Solid fuel rocket engine combustion chamber rear sealing head and combustion chamber shell

Abstract

The invention discloses a solid fuel rocket engine combustion chamber rear sealing head and a combustion chamber shell, and relates to the technical field of solid fuel rocket engines. A multi-stage pressure slow-release assembly is arranged in the metal rear sealing head and comprises a first slow-release plate, a first through hole and a second slow-release plate, and one side of the first slow-release plate is connected with a first supporting ring through multiple sets of first springs distributed annularly. And the instantaneous pressure generated when solid fuel in the combustion chamber shell is ignited can be slowly released, the pressure borne by the metal rear sealing head is effectively relieved, and safety is improved. Dangerous conditions such as breakage, deformation and even explosion of the end socket caused by direct impact of instant pressure are avoided, and reliable guarantee is provided for personnel and equipment. And the structural stability is enhanced. The pressure is uniformly dispersed, the local concentrated stress of the metal rear sealing head is reduced, the structural integrity is kept, and the sealing and supporting effects are stably exerted.

Description

Technical Field

[0001] The invention relates to the technical field of solid fuel rocket engines, and in particular to a solid fuel rocket engine combustion chamber rear head and a combustion chamber casing. Background Art

[0002] The combustion chamber of a solid fuel rocket engine is one of the core components of a rocket. Its main function is to contain solid fuel and generate high-temperature and high-pressure combustion gas after ignition to propel the rocket forward. After the solid fuel is ignited, huge pressure will be generated instantly, and this part of the pressure will directly act on the rear head.

[0003] As an important component of the combustion chamber, the rear head plays a key role in closing the combustion chamber, bearing the combustion pressure, and providing structural support. However, the current solid fuel rocket engine combustion chamber has obvious shortcomings. First, due to the lack of a good buffering method, the rear head is prone to deformation under the impact of instantaneous pressure. This will not only affect the sealing of the combustion chamber, causing gas leakage and reducing the efficiency of the engine, but may also cause serious safety accidents. Secondly, a deformed or even damaged rear head may affect the flight trajectory and stability of the rocket, posing a great threat to the success of the mission.

[0004] In addition, the direct effect of instantaneous pressure on the rear head may also cause the connection of the rear head to loosen, further increasing the risk of gas leakage. In order to solve these problems, we propose a solid fuel rocket engine combustion chamber rear head and combustion chamber shell. Summary of the invention

[0005] 1. Technical issues to be solved

[0006] In view of the shortcomings of the prior art, the present invention provides a solid fuel rocket engine combustion chamber rear head and combustion chamber shell. By designing a multi-stage slow release component, the instantaneous pressure can be released in multiple stages, effectively reducing the pressure on the metal rear head and preventing the metal rear head from being deformed or damaged.

[0007] (II) Technical solution

[0008] To achieve the above-mentioned purpose, the present invention provides the following technical solutions: a solid fuel rocket engine combustion chamber rear head, including a metal rear head; a multi-stage pressure relief assembly is arranged in the metal rear head, and the multi-stage pressure relief assembly includes a first relief plate, a through hole 1 and a second relief plate, one side of the first relief plate is connected to a first support ring through multiple groups of first springs distributed in an annular manner, and one side of the second relief plate is connected to a second support ring through multiple groups of second springs distributed in an annular manner. The plate surfaces of the first relief plate and the second relief plate are respectively provided with multiple groups of through holes 1 and multiple groups of through holes 2, and the through holes 1 and 2 are staggered and asymmetrically arranged.

[0009] Preferably, a group of auxiliary slow-release components are respectively provided in the first spring and the second spring, and the auxiliary slow-release components include a piston cylinder, a pressure rod and a spring connecting plate. A liquid chamber is provided in the piston cylinder, and a first piston is installed in the liquid chamber. A partition with an oil hole in the middle is installed at the rear end of the liquid chamber, and an oil storage chamber is provided behind the partition. The oil storage chamber is connected to the liquid chamber through the oil hole, and the liquid chamber is filled with hydraulic oil. A second piston is installed in the oil storage chamber, and the second piston is connected to the piston cylinder through an auxiliary spring. The pressure rod penetrates into the piston cylinder and is connected to the first piston, and the front end of the pressure rod is respectively connected to the first spring and the second spring through a spring connecting plate. The rear ends of the first spring, the second spring and the piston cylinder are respectively connected to the first support ring and the second support ring behind them.

[0010] Preferably, the through hole 1 and the through hole 2 are both hexagonal structures.

[0011] Preferably, the diameter length of the first slow-release plate is greater than the diameter length of the second slow-release plate, and the diameter length of the first support ring is greater than the diameter length of the second support ring. Both the first support ring and the second support ring are fixed to the inner wall of the metal rear head.

[0012] Preferably, a plurality of gas pipelines communicating with the interior of the metal rear head are installed at the rear end thereof.

[0013] Preferably, a carbon fiber layer is installed in the middle of the rear end of the metal rear head.

[0014] A solid fuel rocket engine combustion chamber casing comprises a burner casing, wherein the burner casing comprises a barrel, a front head top cover and a front skirt. The rear side of the barrel is provided with a front head top cover, and the front end of the barrel is provided with a front skirt.

[0015] Preferably, the front skirt is connected to the metal rear head via a clamping ring.

[0016] Preferably, the inner wall of the barrel is provided with an insulation layer made of EPDM material, and the inner wall of the insulation layer is provided with an anti-ablation coating made of silicon carbide material.

[0017] Preferably, the barrel and the front skirt are made of carbon fiber composite materials, and the front head cover is made of aluminum alloy.

[0018] (III) Beneficial effects

[0019] Compared with the prior art, the present invention provides a solid fuel rocket engine combustion chamber rear head and combustion chamber casing, which has the following beneficial effects:

[0020] 1. By setting up a multi-stage pressure relief component, the instantaneous pressure when the solid fuel inside the combustion chamber shell is ignited can be relieved, effectively reducing the pressure on the metal rear head and improving safety. Avoid the instantaneous pressure directly impacting the rear head, causing rupture, deformation, and even explosion, and other dangerous situations, providing reliable protection for personnel and equipment. And enhance structural stability. Evenly disperse the pressure, reduce the local concentrated stress of the metal rear head, maintain structural integrity, and ensure that its sealing and supporting functions are stable.

[0021] 2. By setting up an auxiliary release component, the pressure during spring compression can be released, thereby further releasing the instantaneous pressure. As part of the pressure release, the stable performance of the spring is crucial to the entire system. The release of the spring compression pressure can ensure that the spring will not be excessively deformed or damaged due to the instantaneous high pressure during operation, thereby ensuring the reliability of the entire pressure release system.

[0022] 3. By setting up the insulation layer and anti-ablation coating in the combustion chamber shell, the EPDM insulation layer itself has good thermal insulation performance, which can effectively block the high-temperature gas in the combustion chamber from transferring heat to the combustion chamber shell, reduce the temperature of the shell, and protect the shell structure from high temperature damage. The anti-ablation coating further enhances the thermal protection capability. The anti-ablation coating can withstand extremely high temperatures and prevent the insulation layer from being directly ablated. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 It is a schematic diagram of the overall structure of the present invention;

[0024] Figure 2 It is a structural schematic diagram of another perspective of the present invention;

[0025] Figure 3 It is a schematic diagram of the cross-section structure of the present invention;

[0026] Figure 4 It is a schematic structural diagram of the metal rear end cover in the present invention;

[0027] Figure 5 for Figure 3 A schematic diagram of the enlarged structure of part A;

[0028] Figure 6 for Figure 3 A schematic diagram of the enlarged structure of part B;

[0029] Figure 7 It is a schematic structural diagram of a cross-section of the auxiliary sustained-release component in the present invention;

[0030] Figure 8 It is a structural schematic diagram of the cross section of the combustion chamber shell in the present invention.

[0031] In the figure: 1, combustion chamber shell; 11, barrel; 12, front head cover; 13, front skirt; 14, insulation layer; 15, anti-ablation coating;

[0032] 2. Metal rear end cap; 3. Gas pipeline; 6. Carbon fiber layer;

[0033] 4. Multi-stage pressure release assembly; 41. First release plate; 42. First spring; 43. First support ring; 44. Second support ring; 45. Second release plate; 46. Second spring; 47. Second through hole; 48. First through hole;

[0034] 5. Auxiliary slow-release assembly; 51. Piston cylinder; 52. Liquid chamber; 53. First piston; 54. Pressure rod; 55. Spring connecting plate; 56. Partition plate; 57. Oil hole; 58. Oil storage chamber; 59. Second piston; 510. Auxiliary spring. DETAILED DESCRIPTION

[0035] In the present invention, unless otherwise specified, the directions used, such as "up" and "down", usually refer to the directions shown in the drawings, or to the vertical, perpendicular or gravity directions; similarly, for ease of understanding and description, "left" and "right" usually refer to the left and right shown in the drawings; "inside" and "outside" refer to the inside and outside relative to the outline of each component itself, but the above-mentioned directions are not used to limit the present invention.

[0036] See also Figure 1-8 The present invention provides a technical solution for a solid fuel rocket engine combustion chamber rear head and combustion chamber shell:

[0037] Embodiment 1, a solid fuel rocket engine combustion chamber rear head, including a metal rear head 2. A multi-stage pressure relief assembly 4 is provided in the metal rear head 2, and the multi-stage pressure relief assembly 4 includes a first relief plate 41, a through hole 1 48 and a second relief plate 45. One side of the first relief plate 41 is connected to a first support ring 43 through multiple groups of first springs 42 distributed in an annular shape, and one side of the second relief plate 45 is connected to a second support ring 44 through multiple groups of second springs 46 distributed in an annular shape. The plate surfaces of the first relief plate 41 and the second relief plate 45 are respectively provided with multiple groups of through holes 1 48 and multiple groups of through holes 2 47, and the through holes 1 48 and the through holes 2 47 are staggered and asymmetrically arranged. The through holes 2 47 help to disperse the pressure and avoid the pressure from being concentrated in a single position, thereby reducing the pressure on the metal rear head 2.

[0038] The first through hole 48 and the second through hole 47 are both hexagonal structures.

[0039] The diameter length of the first slow-release plate 41 is greater than the diameter length of the second slow-release plate 45, and the diameter length of the first support ring 43 is greater than the diameter length of the second support ring 44. The first support ring 43 and the second support ring 44 are both fixed to the inner wall of the metal rear head 2.

[0040] A plurality of gas pipelines 3 connected to the interior of the metal rear end 2 are installed at the rear end thereof. The gas pipelines 3 can connect the combustion chamber and the nozzle, guide the high-temperature and high-pressure gas to flow smoothly from the combustion chamber to the nozzle, and finally eject it at high speed, thereby generating thrust.

[0041] A carbon fiber layer 6 is installed in the middle of the rear end of the metal rear head 2. The carbon fiber layer 6 has extremely high strength and rigidity, and its strength is several times that of steel. Installing the carbon fiber layer 6 in the middle of the rear end of the metal rear head 2 can provide additional strength support for the metal rear head 2 and enhance the bearing capacity of its overall structure.

[0042] When in use, the solid fuel inside the combustion chamber shell 1 is ignited. After the solid fuel is ignited, a chemical reaction occurs rapidly to produce high-temperature and high-pressure combustion gas. At this time, the instantaneous pressure directly acts on the first slow-release plate 41. The first slow-release plate 41 serves as the first buffer defense line. After being compressed, due to the support of the first support ring 43, the first slow-release plate 41 can stably transfer the pressure to the multiple groups of first springs 42. The first spring 42 begins to compress after being compressed, and absorbs and buffers part of the pressure through the elastic deformation of the spring.

[0043] At the same time, the gas generated by the pressure can be conducted to the second release plate 45 through multiple groups of through holes 1 48. The staggered asymmetric arrangement of through holes 1 48 and through holes 2 47 plays a key role here. This arrangement makes the flow path of the gas complicated and irregular when it passes through through hole 1 48. On the one hand, this increases the resistance to gas flow, thereby slowing down the speed of pressure transmission; on the other hand, the asymmetric arrangement prevents the pressure from acting directly and evenly on the second release plate 45 during the conduction process, but applies pressure in a more dispersed and complex manner. Through hole 2 47 helps to disperse the pressure, avoid the pressure from being concentrated in a single location, and reduce the pressure on the metal rear head 2.

[0044] When the pressure is transmitted to the second slow-release plate 45, the second slow-release plate 45, after being compressed, also pushes the second spring 46 to compress under the support of the second support ring 44. The second spring 46 further absorbs and buffers the pressure, and works together with the first spring 42 to achieve multi-stage slow release of the instantaneous pressure generated after the solid fuel is ignited.

[0045] The multi-stage slow-release method effectively reduces the pressure on the metal rear head 2. During the operation of the solid fuel rocket engine, if the huge pressure generated instantly acts directly on the metal rear head 2, it may cause serious consequences such as deformation, rupture, or even explosion of the metal rear head 2. The existence of the multi-stage slow-release assembly 4 greatly reduces this risk and provides higher safety guarantee for the launch and operation of the rocket.

[0046] In the second embodiment, a group of auxiliary slow-release components 5 are respectively arranged in the first spring 42 and the second spring 46, and the auxiliary slow-release components 5 include a piston cylinder 51, a pressure rod 54 and a spring connecting plate 55. A liquid chamber 52 is arranged in the piston cylinder 51, and a first piston 53 is installed in the liquid chamber 52. A partition 56 with an oil hole 57 in the middle is installed at the rear end of the liquid chamber 52. An oil storage chamber 58 is arranged behind the partition 56. The oil storage chamber 58 is connected to the liquid chamber 52 through the oil hole 57, and the liquid chamber 52 is filled with hydraulic oil. A second piston 59 is installed in the oil storage chamber 58, and the second piston 59 is connected to the piston cylinder 51 through an auxiliary spring 510. The pressure rod 54 penetrates into the piston cylinder 51 and is connected to the first piston 53. The front end of the pressure rod 54 is respectively connected to the first spring 42 and the second spring 46 through the spring connecting plate 55. The rear ends of the first spring 42, the second spring 46 and the piston cylinder 51 are respectively connected to the first support ring 43 and the second support ring 44 behind them.

[0047] In specific use, when the first spring 42 and the second spring 46 are compressed, first, the compression force of the spring is transmitted to the pressure rod 54 through the spring connecting plate 55. The pressure rod 54 is connected to the first piston 53. Under the push of the spring connecting plate 55, the pressure rod 54 drives the first piston 53 to move backward in the piston cylinder 51. As the first piston 53 moves backward, it starts to push the hydraulic oil inside the liquid chamber 52. Due to the incompressibility of the liquid, the hydraulic oil seeks a way out under the pressure and enters the oil storage chamber 58 through the oil hole 57.

[0048] After the hydraulic oil enters the oil storage chamber 58, it generates pressure on the second piston 59 in the oil storage chamber 58. The second piston 59 moves backward under the push of the hydraulic oil, thereby compressing the auxiliary spring 510 inside the piston cylinder 51. The auxiliary spring 510 gradually stores energy in this process, and assists in slowly releasing the pressure after the first spring 42 and the second spring 46 are compressed.

[0049] The function of this auxiliary slow-release mechanism is that when instantaneous high pressure acts on the spring, a part of the pressure is converted into elastic potential energy of the auxiliary spring 510 through the hydraulic system and stored, thereby preventing the first spring 42 and the second spring 46 from being excessively deformed or damaged due to the instantaneous high pressure.

[0050] When the pressure ends, the auxiliary spring 510 starts to rebound. The rebound force of the auxiliary spring 510 acts on the hydraulic oil in the oil storage chamber 58 through the second piston 59, pushing the hydraulic oil through the oil hole 57 to enter the liquid chamber 52 again. At the same time, the reverse flow of the hydraulic oil pushes the first piston 53 to move forward. The first piston 53 pushes the spring connecting plate 55 forward through the pressure rod 54 to achieve the reset of the system.

[0051] When the first spring 42 and the second spring 46 rebound, their resilience can also drive the pressure rod 54 to return to its original position through the spring connecting plate 55. At this time, the whole system returns to the initial state.

[0052] The first spring 42 and the second spring 46 are easily affected by the instantaneous high pressure during operation and may be excessively deformed or damaged. The existence of the auxiliary slow-release assembly 5 enables a portion of the pressure to be transferred to the hydraulic system and the auxiliary spring 510 when the spring is under pressure, thereby reducing the burden on the spring, extending the service life of the spring, and improving the reliability of the entire system.

[0053] Embodiment three, a solid fuel rocket engine combustion chamber casing, comprises a burner casing 1, the burner casing 1 comprises a barrel 11, a front head top cover 12 and a front skirt 13, the barrel 11 is provided with a front head top cover 12 at the rear side, and a front skirt 13 is installed at the front end thereof.

[0054] The front skirt 13 is connected to the metal rear head 2 through a clamping ring. Structures matching the clamping ring are processed at the connecting end of the front skirt 13 and the connecting end of the metal rear head 2. An annular protrusion is set at the connecting end of the front skirt, and the connecting end of the metal rear head 2 also has a corresponding structure. Then, the clamping ring is placed between the two connecting ends, and the clamping ring is elastically deformed by external force and clamped into the connecting part of the front skirt 13 and the metal rear head 2. After deformation, the inner diameter of the clamping ring tightly clamps the two connecting ends, thereby realizing a firm connection between the front skirt 13 and the metal rear head 2.

[0055] This connection method has the advantages of easy installation, high connection strength, and good sealing, and can meet the various requirements of the solid fuel rocket engine combustion chamber during operation.

[0056] The inner wall of the barrel 11 is provided with an insulation layer 14 made of EPDM material, and the inner wall of the insulation layer 14 is provided with an anti-ablation coating 15 made of silicon carbide material.

[0057] The barrel 11 and the front skirt 13 are made of carbon fiber composite materials, and the front head cover 12 is made of aluminum alloy.

[0058] During specific use, when the solid fuel burns inside the combustion chamber shell 1, the anti-ablation coating 15 made of silicon carbide directly faces the high-temperature gas and flame in the combustion chamber, further blocking the heat from being transferred to the insulation layer 14 and the barrel 11, while resisting the ablation effect of the high-temperature gas, preventing the insulation layer 14 from being directly ablated, and extending the service life of the entire burner shell. At the same time, the insulation layer 14 made of EPDM mainly plays the role of isolating the high temperature in the combustion chamber. When the solid fuel burns, it will generate extremely high temperatures. The insulation layer 14 can prevent most of the heat from being transferred to the barrel 11, protect the barrel 11 material from being damaged by high temperature, and maintain the structural stability of the combustion chamber shell 1.

[0059] The above are only specific embodiments of the present invention, but the technical features of the present invention are not limited thereto. Any simple changes, equivalent replacements or modifications made based on the present invention to solve basically the same technical problems and achieve basically the same technical effects are all included in the protection scope of the present invention.

Claims

1. A solid fuel rocket engine combustion chamber rear head, characterized in that: It includes a metal rear head (2); A multi-stage pressure relief assembly (4) is provided in the metal rear end cover (2), and the multi-stage pressure relief assembly (4) comprises a first relief plate (41), a through hole (48), and a second relief plate (45); one side of the first relief plate (41) is connected to a first support ring (43) via a plurality of groups of first springs (42) distributed in an annular shape, and one side of the second relief plate (45) is connected to a second support ring (44) via a plurality of groups of second springs (46) distributed in an annular shape; The plate surfaces of the first slow-release plate (41) and the second slow-release plate (45) are respectively provided with a plurality of first through holes (48) and a plurality of second through holes (47), and the first through holes (48) and the second through holes (47) are arranged in an alternating and asymmetrical manner.

2. The solid fuel rocket engine combustion chamber rear head according to claim 1, characterized in that: A group of auxiliary slow-release components (5) are respectively arranged in the first spring (42) and the second spring (46), and the auxiliary slow-release components (5) include a piston cylinder (51), a pressure rod (54) and a spring connecting plate (55); The piston cylinder (51) is provided with a liquid chamber (52), a first piston (53) is installed in the liquid chamber (52), a partition (56) with an oil hole (57) in the middle is installed at the rear end of the liquid chamber (52), an oil storage chamber (58) is provided behind the partition (56), the oil storage chamber (58) is connected to the liquid chamber (52) through the oil hole (57), and the liquid chamber (52) is filled with hydraulic oil; A second piston (59) is installed in the oil storage chamber (58), and the second piston (59) is connected to the piston cylinder (51) via an auxiliary spring (510); The pressure rod (54) penetrates into the piston cylinder (51) and is connected to the first piston (53); the front end of the pressure rod (54) is respectively connected to the first spring (42) and the second spring (46) through a spring connecting plate (55); The rear ends of the first spring (42), the second spring (46) and the piston cylinder (51) are respectively connected to the first support ring (43) and the second support ring (44) behind them.

3. The solid fuel rocket engine combustion chamber rear head according to claim 1, characterized in that: The through hole 1 (48) and the through hole 2 (47) are both hexagonal structures.

4. The solid fuel rocket engine combustion chamber rear head according to claim 1, characterized in that: The diameter length of the first slow-release plate (41) is greater than the diameter length of the second slow-release plate (45), and the diameter length of the first support ring (43) is greater than the diameter length of the second support ring (44); The first support ring (43) and the second support ring (44) are both fixed to the inner wall of the metal rear head (2).

5. The solid fuel rocket engine combustion chamber rear head according to claim 1, characterized in that: The rear end of the metal rear end cap (2) is provided with a plurality of groups of gas pipelines (3) in communication with the interior thereof.

6. The solid fuel rocket engine combustion chamber rear head according to claim 1, characterized in that: A carbon fiber layer (6) is installed in the middle of the rear end of the metal rear end cover (2).

7. A solid fuel rocket engine combustion chamber casing, comprising the metal rear head according to any one of claims 1 to 6, characterized in that: The burner shell (1) comprises a barrel (11), a front head cover (12) and a front skirt (13); the rear side of the barrel (11) is provided with a front head cover (12), and the front end of the barrel (11) is provided with a front skirt (13).

8. A solid fuel rocket engine combustion chamber casing according to claim 7, characterized in that: The front skirt (13) is connected to the metal rear head (2) via a clamping ring.

9. A solid fuel rocket engine combustion chamber casing according to claim 7, characterized in that: The inner wall of the barrel (11) is provided with an insulation layer (14) made of EPDM material, and the inner wall of the insulation layer (14) is provided with an anti-ablation coating (15) made of silicon carbide material.

10. A solid fuel rocket engine combustion chamber casing according to claim 7, characterized in that: The barrel (11) and the front skirt (13) are made of carbon fiber composite material, and the front head cover (12) is made of aluminum alloy.

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