An engine composite pipe body

Abstract

This utility model discloses an engine composite tube body, relating to the field of engine technology. It includes a front section and a rear section connected to the rear end of the front section. The front section includes a front shell and a front heat insulation bushing disposed inside the front shell. The rear section includes a rear shell, a rear heat insulation bushing disposed inside the rear shell, and a working tube structure disposed inside the rear heat insulation bushing. By connecting the front and rear sections, with the front section including the front shell and the front heat insulation bushing, and the rear section including the rear shell and the rear heat insulation bushing, and with the working tube structure installed within the rear heat insulation bushing, heat can be prevented from being transferred from the working tube structure to the heat insulation bushing, avoiding a rapid increase in shell temperature. It features lightweight, ablation resistance, and strong erosion resistance, effectively maintaining structural integrity during engine operation and ensuring normal rocket flight.

Description

Technical Field

[0001] This utility model relates to the field of engine technology, specifically to an engine composite tube body. Background Technology

[0002] A rocket engine is the propulsion system of a rocket, propelling the rocket body into its designated orbit and delivering cargo to its destination. Existing rocket engines primarily include liquid-fueled rocket engines and solid-fueled rocket engines.

[0003] Liquid rocket engines use liquid propellants and are characterized by adjustable thrust and high efficiency. Common liquid propellants include liquid oxygen and kerosene, liquid oxygen and methane, etc.

[0004] Solid rocket engines use solid propellants, have a simple structure, and are suitable for rapid launch, but their thrust is not adjustable. They are typically used in boosters or missiles.

[0005] With the rapid development of launch technology and the widespread application of information technology, the requirements for rocket range and accuracy are becoming increasingly stringent, which in turn leads to higher performance requirements for its propulsion system, namely the rocket engine.

[0006] By changing the propellant of the rocket engine from the original double-base propellant to a composite propellant, high specific impulse and long range can be achieved. However, the high pressure, high temperature and high speed airflow after short combustion cause severe erosion and scouring of the steel tube, resulting in low reliability.

[0007] Therefore, how to solve the reliability problem of rocket engines using composite propellants is one of the key tasks for those skilled in the art. Utility Model Content

[0008] The purpose of this invention is to provide an engine composite tube body to solve the reliability problem of rocket engines using composite propellants.

[0009] To solve the above-mentioned technical problems, this utility model provides an engine composite pipe body, including a front section of the pipe body and a rear section of the pipe body whose front end is connected to the rear end of the front section of the pipe body. The front section of the pipe body includes a front section shell and a front section heat insulation bushing disposed inside the front section shell. The rear section of the pipe body includes a rear section shell, a rear section heat insulation bushing disposed inside the rear section shell, and a working pipe structure disposed inside the rear section heat insulation bushing.

[0010] The working tube structure is connected to the rear heat insulation bushing and the rear housing by multiple pins, or the working tube structure is connected to the rear heat insulation bushing and the rear housing by multiple bolts.

[0011] The rear end of the front housing is located inside the rear housing, and the front insulation bushing and the rear insulation bushing overlap at various points inside the rear housing.

[0012] The front section and the rear section of the pipe are connected by bolts or flanges.

[0013] The front shell and the rear shell are made of 18Ni high-alloy ultra-high-strength steel, 20Ni high-alloy ultra-high-strength steel or 25N high-alloy ultra-high-strength steel.

[0014] The front insulation bushing and the rear insulation bushing are phenolic glass fiber plastic insulation bushings or ceramic fiber insulation bushings.

[0015] The working tube structure is either a graphite working tube structure or a ceramic working tube structure.

[0016] In the longitudinal section of the working pipe structure, the ratio of the outlet area of ​​the pipe body to the throat area is 1:2 to 3:4.

[0017] The throat of the working tube structure includes a central throat and a plurality of edge throats evenly distributed around the central throat.

[0018] The number of edge throat holes is 6 to 10.

[0019] The engine composite tube provided in this embodiment of the present invention has the following advantages compared with the prior art:

[0020] The engine composite tube provided in this embodiment of the utility model adopts a front section and a rear section of tube body connection. The front section of tube body includes a front shell and a front heat insulation bushing, and the rear section of tube body includes a rear shell and a rear heat insulation bushing. The working tube structure is installed in the rear heat insulation bushing, which can prevent heat from being transferred from the working tube structure to the heat insulation bushing, avoid a sharp rise in shell temperature, and has the characteristics of light weight, ablation resistance, and strong erosion resistance. It can effectively maintain structural integrity when the engine is working and ensure the normal flight of the rocket. Attached Figure Description

[0021] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0022] Figure 1 A three-dimensional structural schematic diagram of an embodiment of the engine composite tube provided by this utility model;

[0023] Figure 2 A schematic diagram of the throat structure of an embodiment of the engine composite tube provided by this utility model;

[0024] Figure 3 A schematic diagram of the rear section of the engine composite tube body according to an embodiment of the present invention;

[0025] Among them, 1-front shell, 2-front insulation bushing, 3-rear insulation bushing, 4-rear shell, 5-working pipe structure, 6-pin, 7-middle throat hole, 8-edge throat hole. Detailed Implementation

[0026] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0027] Please refer to Figures 1-3 , Figure 1 A three-dimensional structural schematic diagram of an embodiment of the engine composite tube provided by this utility model; Figure 2 A schematic diagram of the throat structure of an embodiment of the engine composite tube provided by this utility model; Figure 3 A schematic diagram of the rear section of the engine composite tube according to an embodiment of the present invention.

[0028] In one specific embodiment, the engine composite pipe body includes a front section of the pipe body and a rear section of the pipe body whose front end is connected to the rear end of the front section of the pipe body. The front section of the pipe body includes a front section housing 1 and a front section heat insulation bushing 2 disposed inside the front section housing 1. The rear section of the pipe body includes a rear section housing 4, a rear section heat insulation bushing 3 disposed inside the rear section housing 4, and a working pipe structure 5 disposed inside the rear section heat insulation bushing 3.

[0029] By adopting a connection between the front section and the rear section of the tube, the front section of the tube includes the front shell 1 and the front heat insulation bushing 2, and the rear section of the tube includes the rear shell 4 and the rear heat insulation bushing 3. The working tube structure 5 is installed in the rear heat insulation bushing 3, which can prevent heat from being transferred from the working tube structure 5 to the heat insulation bushing, thus avoiding a sharp rise in shell temperature. It has the characteristics of being lightweight, resistant to ablation, and highly resistant to erosion. It can effectively maintain structural integrity when the engine is working, ensuring the normal flight of the rocket.

[0030] In this application, the working tube structure 5 is located inside the rear heat insulation bushing 3. The connection relationship between the two is not limited. The working tube structure 5 is connected to the rear heat insulation bushing 3 and the rear housing 4 by multiple pins 6, or the working tube structure 5 is connected to the rear heat insulation bushing 3 and the rear housing 4 by multiple bolts, or other connection methods are used.

[0031] In this application, the front housing 1 and the rear housing 4 are connected. The connection method and relative position relationship between the two are not limited. In order to reduce heat loss and damage to the outer shell, the rear end of the front housing 1 is located inside the rear housing 4, and the front heat insulation bushing 2 and the rear heat insulation bushing 3 overlap everywhere inside the rear housing 4.

[0032] In this application, the size and shape of the overlapping portion of the front heat insulation bushing 2 and the rear heat insulation bushing 3 are not limited. The two can be connected or simply overlap and intersect.

[0033] In this application, the front section and the rear section of the pipe body are connected at an adjacent point. There are no restrictions on the overlapping part of the two and the connection method. The front section and the rear section of the pipe body are connected by bolts or flanges, or other connection methods are used.

[0034] The bolted connection can be achieved by longitudinally connecting the front and rear sections of the pipe with bolts, or by setting threads on the side walls of both sections and using the sections themselves as bolts for connection.

[0035] This application does not limit the material or size of the front shell 1 and the rear shell 4. The front shell 1 and the rear shell 4 are made of 18Ni high alloy ultra-high strength steel, 20Ni high alloy ultra-high strength steel or 25N high alloy ultra-high strength steel, or shells made of other materials.

[0036] The tube shell is made of high-strength alloy steel to ensure structural strength and guarantee the structural integrity and reliability of the rocket engine during operation.

[0037] In this application, a bushing is used to insulate the shell, which improves the reliability of the shell's operation. There are no limitations on the material, thickness, or connection method of the bushing. The front heat insulation bushing 2 and the rear heat insulation bushing 3 are phenolic glass fiber plastic heat insulation bushings, ceramic fiber heat insulation bushings, or bushings of other materials.

[0038] The bushing is made of heat-insulating materials such as phenolic glass fiber plastic, which serves to prevent heat from being transferred from the working tube structure 5 to the shell and causing a sharp rise in the shell temperature.

[0039] This application does not limit the material of the working tube structure 5. The working tube structure 5 may be a graphite working tube structure 5, a ceramic working tube structure 5, or a working tube structure 5 made of other materials.

[0040] The working tube structure 5 is made of graphite material. Graphite has the functions of high temperature resistance and erosion resistance, which can effectively ensure the integrity of its structure when the engine is working, thereby ensuring the normal operation of the engine.

[0041] Since the structural dimensions of the working pipe structure 5 are relatively small, in order to ensure the normal operation and efficiency of the pipe body, that is, to ensure that the ratio of the pipe body outlet area to the throat area is within a certain range, the ratio of the pipe body outlet area to the throat area in the longitudinal section of the working pipe structure 5 is generally 1:2 to 3:4.

[0042] In this application, the structure of the working tube structure 5 can be set as needed to meet the launch requirements of the corresponding rocket engine.

[0043] To further improve utilization efficiency, increase the specific charge of the transmitter, and extend the range, the throat of the working tube structure 5 includes a central throat 7 and a plurality of edge throats 8 evenly distributed around the central throat 7.

[0044] By setting a central throat 7 and a plurality of edge throats 8 evenly distributed around the central throat 7, the relationship between the setting of a single throat and the size of the shell can be avoided, and multiple structures can be used to improve space utilization efficiency.

[0045] In this application, the size and positional relationship of the central throat 7 and the multiple edge throats 8 evenly distributed around the central throat 7 are not limited, nor is the size relationship between the central throat 7 and the edge throats 8.

[0046] The number of edge throats 8 is 6 to 10, or other numbers, and they are generally distributed at the vertices of a regular polygon centered on the center of the middle throat 7.

[0047] In one embodiment, the engine composite pipe body includes a front section and a rear section. The front section includes a front housing 1 and a front heat insulation bushing 2, with the front heat insulation bushing 2 disposed inside the front housing 1. The rear section includes a rear heat insulation bushing 3, a rear housing 4, a working pipe structure 5, and pins 6. The rear heat insulation bushing 3 is disposed inside the rear housing 4, and similarly, the working pipe structure 5 is disposed inside the rear heat insulation bushing 3. The rear heat insulation bushing 3, the rear housing 4, and the working pipe structure 5 are connected into a whole by four pins 6, and the front and rear sections of the pipe body are connected by threads.

[0048] The tube shell is made of high-strength alloy steel to ensure structural strength; the bushing is made of phenolic fiberglass plastic, which serves as insulation, preventing heat from being transferred from the working tube structure to the shell and causing a rapid increase in shell temperature; the working tube structure is made of graphite material, which has high temperature resistance and erosion resistance, effectively ensuring the integrity of its structure during engine operation, thereby ensuring normal engine operation. Due to the small size of the working tube structure, to ensure the normal operation and efficiency of the tube body, i.e., to ensure that the ratio of the tube body outlet area to the throat area is within a certain range, a design scheme of a central throat and eight throats evenly distributed on the circumference is adopted.

[0049] In summary, the engine composite tube provided by this utility model embodiment, by adopting a connection between a front section and a rear section, includes a front shell and a front heat insulation bushing in the front section, and a rear shell and a rear heat insulation bushing in the rear section. The working tube structure is installed inside the rear heat insulation bushing, which can prevent heat from being transferred from the working tube structure to the heat insulation bushing, thus avoiding a rapid increase in shell temperature. It has the characteristics of being lightweight, erosion-resistant, and having strong scour resistance. It can effectively maintain structural integrity during engine operation and ensure the normal flight of the rocket.

[0050] The engine composite pipe body provided by this utility model has been described in detail above. Specific examples have been used to illustrate the principle and implementation of this utility model. The descriptions of the embodiments above are only for the purpose of helping to understand the method and core idea of ​​this utility model. It should be noted that for those skilled in the art, several improvements and modifications can be made to this utility model without departing from the principle of this utility model, and these improvements and modifications also fall within the protection scope of the claims of this utility model.

Claims

1. An engine composite tube body, characterized in that, The tube includes a front section and a rear section connected to the rear end of the front section. The front section includes a front shell and a front insulation bushing disposed inside the front shell. The rear section includes a rear shell, a rear insulation bushing disposed inside the rear shell, and a working tube structure disposed inside the rear insulation bushing.

2. The engine composite tube body as described in claim 1, characterized in that, The working tube structure is connected to the rear heat insulation bushing and the rear housing by multiple pins, or the working tube structure is connected to the rear heat insulation bushing and the rear housing by multiple bolts.

3. The engine composite tube body as described in claim 1, characterized in that, The rear end of the front housing is located inside the rear housing, and the front insulation bushing and the rear insulation bushing overlap at various points inside the rear housing.

4. The engine composite tube body as described in claim 1, characterized in that, The front section and the rear section of the pipe are connected by bolts or flanges.

5. The engine composite tube body as described in claim 1, characterized in that, The front shell and the rear shell are made of 18Ni high-alloy ultra-high-strength steel, 20Ni high-alloy ultra-high-strength steel or 25N high-alloy ultra-high-strength steel.

6. The engine composite tube body as described in claim 1, characterized in that, The front insulation bushing and the rear insulation bushing are phenolic glass fiber plastic insulation bushings or ceramic fiber insulation bushings.

7. The engine composite tube body as described in claim 1, characterized in that, The working tube structure is either a graphite working tube structure or a ceramic working tube structure.

8. The engine composite tube body as described in claim 7, characterized in that, The ratio of the outlet area to the throat area in the longitudinal section of the working pipe structure is 1:2 to 3:

4.

9. The engine composite tube body as described in claim 8, characterized in that, The throat of the working tube structure includes a central throat and a plurality of edge throats evenly distributed around the central throat.

10. The engine composite tube body as described in claim 9, characterized in that, The number of edge throats is 6 to 10.

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