Liquid rocket traction release device

Abstract

The invention discloses a liquid rocket traction releasing device which comprises a fixing structure, a pressing device and a first rotating shaft, the fixing structure and the pressing device are connected through the first rotating shaft, the bottom of the fixing structure is fixedly connected with a launching platform, and a first containing space is formed in the top of the fixing structure. The upper portion of the pressing device abuts against the rocket foot to lock the rocket foot, the lower portion of the pressing device can rotate in the circumferential direction of the surface of the first rotating shaft, the weight of the side, close to the rocket foot, of the pressing device is smaller than that of the side, away from the rocket foot, of the pressing device, and the pressing device comprises a pressing head, a connecting assembly and a first driving device. The upper end of the pressing head is used for abutting against a rocket foot, the lower end of the side, away from the rocket foot, of the pressing head is connected with the output end of the connecting assembly, and the input end of the connecting assembly is connected with the output end of the first driving device. According to the device, a control system can be simplified, the structural safety and reliability are improved, and meanwhile the cost is greatly saved.

Description

Technical Field

[0001] The present invention relates to the field of aerospace technology, and in particular to a liquid rocket traction and release device. Background Art

[0002] With the rapid development of the aerospace industry, various technologies involved in the rocket field have also achieved rapid progress. To carry more payloads into space, large launch vehicles are required. To increase thrust, large launch vehicles often use multiple engines arranged side by side. To ensure the safe flight of the rocket, a tow release device is required. After the rocket is ignited, the tow release device must ensure that all engines are properly started before the rocket is released. Therefore, after ignition, the rocket body must be restrained. After confirming that all engines are in normal operation, the restraint mechanism is opened to ensure the safe flight of the rocket. Therefore, rocket restraint release technology is crucial. Currently, domestic restraint release mechanisms all use at least two actuator cylinder systems to control the restraint and reverse functions. This results in a large restraint release mechanism and a complex hydraulic system, which brings inconvenience to the operator when installing it. Furthermore, the entire device is complex to operate, increasing the probability of error and significantly increasing construction costs.

[0003] There is an urgent need to provide a liquid rocket traction release device that can simplify the control system, facilitate installation and operation, improve structural safety and reliability, and greatly save costs. Summary of the Invention

[0004] The present invention aims to provide a liquid rocket traction release device that simplifies the control system, facilitates installation and operation, improves structural safety and reliability, significantly reduces costs, and lays the foundation for the safe launch of the rocket.

[0005] In order to achieve the above object, the technical solution adopted by the present invention is as follows: One aspect of the present invention provides a liquid rocket traction and release device, comprising a plurality of traction and release mechanisms arranged on the surface of a launch platform and used to lock the rocket's arrow foot, each of the traction and release mechanisms comprising at least a fixed structure, a clamping device and a first rotating shaft, the fixed structure and the clamping device being connected via the first rotating shaft, the bottom of the fixed structure being fixedly connected to the launch platform, and the top being provided with a first accommodating space for accommodating the clamping device, the upper portion of the clamping device being in contact with the rocket's arrow foot to lock the rocket's arrow foot, and the lower portion being rotatable circumferentially along the surface of the first rotating shaft, The weight of the pressing device close to the rocket foot is less than the weight of the pressing device away from the rocket foot. The clamping device includes a pressure head, a connecting assembly, a first drive device, a second rotating shaft and a first shell containing a second accommodating space. The pressure head, the connecting assembly and the first drive device are all located inside the second accommodating space. The upper end of the pressure head is used to abut against the rocket foot. The lower end of the pressure head close to the rocket foot is fixed in the first shell through the second rotating shaft, and the pressure head can rotate circumferentially along the surface of the second rotating shaft. The lower end of the pressure head away from the rocket foot is connected to the output end of the connecting assembly, and the input end of the connecting assembly is connected to the output end of the first drive device. The first driving device contracts in a direction perpendicular to the rocket axis to drive the connecting assembly to drive the lower end of the pressing head to rotate along the second rotating axis, thereby driving the upper end of the pressing head to move away from the rocket foot, so that the entire clamping device rotates circumferentially along the first rotating axis and then falls into the first accommodating space, completing the release of the rocket foot.

[0006] Furthermore, the fixed structure includes a second shell and a second driving device, the second shell includes a first containment shell containing a first activity space and a second containment shell containing a second activity space, the second containment shell is located at the upper part of the first containment shell away from the rocket foot, wherein the lower part of the first containment shell is used to be fixedly connected to the launch platform, the upper part of the first containment shell is connected to the lower part of the second containment shell, the upper part of the second containment shell extends away from the first containment shell, and the first activity space and the second activity space are interconnected to form the first accommodation space.

[0007] Furthermore, a locking opening and a locking mechanism are provided on the outer wall of the first containment shell on the side away from the rocket foot, and the locking mechanism includes the third rotating shaft and a locking member. One end of the locking member is fixed to the first containment shell through the third rotating shaft and can rotate circumferentially along the third rotating shaft, and the other end of the locking member is used to pass through the locking opening and then abut against the pressing device to fix the pressing device in the first accommodation space.

[0008] Furthermore, a horizontal sliding guide groove is provided at one end of the second containment shell away from the first containment shell, one end of the horizontal sliding guide groove is a closed structure, and the other end is an open structure, and the opening of the open structure faces the side of the rocket foot.

[0009] Furthermore, the second driving device is located in the first receiving shell, and one end of the second driving device is fixedly connected to the first receiving shell through a fourth rotating shaft, and the other end is used to abut against the bottom of the first shell to drive the first shell to rotate circumferentially along the first rotating shaft.

[0010] Furthermore, the second driving device includes a hydraulic cylinder and a support member, the telescopic end of the hydraulic cylinder is connected to the support member through a fifth rotating axis, and the support member can rotate along the surface of the fifth rotating axis, wherein the shape of the support member is an obtuse triangle, the obtuse end is connected to the telescopic end of the hydraulic cylinder, the first acute end corresponding to the long side is used to abut the outer wall of the bottom of the first shell, and the second acute end corresponding to the short side is fixed to the side wall of the first containment shell through the sixth rotating axis.

[0011] Furthermore, the shape of the pressure head is roughly L-shaped, wherein the upper part of the end where the pressure head abuts the rocket foot is an upward convex curved surface, and two rotating holes are provided at the end of the pressure head away from the rocket foot, and an upper recess is provided at the position of the pressure head located between the two rotating holes.

[0012] Further, the connecting assembly includes a first connecting member, a second connecting member, a third connecting member, a fourth connecting member, a seventh rotating shaft, an eighth rotating shaft, a ninth rotating shaft, a tenth rotating shaft, an eleventh rotating shaft and a twelfth rotating shaft, wherein the output end of the first connecting member is connected to the pressure head through the seventh rotating shaft, the input end of the first connecting member is connected to the output end of the second connecting member through the eighth rotating shaft, the fixed end of the second connecting member is connected to the first shell through the ninth rotating shaft, the input end of the second connecting member is connected to the output end of the third connecting member through the tenth rotating shaft, the input end of the third connecting member is connected to the output end of the fourth connecting member through the eleventh rotating shaft, the input end of the fourth connecting member is connected to the output end of the first driving device through the twelfth rotating shaft, and the first driving device is a hydraulic cylinder structure, and the hydraulic cylinder structure fixes the hydraulic cylinder in the first shell through a fixing block.

[0013] Furthermore, the first shell is a closed structure with an opening at one end. The first shell is provided with a first boss for supporting the rocket foot at the open end on one side close to the rocket foot; A heat shield is provided on a side of the first boss away from the rocket foot, and the heat shield is arranged between the first boss and the pressure head. One end of the heat shield is connected to the first boss through a thirteenth rotation axis, and the other end of the heat shield extends away from the first shell and tilts toward the pressure head. A second boss is provided on one end of the first shell close to the rocket foot and away from the opening end, and the second boss is provided with a rotation hole; A U-shaped curved surface concave toward the center of the first shell is provided on a side of the first shell close to the rocket foot; The side wall of the first shell on the side away from the rocket foot transitions to the open end to form a curved inclined surface; A protrusion is provided on the side wall of the first shell away from the rocket foot and close to the curved inclined surface end; The first shell is provided with a slideway for moving the fourth connecting member; Furthermore, the fourth connecting member includes a slider and a boss component located on the upper and lower sides of the slider and extending away from each other, the boss component includes an upper boss assembly and a lower boss assembly, the upper boss assembly includes two symmetrically arranged upper protrusions, and the two upper protrusions are connected to the third connecting member through the eleventh rotating axis, and the lower boss assembly includes two symmetrically arranged lower protrusions, and the two lower protrusions are connected to the first driving device through the twelfth rotating axis.

[0014] Furthermore, symmetrical double-row pulleys are provided on both sides of the slider, and the double-row pulleys can move along the slide. The pulleys on both sides of the double-row pulleys close to the rocket arrow foot are connected through a first connecting shaft, and the pulleys on both sides of the double-row pulleys away from the rocket arrow foot are connected through a second connecting shaft. The extended dimensions at both ends of the second connecting shaft are larger than the extended dimensions at both ends of the first connecting shaft, wherein the two ends of the second connecting shaft are located on the horizontal sliding guide groove on the fixed structure and can move freely along the horizontal sliding guide groove.

[0015] A liquid rocket traction and release device provided in an embodiment of the present invention includes multiple traction and release mechanisms arranged on the surface of a launch platform and used to lock the rocket legs. Each of the traction and release mechanisms is composed of a fixed structure, a clamping device and a first rotating shaft.

[0016] During use, the first drive device contracts in a direction perpendicular to the rocket axis, driving the connecting assembly to cause the lower end of the pressing head to rotate along the second rotation axis, thereby causing the upper end of the pressing head to move away from the rocket leg. Because the weight of the side of the pressing device closer to the rocket leg is less than the weight of the side of the pressing device farther away from the rocket leg, the entire pressing device rotates circumferentially along the first rotation axis and then falls into the first accommodating space, completing the release of the rocket leg.

[0017] The entire liquid rocket traction release device successfully completes the opening and retraction of the traction release device through a set of drive devices and clever use of the uneven weight at both ends of the clamping device. It can simplify the control system, facilitate installation and operation, improve structural safety and reliability, and greatly save costs, laying the foundation for the safe takeoff of the rocket.

[0018] It should be understood that the foregoing general description and the following detailed description are merely exemplary and illustrative and are not intended to limit the scope of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 This is a schematic structural diagram of the liquid rocket traction release device and rocket foot of the present invention; Figure 2 It is a cross-sectional schematic diagram of the liquid rocket traction release device of the present invention; Figure 3 This is a schematic diagram of the structure of the liquid rocket traction release device of the present invention falling back; Figure 4 It is a structural schematic diagram of the pressing device of the present invention; Figure 5 is a structural schematic diagram of the first shell of the present invention; Figure 6 It is a structural schematic diagram of the fixed structure of the present invention; Figure 7 This is a front view of the fourth connecting member and the double pulley of the present invention; Figure 8 is a top view of the fourth connecting member and the double pulley of the present invention; Figure 9 Schematic diagram of the relative positions of the fourth link, the horizontal sliding guide groove, and the slideway when the traction release device of the present invention locks the rocket leg; Figure 10 Schematic diagram of the relative positions of the fourth link, the horizontal sliding guide groove and the slideway when the traction release device of the present invention is opened and reversed; Figure 11 It is a schematic structural diagram of the fourth linking member, the horizontal sliding guide groove and the slideway when the traction release device of the present invention locks the rocket leg; Figure 12 2. It is a schematic structural diagram of the fourth link, the horizontal sliding guide groove and the slideway when the traction release device of the present invention is opened and reversed; Figure 13 is a top view of the first shell of the present invention; Figure 14 It is a top view of the heat shield of the present invention abutting against the first shell.

[0020] Reference numerals: 1 rocket foot 2 fixed structure 3 Clamping device 4 First rotating axis 5 first accommodation space 6 pressure head 7 connecting component 8 first drive device 9 Second rotating shaft 10 First housing 11 second accommodating space 12 second housing 13 second driving device 14 first receiving shell 15 Second housing 16 Locking port 17 locking mechanism 18 third rotation axis 19 locking member 20 horizontal sliding guide groove 21 fourth rotating shaft 22 hydraulic cylinder 23 support member 24 fifth rotation axis 25 sixth rotation axis 26 first connecting member 27 second connecting piece 28 third connecting piece 29 fourth connecting member 30 seventh rotation axis 31 eighth rotation axis 32 ninth rotation axis 33 tenth rotation axis 34 eleventh rotation axis 35 twelfth rotation axis 36 first boss 37 slideway 38 upper boss assembly 39 lower boss assembly 40 double-row pulley 41 first connecting shaft 42 second connecting shaft 43 heat shield 44 second boss DETAILED DESCRIPTION

[0021] In order to make the purpose, technical solutions and advantages of the present invention more clearly understood, the present invention will be further described in detail below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not intended to limit the present invention.

[0022] It should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like, indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention or simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0023] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of the technical features being referred to. Thus, a feature identified as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of the present invention, "plurality" means two or more, unless otherwise specifically defined.

[0024] The word “exemplary” is used exclusively herein to mean “serving as an example, example, or illustration.” Any embodiment described herein as “exemplary” is not necessarily to be construed as preferred or advantageous over other embodiments.

[0025] In addition, numerous specific details are provided in the detailed description below to better illustrate the present application. Those skilled in the art will appreciate that the present application can be practiced without certain specific details. In some instances, methods, means, components, and circuits well known to those skilled in the art are not described in detail in order to highlight the main purpose of the present application.

[0026] like Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 5 and Figure 6 As shown, the present invention provides a liquid rocket traction and release device, comprising a plurality of traction and release mechanisms disposed on the surface of a launch platform and used to lock a rocket leg 1. Each traction and release mechanism comprises at least a fixed structure 2, a clamping device 3, and a first rotating shaft 4. The fixed structure 2 and the clamping device 3 are connected via the first rotating shaft 4. The bottom of the fixed structure 2 is fixedly connected to the launch platform, and a first accommodating space 5 for accommodating the clamping device 3 is provided on the top. The upper portion of the clamping device 3 abuts against the rocket leg 1 to lock the rocket leg 1, and the lower portion can rotate circumferentially along the surface of the first rotating shaft 4.

[0027] The weight of the pressing device 3 on the side close to the rocket foot 1 is less than the weight of the pressing device 3 on the side away from the rocket foot 1.

[0028] The clamping device 3 includes a pressing head 6, a connecting assembly 7, a first driving device 8, a second rotating shaft 9 and a first shell 10 containing a second accommodating space 11. The pressing head 6, the connecting assembly 7 and the first driving device 8 are all located inside the second accommodating space 11. The upper end of the pressing head 6 is used to abut against the rocket foot 1. The lower end of the pressing head 6 close to the rocket foot 1 is fixed in the first shell 10 through the second rotating shaft 9, and the pressing head 6 can rotate circumferentially along the surface of the second rotating shaft 9. The lower end of the pressing head 6 away from the rocket foot 1 is connected to the output end of the connecting assembly 7, and the input end of the connecting assembly 7 is connected to the output end of the first driving device 8.

[0029] The first driving device 8 contracts in a direction perpendicular to the rocket axis to drive the connecting assembly 7 to drive the lower end of the pressing head 6 to rotate along the second rotating axis 9, thereby driving the upper end of the pressing head 6 to move away from the rocket foot 1, so that the entire clamping device 3 rotates circumferentially along the first rotating axis 4 and then falls into the first accommodating space 5, completing the release of the rocket foot.

[0030] Specifically, the present invention provides a liquid rocket traction release device, which includes multiple traction release mechanisms disposed on the launch platform surface and used to lock the rocket legs 1. Each traction release mechanism is composed of a fixing structure 2, a clamping device 3, and a first rotating shaft 4.

[0031] During use, the first driving device 8 contracts in a direction perpendicular to the rocket axis, driving the connecting assembly 7 to drive the lower end of the pressing head 6 to rotate along the second rotation axis 9, thereby driving the upper end of the pressing head 6 to move away from the rocket leg 1. Since the weight of the side of the pressing device 3 close to the rocket leg 1 is less than the weight of the side of the pressing device 3 away from the rocket leg 1, the entire pressing device 3 rotates circumferentially along the first rotation axis 4 and falls into the first accommodating space 5, completing the release of the rocket leg 1.

[0032] The entire liquid rocket traction release device smoothly completes the opening and backward retraction of the traction release device through a set of driving devices and clever use of the uneven weight at both ends of the clamping device 3. It can simplify the control system, facilitate installation and operation, improve structural safety and reliability, and greatly save costs, laying the foundation for the safe takeoff of the rocket.

[0033] It should be pointed out that the fixed structure 2 includes a second shell 12 and a second driving device 13. In order to increase the activity space of the clamping device 3 and facilitate the rapid backward movement of the clamping device 3, for example, the second shell 12 includes a first containing shell 14 containing a first activity space and a second containing shell 15 containing a second activity space, and the second containing shell 15 is located at the upper part of the first containing shell 14 away from the rocket foot 1, wherein the lower part of the first containing shell 14 is used to be fixedly connected to the launch platform, the upper part of the first containing shell 14 is connected to the lower part of the second containing shell 15, and the upper part of the second containing shell 15 extends toward the side away from the first containing shell 14, and the first activity space and the second activity space are interconnected to form a first accommodating space 5.

[0034] In this embodiment, when the clamping device 3 is tilted back (after the first shell 10 is located in the second shell 12), in order to effectively fix the first shell 10 and prevent the first shell 10 from shaking, for example, the outer wall of the first containment shell 14 on the side away from the rocket foot 1 is provided with a locking opening 16 and a locking mechanism 17. The locking mechanism 17 includes a third rotating shaft 18 and a locking member 19. One end of the locking member 19 is fixed to the first containment shell 14 through the third rotating shaft 18 and can rotate circumferentially along the third rotating shaft 18. The other end of the locking member 19 is used to pass through the locking opening 16 and then abut against the clamping device 3 (abutting against the outer surface of the first shell 10) to fix the clamping device 3 in the first accommodating space 5. In order to make the clamping device 3 more firmly fixed, for example, a protrusion is provided on the first shell 10 of the clamping device 3 that matches one end of the locking member 19 (a protrusion is provided on the side wall of the first shell 10 on the side away from the rocket leg 1 and near the curved inclined surface end). After one end of the locking member 19 passes through the locking opening 16, it is tightly attached to the end face of the protrusion on the side away from the second shell 12, and the clamping device 3 is fixed in the first accommodating space 5. When the clamping device 3 is required to clamp the rocket leg 1, the locking member 19 is manually opened to separate the locking member 19 from the protrusion. In this embodiment, the locking member 19 has an L-shaped structure.

[0035] In addition, to facilitate the movement of the clamping device 3 and the fixation of the clamping device 3 to the rocket leg 1, for example, the second driving device 13 includes a hydraulic cylinder 22 and a support member 23. The telescopic end of the hydraulic cylinder 22 is connected to the support member 23 via a fifth rotation axis 24, and the support member 23 can rotate along the surface of the fifth rotation axis 24. The support member 23 has an obtuse triangle shape, with the obtuse end connected to the telescopic end of the hydraulic cylinder 22. The first acute end corresponding to the long side is used to abut the outer wall of the bottom of the first shell 10, and the second acute end corresponding to the short side is fixed to the side wall of the first receiving shell 14 via a sixth rotation axis 25.

[0036] In the same embodiment, the second driving device 13 is located in the first receiving shell 14, and one end of the second driving device 13 is fixedly connected to the first receiving shell 14 through the fourth rotating shaft 21, and the other end is used to abut against the bottom of the first shell 14 to drive the first shell 14 to rotate circumferentially along the first rotating shaft 4.

[0037] In addition, in order to facilitate the fourth connecting member 29 to support the first shell 10 through the horizontal sliding guide groove, for example, a horizontal sliding guide groove 20 is provided at one end of the second containment shell 15 away from the first containment shell 14, and one end of the horizontal sliding guide groove 20 is a closed structure, and the other end is an open structure, and the opening of the open structure faces the side of the rocket foot 1.

[0038] During application, the telescopic end of the hydraulic cylinder 22 extends to drive the first acute-angle end corresponding to the long side of the support 23 to move toward the side of the first shell 10, so that the first acute-angle end corresponding to the long side is tightly attached to the first shell 10 and continues to apply pressure to the first shell 10, thereby causing the first shell 10 to rotate along the first rotation axis until the pressure head 6 abuts against the rocket foot 1, and the telescopic end of the first drive device 8 is extended to push the slider into the horizontal sliding guide groove 20 (the second connecting shaft at least abuts against the lower slide of the horizontal sliding guide groove), thereby realizing the reset of the restraint and release (locking the rocket foot).

[0039] It is further explained that, in order to facilitate the rotation of the pressure head 6, for example, the outer shape of the pressure head 6 is roughly L-shaped. In order to ensure the stability of the pressure head structure, for example, the thickness of the pressure head 6 close to the end of the rocket arrow foot 1 gradually increases toward the bent part of the pressure head 6. Further facilitate the abutment of the pressure head 6 with the rocket arrow foot 1 and improve the connection speed of the pressure head 6 with the rocket arrow foot 1. For example, the upper part of the abutment end of the pressure head 6 with the rocket arrow foot 1 is an upward convex curved surface. In order to facilitate the rotation of the pressure head 6 and reduce the weight of the pressure head at the same time, for example, the end of the pressure head 6 away from the rocket arrow foot 1 is provided with two rotation holes (for cooperating with the second rotation axis and the seventh rotation axis), and the position of the pressure head located between the two rotation holes is provided with an upper concave portion.

[0040] In the same embodiment, the connecting assembly 7 includes a first connecting member 26 , a second connecting member 27 , a third connecting member 28 , a fourth connecting member 29 , a seventh rotating shaft 30 , an eighth rotating shaft 31 , a ninth rotating shaft 32 , a tenth rotating shaft 33 , an eleventh rotating shaft 34 and a twelfth rotating shaft 35 . The output end of the first connecting member 26 is connected to the pressure head 6 via a seventh rotating shaft 30. The input end of the first connecting member 26 is connected to the output end of the second connecting member 27 via an eighth rotating shaft 31. The fixed end of the second connecting member 27 (similar to a convex-shaped member) is connected to the first housing 10 via a ninth rotating shaft 32. The input end of the second connecting member 27 is connected to the output end of the third connecting member 28 via a tenth rotating shaft 33. The input end of the third connecting member 28 is connected to the output end of the fourth connecting member 29 via an eleventh rotating shaft 34. The input end of the fourth connecting member 29 is connected to the output end of the first drive device 8 via a twelfth rotating shaft 35. The first drive device 8 is a hydraulic cylinder structure, which is fixed within the first housing 10 by a fixing block, and the hydraulic cylinder structure moves with the first housing 10. To ensure the structural stability of the fixing block, for example, the fixing block has a cube shape. It is respectively placed on the middle and rear portion of the hydraulic cylinder structure (the front portion of the telescopic part) and is fixed to the first housing with locking bolts.

[0041] In the same embodiment, in order to facilitate the connection between the rocket foot 1 and the pressure head 6 (the rocket foot 1 is provided with an inner recess matching the pressure head 6), for example, the first shell 10 is a closed structure with an opening at one end, and the first shell 10 is close to the side of the rocket foot 1 and is provided with a first boss 36 for supporting the rocket foot 1 at the open end.

[0042] like Figure 1 , Figure 2 and Figure 14 As shown, in order to prevent the components in the first shell 10 from being damaged by high temperature burning, for example, a heat shield 43 is provided on the side of the first boss 36 away from the rocket foot 1. The heat shield 43 is arranged between the first boss 36 and the pressure head 6. One end of the heat shield 43 is connected to the first boss 36 via the thirteenth rotation axis, and the other end of the heat shield 43 extends away from the first shell 10 and tilts toward the pressure head 6. When the first shell 10 falls backward, one end of the heat shield 43 rotates along the thirteenth rotation axis, so that the entire heat shield 43 covers the second accommodating space 11 (the part of the second accommodating space 11 close to the first boss), so that the upper part of the second accommodating space 11 forms a closed plate, isolating the high-temperature flame, and protecting the components in the second accommodating space 11, thereby reducing the damage of the components due to high temperature burning and ensuring the safe use of the fixing structure 2 and the clamping device 3.

[0043] In addition, a second boss 44 is provided on the first shell 10 at one end close to the rocket foot 1 and away from the opening end. The second boss 44 is provided with a rotation hole.

[0044] like Figure 1 and Figure 2 As shown, in order to reduce the weight of the first shell 10 and facilitate the rotation of the first shell 10, for example, the side of the first shell 10 close to the rocket foot 1 is provided with a U-shaped curved surface concave toward the center of the first shell 10, thereby achieving uneven weight on both sides of the first shell, that is, the weight of the side of the first shell 10 close to the rocket foot 1 is less than the weight of the side of the first shell 10 away from the rocket foot 1, which facilitates the rapid rotation of the first shell 10.

[0045] like Figure 3 , Figure 4 and Figure 5 As shown, to facilitate the rotation of the first housing 10 while conserving space within the second housing 12, for example, the sidewall of the first housing 10, facing away from the rocket foot 1, transitions to the open end to form a curved, inclined surface. This curved, inclined surface not only reduces the rotation radius of the first housing 10 but also significantly conserves space within the second housing 12, further facilitating its installation and removal.

[0046] like Figure 1 , Figure 7 , Figure 8 , Figure 9 , Figure 10 , Figure 11 , Figure 12 and Figure 13 As shown, the first housing 10 is provided with a slideway 37 for moving the fourth connecting member 29. The fourth connecting member 29 includes a slider and boss components located on the upper and lower sides of the slider and extending away from each other. The boss components include an upper boss assembly 38 and a lower boss assembly 39. The upper boss assembly 38 includes two symmetrically arranged upper bosses, which are connected to the third connecting member 28 via an eleventh rotation axis 41. The lower boss assembly 39 includes two symmetrically arranged lower bosses, which are connected to the first driving device 8 via a twelfth rotation axis 35.

[0047] It should be noted that symmetrical double-row pulleys 40 are provided on both sides of the slider, and the double-row pulleys 40 can move along the slide. The pulleys on both sides of the double-row pulleys 40 close to the rocket foot 1 are connected by a first connecting shaft 41, and the pulleys on both sides of the double-row pulleys away from the rocket foot 1 are connected by a second connecting shaft 42. The extension of the two ends of the second connecting shaft 42 is larger than the extension of the two ends of the first connecting shaft 41. The two ends of the second connecting shaft 42 are located on the horizontal sliding guide groove 20 on the fixed structure 2 and can move freely along the horizontal sliding guide groove 20. Along the movement direction of the slider, the center line of the horizontal sliding guide groove 20 coincides with the center line of the slide.

[0048] When in use, the telescopic end of the first driving device 8 contracts, driving the lower boss assembly 39 to move toward the side of the rocket arrow foot 1, thereby driving the double-row pulley fixedly connected to the slider to move simultaneously along the horizontal sliding guide groove 20 and the slide 37 (the pulley of the double-row pulley close to the rocket arrow foot 1 is located on the slide, and the pulley of the double-row pulley away from the rocket arrow foot is located on the slide, while the two ends of the second connecting shaft are located on the horizontal sliding guide groove). The upper slide length of the horizontal sliding guide groove 20 is greater than the lower slide length. When the double-row pulley slides, when the second connecting shaft 42 moves a distance exceeding the length of the lower slide, the lower slide of the horizontal sliding guide groove 20 unlocks the second connecting shaft 42 (the lower slide loses support for the second connecting shaft). Since the weight of the clamping device close to the rocket arrow foot 1 is less than the weight of the clamping device 3 away from the rocket arrow foot 1, the entire clamping device 3 rotates circumferentially along the first rotating axis 4 and falls into the first accommodating space 5, completing the release of the rocket arrow foot 1.

[0049] In addition, in order to ensure the structural stability of the upper convex body and the lower convex body, for example, the cross-section of the upper convex body and the lower convex body (such as Figure 2 The shape of the cut section is similar to a triangle.

[0050] The above embodiments can be combined with each other and have corresponding technical effects.

[0051] The above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principles of the present invention. These improvements and modifications should also be considered within the scope of protection of the present invention.

Claims

1. A liquid rocket traction release device, characterized in that: It comprises a plurality of traction and release mechanisms arranged on the surface of the launch platform and used to lock the rocket fins, each of the traction and release mechanisms at least comprises a fixed structure, a clamping device and a first rotating shaft, the fixed structure and the clamping device are connected through the first rotating shaft, the bottom of the fixed structure is fixedly connected to the launch platform, and the top is provided with a first accommodating space for accommodating the clamping device, the upper part of the clamping device abuts against the rocket fins to lock the rocket fins, and the lower part can rotate circumferentially along the surface of the first rotating shaft, The weight of the pressing device close to the rocket foot is less than the weight of the pressing device away from the rocket foot. The clamping device includes a pressure head, a connecting assembly, a first drive device, a second rotating shaft and a first shell containing a second accommodating space. The pressure head, the connecting assembly and the first drive device are all located inside the second accommodating space. The upper end of the pressure head is used to abut against the rocket foot. The lower end of the pressure head close to the rocket foot is fixed in the first shell through the second rotating shaft, and the pressure head can rotate circumferentially along the surface of the second rotating shaft. The lower end of the pressure head away from the rocket foot is connected to the output end of the connecting assembly, and the input end of the connecting assembly is connected to the output end of the first drive device. The first driving device contracts in a direction perpendicular to the rocket axis to drive the connecting assembly to drive the lower end of the pressing head to rotate along the second rotating axis, thereby driving the upper end of the pressing head to move away from the rocket foot, so that the entire clamping device rotates circumferentially along the first rotating axis and then falls into the first accommodating space, completing the release of the rocket foot.

2. The liquid rocket traction release device according to claim 1, characterized in that: The fixed structure includes a second shell and a second driving device, the second shell includes a first containing shell containing a first movable space and a second containing shell containing a second movable space, the second containing shell is located at the upper part of the first containing shell away from the rocket foot, wherein the lower part of the first containing shell is used to be fixedly connected to the launch platform, the upper part of the first containing shell is connected to the lower part of the second containing shell, the upper part of the second containing shell extends toward the side away from the first containing shell, and the first movable space and the second movable space are interconnected to form the first containing space.

3. The liquid rocket traction release device according to claim 2, characterized in that: A locking opening and a locking mechanism are provided on the outer wall of the first containment shell on a side away from the rocket foot. The locking mechanism includes a third rotating shaft and a locking piece. One end of the locking piece is fixed to the first containment shell through the third rotating shaft and can rotate circumferentially along the third rotating shaft. The other end of the locking piece is used to pass through the locking opening and then abut against the clamping device to fix the clamping device in the first accommodation space.

4. The liquid rocket traction release device according to claim 2, characterized in that: A horizontal sliding guide groove is provided at one end of the second containment shell away from the first containment shell, one end of the horizontal sliding guide groove is a closed structure, and the other end is an open structure, and the opening of the open structure faces the side of the rocket foot.

5. The liquid rocket traction release device according to claim 2, characterized in that: The second driving device is located in the first receiving shell, and one end of the second driving device is fixedly connected to the first receiving shell through the fourth rotating shaft, and the other end is used to abut against the bottom of the first shell to drive the first shell to rotate circumferentially along the first rotating shaft.

6. The liquid rocket traction release device according to claim 2, characterized in that: The second driving device includes a hydraulic cylinder and a support member, the telescopic end of the hydraulic cylinder is connected to the support member through a fifth rotating axis, and the support member can rotate along the surface of the fifth rotating axis, wherein the support member has an obtuse triangle shape, the obtuse end is connected to the telescopic end of the hydraulic cylinder, the first acute end corresponding to the long side is used to abut the outer wall of the bottom of the first shell, and the second acute end corresponding to the short side is fixed to the side wall of the first containing shell through the sixth rotating axis.

7. The liquid rocket traction release device according to claim 1, characterized in that: The shape of the pressure head is roughly L-shaped, wherein the upper part of the end where the pressure head abuts the rocket foot is an upward convex curved surface, and two rotating holes are provided at the end of the pressure head away from the rocket foot, and an upper recess is provided at the part of the pressure head located between the two rotating holes.

8. The liquid rocket traction release device according to claim 1, characterized in that: The connecting assembly includes a first connecting member, a second connecting member, a third connecting member, a fourth connecting member, a seventh rotating shaft, an eighth rotating shaft, a ninth rotating shaft, a tenth rotating shaft, an eleventh rotating shaft and a twelfth rotating shaft, wherein the output end of the first connecting member is connected to the pressure head through the seventh rotating shaft, the input end of the first connecting member is connected to the output end of the second connecting member through the eighth rotating shaft, the fixed end of the second connecting member is connected to the first shell through the ninth rotating shaft, the input end of the second connecting member is connected to the output end of the third connecting member through the tenth rotating shaft, the input end of the third connecting member is connected to the output end of the fourth connecting member through the eleventh rotating shaft, and the input end of the fourth connecting member is connected to the output end of the first driving device through the twelfth rotating shaft, and the first driving device is a hydraulic cylinder structure, and the hydraulic cylinder structure fixes the hydraulic cylinder in the first shell through a fixing block.

9. The liquid rocket traction release device according to claim 8, characterized in that: A U-shaped curved surface concave toward the center of the first shell is provided on the side of the first shell close to the rocket foot, and a slide for moving the fourth connecting member is provided on the first shell.

10. The liquid rocket traction release device according to claim 9, characterized in that: The fourth connecting member includes a slider and a boss component located on the upper and lower sides of the slider and extending away from each other, the boss component includes an upper boss assembly and a lower boss assembly, the upper boss assembly includes two symmetrically arranged upper bosses, and the two upper bosses are connected to the third connecting member through the eleventh rotation axis, the lower boss assembly includes two symmetrically arranged lower bosses, and the two lower bosses are connected to the first driving device through the twelfth rotation axis, symmetrical double-row pulleys are provided on both sides of the slider, and the double-row pulleys can move along the slide, the double-row pulleys close to the pulleys on both sides of the rocket arrow foot are connected through the first connecting shaft, and the double-row pulleys away from the pulleys on both sides of the rocket arrow foot are connected through the second connecting shaft, the extended size at both ends of the second connecting shaft is larger than the extended size at both ends of the first connecting shaft, wherein the two ends of the second connecting shaft are located on the horizontal sliding guide groove on the fixed structure and can move freely along the horizontal sliding guide groove.

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