Thermal insulation structure and burner suitable for pressure fluctuation of solid attitude control engine
By designing an insulating structure in the solid attitude control engine, including a shell insulation layer, an artificial debonding layer and an air guide groove, the problem of interface debonding caused by pressure fluctuations is solved, a stable connection between the propellant and the shell is achieved, and the safety of the engine is improved.
Patent Information
- Application Number
- CN202210470999.0
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- Filing Date
- 2022-04-28
- Publication Date
- 2025-09-30
- Estimated Expiration
- 2042-04-28
AI Technical Summary
When a solid attitude control engine is subjected to pressure fluctuations, the interface between the end of the grain and the shell is prone to debonding, resulting in changes in stress and strain, which may cause the engine to explode.
An insulation structure was designed, including a shell insulation layer, an artificial debonding layer and an air guide groove. The artificial debonding layer was divided into two parts, and the air guide groove was connected to the gap to alleviate the stress imbalance caused by pressure fluctuations.
It effectively reduces the interface stress between the grain and the artificial debonding layer, ensures the pressure balance between the inside and outside when the pressure changes, prevents interface debonding, and improves the safety of the engine.
Smart Images
Figure CN114941584B_ABST
Abstract
Description
Technical Field
[0001] The present application relates to the technical field of gas generators, and in particular to a heat-insulating structure and a gas generator suitable for use in solid attitude control engine pressure fluctuations. Background Art
[0002] Under the conditions of solidification, cooling, ignition and internal pressure, the grain of a wall-cast solid rocket engine has stress singularity at its end, which can easily cause interface debonding between the grain end and the shell. This exposes the local grain surface around the end of the grain to high-temperature combustion gas, resulting in an increase in the combustion area, destroying the predetermined thrust and pressure change patterns, and even causing the combustion chamber to overload and explode.
[0003] To prevent excessive thermal stress, an artificial debonding structure is typically installed between the grain and the insulation layer. During the ignition of a pintle-type solid attitude control engine, a shock wave forms during the initial ignition phase, creating a pressure differential between the inside and outside of the artificial debonding layer. Furthermore, the reciprocating motion of the valve pintle causes pressure fluctuations in the combustion chamber, creating a pressure differential within the artificial debonding layer. This pressure differential can cause changes in stress and strain at the debonding site, potentially leading to debonding between the grain and the debonding layer, potentially causing an engine explosion. Summary of the Invention
[0004] The embodiments of the present application provide an insulating structure and a burner suitable for pressure fluctuations in a solid attitude control engine, so as to solve the problem in related technologies that the pressure difference will cause changes in stress and strain at the artificial debonding part, resulting in interface debonding between the grain and the artificial debonding layer, and then causing engine explosion.
[0005] In a first aspect, a heat-insulating structure suitable for use in a solid attitude control engine to withstand pressure fluctuations is provided, comprising:
[0006] a shell heat-insulating layer, the shell heat-insulating layer being used for bonding to the inner wall of the shell;
[0007] an artificial debonding layer, the artificial debonding layer comprising a first portion and a second portion distributed along the axial direction of the shell and connected to each other, the first portion being bonded to the inner wall of the shell insulation layer, and the second portion forming a first gap with the inner wall of the shell insulation layer;
[0008] Furthermore, an air guide groove is provided on the inner wall of the heat insulation layer of the shell, and the air guide groove is communicated with the first gap.
[0009] In some embodiments, the air guide groove extends axially along the housing.
[0010] In some embodiments, a projection of the air guide groove on the surface of the artificial debonding layer is located on the second portion.
[0011] In some embodiments, there are multiple air guide grooves, which are evenly distributed along the circumference of the shell insulation layer.
[0012] In some embodiments, there are 12 air guide grooves.
[0013] In some embodiments, the size of the first gap is 0-0.5 mm, and when the value is 0, the second portion contacts the inner wall of the heat-insulating layer of the shell without being bonded.
[0014] In some embodiments, the cross-section of the air guide groove is rectangular or arc-shaped.
[0015] In some embodiments, a lining layer is further provided on the inner wall of the artificial debonding layer.
[0016] In some embodiments, the artificial debonding layer has artificial debonding crack arrest points on its surface. The artificial debonding crack arrest points are arranged along the circumference of the artificial debonding layer and divide the artificial debonding layer into the first part and the second part.
[0017] In a second aspect, a burner is provided, comprising:
[0018] A housing, one end of which is an ignition cartridge mounting end;
[0019] And, the thermal insulation structure suitable for pressure fluctuation of a solid attitude control engine as described above, which is bonded to the inner wall of the shell, and the second part is located between the first part and the ignition cartridge mounting end;
[0020] Grain columns are filled in the thermal insulation structure.
[0021] The beneficial effects of the technical solution provided by this application include:
[0022] The thermal insulation structure provided in the present application provides an artificial debonding layer which is divided into two parts, one part being a first part which is completely bonded to the thermal insulation layer of the shell, and the other part being a second part which is not bonded to the thermal insulation layer of the shell to form a first gap. At the same time, an air guide groove is opened on the inner wall of the thermal insulation layer of the shell, and the air guide groove is connected to the first gap.
[0023] First, the presence of the air guide groove enables the forces on the inner and outer sides of the artificial debonding layer to quickly reach a balance, reducing the interface stress between the grain and the artificial debonding layer, and effectively preventing interface debonding.
[0024] Secondly, the valve pintle of the solid attitude control engine causes the combustion chamber pressure to fluctuate continuously during its reciprocating motion. The gas guide groove can adapt to the pressure changes in real time, so that the pressure on both sides of the artificial debonding layer is balanced, thereby ensuring the integrity of the grain interface. BRIEF DESCRIPTION OF THE DRAWINGS
[0025] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the following briefly introduces the drawings required for use in the description of the embodiments. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without any creative work.
[0026] Figure 1 Schematic diagram of the burner provided in the embodiment of the present application (loaded with powder column);
[0027] Figure 2 for Figure 1 Partial schematic diagram at point A in the middle;
[0028] Figure 3 Schematic diagram of the burner provided in the embodiment of the present application (without loading of grain);
[0029] Figure 4 for Figure 3 Middle BB view.
[0030] In the figure: 1. Shell; 10. Ignition cartridge mounting end; 2. Shell insulation layer; 20. Gas guide groove; 3. Artificial debonding layer; 30. First gap; 31. Artificial debonding crack arrest point; 4. Lining layer; 5. Grain column. DETAILED DESCRIPTION
[0031] To make the purpose, technical solutions, and advantages of the embodiments of this application more clear, the technical solutions in the embodiments of this application will be clearly and completely described below in conjunction with the drawings in the embodiments of this application. Obviously, the described embodiments are part of the embodiments of this application, not all of the embodiments. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of this application.
[0032] See also Figure 1 、 Figure 2 、 Figure 3 and Figure 4 As shown, an embodiment of the present application provides an insulation structure suitable for pressure fluctuations of a solid attitude control engine, the insulation structure comprising a shell insulation layer 2 and an artificial debonding layer 3, the shell insulation layer 2 and the inner wall of the shell 1 are all bonded together to provide insulation protection for the shell 1; the artificial debonding layer 3 is filled with a charge 5, the artificial debonding layer 3 comprises a first part and a second part distributed along the axial direction of the shell 1, the first part and the second part are connected to each other as a whole, the first part is all bonded to the inner wall of the shell insulation layer 2, the second part forms a first gap 30 with the inner wall of the shell insulation layer 2, an air guide groove 20 is provided on the inner wall of the shell insulation layer 2, and the air guide groove 20 is connected to the first gap 30.
[0033] The thermal insulation structure provided by the present application has an artificial debonding layer 3 divided into two parts: a first part that is completely bonded to the shell thermal insulation layer 2, and a second part that is not bonded to the shell thermal insulation layer 2 to form a first gap 30. At the same time, an air guide groove 20 is provided on the inner wall of the shell thermal insulation layer 2, and the air guide groove 20 is connected to the first gap 30. The advantages are:
[0034] First, the presence of the air guide groove enables the forces on the inner and outer sides of the artificial debonding layer to quickly reach a balance, reducing the interface stress between the grain and the artificial debonding layer, and effectively preventing interface debonding.
[0035] Secondly, the valve pintle of the solid attitude control engine causes the combustion chamber pressure to fluctuate continuously during its reciprocating motion. The gas guide groove can adapt to the pressure changes in real time, so that the pressure on both sides of the artificial debonding layer is balanced, thereby ensuring the integrity of the grain interface.
[0036] There are many forms of the air guide groove 20. For example, a spiral type is adopted. For example, see Figure 3 As shown, the gas guide groove 20 extends axially along the shell 1. On the one hand, it can reduce the difficulty of processing. On the other hand, it is conducive to the entry of the gas into the interface between the artificial debonding layer 3 and the shell insulation layer 2, so that the forces on both sides of the artificial debonding layer can quickly reach balance.
[0037] The projection of the air guide groove 20 on the surface of the artificial debonding layer 3 is located on the second portion.
[0038] The cross section of the air guide groove 20 can have various forms, for example, Figure 4 The one shown is a rectangle with chamfered corners, or an arc.
[0039] There are multiple air guide grooves 20 , and they are evenly distributed along the circumference of the shell insulation layer 2 . For example, there are 12 air guide grooves 20 .
[0040] In some preferred embodiments, the size of first gap 30 is 0 to 0.5 mm. When the gap is 0, the second portion contacts the inner wall of the shell insulation layer 2 without being adhered. The gap between the second portion and the shell insulation layer 2 is small, forming a stagnation zone. After the high-temperature gas is injected, the temperature does not rise too high, effectively protecting the shell wall.
[0041] See also Figure 2 As shown, a lining layer 4 is further provided on the inner wall of the artificial debonding layer 3 so that the drug column 5 and the artificial debonding layer 3 are firmly bonded.
[0042] See also Figure 1 As shown, the surface of the artificial debonding layer 3 has artificial debonding crack arrest points 31 , which are arranged circumferentially along the artificial debonding layer 3 and divide the artificial debonding layer 3 into a first part and a second part.
[0043] See also Figure 1 、 2 and Figure 3 As shown, an embodiment of the present application also provides a burner, which includes a shell 1, an insulating structure provided by any of the above embodiments, and a charge 5. One end of the shell 1 is an ignition cartridge mounting end 10, the insulating structure is bonded to the inner wall of the shell 1, and the second part is located between the first part and the ignition cartridge mounting end 10, and the charge 5 is filled in the insulating structure.
[0044] In summary, the thermal insulation structure provided in the present application improves the stress state of the end face of the grain under the transient pressure of the solid attitude control engine ignition startup, thereby alleviating the stress caused by the pressure shock and avoiding sudden deformation shock that may lead to damage to the engine structure.
[0045] The interface between the artificial debonding layer and the charge is in a bonding state, and the interface with the shell insulation layer is basically in a contact state (0-0.5mm gap). The air guide grooves are evenly opened axially in the shell insulation layer to ensure that the internal and external pressures of the artificial debonding layer are balanced when the combustion chamber pressure fluctuates, reducing the stress level of the interface and thus ensuring the integrity of the charge interface.
[0046] The combination of the above features solves the problem of grain interface debonding in solid attitude control engines when the combustion chamber pressure fluctuates, ensuring that the interface stress of the attitude control engine is at a low level during the entire working process, maintaining the integrity of the interface and increasing the safety of the system.
[0047] In the description of this application, it should be noted that the terms "upper" and "lower" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on this application. Unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" 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 a mechanical connection or an electrical connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be internal communication between two elements. For those of ordinary skill in the art, the specific meanings of the above terms in this application can be understood according to the specific circumstances.
[0048] It should be noted that, in this application, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device comprising a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, an element defined by the sentence "comprising a ..." does not exclude the presence of other identical elements in the process, method, article or device comprising the element.
[0049] The foregoing is merely a list of specific embodiments of the present application, intended to enable those skilled in the art to understand or implement the present application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present application. Therefore, the present application is not limited to the embodiments shown herein, but is intended to conform to the broadest scope consistent with the principles and novel features of the present application.
Claims
1. A heat-insulating structure suitable for use in pressure fluctuations of a solid attitude control engine, characterized in that: It includes: a shell heat-insulating layer (2), the shell heat-insulating layer (2) being used for bonding to the inner wall of the shell (1); An artificial debonding layer (3), the artificial debonding layer (3) comprising a first portion and a second portion distributed along the axial direction of the shell (1) and connected to each other, the first portion being bonded to the inner wall of the shell heat insulation layer (2), the second portion forming a first gap (30) with the inner wall of the shell heat insulation layer (2), the size of the first gap (30) being 0 to 0.5 mm, and when the value is 0, the second portion contacts the inner wall of the shell heat insulation layer (2) without being bonded; Furthermore, an air guide groove (20) is provided on the inner wall of the shell heat insulation layer (2), and the air guide groove (20) extends axially along the shell (1). The air guide groove (20) connects the combustion chamber with the first gap (30), so that the gas generated in the combustion chamber enters the interface between the artificial debonding layer (3) and the shell heat insulation layer (2).
2. The thermal insulation structure for solid attitude control rocket pressure fluctuations according to claim 1, characterized in that: The projection of the air guide groove (20) on the surface of the artificial debonding layer (3) is located on the second part.
3. The thermal insulation structure for solid attitude control rocket pressure fluctuations according to claim 1, characterized in that: There are a plurality of air guide grooves (20), which are evenly distributed along the circumference of the shell insulation layer (2).
4. The thermal insulation structure for solid attitude control rocket pressure fluctuations according to claim 1, characterized in that: There are 12 air guide grooves (20).
5. The thermal insulation structure for solid attitude control rocket pressure fluctuations according to claim 1, characterized in that: The cross section of the air guide groove (20) is rectangular or arc-shaped.
6. The heat-insulating structure for solid attitude control rocket pressure fluctuations according to claim 1, characterized in that: A lining layer (4) is further provided on the inner wall of the artificial debonding layer (3).
7. The thermal insulation structure for solid attitude control rocket pressure fluctuations according to claim 1, characterized in that: The artificial debonding layer (3) has artificial debonding crack arrest points (31) on its surface. The artificial debonding crack arrest points (31) are arranged circumferentially along the artificial debonding layer (3) and divide the artificial debonding layer (3) into the first part and the second part.
8. A burner, characterized in that: It includes: A housing (1), one end of the housing (1) being an ignition cartridge mounting end (10); And, the heat-insulating structure suitable for pressure fluctuation of a solid attitude control engine according to any one of claims 1 to 7, which is bonded to the inner wall of the shell (1), and the second part is located between the first part and the ignition cartridge mounting end (10); A medicine column (5), wherein the medicine column (5) is filled in the thermal insulation structure.