CN115258128B - Reinforcing structure for processing aircraft wall panel - Google Patents
Reinforcing structure for processing aircraft wall panel Download PDFInfo
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- CN115258128B CN115258128B CN202211177688.1A CN202211177688A CN115258128B CN 115258128 B CN115258128 B CN 115258128B CN 202211177688 A CN202211177688 A CN 202211177688A CN 115258128 B CN115258128 B CN 115258128B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
- B64C1/069—Joining arrangements therefor
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/10—Bulkheads
Abstract
The invention discloses a reinforcing structure for processing an aircraft panel, and relates to the technical field of aircraft panel production and processing. The aircraft comprises a driving connecting beam, a supporting main barrel, a supporting auxiliary barrel, a fixing block and a fixing plate group, wherein the driving connecting beam is fixedly connected with the supporting main barrel and the supporting auxiliary barrel, and pressure input ends of the supporting main barrel and the supporting auxiliary barrel are connected with an aircraft wall plate. Aiming at the special connecting structure of the aircraft wall plate, the connecting mechanism, the supporting mechanism and the reinforcing mechanism are additionally arranged on the original connecting structures such as welding, riveting and the like, so that the connecting structure of the aircraft wall plate is reinforced; the driving connecting beam, the reinforcing beam, the supporting main barrel and the supporting auxiliary barrel are arranged, external pressure applied to the aircraft wall plate is used as driving force, a pressure signal is converted into an electric signal through the piezoelectric sensor and the electromagnetic controller, then the electric signal is converted into a magnetic force signal, the magnetic force of the driving block is changed, the motion state of the reinforcing beam is controlled, and the aircraft wall plate connecting structure is reinforced.
Description
Technical Field
The invention belongs to the technical field of aircraft panel production and processing, and particularly relates to a reinforcing structure for aircraft panel processing.
Background
An aircraft panel is a peripheral protective structure mounted on an aircraft framework, and generally bears very large external pressure during the flight of an aircraft; therefore, the safety performance of the airplane is also greatly improved in the aspects of material strength and structural strength of the airplane wallboard; because the strength of the material is difficult to have major breakthrough in a short time, the main mode for improving the safety performance of the airplane is to improve the structural strength, or the safety performance of the airplane can be further improved by improving the structural strength under the same material strength;
the existing connection modes of the aircraft wall plates are generally simple welding, riveting and the like, and the connection structures can still realize enough structural strength when being used at the connection positions of the smooth wall plates of the aircraft, but if the connection structures are used at special-shaped connection positions, namely when an included angle exists between two adjacent wall plates, because the atmospheric pressure of the wall plates at different positions is different, the original connection structures are easily damaged or even deformed when strong impact force is applied in the flight process, and great potential safety hazards exist; in order to solve the problems, a reinforcing structure for processing an aircraft panel is designed by improving the prior art.
Disclosure of Invention
The invention aims to provide a reinforcing structure for processing an aircraft panel, which solves the problems that the existing aircraft panel is simple in connection and reinforcement mode and has large potential safety hazard.
In order to solve the technical problems, the invention is realized by the following technical scheme:
the invention relates to a reinforcing structure for processing aircraft wall plates, which comprises a connecting mechanism, a supporting mechanism and a reinforcing mechanism, wherein the connecting mechanism, the supporting mechanism and the reinforcing mechanism jointly act between an a plate and a b plate of an aircraft wall plate to be connected, each mechanism mainly acts between two aircraft wall plates with different specifications, and if the area of the a plate is smaller than that of the b plate; the connecting mechanism comprises a driving connecting beam, the supporting mechanism comprises a supporting main barrel and a plurality of supporting auxiliary barrels, and the reinforcing mechanism comprises a plurality of fixing blocks and a fixing plate group; the driving connecting beam is erected between the plate a and the plate b, and the upper surface of the driving connecting beam is bolted and fixed with the main supporting cylinder and the auxiliary supporting cylinders; the plate a and the plate b are fixed by welding, and the fixing blocks are fixedly connected to the welding positions of the plate a and the plate b by rivets; the fixing plate group comprises a plurality of high-position fixing plates and a plurality of low-position fixing plates, and the surfaces of the plate a and the plate b are welded and fixed with the high-position fixing plates and the low-position fixing plates simultaneously;
by combining the structure, the connecting mechanism, the supporting mechanism and the reinforcing mechanism which form the reinforcing structure of the aircraft wall plate are all dynamic reinforcing processes, namely the connecting structure of the two mutually connected aircraft wall plates is reinforced and supported before structural deformation is about to occur, so that the driving force source of the driving connecting beam is the deformation force source of the connecting structure of the aircraft wall plate;
the supporting main cylinder is of a hollow structure, a supporting column is slidably clamped in the supporting main cylinder, and a hydraulic cylinder structure is formed between the supporting main cylinder and the supporting column; the upper end of the support column is welded with a connecting plate, the connecting plate is fixedly connected with the plate b, and the fixed connection mode comprises rivet connection and welding; the structure of the auxiliary supporting cylinder is the same as that of the main supporting cylinder, wherein a connecting plate of the auxiliary supporting cylinder is fixed with the plate a in a welding and rivet connection mode; the length of the plate b is greater than that of the plate a, an included angle exists between the plate a and the plate b, the included angle is smaller than 180 degrees and greater than 0 degree;
the upper surface of the driving connecting beam is provided with an electromagnetic controller, a driving block is embedded in the electromagnetic controller, the driving block is an electromagnet, and the driving block is electrically connected with the electromagnetic controller; piezoelectric sensors are welded on the bottom surfaces of the main supporting cylinder and the auxiliary supporting cylinder, and the piezoelectric sensors are electrically connected with the driving block; a conduction spring is adhered between the bottom end of the supporting column and the piezoelectric sensor; by combining the structure, when the aircraft wallboard is impacted by atmospheric pressure or external force, the aircraft wallboard is sequentially extruded to the inside through the connecting plate and the supporting column, the supporting column transmits the pressure to the piezoelectric sensor through the transmission spring, and the pressure is converted into an electric signal by the electromagnetic controller to act on the magnetic variation range of the driving block, and the larger the pressure is, the larger the magnetism of the driving block is;
two connecting cavities are formed in the driving connecting beam and are respectively arranged on two opposite sides of the driving block; reinforcing beams are slidably clamped in the connecting cavity, extend to two opposite ends of the driving connecting beam respectively and are welded and extended to the surfaces of the plate a and the plate b respectively;
one end of the reinforcing beam is welded with a driven plate, wherein the driven plate is a permanent magnet; the driving block is magnetically attracted to the driven plate when being electrified, a connecting spring is adhered between the driven plate and the driving block, and the initial state of the connecting spring is a stretching state;
by combining the structure, when the magnetism of the driving block is enhanced, the driven plate can be attracted and the reinforcing beams can be driven to slide inwards, and the two reinforcing beams can pull the two airplane wallboards inwards and simultaneously when sliding simultaneously, so that the stability of the structure is ensured.
Further, the diameter of the supporting main cylinder is larger than that of the supporting auxiliary cylinder; the upper surface of the driving connecting beam is welded with a plurality of hydraulic conducting pipes, and one ends of the plurality of hydraulic conducting pipes are respectively welded and communicated with the cylinder walls of the supporting main cylinder and the supporting auxiliary cylinder; a support rod is arranged in one end of the hydraulic transmission pipe, wherein the upper end of the support rod extends to the outside of the hydraulic transmission pipe and is fixedly connected with the lower surface of the fixed block through a rivet; support a plurality of that vice section of thick bamboo is connected hydraulic pressure conduction pipe and the crisscross arrangement of hydraulic pressure conduction pipe that supports a main section of thick bamboo and be connected, and hydraulic pressure conduction pipe is rigid tubular product, and when actual concatenation installation, the hydraulic pressure conduction pipe dispersion that supports vice section of thick bamboo and connect sets up in the relative both sides that support a main section of thick bamboo, provides the auxiliary stay effect for supporting the hydraulic pressure conduction pipe that a main section of thick bamboo is connected.
Furthermore, the main supporting cylinder and the auxiliary supporting cylinder, the hydraulic transmission pipe and the supporting rod form a communicating device structure based on hydraulic transmission; the pipe body of the hydraulic transmission pipe comprises a straight pipe and a connecting elbow, wherein the straight pipe is connected and communicated with the connecting elbow through a flange; and hydraulic oil is filled in the hydraulic transmission pipe.
Furthermore, the fixed block upper surface welding has the dead lever, and wherein the dead lever is inlayed in a board between the b board, and a board and b board all with the dead lever welded fastening.
Furthermore, the welding position of the high-position fixing plate and the aircraft wall plate is higher than that of the low-position fixing plate, and the high-position fixing plate and the low-position fixing plate are of the same structure and are of bent plate structures.
Furtherly, fixed slot has been seted up to dead lever week side face, "U" shape groove has all been seted up on the surface of high-order fixed plate and low level fixed plate, and both all through "U" shape groove and fixed slot block, wherein when actual concatenation installation, dead lever and high-order fixed plate and low level fixed plate constitute tenon fourth of the twelve earthly branches block structure jointly.
Further, high-order fixed plate and low level fixed plate are crisscross arranges, and the high-order fixed plate of a board is relative with the low level fixed plate position of b board, and the low level fixed plate of a board is relative with the high-order fixed plate position of b board simultaneously, under actual operating condition, no matter the fixed block lifts or sinks, can both utilize the high-order fixed plate and the low level fixed plate of crisscross block to drive two adjacent aircraft wallboards and move towards same direction, and then strengthen the structural stability between two aircraft wallboards.
By combining the structure, when in production and processing, a plurality of high-position fixing plates and a plurality of low-position fixing plates need to be welded on the connecting surface of the aircraft wall plate in a staggered manner in advance so as to be convenient for subsequent direct reinforcement, splicing and installation;
in the actual working state, when the plate a or the plate b is impacted externally, the plate presses the inside of the structure through the connecting plate and the supporting column, the piezoelectric sensor receives a pressure signal and transmits the pressure signal to the electromagnetic controller, and the pressure signal is converted into an electric signal by the electromagnetic controller to control the driving block to have enhanced magnetism; meanwhile, the driving block attracts reinforcing beams at two ends to slide inwards by utilizing enhanced magnetic attraction, and pulls the plate a and the plate b at the same time, so that a connecting structure between the plate a and the plate b is in opposition to the compression direction to offset pressure;
meanwhile, due to the communicating vessel structure formed by the support main cylinder, the support auxiliary cylinder and the hydraulic transmission pipe, when the support column slides downwards, the support rod slides upwards through a hydraulic transmission principle, so that the fixing block is lifted upwards, and the process interacts with the process of drawing the plate a and the plate b to further reinforce the structure;
simultaneously, the fixed block utilizes the high-order fixed plate and the low level fixed plate of crisscross block to provide ascending support for the junction of two adjacent aircraft wallboards, further strengthens the structural stability between two aircraft wallboards.
The invention has the following beneficial effects:
aiming at the special connecting structure of the aircraft wall plate, the connecting mechanism, the supporting mechanism and the reinforcing mechanism are additionally arranged on the original connecting structures such as welding, riveting and the like, so that the connecting structure of the aircraft wall plate is reinforced; the aircraft panel connection structure is characterized in that a driving connection beam, a reinforcing beam, a supporting main cylinder and a supporting auxiliary cylinder are arranged, external pressure applied to an aircraft panel is used as driving force, a pressure signal is converted into an electric signal through a piezoelectric sensor and an electromagnetic controller and further converted into a magnetic signal, and the magnetic force of a driving block is changed, so that the motion state of the reinforcing beam is controlled, and the aircraft panel connection structure is reinforced;
the hydraulic transmission pipe and the support rod are arranged to form a communicating vessel structure based on a hydraulic transmission principle with the main support cylinder and the auxiliary support cylinder, and external pressure applied to the aircraft wallboard is also used as a driving force element, so that the support rod is driven to lift upwards when the structure is deformed, the antagonistic action is formed on the external pressure, and the structural strength between the aircraft wallboards is enhanced;
simultaneously, through setting up fixed block and fixed plate group, utilize support column and high-order fixed plate and low level fixed plate to constitute tenon fourth of the twelve earthly branches structure jointly, especially the crisscross mode of arranging of high-order fixed plate and low level fixed plate makes the fixed block lift or sink the connection structure that the in-process can both drive the aircraft wallboard and produce the change, has further improved the structural strength between the aircraft wallboard.
Of course, it is not necessary for any product in which the invention is practiced to achieve all of the above-described advantages at the same time.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a front elevation view of an assembled structure of a reinforcing structure for aircraft panel tooling of the present invention;
FIG. 2 is a top plan view of an assembled structure of the reinforcing structure for aircraft panel fabrication of the present invention;
FIG. 3 isbase:Sub>A schematic structural view of section A-A in FIG. 2;
FIG. 4 is a partial view of portion B of FIG. 3;
FIG. 5 is a partial view of portion C of FIG. 3;
FIG. 6 is a schematic view of the structure of section D-D in FIG. 3;
fig. 7 is an assembly structure view of the fixing block and the fixing plate group of the present invention.
In the drawings, the reference numbers indicate the following list of parts:
1. a drive connection beam; 2. supporting the main drum; 3. supporting the auxiliary cylinder; 4. a fixed block; 5. a high-position fixing plate; 19. a low-position fixing plate; 6. a support column; 7. a connecting plate; 8. an electromagnetic controller; 9. a drive block; 10. a piezoelectric sensor; 11. a conductive spring; 12. a connecting cavity; 13. reinforcing the beam; 14. a driven plate; 15. a connecting spring; 16. a hydraulic transfer tube; 17. a support bar; 18. and (5) fixing the rod.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it is to be understood that the terms "upper", "middle", "outer", "inner", and the like, indicate orientations or positional relationships, are used for convenience in describing the present invention and simplifying the description, but do not indicate or imply that the referenced components or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention.
Referring to fig. 1 to 7, the present invention is a reinforcing structure for processing aircraft wall panels, including a connecting mechanism, a supporting mechanism and a reinforcing mechanism, which act together between an a plate and a b plate of an aircraft wall panel to be connected, wherein each mechanism mainly acts between two aircraft wall panels with different specifications, for example, the area of the a plate is smaller than that of the b plate; the connecting mechanism comprises a driving connecting beam 1, the supporting mechanism comprises a supporting main barrel 2 and a plurality of supporting auxiliary barrels 3, and the reinforcing mechanism comprises a plurality of fixing blocks 4 and a fixing plate group; the driving connecting beam 1 is erected between the plate a and the plate b, and the upper surface of the driving connecting beam 1 is bolted and fixed with the supporting main barrel 2 and the plurality of supporting auxiliary barrels 3; the plate a and the plate b are fixed by welding, and the fixing blocks 4 are fixedly connected to the welding positions of the plate a and the plate b by rivets; the fixing plate group comprises a plurality of high-position fixing plates 5 and a plurality of low-position fixing plates 19, and the surfaces of the plate a and the plate b are welded and fixed with the high-position fixing plates 5 and the low-position fixing plates 19 at the same time;
by combining the structure, the connecting mechanism, the supporting mechanism and the reinforcing mechanism which form the reinforcing structure of the aircraft wall panel are all dynamic reinforcing processes, namely, the connecting structure of the two mutually connected aircraft wall panels is reinforced and supported before structural deformation is about to occur, so that the source of the driving force for driving the connecting beam 1 is the deformation source of the connecting structure of the aircraft wall panels;
the supporting main cylinder 2 is of a hollow structure, a supporting column 6 is clamped in the supporting main cylinder in a sliding mode, and a hydraulic cylinder structure is formed between the supporting main cylinder and the supporting main cylinder; the upper end of the support column 6 is welded with a connecting plate 7, the connecting plate 7 is fixedly connected with the plate b, and the fixed connection mode comprises rivet connection and welding; the structure of the support auxiliary cylinder 3 is the same as that of the support main cylinder 2, wherein a connecting plate 7 of the support auxiliary cylinder 3 is fixed with a plate a in a welding and rivet connection mode; the length of the plate b is greater than that of the plate a, an included angle exists between the plate a and the plate b, the included angle is smaller than 180 degrees and greater than 0 degree;
an electromagnetic controller 8 is installed on the upper surface of the driving connecting beam 1, a driving block 9 is embedded in the electromagnetic controller 8, the driving block 9 is an electromagnet, and the driving block 9 is electrically connected with the electromagnetic controller 8; the bottom surfaces of the main supporting cylinder 2 and the auxiliary supporting cylinder 3 are welded with piezoelectric sensors 10, wherein the piezoelectric sensors 10 are electrically connected with the driving block 9; a conduction spring 11 is adhered between the bottom end of the supporting column 6 and the piezoelectric sensor 10; by combining the structure, when the aircraft wallboard is impacted by atmospheric pressure or external force, the aircraft wallboard is sequentially extruded to the inside through the connecting plate 7 and the supporting column 6, the supporting column 6 transmits the pressure to the piezoelectric sensor 10 through the conducting spring 11, and the pressure is converted into an electric signal through the electromagnetic controller 8 to act on the magnetic variation range of the driving block 9, and the larger the pressure is, the larger the magnetism of the driving block 9 is;
two connecting cavities 12 are formed in the driving connecting beam 1, and the two connecting cavities 12 are respectively arranged on two opposite sides of the driving block 9; reinforcing beams 13 are slidably clamped in the connecting cavity 12, and the two reinforcing beams 13 respectively extend to two opposite ends of the driving connecting beam 1 and are respectively welded and extended to the surfaces of the plate a and the plate b;
one end of the reinforcing beam 13 is welded with a driven plate 14, wherein the driven plate 14 is a permanent magnet; when the driving block 9 is electrified, the driving block is magnetically attracted to the driven plate 14, a connecting spring 15 is adhered between the driven plate 14 and the driving block 9, and the initial state of the connecting spring 15 is a stretching state;
with the adoption of the structure, when the magnetism of the driving block 9 is enhanced, the driven plate 14 can be attracted and the reinforcing beams 13 can be driven to slide inwards, and when the two reinforcing beams 13 slide simultaneously, the two airplane wall plates can be pulled inwards and simultaneously, so that the stability of the structure is ensured.
Preferably, the cylinder diameter of the supporting main cylinder 2 is larger than that of the supporting auxiliary cylinder 3; the upper surface of the driving connecting beam 1 is welded with a plurality of hydraulic transmission pipes 16, and one ends of the plurality of hydraulic transmission pipes 16 are respectively welded and communicated with the cylinder walls of the supporting main cylinder 2 and the supporting auxiliary cylinder 3; a support rod 17 is arranged in one end of the hydraulic transmission pipe 16, wherein the upper end of the support rod 17 extends to the outside of the hydraulic transmission pipe 16 and is fixedly connected with the lower surface of the fixed block 4 through a rivet; support a plurality of hydraulic pressure conduction pipes 16 that vice section of thick bamboo 3 is connected and support the crisscross arrangement of hydraulic pressure conduction pipe 16 that main section of thick bamboo 2 is connected, and hydraulic pressure conduction pipe 16 is rigid tubular product, and when actual concatenation installation, the hydraulic pressure conduction pipe 16 that supports vice section of thick bamboo 3 and connect dispersedly sets up in the relative both sides that support main section of thick bamboo 2, provides the auxiliary stay effect for supporting the hydraulic pressure conduction pipe 16 that main section of thick bamboo 2 is connected.
Preferably, the supporting main cylinder 2 and the supporting auxiliary cylinder 3 form a hydraulic transmission-based communicating vessel structure together with the hydraulic transmission pipe 16 and the supporting rod 17; the body of the hydraulic transfer pipe 16 comprises a straight pipe and a connecting elbow, wherein the straight pipe is connected and communicated with the connecting elbow through a flange; the hydraulic transfer pipe 16 is filled with hydraulic oil.
Preferably, the fixing rod 18 is welded on the upper surface of the fixing block 4, wherein the fixing rod 18 is embedded between the plate a and the plate b, and the plate a and the plate b are both welded and fixed with the fixing rod 18.
Preferably, the welding position of the high-position fixing plate 5 and the aircraft wall plate is higher than that of the low-position fixing plate 19, and the high-position fixing plate 5 and the low-position fixing plate 19 have the same structure and are both of a bent plate structure.
Preferably, fixing clamping grooves are formed in the peripheral side faces of the fixing rods 18, the surfaces of the high-position fixing plate 5 and the low-position fixing plate 19 are provided with U-shaped grooves, the high-position fixing plate 5 and the low-position fixing plate 19 are clamped with the fixing clamping grooves through the U-shaped grooves, and when the fixing rods 18, the high-position fixing plate 5 and the low-position fixing plate 19 are actually spliced and installed, the tenon-and-mortise clamping structure is formed jointly by the fixing rods 18.
Preferably, high-order fixed plate 5 and low level fixed plate 19 are crisscross to be arranged, and the high-order fixed plate 5 of a board is relative with the low level fixed plate 19 position of b board, and the low level fixed plate 19 of a board is relative with the high-order fixed plate 5 position of b board simultaneously, under actual operating condition, no matter fixed block 4 lifts or sinks, can both utilize the high-order fixed plate 5 and the low level fixed plate 19 of crisscross block to drive adjacent two aircraft wallboards towards same direction motion, and then strengthen the structural stability between two aircraft wallboards.
In combination with the structure, during production and processing, a plurality of high-position fixing plates 5 and a plurality of low-position fixing plates 19 need to be welded on the connecting surface of the aircraft wall plate in a staggered manner in advance so as to be directly reinforced, spliced and installed in the subsequent process;
in combination with a specific connection structure and working state of the plate a and the plate b, in an actual working state, when the plate a or the plate b is impacted externally, the plate presses the inside of the structure through the connection plate 7 and the supporting column 6, the piezoelectric sensor 10 receives a pressure signal and transmits the pressure signal to the electromagnetic controller 8, and the pressure signal is converted into an electric signal through the electromagnetic controller 8 to control the driving block 9 to enhance the magnetism; meanwhile, the driving block 9 attracts the reinforcing beams 13 at the two ends to slide inwards by utilizing the enhanced magnetic attraction force, and pulls the plate a and the plate b at the same time, so that the connection structure between the plate a and the plate b is in opposition to the compression direction to offset the pressure;
meanwhile, due to the communicating vessel structure formed by the supporting main barrel 2, the supporting auxiliary barrel 3 and the hydraulic transmission pipe 16, when the supporting column 6 slides downwards, the supporting rod 17 slides upwards through the hydraulic transmission principle, and the fixing block 4 is further lifted, and the process interacts with the process of drawing the plate a and the plate b, so that the structure is further reinforced;
meanwhile, the fixing block 4 provides upward support for the joint of two adjacent aircraft wallboards by using the high-position fixing plate 5 and the low-position fixing plate 19 which are clamped in a staggered manner, so that the structural stability between the two aircraft wallboards is further enhanced.
In the description herein, references to the description of "one embodiment," "an example," "a specific example," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
The preferred embodiments of the invention disclosed above are intended to be illustrative only. The preferred embodiments are not intended to be exhaustive or to limit the invention to the precise embodiments disclosed. Obviously, many modifications and variations are possible in light of the above teaching. The embodiments were chosen and described in order to best explain the principles of the invention and the practical application, to thereby enable others skilled in the art to best understand the invention for and utilize the invention. The invention is limited only by the claims and their full scope and equivalents.
Claims (8)
1. A reinforced structure for aircraft panel processing, including coupling mechanism, supporting mechanism and strengthening mechanism, coaction is between aircraft panel a board and the b board of waiting to connect, its characterized in that: the connecting mechanism comprises a driving connecting beam (1), the supporting mechanism comprises a supporting main barrel (2) and a plurality of supporting auxiliary barrels (3), and the reinforcing mechanism comprises a plurality of fixing blocks (4) and a fixing plate group; the driving connecting beam (1) is erected between the plate a and the plate b, and the upper surface of the driving connecting beam (1) is bolted and fixed with the supporting main barrel (2) and the plurality of supporting auxiliary barrels (3); the plate a and the plate b are fixed by welding, and the fixing blocks (4) are fixedly connected to the welding positions of the plate a and the plate b by rivets; the fixing plate group comprises a plurality of high-position fixing plates (5) and a plurality of low-position fixing plates (19), and the surfaces of the plate a and the plate b are welded and fixed with the high-position fixing plates (5) and the low-position fixing plates (19) at the same time;
the supporting main cylinder (2) is of a hollow structure, a supporting column (6) is clamped in the supporting main cylinder in a sliding mode, and a hydraulic cylinder structure is formed between the supporting main cylinder and the supporting main cylinder; the upper end of the supporting column (6) is welded with a connecting plate (7), the connecting plate (7) is fixedly connected with the plate b, and the fixed connection mode comprises rivet connection and welding; the structure of the support auxiliary cylinder (3) is the same as that of the support main cylinder (2), wherein a connecting plate (7) of the support auxiliary cylinder (3) is fixed with an a plate in a welding and rivet connection mode; the length of the plate b is greater than that of the plate a, an included angle exists between the plate a and the plate b, the included angle is smaller than 180 degrees and greater than 0 degree;
an electromagnetic controller (8) is installed on the upper surface of the driving connecting beam (1), a driving block (9) is embedded in the electromagnetic controller (8), and the driving block (9) is an electromagnet; piezoelectric sensors (10) are welded on the bottom surfaces of the main supporting cylinder (2) and the auxiliary supporting cylinder (3), wherein the piezoelectric sensors (10) are electrically connected with the driving block (9); a conduction spring (11) is adhered between the bottom end of the supporting column (6) and the piezoelectric sensor (10);
two connecting cavities (12) are formed in the driving connecting beam (1), and the two connecting cavities (12) are respectively arranged on two opposite sides of the driving block (9); reinforcing beams (13) are slidably clamped in the connecting cavity (12), and the two reinforcing beams (13) respectively extend to the two opposite ends of the driving connecting beam (1) and are respectively welded and extended to the surfaces of the plate a and the plate b;
a driven plate (14) is welded at one end of the reinforcing beam (13), wherein the driven plate (14) is a permanent magnet; when the driving block (9) is electrified, the driving block and the driven plate (14) are magnetically attracted, and a connecting spring (15) is adhered between the driven plate (14) and the driving block (9).
2. The reinforcing structure for aircraft panel processing according to claim 1, characterized in that the supporting primary tube (2) has a larger tube diameter than the supporting secondary tube (3); the upper surface of the driving connecting beam (1) is welded with a plurality of hydraulic transmission pipes (16), and one ends of the hydraulic transmission pipes (16) are respectively welded and communicated with the cylinder walls of the supporting main cylinder (2) and the supporting auxiliary cylinder (3); and a support rod (17) is arranged inside one end of the hydraulic transmission pipe (16), wherein the upper end of the support rod (17) extends to the outside of the hydraulic transmission pipe (16) and is fixedly connected with the lower surface of the fixing block (4) through a rivet.
3. The reinforcing structure for aircraft panel processing according to claim 2, characterized in that the supporting primary barrels (2) and the supporting secondary barrels (3) constitute a hydraulic transmission-based communicating vessel structure with a hydraulic transmission pipe (16) and a supporting rod (17); the body of the hydraulic transmission pipe (16) comprises a straight pipe and a connecting elbow, wherein the straight pipe is connected and communicated with the connecting elbow through a flange; the hydraulic transmission pipe (16) is filled with hydraulic oil.
4. The reinforcing structure for aircraft panel processing according to claim 3, characterized in that a plurality of said hydraulic pressure conduction pipes (16) connected to the supporting secondary drum (3) are staggered with the hydraulic pressure conduction pipes (16) connected to the supporting primary drum (2), and the hydraulic pressure conduction pipes (16) are rigid pipes.
5. The reinforcing structure for aircraft wall panel processing according to claim 4, wherein the fixing rod (18) is welded on the upper surface of the fixing block (4), wherein the fixing rod (18) is embedded between the plate a and the plate b, and the plate a and the plate b are welded and fixed with the fixing rod (18).
6. The reinforcing structure for the processing of the aircraft wall panel as claimed in claim 5, wherein the welding position of the high-position fixing plate (5) and the aircraft wall panel is higher than that of the low-position fixing plate (19), and the high-position fixing plate (5) and the low-position fixing plate (19) are of the same structure and are of a bent plate structure.
7. The reinforcing structure for aircraft panel processing according to claim 6, wherein the fixing rods (18) are provided with fixing slots on the peripheral side, and the surfaces of the high fixing plate (5) and the low fixing plate (19) are provided with U-shaped slots, and the U-shaped slots and the fixing slots are clamped with the fixing slots.
8. The reinforcing structure for aircraft panel processing according to claim 7, wherein the high-level fixing plates (5) and the low-level fixing plates (19) are arranged in a staggered manner, and the high-level fixing plates (5) of the a-plates are opposite to the low-level fixing plates (19) of the b-plates.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211177688.1A CN115258128B (en) | 2022-09-27 | 2022-09-27 | Reinforcing structure for processing aircraft wall panel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211177688.1A CN115258128B (en) | 2022-09-27 | 2022-09-27 | Reinforcing structure for processing aircraft wall panel |
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| CN115258128A CN115258128A (en) | 2022-11-01 |
| CN115258128B true CN115258128B (en) | 2022-12-02 |
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Family Cites Families (21)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
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| US6676080B2 (en) * | 2000-07-19 | 2004-01-13 | Aero Composites, Inc. | Composite airfoil assembly |
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