CN212047854U - Wing body butt joint structure with interchangeability - Google Patents
Wing body butt joint structure with interchangeability Download PDFInfo
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- CN212047854U CN212047854U CN202020219246.9U CN202020219246U CN212047854U CN 212047854 U CN212047854 U CN 212047854U CN 202020219246 U CN202020219246 U CN 202020219246U CN 212047854 U CN212047854 U CN 212047854U
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Abstract
The utility model discloses a wing body butt joint structure with interchangeability, which comprises a wing, wherein the wing comprises a wing front beam joint, a wing rear beam joint and a wing box section, and also comprises a first body frame, a second body frame and a bolt group; one side of the wing box section is respectively provided with a wing front beam joint and a wing rear beam joint; the wing front beam joint and the wing rear beam joint are respectively connected with the first fuselage frame and the second fuselage frame through bolt sets. The utility model changes the connection structure of the sheared lug into the connection structure of the butt bolt, thereby realizing the wing installation without the help of a finish machining platform; the dimensional accuracy is high, the surface quality of the wing is stable, and the aerodynamic appearance is good; the utility model discloses can realize that the part assembly changes to the part equipment, can realize that the wing of the different frame numbers of aircraft exchanges, the butt joint of wing body need not the finish machining platform, and the frock is simple, and low cost has better practicality.
Description
Technical Field
The utility model belongs to the technical field of the aircraft structure, concretely relates to wing body butt joint structure with interchangeability.
Background
The wing body butt joint is the most important part of the aircraft structural design, the load of the wing is transmitted to the fuselage through the butt joint part of the wing body, the load is often the high stress area of the aircraft, the safety of the aircraft is directly influenced, meanwhile, the precision of the wing body butt joint directly influences the posture of the wing, and the structural design of the wing body butt joint needs comprehensive structural strength safety and an assembly process. The common wing body butt joint structure usually adopts the lug to be sheared to transfer load, when the wing is installed, the wing is firstly adjusted to a theoretical position, then the wing body butt joint hole is accurately twisted by using a finish machining platform, the cost of the finish machining platform is high, the hole after twisting loses interchangeability, and the mode can bear large load, which is often seen in medium and large-sized airplanes. In the small airplane category, the parachuting recovery airplane has a high proportion, wings are easy to damage in the recovery landing process, interchangeable wing spare parts are often needed, and meanwhile, the importance of cost is often emphasized by the small airplane.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide a wing body butt-joint structural with interchangeability, the utility model discloses can realize that the part assembly changes to the part equipment, can realize that the wing of the different frame rates of aircraft exchanges, and the butt joint of wing body need not the finish machining platform, and the frock is simple, and low cost has better practicality.
The utility model discloses mainly realize through following technical scheme: a wing body butt joint structure with interchangeability comprises a wing, a first body frame, a second body frame and a bolt group, wherein the wing comprises a wing front beam joint, a wing rear beam joint and a wing box section; one side of the wing box section is respectively provided with a wing front beam joint and a wing rear beam joint; the wing front beam joint and the wing rear beam joint are respectively connected with the first fuselage frame and the second fuselage frame through bolt sets.
In order to better realize the utility model, the front wing beam joint and the rear wing beam joint are respectively provided with two symmetrically arranged butt-joint holes, and the first body frame and the second body frame are respectively provided with two butt-joint holes correspondingly; and the front wing beam joint is connected with adjacent connecting holes at the joint of the first fuselage frame and the rear wing beam joint with the second fuselage frame through bolt groups.
In order to better realize the utility model, furthermore, the planeness of the end surfaces of the wing front beam joint, the wing back beam joint, the first machine body frame and the second machine body frame is 0.05, and the parallelism is 0.1; the perpendicularity between the butt joint hole and the end face is 0.05; the horizontal measurement precision of the wing is 1 mm.
In order to better realize the utility model discloses, it is further, bolt group includes bolt, nut and packing ring, bolt, nut are obtained by high strength alloy steel preparation.
In order to better realize the utility model discloses, it is further, bolt group is to drawing the bolt structure, bolt group adopts non-standard gasket to bear high extrusion stress.
In order to better realize the utility model, furthermore, the wing box section is prepared by adopting a resin transfer molding process; the front beam of the wing box section is mechanically connected with the wing front beam joint, and the back beam of the wing box section is mechanically connected with the wing back beam joint.
The horizontal measurement precision of the wing formed by the front wing beam joint, the rear wing beam joint and the wing box section is not more than 1 mm; when the wing horizontal measurement precision is not more than 1.5mm when the wing horizontal measurement precision is installed on the fuselage; the 4 butt-joint holes on the wings and the corresponding 4 holes on the fuselage are coaxial in pairs, so that the interchangeability of the wings is ensured. The wing body can adopt a split bolt form in butt joint, the load on the wing is mainly transferred to the fuselage through a bolt group, and the bolt group can adopt a nonstandard gasket to bear high extrusion stress.
The utility model has the advantages that:
(1) the utility model has simple structure, the precision of the butt joint hole position is ensured by the machine machining precision of the machine body frame, the machine machining precision of the wing joint and the assembly tool, and the butt joint structure is suitable for the wing body butt joint structure of the small unmanned aerial vehicle with the lower grade of 600 Kg; the product has high dimensional precision, good pneumatic appearance, stable internal quality and convenient disassembly and assembly operation; the conversion from component assembly to component assembly can be realized, and the exchange of wings of different shelves of the airplane can be realized.
(2) The utility model changes the connection structure of the sheared lug into the connection structure of the butt bolt, thereby realizing the wing installation without the help of a finish machining platform; the dimensional accuracy is high, the surface quality of the wing is stable, and the aerodynamic appearance is good; the end surfaces of the wing front beam joint, the wing rear beam joint, the first body frame and the second body frame are reinforced, so that the connection strength and rigidity are increased, the wing tip deformation of the wing is reduced, and the flight control is facilitated; 4 the position precision of the pair of connecting holes is high, and the exchange of wings can be realized; only 4 groups of bolts are needed to be operated for dismounting and mounting the wings, and the airplane is convenient and quick to package, transport, transition and recover.
Drawings
Fig. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic diagram of a typical fitting;
FIG. 3 is a diagram showing relative positions of joint holes;
fig. 4 is a schematic structural diagram of the bolt group.
Wherein: 1-wing front beam joint, 2-wing back beam joint, 3-wing box section, 4-first fuselage frame, 5-second fuselage frame, 6-bolt group, 7-bolt, 8-nut and 9-washer.
Detailed Description
Example 1:
a wing body butt-joint structure with interchangeability is shown in figure 1 and comprises a wing, wherein the wing comprises a wing front beam joint 1, a wing rear beam joint 2 and a wing box section 3, and further comprises a first body frame 4, a second body frame 5 and a bolt group 6; one side of the wing box 3 is respectively provided with a wing front beam joint 1 and a wing rear beam joint 2; the wing front beam joint 1 and the wing rear beam joint 2 are respectively connected with a first fuselage frame 4 and a second fuselage frame 5 through bolt sets 6.
The utility model discloses can realize that the part assembly changes to the part equipment, can realize that the wing of the different frame numbers of aircraft exchanges, the butt joint of wing body need not the finish machining platform, and the frock is simple, and low cost has better practicality.
Example 2:
in this embodiment, optimization is performed on the basis of the embodiment, as shown in fig. 2 and 3, the wing front beam joint 1 and the wing rear beam joint 2 are respectively provided with two symmetrically arranged butt-joint holes, and the first fuselage frame 4 and the second fuselage frame 5 are respectively and correspondingly provided with two butt-joint holes; and the front wing beam joint 1 is connected with adjacent connecting holes at the joint of the first fuselage frame 4 and the rear wing beam joint 2 with the second fuselage frame 5 through a bolt group 6. The flatness of the end surfaces of the wing front beam joint 1, the wing rear beam joint 2, the first fuselage frame 4 and the second fuselage frame 5 is 0.05, and the parallelism is 0.1; the perpendicularity between the butt joint hole and the end face is 0.05; the horizontal measurement precision of the wing is 1 mm.
The wing horizontal measurement precision formed by the wing front beam joint 1, the wing rear beam joint 2 and the wing box section 3 is not more than 1 mm; when the wing horizontal measurement precision is not more than 1.5mm when the wing horizontal measurement precision is installed on the fuselage; the 4 butt-joint holes on the wings and the corresponding 4 holes on the fuselage are coaxial in pairs, so that the interchangeability of the wings is ensured.
The utility model changes the connection structure of the sheared lug into the connection structure of the butt bolt, thereby realizing the wing installation without the help of a finish machining platform; the dimensional accuracy is high, the surface quality of the wing is stable, and the aerodynamic appearance is good; the end surfaces of the wing front beam joint 1, the wing rear beam joint 2, the first fuselage frame 4 and the second fuselage frame 5 are reinforced, so that the connection strength and rigidity are increased, the wing tip deformation of the wing is reduced, and the flight control is facilitated; 4 the position precision of the pair of connecting holes is high, and the exchange of wings can be realized; only 4 groups of bolts 7 need to be operated for dismounting and mounting the wings, and the airplane is convenient and quick to package, transport and recover from a transition.
Other parts of this embodiment are the same as embodiment 1, and thus are not described again.
Example 3:
the embodiment is optimized on the basis of embodiment 1 or 2, as shown in fig. 4, the bolt set 6 comprises a bolt 7, a nut 8 and a washer 9, and the bolt 7 and the nut 8 are made of high-strength alloy steel. The wing box 3 is prepared by adopting a resin transfer molding process; the front beam of the wing box 3 is mechanically connected with the wing front beam joint 1, and the rear beam of the wing box 3 is mechanically connected with the wing rear beam joint 2.
The utility model changes the connection structure of the sheared lug into the connection structure of the butt bolt, thereby realizing the wing installation without the help of a finish machining platform; the dimensional accuracy is high, the surface quality of the wing is stable, and the aerodynamic appearance is good; the end surfaces of the wing front beam joint 1, the wing rear beam joint 2, the first fuselage frame 4 and the second fuselage frame 5 are reinforced, so that the connection strength and rigidity are increased, the wing tip deformation of the wing is reduced, and the flight control is facilitated; 4 the position precision of the pair of connecting holes is high, and the exchange of wings can be realized; only 4 groups of bolts 7 need to be operated for dismounting and mounting the wings, and the airplane is convenient and quick to package, transport and recover from a transition.
The rest of this embodiment is the same as embodiment 1 or 2, and therefore, the description thereof is omitted.
Example 4:
the size of a joint in a figure 2 is a typical size, the typical sizes of a front wing beam joint 1, a rear wing beam joint 2, a first fuselage frame 4 and a second fuselage frame 5 are the same, the planeness of an end face is 0.05, the parallelism is 0.1, the perpendicularity of a butt joint hole and the end face is 0.05, and under the combined action of the sizes, the wing can keep the horizontal measurement accuracy of 1 mm.
Fig. 3 shows the relative positions of the butt-joint holes of the wing front beam joint 1 and the wing rear beam joint 2, the relative positions of the butt-joint holes on the first fuselage frame 4 and the second fuselage frame 5 are the same as those in fig. 3, the hole position accuracy of 4 is respectively ensured by a positioning tool, the hole positions of different wings are changed within an allowable range, no wrong holes are generated, and the interchangeability and the installation accuracy are ensured.
Fig. 4 is a schematic diagram of a bolt assembly 6, the bolt assembly 6 is composed of a bolt 7, a nut 8 and a washer 9, and the bolt 7 is made of high-strength alloy steel, the diameter of the bolt 7 is enough to bear the tensile force and the shearing force and cannot be damaged, and the outer diameter and the thickness of the washer 9 are enough to ensure that all parts of the utility model cannot be damaged by extrusion.
The utility model discloses an in the example, full aircraft appearance is the all-wing aircraft overall arrangement, and wing box 3 adopts RTM (resin transfer molding) technology, realizes wing appearance high accuracy, and 3 front beams of wing box connect through mechanical connection with the front beam, and 3 back beams of wing box connect through mechanical connection with the back beam, and the wing assembly goes on special frock. After several planes are assembled in a scientific research stage, the precision of all horizontal measuring points on the wings is within 1 mm. The wings are installed on the machine body without the help of special tools such as a finish machining table, and after the wings are installed, the precision of the horizontal measuring points of the whole machine is within 1.5mm, so that the wing exchange foundation is provided.
The above is only the preferred embodiment of the present invention, not to the limitation of the present invention in any form, all the technical matters of the present invention all fall into the protection scope of the present invention to any simple modification and equivalent change of the above embodiments.
Claims (6)
1. A wing body butt joint structure with interchangeability is characterized by comprising a wing, wherein the wing comprises a wing front beam joint (1), a wing back beam joint (2) and a wing box section (3), and further comprises a first body frame (4), a second body frame (5) and a bolt group (6); one side of the wing box (3) is respectively provided with a wing front beam joint (1) and a wing back beam joint (2); the wing front beam joint (1) and the wing rear beam joint (2) are respectively connected with the first fuselage frame (4) and the second fuselage frame (5) through bolt sets (6).
2. The wing body butt-joint structure with interchangeability according to claim 1, where the wing front spar joint (1) and the wing back spar joint (2) are respectively provided with two symmetrically arranged butt-joint holes, and the first fuselage frame (4) and the second fuselage frame (5) are respectively provided with two butt-joint holes correspondingly; and the front wing beam joint (1) is connected with adjacent connecting holes at the joint of the first fuselage frame (4) and the rear wing beam joint (2) and the second fuselage frame (5) through a bolt group (6).
3. The wing body butt-joint structure with interchangeability according to claim 2, characterised in that the flatness of the end faces of the wing front beam joint (1), the wing back beam joint (2), the first fuselage frame (4), the second fuselage frame (5) is 0.05, and the parallelism is 0.1; the perpendicularity between the butt joint hole and the end face is 0.05; the horizontal measurement precision of the wing is 1 mm.
4. The wing body butt joint structure with interchangeability according to any one of claims 1-3, where the bolt set (6) includes a bolt (7), a nut (8) and a washer (9), and the bolt (7) and the nut (8) are made of high-strength alloy steel.
5. The wing body butt joint structure with interchangeability according to claim 4, characterised in that the bolt set (6) is of a split bolt (7) structure, and the bolt set (6) is subjected to high extrusion stress by using a non-standard gasket.
6. The wing body butt joint structure with interchangeability according to claim 1, c h a r a c t e r i z e d in that the wing box (3) is made by resin transfer moulding; the front beam of the wing box (3) is mechanically connected with the wing front beam joint (1), and the rear beam of the wing box (3) is mechanically connected with the wing rear beam joint (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020219246.9U CN212047854U (en) | 2020-02-27 | 2020-02-27 | Wing body butt joint structure with interchangeability |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020219246.9U CN212047854U (en) | 2020-02-27 | 2020-02-27 | Wing body butt joint structure with interchangeability |
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| CN212047854U true CN212047854U (en) | 2020-12-01 |
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| CN202020219246.9U Active CN212047854U (en) | 2020-02-27 | 2020-02-27 | Wing body butt joint structure with interchangeability |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112572759A (en) * | 2020-12-29 | 2021-03-30 | 北京北航天宇长鹰无人机科技有限公司 | Wing body combines to connect and unmanned aerial vehicle |
| CN112591073A (en) * | 2020-12-23 | 2021-04-02 | 北京北航天宇长鹰无人机科技有限公司 | Wing body combines to connect and unmanned aerial vehicle |
| CN115107986A (en) * | 2022-07-08 | 2022-09-27 | 白鲸航线(北京)科技有限公司 | Wing body connecting machine body reinforcing frame structure |
-
2020
- 2020-02-27 CN CN202020219246.9U patent/CN212047854U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112591073A (en) * | 2020-12-23 | 2021-04-02 | 北京北航天宇长鹰无人机科技有限公司 | Wing body combines to connect and unmanned aerial vehicle |
| CN112591073B (en) * | 2020-12-23 | 2021-09-24 | 北京北航天宇长鹰无人机科技有限公司 | Wing body combines to connect and unmanned aerial vehicle |
| CN112572759A (en) * | 2020-12-29 | 2021-03-30 | 北京北航天宇长鹰无人机科技有限公司 | Wing body combines to connect and unmanned aerial vehicle |
| CN115107986A (en) * | 2022-07-08 | 2022-09-27 | 白鲸航线(北京)科技有限公司 | Wing body connecting machine body reinforcing frame structure |
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