CN113639593A - Light high-temperature-resistant rudder surface structure and duck rudder piece - Google Patents
Light high-temperature-resistant rudder surface structure and duck rudder piece Download PDFInfo
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- CN113639593A CN113639593A CN202110929764.9A CN202110929764A CN113639593A CN 113639593 A CN113639593 A CN 113639593A CN 202110929764 A CN202110929764 A CN 202110929764A CN 113639593 A CN113639593 A CN 113639593A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/60—Steering arrangements
- F42B10/62—Steering by movement of flight surfaces
- F42B10/64—Steering by movement of flight surfaces of fins
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Abstract
The invention provides a light high-temperature-resistant control surface structure and a duck rudder piece in the technical field of aircraft design, which comprise a control surface mechanism and a dot matrix mechanism, wherein the dot matrix mechanism comprises a plurality of single-surface body cells; the single-face body cell element comprises a connecting rod and a plurality of combined frames, the single-face body cell element is fixedly arranged at an angle through the combined frames, each combined frame comprises a plurality of combined rods, the combined rods are fixedly arranged, and end points of the combined rods are mutually fixed to form a vertex angle connecting point; the single-sided body cell elements are fixedly arranged through vertex angle connecting points, and the dot matrix mechanism is connected and arranged in the control surface mechanism through connecting rods. The invention realizes the requirements of vibration suppression, bearing and heat prevention in a limited space, realizes the isotropy of the structural rigidity and reduces the damage of aerodynamic heat to the structure.
Description
Technical Field
The invention relates to the technical field of aircraft design, in particular to a light high-temperature-resistant control surface structure and a duck rudder piece.
Background
In the technical field of aircraft design, a duck rudder is a key component for generating control force of an aircraft, and the duck rudder is commonly used in the initial stage of a short-range missile at present. Along with the increase of the maneuvering overload capacity requirement of the aircraft, the large overload is paid at the middle section or the tail section of the trajectory, and the telescopic duck rudder provides a simple and feasible solution for the purpose. However, the duck rudder in front of the projectile, in the middle or end of the trajectory, will be subjected to severe aerodynamic noise and aerodynamic heat. The conventional thin control surface structure is difficult to meet the use working condition.
The search of the prior art finds that the Chinese invention patent publication number is CN108824634B, and discloses a light space lattice structure, which comprises N single cells connected with each other; each unit cell comprises an upper polygonal frame a, a lower polygonal frame c and a side rod system b; the upper polygonal frame a and the lower polygonal frame b have the same structure, the side rod systems b are a plurality of connecting rods, and the upper polygonal frame a and the lower polygonal frame b are connected according to the same connecting principle, so that the structure is light. The invention, with the patent publication number of CN107100268B, discloses a light-weight spatial lattice structure, which is a spatial lattice material based on bent-rod cells, and includes N cells, each cell is formed by connecting two groups of bent rods through nodes in the cell, and each cell is connected through nodes between cells, and the cell is extended in the x, y, z directions to form a three-dimensional spatial lattice material. The curvature of each group of the bent rods in the cell elements is different, and the curvature of each group of the bent rods in each cell element adjacent to each other in the x, y and z directions is also different, so that the rigidity in different directions is changed according to the required gradient. However, the above-mentioned techniques have the following disadvantages: the difference between the heat-conducting performance of the internal air and the structure cannot be solved, and a large temperature gradient is often generated to cause structural damage.
Based on this, need to provide a light high temperature resistant rudder surface structure and duck rudder spare at present, need realize suppressing in the finite space and shake, bear and the demand of heat protection, realize structural rigidity's isotropy and reduce the destructive effect of aerodynamic heat to the structure.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a light high-temperature-resistant control surface structure and a duck rudder piece.
The light high-temperature-resistant control surface structure comprises a control surface mechanism and a dot matrix mechanism, wherein the dot matrix mechanism comprises a plurality of single-surface body cells;
the single-face body cell element comprises a connecting rod and a plurality of combined frames, the single-face body cell element is fixedly arranged at an angle through the combined frames, each combined frame comprises a plurality of combined rods, the combined rods are fixedly arranged, and end points of the combined rods are mutually fixed to form a vertex angle connecting point;
the single-sided body cell elements are fixedly arranged through vertex angle connecting points, and the dot matrix mechanism is connected and arranged in the control surface mechanism through connecting rods.
In some embodiments, the control surface mechanism comprises a duck rudder skin and a control surface frame, and the duck rudder skin is fixedly arranged on two sides of the control surface frame.
In some embodiments, the lattice mechanism is fixedly arranged on the duck rudder skin through a vertex angle connecting point.
In some embodiments, the combined frame adopts four combined rods, and the four combined rods are arranged in a regular quadrilateral structure.
In some embodiments, the monohedral cell element comprises twelve combined frames, and twelve combined frames are fixedly arranged into a regular dodecahedron through the connection points of the top corners at the same angle.
In some embodiments, four combined rods are fixedly arranged on the top corner connecting point, and each of the four combined rods is one of four combined frames which are adjacently arranged.
In some embodiments, the control surface frame is arranged in a structure with a triangular section.
In some embodiments, the connecting rod is configured as a hollow cylindrical rod structure.
In some embodiments, the combination post is configured as a hollow cylindrical post structure.
The invention also provides a duck rudder piece which adopts the light high-temperature-resistant rudder surface structure.
Compared with the prior art, the invention has the following beneficial effects:
1. according to the invention, the combined frames are arranged, and the combined frames are mutually fixed to form the single-sided body cell element, so that the single-sided body cell element is strictly formed into a space structure in space, the requirements of vibration suppression, bearing and heat prevention are realized in a limited space, the isotropy of the structural rigidity is realized, and the damage effect of aerodynamic heat on the structure is reduced;
2. according to the lattice structure, the combined frame with the regular quadrilateral structure is arranged, the adjacent single-sided body cell elements are fixed through the vertex angle connecting points formed by mutually fixing the combined rods, and the whole lattice structure is completely communicated through the connecting rods and the combined rods with the hollow cylindrical rod structures.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is an exploded view of a light high temperature resistant rudder surface structure according to the present invention;
FIG. 2 is a schematic structural diagram of a light high temperature resistant rudder surface structure according to the present invention;
FIG. 3 is a schematic cross-sectional view of a light high temperature resistant rudder surface structure according to the present invention;
FIG. 4 is a schematic diagram of a cell of the present invention;
figure 5 is a topological structure diagram of a mono-hedron cell of the present invention.
Reference numerals: 1. a control surface mechanism; 11. covering a duck rudder with skin; 12. a control surface frame; 13. a dot matrix mechanism; 2. a mono-hedral cell; 21. a combined frame; 211. a combination rod; 212. a vertex angle connection point; 22. a connecting rod.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
Fig. 1 is an explosion diagram of a light high temperature resistant control surface structure, fig. 2 is a structural diagram of the light high temperature resistant control surface structure, fig. 3 is a cross-sectional diagram of the light high temperature resistant control surface structure, and the cross-sectional diagram includes a control surface mechanism 1 and a lattice mechanism 13, and the lattice mechanism 13 includes a plurality of single-sided body cells 2.
Fig. 4 is a schematic structural diagram of a monohedral cell element 2, fig. 5 is a structural diagram of a topology of the monohedral cell element 2, the monohedral cell element 2 includes a connecting rod 22 and a plurality of combined frames 21, the monohedral cell element 2 is mutually angularly fixed through the plurality of combined frames 21, the combined frames 21 include a plurality of combined rods 211, the plurality of combined rods 211 are mutually fixed, and end points of the combined rods 211 are mutually fixed to form a vertex angle connecting point 212. In this embodiment, the connecting rod 22 is provided in a hollow cylindrical rod configuration.
The plurality of the monohedral cells 2 are fixedly arranged with each other through the vertex angle connection points 212, and the dot matrix mechanism 13 is connected and arranged in the control surface mechanism 1 through the connecting rod 22. The control surface mechanism 1 comprises a duck rudder skin 11 and a control surface frame 12, the duck rudder skin 11 is fixedly arranged on two sides of the control surface frame 12, and the dot matrix mechanism 13 is fixedly arranged with the duck rudder skin 11 through a vertex angle connecting point 212. In the present embodiment, the control surface frame 12 is provided in a structure having a triangular cross section.
The combined frame 21 adopts four combined rods 211, and the four combined rods 211 are arranged in a regular quadrilateral structure. The monohedral cell 2 comprises twelve combined frames 21, and the twelve combined frames 21 are fixedly arranged into a regular dodecahedron at the same angle through a top corner connecting point 212. Four combined rods 211 are fixedly arranged on the top corner connecting points 212, and the four combined rods 211 are respectively used as one of the four combined frames 21 which are adjacently arranged. In the present embodiment, the combination rod 211 is configured as a hollow cylindrical rod.
When the lattice structure is used, the adjacent single-sided body cell elements 2 are connected by adopting the regular quadrilateral combination frame 21, so that the single-sided body cell elements 2 are strictly formed into a space structure in space, and then the single-sided body cell elements 2 are mutually fixed through the vertex angle connecting points 212 to form the full communication of the whole lattice mechanism 13. And then fixing the lattice mechanisms 13 which are fixed with each other in the control surface frame 12 and fixing the lattice mechanisms and the duck rudder skin 11 with each other. The requirements of vibration suppression, bearing and heat prevention are realized in a limited space, the isotropy of the structural rigidity is realized, and the damage effect of aerodynamic heat on the structure is reduced.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (10)
1. The light high-temperature-resistant control surface structure is characterized by comprising a control surface mechanism (1) and a dot matrix mechanism (13), wherein the dot matrix mechanism (13) comprises a plurality of single-sided body cell elements (2);
the single-face body cell element (2) comprises a connecting rod (22) and a plurality of combined frames (21), the single-face body cell element (2) is fixedly arranged at an angle through the combined frames (21), the combined frames (21) comprise a plurality of combined rods (211), the combined rods (211) are fixedly arranged with each other, and end points of the combined rods (211) are mutually fixed to form a vertex angle connecting point (212);
the single-sided body cell elements (2) are mutually fixedly arranged through vertex angle connecting points (212), and the dot matrix mechanism (13) is connected and arranged in the control surface mechanism (1) through a connecting rod (22).
2. The light high temperature resistant rudder surface structure according to claim 1, wherein the rudder surface structure (1) comprises a duck rudder skin (11) and a rudder surface frame (12), and the duck rudder skin (11) is fixedly arranged on two sides of the rudder surface frame (12).
3. The light high temperature resistant rudder surface structure according to claim 2, wherein the lattice mechanism (13) is fixedly arranged with the duck rudder skin (11) through a vertex angle connection point (212).
4. The light high-temperature-resistant rudder surface structure according to claim 1, wherein the combined frame (21) adopts four combined rods (211), and the four combined rods (211) are arranged in a regular quadrilateral structure.
5. The light high temperature resistant rudder surface structure according to claim 1, wherein the monohedral cell (2) comprises twelve combined frames (21), and the twelve combined frames (21) are fixedly arranged into a regular dodecahedron through the same angle of a vertex angle connecting point (212).
6. The light high-temperature-resistant rudder surface structure according to claim 1, wherein four combined rods (211) are fixedly arranged on the top corner connecting points (212), and the four combined rods (211) are respectively used as one of four combined frames (21) which are adjacently arranged.
7. Light high-temperature control surface structure according to claim 2, characterized in that the control surface frame (12) is arranged in a structure with a triangular cross section.
8. The light high temperature resistant rudder surface structure according to claim 1, characterised in that the connecting rod (22) is arranged in a hollow cylindrical rod structure.
9. The light high-temperature-resistant rudder surface structure according to claim 1, characterized in that the combined rod (211) is arranged in a hollow cylindrical rod structure.
10. A duck rudder piece, which is characterized in that the light high-temperature-resistant rudder surface structure of any one of claims 1 to 9 is adopted.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110929764.9A CN113639593A (en) | 2021-08-13 | 2021-08-13 | Light high-temperature-resistant rudder surface structure and duck rudder piece |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110929764.9A CN113639593A (en) | 2021-08-13 | 2021-08-13 | Light high-temperature-resistant rudder surface structure and duck rudder piece |
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| CN113639593A true CN113639593A (en) | 2021-11-12 |
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| CN202110929764.9A Pending CN113639593A (en) | 2021-08-13 | 2021-08-13 | Light high-temperature-resistant rudder surface structure and duck rudder piece |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030173459A1 (en) * | 2001-12-06 | 2003-09-18 | Kazak Composites, Incorporated | Lattice fin for missiles or other fluid-born bodies and method for producing same |
| CN110705093A (en) * | 2019-09-29 | 2020-01-17 | 北京星航机电装备有限公司 | Lightweight lattice structure parametric modeling and data lightweight processing method |
| CN111301717A (en) * | 2019-12-27 | 2020-06-19 | 北京空间技术研制试验中心 | Bulkhead structure of manned spacecraft sealed cabin |
| CN111425543A (en) * | 2020-03-30 | 2020-07-17 | 华中科技大学 | Enhanced type superposed hollow lattice structure and application thereof |
| CN112743088A (en) * | 2020-12-28 | 2021-05-04 | 北京航星机器制造有限公司 | Rhombic dodecahedron titanium alloy lattice structure, interlayer structure and manufacturing method |
-
2021
- 2021-08-13 CN CN202110929764.9A patent/CN113639593A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030173459A1 (en) * | 2001-12-06 | 2003-09-18 | Kazak Composites, Incorporated | Lattice fin for missiles or other fluid-born bodies and method for producing same |
| CN110705093A (en) * | 2019-09-29 | 2020-01-17 | 北京星航机电装备有限公司 | Lightweight lattice structure parametric modeling and data lightweight processing method |
| CN111301717A (en) * | 2019-12-27 | 2020-06-19 | 北京空间技术研制试验中心 | Bulkhead structure of manned spacecraft sealed cabin |
| CN111425543A (en) * | 2020-03-30 | 2020-07-17 | 华中科技大学 | Enhanced type superposed hollow lattice structure and application thereof |
| CN112743088A (en) * | 2020-12-28 | 2021-05-04 | 北京航星机器制造有限公司 | Rhombic dodecahedron titanium alloy lattice structure, interlayer structure and manufacturing method |
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