CN212710044U - Universal aircraft engine fairing suspension tool - Google Patents
Universal aircraft engine fairing suspension tool Download PDFInfo
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- CN212710044U CN212710044U CN202021447302.0U CN202021447302U CN212710044U CN 212710044 U CN212710044 U CN 212710044U CN 202021447302 U CN202021447302 U CN 202021447302U CN 212710044 U CN212710044 U CN 212710044U
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- rod
- fairing
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- base
- hanging
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Abstract
The utility model discloses a general aircraft engine radome fairing hangs frock, including supporting the base, setting up in the truckle of the bottom of supporting the base, be used for hanging the first pole that hangs of first radome fairing and be used for supporting the first bracing piece of first radome fairing, first pole and the first bracing piece that hangs set up on supporting the base. The utility model discloses a general aircraft engine radome fairing hangs frock can realize hanging and transporting of general aircraft engine radome fairing, the human cost when general aircraft engine radome fairing that can significantly reduce circulates between each station.
Description
Technical Field
The utility model belongs to the technical field of general aviation auxiliary assembly, specifically speaking, the utility model relates to a general aircraft engine radome fairing hangs frock.
Background
With the gradual release of low-altitude airspace and the intensive development of the relevant interest policy of navigation in China, the navigation industry in China has developed in an explosive manner. The airplane general assembly is a technical work which has high technical difficulty, wide subject related and high comprehensive integration level, determines the final quality, the manufacturing cost and the period of the airplane, is a huge obstacle for restricting the rapid development of the airplane in China, and is the development of various tools as a major bottleneck for restricting the technical development of the airplane general assembly. Also, maintenance of the general purpose aircraft is also affected by delays in tooling development.
A fairing on one side of a general airplane is generally divided into A, B, C parts, the fairing occupies a large space in a natural storage state (placed on the ground near the airplane or on a table) due to large size and heavy weight of the fairing, the fairing of one airplane needs 3 persons to transport when each station is circulated, and the fairing is easily damaged by repeated disassembly and placement in the assembling and maintaining processes. In order to solve the problem, engineers generally choose to store in a suspension room, but the problem of difficulty in transportation cannot be solved, and the prior art lacks a tool capable of suspending an aircraft engine fairing.
SUMMERY OF THE UTILITY MODEL
The utility model discloses aim at solving one of the technical problem that exists among the prior art at least. Therefore, the utility model provides a general aircraft engine radome fairing hangs frock, the purpose is that the suspension and the transportation of general aircraft engine radome fairing are realized.
In order to realize the purpose, the utility model discloses the technical scheme who takes does: general aircraft engine radome fairing hangs frock, including supporting the base, set up in the truckle of supporting the bottom of base, be used for hanging the first pole of hanging of first radome fairing and be used for supporting the first bracing piece of first radome fairing, first pole and the first bracing piece of hanging set up on supporting the base.
The general aircraft engine fairing hangs frock still including set up in support base on first hang the dead lever and set up in the first stationary blade that hangs on the dead lever, first hang the dead lever and be located the first top that hangs the pole, first hang the pole and be located the top of first bracing piece.
The end parts of the first suspension rod and the first supporting rod are provided with first protective caps, the first fixing piece is provided with a second protective cap, and the first protective cap and the second protective cap are made of soft materials.
The general aircraft engine fairing hangs frock still include the second pole of hanging that is used for hanging the second fairing and the second bracing piece that is used for supporting the second fairing, the second hangs the pole and the second bracing piece sets up on supporting the base.
The general aircraft engine fairing hangs frock still including set up in support base on the second hang the dead lever and set up in the second stationary blade that hangs the dead lever, the second hangs the dead lever and is located the second hangs the top of pole, the second hangs the pole and is located the top of second bracing piece.
The end parts of the second suspension rod and the second supporting rod are provided with first protective caps, the second fixing piece is provided with a second protective cap, and the first protective cap and the second protective cap are made of soft materials.
The general aircraft engine fairing hangs frock still include the third pole of hanging that is used for hanging the third fairing and the third bracing piece that is used for supporting the third fairing, the second hangs the pole and the third bracing piece sets up on supporting the base.
And the end parts of the third suspension rod and the third supporting rod are provided with first protective caps which are made of soft materials.
The supporting base comprises a vertically arranged bearing rod and a base cross beam connected with the lower end of the bearing rod, the trundles are arranged on the base cross beam, and the base cross beam is provided with a plurality of trundles.
The support base further comprises base reinforcing plates connected with all the base cross beams.
The utility model discloses a general aircraft engine radome fairing hangs frock can realize hanging and transporting of general aircraft engine radome fairing, the human cost when general aircraft engine radome fairing that can significantly reduce circulates between each station.
Drawings
The description includes the following figures, the contents shown are respectively:
FIG. 1 is a schematic structural view of a universal aircraft engine fairing hanging tool of the present invention;
FIG. 2 is a schematic structural view of the universal aircraft engine cowling suspension fixture of the present invention at another angle;
FIG. 3 is a top view of the universal aircraft engine cowling suspension fixture of the present invention;
labeled as: 1. a load-bearing bar; 2. a base beam; 3. a base reinforcing plate; 4. a caster wheel; 5. a first support bar; 6. a first suspension bar; 7. a first hanging fixed rod; 8. a first fixing sheet; 9. a second support bar; 10. a second suspension bar; 11. a second suspension fixing rod; 12. a second fixing sheet; 13. a third support bar; 14. a third suspension bar; 15. a first protective cap; 16. a second protective cap.
Detailed Description
The following detailed description of the embodiments of the present invention will be given with reference to the accompanying drawings, for the purpose of helping those skilled in the art to understand more completely, accurately and deeply the conception and technical solution of the present invention, and to facilitate its implementation.
It should be noted that, in the following embodiments, the terms "first", "second" and "third" do not denote absolute differences in structure and/or function, nor do they denote a sequential order of execution, but rather are used for convenience of description.
As shown in fig. 1 to 3, the utility model provides a general aircraft engine fairing hangs frock, including supporting the base, setting up in the truckle 4 of the bottom of supporting the base, be used for hanging the first pole 6 that hangs of first fairing and be used for supporting the first bracing piece 5 of first fairing, first pole 6 and the first bracing piece 5 that hangs set up on supporting the base.
Specifically speaking, as shown in fig. 1 to 3, the support base includes the bearing bar 1 of vertical setting and the base crossbeam 2 of being connected with the lower extreme of bearing bar 1, truckle 4 sets up on base crossbeam 2, base crossbeam 2 sets up a plurality ofly, and all crossbeams are along circumference evenly distributed, each crossbeam is the level setting, the length direction of crossbeam is mutually perpendicular with the length direction of bearing bar 1, the lower extreme of bearing bar 1 and the tip fixed connection of crossbeam, all crossbeams are radial distribution, the support body stability of formation is good, and structural strength is high. The first suspension rod 6 and the first support rod 5 are fixedly connected with the bearing rod 1, the first suspension rod 6 and the first support rod 5 are sequentially arranged along the length direction of the bearing rod 1, the first suspension rod 6 and the first support rod 5 extend out towards the outer side of the bearing rod 1, and the shapes of the first suspension rod 6 and the first support rod 5 are matched with the shape of the first fairing.
As shown in fig. 1 to 3, in the present embodiment, three cross beams are provided, and an included angle between two adjacent cross beams in the length direction is 120 degrees. All set up a truckle 4 on each crossbeam, truckle 4 is the universal wheel.
As shown in fig. 1 to 3, the utility model discloses a general aircraft engine fairing hangs frock is still including setting up the first dead lever 7 that hangs on supporting the base and setting up the first stationary blade 8 on the first dead lever 7 that hangs, and first dead lever 7 that hangs is located the first top that hangs pole 6, and the first top that hangs pole 6 and is located first bracing piece 5 that hangs. The first fixing piece 8 is used for fixing the fairing by matching with the supporting rod below, so that the fairing is fixed more firmly. One end of the first hanging fixing rod 7 in the length direction is fixedly connected with the bearing rod 1, and the first fixing piece 8 is fixedly connected with the other end of the first hanging fixing rod 7 in the length direction.
As shown in fig. 1 to 3, the first support bar 5 has a cross-shaped structure, and the first hanging bar 6 has a Y-shaped structure. The first hanging rod 6 and the first supporting rod 5 are provided with a first protective cap 15 at the end part, a second protective cap 16 is arranged on the first fixing piece 8, and the first protective cap 15 and the second protective cap 16 are made of soft materials. The first suspension rod 6 is provided with three end parts, one end part of the first suspension rod 6 is fixedly connected with the bearing rod 1, the other two end parts of the first suspension rod 6 are wrapped with first protection caps 15, and the first suspension rod 6 is made of metal materials. First bracing piece 5 has four tip, one of them tip and the 1 fixed connection of bearing bar of first bracing piece 5, all wraps up first protective cap 15 on the other three tip of first bracing piece 5, and first bracing piece 5 adopts the metal material to make. The first protective cap 15 prevents the first suspension bar 6, the first support bar 5 from directly contacting the first fairing, avoiding damage to the fairing. The second protective cap 16 wraps the first fixing piece 8, the first fixing piece 8 is made of metal materials, and the first protective cap 15 prevents the first fixing piece 8 from directly contacting with the first fairing, so that the fairing is prevented from being damaged.
As shown in fig. 1 to 3, the utility model discloses a general aircraft engine fairing hangs frock still hangs pole 10 and the second bracing piece 9 that is used for supporting the second fairing including the second that is used for hanging the second fairing, and the second hangs pole 10 and second bracing piece 9 and sets up on supporting the base. The second suspension rod 10 and the second support rod 9 are fixedly connected with the bearing rod 1, the second suspension rod 10 and the second support rod 9 are sequentially arranged along the length direction of the bearing rod 1, the second suspension rod 10 and the second support rod 9 extend out towards the outer side of the bearing rod 1, and the shapes of the second suspension rod 10 and the second support rod 9 are matched with the shape of the second fairing. The height of the second hanging bar 10 is less than that of the first hanging bar 6, and the height of the second supporting bar 9 is less than that of the first supporting bar 5.
As shown in fig. 1 to 3, the utility model discloses a general aircraft engine fairing hangs frock is still including setting up the second on supporting the base and hanging dead lever 11 and set up the second stationary blade 12 on second hangs dead lever 11, and second hangs dead lever 11 and is located the second and hangs the top of pole 10, and the second hangs pole 10 and is located the top of second bracing piece 9, and the second hangs the height that highly is less than first dead lever 7 that hangs of dead lever 11. One end of the second hanging fixing rod 11 in the length direction is fixedly connected with the bearing rod 1, and the second fixing piece 12 is fixedly connected with the other end of the second hanging fixing rod 11 in the length direction.
As shown in fig. 1 to 3, the second support rod 9 has a Y-shaped structure, and the second hanging rod 10 has a Y-shaped structure. The ends of the second hanging bar 10 and the second supporting bar 9 are also provided with a first protective cap 15, and the second fixing piece 12 is also provided with a second protective cap 16. The second suspension rod 10 has three ends, one end of the second suspension rod 10 is fixedly connected with the bearing rod 1, the other two ends of the second suspension rod 10 are wrapped with second protective caps 16, and the second suspension rod 10 is made of metal materials. The second bracing piece 9 has three tip, one of them tip and the bearing bar 1 fixed connection of second bracing piece 9, all wraps up first protective cap 15 on two other tip of second bracing piece 9, and second bracing piece 9 adopts the metal material to make. The second protective cap 16 prevents the second suspension bar 10, the second support bar 9 from directly contacting the second fairing, avoiding damage to the fairing. The second protective cap 16 wraps the second fixing piece 12, the second fixing piece 12 is made of metal, and the second protective cap 16 prevents the second fixing piece 12 from directly contacting with the second fairing, so that the fairing is prevented from being damaged.
As shown in fig. 1 to 3, the utility model discloses a general aircraft engine fairing hangs frock still hangs pole 14 and the third bracing piece 13 that is used for supporting the third fairing including the third that is used for hanging the third fairing, and the second hangs pole 10 and third bracing piece 13 sets up on supporting the base. The third suspension rod 14 and the third support rod 13 are fixedly connected with the bearing rod 1, the third suspension rod 14 and the third support rod 13 are sequentially arranged along the length direction of the bearing rod 1, the third suspension rod 14 and the third support rod 13 extend out towards the outer side of the bearing rod 1, and the shapes of the third suspension rod 14 and the third support rod 13 are matched with the shape of the third fairing. The height of the third hanging bar 14 is greater than that of the first hanging bar 6, and the height of the third supporting bar 13 is greater than that of the first supporting bar 5.
As shown in fig. 1 to 3, the third support bar 13 has a Y-shaped structure, and the third hanging bar 14 has a Y-shaped structure. The ends of the third hanging bar 14 and the third supporting bar 13 are also provided with a first protective cap 15, and the third fixing piece is also provided with a second protective cap 16. The third hanging rod 14 has three ends, one end of the third hanging rod 14 is fixedly connected with the bearing rod 1, the other two ends of the third hanging rod 14 are wrapped with second protective caps 16, and the third hanging rod 14 is made of metal materials. The third bracing piece 13 has three tip, one of them tip and the bearing bar 1 fixed connection of third bracing piece 13, all wraps up first protective cap 15 on two other tip of third bracing piece 13, and third bracing piece 13 adopts the metal material to make. The second protective cap 16 prevents the third suspension bar 14, the third support bar 13 from directly contacting the third fairing, avoiding damage to the fairing.
Preferably, the first protective cap 15 and the second protective cap 16 are made of rubber, and the second protective cap 16 is bonded to the first fixing piece 8 and the second fixing piece 12, respectively.
As shown in fig. 1 to 3, the support base further includes a base reinforcing plate 3 connected to all of the base cross members 2, and the base reinforcing plate 3 is located below the base cross members 2.
As shown in fig. 1 to 3, the positions of the first support bar 5, the second support bar 9, and the third support bar 13 on the projection plane perpendicular to the length direction of the bearing bar 1 are respectively located between every two circumferentially adjacent base beams 2, which facilitates the arrangement of the cowling.
The invention has been described above by way of example with reference to the accompanying drawings. Obviously, the specific implementation of the present invention is not limited by the above-described manner. Various insubstantial improvements are made by adopting the method conception and the technical proposal of the utility model; or without improvement, the above conception and technical solution of the present invention can be directly applied to other occasions, all within the protection scope of the present invention.
Claims (10)
1. General aircraft engine radome fairing hangs frock, its characterized in that: the supporting base comprises a supporting base, trundles arranged at the bottom of the supporting base, a first suspension rod used for suspending a first fairing and a first supporting rod used for supporting the first fairing, wherein the first suspension rod and the first supporting rod are arranged on the supporting base.
2. The general aircraft engine fairing suspension fixture of claim 1, wherein: the support base is provided with a first hanging fixed rod and a first fixing piece, the first hanging fixed rod is arranged on the support base, the first hanging fixed rod is arranged above the first hanging rod, and the first hanging rod is arranged above the first support rod.
3. The general aircraft engine fairing suspension fixture of claim 2, wherein: the end parts of the first suspension rod and the first supporting rod are provided with first protective caps, the first fixing piece is provided with a second protective cap, and the first protective cap and the second protective cap are made of soft materials.
4. The general aircraft engine fairing hanging tool as claimed in claim 1 or 2, wherein: the second fairing supporting device further comprises a second suspension rod used for suspending the second fairing and a second supporting rod used for supporting the second fairing, and the second suspension rod and the second supporting rod are arranged on the supporting base.
5. The general aircraft engine fairing suspension fixture of claim 4, wherein: the support base is provided with a first hanging fixed rod and a first fixing piece, the first hanging fixed rod is arranged on the support base, the first fixing piece is arranged on the first hanging fixed rod, the first hanging fixed rod is arranged above the first hanging rod, and the first hanging rod is arranged above the first supporting rod.
6. The general aircraft engine fairing suspension fixture of claim 5, wherein: the end parts of the second suspension rod and the second supporting rod are provided with first protective caps, the second fixing piece is provided with a second protective cap, and the first protective cap and the second protective cap are made of soft materials.
7. The general aircraft engine fairing hanging tool as claimed in claim 1 or 2, wherein: the third fairing supporting device further comprises a third suspension rod used for suspending a third fairing and a third supporting rod used for supporting the third fairing, and the second suspension rod and the third supporting rod are arranged on the supporting base.
8. The general aircraft engine fairing suspension fixture of claim 7, wherein: and the end parts of the third suspension rod and the third supporting rod are provided with first protective caps which are made of soft materials.
9. The general aircraft engine fairing hanging tool as claimed in claim 1 or 2, wherein: the supporting base comprises a vertically arranged bearing rod and a base cross beam connected with the lower end of the bearing rod, the trundles are arranged on the base cross beam, and the base cross beam is provided with a plurality of trundles.
10. The general aircraft engine fairing suspension fixture of claim 9, wherein: the support base further comprises base reinforcing plates connected with all the base cross beams.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021447302.0U CN212710044U (en) | 2020-07-21 | 2020-07-21 | Universal aircraft engine fairing suspension tool |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021447302.0U CN212710044U (en) | 2020-07-21 | 2020-07-21 | Universal aircraft engine fairing suspension tool |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN212710044U true CN212710044U (en) | 2021-03-16 |
Family
ID=74908138
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202021447302.0U Active CN212710044U (en) | 2020-07-21 | 2020-07-21 | Universal aircraft engine fairing suspension tool |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN212710044U (en) |
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2020
- 2020-07-21 CN CN202021447302.0U patent/CN212710044U/en active Active
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