Separation surface oil discharge sealing structure

Abstract

The invention discloses a separation surface oil discharge sealing structure, and relates to the technical field of ramjet engines, the separation surface oil discharge sealing structure comprises a fluid transmission mechanism, the fluid transmission mechanism comprises a first oil discharge pipe and a second oil discharge pipe which are respectively arranged in a task load and a boosting structure, and the output end of the first oil discharge pipe is butted and communicated with the input end of the second oil discharge pipe; the pump is used for conveying high-temperature cooling oil; the thermal expansion sealing mechanism sleeves the communication part of the first oil discharge pipe and the second oil discharge pipe; the limiting mechanism sleeves the outer wall of the thermal expansion sealing mechanism; when the first oil discharge pipe discharges high-temperature cooling oil to the second oil discharge pipe, the thermal expansion sealing mechanism is heated to expand, the communication position of the first oil discharge pipe and the second oil discharge pipe is sealed, leakage of the high-temperature cooling oil is avoided, compared with traditional conical surface pressing sealing, axial friction force needing to be overcome does not exist when a task load is separated from a boosting structure, and the service life of the boosting structure is prolonged. Therefore, the separation action can be quickly, smoothly and reliably completed, and the hidden danger of separation delay or failure caused by the fact that the sealing structure is pressed by a conical surface is eliminated.

Description

Technical Field

[0001] This invention relates to the field of ramjet engine technology, and more specifically to a separation surface oil drain sealing structure. Background Technology

[0002] With the rapid development of hypersonic vehicles and ramjet engine technology, these vehicles face severe thermal protection challenges during high-speed flight. To address the operational requirements of the engine combustion chamber and airframe structure in high-temperature environments, oil cooling systems, as an active thermal protection measure, are widely used in hypersonic vehicles. This system achieves effective heat transfer and temperature control through the circulation of cooling oil between the engine and the airframe structure, thereby allowing the vehicle to achieve higher speeds and longer flight durations within the temperature resistance limits of existing materials.

[0003] In existing technologies, cooling oil drain lines are typically arranged in segments, located between the mission payload section and the booster section. The two sections of the oil pipe require a reliable sealing structure at their separation point to ensure the cooling system functions properly during flight. Currently, the commonly used sealing method is a traditional conical compression seal structure, where axial preload forces the conical mating surfaces of the two oil pipe sections to press against each other, forming a sealing interface.

[0004] However, this traditional sealing structure has the following obvious drawbacks: High separation risk: The conical clamping structure introduces additional axial preload and friction at the separation surface, which may cause uneven separation force, separation delay or even separation failure when the mission payload separates from the booster stage, increasing the unreliability and safety risks of the spacecraft separation phase. Summary of the Invention

[0005] In view of the above-mentioned defects or deficiencies in the prior art, it is desirable to provide a separation surface oil drainage sealing structure.

[0006] This invention provides a separation surface oil drainage sealing structure, comprising: A fluid transmission mechanism is used to transmit high-temperature cooling oil after heat exchange with the engine. The fluid transmission mechanism includes a first oil drain pipe and a second oil drain pipe respectively disposed inside the mission load and inside the booster structure. The output end of the first oil drain pipe and the input end of the second oil drain pipe are connected to each other. A thermal expansion sealing mechanism is sleeved at the connection between the first oil drain pipe and the second oil drain pipe; A limiting mechanism is sleeved on the outer wall of the thermal expansion sealing mechanism and is used to radially limit the thermal expansion sealing mechanism; When the first oil drain pipe discharges high-temperature cooling oil into the second oil drain pipe, the thermal expansion sealing mechanism expands due to heat, and the limiting mechanism is used to make the thermal expansion sealing mechanism expand inward to seal the connection between the first oil drain pipe and the second oil drain pipe.

[0007] According to the technical solution provided by the present invention, the mission payload includes a mission payload housing, the booster structure includes a booster structure housing, the mission payload housing abuts against the booster structure housing, and the abutment surface is a separation surface.

[0008] According to the technical solution provided by the present invention, a first groove is formed on the end face of the mission payload housing near the booster structure housing, and a first through hole communicating with the interior of the mission payload housing is formed at the bottom of the first groove, and the first oil drain pipe extends through the first through hole into the first groove; a second groove is formed on the end face of the booster structure housing near the mission payload housing, and a second through hole communicating with the interior of the booster structure housing is formed at the bottom of the second groove, and the second oil drain pipe extends through the second through hole into the second groove; the first groove and the second groove correspond to each other.

[0009] According to the technical solution provided by the present invention, the thermal expansion sealing mechanism includes a first thermal expansion bushing and a second thermal expansion bushing, the first thermal expansion bushing and the second thermal expansion bushing are respectively disposed inside the first groove and the second groove, and the first thermal expansion bushing and the second thermal expansion bushing are in contact with each other; the mating surface of the first thermal expansion bushing and the second thermal expansion bushing are coplanar with the separating surface.

[0010] According to the technical solution provided by the present invention, the limiting mechanism includes a first limiting bushing and a second limiting bushing. The first limiting bushing and the second limiting bushing are respectively disposed in the first groove and the second groove. The first limiting bushing is sleeved on the outer wall of the first thermal expansion bushing, and the outer wall of the first limiting bushing is fixedly connected to the inner wall of the first groove. The second limiting bushing is sleeved on the outer wall of the second thermal expansion bushing, and the outer wall of the second limiting bushing is fixedly connected to the inner wall of the second groove. The first limiting bushing and the second limiting bushing are in contact with each other, and their contact surface is coplanar with the separation surface.

[0011] According to the technical solution provided by the present invention, the mission payload housing and the booster structure housing are connected by an electrical separator.

[0012] According to the technical solution provided by the present invention, one end of the first oil drain pipe that connects to the second oil drain pipe is close to the mission load housing relative to the separation surface.

[0013] According to the technical solution provided by the present invention, the coefficient of thermal expansion of the thermal expansion sealing mechanism is greater than the coefficients of thermal expansion of the first oil drain pipe, the second oil drain pipe and the limiting mechanism.

[0014] In summary, this invention specifically discloses a separation surface oil discharge sealing structure, including a fluid transmission mechanism for transmitting high-temperature cooling oil after heat exchange with the engine. The fluid transmission mechanism includes a first oil discharge pipe and a second oil discharge pipe respectively disposed inside the mission load and inside the booster structure. The output end of the first oil discharge pipe and the input end of the second oil discharge pipe are connected and communicate with each other. A thermal expansion sealing mechanism is sleeved at the connection between the first oil discharge pipe and the second oil discharge pipe. A limiting mechanism is sleeved on the outer wall of the thermal expansion sealing mechanism for radially limiting the thermal expansion sealing mechanism. When the first oil discharge pipe discharges high-temperature cooling oil to the second oil discharge pipe, the thermal expansion sealing mechanism expands due to heat. Under the limiting action of the limiting mechanism, the thermal expansion sealing mechanism can only expand inward, thereby sealing the connection between the first oil discharge pipe and the second oil discharge pipe. The traditional conical surface mating method that relies on axial preload to achieve sealing has been abandoned, and the axial preload at the connection point has been eliminated. When the mission load and the booster structure need to be separated, there is no additional axial friction force that needs to be overcome between the first and second oil pipes, thus ensuring that the separation action can be completed quickly, smoothly and reliably, eliminating the risk of separation delay or failure caused by the conical surface pressing sealing structure. At the same time, high-temperature cooling oil is used as the sealing power source. During the flight operation phase that requires sealing, the high-temperature cooling oil causes the thermal expansion sealing mechanism to expand adaptively to achieve sealing, avoiding damage to mission payloads or electronic components and other structures in the booster structure caused by leakage of high-temperature cooling oil. Attached Figure Description

[0015] Other features, objects, and advantages of the invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings: Figure 1 This is a cross-sectional view of a separation surface oil drainage sealing structure.

[0016] The following are the labels in the diagram: 1. First oil drain pipe; 2. Second oil drain pipe; 3. Mission load housing; 4. Boost structure housing; 5. First thermal expansion bushing; 6. Second thermal expansion bushing; 7. Separation surface; 8. First limiting bushing; 9. Second limiting bushing. Detailed Implementation

[0017] The present invention will now be described in further detail with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and not intended to limit it. Furthermore, it should be noted that, for ease of description, only the parts relevant to the invention are shown in the accompanying drawings.

[0018] It should be noted that, unless otherwise specified, the embodiments and features described in the present invention can be combined with each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0019] Please refer to Figure 1 A separation surface oil drainage sealing structure, comprising: A fluid transmission mechanism is used to transmit high-temperature cooling oil after heat exchange with the engine. The fluid transmission mechanism includes a first oil drain pipe 1 and a second oil drain pipe 2 respectively disposed inside the mission load and inside the booster structure. The output end of the first oil drain pipe 1 and the input end of the second oil drain pipe 2 are connected to each other. A thermal expansion sealing mechanism is fitted at the connection between the first oil pipe 1 and the second oil pipe 2. A limiting mechanism is sleeved on the outer wall of the thermal expansion sealing mechanism and is used to radially limit the thermal expansion sealing mechanism. When the first oil drain pipe 1 discharges high-temperature cooling oil into the second oil drain pipe 2, the thermal expansion sealing mechanism expands due to heat. The limiting mechanism is used to make the thermal expansion sealing mechanism expand inward to seal the connection between the first oil drain pipe 1 and the second oil drain pipe 2.

[0020] Specifically, the mission payload can be a hypersonic aircraft that is powered by a ramjet engine to achieve flight. During flight, the ramjet engine generates heat by doing work and continuously generates heat through high-speed friction with the air. To reduce the heat, an oil cooling method is used. The mission payload is equipped with an oil tank containing cooling oil. Through the pipeline arrangement, the cooling oil flows through the pipeline to exchange heat with the ramjet engine, reducing the heat of the ramjet engine. At the same time, it carries the heat to the fluid transmission mechanism, and then flows through the first oil pipe 1 to the second oil pipe 2, entering the booster structure. The booster structure is equipped with an oil storage section that can receive the high-temperature cooling oil.

[0021] When the mission payload moves to the separation window, the booster structure needs to be separated, which requires disconnecting the connection between the first oil drain pipe 1 and the second oil drain pipe 2. The traditional connection method for the first oil drain pipe 1 and the second oil drain pipe 2 is to achieve a tight connection through a conical pressure sealing structure. That is, the input end of the second oil drain pipe 2 is a conical surface, and the inner wall of the output end of the first oil drain pipe 1 is a conical surface. The input end of the second oil drain pipe 2 is pressed into the output end of the first oil drain pipe 1. The output end of the first oil drain pipe 1 expands radially, and the input end of the second oil drain pipe 2 contracts radially, achieving an interference fit and generating huge contact pressure. This seals the connection between the first oil drain pipe 1 and the second oil drain pipe 2, preventing high-temperature cooling oil leakage from damaging the mission payload or electronic components and other structures within the booster structure.

[0022] However, the traditional conical compression sealing structure has the following risks: when the mission payload moves to the separation window, it is necessary to disconnect the mission payload from the booster structure. However, due to the conical compression effect of the first oil pipe 1 and the second oil pipe 2, there is an axial preload between the output end of the first oil pipe 1 and the input end of the second oil pipe 2, which makes it difficult or difficult to separate the first oil pipe 1 and the second oil pipe 2. This can lead to delays or failures in the separation of the booster structure, increasing the safety risks of hypersonic vehicles.

[0023] This invention provides a separation surface oil drain sealing structure. A thermal expansion sealing mechanism is fitted at the connection between the first and second oil drain pipes, and a limiting mechanism is fitted over the thermal expansion sealing mechanism. When the cooling oil cools the ramjet engine, the high-temperature cooling oil, carrying heat, flows through the first and second oil drain pipes to the booster structure. Through heat conduction, the heat of the high-temperature cooling oil is transferred to the thermal expansion sealing mechanism, causing it to expand. The limiting mechanism on the outside of the thermal expansion sealing mechanism limits its expansion, ensuring that it can only expand radially inward. This achieves a tight seal at the connection between the first and second oil drain pipes, preventing leakage of the high-temperature cooling oil. Furthermore, unlike traditional conical surface compression seals, there is no axial preload between the first and second oil drain pipes. Separation is unaffected by axial preload, ensuring smooth separation and guaranteeing the safety of the hypersonic vehicle.

[0024] Furthermore, the mission payload includes a mission payload housing 3, and the booster structure includes a booster structure housing 4. The mission payload housing 3 abuts against the booster structure housing 4, and the abutment surface is the separation surface 7.

[0025] The mission payload housing 3 and the booster structure housing 4 are connected by an electric separator.

[0026] Specifically, the mission payload housing 3 and the booster structure housing 4 are connected by an electric separator, so that the mission payload housing 3 abuts against the booster structure housing 4, reducing space occupation and wind resistance during flight; optionally, the electric separator is an explosive bolt.

[0027] The electric separation unit is located partly on the mission payload housing 3 and partly on the booster structure housing 4. When the mission payload has not reached the separation window or has not received a separation command, the mission payload carries the booster mechanism in normal flight. When the mission payload reaches the separation window or receives a separation command, the electric separation unit receives an electrical signal and quickly unlocks. Under the influence of air resistance, the booster mechanism can quickly achieve separation. At the same time, since there is no axial preload between the first oil pipe 1 and the second oil pipe 2, it is not affected by the axial preload during separation and will not affect the normal separation of the booster structure and the mission payload.

[0028] Furthermore, a first groove is formed on the end face of the mission payload housing 3 near the booster structure housing 4, and a first through hole communicating with the interior of the mission payload housing 3 is formed at the bottom of the first groove. The first oil drain pipe 1 extends through the first through hole to the first groove. A second groove is formed on the end face of the booster structure housing 4 near the mission payload housing 3, and a second through hole communicating with the interior of the booster structure housing 4 is formed at the bottom of the second groove. The second oil drain pipe 2 extends through the second through hole to the second groove. The first groove and the second groove correspond to each other.

[0029] Specifically, a first groove and a second groove are respectively provided on the side walls of the mission payload shell 3 and the booster structure shell 4 that are close to each other, and the first groove and the second groove correspond to each other.

[0030] The bottom of the first groove has a first through hole that communicates with the inside of the mission load housing 3. The output end of the first oil drain pipe 1 extends through the first through hole into the first groove. The bottom of the second groove has a second through hole that communicates with the inside of the booster structure housing 4. The input end of the second oil drain pipe 2 extends through the second through hole into the second groove. Thus, the output end of the first oil drain pipe 1 and the input end of the second oil drain pipe 2 are connected and communicated, thereby realizing the flow of high-temperature cooling oil.

[0031] Furthermore, the thermal expansion sealing mechanism includes a first thermal expansion bushing 5 and a second thermal expansion bushing 6, which are respectively disposed inside the first groove and the second groove, and are in contact with each other; the mating surface of the first thermal expansion bushing 5 and the second thermal expansion bushing 6 are coplanar with the separating surface 7.

[0032] Specifically, the thermal expansion sealing mechanism includes a first thermal expansion bushing 5 and a second thermal expansion bushing 6. The first thermal expansion bushing 5 and the second thermal expansion bushing 6 are respectively disposed in the first groove and the second groove. The first thermal expansion bushing 5 is sleeved on the outer wall of the first oil drain pipe 1, and the second thermal expansion bushing 6 is sleeved on the outer wall of the second oil drain pipe 6. The first thermal expansion bushing 5 and the second thermal expansion bushing 6 are in contact with each other, and the mating surface and the separating surface 7 are coplanar.

[0033] When the booster structure is not separated, the mission load housing 3 and the booster structure housing 4 are connected by an electrical separator, and the mission load housing 3 and the booster structure housing 4 can abut against each other, thus achieving axial limiting between the first thermal expansion bushing 5 and the second thermal expansion bushing 6, so that the first thermal expansion bushing 5 and the second thermal expansion bushing 6 are tightly mated together, and leakage is avoided at the mating surface of the first thermal expansion bushing 5 and the second thermal expansion bushing 6.

[0034] Furthermore, the limiting mechanism includes a first limiting bushing 8 and a second limiting bushing 9. The first limiting bushing 8 and the second limiting bushing 9 are respectively disposed in the first groove and the second groove. The first limiting bushing 8 is sleeved on the outer wall of the first thermal expansion bushing 5, and the outer wall of the first limiting bushing 8 is fixedly connected to the inner wall of the first groove. The second limiting bushing 9 is sleeved on the outer wall of the second thermal expansion bushing 6, and the outer wall of the second limiting bushing 9 is fixedly connected to the inner wall of the second groove. The first limiting bushing 8 and the second limiting bushing 9 are in contact with each other, and their contact surface is coplanar with the separation surface 7.

[0035] Specifically, the first limiting bushing 8 and the second limiting bushing 9 are respectively disposed in the first groove and the second groove, and the first limiting bushing 8 is sleeved on the outer wall of the first thermal expansion bushing 5 and fixedly connected to the inner wall of the first groove. The second limiting bushing 9 is sleeved on the outer wall of the second thermal expansion bushing 6 and fixedly connected to the outer wall of the second limiting bushing 9 and the inner wall of the second groove. The mating surface of the first limiting bushing 8 and the second limiting bushing 9 are coplanar with the separating surface 7.

[0036] When the booster structure does not separate, the mission load housing 3 and the booster structure housing 4 abut against each other, and the first limiting bushing 8 and the second limiting bushing 9 can achieve tight docking, further limiting the axial direction of the first thermal expansion bushing 5 and the second thermal expansion bushing 6, and at the same time limiting the external direction of the first thermal expansion bushing 5 and the second thermal expansion bushing 6. Therefore, after the cooling oil cools the ramjet engine, the high-temperature cooling oil carrying heat flows through the first oil drain pipe 1 and the second oil drain pipe 2. The heat is transferred to the first thermal expansion bushing 5 and the second thermal expansion bushing 6 through the first oil drain pipe 1 and the second oil drain pipe 2. The first thermal expansion bushing 5 and the second thermal expansion bushing 6 expand due to the heat. Under the axial and external limiting action of the first limiting bushing 8 and the second limiting bushing 9, the first thermal expansion bushing 5 and the second thermal expansion bushing 6 can only deform inward. Thus, the first thermal expansion bushing 5 and the second thermal expansion bushing 6 can squeeze the first oil drain pipe 1 and the second oil drain pipe 2 inward, thereby achieving the purpose of sealing the connection between the first oil drain pipe 1 and the second oil drain pipe 2.

[0037] Furthermore, one end of the first oil pipe 1 that connects to the second oil pipe 2 is close to the mission load housing 3 relative to the separation surface 7.

[0038] Specifically, the connection point between the first oil drain pipe 1 and the second oil drain pipe 2 is opposite to the separation surface 7 and is close to the mission payload housing 3. Therefore, when the booster structure has not separated, the input end of the second oil drain pipe 2 can extend into the first thermal expansion bushing 5. Furthermore, because the first thermal expansion bushing 5 expands inward when heated, it presses against the second oil drain pipe 2, thus limiting the input end of the second oil drain pipe 2 and facilitating the docking of the first and second oil drain pipes 1 and 2. During flight, vibrations inevitably occur between the mission payload and the booster structure. If the first and second oil drain pipes 1 and 2... The connection point of the first oil pipe 1 and the separation surface 7 are coplanar. Vibration can easily cause the first oil pipe 1 and the second oil pipe 2 to become misaligned, which will lead to leakage of high-temperature cooling oil at the connection point of the first oil pipe 1 and the second oil pipe 2, affecting the sealing effect. However, the design that the connection point of the first oil pipe 1 and the second oil pipe 2 is not coplanar with the separation surface 7 prevents the first oil pipe 1 and the second oil pipe 2 from becoming misaligned due to vibration, which helps to ensure the normal connection of the first oil pipe 1 and the second oil pipe 2, and effectively ensures that the output end of the first oil pipe 1 and the input end of the second oil pipe 2 are properly connected.

[0039] Furthermore, the coefficient of thermal expansion of the thermal expansion sealing mechanism is greater than that of the first oil drain pipe 1, the second oil drain pipe 2, and the limiting mechanism.

[0040] Optionally, the first oil pipe 1, the second oil pipe 2, the first limiting bushing 8 and the second limiting bushing 9 are made of nickel-based high-temperature alloy gh4169; the first thermal expansion bushing 5 and the second thermal expansion bushing 6 are made of copper.

[0041] The core application of this separation surface oil drainage sealing structure is in the sealing of the oil drainage pipelines of hypersonic vehicle mission payloads and booster structures. It replaces the traditional conical surface compression seal with a thermal expansion adaptive seal, achieving reliable pipeline sealing while eliminating axial preload and ensuring smooth separation between the two. The specific working principle is as follows: The first oil pipe 1 inside the mission payload is connected to the second oil pipe 2 inside the booster structure. The connection is designed to be close to the mission payload and opposite to the separation surface 7, which can effectively avoid pipeline misalignment and leakage caused by flight vibration. The output end of the first oil pipe 1 extends into the first groove on the side wall of the mission payload housing 3, and the input end of the second oil pipe 2 extends into the second groove on the side wall of the booster structure housing 4.

[0042] The first row of oil pipes 1 is fitted with a first thermal expansion bushing 5 and a first limiting bushing 8 in sequence. The second row of oil pipes 2 is fitted with a second thermal expansion bushing 6 and a second limiting bushing 9 in sequence. The mating surfaces of the first thermal expansion bushing 5 and the second thermal expansion bushing 6, as well as the mating surfaces of the first limiting bushing 8 and the second limiting bushing 9, are all coplanar with the separation surface 7. At the same time, the outer walls of the first limiting bushing 8 and the second limiting bushing are fixed to the inner walls of the first groove and the second groove, respectively. The task load and the booster structure are connected and fixed through an electric separator, thereby forming a reliable axial clamping and limiting of the first thermal expansion bushing 5 and the second thermal expansion bushing 6, and the first limiting bushing 8 and the second limiting bushing 9, to ensure assembly stability.

[0043] During the thermal expansion and sealing process after entering flight conditions, the heat generated by the operation of the ramjet engine and the friction of high-speed flight of the hypersonic vehicle will be absorbed by the cooling oil in the fuel tank inside the mission payload. The high-temperature cooling oil after heat exchange will be transported along the pipeline to the first oil pipe 1, and then flow to the second oil pipe 2 connected to the first oil pipe 1, and finally enter the fuel storage section of the booster structure. During this process, the heat from the high-temperature cooling oil is transferred through the first oil drain pipe 1 and the second oil drain pipe 2 to the first thermal expansion bushing 5 and the second thermal expansion bushing 6. Since the materials of the first thermal expansion bushing 5 and the second thermal expansion bushing 6 have a thermal expansion coefficient greater than that of the first oil drain pipe 1, the second oil drain pipe 2, the first limiting bushing 8, and the second limiting bushing 9, the first thermal expansion bushing 5 and the second thermal expansion bushing 6 will expand due to heat. Furthermore, since the first limiting bushing 8 and the second limiting bushing 9 will limit the first thermal expansion bushing 5 and the second thermal expansion bushing 6, the first thermal expansion bushing 5 and the second thermal expansion bushing 6 can only expand inward after being heated. This inward expansion will cause the first thermal expansion bushing 5 and the second thermal expansion bushing 6 to tightly press the connection between the first oil drain pipe 1 and the second oil drain pipe 2, thereby achieving a reliable seal at the connection, effectively preventing the leakage of high-temperature cooling oil, and avoiding damage to the mission load or critical components such as electronic components inside the booster structure.

[0044] When the hypersonic vehicle reaches the preset separation window, it enters the separation and unlocking process. At this time, the electric separation component receives a control signal and quickly unlocks, releasing the connection between the mission payload and the booster structure. Because this sealing structure uses a thermal expansion sealing method, unlike traditional conical compression seals which generate axial preload, there is no axial preload constraint between the first oil pipe 1 and the second oil pipe 2. Therefore, under the action of air resistance, the mission payload and the booster structure can separate smoothly without separation jamming, delay, or even separation failure caused by axial preload, effectively ensuring the flight safety of the hypersonic vehicle.

[0045] The above description is merely a preferred embodiment of the present invention and an explanation of the technical principles employed. Those skilled in the art should understand that the scope of the invention is not limited to the specific combination of the above-described technical features, but also includes other technical solutions formed by arbitrary combinations of the above-described technical features or their equivalents without departing from the inventive concept. For example, technical solutions formed by substituting the above-described features with (but not limited to) technical features with similar functions disclosed in this invention.

Claims

1. A separation surface oil drainage sealing structure, characterized in that, include: The fluid transmission mechanism includes a first oil drain pipe (1) and a second oil drain pipe (2) respectively disposed inside the mission load and inside the booster structure. The output end of the first oil drain pipe (1) and the input end of the second oil drain pipe (2) are connected and communicated to each other, and are used to transmit high-temperature cooling oil after heat exchange with the engine. A thermal expansion sealing mechanism is sleeved at the connection between the first oil drain pipe (1) and the second oil drain pipe (2); A limiting mechanism is sleeved on the outer wall of the thermal expansion sealing mechanism and is used to radially limit the thermal expansion sealing mechanism; When the first oil drain pipe (1) discharges high-temperature cooling oil into the second oil drain pipe (2), the thermal expansion sealing mechanism expands due to heat. The limiting mechanism is used to make the thermal expansion sealing mechanism expand inward to seal the connection between the first oil drain pipe (1) and the second oil drain pipe (2).

2. The oil-sealing structure for a separating surface according to claim 1, characterized in that, The mission payload includes a mission payload housing (3), the booster structure includes a booster structure housing (4), the mission payload housing (3) abuts against the booster structure housing (4), and the abutment surface is the separation surface (7).

3. The oil-sealing structure for a separating surface according to claim 2, characterized in that, The mission payload housing (3) has a first groove on its end face near the booster structure housing (4). The bottom of the first groove has a first through hole that communicates with the interior of the mission payload housing (3). The first oil drain pipe (1) extends through the first through hole into the first groove. The booster structure housing (4) has a second groove on its end face near the mission payload housing (3). The bottom of the second groove has a second through hole that communicates with the interior of the booster structure housing (4). The second oil drain pipe (2) extends through the second through hole into the second groove. The first groove and the second groove correspond to each other.

4. The oil-sealing structure for a separating surface according to claim 3, characterized in that, The thermal expansion sealing mechanism includes a first thermal expansion bushing (5) and a second thermal expansion bushing (6). The first thermal expansion bushing (5) and the second thermal expansion bushing (6) are respectively disposed inside the first groove and the second groove, and the first thermal expansion bushing (5) and the second thermal expansion bushing (6) are in contact with each other. The mating surfaces of the first thermal expansion bushing (5) and the second thermal expansion bushing (6) are coplanar with the separating surface (7).

5. The oil drain sealing structure for the separation surface according to claim 4, characterized in that, The limiting mechanism includes a first limiting bushing (8) and a second limiting bushing (9). The first limiting bushing (8) and the second limiting bushing (9) are respectively disposed in the first groove and the second groove. The first limiting bushing (8) is sleeved on the outer wall of the first thermal expansion bushing (5), and the outer wall of the first limiting bushing (8) is fixedly connected to the inner wall of the first groove. The second limiting bushing (9) is sleeved on the outer wall of the second thermal expansion bushing (6), and the outer wall of the second limiting bushing (9) is fixedly connected to the inner wall of the second groove. The first limiting bushing (8) and the second limiting bushing (9) are in contact with each other, and their contact surface is coplanar with the separation surface (7).

6. The oil-sealing structure for a separating surface according to claim 2, characterized in that, The mission payload housing (3) and the booster structure housing (4) are connected by an electrical separator.

7. The oil-sealing structure for a separating surface according to claim 2, characterized in that, One end of the first drain pipe (1) that connects to the second drain pipe (2) is close to the mission load housing (3) relative to the separation surface (7).

8. The oil-sealing structure for a separating surface according to claim 1, characterized in that, The coefficient of thermal expansion of the thermal expansion sealing mechanism is greater than that of the first oil drain pipe (1), the second oil drain pipe (2), and the limiting mechanism.

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