CN214875519U - Support body for low-wind-resistance aircraft - Google Patents
Support body for low-wind-resistance aircraft Download PDFInfo
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- CN214875519U CN214875519U CN202120988724.7U CN202120988724U CN214875519U CN 214875519 U CN214875519 U CN 214875519U CN 202120988724 U CN202120988724 U CN 202120988724U CN 214875519 U CN214875519 U CN 214875519U
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- main body
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Abstract
The utility model discloses a support body for a low-wind-resistance aircraft, which comprises a support main body, wherein the outer surface of the support main body is provided with a groove, one end of the support main body is provided with an integrated end seat, the other end of the support main body is provided with an integrated flange main body, the inner side surface of the support main body is provided with an integrated fixing piece, the fixing piece is connected with a reinforcing block, and the inner side of the reinforcing block is provided with a clamping groove; when the working process, if the support main part atress is great, the support body is probably the atress to take place deformation in the working process, influence the structural strength of support main part, lead to this support body to damage, influence the use of this support body, the inboard of this support main part is provided with the stationary blade of integral type, when using the installation, can be equipped with the boss at the stationary blade facial make-up, the boss is through strengthening the safe edge laminating on the inner wall of support main part, improve the overall structure intensity of this support main part, prevent that the support main part atress from taking place deformation.
Description
Technical Field
The utility model belongs to the technical field of the aircraft support, concretely relates to support body that aircraft of low windage was used.
Background
The aircraft is an apparatus flying in the atmosphere or the space outside the atmosphere, and the aircraft is divided into 3 types: aircraft, spacecraft, rockets, and missiles. Flying in the atmosphere is referred to as an aircraft, such as a balloon, airship, airplane, etc. They fly by the static buoyancy of air or the aerodynamic force generated by the relative movement of air. Flying in space is called a spacecraft, such as an artificial earth satellite, a manned spacecraft, a space probe, a space shuttle and the like. They are propelled by a launch vehicle to obtain the necessary velocity to enter space, and then make orbital motion similar to celestial bodies by means of inertia, and the flying vehicles flying in the atmosphere are called aircraft, such as balloon, glider, airship, airplane, helicopter, etc., and they fly by means of the static buoyancy of air or the aerodynamic lift generated by the relative motion of air
The support main part that current low windage's aircraft was used, can the installing support main part usually on low windage's aircraft, the support main part commonly used is when using, usually fixed the installing, in the installation use, because the support main part is awl loop configuration, in working process, if support main part atress is great, possible atress deformation of support body in the working process, influence the structural strength of support main part, lead to this support body to damage, influence the use of this support body, the problem of the practicality of the device has been reduced, we provide the support body that low windage's aircraft was used for this.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide a support body that aircraft of low windage was used, with the support main part that the aircraft of the current low windage that proposes in solving above-mentioned background art was used, can the installing support main part usually on the aircraft of low windage, the support main part commonly used is when using, usually fixed the installing, in the installation use, because the support main part is awl loop configuration, in the course of the work, if support main part atress is great, the support body is possible to receive the force deformation in the course of the work, influence the structural strength of support main part, lead to this support body to damage, influence the use of this support body, the problem of the practicality of the device has been reduced.
In order to achieve the above object, the utility model provides a following technical scheme: the utility model provides a support body that low windage's aircraft was used, includes the support main part, the surface of support main part is seted up flutedly, just the end socket of integral type is seted up to the one end of support main part, the flange main part of integral type is seted up to the other end of support main part, the stationary blade of integral type is seted up to the internal side surface of support main part, the boss has been installed in the connection on the stationary blade, the draw-in groove has been seted up to the inboard of boss, the boss passes through draw-in groove and stationary blade counterpoint installation, just the enhancement safe edge of integral type is seted up at the both ends of boss, the outside screw thread of stationary blade is equipped with the bolt soon.
Preferably, the entire thickness of the bracket body is the same as the entire thickness of the flange body.
Preferably, four reinforcing blocks are arranged on the inner side of the bracket main body in an array mode, and reinforcing protective edges arranged on the four reinforcing blocks are attached to the inner surface of the bracket main body.
Preferably, the fixing piece and the reinforcing block are screwed and fixed through a bolt.
Preferably, the groove array is arranged on the surface of the bracket main body.
Preferably, the depth of the groove is one millimeter.
Compared with the prior art, the beneficial effects of the utility model are that: this support main part is in the course of working, process the support main part into awl loop configuration, in the course of working, if support main part atress is great, the support body is possible the atress to take place deformation in the course of working, influence the structural strength of support main part, lead to this support body to damage, influence the use of this support body, the stationary blade of integral type is provided with in the inboard of this support main part, when using the installation, can be equipped with the boss at the stationary blade facial make-up, the boss is through strengthening the inside wall of safe edge laminating on the support main part, improve the overall structure intensity of this support main part, prevent that support main part atress from taking place deformation, the practicality of this support body has been improved.
Drawings
Fig. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic view of a half-section structure of the present invention;
FIG. 3 is a schematic view of a top-down mounting structure of the reinforcing block of the present invention;
in the figure: 1. a groove; 2. a stent body; 3. an end seat; 4. a flange body; 5. a fixing sheet; 6. a reinforcing block; 7. a bolt; 8. and reinforcing the protective edge.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
Referring to fig. 1, fig. 2 and fig. 3, the present invention provides a technical solution: the utility model provides a support body that low windage's aircraft was used, including support main part 2, support main part 2's surface is seted up flutedly 1, and support main part 2's one end is seted up the end socket 3 of integral type, support main part 2's the other end is seted up the flange main part 4 of integral type, support main part 2's inboard surface is seted up the stationary blade 5 of integral type, the boss 6 has been installed in the connection on stationary blade 5, the draw-in groove has been seted up to the inboard of boss 6, boss 6 is through draw-in groove and the 5 counterpoint installation of stationary blade, and the enhancement safe edge 8 of integral type is seted up at the both ends of boss 6, the outside screw thread of stationary blade 5 is equipped with bolt 7 soon, boss 6 is through strengthening the laminating of safe edge 8 on support main part 2's inner wall, improve this support main part 2's overall structure intensity, prevent that support main part 2 atress from taking place deformation.
For better fixation, in the embodiment, preferably, the fixing piece 5 and the reinforcing block 6 are screwed and fixed by the bolt 7, so as to avoid unstable fixation of the reinforcing block 6 after installation, for better processing and use, in the embodiment, preferably, the groove 1 array is arranged on the surface of the bracket main body 2, for better use, in the present embodiment, it is preferable that the depth of the groove 1 is one millimeter, which is convenient for supporting use, for better use, in the embodiment, the overall thickness of the bracket main body 2 is preferably the same as that of the flange main body 4, so that the installation and use are convenient, in order to improve the supporting strength, in the embodiment, preferably, the inner array of the bracket main body 2 is provided with four reinforcing blocks 6, and the reinforcing protective edges 8 arranged on the four reinforcing blocks 6 are attached to the inner surface of the bracket main body 2, so that the inner side of the bracket main body 2 is stably supported.
The utility model discloses a theory of operation and use flow: the support main body 2 is processed into a conical ring structure, when the support main body 2 is stressed greatly in the working process, the support main body 2 is likely to be stressed and deformed, or the support main body 2 is cracked, the structural strength of the support main body 2 is influenced, the support main body 2 is damaged, and the use of the support main body 2 is influenced, an integrated fixing piece 5 is arranged on the inner side of the support main body 2, when the support is used and installed, a reinforcing block 6 can be taken out, the reinforcing block 6 is clamped on the fixing piece 5 in an aligning way, meanwhile, the reinforcing block 6 corresponds to a screw hole formed in the fixing piece 5 and is screwed and fixed through a bolt 7, an integrated reinforcing protective edge 8 is formed at one end of the reinforcing block 6, the reinforcing block 6 is attached to the inner wall of the support main body 2 through the reinforcing protective edge 8, the overall structural strength of the support main body 2 is improved through the reinforcing block 6 formed by mixing the reinforcing block 6, and the support main body 2 is prevented from being stressed and deformed, the practicability of the bracket body is improved.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (6)
1. The utility model provides a support body that low wind resistance's aircraft was used, includes support main part (2), its characterized in that: the outer surface of the support main body (2) is provided with a groove (1), one end of the support main body (2) is provided with an end seat (3) of an integral type, the other end of the support main body (2) is provided with a flange main body (4) of an integral type, the inner side surface of the support main body (2) is provided with a fixing piece (5) of an integral type, the fixing piece (5) is connected with a reinforcing block (6), the inner side of the reinforcing block (6) is provided with a clamping groove, the reinforcing block (6) is aligned to the fixing piece (5) through the clamping groove, the two ends of the reinforcing block (6) are provided with reinforcing protective edges (8) of an integral type, and the outer side thread of the fixing piece (5) is provided with a bolt (7) in a rotating mode.
2. The bracket body for the low-wind-resistance aircraft according to claim 1, wherein: the whole thickness of the bracket main body (2) is the same as that of the flange main body (4).
3. The bracket body for the low-wind-resistance aircraft according to claim 1, wherein: four reinforcing blocks (6) are arranged on the inner side of the bracket main body (2) in an array mode, and reinforcing protective edges (8) arranged on the four reinforcing blocks (6) are attached to the inner surface of the bracket main body (2).
4. The bracket body for the low-wind-resistance aircraft according to claim 1, wherein: the fixing piece (5) and the reinforcing block (6) are fixed in a rotating mode through a bolt (7).
5. The bracket body for the low-wind-resistance aircraft according to claim 1, wherein: the grooves (1) are arranged on the surface of the support main body (2) in an array mode.
6. The bracket body for the low-wind-resistance aircraft according to claim 1, wherein: the depth of the groove (1) is one millimeter.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120988724.7U CN214875519U (en) | 2021-05-11 | 2021-05-11 | Support body for low-wind-resistance aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120988724.7U CN214875519U (en) | 2021-05-11 | 2021-05-11 | Support body for low-wind-resistance aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN214875519U true CN214875519U (en) | 2021-11-26 |
Family
ID=78946615
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202120988724.7U Active CN214875519U (en) | 2021-05-11 | 2021-05-11 | Support body for low-wind-resistance aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN214875519U (en) |
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2021
- 2021-05-11 CN CN202120988724.7U patent/CN214875519U/en active Active
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