CN111056048A

CN111056048A - Grid rudder

Info

Publication number: CN111056048A
Application number: CN201911399993.3A
Authority: CN
Inventors: 彭小波; 郑立伟; 黄茜
Original assignee: Beijing Interstellar Glory Space Technology Co Ltd; Beijing Interstellar Glory Technology Co Ltd
Current assignee: Beijing Interstellar Glory Space Technology Co Ltd; Beijing Interstellar Glory Technology Co Ltd
Priority date: 2019-12-27
Filing date: 2019-12-27
Publication date: 2020-04-24
Anticipated expiration: 2039-12-27
Also published as: CN111056048B

Abstract

The invention discloses a grid rudder, comprising a connected rudder surface structure and a rudder shaft, the rudder surface structure is formed by a plurality of grid walls staggered and connected to form a grid structure, the rudder shaft is used for connecting with an arrow body; the rudder The thickness of the grid wall at one end of the surface structure close to the rudder shaft is greater than the thickness of the grid wall at the end away from the rudder shaft. The grid wall of the rudder surface structure adopts the structural design of variable thickness, which can reduce the overall weight of the grid rudder under the condition that the maximum stress at the rudder shaft of the grid rudder meets the requirements of the yield stress.

Description

Grid rudder

Technical Field

The invention relates to the technical field of aerospace, in particular to a grid rudder.

Background

Grid rudders are widely used on missiles and launch vehicles. The chord length of the grid rudder is small, the pressure center on the control surface is close to the hinge shaft and is slightly influenced by the state quantity, so that the hinge moment of the control surface is small; the grid rudder can be folded and attached to the surface of the arrow (bomb) when not in use, so that the occupied space is small, and the influence on the appearance of the arrow (bomb) body is small.

Grid rudder among the prior art is as shown in fig. 1, and the check wall thickness of grid rudder is the constant, and the weight of whole grid rudder according to such design is great, is unfavorable for the improvement of arrow body carrying capacity, consequently, needs design one kind can satisfy arrow body gesture adjustment demand and more light and handy grid rudder structure.

Disclosure of Invention

Therefore, the technical problem to be solved by the invention is to overcome the problem that the grid rudder in the prior art has heavy weight, so that the grid rudder is provided.

In order to solve the technical problems, the technical scheme of the invention is as follows:

a grid rudder comprises a rudder surface structure and a rudder shaft which are connected, wherein the rudder surface structure is formed by connecting a plurality of lattice walls in a staggered manner to form a grid structure, and the rudder shaft is used for being connected with an arrow body; the thickness of the grid wall of the rudder surface structure close to one end of the rudder shaft is larger than that of the grid wall of the rudder surface structure far away from one end of the rudder shaft.

Furthermore, one end of the control surface structure close to the control shaft is a control root, and one end of the control surface structure far away from the control shaft is a control tip; and in the direction from the rudder root to the rudder tip, the thickness of the lattice wall is gradually reduced.

Further, the lattice walls include a first lattice wall, a second lattice wall, a third lattice wall, a fourth lattice wall and a fifth lattice wall, wherein the thicknesses of the first lattice wall, the second lattice wall, the third lattice wall, the fourth lattice wall and the fifth lattice wall are gradually reduced from the rudder root to the rudder tip.

Further, in the control surface structure, the area occupation ratios of the first lattice wall, the second lattice wall, and the third lattice wall on the lattice structure are sequentially increased.

Further, the thickness of the first cell wall is 17.07mm, the thickness of the second cell wall is 10mm, the thickness of the third cell wall is 7mm, the thickness of the fourth cell wall is 5mm, and the thickness of the fifth cell wall is 3 mm.

Further, the first lattice wall and the rudder shaft are integrally formed.

Further, the rudder surface structure comprises a rudder frame positioned on the periphery and rudder pieces which are connected in the rudder frame in a staggered mode to form a grid structure.

Further, the control surface structure is thickened on the lattice wall with large maximum yield stress, and the control surface structure is thickened on the lattice wall with small maximum yield stress.

Further, the windward side and/or the back facet of the control surface structure are cambered surfaces.

Furthermore, the cambered surface is a circular arc surface matched with the appearance of the arrow body.

The technical scheme of the invention has the following advantages:

1. according to the grid rudder provided by the invention, because the stress of the rudder surface structure at the end close to the rudder shaft is greater than the stress at the end far away from the rudder shaft, the grid wall of the rudder surface structure is designed in a variable-thickness structure, so that the thickness of the grid wall close to the rudder shaft is greater than that of the grid wall far away from the rudder shaft.

2. According to the grid rudder provided by the invention, the lattice wall of the control surface structure is thickened at the position with large maximum yield stress, and is thickened at the position with small maximum yield stress, so that the quality of the grid rudder is further lighter under the condition that the maximum stress at each position of the grid rudder meets the use requirement of the yield stress.

3. According to the grid rudder provided by the invention, the windward side and/or the back part of the rudder surface structure are designed to be of the cambered surface structure, so that the grid rudder can be well attached to the surface of an arrow body, and the gap between the grid rudder and the arrow body is reduced.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.

FIG. 1 is a schematic diagram of a prior art grid rudder;

FIG. 2 is a schematic structural diagram of a grid rudder in an embodiment of the present invention;

FIG. 3 is a gray scale diagram of stress distribution at the position of a grid rudder root in the embodiment of the present invention;

FIG. 4 is a schematic diagram of stress distribution at the position of a grid rudder root in the embodiment of the invention;

FIG. 5 is a schematic structural view of a grid rudder according to an embodiment of the present invention folded and attached to the surface of an arrow.

Description of reference numerals: 1. a control surface structure; 101. a first cell wall; 102. a second cell wall; 103. a third cell wall; 104. a fourth cell wall; 105. a fifth cell wall; 2. a rudder shaft; 3. an arrow body.

Detailed Description

The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.

As shown in fig. 1, a control surface structure of a grid rudder in the prior art is in a grid shape, and the thickness of all grid walls on the control surface structure is 10 mm. The grid rudder can be folded and attached to the surface of the arrow body when not in use, so that the occupied space of the grid rudder is reduced, and the influence on the appearance of the arrow body is reduced.

As shown in fig. 2, the embodiment of the present invention provides a grid rudder, which comprises a rudder surface structure 1 and a rudder shaft 2 which are connected. The control surface structure 1 is formed by connecting a plurality of grid walls in a staggered mode to form a grid structure, and the control shaft 2 is used for being hinged with the arrow body 3. The thickness of the grid wall of the rudder surface structure 1 at the end close to the rudder shaft 2 is larger than that at the end far away from the rudder shaft 2.

Because the stress of the rudder surface structure 1 close to one end of the rudder shaft 2 is greater than the stress of the rudder shaft 2 far away from one end of the rudder surface structure 1, the lattice wall of the rudder surface structure 1 is designed in a variable thickness structure, so that the thickness of the lattice wall close to the rudder shaft 2 is greater than the thickness of the lattice wall far away from the rudder shaft 2.

Specifically, one end of the control surface structure 1 close to the control shaft 2 is a control root, and one end far away from the control shaft 2 is a control tip; in the direction from the rudder root to the rudder tip, the thickness of the lattice wall is gradually reduced. In a specific embodiment of this embodiment, the control surface structure 1 is divided into five regions, i.e., I-th region, II-th region, III-th region, IV-th region, and V-th region, according to the thickness of the lattice wall, and the thickness of the lattice wall in each region is the same. In other embodiments, the control surface structure 1 may be further divided into two regions, three regions, four regions, or six or more regions according to the thickness of the lattice wall, and the more the division of the regions on the control surface structure 1 is, the more advantageous the light-weight design of the lattice rudder structure is, but the difficulty in designing and manufacturing the control surface structure 1 is also increased, so in the present embodiment, it is preferable to divide the control surface structure 1 into five regions that are connected to each other according to the thickness of the lattice wall.

In the present embodiment, the lattice walls include a first lattice wall 101, a second lattice wall 102, a third lattice wall 103, a fourth lattice wall 104, and a fifth lattice wall 105 whose thicknesses in the direction from the root to the tip of the rudder gradually decrease. Specifically, the thickness of the first cell wall 101 is 17.07mm, the thickness of the second cell wall 102 is 10mm, the thickness of the third cell wall 103 is 7mm, the thickness of the fourth cell wall 104 is 5mm, and the thickness of the fifth cell wall 105 is 3 mm. The mode that cell wall thickness reduces step by step can be under the condition that satisfies the stress demand, makes the structure of grid rudder lighter and more handy.

In the control surface structure 1, the maximum stress value of the grid rudder meeting the use requirement of the yield stress at the position close to the rudder root of the rudder shaft 2 is more, the maximum stress value of the grid rudder meeting the use requirement of the yield stress at the position close to the rudder root of the rudder shaft 2 is smaller, and the maximum stress value of the grid rudder needing to meet the use requirement of the yield stress at each position in the direction from the rudder root to the rudder tip is gradually reduced; therefore, the thickness of the first lattice wall 101 at the connection of the control surface structure 1 and the control shaft 2 is set to be 17.07mm larger than the value of the lattice wall constant of the prior art (specifically, 10mm), while the thickness of the fifth lattice wall 105 farthest from the rudder root is set to be 3mm smaller than the value of the lattice wall constant of the prior art, and the thicknesses of the other second lattice wall 102, third lattice wall 103, and fourth lattice wall 104 are set to be 10mm, 7mm, and 5mm in this order, the rudder root of the lattice rudder of this design structure can well satisfy the yield stress use requirement, and the overall weight of the lattice rudder can be reduced relative to the lattice rudder with the lattice wall constant value of 10 mm.

Specifically, the first lattice wall 101 and the rudder shaft 2 are of an integrally formed structure; the area ratio of the first cell wall 101, the second cell wall 102, and the third cell wall 103 on the lattice structure increases in order. In an embodiment of the present embodiment, taking the number of the ribs of the grid structure as an example, there are four

first cell walls

101, 10 second cell walls 102, 18 third cell walls 103, 26 fourth cell walls 104, and 32 fifth cell walls 105.

On the other hand, the rudder surface structure 1 is composed of a rudder frame positioned on the periphery and rudder pieces which are connected in the rudder frame in a staggered mode to form a grid structure, and the rudder pieces as well as the rudder pieces and the rudder frame are of an integrally formed structure.

In a preferred embodiment of the present embodiment, the control surface structure 1 is thickened on the lattice wall with the large maximum yield stress, and the control surface structure 1 is thickened on the lattice wall with the small maximum yield stress. Under certain conditions (for example, Mach number is 2.0, attack angle is 10 degrees, and height is 0 km), the stress at each position of the grid rudder is analyzed, and the stress distribution diagram of the whole grid rudder is obtained. Taking the stress distribution diagram at the position of the grid rudder root as an example, as shown in fig. 3 and 4, the maximum stress values required to meet the use requirement of the yield stress at each of the areas a, b, c, d, e, f, g, h and i in fig. 5 are sequentially increased; therefore, the lattice wall with the maximum yield stress is thickened according to the stress distribution diagram of the control surface structure 1, and the lattice wall with the minimum yield stress is thickened, so that the overall quality of the grid rudder can be reduced as much as possible under the condition that the stress requirement is met.

As shown in fig. 5, in the present embodiment, the windward side and/or the back side of the control surface structure 1 is a cambered surface. Specifically, when the arrow body 3 is cylindrical, the arc surface is an arc surface matched with the arrow body 3 in shape. The radius of the arc is determined by the radius of the arrow body 3. Compared with the design structure that the windward side and/or the leeward side are both planes in the prior art, the grid rudder with the cambered surface on the windward side and/or the leeward side can be better attached to the surface of the arrow body 3, and the gap between the rudder surface structure 1 and the arrow body 3 when the grid rudder is retracted is reduced.

In summary, according to the grid rudder provided by the embodiment of the present invention, on one hand, the lattice wall of the control surface structure 1 adopts a variable thickness structural design, so that the overall weight of the grid rudder can be reduced under the condition that the maximum stress at the position of the grid rudder shaft 2 meets the use requirement of the yield stress; on the other hand, the windward side and/or the back part of the control surface structure 1 are designed to be cambered surfaces, so that the control surface structure can be better attached to the surfaces of the arrow bodies 3, and gaps between the control surface structure 1 and the arrow bodies 3 when the grid rudder is retracted are reduced.

It should be understood that the above examples are only for clarity of illustration and are not intended to limit the embodiments. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. And obvious variations or modifications therefrom are within the scope of the invention.

Claims

1. The grid rudder comprises a rudder surface structure (1) and a rudder shaft (2) which are connected, wherein the rudder surface structure (1) is formed by connecting a plurality of lattice walls in a staggered manner to form a grid structure, and the rudder shaft (2) is used for being connected with an arrow body (3); the rudder surface structure is characterized in that the thickness of the lattice wall at one end, close to the rudder shaft (2), of the rudder surface structure (1) is larger than that of the lattice wall at one end, far away from the rudder shaft (2).

2. Grid rudder according to claim 1, characterised in that the end of the rudder surface structure (1) close to the rudder shaft (2) is the rudder root and the end remote from the rudder shaft (2) is the rudder tip; and in the direction from the rudder root to the rudder tip, the thickness of the lattice wall is gradually reduced.

3. The lattice rudder of claim 2, wherein the lattice walls include a first lattice wall (101), a second lattice wall (102), a third lattice wall (103), a fourth lattice wall (104), and a fifth lattice wall (105) that gradually decrease in thickness in a direction from the rudder root to the rudder tip.

4. Grid rudder according to claim 3, characterised in that in the control surface structure (1) the area fraction of the first (101), second (102) and third (103) cell walls on the lattice structure increases in the order named.

5. Grid rudder according to claim 4, characterised in that the thickness of the first cell wall (101) is 17.07mm, the thickness of the second cell wall (102) is 10mm, the thickness of the third cell wall (103) is 7mm, the thickness of the fourth cell wall (104) is 5mm and the thickness of the fifth cell wall (105) is 3 mm.

6. Grid rudder according to claim 3, characterised in that the first lattice wall (101) and the rudder shaft (2) are integrally formed.

7. Grid rudder according to claim 1, characterised in that the rudder surface structure (1) comprises a peripherally located rudder frame and rudder blades which are connected in a staggered manner in the rudder frame forming a grid structure.

8. Grid rudder according to claim 1, characterised in that the control surface structure (1) is thickened on the cell walls with a large maximum yield stress and that the control surface structure (1) is thickened on the cell walls with a small maximum yield stress.

9. Grid rudder according to claim 1, characterised in that the windward and/or dorsal facets of the rudder surface structure (1) are cambered surfaces.

10. Grid rudder according to claim 9, characterised in that the curved surface is a circular arc surface matching the shape of the arrow body (3).