CN117508630A - Size-adjustable aircraft side aileron assembly type frame - Google Patents
Size-adjustable aircraft side aileron assembly type frame Download PDFInfo
- Publication number
- CN117508630A CN117508630A CN202410010646.1A CN202410010646A CN117508630A CN 117508630 A CN117508630 A CN 117508630A CN 202410010646 A CN202410010646 A CN 202410010646A CN 117508630 A CN117508630 A CN 117508630A
- Authority
- CN
- China
- Prior art keywords
- sliding
- aileron
- fixing
- fixing bolt
- aircraft
- 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.)
- Granted
Links
- 238000000034 method Methods 0.000 claims description 6
- 230000002093 peripheral effect Effects 0.000 claims description 4
- 239000002131 composite material Substances 0.000 description 4
- 238000004519 manufacturing process Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
Landscapes
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Connection Of Plates (AREA)
Abstract
The invention discloses an aircraft side aileron assembly type frame with adjustable size, which comprises the following components: a sliding rail is arranged in the middle of the upper surface of the base, and support columns are respectively arranged at the opposite ends of the sliding rail; the upper end of the support column is slidably provided with a push rod; a plurality of sliding seats matched with the rear edge tips of the ailerons are arranged on the ejector rod in a sliding manner; a plurality of bases corresponding to the sliding seats are slidably arranged on the sliding rail, and arc grooves matched with the arc surfaces of the aileron front beams are formed in the surfaces of the bases; the two opposite sides of the base are respectively hinged with connecting rods; the upper end of the connecting rod is connected with the sliding seat; the side face of the connecting rod is provided with a plurality of fixing bolts used for limiting the skin of the aileron. The base, the connecting rod, the sliding seat and the fixing bolt are matched to form an assembled frame which can be adjusted according to the size of the aircraft aileron, and the aircraft aileron with different sizes can be supported and fixed by adjusting the height of the ejector rod and the positions of the base and the sliding seat; and the connecting rod is provided with a plurality of fixing bolts to fix the skin.
Description
Technical Field
The invention belongs to the technical field of aircraft manufacturing, and particularly relates to an aircraft side aileron assembly type frame with adjustable size.
Background
An aircraft aileron refers to a small movable piece of airfoil mounted outboard of the trailing edge of the wing tip, one on each of the left and right sides. In the flight process of the aircraft, the left aileron and the right aileron deflect towards different directions to form rolling moment to realize the roll of the aircraft. The pilot moves the steering wheel to the left, the left aileron deflects the lift force upwards to decrease, the right aileron presses the lift force downwards to increase, and the aircraft rolls to the left, and vice versa. The aircraft can freely turn in the air through the cooperation of the left aileron and the right aileron with the rudder.
The aircraft aileron is an important part of an aircraft, has a complex structure, not only comprises an upper skin and a lower skin, but also comprises a plurality of ribs, beams and other structures arranged between the upper skin and the lower skin; at present, most of the aircraft ailerons are of composite material structures, and in the manufacturing process of the aircraft ailerons of the composite material structures, all structures such as an upper skin, a lower skin, ribs, beams and the like are generally required to be manufactured first, and then all the structures are assembled.
Most of the existing assembly equipment is of a fixed structure, only can assemble and assemble the single-model aircraft aileron, cannot be adjusted according to the size of the aircraft aileron, and is single in function and poor in universality.
Disclosure of Invention
The invention aims to provide an aircraft side aileron assembly type frame with adjustable size, which is formed by matching a base, a connecting rod, a sliding seat and a fixing bolt, and can be adjusted according to the aircraft aileron size, so that the problem that the assembly type frame cannot be adjusted in size is solved.
In order to solve the technical problems, the invention is realized by the following technical scheme:
the invention relates to an aircraft side aileron assembly type frame with adjustable size, which comprises a base; a sliding rail is arranged in the middle of the upper surface of the base, the sliding rail is arranged in the middle of the upper surface of the base, and the two opposite side surfaces of the sliding rail are respectively provided with a first sliding groove; support columns are respectively arranged at the opposite ends of the sliding rail; the upper end of the support column is slidably provided with a push rod; the opposite two side surfaces of the ejector rod are respectively provided with a third chute; a plurality of sliding seats matched with the rear edge tips of the ailerons are arranged on the ejector rods in a sliding manner; a plurality of bases corresponding to the sliding seats are slidably arranged on the sliding rail, and arc grooves matched with the arc surfaces of the front beams of the ailerons are formed in the surfaces of the bases; the two opposite sides of the base are respectively hinged with a connecting rod; the upper end of the connecting rod is connected with the sliding seat; the base, the connecting rod and the sliding seat form a fixing assembly for limiting and fixing the aileron; the side face of the connecting rod is provided with a plurality of fixing bolts used for limiting the skin of the aileron.
Further, first limit grooves are longitudinally formed in opposite side faces of the support columns, and a first fixing groove is formed in the other side face of the support column.
Further, the opposite end surfaces of the ejector rod are respectively provided with a connecting seat in sliding fit with the support column, and the connecting seats are in a shape like a Chinese character' [; a first limit post is arranged on one side surface of the connecting seat and is in sliding fit with the first limit groove; the other side face of the connecting seat is provided with a first fixing bolt, and the connecting seat is fixed on the supporting column by matching the first fixing bolt with the first fixing groove.
Further, a fourth chute is arranged on the lower end face of the base, and the fourth chute is in sliding fit with the sliding rail; two opposite inner side surfaces of the fourth chute are respectively provided with a sliding block; the sliding block is in sliding fit with the first sliding groove; a second fixing bolt is further arranged on one side of the fourth chute, and the second fixing bolt is matched with the bottom surface of the fourth chute to fix the base; the two opposite outer side surfaces of the base are respectively provided with a hinged support, and the side surfaces of the hinged supports are provided with a hinge hole.
Further, two sides of the lower end of the connecting rod are respectively provided with a hinge post, and the upper end of the connecting rod is an inclined plane; the side surface of the hinge post, which is close to the aileron, is provided with a plurality of first threaded holes in parallel, and the first threaded holes are counter bores; the fixing bolt is matched with the first threaded hole; the end of the fixing bolt is provided with a rubber gasket.
Further, a fifth sliding groove is arranged at the upper end of the sliding seat, and the fifth sliding groove is in sliding fit with the ejector rod; two opposite inner side surfaces of the fifth sliding groove are respectively provided with a second limiting column, and the second limiting columns are in sliding fit with the third sliding groove; a limit baffle is arranged on the upper end face of the fifth chute; two opposite outer side surfaces of the sliding seat are respectively provided with a fixing seat, and a clamping groove is formed in the middle of the fixing seat; the clamping groove is matched with the connecting rod; and two opposite side surfaces of the clamping groove are transversely provided with a rectangular groove, a third fixing bolt is arranged in the rectangular groove, and the third fixing bolt is used for fixing the connecting rod.
Further, the lower end of the sliding seat is provided with a positioning seat, and the lower end surface of the positioning seat is provided with a triangular groove for fixing the rear edge tip of the aileron; the middle of the triangular groove is provided with a mounting groove, a fourth fixing bolt is arranged in the middle of the mounting groove and used for fixing the trailing edge tip of the aileron.
A method of assembling an aircraft side aileron assembly jig of adjustable size comprising the steps of:
step one: adjusting the position of the base on the slide rail according to the size of the aircraft aileron to be assembled;
loosening second fixing bolts on all the bases, aligning the bases at the outermost sides of the two ends with the side surfaces of the aileron of the airplane, uniformly arranging a plurality of bases in the middle between the two bases at the outermost sides, and tightening the second fixing bolts to fix the bases on the sliding rail so as to finish adjustment and fixation of the bases;
step two: the connecting rods at the two ends of the base are spread outwards, and then the fixing bolt is screwed outwards until the rubber gaskets at the end parts of the fixing bolt move into the first threaded holes;
step three: the ejector rod is moved to the top of the support column, and then the first fixing bolt is screwed down to fix the ejector rod; the positions of the sliding seats are adjusted according to the positions of the bases, and the positions of all the sliding seats are adjusted to correspond to the bases one by one; respectively screwing the third fixing bolt and the fourth fixing bolt outwards to the topmost end;
step four: placing the framework of the aircraft aileron to be assembled on the base, and enabling the two side surfaces of the aircraft aileron to be vertical to the side surfaces of the base at the outermost sides of the two ends;
step five: unscrewing the first fixing bolt, and downwards moving the ejector rod until the top of the triangular groove at the lower end of the sliding seat is aligned with the rear edge tip of the aileron of the airplane, and then screwing the first fixing bolt to fix the ejector rod; then, a fourth fixing bolt is screwed inwards to fix the tail edge tip of the aileron of the airplane;
step six: after fixing the framework of the aircraft aileron, fixing the ribs on two side surfaces of the framework of the aircraft aileron, and then attaching the skin to the framework;
step seven: the connecting rods on two sides of all the bases are pulled upwards, the connecting rods are clamped into clamping grooves on the sliding seat, the side surfaces of the connecting rods are attached to the upper end parts of the clamping grooves, and then third fixing bolts are screwed inwards to fix the connecting rods;
step eight: all the fixing bolts are screwed inwards until the rubber gaskets at the end parts of the fixing bolts are attached to the skin, the skin is positioned, and then rivets are punched on the peripheral side of the skin to fix the skin on the framework.
The invention has the following beneficial effects:
according to the invention, the base, the connecting rod, the sliding seat and the fixing bolt are matched to form an assembled frame which can be adjusted according to the size of the aircraft aileron, and the aircraft aileron with different sizes can be supported and fixed by adjusting the height of the ejector rod and the positions of the base and the sliding seat, so that the rib framework is fixed; the connecting rod is provided with a plurality of fixing bolts to fix the skin, so that subsequent riveting is convenient; positioning assembly of the aileron is realized, and assembly efficiency is improved;
the adjustable fixing assembly is arranged to fix the position of the aircraft aileron, so that the position of the fixing assembly is only required to be adjusted when the aircraft aileron with different sizes is produced, and the whole assembly frame is not required to be replaced; the universality of the assembly type frame is improved, and the production cost is reduced.
Of course, it is not necessary for any one product to practice the invention to achieve all of the advantages set forth above at the same time.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings that are needed for the description of the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic illustration of a size adjustable aircraft side aileron assembly frame;
FIG. 2 is an enlarged view of a portion of FIG. 1 at A;
FIG. 3 is a schematic view of the structure of the base;
FIG. 4 is a schematic view of the structure of the ejector pin;
FIG. 5 is a schematic view of the structure of the base and the link;
FIG. 6 is a schematic view of the structure of the base;
FIG. 7 is a schematic view of a structure of a connecting rod;
FIG. 8 is a schematic view of a carriage;
FIG. 9 is a schematic view of a slide carriage in a structure of a view angle;
FIG. 10 is a schematic view of an assembled airframe with an adjustable size aircraft side flap according to the first embodiment;
in the drawings, the list of components represented by the various numbers is as follows:
1. a base; 2. a push rod; 3. a base; 4. a connecting rod; 5. a slide; 6. a fixing bolt; 7. aileron; 101. a slide rail; 1011. a first chute; 102. a support column; 1021. a first limit groove; 1022. a first fixing groove; 201. a third chute; 202. a connecting seat; 203. a first limit post; 204. a first fixing bolt; 301. an arc-shaped groove; 302. a fourth chute; 3021. a slide block; 3022. a second fixing bolt; 303. a hinged support; 3031. a hinge hole; 401. a hinge post; 402. a first threaded hole; 403. an inclined plane; 501. a fifth chute; 5011. the second limit column; 5012. a limit baffle; 502. a fixing seat; 5021. rectangular grooves; 5022. a third fixing bolt; 5023. a clamping groove; 503. a positioning seat; 5031. triangular grooves; 5032. a mounting groove; 5033. and a fourth fixing bolt.
Detailed Description
The aircraft aileron is an important part of an aircraft, has a complex structure, not only comprises an upper skin and a lower skin, but also comprises a plurality of ribs, beams and other structures arranged between the upper skin and the lower skin; at present, most of the aircraft ailerons are of composite material structures, and in the manufacturing process of the aircraft ailerons of the composite material structures, all structures such as an upper skin, a lower skin, ribs, beams and the like are generally required to be manufactured first, and then all the structures are assembled.
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
In the description of the present invention, it should be understood that the terms "open," "upper," "lower," "thickness," "top," "middle," "length," "inner," "peripheral," and the like indicate orientation or positional relationships, merely for convenience in describing the present invention and to simplify the description, and do not indicate or imply that the components or elements referred to 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 FIGS. 1-9, the invention is an adjustable size aircraft side aileron assembly frame, comprising a base 1; a sliding rail 101 is arranged in the middle of the upper surface of the base 1, and supporting columns 102 are respectively arranged at the opposite ends of the sliding rail 101; the upper end of the support column 102 is slidably provided with a push rod 2; the opposite two side surfaces of the ejector rod 2 are respectively provided with a third chute 201; a plurality of sliding seats 5 matched with the rear edge tips of the ailerons are arranged on the ejector rod 2 in a sliding manner; a plurality of bases 3 corresponding to the sliding seats 5 are slidably arranged on the sliding rail 101, and a connecting rod 4 is respectively hinged to two opposite sides of the bases 3; the upper end of the connecting rod 4 is connected with the slide seat 5; the base 3, the connecting rod 4 and the sliding seat 5 form a fixing component for limiting and fixing the aileron 7; the side surface of the connecting rod 4 is provided with a plurality of fixing bolts 6 for limiting the skin of the aileron 7;
as shown in fig. 3, a sliding rail 101 is installed in the middle of the upper surface of the base 1, and two opposite side surfaces of the sliding rail 101 are respectively provided with a first sliding groove 1011; the opposite side surfaces of the support column 102 are longitudinally provided with first limit grooves 1021, and the other side surface of the support column 102 is provided with a first fixing groove 1022; the sliding rail 101 can be used for realizing left and right sliding of the base 3, the position can be adjusted according to the size of the aileron of the airplane, and the supporting column 102 can be used for realizing up and down movement of the ejector rod 2, so that the position can be adjusted according to the size of the aileron of the airplane.
As shown in fig. 4, the opposite end surfaces of the ejector rod 2 are respectively provided with a connecting seat 202, and the connecting seats are in sliding fit with the support columns 102; the connecting seat 202 is shaped like a Chinese character' [; a first limit post 203 is arranged on one side surface of the connecting seat 202, and the first limit post 203 is in sliding fit with a first limit groove 1021; the first fixing bolt 204 is installed to the opposite side of connecting seat 202, and first fixing bolt 204 and first fixed slot 1022 cooperation are fixed connecting seat 202 on support column 102, and when using, outwards unscrew first fixing bolt 204 earlier, then just can remove the position of ejector pin 2, and after the ejector pin 2 accomplished the position adjustment, again with first fixing bolt 204 screw up the fixed realization ejector pin 2.
It will be appreciated that in the present invention, as shown in fig. 5-9, in order to achieve assembly of aircraft ailerons of different sizes, the present invention provides an assembled frame that can adjust the position of the securing assembly according to the size of the aircraft aileron; specifically, the fixing component provided by the invention comprises a base 3, a connecting rod 4 and a sliding seat 5; the surface of the base 3 is provided with an arc-shaped groove 301 matched with the arc surface of the aileron front beam; positioning of the aircraft aileron front Liang Humian can be achieved by arranging the arc-shaped groove 301; a fourth chute 302 is arranged on the lower end surface of the base 3, and the fourth chute 302 is in sliding fit with the sliding rail 101; two opposite inner sides of the fourth chute 302 are respectively provided with a sliding block 3021; the sliding block 3021 is in sliding fit with the first sliding groove 1011; the base 3 is installed by sleeving the base 3 into the slide rail 101, and then fixing the support columns 102 at two ends of the slide rail 101, wherein the support columns 102 are fixed on the base 1 through screws; a second fixing bolt 3022 is further installed on one side of the fourth chute 302, and the second fixing bolt 3022 is installed on a threaded hole on the side surface of the fourth chute 302; the second fixing bolt 3022 is matched with the bottom surface of the fourth chute 302 to fix the base 3; the opposite outer side surfaces of the base 3 are provided with hinge supports 303, and the side surfaces of the hinge supports 303 are provided with hinge holes 3031;
as shown in fig. 7, two sides of the lower end of the connecting rod 4 are respectively provided with a hinge post 401, the side surface of the hinge post 401, which is close to the aileron, is provided with a plurality of first threaded holes 402 side by side, and the first threaded holes 402 are counter bores; the fixing bolt 6 is matched with the first threaded hole 402; the rubber gasket is installed at the end of the fixing bolt 6, the positioning and fixing effects of the skin are improved by arranging the rubber gasket at the end of the fixing bolt 6, and deformation of the skin caused by overlarge pressure applied by the end of the fixing bolt is avoided.
As shown in fig. 8-9, a fifth chute 501 is arranged at the upper end of the sliding seat 5, and the fifth chute 501 is in sliding fit with the ejector rod 2; two opposite inner side surfaces of the fifth chute 501 are respectively provided with a second limiting post 5011, and the second limiting post 5011 is in sliding fit with the third chute 201; two opposite outer side surfaces of the sliding seat 5 are respectively provided with a fixed seat 502, and a clamping groove 5023 is arranged in the middle of the fixed seat 502; the clamping groove 5023 is matched with the connecting rod 4; two opposite side surfaces of the clamping groove 5023 are transversely provided with a rectangular groove 5021, a third fixing bolt 5022 is arranged in the rectangular groove 5021, and the third fixing bolt 5022 is used for fixing the connecting rod 4; after the framework rib is fixed, when the skin needs to be fixed, the connecting rod 4 is clamped into the clamping groove 5023 on the sliding seat 5, the side surface of the connecting rod 4 is tightly attached to the upper end part of the clamping groove 5023, and then the connecting rod 4 is fixed through the third fixing bolt 5022.
It can be also understood that, in the present invention, as shown in fig. 8-9, in order to fix the trailing edge tip of the aileron of the aircraft, the slide 5 provided by the present invention can perform limit fixing on the trailing edge tip of the aileron of the aircraft; specifically, the lower end of the sliding seat 5 provided by the invention is provided with a positioning seat 503, and the lower end surface of the positioning seat 503 is provided with a triangular groove 5031 for fixing the trailing edge tip of the aileron; the middle of the triangular groove 5031 is provided with a mounting groove 5032, the middle of the mounting groove 5032 is provided with a threaded hole, a fourth fixing bolt 5033 is arranged in the threaded hole, the end part of the fourth fixing bolt 5033 is provided with a rubber anti-slip pad, and the fixing of the tail edge tip of the aileron of the aircraft can be realized by screwing the fourth fixing bolt 5033; in the above-mentioned use, the fourth fixing bolt 5033 is first screwed outward to the outermost side, the aircraft aileron trailing edge tip is locked into the triangular groove 5031, and then the fourth fixing bolt 5033 is screwed inward to fix the aircraft aileron trailing edge tip.
Meanwhile, it can be understood that, in order to avoid that the tops of the two connecting rods 4 at two sides of the base 3 are blocked mutually in the moving process of the connecting rod 4 rotating upwards, as shown in fig. 1, the connecting rod 4 cannot be blocked into the clamping groove 5023, in the invention, the upper end of the connecting rod 4 is set to be an inclined plane 403; in the upward rotation process of the connecting rods 4, two opposite connecting rods 4 can not block the connecting rods 4 from being clamped into the clamping grooves 5023, so that the fixing of the skin to be installed on the aileron of the aircraft can be realized.
It can be understood that the end parts of the fixing bolts used in the invention are provided with the rubber anti-slip pads for increasing friction force and improving the fixing effect of the fixing bolts.
Embodiment one:
a method of assembling an aircraft side aileron assembly jig of adjustable size comprising the steps of:
step one: adjusting the position of the base 3 on the slide rail 101 according to the size of the aircraft aileron to be assembled;
loosening the second fixing bolts 3022 on all the bases 3, aligning the bases 3 at the outermost sides of the two ends with the side surfaces of the aileron of the aircraft, uniformly arranging a plurality of bases 3 in the middle between the two bases 3 at the outermost sides, and tightening the second fixing bolts 3022 to fix the bases 3 on the sliding rail 101 so as to finish adjustment and fixation of the bases 3;
step two: as shown in fig. 10, the connecting rods 4 at both ends of the base 3 are spread outward, and then the fixing bolts 6 are screwed outward until the rubber gaskets at the ends of the fixing bolts 6 move into the first screw holes 402;
step three: moving the ejector rod 2 to the top of the support column 102, and then tightening the first fixing bolt 204 to fix the ejector rod 2; the positions of the sliding seats 5 are adjusted according to the positions of the bases 3, and the positions of all the sliding seats 5 are adjusted to correspond to the bases 3 one by one; both the third fixing bolt 5022 and the fourth fixing bolt 5033 are screwed outward to the topmost end, respectively;
step four: placing the framework of the aircraft aileron to be assembled on the base 3, aligning the two side surfaces of the aircraft aileron with the side surfaces of the base 3 at the outermost sides of the two ends, and keeping the aircraft aileron in a vertical state;
step five: unscrewing the first fixing bolt 204, and moving the ejector rod 2 downwards until the top of the triangular groove 5031 at the lower end of the sliding seat 5 is aligned with the trailing edge tip of the aileron of the airplane, and screwing the first fixing bolt 204 to fix the ejector rod 2; then, the fourth fixing bolt 5033 is screwed inwards to fix the tail edge tip of the aileron of the airplane;
step six: after fixing the framework of the aircraft aileron, fixing the ribs on two side surfaces of the framework of the aircraft aileron, and then attaching the skin to the framework;
step seven: the connecting rods 4 on both sides of the base 3 are pulled upwards, the connecting rods 4 are clamped into the clamping grooves 5023 on the sliding seat 5, the side surfaces of the connecting rods 4 are attached to the upper end parts of the clamping grooves 5023, and then the third fixing bolts 5022 are screwed inwards to fix the connecting rods 4;
step eight: all the fixing bolts 6 are screwed inwards until the rubber gaskets at the end parts of the fixing bolts 6 are attached to the skin, the skin is positioned, and then rivets are punched on the peripheral side of the skin to fix the skin on the framework.
Embodiment two:
as a supplementary scheme of the invention, the connecting seat 202 is fixed at two ends of the ejector rod 2 by a screw or welding mode, when in installation, firstly the sliding seat 5 is sleeved into the ejector rod 2, then the connecting seat 202 is fixed at two ends of the ejector rod 2, and the limit baffle 5012 is arranged on the upper end face of the fifth chute 501; the mechanical strength of the sliding seat 5 is improved, the stress strength of the second limit post 5011 is reduced, and the sliding seat 5 is prevented from falling from the ejector rod 2.
In order to improve the positioning precision during assembly, the invention can be provided with a graduated scale on the sliding rail 101 and the ejector rod 2; in actual operation, not only is the position of the base 3 and the position of the sliding seat 5 convenient for the staff to adjust rapidly, but also the dimensional accuracy during assembly is improved.
In the description of the present specification, the descriptions of the terms "one embodiment," "example," "specific example," and the like, 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 present invention. In this specification, schematic representations of the above terms do not necessarily refer to the same embodiments or examples. 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 only to assist in the explanation of the invention. The preferred embodiments are not exhaustive or to limit the invention to the precise form 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 and utilize the invention. The invention is limited only by the claims and the full scope and equivalents thereof.
Claims (8)
1. An aircraft side aileron assembly type frame with adjustable size comprises a base (1); the novel sliding rail is characterized in that a sliding rail (101) is arranged in the middle of the upper surface of the base (1), the sliding rail (101) is arranged in the middle of the upper surface of the base (1), and a first sliding groove (1011) is respectively arranged on two opposite side surfaces of the sliding rail (101); the two opposite ends of the sliding rail (101) are respectively provided with a supporting column (102);
the upper end of the supporting column (102) is slidably provided with a push rod (2); the opposite two side surfaces of the ejector rod (2) are respectively provided with a third chute (201); a plurality of sliding seats (5) matched with the rear edge tips of the ailerons are arranged on the ejector rod (2) in a sliding manner;
a plurality of bases (3) corresponding to the sliding seat (5) are slidably arranged on the sliding rail (101), and arc-shaped grooves (301) matched with the arc surfaces of the aileron front beams are formed in the surfaces of the bases (3);
the two opposite sides of the base (3) are respectively hinged with a connecting rod (4); the upper end of the connecting rod (4) is connected with the sliding seat (5);
the base (3), the connecting rod (4) and the sliding seat (5) form a fixing assembly for limiting and fixing the aileron;
the side face of the connecting rod (4) is provided with a plurality of fixing bolts (6) for limiting the skin of the aileron.
2. The size-adjustable aircraft side aileron assembly frame of claim 1, wherein opposite sides of the support column (102) are each provided with a first limiting slot (1021) longitudinally, and the other side of the support column (102) is provided with a first fixing slot (1022).
3. The size-adjustable aircraft side aileron assembly type frame according to claim 2, wherein the opposite end surfaces of the ejector rod (2) are respectively provided with a connecting seat (202) which is in sliding fit with the support column (102), and the connecting seat (202) is in a shape of a Chinese character' [; a first limit column (203) is arranged on one side surface of the connecting seat (202), and the first limit column (203) is in sliding fit with a first limit groove (1021);
the other side surface of the connecting seat (202) is provided with a first fixing bolt (204), and the first fixing bolt (204) is matched with the first fixing groove (1022) to fix the connecting seat (202) on the supporting column (102).
4. An aircraft side aileron assembly type frame with adjustable size according to claim 1, characterized in that the lower end surface of the base (3) is provided with a fourth chute (302), the fourth chute (302) being in sliding fit with the slide rail (101); two opposite inner side surfaces of the fourth sliding groove (302) are respectively provided with a sliding block (3021); the sliding block (3021) is in sliding fit with the first sliding groove (1011);
a second fixing bolt (3022) is further mounted on one side of the fourth sliding groove (302), and the second fixing bolt (3022) is matched with the bottom surface of the fourth sliding groove (302) to fix the base (3);
two opposite outer side surfaces of the base (3) are respectively provided with a hinge seat (303), and a hinge hole (3031) is formed in the side surface of the hinge seat (303).
5. The size-adjustable aircraft side aileron assembly type frame according to claim 4, wherein two sides of the lower end of the connecting rod (4) are respectively provided with a hinge post (401), and the upper end of the connecting rod (4) is an inclined plane (403);
a plurality of first threaded holes (402) are formed in the side face, close to the aileron, of the hinge post (401), and the first threaded holes (402) are counter bores; the fixing bolt (6) is matched with the first threaded hole (402); a rubber gasket is arranged at the end part of the fixing bolt (6).
6. The size-adjustable aircraft side aileron assembly type frame according to claim 1, characterized in that a fifth sliding groove (501) is arranged at the upper end of the sliding seat (5), and the fifth sliding groove (501) is in sliding fit with the ejector rod (2); two opposite inner side surfaces of the fifth sliding chute (501) are respectively provided with a second limiting column (5011), and the second limiting columns (5011) are in sliding fit with the third sliding chute (201); a limit baffle (5012) is arranged on the upper end face of the fifth chute (501);
two opposite outer side surfaces of the sliding seat (5) are respectively provided with a fixed seat (502), and a clamping groove (5023) is formed in the middle of the fixed seat (502); the clamping groove (5023) is matched with the connecting rod (4);
opposite sides of the clamping groove (5023) are transversely provided with a rectangular groove (5021), a third fixing bolt (5022) is arranged in the rectangular groove (5021), and the third fixing bolt (5022) is used for fixing the connecting rod (4).
7. The size-adjustable aircraft side aileron assembly type frame according to claim 6, characterized in that a positioning seat (503) is arranged at the lower end of the sliding seat (5), and a triangular groove (5031) for fixing the aileron trailing edge tip is arranged at the lower end surface of the positioning seat (503);
the middle of the triangular groove (5031) is provided with a mounting groove (5032), a fourth fixing bolt (5033) is arranged in the middle of the mounting groove (5032), and the fourth fixing bolt (5033) is used for fixing the trailing edge tip of the aileron.
8. A method of assembling an adjustable size aircraft side flap assembly jig according to any of claims 1-7, comprising the steps of:
step one: adjusting the position of the base (3) on the sliding rail (101) according to the size of the aircraft aileron to be assembled;
loosening second fixing bolts (3022) on all the bases (3), aligning the bases (3) at the outermost sides of the two ends with the side surfaces of the aileron of the airplane, uniformly arranging a plurality of bases (3) in the middle between the two bases (3) at the outermost sides, and tightening the second fixing bolts (3022) to fix the bases (3) on the sliding rail (101) so as to finish adjustment and fixation of the bases (3);
step two: the connecting rods (4) at the two ends of the base (3) are spread outwards, and then the fixing bolt (6) is screwed outwards until the rubber gasket at the end part of the fixing bolt (6) moves into the first threaded hole (402);
step three: the ejector rod (2) is moved to the top of the support column (102), and then the first fixing bolt (204) is screwed to fix the ejector rod (2); the positions of the sliding seats (5) are adjusted according to the positions of the bases (3), and the positions of all the sliding seats (5) are adjusted to correspond to the bases (3) one by one; respectively screwing the third fixing bolt (5022) and the fourth fixing bolt (5033) outwards to the top end;
step four: placing the framework of the aircraft aileron to be assembled on the base (3) to enable the two side surfaces of the aircraft aileron to be aligned with the side surfaces of the base (3) at the outermost sides of the two ends, and then enabling the aircraft aileron to be kept in a vertical state;
step five: unscrewing the first fixing bolt (204), and downwards moving the ejector rod (2) until the top of a triangular groove (5031) at the lower end of the sliding seat (5) is aligned with the trailing edge tip of the aileron of the airplane, and then screwing the first fixing bolt (204) to fix the ejector rod (2); then, a fourth fixing bolt (5033) is screwed inwards to fix the tail edge tip of the aileron of the airplane;
step six: after fixing the framework of the aircraft aileron, fixing the ribs on two side surfaces of the framework of the aircraft aileron, and then attaching the skin to the framework;
step seven: the connecting rods (4) on two sides of all the bases (3) are pulled upwards, the connecting rods (4) are clamped into clamping grooves (5023) on the sliding seat (5), the side surfaces of the connecting rods (4) are attached to the upper end parts of the clamping grooves (5023), and then third fixing bolts (5022) are screwed inwards to fix the connecting rods (4);
step eight: all the fixing bolts (6) are screwed inwards until the rubber gaskets at the end parts of the fixing bolts (6) are attached to the skin, the skin is positioned, and then rivets are punched on the peripheral side of the skin to fix the skin on the framework.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410010646.1A CN117508630B (en) | 2024-01-04 | 2024-01-04 | Size-adjustable aircraft side aileron assembly type frame |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410010646.1A CN117508630B (en) | 2024-01-04 | 2024-01-04 | Size-adjustable aircraft side aileron assembly type frame |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN117508630A true CN117508630A (en) | 2024-02-06 |
| CN117508630B CN117508630B (en) | 2024-04-05 |
Family
ID=89748108
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202410010646.1A Active CN117508630B (en) | 2024-01-04 | 2024-01-04 | Size-adjustable aircraft side aileron assembly type frame |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117508630B (en) |
Citations (23)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0875715A (en) * | 1994-09-05 | 1996-03-22 | Fuji Heavy Ind Ltd | Ultrasonic non-destructive inspection device |
| EP1785350A2 (en) * | 2005-11-15 | 2007-05-16 | The Boeing Company | Apparatus for manipulating heavy loads |
| US20130146717A1 (en) * | 2011-12-12 | 2013-06-13 | The Boeing Company | Wing variable camber trailing edge tip |
| CN103302609A (en) * | 2013-06-24 | 2013-09-18 | 中国商用飞机有限责任公司 | Clamping tool for trimming wing leading edge covering |
| US20140157588A1 (en) * | 2010-01-21 | 2014-06-12 | The Boeing Company | High rate pulsing wing assembly line |
| KR20160076077A (en) * | 2014-12-22 | 2016-06-30 | 주식회사 현대케피코 | Jig for measuring 3D |
| CN107352044A (en) * | 2017-07-07 | 2017-11-17 | 浙江大学 | The layout method of large aircraft trailing edge component posture adjusting system |
| US20170355436A1 (en) * | 2016-06-09 | 2017-12-14 | Airbus Operations Limited | Arrangement of ribs at an interface between an outer end of a wing and a moveable wing tip device |
| CN207191477U (en) * | 2017-07-04 | 2018-04-06 | 西安飞机工业（集团）有限责任公司 | A kind of multiple material stringer of aircraft, wall panel skin upset docking equipment |
| CN108928502A (en) * | 2018-07-05 | 2018-12-04 | 南京航空航天大学 | Assemble the tooling of composite material wing box and the method using tooling assembly wing box |
| CN111186593A (en) * | 2020-01-15 | 2020-05-22 | 通航国际（西安）飞机技术有限公司 | Installation method of airplane wing |
| CN211292741U (en) * | 2019-11-15 | 2020-08-18 | 周美艳 | Novel building material detects fixture of device |
| CN213195735U (en) * | 2020-09-04 | 2021-05-14 | 沈阳华天航空机械有限公司 | Perforating device for wing skin |
| CN113277116A (en) * | 2021-07-23 | 2021-08-20 | 沈阳华天航空机械有限公司 | Leading edge flap assembling tool and assembling process thereof |
| CN215318192U (en) * | 2021-04-26 | 2021-12-28 | 深圳市鸿富瀚科技股份有限公司 | Size-adjustable carrier for automatic equipment |
| CN114322776A (en) * | 2022-01-12 | 2022-04-12 | 安徽信息工程学院 | Automatic adjustable image instrument |
| WO2022088206A1 (en) * | 2020-11-02 | 2022-05-05 | 盐城项远环保设备有限公司 | Clamping device for processing vehicle fittings |
| CN114543618A (en) * | 2022-04-26 | 2022-05-27 | 成都市鸿侠科技有限责任公司 | Aircraft panel inspection tool and inspection method |
| CN115071997A (en) * | 2022-06-20 | 2022-09-20 | 成都飞机工业（集团）有限责任公司 | Aircraft wing assembling device and method |
| CN115743517A (en) * | 2022-12-08 | 2023-03-07 | 昆明高新区亨德森高新一中 | Double-wing type second wing |
| CN218751451U (en) * | 2022-12-22 | 2023-03-28 | 九成通用飞机设计制造(大连)有限公司 | Wing main part assembly fixture |
| CN218747396U (en) * | 2022-12-22 | 2023-03-28 | 九成通用飞机设计制造(大连)有限公司 | Aircraft wing flap assembly fixture |
| CN218806619U (en) * | 2022-12-22 | 2023-04-07 | 九成通用飞机设计制造(大连)有限公司 | Aircraft aileron assembly fixture |
-
2024
- 2024-01-04 CN CN202410010646.1A patent/CN117508630B/en active Active
Patent Citations (23)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0875715A (en) * | 1994-09-05 | 1996-03-22 | Fuji Heavy Ind Ltd | Ultrasonic non-destructive inspection device |
| EP1785350A2 (en) * | 2005-11-15 | 2007-05-16 | The Boeing Company | Apparatus for manipulating heavy loads |
| US20140157588A1 (en) * | 2010-01-21 | 2014-06-12 | The Boeing Company | High rate pulsing wing assembly line |
| US20130146717A1 (en) * | 2011-12-12 | 2013-06-13 | The Boeing Company | Wing variable camber trailing edge tip |
| CN103302609A (en) * | 2013-06-24 | 2013-09-18 | 中国商用飞机有限责任公司 | Clamping tool for trimming wing leading edge covering |
| KR20160076077A (en) * | 2014-12-22 | 2016-06-30 | 주식회사 현대케피코 | Jig for measuring 3D |
| US20170355436A1 (en) * | 2016-06-09 | 2017-12-14 | Airbus Operations Limited | Arrangement of ribs at an interface between an outer end of a wing and a moveable wing tip device |
| CN207191477U (en) * | 2017-07-04 | 2018-04-06 | 西安飞机工业（集团）有限责任公司 | A kind of multiple material stringer of aircraft, wall panel skin upset docking equipment |
| CN107352044A (en) * | 2017-07-07 | 2017-11-17 | 浙江大学 | The layout method of large aircraft trailing edge component posture adjusting system |
| CN108928502A (en) * | 2018-07-05 | 2018-12-04 | 南京航空航天大学 | Assemble the tooling of composite material wing box and the method using tooling assembly wing box |
| CN211292741U (en) * | 2019-11-15 | 2020-08-18 | 周美艳 | Novel building material detects fixture of device |
| CN111186593A (en) * | 2020-01-15 | 2020-05-22 | 通航国际（西安）飞机技术有限公司 | Installation method of airplane wing |
| CN213195735U (en) * | 2020-09-04 | 2021-05-14 | 沈阳华天航空机械有限公司 | Perforating device for wing skin |
| WO2022088206A1 (en) * | 2020-11-02 | 2022-05-05 | 盐城项远环保设备有限公司 | Clamping device for processing vehicle fittings |
| CN215318192U (en) * | 2021-04-26 | 2021-12-28 | 深圳市鸿富瀚科技股份有限公司 | Size-adjustable carrier for automatic equipment |
| CN113277116A (en) * | 2021-07-23 | 2021-08-20 | 沈阳华天航空机械有限公司 | Leading edge flap assembling tool and assembling process thereof |
| CN114322776A (en) * | 2022-01-12 | 2022-04-12 | 安徽信息工程学院 | Automatic adjustable image instrument |
| CN114543618A (en) * | 2022-04-26 | 2022-05-27 | 成都市鸿侠科技有限责任公司 | Aircraft panel inspection tool and inspection method |
| CN115071997A (en) * | 2022-06-20 | 2022-09-20 | 成都飞机工业（集团）有限责任公司 | Aircraft wing assembling device and method |
| CN115743517A (en) * | 2022-12-08 | 2023-03-07 | 昆明高新区亨德森高新一中 | Double-wing type second wing |
| CN218751451U (en) * | 2022-12-22 | 2023-03-28 | 九成通用飞机设计制造(大连)有限公司 | Wing main part assembly fixture |
| CN218747396U (en) * | 2022-12-22 | 2023-03-28 | 九成通用飞机设计制造(大连)有限公司 | Aircraft wing flap assembly fixture |
| CN218806619U (en) * | 2022-12-22 | 2023-04-07 | 九成通用飞机设计制造(大连)有限公司 | Aircraft aileron assembly fixture |
Non-Patent Citations (2)
| Title |
|---|
| 商志涛;: "飞机襟副翼悬挂工艺分析", 科技展望, no. 17, 20 June 2016 (2016-06-20), pages 180 * |
| 王巍;俞鸿均;高雪松;穆志国;: "面向自动钻铆机的机身壁板模块化工装设计", 航空制造技术, no. 21, 1 November 2015 (2015-11-01), pages 34 - 38 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN117508630B (en) | 2024-04-05 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109515683B (en) | Deformable wing with variable chord length and curvature | |
| US5046688A (en) | Wing major assembly jig | |
| US7316372B2 (en) | Fuselage spar for aircraft and central sparbox provided with such a spar | |
| CN112693623B (en) | Missile grid rudder hinge moment model claw disc type self-locking positioning structure | |
| CN111186593B (en) | Installation method of airplane wing | |
| CN117508630B (en) | Size-adjustable aircraft side aileron assembly type frame | |
| CN113624606A (en) | Wallboard compression stability test device | |
| CN114872924B (en) | Repair type frame for aircraft structure | |
| US11267553B2 (en) | Aerofoil structures | |
| CN113092000B (en) | Calibration method of sheet type hinge moment balance with external bridge correction | |
| CN216140209U (en) | Unmanned aerial vehicle fuselage assembly fixture | |
| CN112098041B (en) | Rigidity adjusting device of wing low-speed flutter wind tunnel test model | |
| CN218806619U (en) | Aircraft aileron assembly fixture | |
| CN218747396U (en) | Aircraft wing flap assembly fixture | |
| CN216205706U (en) | Large-load composite material missile wing lightweight structure | |
| US20220315232A1 (en) | Aircraft engine pylon having a movable assembly of cowls | |
| CN216361725U (en) | Wallboard compression stability test device | |
| US20210221537A1 (en) | Fairing bond fixture | |
| CN212605896U (en) | Aileron appearance detects frock | |
| CN109927875B (en) | Aircraft frame | |
| CN209972767U (en) | Aircraft frame | |
| CN107933875B (en) | Truss type unmanned aerial vehicle fuselage with light-weight and rigidity adjustable | |
| CN111300318A (en) | Aircraft tail cone frame equipment frock | |
| WO2020216737A1 (en) | Modular aerostruktur assembly | |
| CN219442976U (en) | Pit shaping device for skin of passenger plane body |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |