A propellant filling connector and filling device

Abstract

This invention provides a propellant refueling connector and refueling device, including a connector body, a fixed frame on the outside of the connector body, a movable frame in front of the fixed frame, a cylinder, and a hook. The movable frame is axially movable. The cylinder body is connected to the fixed frame, and the piston rod is connected to the movable frame. The front end of the hook extends out of the front end of the connector body, and the rear end is hinged to the fixed frame via a first hinge shaft and also hinged to the movable frame via a second hinge shaft, with the second hinge shaft located outside the first hinge shaft. An elastic device is provided between the fixed frame and the movable frame, and the elastic device is sleeved on the outer periphery of the piston rod. In this technical solution, a flange-shaped movable frame is provided on the refueling connector, which drives the hook to move. An elastic device is added between the movable frame and the fixed frame. During the refueling process, even if the air path that drives the piston rod to extend malfunctions, the elastic force of the elastic device can still ensure that the connector and the refueling port are properly locked and sealed, ensuring the normal operation of the refueling.

Description

Technical Field

[0001] This invention relates to the field of launch vehicle technology, and in particular to a propellant refueling connector and refueling equipment. Background Technology

[0002] Before launch, a propellant loading connector needs to mate with the loading port on the launch vehicle to load or unload propellant. After liftoff, the connector detaches from the onboard equipment. Existing propellant loading connectors generally use a cylinder to drive the front-end claw. When loading is required, the cylinder's piston rod extends, pushing the claw to swing and open the side of the loading port, thus mates the propellant loading connector with the loading port. The rear end of the connector is connected to a propellant loading line, allowing propellant to flow sequentially through the line, connector, and loading port into the launch vehicle's propellant tank.

[0003] However, the inventors discovered that this technology has the following problems during the refueling operation: During refueling, leaks or other malfunctions sometimes occur in the cylinder air supply line, leading to a decrease in piston rod thrust. This, in turn, affects the seal between the propellant refueling connector and the refueling port, impacting the normal operation of the refueling process and even posing a risk of the propellant refueling connector accidentally detaching. Therefore, improving the propellant refueling connector to avoid the adverse effects of cylinder air supply line malfunctions on the refueling operation is a problem that needs to be solved. Summary of the Invention

[0004] This invention provides a propellant filling connector and filling device to solve the problem in the prior art that the filling operation cannot be performed normally when there is a leak in the cylinder air supply line.

[0005] To achieve the above objectives, in one aspect, embodiments of the present invention provide a propellant filling connector, including a connector body, a fixed frame, a movable frame, a cylinder, and a hook; the fixed frame is fixedly connected to the connector body, the movable frame is located in front of the fixed frame, and the movable frame can move along the axial direction of the connector body; the cylinder includes a cylinder body and a telescopic piston rod, the cylinder body is connected to the fixed frame, and the piston rod is connected to the movable frame; the front end of the hook extends out of the front end face of the connector body, the rear end of the hook is hinged to the fixed frame through a first hinge axis, and the hook is also hinged to the movable frame through a second hinge axis, and the second hinge axis is located outside the first hinge axis (that is, the distance between the second hinge axis and the axis of the connector body is greater than the distance between the first hinge axis and the axis of the connector body); an elastic device is also provided between the fixed frame and the movable frame, and the elastic device is sleeved on the outer periphery of the piston rod.

[0006] Furthermore, the fixed frame includes a fixed frame sleeve sleeved on the outside of the connector body and a fixed frame flange fixedly connected to the middle of the fixed frame sleeve. A first hinge shaft support is provided at the front end of the fixed frame sleeve. The movable frame is a disc-shaped structure sleeved on the outside of the fixed frame sleeve. The movable frame is arranged parallel to the fixed frame flange. A second hinge shaft support is also provided at the front end of the movable frame.

[0007] Furthermore, there are three cylinders, which are evenly distributed circumferentially.

[0008] Furthermore, the propellant filling connector also includes a guide rod; the front end of the guide rod is fixedly connected to the movable frame, and the rear end of the guide rod passes through the fixed frame.

[0009] Furthermore, there are three guide rods in total, and the guide rods are staggered with the cylinder circumferentially.

[0010] Furthermore, an elastic device is fitted on the outer side of the guide rod.

[0011] Furthermore, the hook is a U-shaped structure consisting of a front section, a middle section, and a rear section connected sequentially. The front section is connected to a clamping screw, and the rear section is provided with an inner hinge hole for the first hinge shaft to pass through and an outer hinge hole for the second hinge shaft to pass through. When the propellant refueling connector is connected to the rocket refueling port, the clamping screw is in a horizontal position.

[0012] Furthermore, the propellant filling connector also includes a claw block that engages with a clamping screw; the end face of the clamping screw is an outwardly convex spherical surface, and the inside of the claw block is provided with an inwardly concave spherical surface that matches the outwardly convex spherical surface.

[0013] Furthermore, a separation push rod is provided on the front side of the movable frame; a first push rod pin is provided radially on the outer side of the fixed frame sleeve, and the middle part of the separation push rod is hinged to the first push rod pin; a push rod support is provided at the front end of the movable frame, and the fixed end of the separation push rod is hinged to the push rod support through a second push rod pin, and the second push rod pin is parallel to the first push rod pin; the limit swing position of the movable end of the separation push rod exceeds the front end face of the connector body.

[0014] Furthermore, there are three release pushers in total, which are evenly distributed circumferentially.

[0015] On the other hand, embodiments of the present invention also provide a refueling device, including a propellant refueling pipeline and a propellant refueling connector as described above, wherein the front end of the propellant refueling pipeline is connected to the rear end of the connector body.

[0016] The above technical solution has the following beneficial effects:

[0017] In this technical solution, a flange-shaped movable frame is set on the propellant refueling connector. The movable frame drives the claw to move. An elastic device is added between the movable frame and the fixed frame. During the refueling process, even if the gas path that pushes the piston rod to extend malfunctions, the elastic force of the elastic device can still ensure that the propellant refueling connector and the rocket refueling port are locked and sealed normally, ensuring the normal progress of the refueling operation.

[0018] In addition, this technical solution also has the following characteristics:

[0019] 1) In the existing technology, when the gas supply pipeline leaks seriously, the piston rod thrust is greatly reduced, and the propellant refueling connector is at risk of accidental detachment, which can easily lead to damage to the rocket or propellant refueling connector components; after adopting this technical solution, due to the existence of elasticity, the accidental detachment of the propellant refueling connector can be effectively avoided.

[0020] 2) When the propellant loading connector is disconnected from the loading port, the pawl is opened by the retraction of the cylinder piston rod. At this time, the propellant loading connector falls under its own weight, which poses a risk of hitting the rocket body during the fall. This technical solution adds a separation push rod. During the retraction of the piston rod, the separation push rod can swing, so that the front end of the separation push rod presses against the side of the loading port, causing the propellant loading connector to move backward. This creates a certain safe distance between the propellant loading connector and the loading port, ensuring that the propellant loading connector will not hit the rocket body during the fall. Attached Figure Description

[0021] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0022] Figure 1 This is a side sectional view of a propellant filling connector according to an embodiment of the present invention;

[0023] Figure 2 This is an isometric schematic diagram of a propellant filling connector according to an embodiment of the present invention;

[0024] Figure 3 This is a schematic diagram of the structure of the fixing frame in an embodiment of the present invention;

[0025] Figure 4 This is a schematic diagram of the hook claw structure in an embodiment of the present invention;

[0026] Figure 5 This is a schematic diagram of the structure of the movable frame in an embodiment of the present invention;

[0027] Figure 6 This is a schematic diagram of the installation of the separation push rod in an embodiment of the present invention;

[0028] Figure 7 This is a schematic diagram of the separation push rod in an embodiment of the present invention.

[0029] Icon labels:

[0030] 1. Fixing bracket; 11. Fixing bracket sleeve; 12. Fixing bracket flange; 13. First hinge shaft support; 14. Cylinder mounting hole;

[0031] 2. Movable frame; 21. Second hinge shaft support; 22. Push rod support; 23. Guide rod mounting hole;

[0032] 3. Cylinder;

[0033] 4. Hook; 41. First hinge shaft; 42. Second hinge shaft; 43. Clamping screw; 44. Hook clamping block; 45. Front section; 46. Middle section; 47. Rear section; 48. Inner hinge hole; 49. Outer hinge hole;

[0034] 5. Connector body; 6. Elastic device; 7. Guide rod; 8. Filler port connection plate;

[0035] 9. Separating push rod; 91. First push rod pin; 92. Second push rod pin; 93. Pulley block;

[0036] 10. Cold insulation sleeve. Detailed Implementation

[0037] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0038] like Figure 1 , Figure 2As shown, this embodiment of the invention provides a propellant filling connector, including a connector body 5, a fixed frame 1, a movable frame 2, a cylinder 3, and a claw 4; the fixed frame 1 is fixedly connected to the connector body 5, the movable frame 2 is located in front of the fixed frame 1, and the movable frame 2 can move axially along the connector body 5; the cylinder 3 includes a cylinder body and a telescopic piston rod (or cylinder push rod), the cylinder body is connected to the fixed frame 1, and the piston rod is connected to the movable frame 2; the front end of the claw 4 extends out of the front end face of the connector body 5, the rear end of the claw 4 is hinged to the fixed frame 1 through a first hinge shaft 41, and the claw 4 is also hinged to the movable frame 2 through a second hinge shaft 42, and the second hinge shaft 42 is located outside the first hinge shaft 41; an elastic device 6 is also provided between the fixed frame 1 and the movable frame 2, and the elastic device 6 is sleeved on the outer periphery of the piston rod.

[0039] To solve the aforementioned problems, in this embodiment of the invention, in addition to using a cylinder 3 to provide the pushing or pulling force for the pawl 4, an additional elastic device 6 (preferably a spring, but other forms may also be used) is provided. The aim is to have the cylinder 3 and the elastic device 6 work together so that even if the piston rod thrust is insufficient during the refueling operation, the propellant refueling connector can be kept in a locked state to prevent leakage from affecting the refueling operation.

[0040] To add the elastic device 6, a suitable installation method must be designed. Therefore, in this embodiment, a movable frame 2 (or a moving frame) is fitted outside the fixed frame 1, with both ends of the elastic device 6 resting against the movable frame 2 and the fixed frame 1 respectively. The movable frame 2 is connected to the piston rod end via a cylinder connecting pin. When the piston rod extends or retracts, it can drive the movable frame 2 to move axially. Simultaneously, in addition to being hinged to the fixed frame 1 via the first hinge shaft 41, the hook 4 is also hinged to the movable frame 2 via the second hinge shaft 42, with the second hinge shaft 42 and the first hinge shaft 41 arranged vertically. Thus, when the movable frame 2 moves axially, it can push the hook 4 to rotate around the first hinge shaft 41 as the axis. Figure 1 As shown, when the hook 4 swings towards the center of the connector body 5, it can be used to lock the filling port, and when the hook 4 swings towards the outside of the connector body 5, it can be used to release the connection and locking state between it and the filling port.

[0041] The specific working process is as follows: At the start of refueling, the gas supply control system (not shown in the figure) gives an action signal, causing the electromagnetic reversing valve (not shown in the figure) in the gas circuit to activate, supplying gas to one chamber of cylinder 3 (which can be called the locking chamber). The piston rod extends and pushes the movable frame 2 to the locking position. At the same time, the movable frame 2 drives the hook 4 to move, pressing against the refueling port connecting plate 8 on the refueling port. At this time, it is in the connection locking state. During the refueling process, even if there is air leakage in the gas supply line, which causes the piston rod thrust to decrease, the front end of the elastic device 6 is still tightly pressed against the movable frame 2. Therefore, the movable frame 2 will not move backward, and the hook 4 will not rotate in the opposite direction. The propellant refueling connector can still be firmly connected to the refueling port and maintain a reliable seal, ensuring the normal operation of the refueling. After the refueling is completed, the electromagnetic reversing valve reverses, supplying gas to another chamber of cylinder 3 (which can be called the detachment chamber), causing the piston rod to overcome the elastic force of the elastic device 6 to retract, and causing the movable frame 2 to retract and drive the hook 4 to rotate in the opposite direction, thereby realizing the separation of the propellant refueling connector from the refueling port. It should be noted that the dual gas supply lines usually do not fail simultaneously. Therefore, if the gas supply line to the locking chamber fails, the gas supply line to the detachment chamber may not also fail, and the piston rod can retract normally. Even if the gas supply line to the detachment chamber fails and the piston rod cannot retract, the rocket is equipped with a backup break mechanism for emergency disconnection of the rocket body from the fueling line during launch, so it will not affect the normal launch of the rocket.

[0042] In addition, in this technical solution, a cold insulation sleeve 10 is provided between the fixed frame 1 and the connector body 5. It is made of low-temperature resistant heat insulation material, which can effectively prevent the low temperature of the conveying medium from causing adverse effects on the components on the outside of the connector body 5 (especially the movable components such as the movable frame 2 and the hook 4).

[0043] Furthermore, the preferred form of the fixing bracket 1 is as follows: Figure 3 As shown, it includes a fixing sleeve 11 sleeved on the outside of the connector body 5, and a fixing flange 12 fixedly connected to the middle of the fixing sleeve 11. A first hinge shaft support 13 is provided at the front end of the fixing sleeve 11 for mounting the first hinge shaft 41; the preferred form of the movable frame 2 is as follows. Figure 5 As shown, the movable frame 2 is a disc-shaped structure fitted onto the outside of the fixed frame sleeve 11. The movable frame 2 is arranged parallel to the fixed frame flange 12, so that both ends of the elastic device 6 abut against the rear side of the movable frame 2 and the front side of the fixed frame flange 12. A second hinge shaft support 21 is also provided at the front end of the movable frame 2 for mounting the second hinge shaft 42. Figure 3 As shown, the cylinder body of cylinder 3 is connected to the mounting bracket 1 through cylinder mounting hole 14.

[0044] Furthermore, there are three cylinders 3, which are evenly distributed around the circumference. This arrangement is the most preferred arrangement, with an included angle of 120° between each pair of adjacent cylinders 3. When the three piston rods push simultaneously, it can ensure that the movable frame 2 is subjected to balanced force. If too many cylinders 3 are set, in addition to increasing costs, it is also difficult to ensure that multiple piston rods move synchronously due to factors such as the machining errors of the cylinders themselves.

[0045] Furthermore, the propellant filling connector also includes a guide rod 7, which provides guidance for the forward and backward movement of the movable frame 2. The front end of the guide rod 7 extends into the guide rod mounting hole 23, and a connecting pin is radially inserted into the front end of the guide rod 7 through a small hole on the edge of the movable frame 2 to achieve a fixed connection between the guide rod 7 and the movable frame 2. The rear end of the guide rod 7 passes through the fixed frame 1 and has a boss at the end with an outer diameter larger than that of the guide rod 7 to achieve limit position limiting. If necessary, a fixed boss can be omitted, and a threaded section can be provided at the rear end of the guide rod 7, with an adjusting nut screwed onto the threaded section. The distance between the fixed frame 1 and the movable frame 2 can be adjusted by adjusting the nut.

[0046] Furthermore, in order to achieve a more stable guiding effect, three guide rods 7 are also provided; at the same time, since the piston rod of the cylinder 3 itself also plays a certain guiding role in the movement of the movable frame 2, the preferred method is to make the three guide rods 7 and the cylinder 3 circumferentially staggered, that is, the included angle between every two adjacent guide rods 7 and the cylinder 3 is 60°.

[0047] Furthermore, an elastic device 6 is sleeved on the outer side of the guide rod 7. At this time, a total of six elastic devices 6 are provided, and the six elastic devices 6 are evenly distributed in the 360° circumferential direction, so that the elastic force on the movable frame 2 is also more evenly distributed.

[0048] Furthermore, to facilitate the clamping action at the filling port, the hook 4 is shaped as follows: Figure 4 As shown, it is a U-shaped structure formed by connecting the front section 45, the middle section 46, and the rear section 47 in sequence. The front section 45 is connected to a clamping screw 43 through a threaded hole. The rear section 47 is provided with an inner hinge hole 48 for the first hinge shaft 41 to pass through and an outer hinge hole 49 for the second hinge shaft 42 to pass through. When the propellant refueling connector is connected to the rocket refueling port, the clamping screw 43 is in a horizontal state to ensure that it can press the front side of the refueling port connecting plate 8 in a vertical manner and avoid accidental loosening.

[0049] Furthermore, to improve the clamping effect, it is not recommended to directly clamp the front end of the clamping screw 43 to the filling port connecting plate 8. Instead, a hook-claw block 44 is engaged with the end of the clamping screw 43. The end face of the clamping screw 43 is an outwardly convex spherical surface, and the inside of the hook-claw block 44 is provided with an inwardly concave spherical surface that matches the outwardly convex spherical surface. The hook-claw block 44 is fitted on the outside of the clamping screw 43, so that the angle between the two spherical surfaces can be finely adjusted as needed to meet the actual requirements. (Due to manufacturing precision, assembly errors, etc., it is difficult to ensure that the clamping screw 43 and the plate surface of the filling port connecting plate 8 are exactly perpendicular. At this time, the fine adjustment between the hook-claw block 44 and the clamping screw 43 can achieve the compensation effect, so that the end face of the hook-claw block 44 is completely in contact with the plate surface of the filling port connecting plate 8.)

[0050] Furthermore, a problem exists in the existing technology: when the propellant loading connector is disconnected from the loading port, the pawl is opened by the retraction of the cylinder piston rod. At this time, the propellant loading connector falls under its own weight. However, before falling, the propellant loading connector is tightly fitted to the loading port, so there is a risk of it hitting the rocket body during the fall. Therefore, as... Figure 6 As shown, this technical solution also includes the following design: a separation push rod 9 is provided on the front side of the movable frame 2; a first push rod pin 91 is provided radially on the outer side of the fixed frame sleeve 11, and the middle part of the separation push rod 9 is hinged to the first push rod pin 91; a push rod support 22 is provided at the front end of the movable frame 2, and the fixed end of the separation push rod 9 is hinged to the push rod support 22 through a second push rod pin 92, and the second push rod pin 92 and the first push rod pin 91 are parallel to each other; the limit swing position of the movable end of the separation push rod 9 exceeds the front end face of the connector body 5.

[0051] With the separation push rod 9 installed, when the piston rod retracts, the movable frame 2 can drive the separation push rod 9 to swing within a plane tangent to the connector body 5. This causes the front end of the separation push rod 9 to press against the rear side of the refueling port connecting plate 8, moving the propellant refueling connector backward. This creates a safe distance between the front end of the propellant refueling connector and the refueling port, preventing the propellant refueling connector from hitting the rocket body during its descent. To avoid damaging the side of the refueling port connecting plate 8, a cylindrical lever 93 is also installed at the movable end of the separation push rod 9, allowing it to push the refueling port connecting plate 8 with its arc-shaped side.

[0052] Furthermore, for the same reason as the aforementioned arrangement of cylinder 3, in order to achieve balanced force distribution, three separation push rods 9 are preferably provided, and the three separation push rods 9 are evenly distributed around the circumference, that is, the included angle between every two separation push rods 9 is also 120°.

[0053] This invention also provides a refueling device, including a propellant refueling pipeline and a propellant refueling connector as described above, wherein the front end of the propellant refueling pipeline is connected to the rear end of the connector body 5.

[0054] The present technical solution is described below with reference to a specific embodiment. The propellant loading connector of this specific embodiment mainly includes the following aspects:

[0055] 1. Locking system

[0056] During locking, the elastic device 6, located between the fixed frame 1 and the movable frame 2, presses against the rear side of the movable frame 2. Simultaneously, the locking chamber of the cylinder 3 is supplied with air at a pressure of 5 MPa. The piston rod pushes the movable frame 2 to the locking position, and the movable frame 2 drives the hook 4 to be in the locking state. At this time, the cylinder 3 and the elastic device 6 work together to lock the propellant filling connector.

[0057] The locking system consists of a fixed frame 1, a movable frame 2, a hook 4, a clamping screw 43, a hook 44, a cylinder 3, an elastic device 6, a guide rod 7, an air supply line, and a solenoid reversing valve.

[0058] 2. Installation of movable frame 2 and fixed frame 1:

[0059] The end faces of three cylinders 3 are installed on the cylinder mounting holes 14 of the fixed frame 1, with the cylinder push rods in the maximum extended state. The elastic device 6 is fitted on them, and the ends of the three cylinder push rods are connected to the movable frame 2 by the cylinder connecting pin. There are three guide rods 7 in total, which are inserted into the elastic device 6 and then connected to the movable frame 2 by the cylinder connecting pin, pressing the distance between the movable frame 2 and the fixed frame 1 to a preset size (e.g., 45mm to 55mm).

[0060] The fixing frame 1 can be fixed to the connector body 5 with non-metallic bolts, serving as the base of the motion mechanism.

[0061] The three locking chambers and three releasing chambers of the three cylinders 3 are connected in parallel by rigid pipes. They are connected together by straight connectors, four-way connectors and rigid pipes to form an air supply line. Air is supplied to the air source supply port, so that the three cylinders 3 can be controlled to lock and release at the same time.

[0062] 3. Installation of hook 4:

[0063] The hook 4 is mounted on the hinge seats (i.e., the first hinge shaft support 13 and the second hinge shaft support 21) of the fixed frame 1 and the movable frame 2 via the hook pin. The hook 4 is mounted on one side of the hook pin and locked with a cap nut.

[0064] 4. Installation of clamping screw 43 and hook clamping block 44:

[0065] First, screw the clamping screw 43 into the threaded hole at the front end of the hook 4. Then, screw the hook 44 into the head of the clamping screw 43. Adjust the clamping screw 43 so that the hook 44 is about 18mm away from the inner cylindrical surface of the hook (further fine-tuning can be done as needed). Tighten the thin nut from the other end of the clamping screw 43 to form a double nut anti-loosening structure.

[0066] 5. Installation of the release push rod 9:

[0067] The separation push rod 9 is mounted on the corresponding hinge seats of the fixed frame 1 and the movable frame 2 via the first push rod pin 91 and the second push rod pin 92.

[0068] In addition, such as Figure 7 As shown, since the separating push rod 9 needs to move forward under the push of the movable frame 2 and swing along the first push rod pin 91, in order to avoid the conflict between swinging and translation, the second hinge hole 95 used to connect the second push rod pin 92 should be set as an oblong hole, while the first hinge hole 94 used to connect the first push rod pin 91 can be a regular round hole.

[0069] In the above detailed description, various features are combined together in a single embodiment to simplify this disclosure. This approach to disclosure should not be construed as reflecting an intention that embodiments of the claimed subject matter require more features than are explicitly stated in each claim. Rather, as reflected in the appended claims, the invention is presented with fewer features than all of the features of the single disclosed embodiment. Therefore, the appended claims are hereby explicitly incorporated into the detailed description, wherein each claim stands alone as a preferred embodiment of the invention.

[0070] The disclosed embodiments have been described above to enable any person skilled in the art to implement or use the present invention. Various modifications to these embodiments will be apparent to those skilled in the art, and the general principles defined herein can be applied to other embodiments without departing from the spirit and scope of this disclosure. Therefore, this disclosure is not limited to the embodiments given herein, but is consistent with the broadest scope of the principles and novel features disclosed in this application.

[0071] The specific embodiments described above further illustrate the purpose, technical solution, and beneficial effects of the present invention. It should be understood that the above description is only a specific embodiment of the present invention and is not intended to limit the scope of protection of the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A propellant loading connector, characterized in that, Includes connector body (5), fixed frame (1), movable frame (2), cylinder (3), and claw (4); The fixed frame (1) is fixedly connected to the connector body (5), the movable frame (2) is located in front of the fixed frame (1), and the movable frame (2) can move along the axial direction of the connector body (5); The cylinder (3) includes a cylinder body and a telescopic piston rod. The cylinder body is connected to the fixed frame (1), and the piston rod is connected to the movable frame (2). The front end of the hook (4) extends out of the front end face of the connector body (5), and the rear end of the hook (4) is hinged to the fixed frame (1) through the first hinge shaft (41). The hook (4) is also hinged to the movable frame (2) through the second hinge shaft (42), and the second hinge shaft (42) is located outside the first hinge shaft (41). An elastic device (6) is also provided between the fixed frame (1) and the movable frame (2), and the elastic device (6) is sleeved on the outer periphery of the piston rod; The hook (4) is a U-shaped structure formed by connecting the front section (45), the middle section (46), and the rear section (47) in sequence. The front section (45) is connected with a clamping screw (43), and the rear section (47) is provided with an inner hinge hole (48) for the first hinge shaft (41) to pass through and an outer hinge hole (49) for the second hinge shaft (42) to pass through. When the propellant refueling connector is connected to the rocket refueling port, the clamping screw (43) is in a horizontal state.

2. The propellant loading connector as described in claim 1, characterized in that, The fixing frame (1) includes a fixing frame sleeve (11) sleeved on the outside of the connector body (5) and a fixing frame flange (12) fixedly connected to the middle of the fixing frame sleeve (11). A first hinge shaft support (13) is provided at the front end of the fixing frame sleeve (11). The movable frame (2) is a disc-shaped structure sleeved on the outside of the fixed frame sleeve (11). The movable frame (2) is arranged parallel to the fixed frame flange (12). The front end of the movable frame (2) is also provided with a second hinge shaft support (21).

3. The propellant loading connector as described in claim 2, characterized in that, There are three cylinders (3), and the three cylinders (3) are evenly distributed around the circumference.

4. The propellant loading connector as described in claim 2, characterized in that, It also includes a guide rod (7); the front end of the guide rod (7) is fixedly connected to the movable frame (2), and the rear end of the guide rod (7) passes through the fixed frame (1).

5. The propellant loading connector as described in claim 4, characterized in that, There are three guide rods (7), and the guide rods (7) and the cylinder (3) are circumferentially staggered.

6. The propellant loading connector as described in claim 5, characterized in that, The elastic device (6) is sleeved on the outer side of the guide rod (7).

7. The propellant loading connector as described in claim 1, characterized in that, It also includes a claw block (44) that engages with the clamping screw (43); the end face of the clamping screw (43) is an outwardly convex spherical surface, and the inside of the claw block (44) is provided with an inwardly concave spherical surface that matches the outwardly convex spherical surface.

8. The propellant loading connector as described in claim 2, characterized in that, A separation push rod (9) is also provided on the front side of the movable frame (2); a first push rod pin (91) is provided radially on the outer side of the fixed frame sleeve (11), and the middle part of the separation push rod (9) is hinged to the first push rod pin (91); a push rod support (22) is also provided at the front end of the movable frame (2), and the fixed end of the separation push rod (9) is hinged to the push rod support (22) through a second push rod pin (92), and the second push rod pin (92) and the first push rod pin (91) are parallel to each other; the limit swing position of the movable end of the separation push rod (9) exceeds the front end face of the connector body (5).

9. The propellant loading connector as described in claim 8, characterized in that, There are three separation push rods (9) in total, and the three separation push rods (9) are evenly distributed circumferentially.

10. A dispensing device, characterized in that, It includes a propellant loading line and a propellant loading connector as described in any one of claims 1-9, wherein the front end of the propellant loading line is connected to the rear end of the connector body (5).

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