Airplane lug joint structure
Through the design of the new connection device and the spiral oil conduction groove, the problems of poor lubrication effect and insufficient structural strength of the aircraft earpiece joints are solved, and higher lubrication effect and connection reliability are achieved, weight is reduced and flight safety is ensured.
Patent Information
- Application Number
- CN202422393577.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-09-30
- Publication Date
- 2025-07-11
- Estimated Expiration
- 2034-09-30
AI Technical Summary
The existing aircraft earpiece joint structure has problems such as poor lubrication effect, insufficient structural strength, excessive weight and insufficient connection reliability. Especially at the connection parts of the landing frame components, there are problems such as long lubricating oil passages, poor lubrication effect, and easy loosening of nuts, which affect flight safety.
New connection devices are adopted, including new oil injection devices, spiral oil guide grooves and safety devices. The traditional oil injection nozzles are abolished and oil injection is replaced with oil holes. New connection bolts and nuts are designed, spiral oil guide grooves are added, and a double-insurance structure of safety bolts and nuts is set up to improve lubricating paths and connection reliability.
It improves the lubrication effect and structural strength of the earpiece joints, reduces the stress of the parts, ensures the safety and reliability of the connection parts, simplifies the assembly process, reduces weight, and improves service life.
Smart Images
Figure CN223089685U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of aircraft design, in particular to an aircraft lug joint structure. Background Art
[0002] In modern aircraft structural design, the fuselage is mainly connected to aircraft structural components such as landing gears, landing gear components, and wings through joint lugs. The joint lugs mostly adopt a structural form of double lugs paired with single lugs, and are connected through bolts, gaskets, and channel nuts, and split pins are used to prevent the nuts from loosening. To improve the connection life of the joints, especially the connection parts of the landing gear components are mostly moving structures and have lubrication requirements. Currently, lubrication is mostly achieved by adding oil injection nozzles and lubrication channels to the double lugs, so as to lubricate the connecting bolts of the lug joints, reduce the sliding friction force, and improve the service life.
[0003] The currently adopted lubrication structure with an oil injection nozzle added to the double lug joint, in the structural form of local opening of the lug, reduces the structural strength. To ensure the structural strength, the size of the lug needs to be increased, and an oil injection nozzle boss structure is added, which not only increases the weight of the double lug joint parts but also increases the processing difficulty of the parts. And the lubricating oil enters the inside of the lug through the oil injection nozzle on the double lug joint, and flows into the single lug joint through the oil guiding groove on the inner bushing of the lug. The lubrication path is relatively long, and the lubrication effect of the single lug joint part is poor. The lug lubrication can only be along the axis direction of the oil injection hole. For the lug joint part with a narrow space in the axis direction, normal lubrication cannot be carried out. And oil guiding grooves are processed on both the inner and outer sides of the bushing. To ensure the force, the bushing needs a certain thickness, which increases the weight of the bushing parts. The connection structure adopts the structural form of ordinary bolts, gaskets, channel nuts plus split pins for anti-loosening. The nut size is large, which increases the structural weight. If the split pin fails during use, it is easy to cause the nut to loosen or even fall off, endangering flight safety. Summary of the Utility Model
[0004] The utility model discloses an aircraft lug joint structure, aiming to solve the technical problems in the background art.
[0005] To achieve the above object, the utility model adopts the following technical solutions:
[0006] An aircraft lug joint structure includes a double lug joint, a single lug joint, and a new connection device. The double lug joint further includes a double lug body and a double lug joint bushing. The single lug joint includes a single lug body and a single lug bushing. The new connection device includes a new oil injection device, a new connecting bolt, a new connecting nut, and a new insurance device.
[0007] By setting double lug connectors, single lug connectors, and new connection devices, on the basis of the original connector structure, the structural form of the oil injection nozzle in the traditional double lug connector design is changed, and a new structural form of the earpiece connector connection device is innovated. The assembly is quick and convenient, and it can effectively improve the disadvantage of the large weight of the original castle nut.
[0008] In a preferred embodiment, the new oil injection device is designed at one end of the screw head of the new connection bolt. The new oil injection device is composed of an oil injection nozzle body and an oil injection nozzle base. The oil injection nozzle base is composed of an assembled spherical base and a cylindrical section. The position of one end of the assembled spherical base is at a distance L1 from the axis. The assembled spherical base serves as the mounting surface of the oil injection nozzle body. An internal thread body is designed inside the assembled spherical base. The internal thread body is assembled with the external thread of the oil injection nozzle body. An external thread body is designed on the outside of the cylindrical section. The new connection bolt is provided with an internal thread, and the external thread body is assembled with the internal thread. The inside of the cylindrical section is designed as a cavity.
[0009] By setting the new connection bolt, by canceling the structural form of the oil injection nozzle designed on the original double lugs and adopting the method of oil hole injection, the integrity of the double lug connector is maintained, the stress level of the parts is reduced, and the service life of the double lugs is improved.
[0010] In a preferred embodiment, the double lug connector bushing is composed of a shoulder and a ring. A first spiral oil guiding groove is designed inside the ring.
[0011] By setting the first spiral oil guiding groove, by changing the oil guiding grooves originally designed both inside and outside the double lug connector bushing to a first spiral oil guiding groove designed inside the double lug connector bushing, on the basis of improving the strength of the parts, it ensures more sufficient lubrication of the earpiece connector, and the first spiral oil guiding groove achieves the purpose of effectively storing lubricating oil.
[0012] In a preferred embodiment, the single lug bushing is a ring structure, and a second spiral oil guiding groove is designed inside the single lug bushing.
[0013] By setting the second spiral oil guiding groove, the lubrication method is changed, and the problem of poor lubrication effect of the original single lug connector is fundamentally solved.
[0014] In a preferred embodiment, the new connection bolt is composed of a cylindrical lubrication channel, a first double lug lubrication hole, a single lug lubrication hole, a second double lug lubrication hole, a safety bolt hole, and a bolt head. A cylindrical lubrication channel is designed inside the new connection bolt. An internal thread is designed at the top of the cylindrical lubrication channel. The assembled spherical base is provided with an external thread body. The first double lug lubrication hole and the second double lug lubrication hole are the lubrication holes for the left and right double lug connector bushings of the double lug connector. The single lug lubrication hole is the lubrication hole on the single lug bushing.
[0015] By setting a new connecting bolt, the lubrication passage can be made simple, reliable and have good lubrication effect.
[0016] In a preferred embodiment, three lubricating holes communicating up and down are respectively designed inside the cylindrical lubrication passage. The new safety device is composed of a safety bolt, a safety gasket, a safety nut and an opening pin, and the new safety device is installed on the planar structure.
[0017] By setting the new safety device, at the assembly part of the safety bolt and the safety nut, the opening pin plays a role in preventing the safety bolt and the safety nut from loosening, thereby realizing a double-safety method for the structure and improving the safety and reliability of the connection part.
[0018] In a preferred embodiment, the new connecting nut is composed of a circular ring base, nut lugs and nut lug holes. The thickness L2 of the circular ring base takes the upper deviation according to the tolerance accumulation. The outer side of the nut lug is a planar structure, the inner side of the nut lug is a cylindrical surface structure, and the diameter φ2 of the nut lug is equal to the size of the new connecting bolt φ1.
[0019] By setting the new connecting nut, the disadvantages of the original grooved nut with large size and heavy weight can be effectively improved.
[0020] In a preferred embodiment, two parallel planes are designed on the bolt head. The bolt rod part of the new connecting bolt is a smooth cylindrical structure, and a safety bolt hole is designed at the tail of the new connecting bolt.
[0021] The present utility model discloses an aircraft lug joint structure, which has the following beneficial effects.
[0022] As can be seen from the above, through the structural form of the new lug joint connecting device of the present utility model, the assembly is quick and convenient, and the disadvantage of the large weight of the original grooved nut can be effectively improved. The new connecting device designs a set of backup anti-loosening devices to realize the double insurance of the structural connection anti-loosening, and improves the technical effects of the safety and reliability of the connection part. Brief Description of the Drawings
[0023] Figure 1 It is an installation structure diagram of an aircraft lug joint structure proposed by the present utility model.
[0024] Figure 2 It is an axonometric view of the new double lug joint and the bushing of an aircraft lug joint structure proposed by the present utility model.
[0025] Figure 3 It is another axonometric view of the new single lug joint and the bushing of an aircraft lug joint structure proposed by the present utility model.
[0026] Figure 4A three-dimensional view of a new connecting device for an aircraft lug joint structure proposed by the present utility model.
[0027] Figure 5 A three-dimensional view of a new oil injection device for an aircraft lug joint structure proposed by the present utility model.
[0028] Figure 6 A schematic diagram of a new connecting bolt for an aircraft lug joint structure proposed by the present utility model.
[0029] Figure 7 A schematic diagram of a new connecting nut for an aircraft lug joint structure proposed by the present utility model.
[0030] Figure 8 A schematic diagram of a new locking device for an aircraft lug joint structure proposed by the present utility model.
[0031] In the attached drawings: 400, double lug joint; 410, double lug body; 420, double lug joint bushing; 421, first spiral oil guiding groove; 422, shoulder; 423, ring.
[0032] 500, single lug joint; 510, single lug body; 520, single lug bushing; 521, second spiral oil guiding groove.
[0033] 600, new connecting device; 610, new oil injection device; 611, oil injection nozzle body; 612, oil injection nozzle base; 613, assembled spherical base; 614, cylindrical section; 615, external threaded body; 616, internal thread; 620, new connecting bolt; 621, cylindrical lubrication channel; 622, internal thread; 623, first double lug lubrication hole; 624, single lug lubrication hole; 625, second double lug lubrication hole; 626, locking bolt hole; 627, bolt head; 628, plane.
[0034] 630, new connecting nut; 631, ring base; 632, nut lug; 633, nut lug hole; 634, planar structure.
[0035] 640, new locking device; 641, locking bolt; 642, locking washer; 643, locking nut; 644, split pin. Detailed implementation manners
[0036] Next, the technical solutions in the embodiments of the present utility model will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present utility model. Obviously, the described embodiments are only a part of the embodiments of the present utility model, rather than all the embodiments.
[0037] In the description of the present utility model, it should be understood that the orientation or positional relationship indicated by the terms "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present utility model and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation to the present utility model.
[0038] Referring to Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 5 , Figure 6 , Figure 7 and Figure 8 , an aircraft lug joint structure includes a double lug joint 400, a single lug joint 500, and a new connecting device 600. The double lug joint 400 includes a double lug body 410 and a double lug joint bushing 420. The single lug joint 500 includes a single lug body 510 and a single lug bushing 520. The new connecting device 600 includes a new oil injection device 610, a new connecting bolt 620, a new connecting nut 630, and a new safety device 640.
[0039] In this solution, when using the aircraft lug joint structure, by setting the double lug joint 400, the single lug joint 500, and the new connecting device 600, on the basis of the original joint structure, the structural form of the oil injection nozzle of the traditional double lug joint is changed, and the structural form of the new lug joint connecting device is innovated. The assembly is quick and convenient, and the disadvantage of the large weight of the original castle nut can be effectively improved.
[0040] Among them, referring to Figure 5 and Figure 6 , in a preferred embodiment, the new oil injection device 610 is designed at one end of the screw head of the new connecting bolt 620. The new oil injection device 610 is composed of an oil injection nozzle body 611 and an oil injection nozzle base 612. The oil injection nozzle base 612 is composed of an assembled spherical base 613 and a cylindrical section 614. The position of one end of the assembled spherical base 613 from the axis L1 serves as the installation surface of the oil injection nozzle body 611. An internal thread body 616 is designed inside the assembled spherical base 613. The internal thread body 616 is assembled with the external thread of the oil injection nozzle body 611. An external thread body 615 is designed on the outside of the cylindrical section 614. The new connecting bolt 620 is provided with an internal thread 622. The external thread body 615 is assembled with the internal thread 622. The inside of the cylindrical section 614 is designed as a cavity. By setting the new connecting bolt 620, by canceling the structural form of the oil injection nozzle designed on the original double lugs and adopting the method of oil hole injection, the integrity of the double lug joint 400 is maintained, the stress level of the parts is reduced, and the service life of the double lugs is improved.
[0041] Further, referring to Figure 1 and Figure 2 , in a preferred embodiment, the double-earpiece joint bushing 420 is composed of a shoulder 422 and a circular ring 423. A first spiral oil guide groove 421 is designed on the inner side of the circular ring 423. By setting the first spiral oil guide groove 421, the oil guide grooves originally designed on both the inside and outside of the double-earpiece joint bushing 420 are changed to the first spiral oil guide groove 421 designed on the inner side of the double-earpiece joint bushing 420. On the basis of improving the strength of the part, it ensures more sufficient lubrication of the earpiece joint, and the first spiral oil guide groove 421 achieves the purpose of effectively storing lubricating oil.
[0042] Among them, referring to Figure 1 and Figure 3 , in a preferred embodiment, the single-earpiece bushing 520 is a circular ring structure. A second spiral oil guide groove 521 is designed on the inner side of the single-earpiece bushing 520. By setting the second spiral oil guide groove 521, the lubrication method is changed, and the problem of poor lubrication effect of the original single-earpiece joint 500 is fundamentally solved.
[0043] Further, referring to Figure 1 and Figure 6 , in a preferred embodiment, the new connecting bolt 620 is composed of a cylindrical lubrication channel 621, a first double-earpiece lubrication hole 623, a single-earpiece lubrication hole 624, a second double-earpiece lubrication hole 625, a safety bolt hole 626, and a bolt head 627. A cylindrical lubrication channel 621 is designed on the inner side of the new connecting bolt 620. An internal thread 622 is designed at the top of the cylindrical lubrication channel 621. The assembled spherical base 613 is provided with an external threaded body 615. The first double-earpiece lubrication hole 623 and the second double-earpiece lubrication hole 625 are lubrication holes for the left and right double-earpiece joint bushings 420 of the double-earpiece joint 400, and the single-earpiece lubrication hole 624 is a lubrication hole on the single-earpiece bushing 520. By setting the new connecting bolt 620, the lubrication path can be simple, reliable, and have a good lubrication effect.
[0044] Among them, referring to Figure 6 and Figure 8 , in a preferred embodiment, three vertically connected lubrication holes are respectively designed inside the cylindrical lubrication channel 621. The new safety device 640 is composed of a safety bolt 641, a safety gasket 642, a safety nut 643, and a split pin 644. The new safety device 640 is installed on the planar structure 634. By setting the new safety device 640, at the assembly position of the safety bolt 641 and the safety nut 643, the split pin 644 plays a role in preventing the loosening of the safety bolt 641 and the safety nut 643, thereby realizing a double-safety method for the structure and improving the safety and reliability of the connection part.
[0045] Furthermore, referring to Figure 4 and Figure 7 , in a preferred embodiment, the new connecting nut 630 is composed of a circular base 631, nut lugs 632, and nut lug holes 633. The thickness L2 of the circular base 631 takes the upper deviation according to the tolerance accumulation. The outer side of the nut lug 632 is a planar structure 634, and the inner side is a cylindrical surface structure. The diameter φ2 of the nut lug 632 is equal to the size of φ1 of the new connecting bolt 620. By setting the new connecting nut 630, the disadvantages of the original grooved nut, such as large size and heavy weight, can be effectively improved.
[0046] Working principle: During assembly, first ensure that the safety bolt hole 626 of the new connecting bolt 620 is coaxial with the nut lug hole 633 of the new connecting nut 630. Then, insert the safety bolt 641 from one side of the planar structure 634 of the new connecting nut 630, and assemble the safety gasket 642 and safety nut 643 with the threaded part of the safety bolt 641 from the other end of the planar structure 634. At the assembly of the safety bolt 641 and the safety nut 643, the split pin 644 is used to prevent the loosening of the safety bolt 641 and the safety nut 643, thus realizing the double - insurance method of the structure and improving the safety and reliability of the connection part;
[0047] During oil injection, the original structural form of designing an oil injection nozzle on the double lugs is cancelled, and the oil injection method is changed to inject oil through the internal oil hole of the new connecting bolt 620, maintaining the integrity of the double - lug joint 400, reducing the part stress level, increasing the service life of the double lugs, and changing the oil guide grooves originally designed both inside and outside the double - lug joint bushing 420 to a first spiral oil guide groove 421 designed on the inner side of the double - lug joint bushing 420. On the basis of improving the part strength, it ensures more sufficient lubrication of the lug joint, and the first spiral oil guide groove 421 achieves the purpose of effectively storing lubricating oil, enabling the lubricating oil to directly enter the first spiral oil guide groove 421 and the second spiral oil guide groove 521 on the inner sides of the double - lug joint bushing 420 and the single - lug bushing 520 of the double - lug joint 400 and the single - lug joint 500 through the oil hole at the end of the new connecting bolt 620. The lubrication path is simple and reliable, and the lubrication effect is good;
[0048] Next, by adopting the structural form of adding an oil injection nozzle base 612, the lubrication direction can be adjusted according to the actual situation of the lug space, achieving the purpose of convenient operation of the lubrication work at the aircraft connection part. By adopting the new structural form of the earpiece connection device, a new connecting nut 630 with lugs is innovated, which can effectively improve the disadvantages of the original grooved nut, such as large size and heavy weight.
[0049] The above are only the preferred specific embodiments of the present utility model, but the protection scope of the present utility model is not limited thereto. The substitution may be the substitution of part of the structure, device, method steps, or a complete technical solution. Any equivalent substitution or change made according to the technical solution of the present utility model and its inventive concept shall be covered within the protection scope of the present utility model.
Claims
1. An aircraft lug joint structure, comprising a double lug joint (400), a single lug joint (500), and a new connecting device (600), characterized in that, Further included are; The double-ear piece joint (400) includes a double-ear piece body (410) and a double-ear piece joint bushing (420), the single-ear piece joint (500) includes a single-ear piece body (510) and a single-ear piece bushing (520), and the new connecting device (600) includes a new oil injection device (610), a new connecting bolt (620), a new connecting nut (630), and a new safety device (640); The new oil injection device (610) is designed at one end of the screw head of the new connecting bolt (620). The new oil injection device (610) is composed of an oil injection nozzle body (611) and an oil injection nozzle base (612). The oil injection nozzle base (612) is composed of an assembled spherical base (613) and a cylindrical section (614). The position of one end of the assembled spherical base (613) from the axis L1 serves as the mounting surface of the oil injection nozzle body (611). An internal threaded body (616) is designed inside the assembled spherical base (613), and the internal threaded body (616) is assembled with the external thread of the oil injection nozzle body (611). An external threaded body (615) is designed on the outer side of the cylindrical section (614). The new connecting bolt (620) is provided with an internal thread (622), and the external threaded body (615) is assembled with the internal thread (622). The inner side of the cylindrical section (614) is designed as a cavity.
2. The structure of an aircraft lug joint according to claim 1, wherein, The double-ear piece joint bushing (420) is composed of a shoulder (422) and a ring (423). A first spiral oil guiding groove (421) is designed inside the ring (423).
3. The aircraft lug joint structure according to claim 1, characterized in that, The single-ear piece bushing (520) is a ring structure. A second spiral oil guiding groove (521) is designed inside the single-ear piece bushing (520).
4. The aircraft lug joint structure according to claim 3, characterized in that, The new connecting bolt (620) is composed of a cylindrical lubrication channel (621), a first double-ear piece lubrication hole (623), a single-ear piece lubrication hole (624), a second double-ear piece lubrication hole (625), a safety bolt hole (626), and a bolt head (627). An inner side of the new connecting bolt (620) is designed with a cylindrical lubrication channel (621). An internal thread (622) is designed at the top of the cylindrical lubrication channel (621). The assembled spherical base (613) is provided with an external threaded body (615). The first double-ear piece lubrication hole (623) and the second double-ear piece lubrication hole (625) are lubrication holes for the left and right double-ear piece joint bushings (420) of the double-ear piece joint (400), and the single-ear piece lubrication hole (624) is a lubrication hole on the single-ear piece bushing (520).
5. The structure of an aircraft lug joint according to claim 4, characterized in that, Three vertically connected lubrication holes are respectively designed inside the cylindrical lubrication channel (621).
6. The structure of an aircraft lug joint according to claim 5, characterized in that, Two parallel planes (628) are designed on the bolt head (627). The bolt rod part of the new connecting bolt (620) is a smooth cylindrical structure. The new connecting bolt (620) is designed with a safety bolt hole (626) at the tail.
7. The aircraft lug joint structure according to claim 1, wherein The new connecting nut (630) consists of an annular base (631), nut lugs (632), and nut lug holes (633). The thickness L2 of the annular base (631) takes the upper deviation according to the cumulative tolerance. The outer side of the nut lugs (632) is a planar structure (634), the inner side of the nut lugs (632) is a cylindrical surface structure, and the diameter φ2 of the nut lugs (632) is equal to the size of φ1 of the new connecting bolt (620).
8. The aircraft lug joint structure according to claim 7, characterized in that, The new safety device (640) consists of a safety bolt (641), a safety gasket (642), a safety nut (643), and a split pin (644). The new safety device (640) is installed on the planar structure (634).