Explosion-proof device for cab of launching ship

Abstract

The utility model discloses a launching ship cab explosion-proof device which comprises a cab frame, glass is fixedly installed on the cab frame, an aluminum alloy double-layer plate located on the outer side of the glass is hinged to the cab frame, and a first fixing block and a second fixing block are fixedly installed on the two sides of the front face of the aluminum alloy double-layer plate respectively. Every two adjacent aluminum alloy double-layer plates are connected through a splicing structure. Through the arrangement of the aluminum alloy double-layer plate, before a rocket is launched, a worker can rotate the aluminum alloy double-layer plate to enable the aluminum alloy double-layer plate to be attached to the glass, so that the glass can be shielded, after the rocket is launched, a large number of high-temperature particles in tail flame of the rocket are ejected out, and at the moment, due to the design of the aluminum alloy double-layer plate, the high-temperature particles can be ejected out. The anti-explosion glass has the advantages that high-temperature particles can be blocked and prevented from being diffused to the glass, so that the glass is protected, and the anti-explosion glass has the advantage of anti-explosion protection for the glass.

Description

Technical Field

[0001] The utility model belongs to the technical field of shipbuilding, and particularly relates to an explosion-proof device for the cab of a launch ship. Background Art

[0002] Onshore rocket launch sites generally have a sufficient safety distance from living function areas. During rocket launches, they generally do not affect the living function areas. However, due to the limited size of launch ships, when conducting rocket launches with a ship as the carrier at sea, rocket exhaust particles will cause exhaust particle pollution, and a strong shock wave will impact during rocket explosions. Therefore, existing launch ships usually set up flow-blocking devices on the launch hull for protection to reduce the use cost of the rocket launch ship. For example, the Chinese patent with the publication number CN117585100B discloses an offshore rocket launch ship, including: a launch hull with multiple aerospace control devices distributed thereon; a launch pad fixedly connected to the launch hull; longitudinal diversion grooves are opened on both sides of the launch pad, and a rocket to be launched is arranged on the launch pad; a flow-blocking device fixedly connected to the launch hull, the flow-blocking device includes: a flow-blocking plate and at least two support structures, the flow-blocking plate is arranged on the launch hull and is fixedly connected to the launch hull on one side; one side of at least two support structures is respectively fixedly connected to the first surface of the flow-blocking plate, and one end is respectively fixedly connected to the launch hull; the flow-blocking device is arranged between the longitudinal diversion groove and the aerospace control device. When the rocket to be launched is launched, the flow-blocking device blocks and diverts the lateral thermal jet generated by the longitudinal diversion groove. The offshore rocket launch ship provided by the present invention can protect the aerospace control device by setting up a flow-blocking device on the launch hull, and reduce the use cost of the rocket launch ship.

[0003] However, there are some problems in the prior art: Although the prior art sets up a flow-blocking device to protect the aerospace control device, in the overall layout of the launch ship, due to considering the driving and navigation functions of the ship, the cab will be arranged on the highest layer of the ship. For the convenience of a wide driving view, a large area of glass will be used around the cab. After the solid rocket is launched, a large number of high-temperature particles are ejected in the rocket exhaust. If they spread to the glass, it will cause high-temperature particle pollution to the glass, resulting in difficult-to-clean consequences. And if the rocket explodes, the cab glass, as the most vulnerable part, will be instantly shattered by the shock wave. Therefore, we propose an explosion-proof device for the cab of a launch ship. Summary of the Utility Model

[0004] Aiming at the problems existing in the prior art, the purpose of the utility model is to provide an explosion-proof device for the cab of a launch ship, which provides explosion-proof protection for the glass by arranging an aluminum alloy double-layer plate outside the cab glass.

[0005] The present utility model is implemented as follows. An explosion-proof device for the cab of a launch ship includes a cab frame. A glass is fixedly installed on the cab frame. An aluminum alloy double-layer plate is hinged on the cab frame outside the glass. On both sides of the front surface of the aluminum alloy double-layer plate, a first fixing block and a second fixing block are respectively fixedly installed. Adjacent two aluminum alloy double-layer plates are connected by a splicing structure. The aluminum alloy double-layer plates can be connected into a whole through the splicing structure, thereby improving the overall stability.

[0006] Optionally, a circular groove is opened at the top of the first fixing block. The splicing structure includes a vertical rod. The vertical rod is fixedly installed at the top of the second fixing block. A slider is movably sleeved in the middle of the outer surface of the vertical rod. The top of the slider is rotatably connected to a horizontal plate. The other side of the bottom of the horizontal plate is fixedly connected to a bolt. The bottom end of the bolt extends into the interior of the circular groove.

[0007] Optionally, a spring is movably sleeved on the outer surface of the vertical rod between the second fixing block and the slider. The two ends of the spring are respectively fixedly connected to the outer surfaces of the second fixing block and the slider.

[0008] Optionally, the aluminum alloy double-layer plate is provided with an inner cavity. A honeycomb core is fixedly installed at the front end of the inner wall of the aluminum alloy double-layer plate. Through holes are opened on the surfaces of both the honeycomb core and the aluminum alloy double-layer plate.

[0009] Optionally, the inner wall of the through hole is provided with wrinkled stripes, and the wrinkled stripes are irregular.

[0010] Optionally, the aluminum alloy double-layer plate is attached to the glass surface, and a gap is provided between the rear end of the inner wall of the aluminum alloy double-layer plate and the honeycomb core.

[0011] Optionally, heat dissipation holes are opened at the top of the aluminum alloy double-layer plate, and the heat dissipation holes are evenly distributed at the top of the aluminum alloy double-layer plate.

[0012] Optionally, the appearance of the aluminum alloy double-layer plate is square, and the surface of the aluminum alloy double-layer plate is coated with epoxy fluorocarbon.

[0013] Compared with the prior art, the beneficial effects of the present utility model are as follows:

[0014] 1. By setting the aluminum alloy double-layer plate in the present utility model, before the rocket launch, the staff can rotate the aluminum alloy double-layer plate so that the aluminum alloy double-layer plate adheres to the glass, thereby being able to block the glass. After the rocket launch, a large number of high-temperature particles are ejected in the rocket tail flame. At this time, due to the design of the aluminum alloy double-layer plate, the high-temperature particles will be blocked, preventing the high-temperature particles from spreading to the glass and avoiding the high-temperature particles from adhering to the glass and being difficult to clean, thus realizing the protection of the glass.

[0015] 2. By providing a vertical rod, a slider, a horizontal plate, a bolt and a spring, the bolt is inserted into the inner part of the circular groove, so as to connect the first fixing block and the second fixing block, and then two aluminum alloy double-layer plates can be spliced. This can avoid the difficulty in installation and operation due to the excessive weight of the large aluminum alloy double-layer plates. By moving the slider upward, the horizontal plate drives the bolt to move upward, so that the bottom end of the bolt is withdrawn from the inner part of the circular groove, and the splicing effect between two adjacent aluminum alloy double-layer plates can be released, thus facilitating the installation or position adjustment of the aluminum alloy double-layer plates by the staff.

[0016] 3. By providing through holes and corrugated stripes, due to the design of the through holes, not only can the overall weight of the aluminum alloy double-layer plates be reduced, facilitating transportation and installation work, but also the shock wave generated during rocket explosion can be absorbed, thereby improving the protection effect on the glass. Through the design of the corrugated stripes, after the shock wave generated by rocket explosion enters the inner part of the aluminum alloy double-layer plates through the through holes, it will be reflected and attenuated multiple times in the complex structure of the corrugated stripes, thus significantly reducing the propagation effect of the shock wave, and further being able to avoid the phenomenon that the glass is impacted and cracked by the shock wave.

[0017] Other features and advantages of the present utility model will become clear through the following detailed description of the exemplary embodiments of the present utility model with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 is the structural schematic diagram provided by the present utility model;

[0019] Figure 2 is the structural schematic diagram of the present utility model when the glass is not protected;

[0020] Figure 3 is the cross-sectional structural schematic diagram of the side of the aluminum alloy double-layer plate provided by the present utility model;

[0021] Figure 4 is the cross-sectional structural schematic diagram of the inner part of the first fixing block provided by the present utility model;

[0022] Figure 5 is the structural schematic diagram of the honeycomb core provided by the present utility model;

[0023] Figure 6 is Figure 5 the partial enlarged structural schematic diagram at A in

[0024] In the figure: 1, cab frame; 2, glass; 3, aluminum alloy double-layer plate; 4, first fixing block; 5, second fixing block; 6, circular groove; 7, vertical rod; 8, slider; 9, horizontal plate; 10, bolt; 11, spring; 12, honeycomb core; 13, through hole; 14, corrugated stripe; 15, heat dissipation hole. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0025] To further understand the utility model content, features and effects of the present utility model, the following embodiments are cited and described in detail with reference to the accompanying drawings as follows.

[0026] As Figures 1 to 6 shown, an explosion-proof device for the cab of a launch ship provided by an embodiment of the present utility model includes a cab frame 1, a glass 2 is fixedly installed on the cab frame 1, and an aluminum alloy double-layer plate 3 is hinged on the cab frame 1 outside the glass 2. First fixing blocks 4 and second fixing blocks 5 are respectively fixedly installed on both sides of the front surface of the aluminum alloy double-layer plate 3. Adjacent two aluminum alloy double-layer plates 3 are connected through a splicing structure. The aluminum alloy double-layer plates 3 can be connected into a whole through the splicing structure, thereby improving the overall stability.

[0027] Further, a circular groove 6 is opened at the top of the first fixing block 4. The splicing structure includes a vertical rod 7. The vertical rod 7 is fixedly installed at the top of the second fixing block 5. A slider 8 is movably sleeved in the middle of the outer surface of the vertical rod 7. The top of the slider 8 is rotatably connected to a cross plate 9. The other side of the bottom of the cross plate 9 is fixedly connected to a bolt 10. The bottom end of the bolt 10 extends into the circular groove 6.

[0028] By inserting the bolt 10 into the circular groove 6, the first fixing block 4 and the second fixing block 5 can be connected, and then the two aluminum alloy double-layer plates 3 can be spliced. By moving the slider 8 upward, the cross plate 9 drives the bolt 10 to move upward, so that the bottom end of the bolt 10 is withdrawn from the circular groove 6, and the splicing effect between adjacent two aluminum alloy double-layer plates 3 can be released, thereby facilitating the installation or position adjustment of the aluminum alloy double-layer plates 3 by the staff.

[0029] Further, a spring 11 is movably sleeved on the outer surface of the vertical rod 7 between the second fixing block 5 and the slider 8. The two ends of the spring 11 are respectively fixedly connected to the outer surfaces of the second fixing block 5 and the slider 8.

[0030] By setting the spring 11 in a stretched state, due to the elastic recovery effect of the spring 11, the slider 8 will tend to move downward, so that the cross plate 9 and the bolt 10 will tend to move downward, and then the bottom end of the bolt 10 can be stably maintained in the circular groove 6.

[0031] Further, the aluminum alloy double-layer plate 3 is provided with an inner cavity. A honeycomb core 12 is fixedly installed at the front end of the inner wall of the aluminum alloy double-layer plate 3. Through holes 13 are opened on the surfaces of both the honeycomb core 12 and the aluminum alloy double-layer plate 3.

[0032] Through the design of the through holes 13, not only can the overall weight of the aluminum alloy double-layer plate 3 be reduced, facilitating transportation and installation work, but also the shock wave generated during rocket explosion can be absorbed, thereby improving the protection effect on the glass 2.

[0033] Further, the inner wall of the through hole 13 is provided with corrugated stripes 14, and the corrugated stripes 14 are irregular in shape.

[0034] Through the design of the corrugated stripes 14, after the shock wave generated by the rocket explosion enters the interior of the aluminum alloy double-layer plate 3 through the through hole 13, it will be reflected and attenuated multiple times in the complex structure of the corrugated stripes 14, thereby significantly reducing the propagation effect of the shock wave, and further being able to avoid the phenomenon that the glass 2 is impacted, cracked and broken by the shock wave.

[0035] Further, the aluminum alloy double-layer plate 3 is attached to the surface of the glass 2, and a gap is provided between the rear end of the inner wall of the aluminum alloy double-layer plate 3 and the honeycomb core 12.

[0036] By providing a gap between the rear end of the inner wall of the aluminum alloy double-layer plate 3 and the honeycomb core 12, when a large number of high-temperature particles in the rocket tail flame are ejected and fall onto the surface of the aluminum alloy double-layer plate 3, the heat will be transferred to the honeycomb core 12, and the honeycomb core 12 is not in contact with the rear end of the inner wall of the aluminum alloy double-layer plate 3, so that the continuous transfer of heat can be blocked, and further the heat is prevented from being transferred from the rear end of the inner wall of the aluminum alloy double-layer plate 3 to the glass 2, thereby further enhancing the protection effect on the glass 2.

[0037] Further, heat dissipation holes 15 are formed in the top of the aluminum alloy double-layer plate 3, and the heat dissipation holes 15 are evenly distributed on the top of the aluminum alloy double-layer plate 3.

[0038] Through the design of the heat dissipation holes 15, air can freely circulate in the aluminum alloy double-layer plate 3, enhancing the air permeability of the aluminum alloy double-layer plate 3, so that the hot air generated by the high-temperature particles in the aluminum alloy double-layer plate 3 is more likely to be dissipated outward through the heat dissipation holes 15 from the gap between the rear side of the inner wall of the aluminum alloy double-layer plate 3 and the honeycomb core 12, thereby enhancing the heat insulation effect.

[0039] Further, the appearance of the aluminum alloy double-layer plate 3 is square, and the surface of the aluminum alloy double-layer plate 3 is coated with epoxy fluorocarbon.

[0040] By coating epoxy fluorocarbon on the surface of the aluminum alloy double-layer plate 3, the corrosion resistance of the aluminum alloy double-layer plate 3 can be improved, thereby reducing the damage caused to the aluminum alloy double-layer plate 3 by the large number of high-temperature particles ejected onto the surface of the aluminum alloy double-layer plate 3 by the rocket tail flame, and enhancing the service life of the aluminum alloy double-layer plate 3.

[0041] Before the rocket is launched, the staff can rotate the double-layer aluminum alloy plate 3 so that the double-layer aluminum alloy plate 3 adheres to the glass 2, thereby being able to block the glass 2. Then, pull the slider 8 upward, rotate the cross plate 9 and the bolt 10 so that the bolt 10 rotates to directly above the circular groove 6. After releasing the slider 8, due to the elastic recovery of the spring 11, the bolt 10 will be inserted into the circular groove 6, thereby connecting the first fixing block 4 and the second fixing block 5, and then being able to splice two adjacent double-layer aluminum alloy plates 3. This avoids the difficulty of installation and operation due to the excessive weight of the large double-layer aluminum alloy plate 3. By moving the slider 8 upward, the cross plate 9 drives the bolt 10 to move upward, so that the bottom end of the bolt 10 is withdrawn from the circular groove 6, and the splicing effect between two adjacent double-layer aluminum alloy plates 3 can be released, thus facilitating the staff to install or adjust the position of the double-layer aluminum alloy plate 3. After the rocket is launched, a large number of high-temperature particles are ejected in the rocket tail flame. At this time, due to the design of the double-layer aluminum alloy plate 3, the high-temperature particles will be blocked, preventing the high-temperature particles from spreading to the glass 2 and adhering to the glass 2, which is difficult to clean, thus realizing the protection of the glass 2. And due to the design of the through hole 13, it can not only reduce the overall weight of the double-layer aluminum alloy plate 3, facilitating transportation and installation work, but also absorb the shock wave generated during the rocket explosion, thereby improving the protection effect on the glass 2. Through the design of the corrugated stripes 14, after the shock wave generated by the rocket explosion enters the double-layer aluminum alloy plate 3 through the through hole 13, it will be reflected and attenuated multiple times in the complex structure of the corrugated stripes 14, thus significantly reducing the propagation effect of the shock wave, and then being able to avoid the phenomenon that the glass 2 is cracked and broken by the impact of the shock wave.

[0042] Although the embodiments of the present invention have been shown and described, for those of ordinary skill in the art, it can be understood that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principles and spirit of the present invention. The scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. An explosion-proof device for a launching ship's cab, comprising a cab frame (1), characterized in that: The cab frame (1) is fixedly mounted with glass (2), the cab frame (1) is hinged with an aluminum alloy double-layer plate (3) located outside the glass (2), the front sides of the aluminum alloy double-layer plate (3) are respectively fixedly mounted with a first fixing block (4) and a second fixing block (5), two adjacent aluminum alloy double-layer plates (3) are connected via a splicing structure, and the aluminum alloy double-layer plates (3) can be connected into a whole via the splicing structure, thereby improving the overall stability.

2. The explosion-proof device for the launch ship's cab according to claim 1, characterized in that: A circular groove (6) is provided on the top of the first fixed block (4), and the splicing structure includes a vertical rod (7), which is fixedly mounted on the top of the second fixed block (5), and a slider (8) is movably sleeved in the middle of the outer surface of the vertical rod (7), and a cross plate (9) is rotatably connected to the top of the slider (8), and a latch (10) is fixedly connected to the other side of the bottom of the cross plate (9), and the bottom end of the latch (10) extends to the inside of the circular groove (6).

3. The explosion-proof device for the launch ship's cab according to claim 2, characterized in that: The outer surface of the vertical rod (7) is movably sleeved with a spring (11) located between the second fixed block (5) and the sliding block (8), and the two ends of the spring (11) are respectively fixedly connected to the outer surfaces of the second fixed block (5) and the sliding block (8).

4. The explosion-proof device for the launch ship cab according to claim 1, characterized in that: The aluminum alloy double-layer plate (3) is provided with an inner cavity, a honeycomb core (12) is fixedly mounted on the front end of the inner wall of the aluminum alloy double-layer plate (3), and through holes (13) are provided on the surfaces of the honeycomb core (12) and the aluminum alloy double-layer plate (3).

5. The explosion-proof device for the launch ship's cab according to claim 4, characterized in that: The inner wall of the through hole (13) is provided with wrinkle stripes (14), and the wrinkle stripes (14) are irregular in shape.

6. The explosion-proof device for the launch ship's cab according to claim 1, characterized in that: The aluminum alloy double-layer plate (3) is attached to the surface of the glass (2), and a gap is provided between the rear end of the inner wall of the aluminum alloy double-layer plate (3) and the honeycomb core (12).

7. The explosion-proof device for the launch ship's cab according to claim 1, characterized in that: The top of the aluminum alloy double-layer plate (3) is provided with heat dissipation holes (15), and the heat dissipation holes (15) are evenly distributed on the top of the aluminum alloy double-layer plate (3).

8. The explosion-proof device for the launch ship's cab according to claim 1, characterized in that: The aluminum alloy double-layer plate (3) has a square appearance, and the surface of the aluminum alloy double-layer plate (3) is coated with epoxy fluorocarbon.

Images