Auxiliary device for butt joint of exhaust pipes of rocket oxygen tank

Abstract

The invention relates to the technical field of rockets, and particularly discloses a rocket oxygen tank exhaust pipe butt joint auxiliary device which comprises a butt joint flange installed on a rocket oxygen tank, and an oxygen exhaust port in the rocket oxygen tank is installed in the center of the butt joint flange; the rack comprises a bearing frame, a base and a linear sliding mechanism, the linear sliding mechanism is installed on the bearing frame, and a sealing piece and a butt joint piece are arranged at the end, close to the butt joint flange, of the connecting pipe; the linear sliding mechanism is connected with the butt joint component through the mounting piece; through the linear sliding mechanism, the butt joint component installed at the end of the exhaust pipe in a matched mode, so that connection between the butt joint component and the butt joint flange can be driven through the linear sliding mechanism, and on the contrary, separation between the butt joint component and the butt joint flange can be driven through the linear sliding mechanism; therefore, workers are prevented from staying near the oxygen outlet of the rocket before the rocket is radiated, and the safety of the workers at the post is effectively improved when the rocket is launched.

Description

Technical Field

[0001] This invention relates to the field of rocket technology, and specifically to an auxiliary device for docking the exhaust pipe of a rocket oxygen tank. Background Technology

[0002] my country's new generation of medium and large rockets are all cryogenic launch vehicles, using cryogenic propellants such as liquid hydrogen and liquid oxygen. Therefore, during the launch preparation phase, there are numerous gas and liquid pipeline interfaces with ground equipment for propellant loading and venting from the rocket's tanks. During liquid oxygen loading and storage, the liquid oxygen tank releases a large amount of cryogenic oxygen generated by boiling and evaporation through the vent connector. Existing vent connectors use a claw-type or rotary clamping design, rigidly connecting to the rocket's oxygen vent. Therefore, the docking and detachment processes require extensive personnel operation, and manual detachment is necessary before launch, leaving many personnel stranded at the front end and unable to evacuate. Summary of the Invention

[0003] To address the shortcomings of existing technologies, this invention provides an auxiliary device for docking rocket oxygen tank exhaust pipes.

[0004] The rocket oxygen tank exhaust pipe docking auxiliary device of the present invention includes: The docking flange is installed on the rocket oxygen tank, and the oxygen vent on the rocket oxygen tank is installed in the center of the docking flange; The frame includes a support frame, a base, and a linear sliding mechanism. The linear sliding mechanism is mounted on the support frame, and the support frame is mounted on the base via a lifting mechanism. The docking component includes a connecting pipe fixedly installed at the end of the exhaust pipe, and a sealing element and a docking element are provided at the end of the connecting pipe near the docking flange. The linear sliding mechanism is connected to the docking component via an mounting component.

[0005] In some embodiments, the sealing element is a conical sleeve, the conical sleeve includes an inner layer and an outer layer, a venting cavity is provided between the inner layer and the outer layer, vent holes are uniformly provided on the outer edge of the inner layer, and an air injection pipe is connected to the venting cavity; Both the inner and outer layers are made of flexible materials.

[0006] In some embodiments, the seal has an internal mating member for transmitting the settling force of the rocket oxygen tank.

[0007] In some embodiments, the docking member includes, A connecting tapered tube is fixedly installed on the connecting pipe and embedded in the center of the inner layer, and the maximum diameter of the connecting tapered tube is greater than the diameter of the connecting flange; and / or a limiting flange, wherein the limiting flange is fixedly connected to the end of the connecting pipe and is adapted to the inner diameter of the mating flange; And / or transfer rods, all of which are fixedly connected to the connecting pipe, and the mating flanges are provided with a number of mating holes for inserting the transfer rods.

[0008] In some embodiments, the linear sliding mechanism includes a slide rail, a sliding block, and a driving member for driving the sliding block to move on the slide rail. The mounting member is mounted on the sliding block, and the connecting pipe in the docking component is detachably connected to the sliding block through the mounting member.

[0009] In some embodiments, the lifting mechanism includes a lead screw, a slider, and a first power component that drives the lead screw to rotate. The output shaft of the first power component is connected to the lead screw via an electromagnetic clutch. The bottom of the base is fixedly connected to the slider, and the slider carries the base to lift and lower by rotating the lead screw.

[0010] In some embodiments, a guide component is also included, the guide component including a first arcuate rail; The first arc-shaped rail is installed on the side of the frame away from the rocket oxygen tank. A limiting ring adapted to the diameter of the exhaust pipe is installed on the first arc-shaped rail. The exhaust pipe between the first arc-shaped rail and the base is arc-shaped. The diameter of the limiting ring is larger than the diameter of the exhaust pipe.

[0011] In some embodiments, a drive roller adapted to the exhaust pipe and a second power component adapted to the exhaust pipe are mounted on the first arc-shaped rail.

[0012] In some embodiments, the guiding component further includes a second arc-shaped rail, with guide rails vertically mounted at adjacent ends of the first and second arc-shaped rails, and driven rollers mounted on the first arc-shaped rail, the second arc-shaped rail, and the guide rails.

[0013] Compared with the prior art, the beneficial effects of the present invention are as follows: 1. This invention uses a linear sliding mechanism in conjunction with a docking component installed at the end of the exhaust pipe. The linear sliding mechanism can drive the docking component to connect with the docking flange, and conversely, it can drive the docking component to separate from the docking flange. This effectively prevents personnel from lingering near the rocket's oxygen vent before launch, thus improving the safety of personnel in this position during rocket launch.

[0014] 2. This invention can effectively transmit the settling force of the rocket oxygen tank through the sealing and docking components in the docking parts. In conjunction with the lifting mechanism, it can effectively follow the changes in the rocket body's position and attitude caused by low temperature contraction. Attached Figure Description

[0015] The accompanying drawings, which are included to provide a further understanding of this application and form part of this application, illustrate exemplary embodiments and are used to explain this application, but do not constitute an undue limitation of this application. In the drawings: Figure 1 This is a front view structural diagram of the present invention; Figure 2 This is a schematic diagram of a half-section of the docking component of the present invention; Figure 3 This is a schematic diagram of the docking component of the present invention, which is a docking tapered tube structure; Figure 4 This is a schematic diagram of the docking component of the present invention, which consists of a docking tapered tube and a limiting flange structure; Figure 5 This is a schematic diagram of the structure of the docking component of the present invention, which consists of a docking tapered tube, a limiting flange, and a transmission rod. Figure 6 This is a schematic diagram of the structure for installing the first arc-shaped rail in Embodiment 2 of the present invention; Figure 7 This is a schematic diagram of the structure for installing the first and second arc-shaped rails according to Embodiment 2 of the present invention; Figure 8 This is a schematic diagram of the structure of the docking component after it is detached from the docking flange of the present invention.

[0016] In the picture: 1. Exhaust pipe; 2. Dating components; 21. Connecting pipe; 22. Mounting lug; 23. Seal; 231. Inner layer; 232. Outer layer; 233. Vent hole; 24. Connecting part; 24a. Connecting tapered tube; 24b. Limiting flange; 24c. Transfer rod; 3. Frame; 31. Support frame; 32. Base; 33. Linear sliding mechanism; 331. Slide rail; 332. Sliding block; 333. Driving component; 34. Lifting mechanism; 341. Lead screw; 342. Slider; 343. Electromagnetic clutch; 344. First power component; 4. Guide assembly; 41. First arc-shaped rail; 42. Drive roller; 43. Second power component; 44. Limiting ring; 45. Driven roller; 46. Second arc-shaped rail; 47. Guide rail; 5. Installation components; 6. Connecting flanges. Detailed Implementation

[0017] The following drawings will disclose several embodiments of the present invention. For clarity, many physical details will be described in the following description. However, it should be understood that these physical details are not intended to limit the invention. That is, in some embodiments of the invention, these physical details are not essential. Furthermore, for the sake of simplicity, some conventional structures and components will be shown in the drawings in a simple schematic manner.

[0018] Furthermore, in this invention, the use of terms such as "first" and "second" is for descriptive purposes only and does not specifically refer to any order or sequence, nor is it intended to limit the invention. They are merely used to distinguish components or operations described using the same technical terms, and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Therefore, a feature defined with "first" or "second" may explicitly or implicitly include at least one of those features. Additionally, the technical solutions of various embodiments can be combined with each other, but only if they are feasible for those skilled in the art. If a combination of technical solutions is contradictory or impossible to implement, such a combination should be considered nonexistent and not within the scope of protection claimed by this invention.

[0019] Example 1: Please see Figures 1-5 The rocket oxygen tank exhaust pipe docking auxiliary device of the present invention includes: The docking flange 6 is installed on the rocket oxygen tank, and the oxygen vent on the rocket oxygen tank is installed in the center of the docking flange 6; The frame 3 includes a support frame 31, a base 32, and a linear sliding mechanism 33. The linear sliding mechanism 33 is mounted on the support frame 31, and the support frame 31 is mounted on the base 32 via a lifting mechanism 34. The docking component 2 includes a connecting pipe 21 fixedly installed at the end of the exhaust pipe 1. The end of the connecting pipe 21 near the docking flange 6 is provided with a sealing element 23 and a docking element 24. The linear sliding mechanism 33 is connected to the docking component 2 via the mounting component 5.

[0020] The sealing element 23 is a conical sleeve, which includes an inner layer 231 and an outer layer 232. A venting cavity is provided between the inner layer 231 and the outer layer 232. Vent holes 233 are evenly provided on the outer edge of the inner layer 231. An air injection pipe is connected to the venting cavity. Both the inner layer 231 and the outer layer 232 are made of flexible materials.

[0021] The sealing element 23 has a docking element 24 inside, which is used to transmit the settling force of the rocket oxygen tank. The docking elements 24 are all connected to the docking flange 6 through the linear movement of the linear sliding mechanism 33.

[0022] Working principle: S1. When in use, the connecting pipe 21 at the end of the exhaust pipe 1 is installed on the linear sliding mechanism 33 through the mounting part 5; S2. Then the linear sliding mechanism 33 is activated, so that the docking component 2 carrying the exhaust pipe 1 approaches the docking flange 6. The seal 23 in the docking component 2 will be fastened to the flange and folded outward under the pressure of the linear sliding mechanism 33. At this time, the vent 233 located on the edge of the seal 23 will be exposed, and the inner layer 231 of the seal 23 will be effectively attached to the periphery of the docking flange 6 under the folding of the seal 23. At the same time, the docking component 24 will be connected to the docking flange 6. S3. During the oxygen filling process in the rocket oxygen tank, sedimentation will occur. The sedimentation force of the rocket oxygen tank will be transmitted to the linear sliding mechanism 33 and the support frame 31 through the docking part 24 and the connecting pipe 21. When the lifting mechanism 34 on the frame 3 is under force, the support frame 31 will descend synchronously with the sedimentation of the rocket oxygen tank. S31. When releasing gas through the oxygen vent, an inert gas, such as nitrogen, will be injected between the inner layer 231 and the outer layer 232 of the seal 23. The inert gas will be discharged through the vent 233 on the edge of the seal 23. If the seal 23 is not completely sealed, the oxygen will mix with the inert gas to form a harmless gas. Furthermore, injecting gas between the inner layer 231 and the outer layer 232 of the seal 23 can further apply pressure to the bend of the inner layer 231, thereby further ensuring its sealing performance. S4. Before launch, the activation of the linear sliding mechanism 33 can disengage the sealing component 23 and the docking component 24 from the docking flange 6, that is, the docking component 2 on the exhaust pipe 1 is automatically separated from the docking flange 6, thereby avoiding personnel from staying near the rocket's oxygen exhaust port before launch and effectively improving the safety of personnel in this position during rocket launch.

[0023] The docking component 24 includes a docking cone tube 24a, which is fixedly installed on the connecting pipe 21 and embedded in the center of the inner layer 231. The maximum diameter of the docking cone tube 24a is greater than the diameter of the docking flange 6. When connected to the docking flange 6, the docking cone tube 24a transmits the settling force of the rocket oxygen tank by fastening it to the docking flange 6. The docking component 24 includes a limiting flange 24b, which is fixedly connected to the end of the connecting pipe 21 and is adapted to the inner diameter of the docking flange 6. Alternatively, the docking component 24 may also include the aforementioned docking tapered pipe 24a. When connected to the docking flange 6, the settling force of the rocket oxygen tank is transmitted through the limiting flange 24b inserted into the docking flange 6, or in conjunction with the docking tapered pipe 24a, the settling force of the rocket oxygen tank is transmitted. The docking component 24 includes several transmission rods 24c, all of which are fixedly connected to the connecting pipe 21. The docking flange 6 has several docking holes corresponding to the transmission rods 24c for insertion. The docking component 24 may also include one or all of the docking cone tube 24a and the limiting flange 24b. When connected to the docking flange 6, the transmission rods 24c inserted into the docking holes on the docking flange 6 mainly transmit the settling force of the rocket oxygen tank, or cooperate with the docking cone tube 24a and the limiting flange 24b to transmit the settling force of the rocket oxygen tank.

[0024] The linear sliding mechanism 33 includes a slide rail 331, a sliding block 332, and a driving component 333 for driving the sliding block 332 to move on the slide rail 331. The motor can be an electric telescopic rod, a telescopic cylinder, or a hydraulic cylinder, etc. The mounting component 5 is mounted on the sliding block 332, and the connecting pipe 21 in the docking component 2 is detachably connected to the sliding block 332 through the mounting component 5. In this embodiment, the mounting component 5 can be a clamp, and the connecting pipe 21 of the docking component 2 is fixedly connected with a mounting ear 22 that is compatible with the mounting component 5; or the connecting pipe 21 is provided with a slot for limiting the clamp. In this embodiment, the lifting mechanism 34 includes a lead screw 341, a slider 342, and a first power component 344 that drives the lead screw 341 to rotate. The output shaft of the first power component 344 is connected to the lead screw 341 through an electromagnetic clutch 343. The bottom of the base 32 is fixedly connected to the slider 342. The slider 342 carries the base 32 to rise and fall by rotating the lead screw 341. After the docking component 2 is connected to the docking flange 6, the electromagnetic clutch 343 is closed, thereby releasing the restriction on the height of the base 32. That is, when the docking component 2 is subjected to the settling force of the rocket oxygen tank, the exhaust pipe 1, the docking component 2, and the base 32 can all move accordingly. The lifting mechanism 34 can be a cylinder, a hydraulic cylinder, or other structures, as long as it can adjust the height of the base 32 before docking with the docking component 2 and remove the height restriction on the base 32 after docking with the docking component 2, so that the base 32 can automatically follow the rocket oxygen tank to sink.

[0025] Example 2: Please see Figures 6-8 As a further improvement to Embodiment 1, the embodiment also includes a guide component 4, which includes a first arc-shaped rail 41. The first arc-shaped rail 41 is installed on the side of the frame 3 away from the rocket oxygen tank. The radius of the first arc-shaped rail 41 is adapted to the radius of the exhaust pipe 1 to ensure that the exhaust pipe 1 can be effectively guided upward from the ground. A limiting ring 44 adapted to the diameter of the exhaust pipe 1 is installed on the first arc-shaped rail 41. The exhaust pipe 1 is arranged in an arc shape between the first arc-shaped rail 41 and the base 32. The diameter of the limiting ring 44 is larger than the diameter of the exhaust pipe 1. The first arc-shaped rail 41 is equipped with a drive roller 42 adapted to the exhaust pipe 1 and a second power component 43 adapted to it. The drive roller 42 is driven by the second power component 43. The limiting ring 44 can be a clamp, such as a linear clamp or a U-shaped clamp; In this embodiment: S1: After partially placing the exhaust pipe 1 on the drive roller 42 of the guide assembly 4, the limiting ring 44 is then installed on the exhaust pipe 1; S2: The second power component 43 is activated, thereby driving the exhaust pipe 1 to move along the trajectory of the first arc-shaped rail 41, which enables the end of the exhaust pipe 1 where the docking component 2 is installed to be pushed upward. When the manual moves the docking component 2 on the exhaust pipe 1 to the linear sliding mechanism 33, the guide component 4 can assist in making it easier for the manual to lift the exhaust pipe 1 upward. S3: After the docking component 2 is installed on the linear sliding mechanism 33, the height of the docking component 2 is further raised by the start of the lifting mechanism 34, so that the docking component 2 and the docking flange 6 are on the moving axis of the linear sliding mechanism 33. S4: When docking component 2 and base 32 descend synchronously with the rocket oxygen tank, or when docking component 2 separates from docking flange 6, the initial position of exhaust pipe 1 located behind docking component 2 will change. Because the exhaust pipe 1 between the first arc-shaped rail 41 and base 32 is arc-shaped, the initial position of exhaust pipe 1 behind docking component 2 will change, causing the arc curvature of this section of exhaust pipe 1 to change. Compared to other arrangements of the exhaust pipe 1, this arrangement avoids changes in the initial position of the exhaust pipe 1 after docking with the component 2, which could cause the exhaust pipe 1 to retract or swing under force. This ensures the stability of the trajectory of the exhaust pipe 1 during the synchronous descent of the rocket oxygen tank, further improving the safety of its use.

[0026] Furthermore, a second arc-shaped rail 46 is installed at one end of the base 32 near the first annular rail. Guide rails 47 are vertically installed at the adjacent ends of the first arc-shaped rail 41 and the second arc-shaped rail 46. Driven rollers 45 are installed on the first arc-shaped rail 41, the second arc-shaped rail 46, and the guide rail 47. This can further guide the movement trajectory of the exhaust pipe 1 carrying the docking component 2 to the linear sliding mechanism 33.

[0027] Both the first power component 344 and the second power component 43 are electric motors; The driving roller and driven roller 45 can be V-shaped rollers.

[0028] The above are merely embodiments of the present invention and are not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principle of the present invention should be included within the scope of the claims of the present invention.

Claims

1. A rocket oxygen tank exhaust pipe docking auxiliary device, characterized in that, include: A docking flange (6) is installed on the rocket oxygen tank, and the oxygen vent on the rocket oxygen tank is installed in the center of the docking flange (6); The frame (3) includes a support frame (31), a base (32), and a linear sliding mechanism (33). The linear sliding mechanism (33) is mounted on the support frame (31), and the support frame (31) is mounted on the base (32) via a lifting mechanism (34). The docking component (2) includes a connecting pipe (21) fixedly installed at the end of the exhaust pipe (1), and the end of the connecting pipe (21) near the docking flange (6) is provided with a sealing element (23) and a docking element (24). The linear sliding mechanism (33) is connected to the docking component (2) via the mounting component (5).

2. The rocket oxygen tank exhaust pipe docking auxiliary device according to claim 1, characterized in that: The sealing element (23) is a conical sleeve, which includes an inner layer (231) and an outer layer (232). A venting cavity is provided between the inner layer (231) and the outer layer (232). Vent holes (233) are uniformly provided on the outer edge of the inner layer (231). An air injection pipe is connected to the venting cavity. Both the inner layer (231) and the outer layer (232) are made of flexible materials.

3. The rocket oxygen tank exhaust pipe docking auxiliary device according to claim 2, characterized in that: The seal (23) has a docking part (24) inside, which is used to transmit the settling force of the rocket oxygen tank.

4. The rocket oxygen tank exhaust pipe docking auxiliary device according to claim 3, characterized in that: The docking component (24) includes, The connecting tapered tube (24a) is fixedly installed on the connecting tube (21) and embedded in the center of the inner layer (231), and the maximum diameter of the connecting tapered tube (24a) is greater than the diameter of the connecting flange (6); and / or a limiting flange (24b), which is fixedly connected to the end of the connecting pipe (21) and is adapted to the inner diameter of the mating flange (6); And / or transfer rods (24c), a plurality of the transfer rods (24c) are fixedly connected to the connecting pipe (21), and a plurality of mating holes for inserting the transfer rods (24c) are provided on the mating flange (6) corresponding to the transfer rods (24c).

5. The rocket oxygen tank exhaust pipe docking auxiliary device according to claim 1, characterized in that: The linear sliding mechanism (33) includes a slide rail (331), a sliding block (332), and a driving member (333) for driving the sliding block (332) to move on the slide rail (331). The mounting member (5) is mounted on the sliding block (332), and the connecting pipe (21) in the docking component (2) is detachably connected to the sliding block (332) through the mounting member (5).

6. The rocket oxygen tank exhaust pipe docking auxiliary device according to claim 1, characterized in that: The lifting mechanism (34) includes a lead screw (341), a slider (342), and a first power component (344) that drives the lead screw (341) to rotate. The output shaft of the first power component (344) is connected to the lead screw (341) through an electromagnetic clutch (343). The bottom of the base (32) is fixedly connected to the slider (342). The slider (342) carries the base (32) to lift and lower by rotating the lead screw (341).

7. A rocket oxygen tank exhaust pipe docking auxiliary device according to any one of claims 1-4, characterized in that: It also includes a guide component (4), which includes a first arc-shaped rail (41). The first arc-shaped rail (41) is installed on the side of the frame (3) away from the rocket oxygen tank. A limiting ring (44) adapted to the diameter of the exhaust pipe (1) is installed on the first arc-shaped rail (41). The exhaust pipe (1) between the first arc-shaped rail (41) and the base (32) is arc-shaped. The diameter of the limiting ring (44) is larger than the diameter of the exhaust pipe (1).

8. The rocket oxygen tank exhaust pipe docking auxiliary device according to claim 7, characterized in that: The first arc-shaped rail (41) is equipped with a drive roller (42) adapted to the exhaust pipe (1) and a second power component (43) adapted to the exhaust pipe (1).

9. The rocket oxygen tank exhaust pipe docking auxiliary device according to claim 8, characterized in that: The guide assembly (4) further includes a second arc-shaped rail (46), and guide rails (47) are vertically installed at the adjacent ends of the first arc-shaped rail (41) and the second arc-shaped rail (46). Driven rollers (45) are installed on the first arc-shaped rail (41), the second arc-shaped rail (46), and the guide rails (47).

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