WO2021015699A1

WO2021015699A1 - Canister cover

Info

Publication number: WO2021015699A1
Application number: PCT/TR2020/050624
Authority: WO
Inventors: Gamze KARAMAN ERKEK; Ali İhsan ÖZEK; Gönül Öykü GÜNGÖR
Original assignee: Roketsan Roket Sanayi̇i̇ Ti̇caret A.Ş.
Priority date: 2019-07-23
Filing date: 2020-07-14
Publication date: 2021-01-28
Also published as: TR201910985A2

Abstract

The present invention relates to a cover for a canister comprising an outer frame (24) and a front plate (20) with at least one wing (30) extending radially inwards from the outer frame (24); a coating layer (50) made of a flexible tearable material coating the front plate (20) along the outer frame (24) in a sealing manner. The cover comprises a hinge (26) in the form of a metal plate integrated with the outer frame (24) by way of adjusting the neck portion (38), through which the wing (30) is engaged with the outer frame (24) when a predetermined threshold force value (fe) is exceeded.

Description

CANISTER COVER

TECHNICAL FIELD

The present invention relates to systems with canister, particularly to a canister cover that does not throw a cover piece.

STATE OF THE ART

Canisters are generally used to protect ammunitions from environmental factors, to provide an interface for the purpose of carrying them, and to solve the storage problems throughout their shelf life. Canisters are provided with a sealing structure so as to protect the ammunitions therein from environmental factors. Therefore, the cover design constitutes great importance, when considering the shelf life of the ammunition. The designed cover should both provide a certain level of sealing and should not throw any pieces from the cover, that may cause any damage to air vehicles, particularly in terms of ammunitions that employ air vehicles as their launchers. When the patents granted for canister covers so far are examined, there have been studies relating to cover designs disassembling into small pieces, cover designs that open through a mechanism, cover designs that open by means of the pressure occurring in the canister due to launching and cover designs that are composed of different layers and that open due to fact that the ammunition nose tears through said layers.

In the document US 20060096449A1 , a dome-shaped cover design comprised of different layers is disclosed. The ammunition tears through said layers, while leaving the canister.

In the document US 4,498,368, a cover design that is comprised of layers consisting of two epoxy and fiberglass with each ply being scored in predetermined patterns is disclosed. In addition to said layers, a layer of a Mylar or aluminum is introduced to the design to provide sealing and electromagnetic protection. It is required also in this design that the ammunition should tear through said layers to be launched out of the canister.

BRIEF DESCRIPTION OF THE INVENTION

Aim of the invention is to provide a simple cover for ammunitions with a canister, that does not throw any pieces at the canister outlet.

In order to achieve that aim, the present invention comprises a cover for a canister comprising an outer frame and a front plate with at least one wing extending radially inwards from the outer frame, a coating layer made of a flexible tearable material that seals the front plate hermetically along the outer frame. Furthermore, the cover comprises a hinge in the form of a metal plate integrated with the outer frame by way of adjusting the neck portion, through which the wing is engaged with the outer frame when a predetermined threshold force value (fe) is exceeded. By means of the hinge in the form of a metal plate that is bent outwards under the force, e.g. in the launching pod to which the canister cover is attached, the wing is swiftly bent outwards through the predetermined threshold force value lower than the outward force impacting during launching rocket. Thus, it is provided a sufficient outlet space to launch the rocket and the wing maintains its outwards bent position during and after launching. The threshold force value may be calculated such that it is lower than the force to be occurred during launching the rocket, but high enough to tear through the coating layer, according to the type of the rocket used and the launching pod.

In a preferred embodiment of the invention, it comprises a notch provided on the coating layer in the line of the outer periphery of the wing. The notch ensures that the coating layer is torn easily along the determined length of the notch such that the cover is bent outwards on the hinge during launching. This prevents an uncontrolled breakup on the coating layer.

In a preferred embodiment of the invention, it comprises a channel that is provided on the periphery of the wing and that limits peripherally the neck portion out of the opposite two ends. The channel prevents the wing from jamming to any adjacent side by means of forming an open space around its periphery during bending outwards.

In a preferred embodiment of the invention, the channel comprises at least two T-like cut-outs angular to each other, which is symmetrically provided at the wing plane on the front plate. The structure of the cut-out ensures that the channel is formed at once by means of cutting-out a planar plate (e.g. punch, press brake). By means of the T- like cut-out structure that limits the wing, both the outwards bendable hinge is formed by creating automatically a neck portion on the plate and it is ensured that the wing is formed on the plate in a slice structure.

In a preferred embodiment of the invention, the channel comprises at least three T-like cut-outs being connected through extending from vertical sides, such that it divides the wing into slices being symmetrical to each other on the front plate. This ensures that the front plate distributes equally the tensions to each hinge in the course of launching and thus that it enables the movement of the wings at the same time and approximately at the same amount.

In a preferred embodiment of the invention, it comprises multiple connection holes made on the front plate and through which the coating layer goes such that it adheres. The connection holes ensure that the coating layer is affixed particularly on the wings such that it prevents it from being released from its position during launching. In a possible embodiment, the connection holes may be provided only on the wings. Furthermore, the connection holes may be distributed in a sequential matrix and confusing manner such that there are multiple thereof.

In a preferred embodiment of the invention, it comprises an adaptor in a pipe form positioned such that it covers a mouth portion of the front plate and said adaptor comprises a flange extending outwards, wherein the coating layer is passed its periphery. The adaptor ensures that the front plate may be easily mounted to the launching pod in a replaceable or permanent manner. The front plate, which is prepared as a separate structure, combined with the adaptor may be integrated into a single or multiple launching pod. Furthermore, it becomes easier to apply the coating layer by means of the flange structure. The coating layer is adapted to the flange and may be easily adapted to the front plate in a sealing manner.

In a preferred embodiment of the invention, it comprises a mounting hole provided oppositely on the flange and outer frame and adapted such that the mechanical connection of the adaptor is ensured by means of a connection element to be positioned to the front plate. The mounting hole ensures a solid connection between the front plate and adaptor by means of another connection element such as pin, rivet, or similar.

In a preferred embodiment of the invention, the front plate comprises a uniform flat metal plate formed through cutting out. This ensures to form easily and swiftly the front plate with the wing/s by means of the metal cutting processes.

In a preferred implementation of the invention, it comprises the process steps of making multiple connection holes on the front plate in the form of a uniform flat metal, separating an outer frame comprised by the front plate by cutting out an integral channel such that it contains wings being co-symmetrically to each other having an outwards bendable hinge from a neck portion, connecting the outer frame with an adaptor and fastening a coating layer on the front plate. It is thus possible to provide a canister, of which sealing is ensured at the storage position and wherein precautions are taken to avoid the piece scattering at the launching position.

In a preferred implementation of the invention, the connection holes are distributed in a matrix structure on the wing. This enables the fact that the coating layer is fastened on the wings through multiple points and that it eliminates the risks of diffraction and scattering.

A preferred implementation of the invention is a rocket launching pod comprising a cover for a canister according to the implementations and embodiments described above. BRIEF DESCRIPTION OF THE FIGURES

FIGURE 1 is a perspective view of the metal sheet plate of a representative embodiment of the inventive cover apparatus.

FIGURE 2 is a front view of the cover apparatus in Figure 1 .

FIGURE 3A is a perspective view in the cover-closed state of a representative embodiment of the inventive canister cover.

FIGURE 3B is a perspective view in the opening state of the canister cover shown in Figure 3a during launching.

FIGURE 4 is a front view of the canister cover shown in Figure 3a.

FIGURE 5 is a side view of the canister cover shown in Figure 3a.

DETAILED DESCRIPTION OF THE INVENTION

In this detailed description, the subject matter of the invention is disclosed through references with examples such that it provides a better understanding of the invention without any restrictions.

In Figure 1 , a representative embodiment of the canister cover subject to the invention is shown in a perspective manner before it’s coated. A flange (12) is formed on the front face of an adaptor (10) having a cuff (14) in a short-pipe structure. The rear face of the cuff (14) may be adapted to, e.g. a launching pod through a mechanical connection. The front plate (20) made of a circular flat sheet leans on the flange (12) such that its peripheries are aligned. Four wings (30) are achieved by means of making a channel (32) having four T-like cut-outs (34) perpendicular to each other on the front plate (20). Each wing (30) comprises a hinge (26) between two cut-outs (34) extensions, that is formed with a neck portion between a circular outer frame (24) and itself. Wings (30) are in a diamond shape, that extends symmetrically to each other and are distant to each other, wherein the channel (32) passes therethrough. Multiple connection holes (37) are made in a sequential and matrix structure on a planar wall provided by the wing (30). Connection holes (37) are at an equal distance and are aligned such that they follow each other on the adjacent wings (30). Thus, the wing (32) constitutes an X-like gap between an end portion (35) of each wing (30) and itself.

The flange (12) is connected to the front plate (20) by means of each connection element (60) going over mounting holes (22) provided sequentially on the circular outer frame (24). Thus, the front plate (20) holds on to the adaptor (10) from its radial outer portion and provides an effective anti-release strength against the pressure coming from a mouth (1 1 ) of the adaptor (10) at the launching position. Analogously, as seen in Figure 2, an opposite wing (40) at the opposition of each wing (30), is adapted such that it may be bent in an outwards bending direction (a) when a force more than a threshold force value is applied through its opposite hinge (28) at its connection with the outer frame (24). The threshold force value is high enough to ensure the bending through the thickness and geometry of the sheet and to tear the coating layer at least along a line, such that it is lower than the launching force to be applied during launching the rocket. In an exemplary implementation, the threshold force may be preferred as 100N. The hinge (26) is formed directly from the front plate (20) itself without arranging an additional part and is adjacent to the outer frame (24) at a neck portion (38) of the wing (30).

In Figure 3a, the front plate (20) is shown at a storage position in a state of coated with a flexible and tearable coating layer (50). The coating layer (50) is formed from e.g. a polyurethane material and covers the front plate (20) entirely. A notch (54) extends such that it is aligned with the channel (32) on the coating layer (50). Said notch (54) is achieved by means of thinning the thickness of the coating layer (50) along a line. The notch (54) extends longitudinally adjacent to a periphery (52) such that it passes through the navel on the coating layer (50). A second notch (56) extends in a manner of passing through the center, such that it is aligned to the channel (32) perpendicularly with the notch (54). Thus, the weakest point is achieved adjacent to the end portions (35) on the coating layer (50) at the full circle center of the front plate (20). An outer coating portion (58) of the coating layer (50) is of an entirely planar form. In Figure 3b, the coating layer (50) is shown in a torn-through state during launching. The wing (30) starts to be bent in the outwards bending direction (a) since the threshold force value is exceeded due to the launching force coming from inside the adaptor (10). In the meanwhile, each wing (30) is simultaneously bent from the outer hinge (26) and opposite hinge (28) and tears the outer coating portion (58) along the notch (54). Each wing (30) coated with the coating layer (50) is bent outwards. Thus, a passage clearance widening from a center portion is formed through the fact that the second lateral portion (33) and the first lateral portion (31 ) provided with the notch (54) and the second notch (54), respectively, leaves from the adjoint sides of the coating layer (50) of the adjacent wing (30) through the coating layer (50). Said clearance provides the maximum passage width by means of bending perpendicularly the wing (30) entirely outwards.

In Figure 4, the cover is shown frontally at a sealing storage state. As shown in Figure 4, the notch (54) and the second notch (56) are achieved by means of a V-like channel on the coating layer and they are perpendicular to each other and also have a plus shape.

In Figure 5, the cover is shown in a cross-section. The adaptor (10) comprises a mounting wall (13) widening inwards. Thus, it may be easily adapted to the mounting wall (13), e.g. a launch pod (not shown) passing from the outer end thereof by means of a mechanical connection. The coating layer (50) is in a thin-walled structure and equipped on the flange (12) through its periphery (52). The coating layer (50) may be formed from a polymeric material such as polyurethane that may easily penetrate the connection holes (37) during the curing process and may also be formed any tearable and flexible material that is obtained through textile materials or hybrid combination thereof. The coating layer (50) may be implemented on the front plate (20) such that it is not only applied on both sides, namely the front and rear but also it faces onto only the exterior surface. The coating layer (50) is torn along only the notch (54) by way of pushing the coating layer (50) and wings (30) along the notch from the weakest point at the center through the rocket nose during the launching. The coating layer (50) prevents any piece from being released, such that the wings (30) hold the corresponding connection holes (37). REFERENCE NUMBERS

10 Adaptor 35 End portion

11 Mouth 36 Connection surface

12 Flange 37 Connection hole

13 Mounting wall 38 Neck portion

14 Cuff 40 Opposite wing

20 Front plate 50 Coating layer

22 Mounting hole 52 Periphery

24 Outer frame 54 Notch

26 Flinge 56 Second notch

28 Opposite Hinge 58 Outer coating portion

30 Wing 60 Connection element

31 First lateral portion a Outwards bending direction

32 Channel

33 Second lateral portion

34 Cut-out

Claims

1 - Cover for a canister comprising an outer frame (24) and a front plate (20) with at least one wing (30) extending radially inwards from the outer frame (24), a coating layer (50) made of a flexible tearable material that seals the front plate (20) hermetically along the outer frame (24) characterized in that; the wing (30) comprises a hinge (26) in a metal plate structure form integrated with the outer frame (24) provided such that a neck portion (38), through which it is connected with the outer frame (24), is adjusted to be bent outwards when a predetermined threshold force value is exceeded.

2- Cover according to Claim 1 , characterized in that; the wing (30) comprises a notch (54) provided on the coating layer (50) in the line of its periphery.

3- Cover according to any one of the preceding claims, characterized in that; the wing (30) comprises a channel (32) that is provided on its periphery and that limits peripherally the neck portion (38) out of the opposite two ends.

4- Cover according to Claim 3, characterized in that; the channel (32) comprises at least two T-like cut-outs (34) angular to each other, which is symmetrically provided at the wing plane on the front plate (20).

5- Cover according to Claim 4, characterized in that; the channel (32) comprises at least three T-like cut-outs (34) being connected through extending from vertical sides, such that it divides the wing (30) into slices being symmetrical to each other on the front plate (20).

6- Cover according to any one of the preceding claims, characterized by comprising multiple connection holes (37) made on the front plate (20) and through which the coating layer (50) goes such that it adheres.

7- Cover according to any one of the preceding claims, characterized by comprising an adaptor (10) in a pipe form positioned such that the front plate (20) covers a mouth (11 ) portion and said adaptor (10) comprises a flange (12) extending outwards, wherein the coating layer (50) is passed its periphery.

8- Cover according to Claim 7, characterized by comprising a mounting hole (22) provided oppositely on the flange (12) and outer frame (24) and adapted such that the mechanical connection of the adaptor (10) is ensured by means of a connection element (60) to be positioned to the front plate (20).

9- Cover according to any one of the preceding claims, characterized in that; the front plate (20) comprises a uniform flat metal plate formed through cutting out.

10- A production method of a cover for a canister, characterized by comprising following process steps:

- making multiple connection holes (37) on the front plate (20) in the form of a uniform flat metal,

- separating an outer frame (34) comprised by the front plate (20) by cutting out an integral channel (32) such that it contains wings (30) being co- symmetrically to each other having an outwards bendable hinge (26) from a neck portion (38),

- connecting the outer frame (34) with an adaptor (10), and

- fastening a coating layer (50) on the front plate (20).

11 - A method according to Claim 10, characterized in that; the connection holes (37) are distributed on the wing (30) in a matrix structure.

12- Rocket launching pod comprising a cover for a canister according to any one of the preceding claims.