Launch vehicle second-level bottom integral heat-proof structure

Abstract

The utility model relates to a carrier rocket secondary bottom integral heat-proof structure, which relates to the technical field of liquid carrier rockets, and comprises a rocket body rear short shell, an engine, heat-proof cloth and a bearing structure, the rocket body rear short shell is detachably connected with the outer wall of a combustion chamber of the engine; the heat-proof cloth forms a cylindrical structure and forms a heat-proof cover body, the head and the tail of the heat-proof cloth are detachably connected, an opening at one end of the heat-proof cover body is detachably connected with the bottom end of the rear short shell of the rocket body, and an opening at the other end of the heat-proof cover body is detachably connected with the outer wall of a spray pipe expansion section of the engine or the outer wall of a combustion chamber of the engine; the force bearing structure is installed on the heat-proof cover body, and the two ends of the force bearing structure are connected with the rocket body rear short shell, the outer wall of the spray pipe expansion section of the engine or the outer wall of a combustion chamber of the engine respectively. The general assembly time of the rocket body can be shortened, the working efficiency is improved, and the labor cost of heat-proof treatment is reduced.

Description

Technical Field

[0001] The utility model relates to the technical field of liquid launch vehicles, in particular to an integral heat protection structure of the second-stage bottom of a launch vehicle. Background Art

[0002] A multi-stage rocket is a space launch vehicle composed of several stages, each equipped with independent engines and propellants. During the flight, the rockets of each stage work and separate in sequence to gradually increase the speed and altitude of the rocket, and finally send the rocket into the predetermined orbit.

[0003] The second stage of a rocket refers to the second stage of a multi-stage rocket. When the fuel of the first stage of the rocket is exhausted, the engine of the first stage rocket will shut down and separate, and the second stage rocket will ignite and continue to work to continue to provide thrust for the rocket.

[0004] The rear bottom and rear short shell of the rocket are components of the rocket tank. The rear bottom is the rear end closed component of the tank, and the rear short shell is the barrel section structure connecting the rear bottom and the tank body, which plays a role of transition and reinforcement. The second stage of a liquid carrier rocket usually uses a single engine as the power source of the rocket body. In order to reduce the weight of the second-stage rocket body and shorten the axial size of the second-stage rocket body, the engine will be connected to the rear bottom of the second-stage rocket tank through a frame. Therefore, the distance between the engine and the rear bottom and rear short shell of the second-stage rocket will be relatively close.

[0005] When the second-stage rocket engine is working, the high-temperature wall of the engine nozzle will generate large thermal radiation, and the distance between the engine and the rear bottom and rear short shell of the second-stage rocket is relatively close, which can easily cause thermal damage to the instruments and cables on the rear bottom and rear short shell. Therefore, it is necessary to carry out heat protection treatment on the instruments and cables on the rear bottom and rear short shell.

[0006] At present, the heat protection treatment of the rear bottom and rear short shell of the rocket is usually carried out by covering the instruments and cables on the rear bottom and rear short shell with heat-proof cloth and pasting aluminum-plated film on the outside of the heat-proof cloth. Since there are many instruments and cables on the rear bottom and rear short shell, during the final assembly of the rocket body, the above heat protection treatment method will cause the operators to spend a long time on the coating work, and the steps are very cumbersome, which greatly reduces the work efficiency and increases the labor cost.

[0007] Therefore, how to conveniently carry out heat protection treatment on the instruments, equipment and cables on the rear bottom and rear short shell, thereby shortening the rocket body assembly time, increasing work efficiency, and reducing labor costs, has become a problem that needs to be solved urgently. Utility Model Content

[0008] The utility model aims to provide an integral heat protection structure for the bottom of the second stage of a launch vehicle to solve the problems existing in the above-mentioned prior art.

[0009] To achieve the above purpose, the utility model provides the following solutions:

[0010] The utility model provides an integral heat protection structure for the bottom of the second stage of a carrier rocket, wherein the rear short shell of the rocket body is detachably connected to the outer wall of the combustion chamber of the engine;

[0011] The heat protection cloth is surrounded by a cylindrical structure and constitutes a heat protection cover body, and the head and tail joints of the heat protection cloth are detachably connected, the opening at one end of the heat protection cover body is detachably connected to the bottom end of the rear short shell of the rocket body, and the opening at the other end is detachably connected to the outer wall of the nozzle expansion section of the engine or the outer wall of the combustion chamber of the engine;

[0012] The load-bearing structure is installed on the heat protection cover, and the two ends of the load-bearing structure are respectively connected to the rear short shell of the rocket body, the outer wall of the nozzle expansion section of the engine or the outer wall of the combustion chamber of the engine.

[0013] According to one embodiment of the utility model, the heat shield body is an inverted frustum of a cone structure, the opening of the large circular surface of the inverted frustum of a cone structure of the heat shield body is detachably connected to the bottom end of the rear short shell of the rocket body, and the opening of the small circular surface of the inverted frustum of a cone structure of the heat shield body is detachably connected to the outer wall of the nozzle expansion section of the engine or the outer wall of the combustion chamber of the engine.

[0014] According to one embodiment of the utility model, the number of the heat-proof cloths is several, and the several heat-proof cloths form a cylindrical structure and constitute the heat-proof cover body, the adjacent heat-proof cloths are detachably connected, the heat-proof cloths on the heat-proof cover body are divided into several layers along the axial direction, and the heat-proof cloths on the heat-proof cover body are divided into several columns along the circumferential direction.

[0015] According to one embodiment of the utility model, the load-bearing structure includes a longitudinal high-temperature rope and annular high-temperature rope, both of which are arranged tautly, and both of which are installed on the heat protection cover, and the two ends of the longitudinal high-temperature rope are respectively connected to the rear short shell of the rocket body, the outer wall of the nozzle expansion section of the engine or the outer wall of the combustion chamber of the engine.

[0016] According to one embodiment of the utility model, the number of the longitudinal high-temperature ropes is several, and each of the longitudinal high-temperature ropes is respectively and sequentially arranged corresponding to the connection point of each column of the heat-proof cloth, and the number of the circumferential high-temperature ropes is several, and each of the circumferential high-temperature ropes is respectively and sequentially arranged corresponding to the connection point of each layer of the heat-proof cloth.

[0017] According to one embodiment of the utility model, flame-retardant nylon fasteners are installed on the heat-proof cloth, the bottom end of the short rear shell of the rocket body, the outer wall of the nozzle expansion section of the engine or the outer wall of the combustion chamber of the engine, and several heat-proof cloths are detachably connected by the flame-retardant nylon fasteners to form the heat-proof cover body; the heat-proof cover body is detachably connected to the bottom end of the short rear shell of the rocket body, the outer wall of the nozzle expansion section of the engine or the combustion chamber of the engine through the flame-retardant nylon fasteners.

[0018] According to one embodiment of the utility model, the number of the flame-retardant nylon buckles installed on the heat-proof cloth is several, and the several flame-retardant nylon buckles on each heat-proof cloth are arranged in sequence along the edge of the heat-proof cloth, and a gap is set between two adjacent flame-retardant nylon buckles.

[0019] According to an embodiment of the utility model, the heat-proof cloth includes an aluminum-plated film layer, a high-silica cloth layer and an aluminum-plated film layer which are sequentially arranged from the outside to the inside.

[0020] According to an embodiment of the utility model, the four sides of the heat-proof cloth are bonded by bonding materials.

[0021] According to an embodiment of the utility model, the heat-proof cloth is provided with through holes, and the area of ​​the through holes is 0.5%-1.5% of the area of ​​the heat-proof cloth.

[0022] The utility model has at least the following technical effects:

[0023] The utility model provides an integral heat protection structure for the second-stage bottom of a carrier rocket. By arranging a heat protection cover body composed of a load-bearing structure and a heat protection cloth, heat protection treatment can be conveniently performed on instruments and cables on the rear bottom and the rear short shell. There is no need to cover the instruments and cables on the rear bottom and the rear short shell with heat protection cloth, and there is no need to stick an aluminum-plated film on the outside of the heat protection cloth after covering. The steps of heat protection treatment are reduced, the overall assembly time of the rocket body is greatly shortened, the work efficiency is increased, and the labor cost of heat protection treatment is reduced. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] In order to more clearly illustrate the embodiments of the utility model or the technical solutions in the prior art, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the utility model. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0025] Figure 1 This is a schematic diagram of the overall structure of the utility model installed on the short shell at the rear of the arrow body and the engine;

[0026] Figure 2 It is a schematic diagram of the overall structure of the utility model;

[0027] Figure 3 It is a schematic diagram of the overall structure of the utility model when viewed from above;

[0028] Figure 4 It is a schematic diagram of the overall structure of the utility model from a top view;

[0029] Figure 5 This is a schematic diagram of the overall structure of the heat-proof cloth in the utility model;

[0030] Figure 6 It is a schematic diagram of the overall structure of the connection between the short shell of the rear arrow body and the heat protection cloth of the utility model;

[0031] Among them, 1. Heat-proof cloth; 2. Short shell at the rear of the rocket body; 3. Engine; 4. Longitudinal high-temperature rope; 5. Circumferential high-temperature rope; 6. Flame-retardant nylon fastener; 7. Heat-proof cover; 8. Turbine pump. DETAILED DESCRIPTION

[0032] The features and exemplary embodiments of various aspects of the present invention will be described in detail below. In order to make the purpose, technical solutions and advantages of the present invention clearer, the present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are only configured to explain the present invention and are used to illustrate the principles of the present invention, and are not configured to limit the present invention. In addition, the structural components in the drawings are not necessarily drawn to scale. For example, the sizes of some structural components or areas in the drawings may be enlarged for other structural components or areas to help understand the embodiments of the present invention.

[0033] The directional words appearing in the following description are all directions shown in the figures, and do not limit the specific structure of the embodiments of the utility model. In the description of the utility model, it should be noted that, unless otherwise specified, the terms "installation", "connection" and "connection" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be directly connected or indirectly connected through an intermediate medium. For ordinary technicians in this field, the specific meanings of the above terms in the utility model can be understood according to the specific circumstances.

[0034] In addition, the terms "include", "comprise", "have" or any other variations thereof are intended to cover non-exclusive inclusion, so that a structure or component including a series of elements includes not only those elements, but also other mechanical elements that are not explicitly listed or inherent in the structure or component. In the absence of more restrictions, the elements defined by the sentence "include..." do not exclude the existence of other identical elements in the article or device including the elements.

[0035] Spatially related terms such as "below", "beneath", "under", "low", "above", "on", "high", etc. are used to facilitate description to explain the positioning of one element relative to a second element, indicating that these terms are intended to cover different orientations of the device in addition to orientations different from those shown in the figures. In addition, for example, "one element is above / below another element" can mean that the two elements are in direct contact, or that there are other elements between the two elements. In addition, terms such as "first", "second", etc. are also used to describe various elements, regions, parts, etc., and do not specifically refer to the meaning of order or sequence, and should not be regarded as limiting. Similar terms are used throughout the description to represent similar elements.

[0036] In the process of describing the utility model below, in certain scene descriptions, only "rocket", "launch vehicle", "spacecraft", "space launch vehicle" or "missile" may be used. This is only for the convenience of description, and its connotation is not limited to the specific words used. Generally, the launch vehicle of the utility model includes not only space launch vehicles and rockets used to carry satellites or spacecraft or other probes, but also various types of missiles, rockets and other weapons used to carry military payloads, as well as similar products that can send payloads into the air. When interpreting the above specific words, those skilled in the art shall not limit the launch vehicle to only one of the space launch vehicles, rockets or missiles based on the specific words used to describe the scene, thereby narrowing the scope of protection of the utility model.

[0037] For those skilled in the art, the present invention can be implemented without some of these specific details. The following description of the embodiments is only intended to provide a better understanding of the present invention by showing examples of the present invention.

[0038] The utility model provides an integral heat protection structure of the second stage bottom of a carrier rocket, comprising a short rear shell 2 of a rocket body, an engine 3, a heat protection cloth 1 and a load-bearing structure, wherein:

[0039] The engine 3 is divided into three parts from upstream to downstream, namely, a combustion chamber, a nozzle expansion section and a nozzle extension section, wherein the combustion chamber and the nozzle expansion section are low-temperature sections, and the nozzle extension section is a high-temperature section. The above are all prior arts known to those skilled in the art and will not be elaborated herein.

[0040] The bottom end of the short rear shell 2 of the rocket body is detachably connected to the top outer wall of the combustion chamber at the top of the engine 3. In this embodiment, a frame (not shown in the figure) is arranged between the short rear shell 2 of the rocket body and the engine 3, and the two ends of the frame can be detachably connected to the bottom end of the short rear shell 2 of the rocket body and the top outer wall of the combustion chamber at the top of the engine 3 by bolts, respectively. The frame is an existing component known to those skilled in the art and will not be described in detail here.

[0041] Reference Figure 1 The heat-proof cloth 1 is surrounded by a cylindrical structure and forms a heat-proof cover body 7, and the head and tail joints of the heat-proof cloth 1 are detachably connected. Figure 6 The opening at one end of the heat shield 7 is detachably connected to the bottom end of the rear short shell 2 of the rocket body, and the opening at the other end is detachably connected to the outer wall of the nozzle expansion section of the engine 3 or the outer wall of the combustion chamber of the engine 3. Further, the combustion chamber of the engine 3 can be located in whole or in part inside the heat shield 7. More preferably, the nozzle expansion section of the engine 3 can also be located in whole or in part inside the heat shield 7.

[0042] In one embodiment of the utility model, the lower end of the heat shield 7 is connected to the outer wall of the nozzle expansion section of the engine 3. At this time, the nozzle extension section of the engine 3 is placed outside the heat shield 7, and the combustion chamber of the engine 3 and the instruments and cables in the short rear shell 2 of the rocket body are all located inside the heat shield 7, so that the heat shield 7 can effectively block the high temperature heat on the wall surface of the nozzle extension section of the engine 3, prevent its heat from affecting the instruments and cables in the short rear shell 2 of the rocket body, and achieve the isolation of the instruments and cables from the high temperature wall surface of the nozzle extension section of the engine 3, ensuring the normal temperature of the instruments and cables in the short rear shell 2 of the rocket body. Among them, the combustion chamber and the nozzle expansion section of the low temperature section will not cause high temperature effects on the instruments and cables in the short rear shell 2 of the rocket body, so they can be located inside the heat shield 7 as a whole or in part.

[0043] Alternatively, the lower end of the heat shield 7 is connected to the outer wall of the combustion chamber of the engine 3. At this time, the nozzle extension section of the engine 3 and the nozzle expansion section of the engine 3 will be located outside the heat shield 7, and the instruments and cables in the short rear shell 2 of the rocket body will be located inside the heat shield 7. Therefore, it can also provide high temperature protection for the instruments and cables in the short rear shell 2 of the rocket body.

[0044] The load-bearing structure is installed on the heat protection cover 7, and the two ends of the load-bearing structure are respectively fixedly connected to the bottom end of the rear short shell 2 of the rocket body, the nozzle expansion section of the engine 3 or the outer wall of the combustion chamber of the engine 3.

[0045] In this embodiment, the lower end of the heat shield 7 is connected to the outer wall of the nozzle expansion section of the engine 3, and the load-bearing structure is also connected to the outer wall of the nozzle expansion section of the engine 3 along with the heat shield 7.

[0046] In addition, if the lower end of the heat shield 7 is connected to the outer wall of the combustion chamber of the engine 3 , the load-bearing structure will be connected to the outer wall of the combustion chamber of the engine 3 along with the heat shield 7 .

[0047] In the utility model, the load-bearing structure can transfer the surface pressure load on the heat shield body 7 to the rocket body, thereby supporting the heat shield body 7.

[0048] In addition, in this embodiment, referring to Figure 1 The outside of the engine 3 also includes a turbopump 8, and the turbopump 8 can also be located on the outside of the heat-proof cover 7, thereby preventing the heat on the wall of the turbopump 8 from affecting the instruments and cables in the short rear shell 2 of the rocket body, further ensuring the normal temperature of the instruments and cables in the short rear shell 2 of the rocket body.

[0049] Among them, the two ends of the turbopump 8 are respectively connected and communicated with the rocket tank in the short rear shell 2 of the rocket body and the combustion chamber of the engine 3. Its function is to use the pump force to push the fuel and oxidizer in the rocket tank in the short rear shell 2 of the rocket body so that the two can be added to the combustion chamber of the engine 3 more quickly. The above are all existing technologies known to technical personnel in this field and will not be elaborated here.

[0050] According to one embodiment of the present invention, referring to Figure 1 and Figure 2 The heat shield body 7 is an inverted frustum structure, and the opening of the large circular surface of the inverted frustum structure of the heat shield body 7 is detachably connected to the bottom end of the rear short shell 2 of the rocket body, and the opening of the small circular surface of the inverted frustum structure of the heat shield body 7 is detachably connected to the outer wall of the nozzle expansion section of the engine 3 or the outer wall of the combustion chamber of the engine 3.

[0051] In this embodiment, the opening of the small circular surface of the inverted frustum structure of the heat shield body 7 is detachably connected to the outer wall of the nozzle expansion section of the engine 3 .

[0052] In one embodiment of the utility model, because the side surface of the heat shield body 7 of the inverted frustum structure is an inclined surface, when the nozzle of the nozzle extension section at the bottom end of the engine 3 sprays out heat, the side surface of the heat shield body 7 can effectively block the heat sprayed out, thereby preventing the high temperature from affecting the instruments and cables in the short shell 2 at the rear of the rocket body.

[0053] In this embodiment, refer to Figure 2-4 The number of heat-proof cloths 1 is several, and several heat-proof cloths 1 form a cylindrical structure and constitute the heat-proof cover body 7. Adjacent heat-proof cloths 1 are detachably connected, and the number of heat-proof cloths 1 is preferably thirty-six. The heat-proof cloths 1 on the heat-proof cover body 7 are divided into several layers along the axial direction (vertical direction), preferably three layers; the heat-proof cloths 1 on the heat-proof cover body 7 are divided into several columns along the circumferential direction (lateral direction), preferably twelve columns.

[0054] For example, in this embodiment, the area of ​​each layer of heat-proof cloth 1 on the heat-proof cover body 7 may be the same, and the area of ​​the upper layer of heat-proof cloth 1 adjacent to each other may be larger than the area of ​​the lower layer of heat-proof cloth 1. Figure 5The shape of the heat-proof cloth 1 can be tile-shaped, so that a plurality of heat-proof cloths 1 can be smoothly used to form a heat-proof cover body 7 with an inverted truncated cone structure.

[0055] According to an embodiment of the utility model, the load-bearing structure includes a longitudinal high-temperature rope 4 and an annular high-temperature rope 5, both of which are tautly arranged, and the annular high-temperature rope 5 is an annular structure, which is connected end to end, and the longitudinal high-temperature rope 4 and the annular high-temperature rope 5 are both fixedly installed on the heat shield 7. The two ends of the longitudinal high-temperature rope 4 are respectively fixedly connected to the bottom end of the rear short shell 2 of the rocket body, the outer wall of the nozzle expansion section of the engine 3, or the outer wall of the combustion chamber of the engine 3.

[0056] In this embodiment, refer to Figure 1 The longitudinal high temperature rope 4 is arranged longitudinally and tautly on the outside of the heat shield 7, and the circumferential high temperature rope 5 is sleeved circumferentially and tautly on the outside of the heat shield 7. When the heat shield 7 is subjected to surface pressure load, the tautly arranged longitudinal high temperature rope 4 and circumferential high temperature rope 5 can support the heat shield 7 and transfer the surface pressure load to the rocket body.

[0057] In this embodiment, the bottom end of the longitudinal high-temperature rope 4 is fixedly connected to the outer wall of the nozzle expansion section of the engine 3.

[0058] In this embodiment, the longitudinal high-temperature rope 4 and the annular high-temperature rope 5 can be fixedly connected to the heat shield 7 by sewing. The fixed connection method can also be any method known in the art. For example, the longitudinal high-temperature rope 4 and the bottom end of the short shell 2 of the rear of the arrow body, the outer wall of the nozzle expansion section of the engine 3, or the outer wall of the combustion chamber of the engine 3 can be fixedly connected by bolts, which is not particularly limited here. The longitudinal high-temperature rope 4 and the annular high-temperature rope 5 can both be preferably high-temperature resistant ropes such as aramid braided ropes, glass fiber ropes or carbon fiber ropes known in the art, which are not particularly limited here.

[0059] In this embodiment, refer to Figure 2-4 The number of longitudinal high-temperature ropes 4 is several, preferably twelve, and the twelve longitudinal high-temperature ropes 4 are respectively and sequentially arranged corresponding to the connection of each row of heat-proof cloth 1. The number of circumferential high-temperature ropes 5 is several, preferably two, and the two circumferential high-temperature ropes 5 are respectively and sequentially arranged corresponding to the connection of each layer of heat-proof cloth 1. Among them, the longitudinal high-temperature ropes 4 and the circumferential high-temperature ropes 5 can form a load-bearing skeleton, thereby transmitting the surface pressure load on the heat-proof cloth 1 to the rocket body through the two.

[0060] The positions of the longitudinal high-temperature rope 4 and the annular high-temperature rope 5 are at a certain distance from the connection point of each heat-proof cloth 1. Therefore, when removing one or more of the heat-proof cloths 1, the longitudinal high-temperature rope 4 and the annular high-temperature rope 5 will not interfere with the heat-proof cloth 1, thereby ensuring the smooth removal of the heat-proof cloth 1.

[0061] According to one embodiment of the utility model, the heat protection cloth 1, the bottom end of the short shell 2 of the rocket body, and the outer wall of the nozzle expansion section of the engine 3 or the outer wall of the combustion chamber of the engine 3 are all fixedly installed with flame retardant nylon fasteners 6, and a plurality of heat protection cloths 1 are detachably connected through the flame retardant nylon fasteners 6 to form a heat protection shield body 7. The heat protection shield body 7 is connected to the bottom end of the short shell 2 of the rocket body through the flame retardant nylon fasteners 6 (refer to Figure 6 ), the outer wall of the nozzle expansion section of the engine 3 or the combustion chamber of the engine 3 can be detachably connected; wherein, the flame retardant nylon fastener 6 is a prior art known to those skilled in the art, and its material can preferably be an aromatic nylon material known in the art.

[0062] In this embodiment, the flame-retardant Velcro 6 is fixedly mounted on the outer wall of the nozzle expansion section of the engine 3 , thereby detachably connecting the bottom end of the heat shield 7 to the outer wall of the nozzle expansion section of the engine 3 .

[0063] In this embodiment, the thickness of the heat protection cloth 1 is preferably 0.1mm-0.3mm, which is relatively thin. Flame-retardant nylon fasteners 6 can be used to connect multiple heat protection cloths 1. The installation positions of the hook surface and the wool surface of the flame-retardant nylon fastener 6 on the heat protection cloth 1, the bottom end of the short shell 2 of the rear of the rocket body, and the outer wall of the nozzle expansion section of the engine 3 are not particularly limited. Technical personnel in this field can install them according to actual conditions so that they can be connected to each other.

[0064] In addition, the detachable connection method between several heat-proof cloths 1, between the heat-proof cover body 7 and the bottom end of the short rear shell 2 of the rocket body, and the outer wall of the nozzle expansion section of the engine 3 can be any detachable connection method known in the art. For example, several heat-proof cloths 1 can be detachably connected by buttons, and the heat-proof cover body 7 and the bottom end of the short rear shell 2 of the rocket body, and the outer wall of the nozzle expansion section of the engine 3 can also be detachably connected by buttons, which is not particularly limited here.

[0065] According to one embodiment of the utility model, referring to Figure 5 The number of flame-retardant nylon fasteners 6 installed on the heat-proof cloth 1 is several, and the several flame-retardant nylon fasteners 6 on each heat-proof cloth 1 can be arranged in sequence along the edge of the heat-proof cloth 1, and a gap is set between two adjacent flame-retardant nylon fasteners 6.

[0066] By setting the gaps between adjacent flame-retardant nylon fasteners 6, exhaust inside the heat shield 7 is facilitated during the flight of the rocket body; at the same time, the setting of the gaps also makes it convenient for the staff to enter the heat shield 7 to perform operations, that is, the setting of the gaps can also make it convenient for the staff to unbutton the heat-proof cloth 1. Specifically, the staff can put their hands into the gaps and tear the heat-proof cloth 1 outwards to easily remove the heat-proof cloth 1.

[0067] According to an embodiment of the present invention, the heat-proof cloth 1 comprises a multi-layer structure consisting of an aluminum-plated film layer, a high-silica cloth layer and an aluminum-plated film layer which are sequentially arranged from the outside to the inside.

[0068] In this embodiment, the heat-proof cloth 1 preferably has a three-layer structure, the outer layer of the heat-proof cloth 1 is an aluminum-plated film layer, the middle layer is a high-silica cloth layer, and the inner layer is an aluminum-plated film layer, wherein the aluminum-plated film and high-silica cloth are existing materials known in the art and will not be elaborated here.

[0069] According to one embodiment of the utility model, the heat-proof cloth 1 with a multi-layer structure is bonded on all sides by any suitable known adhesive material, preferably by using an adhesive tape known in the art; thereby, it is possible to effectively prevent excess materials on the high-silica cloth layer in the middle layer of the heat-proof cloth 1 from falling onto the rocket body.

[0070] According to one embodiment of the utility model, a through hole is provided on the heat-proof cloth 1, and the area of ​​the through hole is 0.5%-1.5% of the area of ​​the heat-proof cloth 1; wherein, the provision of the through hole can play a ventilation role, which can reduce the force on the heat-proof cloth 1 during flight, and further ensure the stability of the heat-proof cloth 1 during flight.

[0071] In this embodiment, the area of ​​the through hole is preferably about 1% of the area of ​​the heat-proof cloth 1. If the area of ​​the through hole is too small, it will not play a role in reducing the load of the heat-proof cloth 1. If the area of ​​the through hole is too large, the heat of the high-temperature wall surface of the extended section of the nozzle of the engine 3 will enter the heat-proof cover 7, affecting the heat-proof effect of the heat-proof cover 7.

[0072] The above-mentioned embodiments of the present invention can be combined with each other and have corresponding technical effects.

[0073] The above are only preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. An integral heat protection structure for the bottom of the second stage of a launch vehicle, comprising a short rear shell (2) of a rocket body and an engine (3), characterized in that: It also includes a heat-proof cloth (1) and a load-bearing structure, wherein: The short rear shell (2) of the rocket body is detachably connected to the outer wall of the combustion chamber of the engine (3); The heat protection cloth (1) is surrounded by a cylindrical structure and constitutes a heat protection cover body (7), and the head and tail joints of the heat protection cloth (1) are detachably connected, the opening at one end of the heat protection cover body (7) is detachably connected to the bottom end of the rear short shell (2) of the rocket body, and the opening at the other end is detachably connected to the outer wall of the nozzle expansion section of the engine (3) or the outer wall of the combustion chamber of the engine (3); The load-bearing structure is mounted on the heat shield (7), and two ends of the load-bearing structure are respectively connected to the rear short shell (2) of the rocket body, the outer wall of the nozzle expansion section of the engine (3), or the outer wall of the combustion chamber of the engine (3).

2. The integral heat protection structure of the second stage bottom of a launch vehicle according to claim 1, characterized in that: The heat shield (7) is an inverted truncated cone structure, the opening of the large circular surface of the inverted truncated cone structure of the heat shield (7) is detachably connected to the bottom end of the rear short shell (2) of the rocket body, and the opening of the small circular surface of the inverted truncated cone structure of the heat shield (7) is detachably connected to the outer wall of the nozzle expansion section of the engine (3) or the outer wall of the combustion chamber of the engine (3).

3. The integral heat protection structure of the second stage bottom of a launch vehicle according to claim 2, characterized in that: The number of the heat-proof cloths (1) is several, and the several heat-proof cloths (1) form a cylindrical structure and constitute the heat-proof cover body (7), the adjacent heat-proof cloths (1) are detachably connected, the heat-proof cloths (1) on the heat-proof cover body (7) are divided into several layers along the axial direction, and the heat-proof cloths (1) on the heat-proof cover body (7) are divided into several columns along the circumferential direction.

4. The integral heat protection structure for the second stage bottom of a launch vehicle according to claim 3, characterized in that: The load-bearing structure comprises a longitudinal high-temperature rope (4) and an annular high-temperature rope (5), the longitudinal high-temperature rope (4) and the annular high-temperature rope (5) are both arranged in a taut manner, and the longitudinal high-temperature rope (4) and the annular high-temperature rope (5) are both installed on the heat-proof cover (7), and the two ends of the longitudinal high-temperature rope (4) are respectively connected to the rear short shell (2) of the rocket body, the outer wall of the nozzle expansion section of the engine (3), or the outer wall of the combustion chamber of the engine (3).

5. The integral heat protection structure for the second stage bottom of a launch vehicle according to claim 4, characterized in that: The number of the longitudinal high-temperature ropes (4) is several, and each of the longitudinal high-temperature ropes (4) is respectively and sequentially arranged corresponding to the connection point of each row of the heat-proof cloth (1); the number of the circumferential high-temperature ropes (5) is several, and each of the circumferential high-temperature ropes (5) is respectively and sequentially arranged corresponding to the connection point of each layer of the heat-proof cloth (1).

6. The integral heat protection structure for the second stage bottom of a launch vehicle according to claim 1, characterized in that: The heat protection cloth (1), the bottom end of the short rear shell (2) of the rocket body, the outer wall of the nozzle expansion section of the engine (3) or the outer wall of the combustion chamber of the engine (3) are all installed with flame-retardant nylon fasteners (6); a plurality of the heat protection cloths (1) are detachably connected via the flame-retardant nylon fasteners (6) to form the heat protection cover body (7); the heat protection cover body (7) is detachably connected to the bottom end of the short rear shell (2) of the rocket body, the outer wall of the nozzle expansion section of the engine (3) or the combustion chamber of the engine (3) via the flame-retardant nylon fasteners (6).

7. The integral heat protection structure for the second stage bottom of a launch vehicle according to claim 6, characterized in that: The number of the flame-retardant nylon buckles (6) installed on the heat-proof cloth (1) is several, and the several flame-retardant nylon buckles (6) on each heat-proof cloth (1) are arranged in sequence along the edge of the heat-proof cloth (1), and a gap is arranged between two adjacent flame-retardant nylon buckles (6).

8. The integral heat protection structure for the second stage bottom of a launch vehicle according to claim 1, characterized in that: The heat-proof cloth (1) comprises an aluminum-plated film layer, a high-silica cloth layer and an aluminum-plated film layer, which are arranged in sequence from the outside to the inside.

9. The integral heat protection structure for the second stage bottom of a launch vehicle according to claim 8, characterized in that: The heat-proof cloth (1) is bonded around four sides by bonding material.

10. The integral heat protection structure of the second stage bottom of a launch vehicle according to claim 1, characterized in that: The heat-proof cloth (1) is provided with a through hole, and the area of ​​the through hole is 0.5%-1.5% of the area of ​​the heat-proof cloth (1).

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