Interlayer type pulse engine

Abstract

The utility model belongs to the technical field of solid rocket engines, and particularly relates to an interlayer type pulse engine. The interlayer type pulse engine comprises a first-stage pulse shell, a second-stage pulse shell and a third-stage pulse shell, a second-stage pulse combustion chamber is formed in the second-stage pulse shell and is spliced with the first-stage pulse shell along the axial direction; the second-stage solid grain is arranged in the second-stage pulse combustion chamber; the interlayer device is arranged at the axial opening end, facing the first-stage pulse shell, of the second-stage pulse shell and is connected to the inner circumferential wall of the second-stage pulse shell; the interlayer device can isolate the first-stage pulse combustion chamber from the second-stage pulse combustion chamber, an axial gap is formed between the interlayer device and the second-stage pulse shell in the axial direction, and the interlayer device can move towards the second-stage solid grain in the axial direction and is connected to the axial end face of the second-stage solid grain. In the utility model, the interlayer device adopts a detachable assembly scheme and has an axial movement freedom degree, so that the grain can be conveniently checked, and the interlayer device is self-adaptive to the axial deformation of the grain.

Description

Technical Field

[0001] This application belongs to the field of solid rocket engine technology, and in particular relates to a layered pulse engine. Background Technology

[0002] A solid-fuel dual-pulse engine essentially divides the combustion chamber of a solid-fuel engine into two parts using an isolation device, allowing for two separate shutdowns and restarts. Aircraft using a solid-fuel dual-pulse engine as their power source can achieve optimal control of the flight trajectory and optimal management of engine energy by rationally allocating the intervals between the two pulse thrust stages through onboard control programs, thereby meeting the requirements of different flight performance characteristics.

[0003] For dual-pulse engines with a second-stage pulse as the end-face combustion propellant, the existing approach is to install a rubber diaphragm on the initial combustion end face of the end-face combustion propellant to isolate the first-stage pulse combustion chamber from the second-stage pulse combustion chamber.

[0004] However, since the rubber separator is fixed to the end face of the propellant, it is difficult to remove the rubber separator to inspect the propellant. Moreover, the propellant will deform to a certain extent due to the influence of ambient temperature during the manufacturing and operation process, resulting in a gap between the rubber separator and the end face of the propellant. The gas in the gap is greatly affected by the ambient temperature, which greatly increases the risk of cracking of the rubber separator. In other words, the fixed rubber separator solution is not suitable for situations where there is a gap between the propellant and the rubber separator. Utility Model Content

[0005] This application provides a diaphragm-type pulse engine to solve the technical problems of existing methods that use adhesive bonding to fix the rubber diaphragm, making it difficult to inspect the propellant and to utilize the axial gap caused by propellant deformation.

[0006] According to one aspect of this application, a diaphragm-type pulse engine is provided, comprising a primary pulse housing, a secondary pulse housing, a secondary solid propellant grain, and a diaphragm device. A primary pulse combustion chamber is formed within the primary pulse housing; a secondary pulse combustion chamber is formed within the secondary pulse housing and axially connected to the primary pulse housing, with the secondary pulse combustion chamber and the primary pulse combustion chamber axially connected; the secondary solid propellant grain is disposed within the secondary pulse combustion chamber; the diaphragm device is disposed at the axially open end of the secondary pulse housing facing the primary pulse housing and is connected to the inner peripheral wall of the secondary pulse housing; wherein the diaphragm device is capable of isolating the primary pulse combustion chamber and the secondary pulse combustion chamber, and forms an axial gap with the secondary pulse housing in the axial direction, and the diaphragm device is configured to be movable axially toward the secondary solid propellant grain and connected to the axial end face of the secondary solid propellant grain.

[0007] In an optional embodiment of this application, the axial clearance includes a first axial clearance and a second axial clearance; the first axial clearance is located on the outer periphery of the second axial clearance and is closer to the primary pulse housing than the second axial clearance.

[0008] In an optional embodiment of this application, the axial spacing of the first axial clearance is smaller than the axial spacing of the second axial clearance.

[0009] In the optional embodiments of this application, a primary solid propellant column is also included, which is disposed within the primary pulse housing; the primary solid propellant column is an internal bore type propellant column, and the secondary solid propellant column is an end face type propellant column.

[0010] In an optional embodiment of this application, the partition device includes a composite partition, which includes a heat insulation layer and an inner reinforcing layer. The inner reinforcing layer is located inside the heat insulation layer and axially divides the heat insulation layer into a first heat insulation layer and a second heat insulation layer. The axial sides of the first heat insulation layer and the axial sides of the second heat insulation layer are respectively formed with a first opening and a second opening facing away from each other. The first opening receives one axial end of the secondary solid propellant column, and the second opening faces the primary pulse combustion chamber. The composite partition is provided with a weakening structure, which is configured to crack when subjected to pressure from the second opening towards the first opening, and form an opening connecting the second opening and the first opening.

[0011] In an optional embodiment of this application, the middle part of the composite partition protrudes axially toward the first open cavity and forms a deepened annular cavity located on the periphery of the first open cavity. The periphery of the first open cavity is the deepened annular cavity, and the deepened annular cavity partially overlaps with the circumferential projection of the second open cavity.

[0012] In an optional embodiment of this application, the composite partition further includes an outer reinforcing layer, which is located on at least a portion of the surface of the first thermal insulation layer at the location of the deepened annular cavity.

[0013] In an optional embodiment of this application, the weakening structure is formed between the first insulation layer and the inner reinforcing layer and includes multiple straight grooves that intersect at a single point.

[0014] In an optional embodiment of this application, the partition device further includes a fixing ring and a sealing ring; the fixing ring is connected to the outer peripheral side of the composite partition, and the sealing ring is disposed on the outer peripheral side of the fixing ring and connected to the inner peripheral wall of the secondary pulse housing; an axial gap is formed between the composite partition and the fixing ring on the same axial side and the axial opening end of the secondary pulse housing.

[0015] In an optional embodiment of this application, a nozzle is also included, which is connected to the axial side of the primary pulse housing away from the secondary pulse housing.

[0016] In summary, the sectional pulse engine provided in this application has at least the following beneficial effects:

[0017] In this diaphragm-type pulse engine, the diaphragm device is detachably assembled inside the secondary pulse housing and fitted over one axial end of the secondary solid propellant grain. Compared to existing adhesive-based fixing methods, the detachable diaphragm device allows for inspection of the secondary solid propellant grain. Furthermore, an axial clearance is formed between the diaphragm device and the secondary pulse housing, allowing for axial movement compensation of the diaphragm device.

[0018] The axial clearance here is also a type of annular clearance, surrounding the outer periphery of the secondary solid propellant grain. Additionally, during manufacturing and primary pulse operation, the secondary solid propellant grain undergoes slight deformation due to ambient temperature, resulting in a gap between the diaphragm device and the end of the secondary solid propellant grain. The pressure exerted on the diaphragm device during primary pulse operation allows it to move towards the secondary solid propellant grain, eliminating the axial gap between them.

[0019] It is evident that the partition device has a limited degree of freedom for axial sliding, which can be well adapted to situations where there is an axial gap between the partition device and the secondary solid propellant column, reducing the risk of seal failure caused by the gas in the gap being affected by ambient temperature.

[0020] Furthermore, the partition device adopts a composite structure of metal and non-metal, which plays a role in axial heat insulation and sealing in the solid dual-pulse engine, as well as having a forward opening function, thus meeting the dual requirements of structure and function.

[0021] Among them, the composite partition is made of non-metallic materials and the fixing ring is made of metallic materials. The composite partition adopts a multi-material layer structure, which improves the structural strength under the action of the reinforcing layer, ensures that the partition will not be damaged due to large deformation, and ensures heat insulation and deformation capacity. The partition device is easy to assemble, reduces the weight of the partition device, and improves the engine weight ratio. Attached Figure Description

[0022] To more clearly illustrate the technical solutions in the specific embodiments of this application or the prior art, the accompanying drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this application; those skilled in the art can obtain other drawings based on these drawings without any creative effort.

[0023] Figure 1 A cross-sectional view of a sectional pulse engine provided according to one embodiment of this application;

[0024] Figure 2 for Figure 1 A close-up view of the location of the intermediate partition device;

[0025] Figure 3a This is a schematic diagram of a partition device provided according to one embodiment of this application;

[0026] Figure 3b for Figure 3a Sectional view at point BB;

[0027] Figure 3c for Figure 3a Sectional view at EE;

[0028] Figure 4 for Figure 3b A partial sectional view of the central fixed ring.

[0029] The attached figures are labeled as follows:

[0030] 100. Layered pulse engine;

[0031] 10. First-stage pulse housing; R1. First-stage pulse combustion chamber;

[0032] 20. Secondary pulse housing; R2. Secondary pulse combustion chamber;

[0033] 30. Secondary solid propellant charge; 31. Secondary pulse ignition

[0034] 40. Partition device; 41. Composite partition; 411. Insulation layer; 4111. First insulation layer; 4112. Second insulation layer; 412. Inner reinforcing layer; 413. Weakening structure; 414. Outer reinforcing layer;

[0035] 42. Retaining ring; 43. Sealing ring; F. Sealing ring groove;

[0036] 50. First-stage solid propellant; 51. First-stage pulse ignition;

[0037] 60. Nozzle;

[0038] A1, First axial clearance; A2, Second axial clearance;

[0039] C1, First open oral cavity; C11, Deepened annular cavity; C2, Second open oral cavity;

[0040] D. Straight groove. Detailed Implementation

[0041] Furthermore, features specified with terms such as "first," "second," "primary," or "secondary" are for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Features specified with "first," "second," "primary," or "secondary" may explicitly or implicitly include at least one of the specified features. The use of the term "multiple" generally means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0042] In this application, unless otherwise explicitly specified and limited, terms such as "installation," "connection," "joining," and "fixing" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can be a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0043] In the description of this specification, the terms "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that the specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of this application. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0044] The term "axial" as used in this application may refer to the length direction of the diaphragm pulse engine 100, and "circumferential" may refer to the circumferential direction of the diaphragm pulse engine 100.

[0045] Figure 1 This is a cross-sectional view of a sectional pulse engine 100 provided according to one embodiment of this application. Figure 2 for Figure 1 A partial enlarged view of the location of the interlayer device 40. Please refer to [link / reference]. Figure 1 and Figure 2 The diaphragm-type pulse engine 100 includes a primary pulse housing 10, a secondary pulse housing 20, a secondary solid propellant 30, and a diaphragm device 40.

[0046] A primary pulse combustion chamber R1 is formed within the primary pulse housing 10. A secondary pulse combustion chamber R2 is formed within the secondary pulse housing 20 and is axially connected to the primary pulse housing 10; the secondary pulse combustion chamber R2 and the primary pulse combustion chamber R1 are axially connected. A secondary solid propellant 30 is disposed within the secondary pulse combustion chamber R2. A partition device 40 is disposed at the axially open end of the secondary pulse housing 20 facing the primary pulse housing 10 and is connected to the inner peripheral wall of the secondary pulse housing 20.

[0047] The partition device 40 can isolate the primary pulse combustion chamber R1 from the secondary pulse combustion chamber R2, and forms an axial gap with the secondary pulse housing 20 in the axial direction. The partition device 40 is configured to move axially toward the secondary solid propellant 30 and connect with the axial end face of the secondary solid propellant 30.

[0048] In this embodiment, the layered pulse engine 100 can be a dual-pulse solid engine. A first-stage pulse combustion chamber R1 is formed in the first-stage pulse housing 10 and is used to house a first-stage solid propellant 50 for generating a first-stage pulse. A second-stage pulse combustion chamber R2 is formed in the second-stage pulse housing 20 and is used to house a second-stage solid propellant 30 for generating a second-stage pulse.

[0049] The partition device 40 is located at the axial opening end of the secondary pulse housing 20 and cooperates with the inner peripheral wall of the secondary pulse housing 20 to isolate the primary pulse combustion chamber R1 from the secondary pulse combustion chamber R2, thereby preventing the ignition of the secondary solid propellant 30 during primary pulse operation. Specifically, the partition device 40 has certain sealing and heat insulation properties to prevent the high-temperature and high-pressure gas generated during primary pulse operation from entering the secondary pulse combustion chamber R2, thus preventing the ignition of the secondary solid propellant 30 and effectively achieving intermittent operation of the two pulses.

[0050] The diaphragm device 40 is detachably assembled inside the secondary pulse housing 20 and sleeved on one axial end of the secondary solid propellant column 30. Compared to the existing adhesive fixing method, the detachable diaphragm device 40 allows for inspection of the secondary solid propellant column 30. In addition, an axial gap is formed between the diaphragm device 40 and the secondary pulse housing 20, which allows the diaphragm device 40 to compensate for axial movement.

[0051] It should be noted that the axial clearance here is also an annular clearance, surrounding the outer periphery of the secondary solid propellant grain 30. Furthermore, during manufacturing and primary pulse operation, the secondary solid propellant grain 30 may undergo slight deformation due to ambient temperature, resulting in a gap between the diaphragm device 40 and the end face of the secondary solid propellant grain 30. The pressure acting on the diaphragm device 40 during primary pulse operation allows the diaphragm device 40 to move towards the secondary solid propellant grain 30, eliminating the axial gap between them.

[0052] It is evident that the partition device 40 has a limited degree of freedom for axial sliding, which can be well adapted to situations where there is an axial gap between the partition device 40 and the secondary solid propellant 30, reducing the risk of seal failure caused by the gas in the gap being affected by ambient temperature.

[0053] In a further optional embodiment, the axial clearance includes a first axial clearance A1 and a second axial clearance A2, the first axial clearance A1 being located on the outer periphery of the second axial clearance A2 and being closer to the primary pulse housing 10 than the second axial clearance A2.

[0054] In this embodiment, the axial gap includes at least a first axial gap A1 and a second axial gap A2. Both the first axial gap A1 and the second axial gap A2 are annular gaps surrounding the outer periphery of the secondary solid propellant column 30, and are staggered in the axial and radial directions, thus forming a labyrinth structure to ensure sealing.

[0055] Furthermore, the axial spacing of the first axial gap A1 is smaller than the axial spacing of the second axial gap A2. In this embodiment, the axial sliding distance of the partition device 40 is determined by the axial spacing of the first axial gap A1, which is radially outward and axially closer to the first-stage pulse combustion chamber R1. Thus, during the axial movement of the partition device 40, the first axial gap A1 disappears before the second axial gap A2, ensuring the existence of the second axial gap A2 and guaranteeing airtightness.

[0056] In some optional embodiments, the diaphragm pulse engine 100 further includes a primary solid propellant 50 disposed within the primary pulse housing 10. The primary solid propellant 50 is an internally bore type propellant, and the secondary solid propellant 30 is an end-face type propellant.

[0057] In this embodiment, a primary solid propellant 50 is housed inside the primary pulse housing 10. The primary solid propellant 50 is a perforated propellant 50, with its perforated portion serving as the combustion surface. During combustion, combustion begins from the surface of the perforated portion, and the combustion surface gradually expands outward to form a gradually increasing combustion area.

[0058] The secondary solid propellant grain 30 is an end-face type grain, and combustion begins from one axial end of the grain, with the combustion surface gradually moving towards the other end along the axial direction of the grain. It should be noted that the separator device 40 is located on one axial end side of the secondary solid propellant grain 30, which is the starting combustion end of the secondary solid propellant grain 30.

[0059] Please see Figure 1A primary pulse ignition 51 is installed inside the inner hole of the primary solid propellant 50, and a secondary pulse ignition 31 is installed at the starting combustion end of the secondary solid propellant 30. The primary pulse ignition 51 is used to initiate the primary pulse, and the secondary pulse ignition 31 is used to initiate the secondary pulse. In specific applications, ignition wires are pre-embedded in the primary pulse housing 10 and the secondary pulse housing 20 to ignite the primary pulse ignition 51 and the secondary pulse ignition 31 respectively.

[0060] Figure 3a This is a schematic diagram of a partition device 40 provided according to one embodiment of this application. Figure 3b for Figure 3a Sectional view at point BB. Figure 3c for Figure 3a Sectional view at EE. See also Figure 3a and Figure 3b In some alternative embodiments, the partition device 40 includes a composite partition 41, which includes a heat insulation layer 411 and an inner reinforcing layer 412. The inner reinforcing layer 412 is located inside the heat insulation layer 411 and axially divides the heat insulation layer 411 into a first heat insulation layer 4111 and a second heat insulation layer 4112.

[0061] The first heat insulation layer 4111 and the second heat insulation layer 4112 have corresponding axial sides with a first open cavity C1 and a second open cavity C2 facing away from each other. The first open cavity C1 contains one axial end of the secondary solid propellant column 30, and the second open cavity C2 faces the primary pulse combustion chamber R1.

[0062] The composite partition 41 is provided with a weakening structure 413, which is configured to crack when subjected to pressure from the second opening C2 toward the first opening C1, and form an opening connecting the second opening C2 and the first opening C1.

[0063] In this embodiment, the composite partition 41 is a multi-layered structure composed of a variety of materials. Specifically, an inner reinforcing layer 412 is provided inside the heat insulation layer 411. The inner reinforcing layer 412 divides the heat insulation layer 411 in the axial direction, forming a layout in which the first heat insulation layer 4111, the inner reinforcing layer 412, and the second heat insulation layer 4112 are stacked sequentially in the axial direction.

[0064] Furthermore, a first open cavity C1 and a second open cavity C2 are formed on the axial sides of the composite partition 41. It should be noted that an open cavity here refers to a chamber with an opening on one axial side. The first open cavity C1 is located on the axial side of the first heat insulation layer 4111, and the second open cavity C2 is located on the axial side of the second heat insulation layer 4112.

[0065] Specifically, the first open cavity C1 is positioned facing the primary pulse combustion chamber R1, and the second open cavity C2 is positioned facing the secondary pulse combustion chamber R2 and houses one axial end of the secondary solid propellant 30. Here, the secondary solid propellant 30 is an end-face type propellant, and the axial end of the secondary solid propellant 30 housed in the second open cavity C2 is the starting combustion end.

[0066] Furthermore, the composite partition 41 has a weakening structure 413. It should be noted that the structural strength at the weakening structure 413 is lower than that at other locations on the composite partition 41. Therefore, when subjected to pressure from the second opening C2 toward the first opening C1 (which is also the direction of gas flow for the second-stage pulse, hereinafter referred to as the forward direction), the weakening structure 413 cracks and forms an opening to connect the second opening C2 and the first opening C1, thereby connecting the second-stage pulse combustion chamber R2 and the first-stage pulse combustion chamber R1.

[0067] Furthermore, during combustion of the primary solid propellant, although pressure is exerted on the composite partition 41 from the first open cavity C1 towards the second open cavity C2 (also the direction from the primary pulse combustion chamber R1 towards the secondary pulse combustion chamber R2, hereinafter referred to as reverse), the composite partition 41 is in close contact with one axial end of the secondary solid propellant 30. Therefore, the composite partition 41 cannot undergo significant deformation under reverse pressure, preventing the weakening structure 413 from cracking and forming an opening under reverse pressure. In other words, the assembly position of the composite partition 41 ensures that the weakening structure 413 can only open in the forward direction to form an opening.

[0068] Therefore, it can be seen that the composite partition 41 can play a sealing and heat insulation role during the first-stage pulse operation, preventing the second-stage solid propellant 30 from being ignited. During the second-stage pulse operation, the composite partition 41 is weakened by the impact of the high-temperature gas in the second-stage pulse combustion chamber R2, and the structure 413 is opened to form an opening, thereby realizing the function of intermittent operation on both sides of the engine.

[0069] Furthermore, since an inner reinforcing layer 412 is additionally added to the heat insulation layer 411, the composite partition layer 41 has good structural strength and can ensure good sealing even when a large reverse pressure is generated during the first-stage pulse operation. Moreover, the second open cavity C2 covers the axial starting combustion end of the second-stage solid propellant column 30, which has better sealing performance.

[0070] Because of the increased structural strength of the composite partition 41, no large fragments are generated during the opening formation process. After the opening is opened, the composite partition 41 is gradually ablated outward from the opening, reducing the risk of nozzle blockage. In other words, the inner reinforcing layer 412 is the internal reinforcing material of the heat insulation layer 411, which improves the heat insulation layer 411's ability to withstand first-stage pulse (reverse pressure) deformation and also ensures the structural integrity when the weakened structure 413 is opened.

[0071] Moreover, due to the increased structural strength of the composite partition 41, a simpler structural design can be adopted, making the partition device 40 lighter and thus not affecting the engine's mass ratio.

[0072] Figure 4 for Figure 3b A partial sectional view of the middle fixing ring 42. Please refer to... Figure 2 , Figure 3b as well as Figure 4 In some alternative embodiments, the partition device 40 further includes a retaining ring 42 and a sealing ring 43.

[0073] A retaining ring 42 is connected to the outer periphery of the composite partition 41, and a sealing ring 43 is disposed on the outer periphery of the retaining ring 42 and is in contact with the inner peripheral wall of the secondary pulse housing 20. An axial gap is formed between the axially aligned sides of the composite partition 41 and the retaining ring 42 and the axially open end of the secondary pulse housing 20.

[0074] In this embodiment, the composite partition 41 is fixed by a retaining ring 42, which can engage with the inner peripheral wall of the engine's combustion chamber via a sealing ring 43. Specifically, the outer peripheral side of the retaining ring 42 is provided with a sealing ring groove F, which is used to install the sealing ring 43.

[0075] Furthermore, since the fixing ring 42 is located on the outer periphery of the composite partition 41, and the axial length of the fixing ring 42 is less than the axial length of the composite partition 41, the fixing ring 42 and the composite partition 41 cooperate on the same axial side to form a stepped structure. This stepped structure forms an axial gap with the stepped portion at the axial opening end of the secondary pulse housing 20. In one embodiment, this stepped structure cooperates with the secondary pulse housing 20 to form a first axial gap A1 and a second axial gap A2.

[0076] In practical applications, the retaining ring 42 is a metal ring, such as an aluminum alloy ring or a titanium alloy ring, like hard aluminum LY20, ensuring sufficient strength while being lightweight and easy to assemble. Furthermore, the inner circumference of the retaining ring 42 has an irregular shape with grooves and protrusions, and grooves are also designed at both axial ends. These designs increase the bonding area between the retaining ring 42 and the composite spacer 41, and also improve the interface failure stress threshold by changing the shape of the bonding surface.

[0077] In a further optional embodiment, the middle part of the composite partition 41 protrudes axially toward the first open cavity C1 and forms a deepened annular cavity C11 located on the periphery of the first open cavity C1. The periphery of the first open cavity C1 is the deepened annular cavity C11, and the deepened annular cavity C11 partially overlaps with the circumferential projection of the second open cavity C2.

[0078] In this embodiment, the middle part of the composite partition 41 is convex in the positive direction, and the peripheral part of the first open cavity C1 is correspondingly formed with a deepened annular cavity C11. The deepened annular cavity C11 surrounds the outer peripheral side of the second open cavity C2, that is, the deep annular cavity C11 and the second open cavity C2 partially overlap in the circumferential direction.

[0079] Thus, the middle part of the composite partition 41 protrudes towards the primary pulse combustion chamber R1, thereby enabling the composite partition 41 to deform under reverse pressure.

[0080] Furthermore, the composite partition 41 also includes an outer reinforcing layer 414, which is located on at least a portion of the surface of the first heat insulation layer 4111 at the location of the deepened annular cavity C11.

[0081] In this embodiment, an outer reinforcing layer 414 is provided on the surface of the first heat insulation layer 4111 at the location of the deepened annular cavity C11. The outer reinforcing layer 414 can further improve the composite partition layer 41's ability to withstand the deformation of a first-level pulse.

[0082] In practical applications, the insulation layer 411 is a rubber layer, specifically nitrile rubber, which has a density of less than 1.20 × 10⁻⁶. 3 The material has a weight of kg / m3, which can reduce the mass of the partition device 40 and improve the engine mass ratio; the material has an elongation at break of more than 300%, which can well adapt to the deformation requirements; at the same time, under the action of high temperature and high pressure combustion gas in the engine, the material has low linear ablation rate and thermal conductivity, with a linear ablation rate of less than 0.06 mm / s, which well meets the requirements of ablation and heat insulation.

[0083] The inner reinforcing layer 412 and the outer reinforcing layer 414 are reinforcing fabrics, specifically nylon fabric, which has good compatibility with nitrile rubber materials. Nylon fabric material properties: density greater than 1.1 g / m³, tensile strength greater than 100 MPa, elongation greater than 100%, melting point greater than 100℃.

[0084] Furthermore, the partition device 40 is integrally molded using a molding and bonding process. The heat insulation layer 411, the inner reinforcing layer 412, and the outer reinforcing layer 414 are molded together and directly bonded to the fixing ring 42. Moreover, the nitrile rubber material and the aluminum alloy material have good interfacial adhesion properties, ensuring that the two will not easily detach.

[0085] In some alternative embodiments, the second open cavity C2 is configured to taper in the direction from the opening side of the second open cavity C2 toward the first open cavity C1.

[0086] In this embodiment, the opening side of the second open cavity C2 is larger than the inner side, which facilitates assembly and the covering of the composite separator 41 on the axial starting combustion end of the secondary solid propellant 30.

[0087] In some alternative embodiments, the portion of the deepened annular cavity C11 that overlaps with the second open cavity C2 in the circumferential direction is configured to taper from the opening side of the first open cavity C1 toward the second open cavity C2.

[0088] In this embodiment, the deeper the annular cavity C11 is, the narrower its size, and the inner side of the deep annular cavity C11 can have a smoothly transitioned pointed shape. Please refer to [link / reference]. Figure 3b In this case, the cross-sectional shape of the composite partition 41 is similar to a W shape. Under the action of the first-stage pulse (reverse pressure), it has a certain deformation capacity to adapt to the partial axial deformation of the propellant caused by the working pressure of the first-stage pulse, so as to avoid structural damage to the composite partition 41 under large axial deformation, and to ensure complete axial isolation of the two combustion chambers. Of course, this shape also meets the structural shape requirements of the molding process.

[0089] In some alternative embodiments, the weakening structure 413 is formed between the first insulation layer 4111 and the inner reinforcing layer 412 and includes a plurality of straight grooves D that intersect at a point.

[0090] In this embodiment, the weakening structure 413 is composed of multiple straight grooves D, which intersect at a point, thus forming a radial arrangement of multiple straight groove structures with the intersection point as the radiation center. Preferably, the intersection point of the multiple straight grooves D is located on the axis of the partition device 40.

[0091] It should be noted that the partition device 40 is generally coaxially assembled with the secondary solid propellant column 30, that is, the intersection point of multiple straight grooves D is arranged close to the axis of the secondary solid propellant column 30.

[0092] It should be understood that the thickness at the straight groove D is the smallest, and therefore the strength at the straight groove D is the lowest. When the secondary pulse is ignited, a gas flow is formed towards the primary pulse combustion chamber R1. The gas flow near the axis is the largest and the temperature is the highest. Thus, cracking can start from the intersection point and crack along the straight groove D. In this way, even under the lower positive pressure formed when the secondary pulse is working, it can open smoothly in a petal shape without producing fragments.

[0093] In specific applications, the inner reinforcing layer 412 also has slots. The number and position of the slots on the inner reinforcing layer 412 are the same as those on the first heat insulation layer 4111. The two work together to form the straight groove D in the weakening structure 413. That is, the weakening structure 413 is formed on the first heat insulation layer 4111 and the inner reinforcing layer 412.

[0094] In addition, a weakening structure 413 is formed in the middle of the composite partition 41. The middle of the composite partition 41 protrudes toward the first-stage pulse combustion chamber R1. That is, the weakening structure 413 is located at the protruding position of the first heat insulation layer 4111 and the inner reinforcing layer 412 in the composite partition 41.

[0095] It should be noted that the first heat insulation layer 4111 at the middle position of the composite partition 41 corresponds to the convex side layer, and correspondingly, the second heat insulation layer 4112 corresponds to the concave side layer. Obviously, the weakening structure 413 is located on the convex side, and the outer reinforcing layer 414 is not provided at the protruding position in the middle of the composite partition 41. This makes it easier for the positive pressure (during the secondary pulse ignition) to break through the weakening structure 413 to form an opening.

[0096] exist Figure 3a In the illustrated embodiment, there are eight linear grooves D, and one end of these linear grooves D converges at a point, forming a radial shape structure with the convergence point as the radiation center. The number of linear grooves D can be adjusted appropriately, preferably six to eight.

[0097] In a further optional embodiment, the cross-section of the straight groove D is gradually tapered inward on the opening side of the straight groove D.

[0098] In this embodiment, the opening side of the straight groove D is the widest, and it becomes narrower towards the inside. Figure 3c In the embodiment shown, the cross-section of the straight groove D is V-shaped, but it is not limited to this; for example, it can also be semi-circular, teardrop-shaped, etc.

[0099] It should be understood that the thickness of the interlayer at the location of the straight groove D is an important factor affecting the strength of the weakened structure 413, and it is set according to the material and the working duration of the first-stage pulse.

[0100] In some alternative embodiments, the sectional pulse engine 100 further includes a nozzle 60 connected to the axial side of the primary pulse housing 10 away from the secondary pulse housing 20.

[0101] In this embodiment, the gas generated during the first-stage pulse operation is ejected from the nozzle 60. After the first-stage pulse operation is completed, the second-stage pulse is started. The weakening structure 413 of the partition device 40 is opened by the second-stage pulse and forms an opening. The gas generated during the second-stage pulse operation enters the first-stage pulse combustion chamber R1 and is ejected through the nozzle 60, thus forming a two-stage pulse operation.

[0102] In practical applications, the sectional pulse engine 100 is assembled through the following steps:

[0103] The first step is to install the first-stage pulse ignition 51 inside the first-stage solid propellant 50 in the first-stage pulse combustion chamber R1 and connect it to the ignition wire.

[0104] The second step is to install the secondary pulse ignition 31 at the end of the secondary solid propellant 30 in the secondary pulse combustion chamber R2 and connect the ignition wire.

[0105] The third step is to install the sealing ring 43 in the sealing ring groove F of the partition device 40.

[0106] The fourth step is to install the partition device 40 with the sealing ring 43 at the opening step of the secondary pulse combustion chamber R2, wherein the side of the partition device 40 with the weakening structure 413 is close to the primary pulse combustion chamber R1.

[0107] The fifth step is to dock the first-stage pulse housing 10 with the second-stage pulse housing 20.

[0108] Step 6: Connect and assemble the nozzle 60 with the first-stage pulse housing 10.

[0109] It can be seen that the partition device 40 is fixed to the starting combustion end side of the secondary solid propellant 30 in a detachable assembly form, and the first axial gap A1 and the second axial gap A2 formed by the assembly ensure that the partition device 40 can slide axially on the cylindrical surface of the axial opening of the secondary pulse housing 20 to meet its dual-pulse operation requirements.

[0110] In addition, the partition device 40 adopts a composite structure of metal and non-metal, which plays a role in axial heat insulation and sealing in the solid dual-pulse engine, as well as having a forward opening function, thus meeting the dual requirements of structure and function.

[0111] The composite partition 41 is made of non-metallic materials, and the fixing ring 42 is made of metallic materials. The composite partition 41 adopts a multi-material layered structure, which improves the structural strength under the action of the reinforcing layer, ensuring that the partition will not be damaged due to large deformation, and ensuring heat insulation and deformation capacity. The partition device 40 is easy to assemble, reduces the weight of the partition device 40, and improves the engine's weight-to-weight ratio. It should be noted that this partition device 40 is not limited to solid dual-pulse engines, but can also be used in other multi-pulse engines.

[0112] Although embodiments of this application have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting this application. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of this application.

Claims

1. A staged pulse engine, characterized by, The application relates to a two-stage pulse shell, which comprises: a first-stage pulse shell (10) in which a first-stage pulse combustion chamber (R1) is formed; a second-stage pulse shell (20) in which a second-stage pulse combustion chamber (R2) is formed and which is axially spliced with the first-stage pulse shell (10), the second-stage pulse combustion chamber (R2) being axially spliced with the first-stage pulse combustion chamber (R1); a second-stage solid propellant column (30) arranged in the second-stage pulse combustion chamber (R2); and a partition device (40) arranged at an axial opening end of the second-stage pulse shell (20) towards the first-stage pulse shell (10) and connected to an inner circumferential wall of the second-stage pulse shell (20); wherein the partition device (40) can isolate the first-stage pulse combustion chamber (R1) from the second-stage pulse combustion chamber (R2), and an axial gap is formed between the partition device (40) and the second-stage pulse shell (20) in the axial direction, and the partition device (40) is arranged to be capable of moving in the axial direction towards the axial end surface of the second-stage solid propellant column (30) and being connected to the axial end surface of the second-stage solid propellant column (30).

2. The skiplaunch pulse engine of claim 1 wherein, The axial gap comprises a first axial gap (A1) and a second axial gap (A2); The first axial gap (A1) is located at the outer circumferential side of the second axial gap (A2) and is closer to the first-stage pulse shell (10) than the second axial gap (A2).

3. The skiff pulse engine of claim 2, wherein, The axial spacing of the first axial gap (A1) is smaller than the axial spacing of the second axial gap (A2).

4. The skiplaunch pulse engine of claim 1 wherein, The application further comprises a first-stage solid propellant column (50) arranged in the first-stage pulse shell (10); The first-stage solid propellant column (50) is a hole-type propellant column, and the second-stage solid propellant column (30) is an end surface-type propellant column.

5. The skiff pulse engine of claim 1, wherein, The partition device (40) comprises a composite partition (41), the composite partition (41) comprising a heat insulation layer (411) and an inner reinforcing layer (412), the inner reinforcing layer (412) being located in the heat insulation layer (411) and dividing the heat insulation layer (411) into a first heat insulation layer (4111) and a second heat insulation layer (4112) in the axial direction; The axial side of the first heat insulation layer (4111) and the axial side of the second heat insulation layer (4112) correspondingly form first and second open cavities (C1 and C2) facing away from each other, the first open cavity (C1) accommodating one end of the second-stage solid propellant column (30) in the axial direction, and the second open cavity (C2) facing the first-stage pulse combustion chamber (R1); The composite partition (41) is provided with a weakening structure (413) arranged to crack and form an opening connecting the second open cavity (C2) and the first open cavity (C1) when bearing pressure from the second open cavity (C2) towards the first open cavity (C1).

6. The skiplaunch pulse engine of claim 5, wherein, The middle part of the composite partition layer (41) is convexly arranged along the axial direction towards the first open cavity (C1) and forms a deepened ring cavity (C11) located at the periphery of the first open cavity (C1), the periphery of the first open cavity (C1) is the deepened ring cavity (C11), and the deepened ring cavity (C11) overlaps with the partial projection of the second open cavity (C2) in the circumferential direction.

7. The skiff pulse engine of claim 6, wherein, The composite partition layer (41) further comprises an outer reinforcing layer (414) located at least part of the surface of the first heat insulation layer (4111) at the position of the deepened ring cavity (C11).

8. The skiff pulse engine of claim 5, wherein, The weakening structure (413) is formed between the first heat insulation layer (4111) and the inner reinforcing layer (412) and comprises a plurality of straight grooves (D), and the plurality of straight grooves (D) intersect at a point.

9. The skiff pulse engine of claim 5, wherein, The partition layer device (40) further comprises a fixing ring (42) and a sealing ring (43); The fixing ring (42) is connected to the outer periphery of the composite partition layer (41), and the sealing ring (43) is arranged on the outer periphery of the fixing ring (42) and is connected to the inner peripheral wall of the two-stage pulse shell (20); The axial side of the composite partition layer (41) and the fixing ring (42) is located between the axial opening end of the two-stage pulse shell (20).

10. The skiplaunch pulse engine of any one of claims 1 to 9, wherein, Further comprising a nozzle (60) connected to the axial side of the one-stage pulse shell (10) away from the two-stage pulse shell (20).

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