阅读说明：本技术 一种分瓣式悬抛整流罩结构 (Split type suspension casting fairing structure ) 是由 何爱颖 张伟方 谢雪明 任广为 刘广宁 徐然 于 2020-10-29 设计创作，主要内容包括：本发明公开一种分瓣式悬抛整流罩结构。整流罩结构包括端头帽、锥段、柱段及集中力扩散段；其中端头帽采用分瓣式的玻璃钢结构,锥段和柱段采用分瓣式蜂窝夹层结构,集中力扩散段采用分瓣式蒙皮桁条结构,并在集中力扩散段安装分离弹簧和悬抛铰链。横向方向分瓣的各段通过螺钉连接,纵向方向通过爆炸螺栓将两瓣结构连接为一体。整流罩与箭体通过横向爆炸螺栓连接。当箭体与整流罩分离时,横向、纵向爆炸螺栓启爆,整流罩在弹簧力的作用下,沿着铰链转轴进行旋转及分离,实现整流罩与箭体的分离。在轴压和外压联合作用的情况下,该整流罩结构形式具有质量小、结构效率高、加工工艺性好、加工周期短、成本低等优点。关键词：整流罩,蜂窝夹层,悬抛。(The invention discloses a split type suspension throwing fairing structure. The fairing structure comprises an end cap, a conical section, a column section and a concentrated force diffusion section; the end cap is of a split glass fiber reinforced plastic structure, the cone section and the column section are of a split honeycomb sandwich structure, the concentrated force diffusion section is of a split skin-stringer structure, and a separation spring and a suspension hinge are mounted on the concentrated force diffusion section. The sections of the transverse valving are connected through screws, and the two valving structures are connected into a whole through explosive bolts in the longitudinal direction. The fairing is connected with the arrow body through a transverse explosion bolt. When the rocket body is separated from the fairing, the transverse and longitudinal explosion bolts are exploded, and the fairing rotates and separates along the hinge rotating shaft under the action of the spring force, so that the fairing is separated from the rocket body. Under the combined action of axial pressure and external pressure, the structural form of the fairing has the advantages of small mass, high structural efficiency, good processing manufacturability, short processing period, low cost and the like. Key words: fairing, honeycomb sandwich and suspension throwing.)

1. The utility model provides a split type hangs and throws radome fairing structure which characterized in that: the structure comprises an end cap 1, a conical section 2, a column section 3, a concentrated force dispersion section 4 and a longitudinal separation assembly 5;

the end cap 1 consists of two half covers, wherein each half cover comprises a shell 102, a bottom butt joint frame 101, an end reinforcing frame 103 and the like;

the conical section 2 consists of two half covers, wherein each conical section half cover comprises a panel 207, a honeycomb core 206, an end frame, a reinforcing frame 205, a cushion block 204 and the like;

the column section 3 consists of two half covers, wherein each half cover comprises a panel 307, a honeycomb core 306, an end frame, a reinforcing frame 305, a cushion block 304 and the like;

the concentrated force dispersing section 4 consists of two half covers, and the concentrated force dispersing section half cover comprises a skin 404, a stringer 402, an end frame, a separation spring assembly 6, a hinge 8, a transverse explosion bolt box 7 and the like; the separation spring assembly 6 comprises a spring bracket 601, a locking screw 602, a push rod 603, a mandrel 604, a spring 605 and the like;

the longitudinal separation assembly 5 comprises a longitudinal explosion bolt box 1(501), an explosion bolt 502, a nut (503) and a longitudinal explosion bolt box 2 (504).

2. The end cap of claim 1 wherein: the casing adopts the glass steel material that prevents to insulate against heat effectually, and the joint frame adopts aluminum alloy material with the strengthening frame, guarantees the joint strength and the rigidity of end cap, and the casing adopts countersunk screw with joint frame and strengthening frame to be connected, guarantees the smoothness nature on casing surface, reduces rocket body flight resistance and local pneumatic heating.

3. The cone segment of claim 1 wherein: the cone section adopts a honeycomb sandwich structure, and materials of the panel and the honeycomb core can be optimally selected according to the size of the load; the connecting part is reinforced by adopting an end frame made of aluminum alloy and a reinforcing frame and a cushion block, and the reinforcing frame and the cushion block can be optimally designed according to the load; the reinforcing frame, the cushion block, the end frame and the panel are connected through screws or rivets, the panel is connected with the honeycomb core through glue joint, and curing is carried out through hot-pressing pouring.

4. The column section of claim 1, wherein: the column section also adopts a honeycomb sandwich structure, and the structures of the honeycomb sandwich structure, the end frame and the like are consistent with the conical section for the convenience of production, processing and assembly.

5. The concentrated force dispersing section of claim 1, wherein: the concentrated force dispersing section needs to bear larger axial force, concentrated force of a transverse separation spring and hinge moment which is hung and thrown along a hinge rotating shaft when the fairing is separated, the structural form is a skin-stringer structure, and the thickness of the skin and the shape and distribution of the section of the stringer can be optimally designed according to the size of load; the covering is connected with the stringers, the end frames, the transverse explosion bolt boxes and the like through rivets, in order to facilitate the tightening of the transverse explosion bolts, an installation operation opening is formed in the covering, and the opening frames are used for sealing after the explosion bolts are tightened.

6. The breakaway spring assembly of claim 1, wherein: the spring bracket 601 is riveted on the skin 404 through a rivet, the push rod 603, the mandrel 604 and the spring 605 are connected into a whole through a locking screw 602, and the elasticity of the spring can be adjusted by screwing the locking screw; after being adjusted, the spring support 601 is mounted on the base through a screw; after the fairing is mounted on the arrow body, the locking screw 602 is removed, so that the elastic force of the spring 605 can be transmitted to the arrow body through the push rod 603.

7. The separation spring assembly of claims 1 and 6, wherein: the spring assembly 6 is arranged in quadrants II and IV of the concentrated force dispersing section 4, and the hinge 8 is arranged in quadrant I, III of the concentrated force dispersing section 4, so that the elastic force of the spring is ensured to provide larger rotating moment of the fairing.

8. The longitudinal separation assembly of claims 1, 6, wherein: explosive bolt boxes 1(501) and explosive bolt boxes 2(504) are arranged on two sides of the explosive bolt 502 to prevent the remains of the explosive bolt 502 after the explosive separation from falling and touching parts such as instruments and equipment.

Technical Field

The invention belongs to the technical field of rocket projectiles, carrier rockets and the like, and particularly relates to a split type suspension throwing fairing structure.

Background

The fairing is located at the forward most end of the arrow body. When the rocket flies in the atmosphere, the fairing mainly plays a role in maintaining the appearance of the rocket body, protecting the load and the like. After the rocket flies out of the atmosphere, the task of protecting the load is completed, and in order to improve the efficiency, increase the carrying capacity of the rocket and make the release passage of the load free, the fairing needs to be thrown away. The cowlings are generally made up of two clamshell structures connected together by a locking mechanism. To achieve separation of the two clamshell halves, a separating mechanism is also necessary on the fairing. The separation mode comprises transverse horizontal pushing and rotary separation; the separation energy comprises a shooting barrel, a pollution-free detonating fuse, a spring and the like.

During the flight of the rocket, the fairing mainly bears bending moment formed by wind shear, transverse shear, overload during accelerated flight, internal pressure and external pressure. Under these external loads, the structure of the fairing should meet the following requirements: firstly, the material has enough strength, and instability and strength damage are avoided; secondly, the fairing has enough rigidity and does not deform greatly, so that the fairing is prevented from colliding with the load; and thirdly, the two half covers are reliably locked and separated, and the collision between the two half covers and a load and an arrow body is avoided in the separation process.

Common fairing structures are a semi-hard shell structure and a honeycomb sandwich structure, the semi-hard shell structure can bear large axial pressure, and the fairing structure has good rigidity but low structural efficiency. The honeycomb sandwich structure has high efficiency and large specific rigidity, but has poor bearing capacity of axial pressure and concentration force. In order to enable the fairing to bear large axial pressure and enable the fairing to be high in structural efficiency, the two structural forms are combined, a semi-hard shell structure is adopted in a section with large axial pressure and small external pressure, and a honeycomb sandwich structure is adopted in a section with small axial pressure and large external pressure.

Disclosure of Invention

In view of the above, the invention provides a split type suspension-throwing fairing structure, the separation mode adopts suspension-throwing separation, the separation energy comes from the elastic force of a spring, and the structure adopts a form of combining a honeycomb sandwich structure and a skin-stringer structure. The fairing can bear large combined acting force of axial pressure and external pressure and can bear concentrated load on a transverse separation point, and has the advantages of small mass, high structural efficiency, good processing manufacturability, short processing period, low cost, reliable separation and the like.

A split type suspension throwing fairing structure is composed of four cabin sections, namely an end cap, a conical section, a column section and a concentrated force dispersion section; the fairing is divided into two half shrouds, a half shroud I and a half shroud III, the two half shrouds are symmetrical about quadrants II-IV, all cabin sections on the half shrouds are connected through screws, and the half shrouds are connected through longitudinal explosion bolts. And the separation springs are arranged at the quadrants II and IV, and hinges are arranged at the quadrants I and III. When the fairing is separated, the transverse and longitudinal explosion bolts are exploded, and the two half shrouds rotate around the hinge rotating shaft to be separated under the elastic force action of the separation spring, so that the fairing is separated from the rocket body.

The end cap consists of two half covers, wherein each half cover comprises a shell, a bottom butt joint frame, an end reinforcing frame and the like;

the conical section consists of two half covers, and the conical section half cover comprises a panel, a honeycomb core, an end frame, a reinforcing frame, a cushion block and the like;

the column section consists of two half covers, and the column section half cover comprises a panel, a honeycomb core, an end frame, a reinforcing frame, a cushion block and the like;

the concentrated force dispersing section consists of two half covers, and the concentrated force dispersing section half cover comprises a skin, a stringer, an end frame, a spring assembly, a hinge, a transverse explosion bolt box and the like; the spring assembly comprises a spring bracket, a locking screw, a push rod, a mandrel, a spring and the like.

When the fairing is separated, the debris after separation of the explosive bolts needs to be protected in order to prevent the debris from falling and touching parts such as instruments and equipment. Mounting an explosive bolt box 1 and an explosive bolt box 2 at two sides of a longitudinal explosive bolt; a transverse separation explosion bolt box is arranged at the transverse explosion bolt, so that a nut of the transverse explosion bolt is convenient to install, an installation operation opening is formed in a skin of the concentrated force dispersion section, and the transverse separation explosion bolt box is arranged on the inner surface of the skin, so that the nut is prevented from falling into a cabin in the screwing process, and remains after explosion are prevented from falling into the cabin.

In order to ensure that the cowlings are separated smoothly and a large rotating moment is obtained during separation, the separation spring is symmetrically arranged at a position far away from the hinge rotating shaft.

Drawings

FIG. 1 is a view showing the structure of the present invention

FIG. 2 is a front view and a side view of the present invention

FIG. 3 is a schematic view of the end cap half-cover of the present invention

FIG. 4 is a cross-sectional view of the end cap half-shell of the present invention

FIG. 5 is a view of the structure of the conical section half cover of the present invention

FIG. 6 is a schematic view of a half-cover column section according to the present invention

FIG. 7 is a view showing the structure of the concentration force dispersing half cover according to the present invention

FIG. 8 is a view of the longitudinal separator assembly of the present invention

FIG. 9 is a view showing the construction of the longitudinal explosion bolt case 1 of the present invention

FIG. 10 is a view showing the construction of the longitudinal explosion bolt housing 2 of the present invention

FIG. 11 is a view of the split spring assembly of the present invention

Wherein, 1-end cap, 2-conical section, 3-column section, 4-concentrated force dispersion section, 5-longitudinal separation component, 6-separation spring component, 7-transverse explosion bolt box, 8-hinge;

101-a butt joint frame at the bottom of the end cap, 102-an end cap shell and 103-a reinforcing frame at the end part of the end cap;

201-upper end frame of conical section, 202-longitudinal end frame of conical section, 203-lower end frame of conical section, 204-cushion block, 205-reinforcing frame, 206-honeycomb core,

207-a panel;

301-column section upper end frame, 302-column section longitudinal end frame, 303-column section lower end frame, 304-cushion block, 305-reinforcing frame, 306-honeycomb core,

307-a panel;

401-upper end frame, 402-stringer, 403-lower end frame, 404-skin, 405-mouth frame;

501-longitudinal explosive bolt box 1, 502-explosive bolt, 503-nut, 504-longitudinal explosive bolt box 2;

601-spring support, 602-locking screw, 603-push rod, 604-mandrel, 605-spring;

Detailed Description

The invention is described in detail below by way of example with reference to the accompanying drawings.

As shown in fig. 1 and 2, the invention provides a split type suspension throwing fairing structure, which comprises a head cap 1, a conical section 2, a column section 3, a concentrated force dispersion section 4, a longitudinal separation assembly 5, a separation spring assembly 6, a transverse explosion bolt box 7 and a hinge 8;

the end cap 1 consists of two half covers, the structure of which is shown in figures 3 and 4 and comprises a shell 102, a bottom butt joint frame 101, an end reinforcing frame 103 and the like; in the rocket flying process, the end cap is heated pneumatically more seriously, the shell 102 is made of glass fiber reinforced plastics with good heat insulation effect, the bottom butt joint frame 101 and the end reinforcing frame 103 are made of aluminum alloy sections, and the shell 102 is connected with the bottom butt joint frame 101 and the end reinforcing frame 103 through countersunk screws.

The cone section 2 is composed of two half covers, the structure of the cone section half cover is shown in FIG. 5, and the cone section half cover comprises a panel 207, a honeycomb core 206, an end frame, a reinforcing frame 205, a cushion block 204 and the like, wherein the end frame comprises an upper end frame 201, a lower end frame 203 and a longitudinal end frame 202; the end frame is connected with the cushion block 204, the reinforcing frame 205 and the panel 207 through rivets; the end frames, the cushion blocks 204 and the reinforcing frames 205 are made of aluminum alloy sections, the panel 207 and the honeycomb core 206 can be selected according to the requirements of load and use performance, and the panel is made of aluminum alloy materials and carbon fiber composite materials; the honeycomb core material is typically aluminum honeycomb, paper honeycomb, etc. and the honeycomb core 206 is glued to the face sheet 207 and cured by hot-pressure pouring.

The column section 3 is composed of two half covers, and the column section half cover structure is shown in FIG. 6 and comprises a panel 307, a honeycomb core 306, an end frame, a reinforcing frame 305, a cushion block 304 and the like; the end frame comprises an upper end frame 301, a lower end frame 303 and a longitudinal end frame 302; the column section half-cover structure material, the connection mode and the connection process are consistent with those of the cone section.

The concentrated force dispersing section 4 is composed of two half covers, and the structure of the concentrated force dispersing section half cover is shown in fig. 7 and comprises a skin 404, stringers 402, an upper end frame 401, a lower end frame 403, a spring assembly 6, a hinge 8, a transverse explosion bolt box 7 and the like; wherein the skin 404, the stringers 402, the end frames and the transverse explosion bolt boxes 7 are made of aluminum alloy and are connected through rivets. The cross section of the stringer 402 has an i-shape, an L-shape, a T-shape, etc., and the section with different cross sections can be selected according to the load. The hinge 8 supports the rotation of the half cover in the separation process of the fairing, bears larger hinge moment, and selects alloy steel as the material of the hinge 8 to ensure sufficient strength and rigidity in order to ensure the rotation stability of the half cover. An operation opening is formed in the skin, so that the transverse explosive bolt can be conveniently screwed down, and the opening frame 405 is used for sealing.

The spring assembly 6 includes a spring bracket 601, a locking screw 602, a push rod 603, a spindle 604, a spring 605, and the like, as shown in fig. 11. The spring bracket 601 is riveted on the skin 404 through a rivet; the push rod 603, the mandrel 604 and the spring 605 are connected into a whole through a locking screw 602, and the elasticity of the spring can be adjusted by screwing the locking screw; after being adjusted, the spring support 601 is mounted on the base through a screw; after the fairing is mounted on the arrow body, the locking screw 602 is removed, so that the elastic force of the spring 605 is transmitted to the arrow body through the push rod 603.

As shown in fig. 2 and 7, the hinge 8 is installed in the I, III quadrant of the concentrated force dispersing section 4, and the spring assembly 6 is installed in the II and IV quadrants of the concentrated force dispersing section 4, so that the elastic force of the spring provides a larger rotating moment of the fairing.

The fairing comprises two half-shrouds, each cabin section on the two half-shrouds is connected through a screw, the half-shrouds are connected through an explosion bolt 502, as shown in fig. 8, 9 and 10, explosion bolt boxes 1(501) and 2(504) are arranged on two sides of the explosion bolt, and debris after explosion separation of the explosion bolt 502 is prevented from falling and touching parts such as instruments and equipment.