阅读说明：本技术 飞机副油箱环筋结构 (Ring rib structure of airplane auxiliary fuel tank ) 是由 季宝锋 张毅 曹亮 王非 郭浩 张鹏 于 2021-07-30 设计创作，主要内容包括：本发明提供了一种飞机副油箱环筋结构,包括副油箱壳体和环筋；副油箱壳体是采用复合材料制作的；环筋安装在副油箱壳体的前段内部吊耳梁的侧面位置；环筋的环内壁厚沿着环形方向自下部分弧段至上部分弧段逐渐变大,使环筋的下部分弧段为壁厚较小的连接弧段,环筋的上部分弧段为壁厚较大的支撑弧段；环筋为变截面偏心环结构。本发明的环筋安装在副油箱壳体的前段内部吊耳梁的侧面位置,以对吊耳梁处进行支撑；环筋的下部分弧段为壁厚较小的连接弧段,上部分弧段为壁厚较大的支撑弧段,减轻了整个环筋的重量,并且上部分弧段的支撑力强。(The invention provides an aircraft auxiliary fuel tank ring rib structure, which comprises an auxiliary fuel tank shell and a ring rib, wherein the ring rib is arranged on the auxiliary fuel tank shell; the auxiliary oil tank shell is made of composite materials; the ring rib is arranged on the side surface of the lug beam in the front section of the auxiliary oil tank shell; the wall thickness in the ring of the ring rib is gradually increased from the lower arc section to the upper arc section along the annular direction, so that the lower arc section of the ring rib is a connecting arc section with smaller wall thickness, and the upper arc section of the ring rib is a supporting arc section with larger wall thickness; the ring rib is a variable cross-section eccentric ring structure. The ring rib is arranged on the side surface of the lug beam in the front section of the auxiliary oil tank shell to support the lug beam; the lower part segmental arc of ring muscle is the less connection segmental arc of wall thickness, and the upper portion segmental arc is the great support segmental arc of wall thickness, has alleviateed the weight of whole ring muscle to the holding power of upper portion segmental arc is strong.)

1. The utility model provides an aircraft bellytank gird structure which characterized in that: comprises a secondary oil tank shell (100) and a ring rib (200);

the auxiliary oil tank shell (100) is made of composite materials;

the ring rib (200) is arranged on the side surface of a lug beam in the front section of the auxiliary oil tank shell (100);

the wall thickness in the ring of the ring rib (200) is gradually increased from the lower arc section to the upper arc section along the annular direction, so that the lower arc section of the ring rib (200) is a connecting arc section (201) with smaller wall thickness, and the upper arc section of the ring rib (200) is a supporting arc section (202) with larger wall thickness; the ring rib (200) is of a variable cross-section eccentric ring structure.

2. The aircraft drop tank ring rib structure as claimed in claim 1, wherein: a first lightening hole (203) is formed in the supporting arc section (202) along the axial direction of the ring rib (200);

the number of the first lightening holes (203) is a plurality of the first lightening holes which are uniformly distributed.

3. The aircraft drop tank ring rib structure as claimed in claim 2, wherein: a second lightening hole (204) is formed in the supporting arc section (202) along the radial direction of the ring rib (200);

the number of the second lightening holes (204) is a plurality of the second lightening holes which are uniformly distributed.

4. The aircraft drop tank ring rib structure as claimed in claim 3, wherein: the diameter of the first lightening hole (203) is larger than that of the second lightening hole (204).

5. The aircraft drop tank ring rib structure of claim 4, wherein: the first lightening holes (203) are in a conical shape with a narrow inner part and a wide outer part.

6. The aircraft drop tank ring rib structure of claim 5, wherein: the first lightening hole (203) and the second lightening hole (204) are inclined holes which are obliquely arranged along the wall thickness of the support arc section (202).

7. The aircraft drop tank ring rib structure as claimed in claim 6, wherein: the ring rib (200) is of a hollow ring structure.

8. An aircraft drop tank ring rib structure according to claim 7, wherein: the cross section of the connecting arc section (201) and the cross section of the supporting arc section (202) are both trapezoidal with wide inside and narrow outside.

9. An aircraft drop tank ring rib structure according to claim 8, wherein: the supporting arc section (202) is provided with a reinforcing rib (205) along the radial direction of the annular rib (200).

Technical Field

The invention belongs to the technical field of aircraft auxiliary fuel tank supporting pieces, and particularly relates to an aircraft auxiliary fuel tank ring rib structure.

Background

The airplane auxiliary fuel tank is a fuel tank which is hung below the fuselage or wing of an airplane, has a thick middle part and two sharp ends and is in a streamline shape. The auxiliary fuel tank can be hung to increase the voyage and endurance time of the airplane, and when the airplane is in air battle, the auxiliary fuel tank can be thrown away if necessary, so that the airplane can be put into battle with better maneuverability.

In the prior art, the auxiliary oil tank shell is made of metal materials so as to improve the strength of the whole shell, and the shell has strong impact resistance. Two ring ribs are connected to the inner position of the auxiliary oil tank shell at the lifting lug beam on the outer side face of the auxiliary oil tank shell so as to improve the supporting force of the lifting lug beam.

However, the secondary fuel tank shell is made of metal materials, so that the whole shell is heavy in weight and poor in impact resistance. The existing annular rib is of an annular structure, the wall thickness of each position of the annular rib along the annular direction is the same, and the supporting force of each position of the annular rib along the annular direction is the same; and the ring muscle is when supporting the lug roof beam, mainly relies on the upper portion segmental arc to support, and the holding power of lower part segmental arc is less, can not receive the atress even, will lead to the weight of whole ring muscle heavy like this, and support intensity is low.

Disclosure of Invention

In view of the above, the invention aims to provide an aircraft auxiliary fuel tank ring rib structure to solve the problems that in the prior art, an auxiliary fuel tank shell is made of a metal material, so that the weight is heavy and the impact resistance is poor; the wall thickness homogeneous phase of each position of ring muscle along the annular direction is the same, and the holding power of each position is the same, and when supporting the lug roof beam, the support of upper portion segmental arc is strong, and lower part segmental arc atress is less, need not the atress even, leads to the heavy problem that support intensity is low of whole ring muscle.

In order to achieve the purpose, the technical scheme of the invention is realized as follows:

an annular rib structure of an aircraft auxiliary fuel tank comprises an auxiliary fuel tank shell and an annular rib;

the auxiliary oil tank shell is made of composite materials;

the ring rib is arranged on the side surface of the lug beam in the front section of the auxiliary oil tank shell;

the wall thickness in the ring of the ring rib is gradually increased from the lower arc section to the upper arc section along the annular direction, so that the lower arc section of the ring rib is a connecting arc section with smaller wall thickness, and the upper arc section of the ring rib is a supporting arc section with larger wall thickness; the ring rib is a variable cross-section eccentric ring structure.

Furthermore, a first lightening hole is formed in the supporting arc section along the axial direction of the ring rib;

the number of the first lightening holes is a plurality of the first lightening holes which are uniformly distributed.

Furthermore, a second lightening hole is formed in the supporting arc section along the radial direction of the ring rib;

the number of the second lightening holes is a plurality of second lightening holes which are uniformly distributed.

Further, the diameter of the first lightening hole is larger than that of the second lightening hole.

Further, the first lightening holes are in a conical shape with a narrow inner part and a wide outer part.

Furthermore, the first lightening hole and the second lightening hole are inclined holes which are obliquely arranged along the wall thickness of the supporting arc section.

Furthermore, the ring rib is a hollow ring structure.

Furthermore, the cross section of the connecting arc section and the cross section of the supporting arc section are both trapezoidal with wide inside and narrow outside.

Furthermore, the supporting arc section is provided with a reinforcing rib along the radial direction of the ring rib.

Compared with the prior art, the ring rib structure of the aircraft auxiliary fuel tank has the following advantages:

the auxiliary oil tank shell is made of composite materials, and the whole auxiliary oil tank shell is light in weight, high in strength and good in impact resistance; the ring rib is arranged on the side surface of the lug beam in the front section of the auxiliary oil tank shell to support the position of the lug beam; the wall thickness in the ring of the ring rib is gradually increased from the lower arc section to the upper arc section along the annular direction, so that the lower arc section of the ring rib is a connecting arc section with smaller wall thickness, and the part of the arc section only plays a role in connection; the upper arc section of the ring rib is a supporting arc section with larger wall thickness, the partial arc section can play a supporting role, and supporting stress points are concentrated on the supporting arc section, so that the supporting force of the part is strong; the ring rib forms the structure of variable cross section eccentric ring, and when using, the light in weight of whole ring rib supports the intensity height.

Drawings

The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate an embodiment of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:

FIG. 1 is a schematic view of a ring rib structure of an auxiliary fuel tank of an aircraft in an embodiment of the invention in a use state;

FIG. 2 is a front view of a ring rib in an embodiment of the present invention;

FIG. 3 is a schematic structural diagram of a ring rib according to an embodiment of the present invention;

fig. 4 is a partially cut-away schematic view of a ring rib in an embodiment of the invention.

Description of reference numerals:

100-a secondary tank housing; 200-ring ribs;

201-connecting arc segments; 202-supporting arc segment;

203-first lightening holes; 204-second lightening holes;

205-reinforcing ribs.

Detailed Description

It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict.

In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "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 used only for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention. Furthermore, the terms "first", "second", etc. are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless otherwise specified.

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 meaning of the above terms in the present invention can be understood by those of ordinary skill in the art through specific situations.

The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.

As shown in fig. 1 to 4, the invention provides an aircraft drop tank ring rib structure, which comprises a drop tank shell 100 and a ring rib 200;

the secondary fuel tank housing 100 is made of a composite material;

the ring rib 200 is arranged at the side position of the lug beam in the front section of the auxiliary oil tank shell 100;

the wall thickness in the ring of the ring rib 200 gradually increases from the lower arc section to the upper arc section along the annular direction, so that the lower arc section of the ring rib 200 is a connecting arc section 201 with smaller wall thickness, and the upper arc section of the ring rib 200 is a supporting arc section 202 with larger wall thickness; the ring rib 200 is a variable cross-section eccentric ring structure.

Specifically, referring to fig. 1, the secondary fuel tank housing 100 is made of a composite material, the composite material reduces the weight of the entire secondary fuel tank housing 100, and the secondary fuel tank housing 100 has high strength and good impact resistance; because the bellytank casing 100 adopts combined material to make, the ring muscle 200 adopts the material of metal to make, and when the internal connection of ring muscle 200 and bellytank casing 100, the laminating is more firm between metal and the combined material, and the leakproofness is better. And when carrying out large-scale production, compare in the prior art, bellytank casing 100 adopts the metal material to make, the bellytank casing 100 of this application adopts combined material to make, has advantages such as production simple process, with low costs, production cycle are short.

Referring to fig. 2, the lower arc segment of the ring rib 200 is a connecting arc segment 201, the upper arc segment is a supporting arc segment 202, and the wall thickness in the ring is gradually increased from the connecting arc segment 201 to the supporting arc segment 202. After the ring rib 200 is installed, the stress of the lower arc section is smaller, even is not stressed, and the wall thickness of the connecting arc section 201 is reduced, so that the weight of the whole ring rib 200 is reduced; and after the ring rib 200 is installed, the thickness of the upper arc section is gradually increased, so that the supporting force of the supporting arc section 202 is improved.

After the ring rib 200 is installed, an eccentric ring structure with a variable cross section with a wide upper part and a narrow lower part is formed, so that the weight of the whole ring rib 200 is reduced, and the supporting force of the upper arc section is improved.

In one embodiment of the present invention, as shown in fig. 2 and 3, the support arc section 202 is provided with a first lightening hole 203 along the axial direction of the ring rib 200;

the number of the first lightening holes 203 is a plurality of the first lightening holes which are uniformly distributed.

Specifically, since the wall thickness of the support arc section 202 in the axial direction is an arc plane structure, the plurality of first lightening holes 203 are formed in the support arc section 202 along the axial direction of the ring rib 200, so that the weight of the entire support arc section 202 is reduced, and the supporting force of the support arc section 202 is not affected.

In practical use, the first lightening holes 203 may be through holes or blind holes.

In one embodiment of the present invention, as shown in fig. 2 and 3, the supporting arc section 202 is provided with a second lightening hole 204 along the radial direction of the ring rib 200;

the number of the second lightening holes 204 is a plurality of the second lightening holes which are uniformly distributed.

Specifically, since the outer peripheral surface of the support arc section 202 is an arc-shaped surface structure, the plurality of second lightening holes 204 are formed in the support arc section 202 along the radial direction of the ring rib 200, so that the weight of the whole support arc section 202 is reduced, and the supporting force of the support arc section 202 is not affected.

In practical use, the second lightening holes 204 may be through holes or blind holes.

In one embodiment of the present invention, as shown in fig. 2 and 3, the diameter of the first lightening hole 203 is larger than that of the second lightening hole 204.

Specifically, since the supporting force in the circumferential direction of the supporting arc 202 is greater than the supporting force in the radial direction of the supporting arc 202, the diameter of the first lightening hole 203 is greater than the diameter of the second lightening hole 204, which not only does not affect the supporting force of the supporting arc 202, but also reduces the weight of the entire supporting arc 202.

In one embodiment of the present invention, the first lightening holes 203 are tapered with a narrow inside and a wide outside.

Specifically, the first lightening holes 203 are arranged in the radial direction of the support arc section 202, and a structure with a narrow inner part and a wide outer part is adopted, so that the support force at the inner side end position of the first lightening holes 203 is not affected, and the support force of the support arc section 202 can be reduced.

In an embodiment of the present invention, each of the first lightening hole 203 and the second lightening hole 204 is an inclined hole obliquely arranged along the wall thickness of the support arc section 202.

Specifically, the first lightening hole 203 and the second lightening hole 204 are both arranged in an inclined hole structure, and the inclined holes can increase the area of the holes, reduce the weight and do not affect the supporting force of the supporting arc section 202.

In one embodiment of the present invention, as shown in fig. 3 and 4, the ring rib 200 is a hollow ring structure.

Specifically, the ring rib 200 is a hollow structure, so that the weight of the whole ring rib 200 is reduced.

In one embodiment of the present invention, as shown in fig. 3, the cross section of the connecting arc segment 201 and the cross section of the supporting arc segment 202 are both trapezoidal with a wide inside and a narrow outside.

Specifically, the cross section of the connecting arc segment 201 is set to be trapezoidal with the inner width and the outer width, so that the bottom supporting force of the connecting arc segment 201 is not affected, the outer part of the connecting arc segment 201 is narrow, and the outer connecting structure is not affected.

The cross section of the supporting arc section 202 is in a trapezoid shape with a wide inner part and a narrow outer part, so that the supporting force at the bottom of the supporting arc section 202 is not affected, the outer part of the supporting arc section 202 is narrow, the concentration of the supporting force at the outer part is ensured, and the supporting force is strong.

In one embodiment of the present invention, as shown in fig. 3, the support arc 202 is provided with a reinforcing rib 205 along a radial direction of the ring rib 200.

Specifically, on the supporting arc section 202, reinforcing ribs 205 are respectively arranged on two sides of the plurality of first lightening holes 203, and the supporting arc section 202 is reinforced and fixed by the two reinforcing ribs 205, so that the strong supporting force at two side positions of the plurality of first lightening holes 203 is ensured.

The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.