwardly from said skin portion whereby said skin portion is subjected to bending forces without substantial tensioning or crushing stresses being imparted thereto.
According to another aspect of the invention there is provided an apparatus for the deformation of sheet metal provided with reinforcing ribs extending perpendicularly from one sheet metal surface thereof and extending in a direction in which a curvature of the sheet is to be made, means -to alter the length of ~3 ~ t~ 2 said ribs to vary the curvature of said sheet me-tal comprising:
at least two pairs of clamping jaws adapted to engage respectively one of said ribs at spaced apart points, adjustmen-t means associated with at least one of said pairs of clamping jaws for adjusting the distance by which said points are spaced apart, power drive means for moving said jaw pairs relative to one another, and stop means for limiting said rela-tive movement.
BRIEF DESCRIPTION OF THE DRAWINGS
Figure 1 illustrates isometrically an example oE a panel to be brought to the shape shown by means of the method of the present invention, Figure 2 is a schematized sectional view of a preferred embodiment of the apparatus of the invention, Figure 3 is a part of a plan view of the apparatus shown in Figure 2, Figure 4a and 4b illustrate, respectively, two positions of the gripping elements when engaging ribs of the panel, the illustration being substantially in the plane indicated IV-IV in Figure 1, Figure 5 is a diagram illustrating the strain distribution in the panel, F`igure 6 is a longitudinal section of an auxiliary device to be combined with the appratus, and Figure 7 is a plan view of the device shown in Figure 6.
DESCRIPTION OF A PREFERRED EMBODIMENT
Figure 1 illustrates, as an example, a panel 1 shaped in accordance with the teachings of the present invention. It is a B
3~
part of an aircraft wing and comprises an outer con-tiguous skin
2 having an external Eace 3 and orthogonally intersecting ribs 4 and 5, respectively, the ribs being integrally formed with the skin 2. HereinaEter, ribs 4 which extend along the panel will be designated "stringers" while the ribs 5 extending orthogonally with respect -to -the stringers will be called "fins". Skin and ribs are provided by means of mi]ling operations or equivalent machining, rectangular cavities 6 being formed thereby. The dimensions of skin thickness, rib width and height are de-termined in accordance with the expected load, and all these dimensions may vary at different points along the same panel. The intersections of stringers and fins result in junctions 8, the corners of the cavities ~ at such junctions being rounded as at 9 (cf. Figure 3).
An apparatus suited to shape such panels will be described below. It is to be noted, however, that this appara-tus (and the method associated with it) may also be used for the shaping of panels having stringers only but no fins, or for the shaping of panels comprising a skin part made of sheet material to which ribs are fastened by means of riveting, or by any other means.
Turning now to F'igures 2 and 3, the apparatus designated with reference numeral 10 comprises a bending unit 11 and a hydraulically operated ac-tuator 12. Bending unit 11 comprises a carrier bar 14 supporting -two carriers 15 and 16, respectively.
Carriers 15 and 16 are mounted on bar 14 such that their relative spacing is adjustable and -the adjusted position may be locked.
Each carrier has an arm 17 and 18, respectively, extending orthogonally with respect to the axis of bar 14 in plane E'-E'.
B
The arms provide guide means in a common plane E-E for clamping jaw pairs 22,22' at arm 17 and 23,23' at arm 18. Plane E'-E' ex-tends perpendicularly with respect -to plane E-E which extends through bar 14 and arms 17 and 18.
A stop member 31 is disposed on bar 14 between carriers 15 and 16; member 31 may be adjusted in axial position and may be locked by means of set screw 30. Carrier 16 is movably dis-posed on carrier bar 14 and abuts stop ring 33 screwed on -the distal end of bar 14 by means oE threads 28 which also enable ad-justment of the position of member 31. The other end of bar 14 has an extension 36 which carries the annular piston 40 of hy-draulic actuator 12. Piston 40 is received in hydraulic cylinder 41 and defines, together with the cylinder, fluid chamber 42. The piston face 43' and cylinder face 43 are subjected to the pressure of fluid admitted to chamber 42 via inlet and outlet means 42' which may be connected alternatively to a source of pressurized fluid and a reservoir, respectively, by means of appropriate con-trol valves; such valves are readily available on the market and therefore are no-t illustrated in the drawings.
The free end of piston 40 is threaded onto connecting member 46 by means of threads 44. Member 46, in turn, has screw threads 46lby means of which it is fastened to extension 36 of bar 14. Set screw 45 prevents relative rotation of member 46.
Cylinder 41 abuts axially at carri.er 15. Between the latter and s-top member 31, axially extending compression springs 32 are disposed, the bias developed by said springs serving to hold carriers 1~ and 16 spaced apart when actuator 12 is discon--nected frorn the pressurized fluid source.
Arms 17 and 18 have inclined wedging sur-faces 48 engaging coun-ter-surfaces 48' of their respective clamping jaws 22,22', 23,23'. Upon the jaws being engaged over a fin, these wedging surfaces act such that the jaws, when pushed against surfaces 48, will securely clamp rib 5. This pushing occurs when -the front surfaces of the jaws abut a stringer 4, rounded edge 52 being adapted to the contour of the rounded corners 9 at in-tersections 4-5. Compression springs 49 bias the jaws into their disengaging position, in which their clamping faces 51 are spaced from rib 5.
The entire apparatus may be handled manually by means of a handle 54.
Figure 4 illustrates section views according to line IV-IV of Figure 1, parallel to the plane of one of the s-tringers 4. Arrows "P" indicate the position of the jaws 22,22'23,23' where they engage stringer 4 and rib 5; spaced aparL from the neutral axis Nf of the panel skin by a distance s is the surface center Sp assumed at which the power will be injected. Thus, the engaging surface portions of the jaws are cross-hatched in the drawing. It is to be noted that s (the distance between the arrows P and the centre plane of the skin 2) is different in Figures 4a and 4b, and that consequently even with otherwise identical condi-tions the bending will affect -the individual parts of the panel in quite a different manner.
Figure 5 is a diagram in which the bending stress and crushing stress, respectively, in skin 2 and ribs 5, respectively, are indicated. It is to be noted that, with proper election of -the spacing s, only minor tensioning or crushing stresses will be B
developed in skin 2, or there are even no such stresses at all at least in the neutral axis Nf which is coincident with the skin cen-ter plane. The shaping apparatus may be posi-tioned such that this neutral axis will always have -the same posi-tion with respect to the outer face 3 of skin 2 irrespective of skin thickness variation, with the result that no corruga-tions will be created on the outer face due to the entire shaping operation.
Figures 6 and 7 illustrate an auxiliary device 55 to be used in case oE panels where a fin terminates at a stringer. It is evident tha-t under these circumstances, one pair of jaws can-not clamp a fin. Device 55 engages stringer 4 with a transverse face 59, and it is positioned with respect to the intersection by means of depending portions 56 engaging the lateral rib surfaces 60. At its opposite end, device 55 has a -tail portion 58 having the design and size of a rib 5 so that it may be engaged by the respective pair of jaws 22,22' or 23,23'.
The apparatus operates as follows:
At first, the distance hetween carrier 15 and carrier 16 is adjusted such that their clamping jaws 22,22' and 23,23' engage a rib behind its intersection wi-th stringers, at leas-t two stringers being between the carriers. Fur-ther, stop member 31 is axially positioned on bar 1~ by means of its screw thread and is locked such that a desired shaping stroke may be executed. The ac-tuator is then Eed with pressurized hydraulic fluid into its cylinder chamber ~2 so that piston 40 is moved and shortens the distance between carriers 15 and 16. Because of the wedging surfaces ~8,~8l the jaws 22~22', 23,23' will safely grip the rib B
Z
5, and during the piston stroke which is limi-ted by stop member 31 the rib portion between the pairs of jaws will be upse-t. ~pon removal of the pressure in chamber 42, the carrlers will be moved apart because oE the bias of springs 32, and springs 49 will cause disengagement of the jaws from the lateral surfaces of rib 5.
An e~pert skilled in the art will easily realize that thedevice may be modified to shape the panel by means of elongation instead of upsetting.
.~
An apparatus suited to shape such panels will be described below. It is to be noted, however, that this appara-tus (and the method associated with it) may also be used for the shaping of panels having stringers only but no fins, or for the shaping of panels comprising a skin part made of sheet material to which ribs are fastened by means of riveting, or by any other means.
Turning now to F'igures 2 and 3, the apparatus designated with reference numeral 10 comprises a bending unit 11 and a hydraulically operated ac-tuator 12. Bending unit 11 comprises a carrier bar 14 supporting -two carriers 15 and 16, respectively.
Carriers 15 and 16 are mounted on bar 14 such that their relative spacing is adjustable and -the adjusted position may be locked.
Each carrier has an arm 17 and 18, respectively, extending orthogonally with respect to the axis of bar 14 in plane E'-E'.
B
The arms provide guide means in a common plane E-E for clamping jaw pairs 22,22' at arm 17 and 23,23' at arm 18. Plane E'-E' ex-tends perpendicularly with respect -to plane E-E which extends through bar 14 and arms 17 and 18.
A stop member 31 is disposed on bar 14 between carriers 15 and 16; member 31 may be adjusted in axial position and may be locked by means of set screw 30. Carrier 16 is movably dis-posed on carrier bar 14 and abuts stop ring 33 screwed on -the distal end of bar 14 by means oE threads 28 which also enable ad-justment of the position of member 31. The other end of bar 14 has an extension 36 which carries the annular piston 40 of hy-draulic actuator 12. Piston 40 is received in hydraulic cylinder 41 and defines, together with the cylinder, fluid chamber 42. The piston face 43' and cylinder face 43 are subjected to the pressure of fluid admitted to chamber 42 via inlet and outlet means 42' which may be connected alternatively to a source of pressurized fluid and a reservoir, respectively, by means of appropriate con-trol valves; such valves are readily available on the market and therefore are no-t illustrated in the drawings.
The free end of piston 40 is threaded onto connecting member 46 by means of threads 44. Member 46, in turn, has screw threads 46lby means of which it is fastened to extension 36 of bar 14. Set screw 45 prevents relative rotation of member 46.
Cylinder 41 abuts axially at carri.er 15. Between the latter and s-top member 31, axially extending compression springs 32 are disposed, the bias developed by said springs serving to hold carriers 1~ and 16 spaced apart when actuator 12 is discon--nected frorn the pressurized fluid source.
Arms 17 and 18 have inclined wedging sur-faces 48 engaging coun-ter-surfaces 48' of their respective clamping jaws 22,22', 23,23'. Upon the jaws being engaged over a fin, these wedging surfaces act such that the jaws, when pushed against surfaces 48, will securely clamp rib 5. This pushing occurs when -the front surfaces of the jaws abut a stringer 4, rounded edge 52 being adapted to the contour of the rounded corners 9 at in-tersections 4-5. Compression springs 49 bias the jaws into their disengaging position, in which their clamping faces 51 are spaced from rib 5.
The entire apparatus may be handled manually by means of a handle 54.
Figure 4 illustrates section views according to line IV-IV of Figure 1, parallel to the plane of one of the s-tringers 4. Arrows "P" indicate the position of the jaws 22,22'23,23' where they engage stringer 4 and rib 5; spaced aparL from the neutral axis Nf of the panel skin by a distance s is the surface center Sp assumed at which the power will be injected. Thus, the engaging surface portions of the jaws are cross-hatched in the drawing. It is to be noted that s (the distance between the arrows P and the centre plane of the skin 2) is different in Figures 4a and 4b, and that consequently even with otherwise identical condi-tions the bending will affect -the individual parts of the panel in quite a different manner.
Figure 5 is a diagram in which the bending stress and crushing stress, respectively, in skin 2 and ribs 5, respectively, are indicated. It is to be noted that, with proper election of -the spacing s, only minor tensioning or crushing stresses will be B
developed in skin 2, or there are even no such stresses at all at least in the neutral axis Nf which is coincident with the skin cen-ter plane. The shaping apparatus may be posi-tioned such that this neutral axis will always have -the same posi-tion with respect to the outer face 3 of skin 2 irrespective of skin thickness variation, with the result that no corruga-tions will be created on the outer face due to the entire shaping operation.
Figures 6 and 7 illustrate an auxiliary device 55 to be used in case oE panels where a fin terminates at a stringer. It is evident tha-t under these circumstances, one pair of jaws can-not clamp a fin. Device 55 engages stringer 4 with a transverse face 59, and it is positioned with respect to the intersection by means of depending portions 56 engaging the lateral rib surfaces 60. At its opposite end, device 55 has a -tail portion 58 having the design and size of a rib 5 so that it may be engaged by the respective pair of jaws 22,22' or 23,23'.
The apparatus operates as follows:
At first, the distance hetween carrier 15 and carrier 16 is adjusted such that their clamping jaws 22,22' and 23,23' engage a rib behind its intersection wi-th stringers, at leas-t two stringers being between the carriers. Fur-ther, stop member 31 is axially positioned on bar 1~ by means of its screw thread and is locked such that a desired shaping stroke may be executed. The ac-tuator is then Eed with pressurized hydraulic fluid into its cylinder chamber ~2 so that piston 40 is moved and shortens the distance between carriers 15 and 16. Because of the wedging surfaces ~8,~8l the jaws 22~22', 23,23' will safely grip the rib B
Z
5, and during the piston stroke which is limi-ted by stop member 31 the rib portion between the pairs of jaws will be upse-t. ~pon removal of the pressure in chamber 42, the carrlers will be moved apart because oE the bias of springs 32, and springs 49 will cause disengagement of the jaws from the lateral surfaces of rib 5.
An e~pert skilled in the art will easily realize that thedevice may be modified to shape the panel by means of elongation instead of upsetting.
.~
Claims (10)
PROPERTY OR PRIVILEGE IS CLAIMED ARE DEFINED AS FOLLOWS:
1. A method for shaping panels made of a plastically deformable material having both a skin portion and a plurality of intersecting stiffening and secondary ribs on one surface of said skin portion, comprising the steps of transmitting force along said stiffening ribs to plastically vary the length thereof, said force being transmitted to a stiffening rib by engaging the stiffening rib and applying force at the points of intersection between said stiffening and secondary ribs at a predetermined distance spaced outwardly from said skin portion whereby said skin portion is subjected to bending forces without substantial tensioning or crushing stresses being imparted thereto.
2. A method as set forth in claim 1 wherein said predeter-mined distance is selected such that a neutral axis is at least approximately in the center of said skin portion halfway from said one surface thereof.
3. A method as in claim 1, wherein the stiffening and second ribs intersect one another orthogonally.
4. A method as in claim 1, wherein the force is applied on the opposite sides of a pair of said second ribs.
5. An apparatus for the deformation of sheet metal provided with reinforcing ribs extending perpendicularly from one sheet metal surface thereof and extending in a direction in which a curvature of the sheet is to be made, means to alter the length of said ribs to vary the curvature of said sheet metal comprising:
at least two pairs of clamping jaws adapted to engage respect-ively one of said ribs at spaced apart points, adjustment means associated with at least one of said pairs of clamping jaws for adjusting the distance by which said points are spaced apart, power drive means for moving said jaw pairs relative to one another, and stop means for limiting said relative movement.
at least two pairs of clamping jaws adapted to engage respect-ively one of said ribs at spaced apart points, adjustment means associated with at least one of said pairs of clamping jaws for adjusting the distance by which said points are spaced apart, power drive means for moving said jaw pairs relative to one another, and stop means for limiting said relative movement.
6. An apparatus as set forth in claim 5 wherein a first jaw carrier for a first pair of said clamping jaws is mounted station-arily on a support, a second jaw carrier for a second pair of said clamping jaws is mounted to be movable along said support by said adjustment means and is lockable at a selected position, a stop member providing said stop means is disposed on said support be-tween said first and said second jaw carriers, and a hydraulic ram provides said power drive means and is adapted to alter the length of said support between said carriers by a distance defined by said stop member.
7. An apparatus as set forth in claim 6 wherein said clamping jaws are supported by said jaw carriers via wedging surfaces such that two jaws forming a jaw pair clamp said rib between them when a force acting in a predetermined direction parallel to said rib is exerted upon their respective carriers.
8. An apparatus as set forth in claim 6 wherein said support comprises: a hydraulic ram cylinder on which said first jaw carrier and a counter stop member are mounted, and a piston which is hydraulically displacable in said cylinder and has a piston rod which carries said second jaw carrier and said stop member.
9. An apparatus as set forth in claim 7 wherein reset spring means are provided biasing said jaw carriers into their initial position upon deactivation of said power drive means.
10. An apparatus as set forth in claim 5 for deforming panels which have first ribs to be engaged by one of said clamping jaw pairs and second ribs intersecting said first ribs orthogonally, wherein said apparatus has an intermediate force transmitting member engageable over one of said second ribs adjacent one of said intersections and provided with a tail portion to be engaged by the other pair of jaws.
Applications Claiming Priority (4)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE19813139836 DE3139836A1 (en) | 1981-10-07 | 1981-10-07 | Method and device for the bending of panels, in particular for the shell of the body of aircraft |
| DEP3139836.7 | 1981-10-07 | ||
| DEG8129965.6 | 1981-10-14 | ||
| DE19818129965 DE8129965U1 (en) | 1981-10-14 | 1981-10-14 | "DEVICE FOR CHIP-FREE SHAPING OF SHEETS WITH REINFORCING RIBS" |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA1198322A true CA1198322A (en) | 1985-12-24 |
Family
ID=25796580
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA000412907A Expired CA1198322A (en) | 1981-10-07 | 1982-10-06 | Method for shaping panels by bending operation, in particular panels for planking aircraft fuselage, and apparatus for implementing such method |
Country Status (4)
| Country | Link |
|---|---|
| EP (1) | EP0078891B1 (en) |
| CA (1) | CA1198322A (en) |
| DE (1) | DE3268822D1 (en) |
| IL (1) | IL66912A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7195203B2 (en) | 2002-03-27 | 2007-03-27 | Airbus Uk Limited | Wing skin and method of manufacture thereof |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE10007995C2 (en) * | 2000-02-22 | 2002-03-07 | Airbus Gmbh | Structural component, in particular for an aircraft and method for producing a structural component |
| US7093470B2 (en) * | 2002-09-24 | 2006-08-22 | The Boeing Company | Methods of making integrally stiffened axial load carrying skin panels for primary aircraft structure and fuel tank structures |
| CN114799756B (en) * | 2022-04-29 | 2023-10-31 | 沈阳飞机工业（集团）有限公司 | Composite manufacturing device and method for high-rib thin-wall aluminum alloy wallboard part |
| CN115090750B (en) * | 2022-07-14 | 2024-01-26 | 中国航空制造技术研究院 | High-reinforced discontinuous wall panel shot peening pre-bending tooling and forming method using same |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2980156A (en) * | 1956-10-15 | 1961-04-18 | Lockheed Aircraft Corp | Method and apparatus for stretch shaping panels |
| DE1197841B (en) * | 1963-02-14 | 1965-08-05 | Ver Flugtechnische Werke Ges M | Method and device for shaping honeycomb mats |
| FR2237435A5 (en) * | 1973-07-10 | 1975-02-07 | Aerospatiale | |
| CH624318A5 (en) * | 1977-06-16 | 1981-07-31 | Naeslund G Korstraesk Mekanisk | Method and apparatus for bending a corrugated sheet and a corrugated sheet bent by this method |
-
1982
- 1982-08-18 EP EP82107511A patent/EP0078891B1/en not_active Expired
- 1982-08-18 DE DE8282107511T patent/DE3268822D1/en not_active Expired
- 1982-09-30 IL IL66912A patent/IL66912A/en unknown
- 1982-10-06 CA CA000412907A patent/CA1198322A/en not_active Expired
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7195203B2 (en) | 2002-03-27 | 2007-03-27 | Airbus Uk Limited | Wing skin and method of manufacture thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| IL66912A (en) | 1986-03-31 |
| EP0078891A1 (en) | 1983-05-18 |
| EP0078891B1 (en) | 1986-01-29 |
| DE3268822D1 (en) | 1986-03-13 |
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| Date | Code | Title | Description |
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| MKEX | Expiry |