A stainless steel rocket second stage zero-second drop refueling connector

Abstract

The present invention discloses a zero-second drop-off refueling connector based on a stainless steel rocket stage, and relates to the field of aerospace technology. The zero-second drop-off refueling connector based on a stainless steel rocket stage comprises an upper panel installed on a cryogenic rocket and a ground panel used to dock with the upper panel before the cryogenic rocket is erected, a standard flange is installed on the ground panel, and the standard flange is connected to the ground through a metal hose; before the cryogenic rocket takes off, the upper panel is locked with the ground panel through a locking device, and a traction rope is provided on the ground panel to unlock the locking device when the cryogenic rocket takes off, and the end of the traction rope away from the locking device is fixedly connected to the launch tower, which solves the problem of low reliability of the current zero-second drop mode.

Description

Technical Field

[0001] The invention relates to the field of aerospace technology, and in particular to a stainless steel rocket second-stage zero-second drop-off refueling connector. Background Art

[0002] Cryogenic liquid rockets need to be filled with propellant before launch. In order to maintain the temperature of the cryogenic propellant, the propellant needs to be filled shortly before launch. At present, the connectors used on most launch vehicles are in the form of early detachment to ensure the reliability of detachment. They use locking devices such as pneumatic claw connections and ball lock structures to complete the separation of the rocket-ground connection device about 5 minutes before launch. If an abnormal situation occurs and the cryogenic propellant cannot be discharged, the rocket tank will increase in pressure as the propellant evaporates, and there is a risk of explosion.

[0003] The existing zero-second disengagement methods mainly include high-pressure gas disengagement and oil cylinder or hydraulic cylinder pulling disengagement. The secondary filling connector is far away from the ground, and the supporting and disengaging methods are relatively difficult, and there is a problem of low reliability of the disengagement method. Summary of the invention

[0004] In view of the deficiencies in the prior art, the present invention provides a stainless steel rocket second-stage zero-second detachment refueling connector, which solves the problem of low reliability of the current zero-second detachment method.

[0005] To achieve the above objectives, the present invention is implemented through the following technical solutions: a stainless steel rocket second-stage zero-second detachment refueling connector, comprising an arrow-mounted panel installed on a cryogenic rocket and a ground panel used to dock with the arrow-mounted panel before the cryogenic rocket is erected, a standard flange is installed on the ground panel, and the standard flange is connected to the ground through a metal hose; before the cryogenic rocket takes off, the arrow-mounted panel is locked with the ground panel through a locking device, and a traction rope is provided on the ground panel for unlocking the locking device when the cryogenic rocket takes off, and the traction rope is fixedly connected to the launch tower at one end away from the locking device.

[0006] Furthermore, the locking device includes two lock shells, which are fixedly connected to the arrow panel and the ground panel respectively; a lock hook is rotatably provided inside each of the lock shells through a rotating shaft; before the cryogenic rocket takes off, the two lock hooks are docked; a lock pin for locking the lock hooks is also provided inside each of the lock shells, which is used to fix the two lock hooks before the cryogenic rocket takes off; the traction rope is fixedly connected to the lock pin in the lock shell installed on the ground panel; before the cryogenic rocket takes off, the traction rope is pulled when the launch tower falls backward, driving the lock pin to disengage from the lock hook, and the lock hook returns to a rotatable state.

[0007] Furthermore, the locking pin includes a locking rod, a first locking block and a second locking block, the first locking block and the second locking block are both fixedly connected to the locking rod, a snap-in groove is provided inside the lock shell, a limiting groove is provided on the surface of the lock hook, the locking rod movably passes through the lock shell and extends to the outside of the lock shell, the locking rod movably passing through the lock shell installed on the ground panel is fixedly connected to the traction rope; before the cryogenic rocket takes off, the first locking block is movably connected to the inner side wall of the snap-in groove, and the second locking block is movably connected to the inner side wall of the limiting groove.

[0008] Furthermore, the rotating shaft is a break bolt structure.

[0009] Furthermore, the surface of the ground panel is connected to a steering wheel via a short shaft, and the surface of the traction rope is movably connected to the surface of the steering wheel.

[0010] Furthermore, the surface of the lock shell installed on the ground panel is provided with two clamping members for clamping and limiting the traction rope, the two clamping members are symmetrically arranged, and the two clamping members are movably connected to the two limit shells respectively through connecting springs, and the two limit shells are fixedly connected to the surface of the lock shell; the surface of the lock shell is fixedly connected to two plug-in shells, and the surface of the traction rope is fixedly connected to a plug-in member, the plug-in member movably passes through the two plug-in shells and is inserted into the interior of the two limit shells, and the surface of the plug-in member is movably connected to the surface of the clamping member; the plug-in member is connected to the inner wall of the plug-in shell.

[0011] Furthermore, the clamping part includes a sliding part, a triangular fixing part and a guiding part, the guiding part is fixedly connected to the surface of the sliding part, and the triangular fixing part is fixedly connected to the surface of the sliding part, and is used to clamp the traction rope; the guiding part movably passes through the limiting shell, the connecting spring is sleeved on the surface of the guiding part, one end of the connecting spring is fixedly connected to the surface of the sliding part, and the other end of the connecting spring is fixedly connected to the inner side wall of the limiting shell; the plug-in part includes a fixing part and two plug-in parts, the two plug-in parts are fixedly connected to the surface of the fixing part, the fixing part is fixedly connected to the surface of the traction rope, and the plug-in shell and the plug-in part are connected by breaking bolts.

[0012] Furthermore, the traction rope includes a buffer section and a pulling section, the buffer section is between the sliding portion and the locking rod, and the buffer section is arranged in a curved manner.

[0013] Furthermore, a first inclined surface is arranged at the top of the plug-in portion facing the traction rope, and a second inclined surface is arranged at the bottom of the sliding portion away from the traction rope.

[0014] Furthermore, a positioning block is fixedly connected to the inner side wall of the limiting shell, a positioning groove is provided on the surface of the plug-in portion, and the surface of the positioning block is movably connected to the inner side wall of the positioning groove.

[0015] The present invention has the following beneficial effects:

[0016] This stainless steel rocket second-stage zero-second detachment filling connector gets rid of low-reliability detachment methods such as high-pressure air supply, and adopts mechanical passive detachment. The launch tower falls backward before the low-temperature rocket takes off, and the locking device is pulled to unlock it, which greatly improves the detachment reliability. A redundant detachment method is designed on the locking structure. If the launch tower is not unlocked when it falls backward, it can be forcibly unlocked when the rocket takes off to avoid the unlocking situation.

[0017] Of course, any product implementing the present invention does not necessarily need to achieve all of the advantages described above at the same time. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a schematic diagram of the overall structure of the present invention.

[0019] Figure 2 It is a top view of the lock housing of the present invention.

[0020] Figure 3 For the present invention Figure 2 Sectional view at AA.

[0021] Figure 4 It is a schematic diagram of the locking rod structure of the present invention.

[0022] Figure 5 It is a schematic diagram of the lock hook structure of the present invention.

[0023] Figure 6 It is a schematic diagram of the internal structure of the lock housing of the present invention.

[0024] Figure 7 It is a structural schematic diagram of the connector of the present invention.

[0025] Figure 8 It is a schematic diagram of the structure of the limiting shell of the present invention.

[0026] Fig. 9 For the present invention Figure 8 Schematic diagram of the structure at point A in the middle.

[0027] Fig.10 It is a schematic diagram of the structure of the clamping member of the present invention.

[0028] In the figure, 1, arrow-up panel; 2, ground panel; 3, traction rope; 301, buffer section; 302, pulling section; 4, lock shell; 5, rotating shaft; 6, lock hook; 7, lock pin; 701, lock rod; 702, first lock block; 703, second lock block; 8, snap-in groove; 9, limit groove; 10, steering wheel; 11, clamping piece; 1101, sliding part; 1102, triangular fixing part; 1103, guide part; 12, connecting spring; 13, limit shell; 14, plug-in shell; 15, plug-in piece; 1501, fixing part; 1502, plug-in part; 16, first inclined plane; 17, second inclined plane; 18, positioning block; 19, positioning groove. DETAILED DESCRIPTION

[0029] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0030] In the description of the present invention, it should be understood that the terms "opening", "upper", "lower", "thickness", "top", "middle", "length", "inside", "all around" and the like indicating orientation or positional relationship are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the components or elements 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.

[0031] See also Figure 1-Figure 10 An embodiment of the present invention provides a technical solution: a stainless steel rocket second-stage zero-second detachment refueling connector, comprising an arrow-mounted panel 1 installed on a cryogenic rocket and a ground panel 2 used to dock with the arrow-mounted panel 1 before the cryogenic rocket is erected, a standard flange is installed on the ground panel 2, and the standard flange is connected to the ground through a metal hose; before the cryogenic rocket takes off, the arrow-mounted panel 1 is locked with the ground panel 2 through a locking device, and a traction rope 3 is provided on the ground panel 2 for unlocking the locking device when the cryogenic rocket takes off, and the end of the traction rope 3 away from the locking device is fixedly connected to the launch tower.

[0032] Specifically, the locking device includes two lock shells 4, which are fixedly connected to the upper panel 1 and the ground panel 2 respectively. A lock hook 6 is rotatably arranged inside each lock shell 4 through a rotating shaft 5. Before the cryogenic rocket takes off, the two lock hooks 6 are docked. A lock pin 7 for locking the lock hook 6 is also arranged inside each lock shell 4, which is used to fix the two lock hooks 6 before the cryogenic rocket takes off. The traction rope 3 is fixedly connected to the lock pin 7 in the lock shell 4 installed on the ground panel 2. Before the cryogenic rocket takes off, the traction rope 3 is pulled when the launch tower falls backward, driving the lock pin 7 to disengage the lock pin 7 from the lock hook 6, and the lock hook 6 resumes a rotatable state. The rotating shaft 5 is a pull-off bolt structure.

[0033] Specifically, the locking pin 7 includes a locking rod 701, a first locking block 702 and a second locking block 703. The first locking block 702 and the second locking block 703 are both fixedly connected to the locking rod 701. A snap-in groove 8 is provided inside the lock shell 4. A limiting groove 9 is provided on the surface of the lock hook 6. The locking rod 701 movably penetrates the lock shell 4 and extends to the outside of the lock shell 4. The locking rod 701 movably penetrates the lock shell 4 installed on the ground panel 2 and is fixedly connected to the traction rope 3; before the cryogenic rocket takes off, the first locking block 702 is movably connected to the inner side wall of the snap-in groove 8, and the second locking block 703 is movably connected to the inner side wall of the limiting groove 9.

[0034] In this embodiment, before the cryogenic rocket takes off, it is locked by a locking device, wherein the locking device includes two lock shells 4, and the two lock shells 4 are respectively fixedly connected to the upper panel 1 and the ground panel 2, and each lock shell 4 has a lock hook 6 rotatably provided inside through a rotating shaft 5, and the rotating shaft 5 is a breaking bolt structure. The locking pin 7 includes a locking rod 701, a first locking block 702 and a second locking block 703. The first locking block 702 and the second locking block 703 are both fixedly connected to the locking rod 701, wherein a limiting groove 9 is provided on the locking hook 6, and a snap-in groove 8 is provided inside the lock shell 4. Before the cryogenic rocket takes off, the two locking hooks 6 are snap-connected. In order to prevent rotation, the locking pin 7 is used for limiting the position, wherein the first locking block 702 is connected to the snap-in groove 8 of the lock shell 4, and the second locking block 703 is connected to the limiting groove 9. At this time, when the two lock shells 4 are subjected to separation force, the limiting groove 9 of the locking hook 6 squeezes the second locking block 703, thereby squeezing the first locking block 702 to the snap-in groove 8 through the locking rod 701, but the locking pin 7 cannot rotate and thus cannot be unlocked.

[0035] Specifically, the surface of the ground panel 2 is connected to the steering wheel 10 via a short shaft, and the surface of the traction rope 3 is movably connected to the surface of the steering wheel 10 .

[0036] In this embodiment, the launch tower can fall backwards by pulling the traction rope 3 to move, and the steering wheel 10 plays a role in changing the pulling direction, thereby moving the locking rod 701, and then the first locking block 702 and the second locking block 703 move simultaneously.

[0037] Specifically, the surface of the lock shell 4 installed on the ground panel 2 is provided with two clamping members 11 for clamping and limiting the traction rope 3. The two clamping members 11 are symmetrically arranged, and the two clamping members 11 are movably connected to the two limiting shells 13 respectively through the connecting spring 12, and the two limiting shells 13 are fixedly connected to the surface of the lock shell 4; the surface of the lock shell 4 is fixedly connected with two plug-in shells 14, and the surface of the traction rope 3 is fixedly connected with a plug-in member 15, the plug-in member 15 is movably passed through the two plug-in shells 14 and inserted into the interior of the two limiting shells 13, and the surface of the plug-in member 15 is movably connected to the surface of the clamping member 11; the plug-in member 15 is connected to the inner wall of the plug-in shell 14.

[0038] Specifically, the clamping member 11 includes a sliding portion 1101, a triangular fixing portion 1102 and a guiding portion 1103, wherein the guiding portion 1103 is fixedly connected to the surface of the sliding portion 1101, and the triangular fixing portion 1102 is fixedly connected to the surface of the sliding portion 1101, and is used to clamp the traction rope 3; the guiding portion 1103 movably penetrates the limiting shell 13, the connecting spring 12 is sleeved on the surface of the guiding portion 1103, one end of the connecting spring 12 is fixedly connected to the surface of the sliding portion 1101, and the other end of the connecting spring 12 is fixedly connected to the inner side wall of the limiting shell 13; the plug-in component 15 includes a fixing portion 1501 and two plug-in portions 1502, the two plug-in portions 1502 are fixedly connected to the surface of the fixing portion 1501, the fixing portion 1501 is fixedly connected to the surface of the traction rope 3, and the plug-in shell 14 is connected to the plug-in portion 1502 by breaking bolts.

[0039] A positioning block 18 is fixedly connected to the inner side wall of the limiting shell 13 , a positioning groove 19 is formed on the surface of the plug-in portion 1502 , and the surface of the positioning block 18 is movably connected to the inner side wall of the positioning groove 19 .

[0040] In this embodiment, in order to prevent the connector 15 from falling off, the plug-in part 1502 is fixed to the plug-in shell 14 by pulling off the bolts. In addition, the inner wall of the limiting shell 13 is fixedly connected with a positioning block 18, and the surface of the plug-in part 1502 is provided with a positioning groove 19, which can play a guiding and limiting role when installing the plug-in part 1502.

[0041] Specifically, the traction rope 3 includes a buffer section 301 and a pulling section 302 . The buffer section 301 is between the sliding portion 1101 and the locking rod 701 , and the buffer section 301 is arranged in a curved manner.

[0042] In this embodiment, the buffer section 301 is provided to enable the connector 15 and the locking pin 7 to move in steps. The plug-in portion 1502 of the connector 15 interacts with the breaking bolt under the action of the traction rope 3, so that the breaking bolt is broken, and then the plug-in portion 1502 is separated from the sliding portion 1101. Under the action of the connecting spring 12, the sliding portion 1101 drives the triangular fixing portion 1102 to move and separate from the wire rope. When the buffer section 301 is straightened, the plug-in portion 1502 is completely separated from the plug-in shell 14, and then the traction rope 3 moves the locking pin 7 to achieve unlocking.

[0043] Specifically, a first inclined surface 16 is provided at the top of the plug-in portion 1502 facing the traction rope 3 , and a second inclined surface 17 is provided at the bottom of the sliding portion 1101 away from the traction rope 3 .

[0044] In this embodiment, during installation, the plug-in portion 1502 passes through the plug-in shell 14 and enters into the interior of the limiting shell 13. The plug-in portion 1502 is provided with a first inclined surface 16 at the top facing the traction rope 3, and the sliding portion 1101 is provided with a second inclined surface 17 at the bottom facing the traction rope 3. The first inclined surface 16 and the second inclined surface 17 are squeezed against each other, so that the clamping member 11 can move toward the direction approaching the traction rope 3, thereby making the triangular fixing portion 1102 contact with the traction rope 3 and fix the traction rope 3.

[0045] When in use, the arrow-mounted panel 1 is installed on the cryogenic rocket, and the ground panel 2 is docked with the arrow-mounted panel 1 before the rocket is erected. A standard flange is designed on the ground panel 2, and a metal hose is connected to connect it to the ground.

[0046] Before the cryogenic rocket takes off, it is locked by a locking device, wherein the locking device includes two lock shells 4, and the two lock shells 4 are respectively fixedly connected to the upper panel 1 and the ground panel 2, and each lock shell 4 has a lock hook 6 rotatably arranged inside through a rotating shaft 5, and the rotating shaft 5 is a breaking bolt structure. The locking pin 7 includes a locking rod 701, a first locking block 702 and a second locking block 703. The first locking block 702 and the second locking block 703 are both fixedly connected to the locking rod 701, wherein a limiting groove 9 is provided on the locking hook 6, and a snap-in groove 8 is provided inside the lock shell 4. Before the cryogenic rocket takes off, the two locking hooks 6 are snap-connected. In order to prevent rotation, the locking pin 7 is used for limiting the position, wherein the first locking block 702 is connected to the snap-in groove 8 of the lock shell 4, and the second locking block 703 is connected to the limiting groove 9. At this time, when the two lock shells 4 are subjected to separation force, the limiting groove 9 of the locking hook 6 squeezes the second locking block 703, thereby squeezing the first locking block 702 to the snap-in groove 8 through the locking rod 701, but the locking pin 7 cannot rotate and thus cannot be unlocked.

[0047] In order for the cryogenic rocket to take off normally, it is necessary to disengage the second locking block 703 from the limiting groove 9 before takeoff. The distance between the first locking block 702 and the second locking block 703 is greater than or equal to the maximum thickness of the locking hook 6. The outside of the locking rod 701 on the lock shell 4 connected to the ground panel 2 is fixedly connected with a traction rope 3, and the other end of the traction rope 3 is connected to the launch tower. Before the cryogenic rocket takes off, the launch tower falls backward, and the traction rope 3 can be pulled to move. The steering wheel 10 plays a role in changing the pulling direction, thereby moving the locking rod 701, and then moving the first locking block 702 and the second locking block 703 at the same time. The locking hook 6 has a side with the limiting groove 9 and the interior of the lock shell 4 has a space for accommodating the second locking block 703, while the other side is in contact with the inner wall of the lock shell 4.

[0048] When the second lock block 703 is out of contact with the limit groove 9, the first lock shell 4 still remains inside the clamping groove 8, and the arrow-up panel 1 moves upward under the action of the cryogenic rocket, thereby causing the lock shell 4 on the arrow-up panel 1 to move, causing the lock hook 6 inside the lock shell 4 to move, thereby squeezing the lock hook 6 in the lock shell 4 fixed to the ground panel 2. Since the lock hook 6 is movable, it will rotate around the rotating shaft 5 under the action of the squeezing force, thereby disengaging the two lock hooks 6, achieving unlocking, and the cryogenic rocket takes off smoothly. However, when there is a failure to unlock, the rotating shaft 5 of the bolt structure will be broken under the action of the upward force of the cryogenic rocket, thereby not affecting the take-off of the cryogenic rocket.

[0049] In addition, the side of the lock hook 6 with the limiting groove 9 can also contact the inner wall of the lock shell 4, but the other side has space for accommodating the first lock block 702 inside the lock shell 4. Before takeoff, the first lock shell 4 is disengaged from the clamping groove 8, and the lock hook 6 squeezes the second lock shell 4 through the limiting groove 9, driving the lock pin 7 to rotate synchronously to achieve unlocking. However, this method has the problem of synchronous rotation of the lock pin 7, resulting in the need to synchronize the reset of the lock pin 7 during subsequent resetting, which adds steps. Of course, both sides of the lock hook 6 can have space inside the lock shell 4. During unlocking before takeoff, the first lock block 702 is disengaged from the clamping groove 8, and the second lock block 703 is disengaged from the limiting groove 9. However, when the side of the lock hook 6 close to the first lock block 702 rotates, it can drive the first lock block 702 to move at the same time. Therefore, during subsequent resetting, the lock pin 7 may also need to be reset synchronously. In comparison, the lock hook 6 has a side with the limiting groove 9 and a space inside the lock housing 4 for accommodating the second lock block 703, while the other side contacts the inner wall of the lock housing 4, so the lock pin 7 does not need to be rotated and reset.

[0050] The above method can achieve the fixation of the ground panel 2 and the upper panel 1 before takeoff. However, since the locking pin 7 is movable, when the traction rope 3 is accidentally touched, the locking pin 7 may move, thereby causing premature unlocking and fixation failure.

[0051] Two plug-in parts 15 are symmetrically arranged on the lock shell 4 fixed on the ground panel 2 through two limit shells 13, wherein the plug-in part 15 includes a sliding part 1101, a triangular fixing part 1102 and a guide part 1103, the guide part 1103 is fixedly connected to the surface of the sliding part 1101, the triangular fixing part 1102 is fixedly connected to the surface of the sliding part 1101, the guide part 1103 is cylindrical, and the plug-in part 15 is fixedly connected to the traction rope 3, and the plug-in part 15 includes a fixing part 1501 and two plug-in parts 1502, and the plug-in part 1502 is fixedly connected to the surface of the fixing part 1501. During installation, the plug-in part 1502 passes through the plug-in shell 14 and enters into the interior of the limiting shell 13. The plug-in part 1502 is provided with a first inclined surface 16 at the top of the side facing the traction rope 3, and the sliding part 1101 is provided with a second inclined surface 17 at the bottom of the side away from the traction rope 3. The first inclined surface 16 and the second inclined surface 17 are squeezed against each other, so that the clamping part 11 can move in the direction close to the traction rope 3, so that the triangular fixing part 1102 contacts with the traction rope 3 and fixes the traction rope 3.

[0052] In order to prevent the connector 15 from falling off, the plug-in part 1502 is fixed to the plug-in shell 14 by pulling off the bolts. In addition, the inner wall of the limiting shell 13 is fixedly connected with a positioning block 18, and the surface of the plug-in part 1502 is provided with a positioning groove 19, which can play a guiding and limiting role when installing the plug-in part 1502.

[0053] Before takeoff, the launch tower falls backwards and pulls the traction rope 3. At this time, the traction rope 3 is divided into a buffer section 301 and a pulling section 302. The buffer section 301 is between the sliding part 1101 and the locking rod 701, and is arranged in a curved manner. The remaining part is the pulling section 302. The buffer section 301 is provided to enable the connector 15 and the locking pin 7 to move in steps. The plug-in part 1502 of the connector 15 interacts with the breaking bolt under the action of the traction rope 3, so that the breaking bolt is broken, and then the plug-in part 1502 is separated from the sliding part 1101. Under the action of the connecting spring 12, the sliding part 1101 drives the triangular fixing part 1102 to move and separate from the wire rope. When the buffer section 301 is straightened, the plug-in part 1502 is completely separated from the plug-in shell 14. Then the traction rope 3 moves the locking pin 7 to achieve unlocking.

[0054] It should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device.

[0055] The preferred embodiments of the present invention disclosed above are only used to help illustrate the present invention. The preferred embodiments do not describe all the details in detail, nor do they limit the invention to the specific implementation methods described. Obviously, many modifications and changes can be made according to the content of this specification. This specification selects and specifically describes these embodiments in order to better explain the principles and practical applications of the present invention, so that those skilled in the art can understand and use the present invention well. The present invention is limited only by the claims and their full scope and equivalents.

Claims

1. A stainless steel rocket second-stage zero-second drop-off refueling connector, characterized in that: It comprises an arrow-mounted panel (1) mounted on a cryogenic rocket and a ground panel (2) used to dock with the arrow-mounted panel (1) before the cryogenic rocket is erected, wherein a standard flange is mounted on the ground panel (2), and the standard flange is connected to the ground via a metal hose; Before the cryogenic rocket takes off, the arrow-mounted panel (1) is locked with the ground panel (2) via a locking device, and a traction rope (3) is provided on the ground panel (2) for unlocking the locking device when the cryogenic rocket takes off, and one end of the traction rope (3) away from the locking device is fixedly connected to the launch tower; The locking device comprises two lock shells (4), the two lock shells (4) being fixedly connected to the upper panel (1) and the ground panel (2) respectively, and each lock shell (4) is provided with a lock hook (6) rotatably arranged inside via a rotating shaft (5), and before the cryogenic rocket takes off, the two lock hooks (6) are butted against each other, and a lock pin (7) for locking the lock hook (6) is also arranged inside each lock shell (4), and is used to fix the two lock hooks (6) before the cryogenic rocket takes off; The traction rope (3) is fixedly connected to a lock pin (7) in a lock housing (4) installed on a ground panel (2); before the cryogenic rocket takes off, the traction rope (3) is pulled when the launch tower falls backwards, driving the lock pin (7) so that the lock pin (7) is separated from the lock hook (6), and the lock hook (6) resumes a rotatable state.

2. According to claim 1, a stainless steel rocket second-stage zero-second drop-off refueling connector is characterized in that: The lock pin (7) comprises a lock rod (701), a first lock block (702) and a second lock block (703); the first lock block (702) and the second lock block (703) are both fixedly connected to the lock rod (701); a clamping groove (8) is provided inside the lock shell (4); a limiting groove (9) is provided on the surface of the lock hook (6); the lock rod (701) movably penetrates the lock shell (4) and extends to the outside of the lock shell (4); the lock rod (701) movably penetrates the lock shell (4) installed on the ground panel (2) and is fixedly connected to the traction rope (3); Before the cryogenic rocket takes off, the first locking block (702) is movably connected to the inner side wall of the clamping groove (8), and the second locking block (703) is movably connected to the inner side wall of the limiting groove (9).

3. According to claim 2, a stainless steel rocket second-stage zero-second drop-off refueling connector is characterized in that: The rotating shaft (5) is a pull-off bolt structure.

4. According to claim 2, a stainless steel rocket second-stage zero-second drop-off refueling connector is characterized in that: The surface of the ground panel (2) is connected to a steering wheel (10) via a short shaft, and the surface of the traction rope (3) is movably connected to the surface of the steering wheel (10).

5. According to claim 2, a stainless steel rocket second-stage zero-second drop-off refueling connector is characterized in that: The surface of the lock housing (4) mounted on the ground panel (2) is provided with two clamping members (11) for clamping and limiting the traction rope (3), the two clamping members (11) are symmetrically arranged, and the two clamping members (11) are movably connected to two limiting shells (13) respectively through connecting springs (12), and the two limiting shells (13) are fixedly connected to the surface of the lock housing (4); The surface of the lock housing (4) is fixedly connected to two plug-in housings (14), the surface of the traction rope (3) is fixedly connected to a plug-in component (15), the plug-in component (15) movably penetrates the two plug-in housings (14) and is inserted into the interior of the two limit housings (13), and the surface of the plug-in component (15) is movably connected to the surface of the clamping component (11); The plug connector (15) is connected to the inner side wall of the plug housing (14).

6. According to claim 5, a stainless steel rocket second-stage zero-second drop-off refueling connector is characterized in that: The clamping member (11) comprises a sliding portion (1101), a triangular fixing portion (1102) and a guiding portion (1103); the guiding portion (1103) is fixedly connected to the surface of the sliding portion (1101); and the triangular fixing portion (1102) is fixedly connected to the surface of the sliding portion (1101), and is used to clamp the traction rope (3); The guide portion (1103) movably penetrates the limiting shell (13), the connecting spring (12) is sleeved on the surface of the guide portion (1103), one end of the connecting spring (12) is fixedly connected to the surface of the sliding portion (1101), and the other end of the connecting spring (12) is fixedly connected to the inner wall of the limiting shell (13); The plug-in connector (15) comprises a fixing portion (1501) and two plug-in portions (1502), the two plug-in portions (1502) being fixedly connected to the surface of the fixing portion (1501), the fixing portion (1501) being fixedly connected to the surface of the traction rope (3), and the plug-in shell (14) and the plug-in portions (1502) being connected via a breaking bolt.

7. According to claim 6, a stainless steel rocket second-stage zero-second drop-off refueling connector is characterized in that: The traction rope (3) comprises a buffer section (301) and a pulling section (302); the buffer section (301) is between the sliding portion (1101) and the locking rod (701); and the buffer section (301) is arranged in a curved manner.

8. According to claim 7, a stainless steel rocket second-stage zero-second drop-off refueling connector is characterized in that: A first inclined surface (16) is provided at the top of the plug-in portion (1502) on the side facing the traction rope (3), and a second inclined surface (17) is provided at the bottom of the sliding portion (1101) on the side away from the traction rope (3).

9. The stainless steel rocket two-stage zero-second drop-off refueling connector according to claim 7 is characterized in that: A positioning block (18) is fixedly connected to the inner side wall of the limiting shell (13), a positioning groove (19) is provided on the surface of the plug-in portion (1502), and the surface of the positioning block (18) is movably connected to the inner side wall of the positioning groove (19).

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