阅读说明：本技术 一种大外压低冲击力易碎盖 (Large external pressure low impact force frangible cover ) 是由 饶安梅 汪鑫 于 2021-08-30 设计创作，主要内容包括：本发明提供了一种大外压低冲击力易碎盖,包括盖体；所述盖体为圆弧面结构,盖体内凹有多条凹陷的内径向槽,内径向槽位于盖体的等分线上且多条内径向槽相交于圆心。本发明能有效增大外向承压能力；既能实现及时破碎,又能沿沟槽位置破碎；水下承压效果及冲击效果最佳；不仅能提高外向承压能力,又能更好的保证冲击力的传递及有效断裂；内外设置环形沟槽使飞行器顺利出筒更可靠。(The invention provides a fragile cover with high external pressure and low impact force, which comprises a cover body; the lid is the arc surface structure, and the lid indent has many sunken internal radial grooves, and internal radial groove is located the bisector of lid and many internal radial grooves intersect in the centre of a circle. The invention can effectively increase the outward bearing capacity; not only can realize timely crushing, but also can realize crushing along the position of the groove; the underwater pressure bearing effect and the impact effect are optimal; the outward bearing capacity can be improved, and the transmission of impact force and effective fracture can be better ensured; the annular grooves are arranged inside and outside, so that the smooth cylinder discharging of the aircraft is more reliable.)

1. The utility model provides a fragile lid of low impact force of big external pressure, includes the lid, its characterized in that: the cover body is of an arc surface structure, a plurality of concave inner radial grooves (1) are formed in the cover body in an inwards concave mode, the inner radial grooves (1) are located on the bisector of the cover body, and the inner radial grooves (1) are intersected in the circle center.

2. The high external pressure low impact frangible cover of claim 1, wherein: the number of the inner radial grooves (1) is two; the inner radial grooves (1) are uniformly distributed along the circumference.

3. The high external pressure low impact frangible cover of claim 1, wherein: the inner radial grooves (1) in the cover body are intersected with one another, concave inner conical grooves (2) are formed in the positions, and the inner conical grooves (2) are conical.

4. The high external pressure low impact frangible cover of claim 1, wherein: the periphery of the position, close to the edge, of the concave surface in the cover body is provided with a lateral annular convex structure, and a concave inner annular groove (3) is distributed on the lateral annular convex structure.

5. The high external pressure low impact frangible cover of claim 1, wherein: the periphery of the position of the convex surface outside the cover body, which is close to the edge, is provided with a lateral annular convex structure, and the lateral annular convex structure is provided with a concave outer ring groove (5).

6. An external pressure and low impact frangible cover as claimed in claim 4 or 5 wherein: the distribution radius of the inner ring groove (3) is smaller than that of the outer ring groove (5).

7. The high external pressure low impact frangible cover of claim 1, wherein: an inner reinforcing layer (4) is covered on the non-sunken position on the concave surface of the cover body.

8. The high external pressure low impact frangible cover of claim 1, wherein: an outer reinforcing layer (6) is covered on the non-concave position on the convex surface outside the cover body.

9. An external pressure and low impact frangible cover as claimed in claim 7 or 8 wherein: the inner reinforcing layer (4) and the outer reinforcing layer (6) are both made of polyurethane foam materials and are internally provided with metal frameworks.

10. The high external pressure low impact frangible cover of claim 1, wherein: the depth of the inner radial groove (1) is gradually reduced from the circle center to the circumference.

Technical Field

The invention relates to a fragile cover with high external pressure and low impact force.

Background

The frangible cover has a direct impact on the aircraft's shelf life, service and maintenance performance, reaction time on launch, and reliability. The traditional electromechanical cover has complex mechanism, long reaction time and high maintenance and repair cost; the blasting cap is quick in response, but the loading and maintenance procedures are complex, and potential safety hazards exist; in recent years, a fragile lid using a composite material with impact or gas pressure wave as lid opening power has been favored because of its characteristics such as simple structure, light weight, high strength, and corrosion resistance.

Aiming at specific products, the existing fragile cover can not meet the underwater launching requirement, and the main reason is that the external pressure is large in the underwater environment, and the existing fragile cover is easily broken by the external pressure of the underwater environment.

Disclosure of Invention

In order to solve the technical problems, the invention provides the high-external-pressure low-impact-force frangible cover which can effectively increase the outward pressure-bearing capacity, can realize timely crushing and can crush along the groove position.

The invention is realized by the following technical scheme.

The invention provides a fragile cover with high external pressure and low impact force, which comprises a cover body; the lid is the arc surface structure, and the lid indent has many sunken internal radial grooves, and internal radial groove is located the bisector of lid and many internal radial grooves intersect in the centre of a circle.

The number of the inner radial grooves is two; the inner radial grooves are uniformly distributed along the circumference.

The inner radial grooves are arranged in the cover body and are intersected with one another, and the inner radial grooves are concave and conical.

The periphery of the position, close to the edge, of the concave surface in the cover body is provided with a lateral annular convex structure, and concave inner annular grooves are distributed on the lateral annular convex structure.

The periphery of the position of the convex surface outside the cover body, which is close to the edge, is provided with a lateral annular convex structure, and the lateral annular convex structure is provided with a concave outer ring groove.

The distribution radius of the inner ring groove is smaller than that of the outer ring groove.

An inner reinforcing layer is covered at a non-sunken position on the inner concave surface of the cover body.

And an external reinforcing layer is covered on the non-concave position on the convex surface outside the cover body.

The inner reinforcing layer and the outer reinforcing layer are both made of polyurethane foam materials and are internally provided with metal frameworks.

The depth of the inner radial groove is gradually reduced from the circle center to the circumference.

The invention has the beneficial effects that: the outward bearing capacity can be effectively increased; not only can realize timely crushing, but also can realize crushing along the position of the groove; the underwater pressure bearing effect and the impact effect are optimal; the outward bearing capacity can be improved, and the transmission of impact force and effective fracture can be better ensured; the annular grooves are arranged inside and outside, so that the smooth cylinder discharging of the aircraft is more reliable.

Drawings

FIG. 1 is a top view of the present invention;

FIG. 2 is a bottom view of the present invention;

fig. 3 is a side half sectional view of the present invention.

In the figure: 1-inner radial groove, 2-inner cone groove, 3-inner ring groove, 4-inner reinforced layer, 5-outer ring groove, 6-outer reinforced layer.

Detailed Description

The technical solution of the present invention is further described below, but the scope of the claimed invention is not limited to the described.

Example 1

1-3, a high external pressure, low impact frangible cover comprising a cover body; the cover body is of an arc surface structure, a plurality of concave inner radial grooves 1 are formed in the cover body in an inwards concave mode, the inner radial grooves 1 are located on the dividing line of the cover body, and the inner radial grooves 1 intersect at the circle center.

Example 2

Based on the embodiment 1, the number of the inner radial grooves 1 is two; the inner radial grooves 1 are uniformly distributed along the circumference.

Example 3

Based on embodiment 1, the intersecting positions of the plurality of inner radial grooves 1 in the cover body are provided with concave inner conical grooves 2, and the inner conical grooves 2 are conical.

Example 4

Based on embodiment 1, the periphery of the position of the concave surface of the cover body close to the edge is provided with a lateral annular convex structure, and the lateral annular convex structure is provided with a concave inner annular groove 3.

Example 5

Based on embodiment 1, the outer convex surface of the cover body is provided with a lateral annular convex structure at the periphery close to the edge, and the lateral annular convex structure is provided with a concave outer annular groove 5.

Example 6

Based on examples 4 and 5, the distribution radius of the inner ring groove 3 is smaller than that of the outer ring groove 5.

Example 7

Based on the embodiment 1, the non-concave position on the concave surface of the cover body is covered with the inner reinforcing layer 4.

Example 8

Based on the embodiment 1, the non-concave position on the outer convex surface of the cover body is covered with an external reinforcing layer 6.

Example 9

Based on examples 7 and 8, the inner reinforcement layer 4 and the outer reinforcement layer 6 are both made of polyurethane foam and have a metal skeleton built therein.

Example 10

Based on embodiment 1, the depth of the inner radial groove 1 gradually decreases from the center of the circle to the circumference.

Example 11

Based on above-mentioned embodiment, the lid appearance is the spherical crown shape, and the smooth transition of spherical crown is to the flange face, and is whole just like iron pan structure. The inner center of the inner part is a multi-angle conical groove, so that the arc surface of the tip is effectively superposed with the central cone of the frangible cover; 2 radial grooves are uniformly distributed on the inner arc surface of the groove, the groove is in a petal shape, and the intersection point of the grooves is superposed with the center of the conical groove; the inner end face and the outer end face of the inner part are provided with annular grooves, wherein the inner annular groove is intersected with the 2 radial grooves, and the positions of the inner annular groove and the outer annular groove are staggered, so that the cover opening by collision is facilitated; fiber reinforced layers are arranged inside and outside the fragile cover. The density of the rigid polyurethane foam material is 0.3g/cm³～0.5g/cm³。

The depth of the radial groove is gradually reduced from the center of the petal to the end face, preferably the depth is 5 mm-14 mm, the width is 3 mm-7 mm, and the groove is U-shaped. The depth of the annular groove is 5 mm-12 mm, the width of the groove is 3 mm-7 mm, and the groove is U-shaped. The depth of the conical grooves is consistent with the depth of the intersection points of the radial grooves. Experiments prove that the fragile cover with the structure can bear large external pressure, and can be broken according to the preset groove under the action of low impact force, so that the aircraft can smoothly go out of the cylinder.

In general, a typical method of forming the above-described embodiment is as follows:

and cutting the fiber cloth according to the inner and outer shapes of the fragile cover, and heating the fiber cloth after silk drawing treatment so as to facilitate penetration of the polyurethane foam material. After the forming die is heated, fiber cloth is respectively stuck in the cavity of the upper die and the cavity of the lower die, and the fiber cloth is stuck at the position avoiding all the grooves. After the fiber cloth is pasted, the polyurethane raw material is poured so that the two materials are integrally formed.