阅读说明：本技术 一种弹射用固体火箭发动机的连接裙装置及连接方法 (Connecting skirt device and connecting method of solid rocket engine for ejection ) 是由 余明敏 郑磊 周睿 王亚洲 高列义 赵飞 钟志文 周子翔 李莹 杨渊 于 2021-08-03 设计创作，主要内容包括：本申请涉及一种弹射用固体火箭发动机的连接裙装置及连接方法,该装置为环形多层结构,其包括铝合金裙和缠绕层。铝合金裙的内外两侧面分别铺设有第一弹性层和第二弹性层,缠绕层包括碳纤维方格布层和环向层,碳纤维方格布层铺设于第二弹性层的外侧面,环向层设置于碳纤维方格布层的外侧面,环向层为碳纤维缠绕成型。第一弹性层的内侧面与发动机壳体的外表面过盈配合。该装置通过相应材料特性和工艺,增加了各层与铝合金裙以及发动机壳体之间的粘贴强度,保证了结构完整性,能避免由于导弹在飞行或弹射的过程中,连接裙装置出现破坏或与发动机脱离,导致发动机无法继续为导弹传递推力或荷载的情况。(The application relates to a connecting skirt device and a connecting method of a solid rocket engine for ejection, wherein the device is of an annular multilayer structure and comprises an aluminum alloy skirt and a winding layer. First elastic layer and second elastic layer have been laid respectively to the inside and outside both sides face of aluminum alloy skirt, and the winding layer includes carbon fiber square check cloth layer and hoop layer, and the lateral surface on second elastic layer is laid to carbon fiber square check cloth layer, and the hoop layer sets up in the lateral surface on carbon fiber square check cloth layer, and the hoop layer is carbon fiber winding shaping. The inner side surface of the first elastic layer is in interference fit with the outer surface of the engine shell. The device increases the bonding strength between each layer and the aluminum alloy skirt and between each layer and the engine shell through corresponding material characteristics and processes, ensures the structural integrity, and can avoid the situation that the engine cannot continuously transmit thrust or load for the missile due to the fact that the connecting skirt device is damaged or separated from the engine in the process of flying or ejecting the missile.)

1. The utility model provides a launch and use solid rocket engine's connection skirt device, is ring structure, its characterized in that: it comprises an aluminum alloy skirt (1) and a winding layer;

the aluminum alloy skirt (1) is of an annular structure, and a first elastic layer (4) and a second elastic layer (5) for buffering are respectively paved on the inner side surface and the outer side surface of the aluminum alloy skirt;

the winding layer comprises a carbon fiber square cloth layer (2) and an annular layer (3), the carbon fiber square cloth layer (2) is laid on the outer side face of the second elastic layer (5), the annular layer (3) is arranged on the outer side face of the carbon fiber square cloth layer (2), and the annular layer (3) is formed by winding carbon fibers;

the inner side surface of the first elastic layer (4) is in interference fit with the outer surface of the engine shell (6).

2. A connecting skirt device for a solid rocket engine for catapults according to claim 1, wherein:

the radial section of the aluminum alloy skirt (1) is L-shaped, and the outer side of an L-shaped short edge (11) is provided with a threaded hole for being in threaded connection with other cabin sections of the rocket;

l type long limit (12) divide into first section (121) and second section (122), lay respectively in first elastic layer (4) and second elastic layer (5) the inside and outside both sides face of first section (121), second section (122) are connected with short edge (11) of L type, just the length of first section (121) is greater than second section (122).

3. A connecting skirt device for a solid rocket engine for catapulting according to claim 2, wherein: aluminum alloy skirt (1) is provided with a plurality of radial deformation adaptation grooves (7) that set up, and is a plurality of deformation adaptation groove (7) all are located first section (121), and equidistant setting.

4. A connecting skirt device for a solid rocket engine for catapulting according to claim 2, wherein: and reinforcing blocks (8) are arranged at the junction of the second section (122) and the short side (11), and the reinforcing blocks (8) are arranged at equal intervals.

5. The connecting skirt device of a solid rocket engine for ejection according to claim 4, wherein: and a lightening groove (9) is further formed in the junction of the second section (122) and the short side (11), the lightening groove (9) is a strip-shaped groove and is arranged between every two adjacent reinforcing blocks (8).

6. A connecting skirt device for a solid rocket engine for catapults according to claim 1, wherein: the carbon fiber square cloth layer (2) is a T300/T700 carbon fiber woven product and has 5 layers in total.

7. A connecting skirt device for a solid rocket engine for catapults according to claim 1, wherein: the first elastic layer (4) and the second elastic layer (5) are both nitrile rubber.

8. A method of attaching a connecting skirt device of a solid rocket engine for ejection according to any one of claims 1 to 7, comprising the steps of:

s1, anodizing the surface of the aluminum alloy skirt (1), and then respectively sticking the first elastic layer (4) and the second elastic layer (5) to the inner side surface and the outer side surface of the aluminum alloy skirt (1);

s2, mounting the aluminum alloy skirt (1) with the first elastic layer (4) and the second elastic layer (5) to the outer surface of the engine shell (6);

s3, adhering the carbon fiber square cloth layer (2) to the outer side surface of the second elastic layer (5);

and S4, winding the annular layer (3) on the outer side surface of the carbon fiber square cloth layer (2) in the annular direction, and fixing the aluminum alloy skirt (1) on the engine shell.

9. The connecting method according to claim 8, wherein: the step S1 further includes:

the first elastic layer (4) and the second elastic layer (5) are adhered to the aluminum alloy skirt (1) manually, and are preformed in an adhering area in a vacuum bag pressurization and curing mode after adhesion is finished, and then cured in a hot pressing tank mode.

10. The connecting method according to claim 8, wherein: in the step S3, 5 layers of carbon fiber square cloth layers (2) are adhered, after each layer is adhered, the carbon fiber square cloth layers are compacted in a hoop winding mode and then adhered to the next layer, and the carbon fiber square cloth layers (2) are T300/T700 carbon fiber woven products.

Technical Field

The application relates to the technical field of aerospace power, in particular to a connecting skirt device and a connecting method of a solid rocket engine for ejection.

Background

In the process of guided missile flight, thrust and ejection load generated by the engine are transmitted to the missile body through the skirt connection area of the engine, so that the skirt connection area is the area with the most severe stress in the process of guided missile flight. A large number of missile flight experiments and shell axial pressure experiments of the engine show that the shell damage of the engine is mostly caused by the failure of a connecting skirt device in the shell. In addition, the peak load of the missile in the launching process is far larger than the load of the missile in the flying process, and the connecting skirt device in the shell of the conventional solid rocket engine is easy to damage or separate from the engine (namely the connecting skirt device fails) under the action of impact load, so that the engine cannot continuously transmit thrust or load to the missile.

In order to meet the requirement that the solid rocket engine can normally work in the ejection environment and transmit thrust or load for the missile, the connecting skirt device of the solid rocket engine for ejection needs to be developed.

Disclosure of Invention

The embodiment of the application provides a connecting skirt device of a solid rocket engine for ejection and a connecting method, so that the connecting skirt device is prevented from being damaged or separated from the engine in the process of flying or ejecting a missile, and the problem that the engine cannot continuously transmit thrust or load to the missile is further avoided.

The embodiment of the application provides a connecting skirt device of a solid rocket engine for ejection, which is of an annular structure and comprises an aluminum alloy skirt and a winding layer;

the aluminum alloy skirt is of an annular structure, and a first elastic layer and a second elastic layer for buffering are respectively paved on the inner side surface and the outer side surface of the aluminum alloy skirt;

the winding layer comprises a carbon fiber square cloth layer and an annular layer, the carbon fiber square cloth layer is laid on the outer side face of the second elastic layer, the annular layer is arranged on the outer side face of the carbon fiber square cloth layer, and the annular layer is formed by winding carbon fibers;

the inner side surface of the first elastic layer is in interference fit with the outer surface of the engine shell.

Furthermore, the radial section of the aluminum alloy skirt is L-shaped, and a threaded hole is formed in the outer side of the short edge of the L-shaped skirt and is used for being in threaded connection with other cabin sections of the rocket;

the L-shaped long edge is divided into a first section and a second section, the first elastic layer and the second elastic layer are respectively laid on the inner side surface and the outer side surface of the first section, the second section is connected with the short edge of the L-shaped long edge, and the length of the first section is larger than that of the second section.

Further, the aluminum alloy skirt is provided with a plurality of deformation adaptation grooves that radially set up, a plurality of deformation adaptation grooves all are located first section, and equidistant setting.

Furthermore, reinforcing blocks are arranged at the junction of the second section and the short side and are arranged at equal intervals.

Furthermore, a lightening groove is further formed in the junction of the second section and the short edge, is a strip-shaped groove and is arranged between every two adjacent reinforcing blocks.

Further, the carbon fiber square cloth layer is a T300/T700 carbon fiber woven product, and the total number of the layers is 5.

Further, the first elastic layer and the second elastic layer are both nitrile rubber.

The present application also provides a method of attaching a connecting skirt device of a solid rocket engine for ejection according to any one of claims 1 to 7, comprising the steps of:

s1, anodizing the surface of the aluminum alloy skirt, and then respectively sticking the first elastic layer and the second elastic layer to the inner side surface and the outer side surface of the aluminum alloy skirt;

s2, mounting the aluminum alloy skirt with the first elastic layer and the second elastic layer on the outer surface of the engine shell;

s3, adhering the carbon fiber square cloth layer to the outer side surface of the second elastic layer;

and S4, winding the annular layer on the outer side surface of the carbon fiber square cloth layer in the annular direction, and fixing the aluminum alloy skirt on the engine shell.

Further, the step S1 further includes:

the first elastic layer and the second elastic layer are both adhered to the aluminum alloy skirt in a manual mode, and are preformed in an adhering area in a vacuum bag pressurization curing mode after the adhesion is finished, and then are cured in a hot pressing tank mode.

Further, in the step S3, 5 layers of carbon fiber square cloth layers are adhered, after each layer is adhered, the carbon fiber square cloth layers are pressed in a hoop winding manner, and then the next layer is adhered, and the carbon fiber square cloth layers are T300/T700 carbon fiber woven products.

The beneficial effect that technical scheme that this application provided brought includes:

the embodiment of the application provides a connecting skirt device and a connecting method of a solid rocket engine for ejection, the device is of a multilayer structure, an elastic layer plays a role in buffering and can reduce the deformation degree of an aluminum alloy skirt, a circumferential layer can ensure that the aluminum alloy skirt is fully contacted with an engine shell, a carbon fiber square grid cloth layer can transmit ejection impact force to increase the bonding strength between layers, the carbon fiber square grid cloth layer cannot be easily damaged, the structural integrity is ensured, the engine shell and other cabin sections of the rocket can be more firmly connected together, and the engine can normally transmit thrust or load.

Drawings

In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings needed to be used in the description of the embodiments are briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.

Fig. 1 is a schematic radial cross-section of the present invention.

Fig. 2 is a schematic view of the present invention mounted to an engine housing.

Fig. 3 is a schematic view of the aluminum alloy skirt of fig. 1.

Reference numerals:

1. an aluminum alloy skirt; 11. a short side; 12. a long side; 121. a first stage; 122. a second stage; 2. a carbon fiber square cloth layer; 3. a circumferential layer; 4. a first elastic layer; 5. a second elastic layer; 6. an engine housing; 7. a deformation adapting groove; 8. a reinforcing block; 9. and a weight reduction groove.

Detailed Description

In order to make the objects, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are some embodiments of the present application, but not all embodiments. 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 application.

The embodiment of the application provides a connecting skirt device of a solid rocket engine for ejection, which can avoid the situation that the engine cannot continuously transmit thrust or load to a missile due to the fact that the connecting skirt device is damaged or separated from the engine in the process of flying or ejecting the missile.

As shown in figure 1, the connecting skirt device of the solid rocket engine for ejection is provided, and is of an annular structure and comprises an aluminum alloy skirt 1 and a winding layer.

Wherein, aluminum alloy skirt 1 is the loop configuration, and inside and outside both sides face has laid first elastic layer 4 and second elastic layer 5 that have buffer function respectively.

The winding layer includes carbon fiber square cloth layer 2 and hoop layer 3, and the lateral surface of second elastic layer 5 is laid to carbon fiber square cloth layer 2, and hoop layer 3 sets up in carbon fiber square cloth layer 2's lateral surface, and wherein, hoop layer 3 is carbon fiber winding shaping.

As shown in fig. 2, the inner surface of the first elastic layer 4 is connected to the outer surface of the engine case 6, and the inner diameter thereof is required to be in interference fit with the outer diameter of the engine case 6, and the radius interference is 0.2-1.5 mm.

Further, as shown in fig. 1, in this embodiment, the aluminum alloy skirt 1 is a forged piece 7050, and has an L-shaped radial cross-sectional shape, and a threaded hole is formed in an outer side of a short side 11 of the L-shaped forged piece for being screwed with another cabin section of the rocket, specifically, one surface of the short side 11 is connected with a surface of another cabin section of the rocket, and the surface-to-surface connection mode has a large contact area, so that the aluminum alloy skirt 1 is connected with another cabin section of the rocket more firmly.

The long side 12 of the L-shape is divided into a first section 121 and a second section 122, and the length of the first section 121 is greater than that of the second section 122. The first segment 121 is connected to the second segment 122 by an inclined segment, and the outer side of the second segment 122 protrudes outward from the outer side of the first segment 121.

Specifically, as shown in fig. 1, the first elastic layer 4 is adhered to the inner side surface of the first segment 121, and the second elastic layer 5 is adhered to the outer side surface of the first segment 121, which can ensure that the outer side surfaces of the first segment 121 and the second segment 122 are in a flush state after the adhering is completed, and can save materials. The end of the second L-shaped section 122 is connected to the short side 11 of the L.

In other embodiments, the aluminum alloy skirt 1 may be rectilinear, i.e. without the short side 11 of the inclined section or L-shape.

Further, as shown in fig. 3, the aluminum alloy skirt 1 is further provided with a plurality of deformation accommodating grooves 7, and the plurality of deformation accommodating grooves 7 are radially provided in the L-shaped first segment 121 and are equally spaced. The function of the deformation accommodation grooves 7 is to enable the aluminum alloy skirt 1 to better accommodate or alleviate deformation during attachment to the engine case 6 and during operation.

In the present embodiment, the width of the deformation adaptive groove 7 is 2-5mm, and in other embodiments, the width can be specifically set according to actual conditions.

Further, as shown in fig. 3, a reinforcing block 8 is disposed at a boundary between the second section 122 and the short side 11, and the reinforcing block 8 may be made of an aluminum alloy or other materials. And the shape of boss 8 is the triangular prism body, and its two sides are connected with the second section 122 of aluminum alloy skirt 1 and the inboard of minor face 11 respectively, and boss 8 plays the effect of strengthening to aluminum alloy skirt 1 to the equidistant setting of boss 8 can guarantee to a certain extent that aluminum alloy skirt 1 is even at this weak department atress.

In other embodiments, the stiffener 8 may be a cylinder, a quadrangular prism, or the like.

Furthermore, as shown in fig. 3, a lightening groove 9 is further provided at the boundary of the second section 122 and the short side 11, so that the self weight of the connecting skirt device can be lightened. The lightening grooves 9 are strip-shaped grooves, the number of the lightening grooves is multiple, in the embodiment, the lightening grooves 9 are arranged between every two adjacent reinforcing blocks 8, the two ends of each lightening groove are respectively connected with the reinforcing blocks 8, and in other embodiments, the length of the lightening grooves 9 can be specifically set according to actual conditions.

In this embodiment, the carbon fiber scrim layer 2 may be a T300/T700 carbon fiber woven product, which has 5 layers in total, and has a thickness of 0.1-1.0mm, and is used for transferring the ejection impact force. In other embodiments, the number of layers and the thickness can be specifically set according to actual conditions.

In this embodiment, the first elastic layer 4 and the second elastic layer 5 are made of nitrile rubber, and have relatively high shear strength and elongation at break, so that the first elastic layer 4 and the second elastic layer 5 can buffer and better adapt to deformation between the aluminum alloy skirt 1 and the winding layer. In other embodiments, the first elastic layer 4 and the second elastic layer 5 may be other elastic materials.

In the embodiment, the circumferential layer 3 is formed by winding carbon fibers, and the winding fibers have tension of 30-100N, so that the aluminum alloy skirt 1 can be fully contacted with the engine shell 6.

The application also provides an embodiment of a connecting method, which can be used for the connecting method of the connecting skirt device of the solid rocket engine for ejection, and the method comprises the following steps:

in the first step, the surface of the aluminum alloy skirt 1 is anodized to increase the bonding strength between the aluminum alloy skirt 1 and the first elastic layer 4 and the second elastic layer 5. The first elastic layer 4 is adhered to the inner side surface of the aluminum alloy skirt 1, and the second elastic layer 5 is adhered to the outer side surface of the aluminum alloy skirt 1. Both the first elastic layer 4 and the second elastic layer 5 are green sheets before being pasted, and curing treatment is not required.

Secondly, mounting the aluminum alloy skirt 1 with the first elastic layer 4 and the second elastic layer 5 on the outer surface of the engine shell 6;

thirdly, the carbon fiber square cloth layer 2 is adhered to the outer side surface of the second elastic layer 5.

And fourthly, winding the annular layer 3 on the outer side surface of the carbon fiber square cloth layer 2 in an annular mode, and fixing the aluminum alloy skirt 1 on the engine shell 6.

For the first step in the above connection method, in order to achieve a better pasting effect, the present application also provides a better processing method, which specifically comprises the following steps:

the first elastic layer 4 and the second elastic layer 5 are both adhered to the aluminum alloy skirt 1 in a manual mode, and adhesion needs to be guaranteed to be tight, so that air bubbles or sticking edges cannot be protruded. After the bonding is finished, the bonding area is preformed in a vacuum bag pressurization curing mode, and then cured in a hot pressing tank mode, and the curing can be performed in a 0.3-1.0MPa 70-150 ℃ mode, so that the first elastic layer 4 and the second elastic layer 5 are bonded with the aluminum alloy skirt 1 more firmly.

For the third step in the above connection method, in order to achieve a better pasting effect, the present application also provides a better processing method, which specifically comprises the following steps: because 5 layers are pasted together on carbon fiber check cloth layer 2, in the process of pasting, after pasting each layer, all adopt hoop winding mode to compress tightly, paste next layer again, carbon fiber check cloth layer 2 can be T300/T700 carbon fiber establishment product.

In this embodiment, in order to make the aluminum alloy skirt 1 and the engine case 6 work together better, a certain filling process is required. The deformation accommodating grooves 7 of the aluminum alloy skirt 1 are filled with an elastic material such as rubber. The boundary where the end of the long side 12 of the aluminum alloy skirt 1 is connected to the engine case 6 is filled with carbon fiber so as not to leave a gap after installation.

In the description of the present application, it should be noted that the terms "upper", "lower", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, which are only for convenience in describing the present application and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and operate, and thus, should not be construed as limiting the present application. Unless expressly stated or limited otherwise, the terms "mounted," "connected," and "connected" are intended to be inclusive and mean, for example, that they may be fixedly connected, detachably connected, or integrally connected; 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 application can be understood by those of ordinary skill in the art as appropriate.

It is noted that, in the present application, relational terms such as "first" and "second", and the like, are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element.

The above description is merely exemplary of the present application and is presented to enable those skilled in the art to understand and practice the present application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the application. Thus, the present application is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.