Rocket heat preservation protection device

Abstract

The invention discloses a rocket heat preservation protection device, which belongs to the field of rocket protection facilities, and comprises a first flexible protection structure and a second flexible protection structure, the first flexible protection structure is arranged above the second flexible protection structure; the first flexible protection structure and the second flexible protection structure are matched with a supporting face on the lower portion of a rocket body to form a closed protection cavity used for containing the rocket body. The rocket can be protected, the economical efficiency is good, and the rocket can be quickly withdrawn.

Description

Technical Field

[0001] The invention relates to the field of rocket protection facilities, and in particular to a rocket thermal insulation protection device. Background Art

[0002] Modern large solid-fuel bundled rocket launches are designed to take into account multiple factors such as economy and flexibility, and will take into account both land and sea launch requirements. Before launch in any of the above external environments, the rocket needs to be provided with a protective environment that meets the requirements, so corresponding protective devices need to be designed to meet the rocket's pre-launch status inspection and maintain the rocket in good condition before launch.

[0003] The current method is to stick thermal insulation foam on certain parts of the rocket body. In practice, it is found that the thermal insulation effect is not good and it is rather cumbersome.

[0004] In addition, when a rocket is launched from land, the pre-launch protection device is mostly a protection tower at a fixed location on land. As the size of the rocket increases and the size of the supporting launch support system increases, the size of the protection tower also becomes large and heavy, suitable for use in fixed locations on land. It lacks flexibility and has a relatively high cost compared to its frequency of use.

[0005] In view of this, it is necessary to provide a new technical solution to solve the above problems. Summary of the invention

[0006] In order to solve the above-mentioned technical problems, the present application provides a rocket thermal insulation protection device, which can protect the rocket, has good economy, and can be quickly withdrawn.

[0007] A rocket thermal insulation protection device includes: a first flexible protection structure and a second flexible protection structure; the first flexible protection structure is arranged above the second flexible protection structure; the first flexible protection structure and the second flexible protection structure cooperate with the supporting surface of the lower part of the rocket body to form a closed protection cavity for accommodating the rocket body.

[0008] Preferably, the first flexible protective structure includes a flexible quiver having a cavity inside; the flexible quiver includes an end cap and a quiver body that are fixedly connected in sequence from top to bottom; the quiver body protects a first cone section and a column section that are fixedly connected in sequence; the bottom of the flexible quiver is fixedly connected to the upper part of the second flexible protective structure.

[0009] Preferably, the arrow cover body also includes a second cone section arranged below the column section and fixedly connected thereto; the second cone section covers the upper part of the second flexible protective structure.

[0010] Preferably, the quiver body comprises a plurality of vertically arranged opening and closing seam structures, and the opening and closing seam structures divide the quiver body into a plurality of half quivers; Velcro is provided at the opening and closing seam structures; and adjacent half quivers are detachably fixedly connected by the Velcro.

[0011] Preferably, the flexible quiver further comprises an opening and closing seam cover cloth capable of covering the outer surface of the opening and closing seam structure.

[0012] Preferably, the first flexible protective structure further comprises a flexible support block; the flexible support block is arranged in the cavity of the column segment.

[0013] Preferably, the flexible quiver is made of antistatic coated cloth.

[0014] Preferably, the second flexible protective structure is an inflatable membrane structure with a cavity, comprising a first inflatable membrane half and a second inflatable membrane half; the first inflatable membrane half and the second inflatable membrane half are detachably fixedly connected; the first inflatable membrane half comprises a first half cone cabin section and a first half column cabin section fixedly connected to each other; the second inflatable membrane half comprises a second half cone cabin section and a second half column cabin section fixedly connected to each other.

[0015] Preferably, the second flexible protective structure is also provided with a personnel passage and an air-conditioning duct passage.

[0016] Preferably, the rocket thermal insulation protection device also includes a winch, an inflation device and a plurality of pulling belts; the second flexible protection structure includes a cone section pulling point and a column section pulling point; one end of the pulling belt is fixedly connected to the cone section pulling point or the column section pulling point; the other end of the pulling belt is fixedly connected to the winch; the inflation device is configured to inflate the second flexible protection structure through a pipeline.

[0017] Compared with the prior art, this application has at least the following beneficial effects:

[0018] 1. The rocket heat preservation and protection device of the present invention can protect the rocket in severe weather such as strong winds and rain and snow, thereby ensuring the safety of the rocket body.

[0019] 2. The rocket thermal insulation and protection device of the present invention, by cooperating with the air conditioner, can effectively control the temperature and humidity inside the rocket thermal insulation and protection device, and provide a suitable temperature and humidity environment for the rocket engine and related components.

[0020] 3. The rocket thermal insulation protection device of the present invention adopts a flexible structure, which can be quickly withdrawn during launch, avoiding the risk of ablation, achieving product reuse, and effectively realizing the economy of the product.

[0021] 4. The rocket thermal insulation protection device of the present invention can adapt to the rocket launch environment after it leaves the final assembly technical plant, during transfer, and on land or at sea. It has a wide range of applicable environments and a long protection period. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Hereinafter, some specific embodiments of the present invention will be described in detail in an exemplary and non-limiting manner with reference to the accompanying drawings. The same reference numerals in the accompanying drawings indicate the same or similar components or parts. It should be understood by those skilled in the art that these drawings are not necessarily drawn to scale.

[0023] In the figure:

[0024] Figure 1 It is a schematic diagram of the overall structure of an embodiment of the present invention;

[0025] Figure 2 This is a schematic diagram of the overall structure of a first flexible protective structure in one embodiment of the present invention;

[0026] Figure 3 is a longitudinal cross-sectional view of a first flexible protective structure in one embodiment of the present invention;

[0027] Figure 4 is a top view of a first flexible protective structure in one embodiment of the present invention;

[0028] Figure 5 This is a schematic diagram of the overall structure of the second flexible protective structure in one embodiment of the present invention;

[0029] Figure 6 FIG. 1 is a diagram showing a half-step split structure of the second flexible protective structure in one embodiment of the present invention.

[0030] intention;

[0031] Figure 7 The horizontal direction of the inflatable membrane of the second flexible protective structure column section in one embodiment of the present invention is

[0032] Sectional view;

[0033] Figure 8 This is a schematic diagram of the overall structure of a first flexible protective structure according to another embodiment of the present invention;

[0034] Fig. 9 is a longitudinal cross-sectional view of a first flexible protective structure according to another embodiment of the present invention;

[0035] Fig.10 It is a schematic diagram of the overall structure of another embodiment of the present invention.

[0036] The above drawings include the following reference numerals:

[0037] 10. First flexible protective structure; 11. End cap; 12. First cone section; 13. Column section; 14. Second cone section; 15. Opening and closing seam structure; 16. Flexible support block; 20. Second flexible protective structure; 30. Air conditioning; 40. Winch; 50. Pulling belt; 60. Control cabinet; 70. Inflatable device; 21. Cone section inflatable membrane; 211. First half of cone cabin section; 212. Second half of cone cabin section; 22. Column section inflatable membrane; 221. First half of column cabin section; 222. Second half of column cabin section; 23. Column section pulling point; 24. Cone section pulling point; 25. Air conditioning duct channel; 26. Personnel channel; 27. Air hole; 28. Inner membrane pulling ring. DETAILED DESCRIPTION

[0038] In order to make the purpose, technical solution and advantages of the present application clearer, the technical solution of the present application will be clearly and completely described below in combination with the specific embodiments of the present application and the corresponding drawings. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present application.

[0039] like Figure 1-Figure 7 As shown, a rocket thermal insulation protection device includes: a first flexible protection structure 10 and a second flexible protection structure 20; the first flexible protection structure 10 is arranged above the second flexible protection structure 20. The first flexible protection structure 10 and the second flexible protection structure 20 cooperate with the support surface at the lower part of the rocket body to form a closed protection cavity for accommodating the rocket body.

[0040] Specifically, the first flexible protective structure 10 includes a flexible quiver with a cavity inside; the flexible quiver includes an end cap 11 and a quiver body that are fixedly connected in sequence from top to bottom; the quiver body protects a first cone section 12 and a column section 13 that are fixedly connected in sequence. The bottom of the flexible quiver is fixedly connected to the upper part of the second flexible protective structure 20, so that a connected closed cavity is formed between the first flexible protective structure 10 and the second flexible protective structure 20.

[0041] Preferably, the quiver body includes a plurality of vertically arranged opening and closing seam structures 15, which divide the quiver body into a plurality of half quivers; Velcro is arranged at the opening and closing seam structures 15; and adjacent half quivers are detachably fixedly connected by the Velcro. The adjacent half quivers are attached by the Velcro, which can realize the rapid assembly and disassembly of the flexible quiver, improve the efficiency, and effectively reduce the production cost of the flexible quiver.

[0042] In addition, in order to achieve rapid assembly and disassembly of the flexible quiver, adjacent halves of the quiver can be detachably fixedly connected by means of knots or zippers.

[0043] As another embodiment of the present invention, the flexible arrow jacket also includes an opening and closing seam cover cloth that can cover the outer surface of the opening and closing seam structure 15. The opening and closing seam cover cloth is made of waterproof material, and the setting of the opening and closing seam cover cloth can further prevent external rain and snow from entering the first flexible protective structure 10. In addition, in the sea-launching environment of the rocket, the setting of the opening and closing seam cover cloth can also effectively prevent seawater rolled up by wind and waves from entering the first flexible protective structure 10, effectively preventing the rocket body from being corroded by seawater.

[0044] As another embodiment of the present invention, the first flexible protective structure 10 also includes a flexible support block 16, which is arranged in the cavity of the column section 13. Through the arrangement of the flexible support block 16, a certain gap can be provided between the arrow body and the arrow body, ensuring that there is a gap for air flow in the first flexible protective structure 10, and ensuring that the arrow body at this position is in a corresponding temperature and humidity state. At the same time, the arrangement of the flexible support block 16 can also reduce the friction between the flexible arrow body and the surface of the arrow body, and reduce the damage of the flexible arrow body to the surface of the arrow body under harsh environmental conditions.

[0045] Preferably, the flexible quiver is made of antistatic coated cloth.

[0046] Preferably, the flexible support block is made of sponge, rubber, silicone or is surrounded by a fabric bag filled with foaming material.

[0047] The second flexible protective structure 20 is an inflatable membrane structure with a cavity inside, and the cavity is adapted to the lower half of the rocket, and there is a corresponding space between the second flexible protective structure 20 and the rocket body to ensure sufficient service space. Specifically, when the rocket has a booster stage, the inner diameter of the second flexible protective structure 20 is larger than the maximum outer envelope size of the booster stage area; when the rocket does not have a booster stage, the inner diameter of the second flexible protective structure 20 is larger than the maximum outer diameter of the core stage.

[0048] The second flexible protective structure 20 includes a cone-segment inflatable membrane 21 and a column-segment inflatable membrane 22. The column-segment inflatable membrane 22 is disposed below and fixedly connected to the cone-segment inflatable membrane 21. The outer surfaces of the cone-segment inflatable membrane 21 and the column-segment inflatable membrane 22 are both provided with a plurality of air holes 27 for inflation.

[0049] The inflatable membrane structure is divided into a first inflatable membrane half and a second inflatable membrane half, and Velcro is arranged at the edge of the first inflatable membrane half and the second inflatable membrane half at the adjacent part thereof, and the first inflatable membrane half and the second inflatable membrane half are detachably fixedly connected by the Velcro. When disassembling the inflatable membrane structure, the Velcro at the adjacent part of the first inflatable membrane half and the second inflatable membrane half can be torn off to realize quick disassembly.

[0050] In some other embodiments of the present invention, the first inflatable membrane half and the second inflatable membrane half can also be detachably fixedly connected by means of a knot or a zipper.

[0051] The first inflatable membrane half includes a first half cone compartment section 211 and a first half column compartment section 221 which are fixedly connected to each other; the second inflatable membrane half includes a second half cone compartment section 212 and a second half column compartment section 222 which are fixedly connected to each other.

[0052] Preferably, a personnel passage 26 and an air conditioning duct passage 25 are also provided on the second flexible protective structure 20 .

[0053] As another embodiment of the present invention, Figure 8-10 As shown, the arrow jacket body also includes a second cone section 14 disposed below the column section 13 and fixedly connected thereto. The second cone section 14 is covered on the upper part of the second flexible protective structure 20.

[0054] As another embodiment of the present invention, the rocket thermal insulation protection device also includes a winch 40, an inflation device 70, a plurality of pulling belts 50 and a control cabinet 60. The second flexible protective structure 20 includes a cone section pulling point 24 and a column section pulling point 23. The cone section pulling point 24 is located above the column section pulling point 23. One end of the pulling belt 50 is fixedly connected to the cone section pulling point 24 or the column section pulling point 23, and the other end is fixedly connected to the winch 40. By controlling the winch 40, the length of the pulling belt 50 can be controlled, thereby ensuring that the pulling belt 50 is fixed to the second flexible protective structure 20. The inflation device 70 is configured to inflate the second flexible protective structure 20 through a pipeline. Electrical control components are arranged in the control cabinet 60 for controlling the opening and closing of the winch 40 and the inflation device 70. The inflation device 70 is preferably an inflation fan or an inflation pump.

[0055] As another embodiment of the present invention, an inner membrane pulling ring 28 is further provided on the inner cavity wall of the second flexible protective structure 20 of the rocket thermal insulation protection device for fixing the inside of the quiver.

[0056] When in use, the first inflatable membrane half and the second inflatable membrane half of the second flexible protective structure 20 are arranged around the circumference of the rocket body and assembled at the adjacent parts of the two. After the second flexible protective structure 20 is assembled, the air storage membrane of the inflatable membrane structure is inflated by the inflation device 70, so that the second flexible protective structure 20 expands and stands up. The first flexible protective structure 10 is inserted from the top of the rocket, and its lower part is connected to the second flexible protective structure 20 to realize the assembly of the first flexible protective structure 10 and the second flexible protective structure 20, and then the rocket thermal insulation protection device protects the rocket. The rocket thermal insulation protection device can be used in multiple environments after the rocket leaves the general assembly technical plant, during the transfer, and before launching on land or at sea, to achieve all-round protection for the rocket.

[0057] In addition, when the rocket needs to be in a fixed external environment for a long time, the column section pulling point 23 and / or the cone section pulling point 24 outside the second flexible protective structure 20 can be connected to the winch 40 through the pulling belt 50, and the second flexible protective structure 20 and the rocket thermal insulation protection device can be fixed by relying on the pulling force of the winch 40.

[0058] For ease of description, spatially relative terms such as "above", "above", "on the upper surface of", "above", etc. may be used here to describe the spatial positional relationship between a device or feature and other devices or features as shown in the figure. It should be understood that spatially relative terms are intended to include different orientations of the device in use or operation in addition to the orientation described in the figure. For example, if the device in the accompanying drawings is inverted, the device described as "above other devices or structures" or "above other devices or structures" will be positioned as "below other devices or structures" or "below other devices or structures". Thus, the exemplary term "above" can include both "above" and "below". The device can also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatially relative descriptions used here are interpreted accordingly.

[0059] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit the exemplary embodiments according to the present application. As used herein, unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. In addition, it should be understood that when the terms "comprise" and / or "include" are used in this specification, it indicates the presence of features, steps, operations, devices, components and / or combinations thereof.

[0060] It should be noted that the terms "first", "second", etc. in the specification and claims of the present application and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It should be understood that the numbers used in this way can be interchanged where appropriate, so that the embodiments of the present application described herein can be implemented in an order other than those illustrated or described herein.

[0061] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A rocket thermal insulation protection device, characterized in that: include: A first flexible protective structure and a second flexible protective structure; the first flexible protective structure is arranged above the second flexible protective structure; the first flexible protective structure and the second flexible protective structure cooperate with the supporting surface of the lower part of the arrow body to form a closed protective cavity for accommodating the arrow body.

2. The rocket thermal insulation protection device according to claim 1, characterized in that: The first flexible protective structure includes a flexible quiver with a cavity inside; the flexible quiver includes an end cap and a quiver body that are fixedly connected in sequence from top to bottom; the quiver body protects a first cone section and a column section that are fixedly connected in sequence; the bottom of the flexible quiver is fixedly connected to the upper part of the second flexible protective structure.

3. The rocket thermal insulation protection device according to claim 2, characterized in that: The arrow jacket body also includes a second cone section arranged below the column section and fixedly connected thereto; the second cone section is covered on the upper part of the second flexible protective structure.

4. The rocket thermal insulation protection device according to claim 2 or 3, characterized in that: The quiver body comprises a plurality of vertically arranged opening and closing seam structures, wherein the opening and closing seam structures divide the quiver body into a plurality of half quivers; Velcro is arranged at the opening and closing seam structures; and adjacent half quivers are detachably fixedly connected by the Velcro.

5. The rocket thermal insulation protection device according to claim 4, characterized in that: The flexible quiver also includes an opening and closing seam cover cloth capable of covering the outer surface of the opening and closing seam structure.

6. The rocket thermal insulation protection device according to claim 2 or 3, characterized in that: The first flexible protective structure also includes a flexible support block; the flexible support block is arranged in the cavity of the column segment.

7. The rocket thermal insulation protection device according to claim 2, characterized in that: The flexible quiver is made of antistatic coated cloth.

8. The rocket thermal insulation protection device according to any one of claims 1, characterized in that: The second flexible protective structure is an inflatable membrane structure with a cavity, including a cone segment inflatable membrane and a column segment inflatable membrane; the column segment inflatable membrane is arranged under the cone segment inflatable membrane and fixedly connected thereto; the inflatable membrane structure is divided into a first inflatable membrane half and a second inflatable membrane half; the first inflatable membrane half and the second inflatable membrane half are detachably fixedly connected; the first inflatable membrane half includes a first half cone cabin section and a first half column cabin section fixedly connected to each other; the second inflatable membrane half includes a second half cone cabin section and a second half column cabin section fixedly connected to each other.

9. The rocket thermal insulation protection device according to claim 1 or 8, characterized in that: The second flexible protective structure is also provided with a personnel passage and an air conditioning duct passage.

10. The rocket thermal insulation protection device according to claim 1 or 8, characterized in that: The rocket thermal insulation protection device also includes a winch, an inflation device and several pulling belts; the second flexible protection structure includes a cone section pulling point and a column section pulling point; one end of the pulling belt is fixedly connected to the cone section pulling point or the column section pulling point; the other end of the pulling belt is fixedly connected to the winch; the inflation device is configured to inflate the second flexible protection structure through a pipeline.

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