CN217617880U - Aircraft nose landing gear clamp dabber - Google Patents
Aircraft nose landing gear clamp dabber Download PDFInfo
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- CN217617880U CN217617880U CN202221353784.2U CN202221353784U CN217617880U CN 217617880 U CN217617880 U CN 217617880U CN 202221353784 U CN202221353784 U CN 202221353784U CN 217617880 U CN217617880 U CN 217617880U
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- landing gear
- shaft
- section
- nose landing
- annular groove
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Abstract
The utility model provides an aircraft nose landing gear clamp dabber, the one end of dabber body is provided with the end shaft section, the opposite side of end shaft section is provided with the axle head and keeps off the ring, the opposite side that the ring was kept off to the axle head is first axle collar, the opposite side of first axle collar is the third ring channel, the opposite side of third ring channel is the second axle collar, the opposite side of second axle collar is first shoulder section, the opposite side of first shoulder section is the second shoulder section, the opposite side of second shoulder section is fourth annular groove, the opposite side of fourth annular groove is the third axle collar, the opposite side of third axle collar is fifth annular groove, the opposite side of fifth annular groove is the tooth's socket section, the opposite side of tooth's socket section is end tail shaft section. The mandrel can be used for carrying out coaxial simulation assembly on the linkage seat of the nose landing gear, the steering clamp plate of the nose landing gear and the outer cylinder of the nose landing gear so as to test the coaxial assembly quality of each part; and after the simulation assembly is completed, the drilling process can be performed on the front landing gear linkage seat and the front landing gear outer barrel after the assembly, so that the concentricity of the two hole sites is ensured.
Description
Technical Field
The utility model relates to an aircraft overhauls technical field, concretely relates to aircraft nose landing gear clamp dabber.
Background
The aircraft nose landing gear comprises three groups of parts including a nose landing gear linkage seat, a nose landing gear steering clamp plate and a nose landing gear outer barrel, wherein the three groups of parts are arranged in a coaxial mode and are coaxially assembled on a nose landing gear clamp mandrel, the parts are required to be assembled and inspected in the split machining or assembling and manufacturing process, the drilling process is carried out after the parts are verified and assembled, and the coaxiality and the concentricity of the machined hole positions are guaranteed. At the moment, a corresponding nose landing gear hoop mandrel needs to be designed for the coaxial simulation assembly and verification of the parts, and the follow-up coaxial hole matching processing of the nose landing gear outer barrel and the nose landing gear linkage seat can be guaranteed.
SUMMERY OF THE UTILITY MODEL
The utility model aims to overcome the defects of the prior art and provide a hoop mandrel of a nose landing gear of an airplane, which can be used for carrying out coaxial simulation assembly on a linkage seat of the nose landing gear, a steering hoop plate of the nose landing gear and an outer barrel of the nose landing gear so as to test the coaxial assembly quality of each part; and after the simulation assembly is completed, the drilling process can be performed on the front landing gear linkage seat and the front landing gear outer barrel after the assembly, so that the concentricity of the two hole sites is ensured.
In order to realize the technical characteristics, the purpose of the utility model is realized as follows: the utility model provides an aircraft nose landing gear clamp dabber, it includes the dabber body, the one end of dabber body is provided with the end shaft section, the opposite side of end shaft section is provided with the axle head and keeps off the ring, the opposite side that the ring was kept off to the axle head is first axle collar, the opposite side of first axle collar is the third ring channel, the opposite side of third ring channel is the second axle collar, the opposite side of second axle collar is first shoulder section, the opposite side of first shoulder section is the second shoulder section, the opposite side of second shoulder section is fourth annular groove, the opposite side of fourth annular groove is the third axle collar, the opposite side of third axle collar is fifth annular groove, the opposite side of fifth annular groove is the tooth's socket section, the opposite side of tooth's socket section is end tail shaft section.
The central through hole is processed at the center of the mandrel body, and conical openings are arranged at two ends of the central through hole.
A first annular groove is formed between the end shaft section and the shaft end baffle ring.
And a second annular groove is formed between the shaft end baffle ring and the first shaft ring.
And a sixth annular groove is formed between the tooth groove section and the end tail shaft section.
The cross section of the shaft section where the second shaft ring is located is of an axisymmetric structure and comprises a first arc cylindrical surface located at the position of the symmetric shaft, the other end of the first arc cylindrical surface is in transitional connection with a second arc cylindrical surface through a first transitional arc cylindrical surface, the other end of the second arc cylindrical surface is provided with convex tooth cylindrical surfaces and groove cylindrical surfaces which are alternately arranged, and the tail end of the second arc cylindrical surface is in transitional connection with the first arc cylindrical surface at the position of the other end of the symmetric shaft through a second transitional arc cylindrical surface.
And the radiuses of the second arc cylindrical surface and the groove cylindrical surface are equal.
During assembly, the mandrel body is sequentially assembled with the nose landing gear outer barrel, the nose landing gear steering clamp plate and the nose landing gear linkage seat from the shaft end baffle ring; and the first through hole on the outer barrel of the nose landing gear and the second through hole on the linkage seat of the nose landing gear are concentrically arranged.
The utility model discloses there is following beneficial effect:
the mandrel can be used for carrying out coaxial simulation assembly on the linkage seat of the nose landing gear, the steering clamp plate of the nose landing gear and the outer cylinder of the nose landing gear so as to test the coaxial assembly quality of each part; and after the simulated assembly is completed, the drilling process can be performed on the front landing gear linkage seat and the front landing gear outer barrel after the assembly, so that the concentricity of the two hole sites is ensured.
Drawings
The present invention will be further described with reference to the accompanying drawings and examples.
Fig. 1 is a half sectional view of the present invention.
Fig. 2 isbase:Sub>A view frombase:Sub>A-base:Sub>A of fig. 1 according to the present invention.
Fig. 3 is a state diagram of the present invention when assembled for use.
In the figure: the mandrel comprises a mandrel body 1, a central through hole 2, a conical opening 3, a tip shaft section 4, a first annular groove 5, a shaft end baffle ring 6, a first shaft ring 7, a third annular groove 8, a second shaft ring 9, a first shaft shoulder section 10, a second shaft shoulder section 11, a fourth annular groove 12, a third shaft ring 13, a fifth annular groove 14, a tooth socket section 15, a tip tail shaft section 16, a nose landing gear steering clamp plate 17, a nose landing gear linkage seat 18, a first through hole 19, a second through hole 20 and a nose landing gear outer barrel 21;
a first circular arc cylindrical surface 901, a first transition circular arc cylindrical surface 902, a second circular arc cylindrical surface 903, a convex tooth cylindrical surface 904, a groove cylindrical surface 905 and a second transition circular arc cylindrical surface 906.
Detailed Description
The following describes embodiments of the present invention with reference to the accompanying drawings.
Referring to fig. 1-3, a hoop mandrel for an aircraft nose landing gear comprises a mandrel body 1, wherein one end of the mandrel body 1 is provided with an end shaft section 4, the other side of the end shaft section 4 is provided with a shaft end baffle ring 6, the other side of the shaft end baffle ring 6 is provided with a first shaft ring 7, the other side of the first shaft ring 7 is provided with a third annular groove 8, the other side of the third annular groove 8 is provided with a second shaft ring 9, the other side of the second shaft ring 9 is provided with a first shoulder section 10, the other side of the first shoulder section 10 is provided with a second shoulder section 11, the other side of the second shoulder section 11 is provided with a fourth annular groove 12, the other side of the fourth annular groove 12 is provided with a third shaft ring 13, the other side of the third shaft ring 13 is provided with a fifth annular groove 14, the other side of the fifth annular groove 14 is provided with a tooth space section 15, and the other side of the tooth space section 15 is provided with a tail shaft section 16. The mandrel can be used for carrying out coaxial simulation assembly on the linkage seat of the nose landing gear, the steering clamp plate of the nose landing gear and the outer cylinder of the nose landing gear so as to test the coaxial assembly quality of each part; and after the simulated assembly is completed, the drilling process can be performed on the front landing gear linkage seat and the front landing gear outer barrel after the assembly, so that the concentricity of the two hole sites is ensured.
Further, a central through hole 2 is processed in the center of the mandrel body 1, and two ends of the central through hole 2 are provided with conical openings 3. The conical opening 3 is adopted, so that centering and centering in the machining process of the mandrel body 1 are facilitated, and the machining precision and quality are further ensured.
Furthermore, a first annular groove 5 is arranged between the end shaft section 4 and the shaft end baffle ring 6. The first annular groove 5 functions as a relief groove.
Further, a second annular groove is formed between the shaft end baffle ring 6 and the first shaft ring 7. The second annular groove functions as a relief groove.
Further, a sixth annular groove is arranged between the tooth groove section 15 and the end tail shaft section 16. The sixth annular groove functions as a relief groove.
Further, the cross section of the shaft section where the second collar 9 is located is of an axisymmetric structure, and includes a first arc cylindrical surface 901 located at the position of the symmetry axis, the other end of the first arc cylindrical surface 901 is in transition connection with a second arc cylindrical surface 903 through a first transition arc cylindrical surface 902, the other end of the second arc cylindrical surface 903 is provided with a convex tooth cylindrical surface 904 and a concave groove cylindrical surface 905 which are alternately arranged, and the tail end of the second arc cylindrical surface 903 is in transition connection with the first arc cylindrical surface 901 located at the other end of the symmetry axis through a second transition arc cylindrical surface 906. Subsequent assembly with the nose gear outer barrel 21 is facilitated by the use of the second collar 9 described above.
Further, the radius of the second cylindrical surface 903 is equal to that of the grooved cylindrical surface 905. By using the same radius, the dimensional requirements are met.
Further, during assembly, the mandrel body 1 is sequentially assembled with a nose landing gear outer cylinder 21, a nose landing gear steering clamp plate 17 and a nose landing gear linkage seat 18 from the shaft end baffle ring 6; and the first through hole 19 on the nose landing gear outer cylinder 21 and the second through hole 20 on the nose landing gear linkage seat 18 are arranged concentrically. The coaxial assembly of the three parts to be assembled can be realized by adopting the assembly, and the concentricity of the three parts is ensured. And the concentricity of the first through hole 19 on the subsequent nose gear outer cylinder 21 and the second through hole 20 on the nose gear linkage seat 18 is ensured.
The utility model discloses a working process and principle:
firstly, a nose landing gear outer cylinder 21, a nose landing gear steering clamp plate 17 and a nose landing gear linkage seat 18 which need to be verified and assembled are sequentially assembled to a mandrel body 1, the concentric arrangement of the three is guaranteed, the three are clamped and fixed and integrally clamped on a drilling platform, the relative positions of the nose landing gear outer cylinder 21 and the nose landing gear linkage seat 18 are guaranteed to be fixed, then, the simultaneous processing of a first through hole 19 on the nose landing gear outer cylinder 21 and a second through hole 20 on the nose landing gear linkage seat 18 is completed at one time, and further the concentricity of the first through hole 19 and the second through hole 20 is guaranteed.
Claims (8)
1. The utility model provides an aircraft nose landing gear clamp dabber which characterized in that: the novel mandrel comprises a mandrel body (1), wherein an end shaft section (4) is arranged at one end of the mandrel body (1), a shaft end baffle ring (6) is arranged at the other side of the end shaft section (4), a first shaft ring (7) is arranged at the other side of the shaft end baffle ring (6), a third annular groove (8) is arranged at the other side of the first shaft ring (7), a second shaft ring (9) is arranged at the other side of the third annular groove (8), a first shaft shoulder section (10) is arranged at the other side of the second shaft ring (9), a second shaft shoulder section (11) is arranged at the other side of the first shaft shoulder section (10), a fourth annular groove (12) is arranged at the other side of the fourth annular groove (12), a third shaft ring (13) is arranged at the other side of the third shaft ring (13), a fifth annular groove (14) is arranged at the other side of the fifth annular groove (14), a tooth groove section (15) is arranged at the other side of the tooth groove section (15), and a tail shaft section (16) is arranged at the other side of the end.
2. An aircraft nose landing gear band mandrel as claimed in claim 1, wherein: the central through hole (2) is machined in the center of the mandrel body (1), and conical openings (3) are formed in two ends of the central through hole (2).
3. An aircraft nose landing gear band mandrel as claimed in claim 1, wherein: a first annular groove (5) is arranged between the end shaft section (4) and the shaft end baffle ring (6).
4. An aircraft nose landing gear band mandrel as claimed in claim 1, wherein: and a second annular groove is formed between the shaft end baffle ring (6) and the first shaft ring (7).
5. An aircraft nose landing gear band mandrel as claimed in claim 1, wherein: and a sixth annular groove is formed between the tooth groove section (15) and the end tail shaft section (16).
6. An aircraft nose landing gear band mandrel as claimed in claim 1, wherein: the cross section of the shaft section where the second shaft ring (9) is located is of an axisymmetric structure and comprises a first arc cylindrical surface (901) located at the position of the symmetric axis, the other end of the first arc cylindrical surface (901) is in transitional connection with a second arc cylindrical surface (903) through a first transitional arc cylindrical surface (902), the other end of the second arc cylindrical surface (903) is provided with convex tooth cylindrical surfaces (904) and groove cylindrical surfaces (905) which are alternately arranged, and the tail end of the second arc cylindrical surface (903) is in transitional connection with the first arc cylindrical surface (901) at the position of the other end of the symmetric axis through a second transitional arc cylindrical surface (906).
7. An aircraft nose landing gear clip mandrel as claimed in claim 6, wherein: the second circular arc cylindrical surface (903) and the groove cylindrical surface (905) have the same radius.
8. An aircraft nose landing gear band mandrel as claimed in claim 1, wherein: during assembly, a front landing gear outer barrel (21), a front landing gear steering clamp plate (17) and a front landing gear linkage seat (18) are sequentially assembled on the mandrel body (1) from a shaft end baffle ring (6); and a first through hole (19) on the outer cylinder (21) of the nose landing gear and a second through hole (20) on the linkage seat (18) of the nose landing gear are concentrically arranged.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221353784.2U CN217617880U (en) | 2022-06-01 | 2022-06-01 | Aircraft nose landing gear clamp dabber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221353784.2U CN217617880U (en) | 2022-06-01 | 2022-06-01 | Aircraft nose landing gear clamp dabber |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217617880U true CN217617880U (en) | 2022-10-21 |
Family
ID=83620761
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202221353784.2U Active CN217617880U (en) | 2022-06-01 | 2022-06-01 | Aircraft nose landing gear clamp dabber |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217617880U (en) |
-
2022
- 2022-06-01 CN CN202221353784.2U patent/CN217617880U/en active Active
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