Multi-layer heat shield for overall heat protection of rocket secondary bottom and rocket sublevel structure

Abstract

The utility model provides a multi-layer heat shield for overall heat protection of a rocket secondary bottom and a rocket sublevel structure, which are mounted at the rocket secondary bottom to perform heat protection on an upper element of a rocket secondary engine and at least comprise an upper reflecting layer with a heat protection function, a lower reflecting layer, a spacer layer and a locking wire, the spacer layer is arranged between the upper reflecting layer and the lower reflecting layer, and the upper surface and the lower surface of the spacer layer are tightly attached to the lower surface of the upper reflecting layer and the upper surface of the lower reflecting layer respectively. The upper reflecting layer, the lower reflecting layer and the spacer layer are sewn together through the locking wires to form a multi-layer heat shield body, and the locking wires are further used for being connected with a rocket second-stage bottom support so that the multi-layer heat shield body can be fixed to the rocket second-stage bottom. The heat shield can effectively perform heat protection on the upper element of the rocket secondary engine, ensures the stable structure and safe operation of the element, and can also reduce the heat protection coating workload, improve the working efficiency and save the cost.

Description

TECHNICAL FIELD

[0001] The utility model relates to rocket power technical field especially relates to a multilayer heat shield for the whole heat protection of rocket second stage bottom and rocket substage structure. BACKGROUND

[0002] With the rapid development of space industry, the technology involved in the field of rocket has also achieved rapid development. When the rocket second stage main engine is working, the engine nozzle wall and the jet flow will produce heat radiation and heat convection to the internal equipment, cables, engine frame, servo mechanism, etc. of the rocket second stage rear short shell, especially the heat radiation accounts for a large proportion.

[0003] At present, the mainstream of the heat protection of the rocket second stage bottom is to adopt the scheme of covering the cables and equipment respectively. Covering the cables has always been a large workload of final assembly, and it is necessary to use the half-lapping method to cover from one end of the cable to the other end, and a large number of cable covering is also easy to damage the cable. In addition, due to different heat flow conditions, the heat protection schemes of the equipment, cables, frame, etc. are different, and the covering workload continues to increase due to the different shapes of the covered objects. In addition, the equipment, cables, parts of the rocket second stage bottom adopt various heat protection covering measures, and the thermal conductivity coefficient is difficult to accurately measure, which needs to be verified through static heating test, which undoubtedly increases the time cost and test cost.

[0004] Therefore, it is urgent to design a multilayer heat shield for the whole heat protection of the rocket second stage bottom to effectively protect the upper elements of the rocket second stage engine from heat and ensure the stable and safe operation of the elements. SUMMARY

[0005] The utility model discloses a multilayer heat shield for the whole heat protection of the rocket second stage bottom, which can effectively protect the upper elements of the rocket second stage engine from heat, ensure the stable and safe operation of the elements, reduce the workload, improve the work efficiency, save the cost and have other advantages.

[0006] The utility model discloses a multilayer heat shield for the whole heat protection of the rocket second stage bottom, which can effectively protect the upper elements of the rocket second stage engine from heat, ensure the stable and safe operation of the elements, reduce the workload, improve the work efficiency, save the cost and have other advantages.

[0007] In the same embodiment, the multi-layer heat shield body surface is uniformly provided with exhaust holes, and the exhaust holes penetrate the multi-layer heat shield body.

[0008] In the same embodiment, the multi-layer heat shield body has a volume of V liters, and the exhaust hole area is Scm 2 , S = 0.1V.

[0009] In the same embodiment, the thickness of the multi-layer heat shield body is A microns, wherein 80≤A≤130.

[0010] In the same embodiment, the upper reflective layer and the upper reflective layer are both double-sided aluminum-coated polyimide films.

[0011] In the same embodiment, the thickness of the double-sided aluminum-coated polyimide film is B microns, wherein 15≤B≤40.

[0012] In the same embodiment, the spacer layer is a glass fiber cloth.

[0013] In the same embodiment, the thickness of the glass fiber cloth is C microns, wherein 40≤C≤85.

[0014] In the same embodiment, the locking wire is a polyimide rope, and the diameter of the polyimide rope is D millimeters, wherein 2≤D≤6.

[0015] The utility model also provides a rocket sublevel structure, contains above any one for rocket two level bottom whole heat -proof multi -layer heat shield.

[0016] Compared with the prior art, the utility model has at least one of the following beneficial effects:

[0017] The multi-layer heat shield of the application is composed of an upper reflective layer, a lower reflective layer, a spacer layer and a locking wire with heat protection function. The overall multi-layer heat shield body has excellent heat insulation performance in a low-pressure vacuum state. When applied, the high-temperature radiant heat flows successively through the upper reflective layer, the spacer layer and the lower reflective layer with heat protection function. Most of the heat flows reaching the lower reflective layer are reflected, and a small part of the heat flows reaching the lower reflective layer are absorbed. The absorbed heat flows cause the lower reflective layer to heat up, continue to heat radiate to the closely attached spacer layer, the spacer layer heats up, and then radiate to the closely attached upper reflective layer. The heat flows are again reflected by the upper reflective layer, and a small part of the heat flows reaching the upper reflective layer are absorbed. Finally, after the heat protection of the multi-layer heat shield, the high-temperature radiant heat flows are weakened several times, and the cumulative heat reaching the surface of the equipment and cables in the rocket two-level short shell has little effect, thereby avoiding the direct action of the high-temperature radiant heat flows of the two-level engine jet on the surface of the equipment and cables in the rocket two-level short shell. The upper elements of the rocket two-level engine can be effectively heat protected, the element structure is stable and safe to operate, the work efficiency is improved, and the cost is saved.

[0018] The upper reflective layer, the lower reflective layer and the spacer layer of the present application are sewn together by locking wire to form a multilayer heat shield body, and the upper reflective layer, the lower reflective layer and the spacer are connected tightly and fixed firmly by the locking wire, so as to ensure the structural stability of the multilayer heat shield body.

[0019] In addition, the multilayer heat shield body can be manufactured in a free space, without the need for step-by-step installation on the rocket, thereby greatly saving the installation time, avoiding damage to equipment and cables during implementation on the rocket, reducing the workload, and greatly improving the work efficiency.

[0020] It should be understood that the foregoing general description and the following detailed description are only exemplary and explanatory, and do not limit the scope of the present application. BRIEF DESCRIPTION OF DRAWINGS

[0021] The following drawings are part of the specification of the present application, which illustrate the example embodiments of the present application, and the accompanying drawings and the description of the specification are used to illustrate the principles of the present application.

[0022] Figure 1 The structure of the multilayer heat shield body in the embodiments of the present application is shown in the figure.

[0023] Explanation of reference signs:

[0024] 1 multilayer heat shield body 2 nylon buckle 3 polyimide rope DETAILED DESCRIPTION

[0025] Now, a variety of exemplary embodiments of the present application will be described in detail, which should not be considered as limiting the present application, but should be understood as a more detailed description of certain aspects, characteristics and embodiments of the present application.

[0026] Various modifications and changes can be made to the specific implementation of the present application without departing from the scope or spirit of the present application, which will be apparent to those skilled in the art. Other embodiments obtained from the specification of the present application will be apparent to those skilled in the art. The specification and examples of the present application are only exemplary.

[0027] As Figure 1The utility model discloses a multilayer heat shield for the overall heat protection of the second stage bottom of a rocket, which provides heat protection for the upper elements of the second stage engine of the rocket by being installed on the second stage bottom of the rocket, and at least comprises an upper reflective layer, a lower reflective layer, a spacer layer and locking wires with heat protection function. The spacer layer is arranged between the upper reflective layer and the lower reflective layer, and the upper and lower surfaces of the spacer layer are in close contact with the lower surface of the upper reflective layer and the upper surface of the lower reflective layer respectively. The upper reflective layer, the lower reflective layer and the spacer layer are sewn together by the locking wires to form a multilayer heat shield body 1, and the locking wires are also used to connect with the bracket of the second stage bottom of the rocket to fix the multilayer heat shield body 1 on the second stage bottom of the rocket.

[0028] Specifically, the multilayer heat shield provided by the utility model embodiment is composed of an upper reflective layer, a lower reflective layer, a spacer layer and locking wires with heat protection function. The overall multilayer heat shield body 1 has excellent heat insulation performance in a low-pressure vacuum state. When applied, high-temperature radiant heat flows pass through the upper reflective layer, the spacer layer and the lower reflective layer with heat protection function in turn. Most of the heat flows are reflected by the lower reflective layer, and a small part of the heat flows reaching the lower reflective layer are absorbed. The heat flows absorbed by the heat shield cause the lower reflective layer to heat up, continue to heat radiate to the closely attached spacer layer, the spacer layer heats up, and then heat radiate to the closely attached upper reflective layer. The heat flows are reflected by the upper reflective layer again, a small part of the heat flows reaching the upper reflective layer are absorbed, and finally the high-temperature radiant heat flows are weakened for many times. The cumulative heat reaching the surface of the equipment and cables in the short shell behind the second stage of the rocket is small, thereby avoiding the direct action of the high-temperature radiant heat flows of the second stage engine jet on the surface of the equipment and cables in the short shell behind the second stage of the rocket. The upper elements of the second stage engine can be effectively heat protected, the element structure is stable and safe to operate, and the work efficiency is improved and the cost is saved due to simple installation.

[0029] The upper reflective layer, the lower reflective layer and the spacer layer of the present application are sewn together by the locking wires to form a multilayer heat shield body 1, and the upper reflective layer, the lower reflective layer and the spacer are connected closely and fixed firmly by the locking wires, thereby ensuring the structural stability of the multilayer heat shield body 1.

[0030] In addition, the multilayer heat shield body can be made in an idle place, and does not need to be installed step by step on the rocket, thereby greatly saving the installation time and avoiding damage to the equipment and cables during the coating process on the rocket, reducing the workload and greatly improving the work efficiency.

[0031] In the embodiment, in order to exhaust the residual gas in the multi-layer heat shield body 1 and the closed space of the rocket second stage rear short shell, and avoid the multi-layer heat shield body 1 from separating from the rocket due to the internal and external pressure difference during the rapid drop of external pressure in the rocket ascending stage, for example, the exhaust holes are uniformly arranged on the surface of the multi-layer heat shield body. For example, the exhaust holes penetrate the multi-layer heat shield body, and the arrangement of the exhaust holes balances the internal and external pressure of the multi-layer heat shield body 1, which is beneficial to the installation and heat protection of the multi-layer heat shield body 1, and avoids the heat shield from falling off during the flight of the rocket.

[0032] In addition, through a large number of test simulations, when the volume of the multi-layer heat shield body 1 is V liters, the area of the exhaust hole is Scm 2 , and S = 0.1V is satisfied, the internal and external pressure balance of the multi-layer heat shield body can be better ensured without affecting the heat protection of the multi-layer heat shield body, thereby avoiding the multi-layer heat shield body 1 from separating from the rocket.

[0033] In the same embodiment, without affecting the heat protection effect of the multi-layer heat shield body 1, the weight of the multi-layer heat shield body 1 can also be reduced by adjusting the thickness of the heat shield. Through a large number of tests, for example, when the thickness of the multi-layer heat shield body 1 is A microns and 80≤A≤130 is satisfied, the heat protection effect of the multi-layer heat shield body 1 can be ensured, and the weight of the multi-layer heat shield body 1 can also be reduced.

[0034] In the same embodiment, in order to improve the launch efficiency, for example, the upper reflective layer and the upper reflective layer are both double-sided aluminum-coated polyimide films. The double-sided aluminum-coated polyimide film has a reflectivity of more than 78% for radiation with a wavelength of 0.2 microns to 1.2 microns, and the structure is stable, which can greatly improve the reflection efficiency.

[0035] In the embodiment, the double-sided aluminum-coated polyimide film is lightened without affecting the reflection effect, for example, the thickness of the double-sided aluminum-coated polyimide film is B microns, and 15≤B≤40 is satisfied.

[0036] In addition, in order to avoid the spacer layer from burning for a long time at high temperature, for example, the spacer layer is a glass fiber cloth. The glass fiber cloth not only resists high temperature, but also has a fire-retardant effect, which ensures the stability of the structure of the entire multi-layer heat shield body 1.

[0037] Through a large number of test simulations, when the thickness of the glass fiber cloth is C microns and 40≤C≤85 is satisfied, the glass fiber cloth can not only resist high temperature and have a fire-retardant effect, but also be lightweight, which is beneficial to improve the carrying capacity of the rocket.

[0038] In the same embodiment, in order to ensure that the locking wire has high temperature resistance, for example, the locking wire is a polyimide rope 3. In order to facilitate the fixing of the upper reflective layer, the spacer layer and the lower reflective layer, for example, the diameter of the polyimide rope 3 is D millimeters, and 2≤D≤6 is satisfied.

[0039] In actual application, the preparation process of the multilayer heat shield is specifically as follows:

[0040] First, the multilayer heat shield body 1 is made, and a punching device is used to punch the multilayer heat shield body 1;

[0041] Second, according to the structure of the inner side of the rocket second stage rear short shell, the multilayer heat shield body 1 is correspondingly cut into a plurality of short pieces;

[0042] Third, according to the diameter of the rocket second stage short shell and the distance from the short shell to the engine throat, the polyimide rope 3 is knotted into a multilayer mounting framework, and the framework is in a circular ring network as shown in the drawing; Figure 1

[0043] Fourth, the plurality of short pieces are sewn on the framework through the polyimide rope 3, and the framework with the plurality of short pieces is connected to the rocket second stage bottom support through the polyimide rope 3;

[0044] Fifth, the hook surface of the Velcro 2 is sewn on the edge of the short piece, the hook surface of the Velcro 2 and the pile surface of the Velcro are respectively sewn on the two edges of the short piece overlap (adjacent short pieces), and the hook surface and the pile surface of the matching Velcro are adhered to each other to form a multilayer heat shield structure (at least one opening is formed between adjacent short pieces to facilitate installation and maintenance of the short pieces, and the opening is covered by adhering the circumferential outer surface of the short piece to the opening).

[0045] Sixth, the pile surface of the Velcro is pasted on the inner side of the rocket second stage rear short shell near the lower edge area and the rocket frame surface (the Velcro is adhesively connected to the inner side of the rocket second stage rear short shell near the lower edge area and the rocket frame surface), and the hook surface part of the outermost side of the plurality of short pieces is pasted with the corresponding pile surface of the Velcro 2 pasted on the inner side of the rocket second stage rear short shell near the lower edge area and the rocket frame surface, and the installation and fixing of the multilayer heat shield body are completed.

[0046] The utility model also provides a rocket sub-stage structure, contains above any one for rocket second stage bottom whole heat protection multilayer heat shield.

[0047] The above merely illustrates the specific embodiments of the utility model, and any equivalent changes and modifications made by any person skilled in the art without departing from the concept and principles of the utility model shall belong to the protection scope of the utility model.​

Claims

1. A multilayer heat shield for the overall heat protection of the second stage bottom of a rocket, which protects the upper elements of the second stage engine of the rocket by being installed on the second stage bottom of the rocket, characterized in that, At least comprising: an upper reflective layer with heat-proof function, a lower reflective layer, a spacer layer and a locking wire; the spacer layer is arranged between the upper reflective layer and the lower reflective layer, and the upper and lower surfaces of the spacer layer are in close contact with the lower surface of the upper reflective layer and the upper surface of the lower reflective layer respectively; the upper reflective layer, the lower reflective layer and the spacer layer are sewn together by the locking wire to form a multilayer heat shield body, and the locking wire is also used to connect with the rocket second stage bottom support to fix the multilayer heat shield body on the rocket second stage bottom.

2. The multilayer heat shield for the rocket second stage bottom monolith heat protection according to claim 1, characterized in that, The surface of the multilayer heat shield body is uniformly provided with exhaust holes, and the exhaust holes penetrate through the multilayer heat shield body.

3. The multilayer heat shield for the rocket second stage bottom monolith heat protection according to claim 2, characterized in that, The multilayer heat shield body volume is V liters, and the exhaust hole area is Scm 2 S = 0.1V.

4. The multilayer heat shield for the rocket second stage bottom monolith heat shield according to claim 1, characterized in that, The thickness of the multilayer heat shield body is A microns, wherein 80≤A≤130.

5. The multilayer heat shield for the rocket second stage bottom monolith heat protection according to claim 1, characterized in that, The upper reflective layer and the lower reflective layer are both double-sided aluminum-plated polyimide films.

6. The multilayer heat shield for the rocket second stage bottom monolith heat protection according to claim 5, characterized in that, The thickness of the double-sided aluminum-plated polyimide film is B microns, wherein 15≤B≤40.

7. The multilayer heat shield for a rocket second stage bottom monolithic thermal protection according to claim 1, characterized in that, The spacer layer is a glass fiber cloth.

8. The multilayer heat shield for the rocket second stage bottom monolith heat protection according to claim 7, characterized in that, The thickness of the glass fiber cloth is C microns, wherein 40≤C≤85.

9. The multilayer heat shield for a rocket second stage bottom monolithic thermal protection according to claim 1, characterized in that, The locking wire is a polyimide rope, and the diameter of the polyimide rope is D millimeters, wherein 2≤D≤6.

10. A rocket stage structure, characterized by A multilayer heat shield for overall heat protection of a rocket second stage bottom comprising the multilayer heat shield according to any one of claims 1-9.

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