Thrust regulating device for variable thrust solid rocket engine with integrated drive and cooling

Abstract

The invention discloses a thrust regulating device for a variable thrust solid rocket engine with drive cooling integration, comprising a throat plug assembly, a high-pressure cold air source and a cold air channel; the throat plug assembly is arranged at the convergence section of the nozzle, the throat plug assembly comprises a base and a throat plug, a throat plug driving cavity is arranged in the base, the first end of the throat plug is slidably connected in the throat plug driving cavity, the second end of the throat plug is located at the throat of the nozzle, and a tension piece is connected between the throat plug and the base; the high-pressure cold air source is arranged outside the nozzle, one end of the cold air channel is connected to the throat plug driving cavity, and the other end is connected to the high-pressure cold air source after passing through the wall of the nozzle; an air film hole is arranged on the throat plug, one end of the air film hole is connected to the throat plug driving cavity, and the other end is connected to the nozzle. The invention is applied to the field of rocket engines, and can realize the driving movement of the throat plug on the basis of avoiding adverse effects on the engine charge and performance, and effectively reduce the high-temperature ablation of the throat plug by the combustion chamber gas during the working process.

Description

Technical Field

[0001] The invention relates to the technical field of rocket engines, in particular to a thrust regulating device for a variable thrust solid rocket engine with integrated driving and cooling. Background Art

[0002] The throat plug type variable thrust solid rocket engine can realize active, real-time and wide range of thrust infinite adjustment, which is an important research direction of solid rocket engine thrust regulation. Its working principle is to change the cross-sectional area of ​​the nozzle throat by driving the throat plug to move, thereby realizing thrust regulation. As a key component of solid engine thrust regulation, the throat plug usually suffers from ablation under the action of high temperature and high pressure gas, which will directly affect the engine performance and even cause engine failure. Therefore, anti-ablation research is necessary for engine design and ensuring the normal operation of the engine.

[0003] At present, the main strategies for anti-ablation of the throat plug of variable thrust solid rocket engines are: (1) using material properties to resist ablation, that is, using high melting point alloys as throat plug materials or using low combustion temperature propellants. This method uses the characteristics of the material itself to make the throat plug melting point higher than the gas temperature, which will result in higher development costs or lower performance of variable thrust solid rocket engines. (2) Using structural design to resist ablation, that is, using special structural design to reduce the surface temperature of the throat plug. This method achieves better anti-ablation effects on the basis that the engine development cost and internal ballistic performance are not affected by material properties. However, the coaxial drive method it adopts will affect the variable thrust solid rocket engine charge, thereby having an adverse effect on engine performance. Summary of the invention

[0004] In view of the deficiencies in the above-mentioned prior art, the present invention provides a thrust regulating device for a variable thrust solid rocket engine with integrated drive and cooling. Through structural design, it can realize the movement of the driving throat plug while avoiding adverse effects on the engine charge and performance, while effectively reducing the high-temperature ablation of the throat plug by the combustion chamber gas during operation.

[0005] To achieve the above-mentioned object, the present invention provides a thrust regulating device for a variable thrust solid rocket engine with integrated driving and cooling, comprising a coaxially connected combustion chamber and nozzle, as well as a throat plug assembly, a high-pressure cold air source, and a cold air channel;

[0006] The throat plug assembly is arranged at the convergent section of the nozzle, and the throat plug assembly comprises a base and a throat plug, a throat plug driving cavity is arranged in the base, a first end of the throat plug is slidably connected in the throat plug driving cavity, a second end of the throat plug is located at the throat of the nozzle, and a tension piece is connected between the throat plug and the base;

[0007] The high-pressure cold air source is arranged outside the nozzle, one end of the cold air channel is connected to the throat plug driving chamber, and the other end passes through the wall of the nozzle and is connected to the high-pressure cold air source;

[0008] An air film hole is provided on the throat plug, one end of the air film hole is connected to the throat plug driving cavity, and the other end is connected to the nozzle, so that the high-pressure cold air used to drive the displacement of the throat plug is discharged through the air film hole to form an air film on the surface of the throat plug;

[0009] The base and the throat plug are both hollow cylindrical structures with one end open, and the open end of the throat plug is the first end and the closed end is the second end;

[0010] The open end of the throat plug is slidably connected to the open end of the base, that is, the base and the throat plug together form the throat plug driving cavity, and the air film hole is opened on the side wall of the second end of the throat plug.

[0011] In one embodiment, the base includes a cylinder and a first end cover;

[0012] The cylinder is a hollow cylindrical structure with two ends open, the first end cover is threadedly connected to the first end of the cylinder, and the open end of the throat plug is slidably connected to the inside of the second end of the cylinder;

[0013] The tension member is connected between the first end cover and the inner wall of the second end of the throat plug.

[0014] In one embodiment, the second end of the barrel is provided with a first protrusion extending inwardly, and the open end of the throat plug is provided with a second protrusion extending outwardly;

[0015] During the displacement of the laryngeal plug, the first protrusion is located on the displacement path of the second protrusion.

[0016] In one embodiment, the number of the air film holes is multiple, and the air film holes are arranged in multiple rows along the axial direction of the throat plug at intervals on the side wall of the second end of the throat plug;

[0017] The air film holes in each row are evenly spaced along the circumference of the throat plug, and the air film holes in two adjacent rows are staggered with each other.

[0018] In one embodiment, the cold air channel includes a channel body, a second end cover and a ventilation pipeline;

[0019] The first end of the channel body is welded and fixed to the base to communicate with the throat plug driving chamber, the middle part of the channel body is welded and fixed to the wall of the nozzle, and the second end cover is connected to the second end of the channel body;

[0020] One end of the ventilation pipeline passes through the second end cover and is communicated with the channel body, and the other end is connected to the high-pressure cold air source.

[0021] In one of the embodiments, a pressure-stabilizing valve is provided on the ventilation pipeline.

[0022] In one embodiment, the tension member is a spring.

[0023] Compared with the prior art, the present invention has the following beneficial technical effects:

[0024] 1. When the thrust regulating device of the present invention is working, the high-pressure cold air source provides high-pressure and low-temperature cold air. While driving the throat plug to move, the high-pressure and low-temperature cold air is ejected through the air film hole to form an air film between the mainstream gas and the surface of the throat plug, thereby reducing the direct contact between the mainstream gas and the throat plug, thereby reducing the degree of ablation of the throat plug and increasing the service life of the throat plug;

[0025] 2. All parts of the thrust regulating device in the present invention are protected by low-temperature cold air, which reduces the temperature of the throat plug, improves the anti-ablation ability, and increases the working life of the thrust regulating device;

[0026] 3. The thrust regulating device of the present invention uses a high-pressure cold air source to provide high-pressure and low-temperature cold air to drive the throat plug forward, and the tension member drives the throat plug backward, thus realizing a drive-cooling integrated design. Compared with the coaxial mechanical drive method, the overall mass of the engine is reduced, and the mass of the engine charge is improved;

[0027] 4. The thrust regulating device of the present invention integrates the drive cooling into an integrated design, and does not need to set up a complex servo mechanism to regulate the pressure of the throat plug drive chamber, thereby simplifying the system structure and further reducing the overall mass of the engine;

[0028] 5. When the thrust regulating device of the present invention is working, the high-pressure and low-temperature cold air can also converge with the mainstream combustion gas after the air film is formed, thereby effectively realizing the improvement of the total impulse of the engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the structures shown in these drawings without paying creative work.

[0030] Figure 1 It is a structural schematic diagram of a variable thrust solid rocket engine equipped with a thrust regulating device in an embodiment of the present invention;

[0031] Figure 2It is a partial schematic diagram of the thrust adjustment device in an embodiment of the present invention;

[0032] Figure 3 It is a partial schematic diagram of the laryngeal plug in an embodiment of the present invention.

[0033] Figure numbers: high-pressure cold air source 1, cold air channel 2, channel body 201, second end cover 202, ventilation pipeline 203, base 3, cylinder 301, first end cover 302, throat plug 4, air film hole 401, throat plug driving chamber 5, tension member 6, pressure stabilizing valve 7, combustion chamber 8, nozzle 9, propellant 10.

[0034] The realization of the purpose, functional features and advantages of the present invention will be further explained in conjunction with embodiments and with reference to the accompanying drawings. DETAILED DESCRIPTION

[0035] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0036] It should be noted that all directional indications (such as up, down, left, right, front, back, etc.) in the embodiments of the present invention are only used to explain the relative position relationship, movement status, etc. between the components under a certain specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indication will also change accordingly.

[0037] In addition, in the present invention, descriptions such as "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" or "second" may explicitly or implicitly include at least one of the features. In the description of the present invention, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0038] In the present invention, unless otherwise clearly specified and limited, the terms "connection", "fixation", etc. should be understood in a broad sense. For example, "fixation" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection, an electrical connection, a physical connection, or a wireless communication connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0039] In addition, the technical solutions between the various embodiments of the present invention can be combined with each other, but it must be based on the fact that ordinary technicians in the field can implement it. When the combination of technical solutions is contradictory or cannot be implemented, it should be deemed that such combination of technical solutions does not exist and is not within the scope of protection required by the present invention.

[0040] The present embodiment discloses a thrust regulating device for a variable thrust solid rocket engine with integrated drive and cooling (hereinafter referred to as the "thrust regulating device"), which includes a throat plug assembly, a high-pressure cold air source 1 and a cold air channel 2, and is mainly used to drive the throat plug 4 to move while avoiding adverse effects on the engine charge and performance, while effectively reducing high-temperature ablation of the throat plug 4 by the combustion chamber 8 gas during operation.

[0041] refer to Figure 1 , is a schematic diagram of the structure of a variable thrust solid rocket engine equipped with a thrust regulating device in this embodiment. The solid rocket engine includes a combustion chamber 8 and a nozzle 9 connected by coaxial threads and / or bolts. A propellant 10 is arranged in the thrust chamber. The propellant 10 burns in the combustion chamber 8 to generate high-temperature and high-pressure combustion gas called mainstream combustion gas.

[0042] refer to Figure 1 , Figure 2 , the throat plug assembly is mainly arranged in the convergence section of the nozzle 9. Specifically, the throat plug assembly includes a base 3 and a throat plug 4, a throat plug driving chamber 5 is arranged in the base 3, the first end of the throat plug 4 is slidably connected in the throat plug driving chamber 5, the second end of the throat plug 4 is located at the throat of the nozzle 9, and a tension piece 6 is connected between the throat plug 4 and the base 3, and the tension piece 6 is continuously subjected to tension when the throat plug 4 moves outward. The high-pressure cold air source 1 is arranged outside the nozzle 9, one end of the cold air channel 2 is connected to the throat plug driving chamber 5, and the other end is connected to the high-pressure cold air source 1 after passing through the wall of the nozzle 9, and at the same time, an air film hole 401 is arranged on the throat plug 4, one end of the air film hole 401 is connected to the throat plug driving chamber 5, and the other end is connected to the nozzle 9, so that the high-pressure cold air used to drive the displacement of the throat plug 4 is discharged through the air film hole 401 to form an air film on the surface of the throat plug 4, so as to avoid the throat plug 4 from directly contacting with the high-temperature mainstream combustion gas formed by the combustion of the propellant 10, and realize the surface cooling of the throat plug 4.

[0043] When the thrust regulating device in this embodiment is working, the high-pressure cold air source 1 provides high-pressure and low-temperature cold air. While driving the throat plug 4 to move, the high-pressure and low-temperature cold air is ejected through the air film hole 401 to form an air film between the mainstream gas and the surface of the throat plug 4, thereby reducing the direct contact between the mainstream gas and the throat plug 4, thereby reducing the degree of ablation of the throat plug 4 and improving the service life of the throat plug 4. At the same time, all parts of the thrust regulating device are protected by the low-temperature cold air, which reduces the temperature of the throat plug 4, improves the anti-ablation ability, and improves the service life of the thrust regulating device. In addition, through the integrated design of drive and cooling, not only the overall mass of the engine is reduced and the mass of the engine charge is improved compared with the coaxial mechanical drive mode, but also there is no need to set a complex servo mechanism to adjust the pressure of the throat plug drive chamber 5, which simplifies the system structure and further reduces the overall mass of the engine. After the air film is formed, the high-pressure and low-temperature cold air can also converge with the mainstream gas, thereby effectively realizing the improvement of the total impulse of the engine.

[0044] In the specific implementation process, the base 3 and the throat plug 4 are both hollow cylindrical structures with one end open, and the open end of the throat plug 4 is the first end and the closed end is the second end. The open end of the throat plug 4 is slidably connected to the open end of the base 3, that is, the base 3 and the throat plug 4 together form a throat plug drive chamber 5, and the air film hole 401 is provided on the side wall of the second end of the throat plug 4. Specifically, the base 3 includes a cylinder 301 and a first end cover 302, the cylinder 301 is a hollow cylindrical structure with two ends open, the first end cover 302 is threadedly connected to the first end of the cylinder 301, the open end of the throat plug 4 is slidably connected to the inside of the second end of the cylinder 301, and the tension member 6 is connected between the first end cover 302 and the inner wall of the second end of the throat plug 4. The tension member 6 in this embodiment is a spring, that is, spring mounting seats are respectively welded on the inner wall of the first end cover 302 and the second end of the throat plug 4 for mounting the tension member 6.

[0045] As a preferred embodiment, the second end of the cylinder 301 is provided with a first protrusion extending inwardly, and the open end of the throat plug 4 is provided with a second protrusion extending outwardly. During the displacement of the throat plug 4, the first protrusion is located on the displacement path of the second protrusion, so as to limit the sliding of the throat plug 4 and prevent the throat plug 4 from sliding off the base 3.

[0046] refer to Figure 3 There are multiple air film holes 401, and each air film hole 401 is arranged in multiple rows along the axial direction of the throat plug 4 on the side wall of the second end of the throat plug 4. The air film holes 401 in each row are evenly spaced along the circumference of the throat plug 4, and the air film holes 401 in two adjacent rows are staggered with each other to form a more uniform air film on the surface of the throat plug 4.

[0047] In this embodiment, the cold air channel 2 includes a channel body 201, a second end cover 202 and a ventilation pipeline 203. The first end of the channel body 201 is connected to the throat plug driving chamber 5 after being welded and fixed to the base 3. The middle part of the channel body 201 is welded and fixed to the wall of the nozzle 9. The second end cover 202 is connected to the second end of the channel body 201, that is, the base 3 is fixedly connected to the nozzle 9 through the channel body 201 as a support. One end of the ventilation pipeline 203 passes through the second end cover 202 and is connected to the channel body 201, and the other end is connected to the high-pressure cold air source 1, and a pressure-stabilizing valve 7 is provided on the ventilation pipeline 203.

[0048] The working process of the thrust regulating device in this embodiment is as follows:

[0049] After the high-pressure cold air provided by the high-pressure cold air source 1 is regulated by the pressure regulating valve 7, it enters the throat plug drive chamber 5 through the ventilation pipeline 203 and the channel body 201. During the working process, the pressure of the throat plug drive chamber 5 is always greater than the pressure of the combustion chamber 8, and the tension member 6 is kept under tension. Under the joint action of the pressure of the throat plug drive chamber 5, the pressure of the combustion chamber 8 and the tension of the tension member 6, the throat plug 4 can be driven to move forward and backward by adjusting the pressure of the pressure regulating valve 7. At the same time, the high-pressure and low-temperature cold air in the throat plug drive chamber 5 is discharged from the air film hole 401 at the head of the throat plug 4, and under the action of the mainstream gas in the throat of the nozzle 9, an air film is formed on the surface of the head of the throat plug 4, avoiding the contact between the mainstream high-temperature gas and the surface of the throat plug 4, and reducing the ablation of the throat plug 4. The drive cooling integrated regulation of the throat plug 4 of the variable thrust solid rocket engine is realized. In addition, the low-temperature cold air after the air film is formed converges with the mainstream gas to increase the total impulse of the variable thrust solid rocket engine.

[0050] The above description is only a preferred embodiment of the present invention, and does not limit the protection scope of the present invention. All equivalent structural changes made by using the contents of the present invention specification and drawings under the inventive concept of the present invention, or directly / indirectly applied in other related technical fields are included in the protection scope of the present invention.

Claims

1. A thrust regulating device for a variable thrust solid rocket engine with integrated drive and cooling, characterized in that: It includes a throat plug assembly, a high-pressure cold air source and a cold air channel; The throat plug assembly is arranged at the convergent section of the nozzle, and the throat plug assembly comprises a base and a throat plug, a throat plug driving chamber is arranged in the base, a first end of the throat plug is slidably connected in the throat plug driving chamber, a second end of the throat plug is located at the throat of the nozzle, and a tension piece is connected between the throat plug and the base, and the tension piece is a spring; The high-pressure cold air source is arranged outside the nozzle, one end of the cold air channel is connected to the throat plug driving chamber, and the other end passes through the wall of the nozzle and is connected to the high-pressure cold air source; An air film hole is provided on the throat plug, one end of the air film hole is connected to the throat plug driving cavity, and the other end is connected to the nozzle, so that the high-pressure cold air used to drive the displacement of the throat plug is discharged through the air film hole to form an air film on the surface of the throat plug; The base and the throat plug are both hollow cylindrical structures with one end open, and the open end of the throat plug is the first end and the closed end is the second end; The open end of the throat plug is slidably connected to the open end of the base, that is, the base and the throat plug together form the throat plug driving cavity, and the air film hole is opened on the side wall of the second end of the throat plug; The cold air channel comprises a channel body, a second end cover and a ventilation pipeline; The first end of the channel body is welded and fixed to the base to communicate with the throat plug driving chamber, the middle part of the channel body is welded and fixed to the wall of the nozzle, and the second end cover is connected to the second end of the channel body; One end of the ventilation pipeline passes through the second end cover and communicates with the channel body, and the other end is connected to the high-pressure cold air source; A pressure stabilizing valve is provided on the ventilation pipeline; The high-pressure cold air provided by the high-pressure cold air source is pressure-regulated by the pressure-stabilizing valve and then enters the throat plug driving chamber through the ventilation pipeline and the channel body. During the working process, the pressure in the throat plug driving chamber is always greater than the pressure in the combustion chamber, so that the tension piece is continuously subjected to tension. Under the combined effect of the throat plug driving chamber pressure, the combustion chamber pressure and the tension of the tension piece, the throat plug is driven to move forward and backward by adjusting the pressure of the pressure-stabilizing valve.

2. The thrust regulating device of the variable thrust solid rocket engine with integrated driving and cooling according to claim 1 is characterized in that: The base comprises a cylinder and a first end cover; The cylinder is a hollow cylindrical structure with two ends open, the first end cover is threadedly connected to the first end of the cylinder, and the open end of the throat plug is slidably connected to the inside of the second end of the cylinder; The tension member is connected between the first end cover and the inner wall of the second end of the throat plug.

3. The thrust regulating device of the variable thrust solid rocket engine with integrated driving and cooling according to claim 2 is characterized in that: The second end of the cylinder is provided with a first protrusion extending inwardly, and the open end of the throat plug is provided with a second protrusion extending outwardly; During the displacement of the laryngeal plug, the first protrusion is located on the displacement path of the second protrusion.

4. The thrust regulating device of the variable thrust solid rocket engine with integrated driving and cooling according to any one of claims 1 to 3, characterized in that: The number of the air film holes is multiple, and the air film holes are arranged in multiple rows along the axial direction of the throat plug at intervals on the side wall of the second end of the throat plug; The air film holes in each row are evenly spaced along the circumference of the throat plug, and the air film holes in two adjacent rows are staggered with each other.

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