A device for locking a rocket landing leg to a rocket body

Abstract

The utility model relates to a device for locking rocket landing leg on rocket body, including first jaw, second jaw, drive mechanism, first connecting seat and lock bar, first jaw and second jaw all articulate in one end of first connecting seat and mutually symmetrical setting, the other end of first connecting seat is used for with the outer wall of rocket body body connection, one end of lock bar is detachably connected between first jaw and second jaw, the other end of lock bar swing joint has base shell, the one end of base shell away from lock bar is used for with landing leg body connection, drive mechanism installs on first connecting seat, and drive mechanism is used for driving the opening and closing of first jaw and second jaw. The device of the utility model can firmly lock the rocket landing leg in the retracted state on the rocket body, can avoid the unexpected unfolding of rocket landing leg, further will not disturb the normal flight of rocket, can also avoid damaging the adjacent parts with rocket landing leg.

Description

Technical Field

[0001] This utility model relates to the field of aerospace technology, and in particular to a device for locking rocket landing legs to the rocket body. Background Technology

[0002] Rocket landing legs are critical components ensuring stable support for the rocket body during the reentry and landing phase. To balance the aerodynamic performance during rocket flight with the support requirements during landing, rocket landing legs can be retractable. For example, during flight, the landing legs are retracted to maintain the rocket's aerodynamic shape and avoid interfering with its normal flight; while before landing, the landing legs need to be deployed quickly and reliably to provide effective support for the rocket body.

[0003] During flight (i.e., when the rocket's landing legs are retracted), the rocket body faces a complex aerodynamic environment, a severe vibration environment, and a high-intensity noise environment. The combined effect of these external loads causes the rocket body to experience a significant dynamic response. At this time, the rocket's landing legs are highly susceptible to unexpected deployment under the influence of this significant dynamic response. Such unintended deployment can not only damage components adjacent to the landing legs but also interfere with the rocket's normal flight.

[0004] Therefore, there is an urgent need for a device that can securely lock the rocket landing legs to the rocket body when the rocket landing legs are in the retracted state, in order to avoid the above situation from occurring. Utility Model Content

[0005] The purpose of this invention is to provide a device for locking rocket landing legs to the rocket body, so as to solve the problems existing in the prior art.

[0006] To achieve the above objectives, this utility model provides the following solution: This utility model provides a device for locking rocket landing legs to the rocket body, including a first gripper, a second gripper, a drive mechanism, a first connecting seat, and a locking rod, wherein: The first gripper and the second gripper are both hinged to one end of the first connecting seat and are arranged symmetrically to each other. The other end of the first connecting seat is used to connect to the outer wall of the rocket body. One end of the locking rod is detachably connected between the first gripper and the second gripper, and the other end of the locking rod is movably connected to a base connector. The end of the base connector away from the locking rod is used to connect to the landing leg body. The drive mechanism is mounted on the first connecting seat and is used to drive the opening and closing of the first gripper and the second gripper to realize the detachable connection of the locking rod between the first gripper and the second gripper.

[0007] According to one embodiment of the present invention, a first hinge shaft and a second hinge shaft are installed at the end of the first connecting seat away from the rocket body. The first gripper is hinged to the first connecting seat through the first hinge shaft, and the second gripper is hinged to the first connecting seat through the second hinge shaft.

[0008] According to one embodiment of the present invention, a latch is installed at the end of the locking rod away from the base connector, the latch is perpendicular to the locking rod, and the end of the locking rod away from the base connector is detachably connected between the first gripper and the second gripper via the latch.

[0009] According to one embodiment of the present invention, the base connector includes a base housing, one end of the locking rod near the base housing is movably connected to the base housing, and the other end of the base housing away from the locking rod is used to connect to the landing leg body; The base housing contains a base core, and the base housing has a locking rod through hole. The diameter of the locking rod through hole is larger than the cross-sectional diameter of the locking rod. One end of the locking rod near the base housing is located in the locking rod through hole and is connected to the base core by a ball joint. The locking rod is movably connected to the base housing through the ball joint connection between the locking rod and the base core.

[0010] According to one embodiment of the present invention, a vibration isolation filling layer is installed between the base housing and the base core, and the damping coefficient of the vibration isolation filling layer is 0.1-1.0.

[0011] According to one embodiment of the present invention, the driving mechanism includes a guide block, a first connecting rod, a second connecting rod, and a power unit, wherein: The guide block is mounted on the first connecting seat. The guide block has a guide arc-shaped hole. A fourth hinge shaft is slidably fitted inside the guide arc-shaped hole. One end of the first connecting rod is hinged to one end of the second connecting rod through the fourth hinge shaft. A third hinge shaft is mounted on the first gripper, and the other end of the first connecting rod is hinged to the first gripper through the third hinge shaft; a fifth hinge shaft is mounted on the second gripper, and the fifth hinge shaft is symmetrically arranged with the third hinge shaft, and the other end of the second connecting rod is hinged to the second gripper through the fifth hinge shaft. When the fourth hinge shaft abuts against the bottom inner wall of the guide arc hole, the first connecting rod and the second connecting rod are parallel and the first gripper and the second gripper are in a clamping state. The power unit is mounted on the guide block, and the power unit is used to make the fourth hinge shaft slide inside the guide arc hole to drive the opening and closing of the first gripper and the second gripper.

[0012] According to one embodiment of the present invention, the ratio of the length of the second link to the length of the first link is 5:14; The center of the guide arc-shaped hole is located on the connecting line between the third hinge axis and the fifth hinge axis when the first connecting rod and the second connecting rod are parallel, and the ratio of the straight distance between the center of the guide arc-shaped hole and the fifth hinge axis to the straight distance between the center of the guide arc-shaped hole and the third hinge axis is 13:23.

[0013] According to one embodiment of the present invention, the power unit includes a drive cylinder, the fixed end of the drive cylinder is hinged to the end of the guide block away from the first connecting seat, and the output end of the drive cylinder is connected to the fourth hinge shaft to allow the fourth hinge shaft to slide inside the guide arc-shaped hole and drive the opening and closing of the first gripper and the second gripper.

[0014] According to one embodiment of the present invention, a sixth hinge shaft is installed at the end of the guide block away from the first connecting seat, and the fixed end of the drive cylinder is hinged to the end of the guide block away from the first connecting seat through the sixth hinge shaft.

[0015] According to one embodiment of the present invention, a second connecting seat is installed at one end of the first connecting seat near the rocket body, and the end of the second connecting seat away from the first connecting seat is used to connect to the outer wall of the rocket body. The first connecting seat is connected to the outer wall of the rocket body through the second connecting seat.

[0016] Beneficial effects This utility model has at least the following technical effects: This invention, through the arrangement of a first gripper, a second gripper, a drive mechanism, and a locking rod, can securely lock and fix the retracted rocket landing legs (i.e., the landing leg body) to the rocket body (i.e., the rocket body body). This prevents the landing legs from accidentally deploying due to the large dynamic response generated during rocket flight, thus avoiding interference with the normal flight of the rocket and preventing damage to components adjacent to the landing legs. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in the embodiments of this utility model 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 this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0018] Figure 1 This is a schematic diagram of the overall structure of this utility model; Figure 2 for Figure 1 A schematic diagram of the overall structure from another angle; Figure 3 for Figure 2 A schematic diagram of the overall structure from another angle; Figure 4 This is a schematic diagram of the overall structure of the first gripper, the second gripper, the first connecting rod, and the second connecting rod in this utility model. Figure 5 for Figure 4 A schematic diagram of the overall structure from another angle; Figure 6 This is a schematic diagram of the overall structure of the guide block, the guide arc hole, and the first connecting seat in this utility model; Figure 7 for Figure 4 The diagram shows the overall structure after the addition of the guide block, the first connecting seat, and the drive cylinder. Figure 8 This is a schematic diagram of the overall structure of the first and second grippers in this utility model; Figure 9 This is a schematic diagram of the overall structure of the latch and locking rod in this utility model; Figure 10 A schematic diagram of the overall structure of the latch, locking bar, base housing, and locking bar through hole; Figure 11 for Figure 10 A cross-sectional schematic diagram of the overall structure; Figure 12 This is a schematic diagram of the overall structure of the landing leg body in the deployed state, as an example. Figure 13 This is a schematic diagram of the overall structure of the landing leg body in the retracted state, as an example. Figure 14 This is a schematic diagram illustrating the center position of an exemplary guide arc hole.

[0019] Explanation of reference numerals in the attached figures: 1. First gripper; 2. Second gripper; 3. Guide block; 4. Guide arc hole; 5. Drive cylinder; 6. First connecting seat; 7. First hinge shaft; 8. Second hinge shaft; 9. Third hinge shaft; 10. Fourth hinge shaft; 11. Fifth hinge shaft; 12. Sixth hinge shaft; 13. First connecting rod; 14. Second connecting rod; 15. Latch; 16. Locking rod; 17. Base core; 18. Base shell; 19. Vibration isolation filling layer; 20. Locking rod through hole; 21. Second connecting seat; 22. Rocket body; 23. Landing leg body; 24. Telescopic hydraulic cylinder. Detailed Implementation

[0020] The features and exemplary embodiments of various aspects of this utility model will be described in detail below. To make the objectives, technical solutions, and advantages of this utility model clearer, the following detailed description is provided in conjunction with the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are only configured to explain this utility model and to exemplarily illustrate the principles of this utility model, and are not configured to limit this utility model. In addition, the structural components in the drawings are not necessarily drawn to scale. For example, the dimensions of some structural components or regions in the drawings may be enlarged for other structural components or regions to aid in the understanding of the embodiments of this utility model.

[0021] The directional terms used in the following description refer to the directions shown in the figures and are not intended to limit the specific structure of the embodiments of this utility model. In the description of this utility model, it should be noted that, unless otherwise stated, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0022] Furthermore, the terms "comprising," "including," "having," or any other variations thereof are intended to cover non-exclusive inclusion, such that a structure or component that includes a list of elements includes not only those elements but also other structural elements that are not expressly listed or inherent to the structure or component. Without further limitations, an element defined by the phrase "comprising..." does not exclude the presence of other identical elements in the article or apparatus that includes the element.

[0023] Spatial relation terms such as "below," "under," "under," "low," "above," "on," and "high" are used for descriptive convenience to explain the positioning of one element relative to a second element, indicating that these terms are intended to cover different orientations of the device, in addition to those different from those shown in the figure. Furthermore, phrases such as "one element on / below another element" can indicate that two elements are in direct contact, or that there are other elements between the two elements. In addition, terms such as "first" and "second" are also used to describe individual elements, areas, parts, etc., without specifically indicating order or sequence, and should not be considered restrictive. Similar terms are used throughout the description to represent similar elements.

[0024] For those skilled in the art, this invention can be implemented without some of these specific details. The following description of the embodiments is merely intended to provide a better understanding of the invention by illustrating examples.

[0025] In the following embodiments, there may be descriptions such as "this device". Those skilled in the art should understand that "this device" refers to a device provided by the present invention for locking the landing legs of a rocket to the rocket body.

[0026] like Figures 1-11 As shown, this utility model provides a device for locking the landing legs of a rocket to the rocket body.

[0027] like Figure 1 , Figure 2 and Figure 3 As shown, this device includes at least a first gripper 1, a second gripper 2, a drive mechanism, a first connecting seat 6, and a locking rod 16, wherein: like Figure 1 , Figure 2 and Figure 3 As shown, both the first gripper 1 and the second gripper 2 are hinged to one end of the first connecting seat 6 (i.e. Figure 1 The bottom end of the first connecting seat 6) and they are arranged symmetrically with each other (i.e. Figure 1 The left and right sides are symmetrically arranged), the other end of the first connecting seat 6 (i.e. Figure 1 The top of the first connecting seat 6 is used to connect with the outer wall of the rocket body 22 (the connected state can be referred to). Figure 12 and Figure 13 ).

[0028] In this embodiment, the rocket body 22 is a prior art known in the art, and will not be described in detail here.

[0029] In this embodiment, as Figure 1 , Figure 2 , Figure 4 and Figure 5 As shown, the first gripper 1 and the second gripper 2 can be or are approximately "mirror-symmetric" (i.e., symmetrically arranged as described above) structures (i.e., the size and shape are the same or approximately the same), and the bottom ends of the first gripper 1 and the second gripper 2 (i.e., Figure 5 The bottom ends of the first gripper 1 and the second gripper 2 can be or are approximately inwardly concave.

[0030] In one embodiment of this utility model, specifically, as follows: Figure 1 , Figure 2 and Figure 3 As shown, the end of the first connecting seat 6 furthest from the rocket body 22 (i.e. Figure 1 The bottom end of the first connecting seat 6 is rotatably mounted with a first hinge shaft 7 and a second hinge shaft 8. The first gripper 1 can be hinged to the first connecting seat 6 via the first hinge shaft 7, and the second gripper 2 can be hinged to the first connecting seat 6 via the second hinge shaft 8, thereby realizing the mutual hinge between the first gripper 1 and the first connecting seat 6, and the second gripper 2 and the first connecting seat 6, respectively.

[0031] Furthermore, in order to further improve the firmness of the connection between the first connecting seat 6 and the outer wall of the rocket body 22, and thus further improve the firmness of the connection between this device and the outer wall of the rocket body 22, such as... Figure 1 , Figure 2 and Figure 3 As shown, the first connecting seat 6 is located at one end near the rocket body 22 (i.e., Figure 1 A second connector 21 is installed at the top of the first connector 6. The end of the second connector 21 that is away from the first connector 6 (i.e. Figure 1 The top of the second connecting seat 21 is used to connect with the outer wall of the rocket body 22, that is, the first connecting seat 6 can be connected to the outer wall of the rocket body 22 through the second connecting seat 21.

[0032] In this embodiment, the first connecting seat 6 can be connected to the second connecting seat 21 by a bolt connection (not shown in the figure) known in the art, and the second connecting seat 21 can also be connected to the outer wall of the rocket body 22 by a bolt connection (not shown in the figure) known in the art, without any particular limitation.

[0033] In this embodiment, the second connecting seat 21 is located at one end near the rocket body 22 (i.e., Figure 1 The top of the second connecting seat 21 can be a shape or structure that is adapted to the outer wall of the rocket body 22, so that the connection between the second connecting seat 21 and the outer wall of the rocket body 22 can be more firm and stable.

[0034] like Figure 1 , Figure 2 and Figure 3 As shown, one end of the locking lever 16 (i.e. Figure 1 The top end of the locking rod 16 is detachably connected between the first gripper 1 and the second gripper 2. That is, when the first gripper 1 and the second gripper 2 are in the clamping state, they can clamp the locking rod 16; when the first gripper 1 and the second gripper 2 are in the open state, they can release the clamp on the locking rod 16. The other end of the locking rod 16 (i.e....) Figure 1 The bottom end of the locking bar 16 is movably connected to a base connector, and the end of the base connector away from the locking bar 16 is used to connect to the landing leg body 23.

[0035] In this embodiment, the landing leg body 23 is a prior art known in the art, and the landing leg body 23 is the rocket landing leg. When the rocket body 22 lands, the landing leg body 23 can provide support for the rocket body 22, which will not be described in detail here.

[0036] In one embodiment of this utility model, specifically, as follows: Figure 1 , Figure 2 , Figure 3 , Figure 9 , Figure 10 and Figure 11 As shown, the end of the locking lever 16 furthest from the base connector (i.e. Figure 1 A latch 15 is installed at the top of the locking rod 16, meaning that the end of the locking rod 16 away from the base connector can be detachably connected between the first gripper 1 and the second gripper 2 via the latch 15.

[0037] In this embodiment, as Figure 9 , Figure 10 and Figure 11 As shown, both the latch 15 and the locking bar 16 can be cylindrical or approximately cylindrical in shape, and they can be arranged perpendicularly to each other, i.e., they will form or approximately form a T-shape. For example, Figure 5 As shown, due to the bottom ends of the first gripper 1 and the second gripper 2 (i.e. Figure 5 The bottom ends of the first clamping jaw 1 and the second clamping jaw 2 are inwardly converging. Therefore, when the first clamping jaw 1 and the second clamping jaw 2 are in the convergent state, a roughly cylindrical cavity is formed between the first clamping jaw 1 and the second clamping jaw 2. The latch 15 can be clamped in the cavity by the first clamping jaw 1 and the second clamping jaw 2, that is, the first clamping jaw 1 and the second clamping jaw 2 clamp the locking bar 16 (that is, the locking bar 16 is detachably connected between the first clamping jaw 1 and the second clamping jaw 2).

[0038] Furthermore, in order to reduce vibration transmission between the landing leg body 23 and the rocket body 22, and to better prevent damage to the device, the landing leg body 23, and the rocket body 22, such as Figure 1 and Figure 11 As shown, the base connector includes at least a base housing 18, and a locking rod 16 at one end near the base housing 18 (i.e., Figure 1 The bottom end of the locking rod 16 is movably connected to the base housing 18, and the end of the base housing 18 furthest from the locking rod 16 (i.e., Figure 1 The bottom end of the base housing 18 is used to connect with the landing leg body 23 (the connected state can be referred to). Figure 12 and Figure 13 ), among which, such as Figure 11 As shown, a base core 17 is installed inside the base housing 18, and a base core 17 is mounted on the base housing 18 (i.e. Figure 11 A locking rod through hole 20 is provided at the top of the base housing 18, and the diameter of the locking rod through hole 20 is larger than the cross-sectional diameter of the locking rod 16. That is, the inner wall of the locking rod through hole 20 does not contact the outer wall of the locking rod 16, and there will be a certain gap between them. The end of the locking rod 16 closest to the base housing 18 (i.e., Figure 11 The bottom end of the locking rod 16 is located inside the locking rod through hole 20 and is connected to the top end of the base core 17 (i.e., Figure 11 The top of the base core 17 is connected by a ball joint (i.e., the aforementioned locking rod 16 is movably connected to the base housing 18). The locking rod 16 can be movably connected to the base core 17 and the base housing 18 through its ball joint connection. For example, Figure 11 As shown, there is a certain gap between the base housing 18 and the base core 17, and a vibration isolation filling layer 19 is installed between the base housing 18 and the base core 17. The damping coefficient of the vibration isolation filling layer 19 can be 0.1-1.0.

[0039] In this embodiment, as Figure 10 As shown, the base housing 18 can be or approximately a frustum-shaped structure, and the base core 17 can also be or approximately a frustum-shaped structure, without any particular limitation.

[0040] In this embodiment, the bottom end of the base core 17 (i.e. Figure 11 The bottom end of the base core 17 can abut against or connect with the landing leg body 23. Both the base housing 18 and the base core 17 can be connected to the landing leg body 23 using bolts, a method known in the art, and are not specifically limited herein.

[0041] In this embodiment, the vibration isolation filling layer 19 is a known material in the art, such as high-temperature resistant rubber, which will not be described in detail here.

[0042] In this embodiment, the damping coefficient of the vibration isolation filling layer 19 can preferably be 0.5, that is, the vibration isolation filling layer 19 can preferably be a high-temperature resistant rubber with a damping coefficient of 0.5 known in the art, and is not particularly limited here.

[0043] In this embodiment, since the end of the locking rod 16 near the base housing 18 is located inside the locking rod through hole 20 and is ball-jointed to the top of the base core 17, and the diameter of the locking rod through hole 20 is larger than the cross-sectional diameter of the locking rod 16, the locking rod 16 can move freely within the locking rod through hole 20. Wherein, as Figure 11 As shown, the vibration isolation filling layer 19 does not contact the outer wall of the locking rod 16, that is, there will be a certain gap between the two, so as not to interfere with the free movement of the locking rod 16 in the locking rod through hole 20.

[0044] According to one embodiment of the present invention, the drive mechanism is installed on the first connecting seat 6. The drive mechanism can be used to drive (i.e. control) the opening and closing of the first gripper 1 and the second gripper 2, thereby realizing the detachable connection between the locking rod 16 and the first gripper 1 and the second gripper 2, that is, realizing the clamping of the locking rod 16 by the first gripper 1 and the second gripper 2 or realizing the release of the clamping of the locking rod 16 by the first gripper 1 and the second gripper 2.

[0045] In one embodiment of this utility model, specifically, as follows: Figure 1 , Figure 2 , Figure 3 , Figure 6 and Figure 7 As shown, the drive mechanism includes at least a guide block 3, a first link 13, a second link 14, and a power unit, wherein: The guide block 3 is mounted on the first connecting seat 6. The guide block 3 has a guide arc-shaped hole 4, and a fourth hinge shaft 10 is slidably fitted inside the guide arc-shaped hole 4. One end of the first connecting rod 13 (i.e....) Figure 1 The left end of the first link 13 can be connected to one end of the second link 14 (i.e., the left end of the first link 13) via the fourth hinge shaft 10. Figure 1 The left ends of the second link 14 are hinged to each other.

[0046] In this embodiment, the guide block 3 can be located on the side of the second gripper 2 away from the first gripper 1, that is, the second gripper 2 will be located between the guide block 3 and the first gripper 1, which is not particularly limited here.

[0047] like Figure 1 , Figure 2 , Figure 3 and Figure 4 As shown, a third hinge shaft 9 is mounted on the first gripper 1, and the other end of the first connecting rod 13 (i.e. Figure 1 The right end of the first connecting rod 13 can be hinged to the first gripper 1 via the third hinge shaft 9. A fifth hinge shaft 11 is mounted on the second gripper 2, and the fifth hinge shaft 11 and the third hinge shaft 9 are symmetrically arranged (symmetrically arranged with the midpoint between the first gripper 1 and the second gripper 2 as the axis of symmetry). The other end of the second connecting rod 14 (i.e....) Figure 1 The right end of the second link 14 can be hinged to the second gripper 2 via the fifth hinge shaft 11.

[0048] In this embodiment, the third hinge shaft 9 can be located slightly to the right of approximately the center of the first gripper 1 (i.e., Figure 1 At the right end of the middle, the fifth hinge shaft 11 can be located slightly to the left of the approximate middle position of the second gripper 2 (i.e., Figure 1 The left end of the text is not specifically defined here.

[0049] In this embodiment, as Figure 4 As shown, the first link 13 and the second link 14 can both be rod-shaped structures that are slightly narrower in the middle and slightly wider at both ends, and no special limitation is made here.

[0050] In this embodiment, when the bottom end of the fourth hinge shaft 10 (i.e. Figure 1 The bottom end of the fourth hinge shaft 10 and the inner wall of the bottom end of the guide arc hole 4 (i.e. Figure 1 When the inner walls of the bottom end of the guide arc hole 4 abut against each other, the first link 13 and the second link 14 will be in a parallel state, and the first gripper 1 and the second gripper 2 will be in a clamping state (i.e., a holding state) at the same time.

[0051] In this embodiment, the power unit is mounted on the guide block 3. The power unit is used to make the fourth hinge shaft 10 slide inside the guide arc-shaped hole 4, thereby driving the opening and closing of the first gripper 1 and the second gripper 2. That is, the power unit can provide power to make the first gripper 1 and the second gripper 2 be in an open or closed state.

[0052] In this embodiment, specifically, as Figure 1 and Figure 7 As shown, the power unit includes at least one drive cylinder 5. The fixed end of the drive cylinder 5 is hinged to the end of the guide block 3 away from the first connecting seat 6 (i.e., Figure 7 The bottom end of the guide block 3), the output end of the drive cylinder 5 (that is, the extension end of the drive cylinder 5) is connected to the fourth hinge shaft 10 to make the fourth hinge shaft 10 slide inside the guide arc hole 4 and drive the opening and closing of the first gripper 1 and the second gripper 2 so that the first gripper 1 and the second gripper 2 are in an open or closed state.

[0053] In this embodiment, the drive cylinder 5 is a prior art known in the art and is not particularly limited herein.

[0054] In this embodiment, the drive cylinder 5 can be supplied with air by an air supply assembly (not shown in the figure and known in the art) installed on the rocket body 22, thereby controlling the extension and retraction of the drive cylinder 5. Details will not be elaborated here.

[0055] In this embodiment, more specifically, such as Figure 1 and Figure 7 As shown, the end of the guide block 3 furthest from the first connector 6 (i.e. Figure 7 A sixth hinge shaft 12 is mounted on the bottom end of the guide block 3. The fixed end of the drive cylinder 5 can be connected to the end of the guide block 3 away from the first connecting seat 6 via the sixth hinge shaft 12. Figure 7 The bottom ends of the middle guide block 3 are hinged together.

[0056] In one embodiment of this utility model, the length of the second connecting rod 14, the length of the first connecting rod 13, and the center position of the guide arc hole 4 can be set as follows (i.e., including but not limited to): like Figure 14 As shown, the ratio of the length of the second link 14 to the length of the first link 13 can be 5:14. The center of the guide arc hole 4 will be located on the connecting line between the third hinge shaft 9 and the fifth hinge shaft 11 when the first link 13 and the second link 14 are parallel to each other (i.e., when the bottom end of the fourth hinge shaft 10 abuts against the inner wall of the bottom end of the guide arc hole 4, i.e., when the first gripper 1 and the second gripper 2 are in the closed state), and the center o of the guide arc hole 4 (the center of the guide arc hole 4 is...) Figure 14 The ratio of the straight-line distance between the point marked o and the fifth hinge axis 11 and the straight-line distance between the center o of the guide arc hole 4 and the third hinge axis 9 can be 13:23.

[0057] In this embodiment, the first hinge axis 7, the second hinge axis 8, the third hinge axis 9, the fourth hinge axis 10, the fifth hinge axis 11, and the sixth hinge axis 12 (i.e., hinge axes) are all prior art known in the art, and will not be described in detail here.

[0058] The most preferred operating process of this device will be briefly described below with reference to the above embodiments: like Figure 12 and Figure 13 As shown, Figure 12 This is an exemplary schematic diagram of the overall structure of the landing leg body 23 in the deployed state. Figure 13 This is an exemplary schematic diagram of the overall structure of the landing leg body 23 in the retracted state. One end of the landing leg body 23 can be hinged to the bottom outer wall of the rocket body 22, and the other end of the landing leg body 23 is hinged to a telescopic hydraulic cylinder 24 (also known as a multi-stage hydraulic cylinder) known in the art. The other end of the telescopic hydraulic cylinder 24 is hinged to the outer wall of the rocket body 22.

[0059] When the landing leg body 23 needs to be retracted (i.e., by...) Figure 12 The state becomes Figure 13When the landing leg body 23 is in the retracted state, the telescopic hydraulic cylinder 24 will retract, thereby driving the landing leg body 23 to retract. Specifically, when the landing leg body 23 retracts to the position where the latch 15 installed on the landing leg body 23 is located at the position of the first gripper 1 and the second gripper 2 installed on the outer wall of the rocket body 22, the drive cylinder 5 will simultaneously retract and drive the fourth hinge shaft 10 towards the guide arc-shaped hole 4. Figure 1 When the lever moves downwards, the first link 13 and the second link 14 will cause the first gripper 1 and the second gripper 2 to close (i.e., be in a clamping state), thereby clamping the latch 15. Since the latch 15 is connected to the landing leg body 23 through the locking rod 16 and the base housing 18, clamping the latch 15 is equivalent to clamping the retracted landing leg body 23. This means that the retracted rocket landing leg (i.e., the landing leg body 23) can be firmly locked and fixed on the rocket body (i.e., the rocket body 22), thus preventing the landing leg body 23 from being accidentally deployed due to the large dynamic response generated during rocket flight. This will not interfere with the normal flight of the rocket and will also prevent damage to the components adjacent to the landing leg body 23.

[0060] Conversely, when the landing leg body 23 needs to be deployed (i.e., by...) Figure 13 The state becomes Figure 12 When in the state of extension, the telescopic hydraulic cylinder 24 will extend, at which time the fourth hinge shaft 10 is positioned within the guide arc hole 4 towards... Figure 1 The system moves upwards, and simultaneously the first gripper 1 and the second gripper 2 open (i.e., in the open state). After opening, the telescopic hydraulic cylinder 24 extends, thereby allowing the landing leg body 23 to unfold, thus providing support for the rocket body 22 that is landing or about to land.

[0061] In some embodiments of this utility model, the telescopic hydraulic cylinder 24 may also be a telescopic pneumatic cylinder known in the art, and no particular limitation is made here.

[0062] It should be understood that in some embodiments of this utility model, the telescopic hydraulic cylinder 24 is also known as the "landing leg main leg" and the landing leg body 23 is also known as the "landing leg auxiliary leg", which will not be elaborated here.

[0063] In this embodiment, the device installed on the rocket body 22 and the landing leg body 23 can be one or more (e.g., Figure 12 and Figure 13 (The two mentioned above) are not specifically limited here.

[0064] In this embodiment, the present invention also has at least the following technical effects: Firstly, this device can move the first connecting rod 13 and the second connecting rod 14 using a single drive cylinder 5. The movement of the first connecting rod 13 and the second connecting rod 14 synchronously drives the first gripper 1 and the second gripper 2 to open or close. In other words, the opening or closing of the first gripper 1 and the second gripper 2 can be achieved with a single drive cylinder 5. Therefore, compared to traditional structures or methods that require individual control of each gripper, this device optimizes the overall operation and improves work efficiency.

[0065] Secondly, due to the structure or method of controlling each gripper individually, the movement of the two grippers is prone to incoordination, which in turn affects the gripping of the object by the two grippers. However, this device uses a drive cylinder 5 to drive the first link 13 and the second link 14 to move simultaneously, which enables the two grippers (i.e., the first gripper 1 and the second gripper 2) to move in coordination, thus preventing the two grippers (i.e., the first gripper 1 and the second gripper 2) from moving incoordination. This allows the first gripper 1 and the second gripper 2 to grip the latch 15 (that is, the first gripper 1 and the second gripper 2) more firmly and stably.

[0066] Finally, when the first gripper 1 and the second gripper 2 are in the closed state (that is, when the bottom end of the fourth hinge shaft 10 abuts against the inner wall of the bottom end of the guide arc hole 4), since the first link 13 and the second link 14 are in a parallel state, the first gripper 1 and the second gripper 2 in the closed state can be "self-locked", thereby effectively preventing the first gripper 1 and the second gripper 2 from being accidentally opened, so that the first gripper 1 and the second gripper 2 can hold the latch 15 (that is, the first gripper 1 and the second gripper 2 against the landing leg body 23) more firmly and stably.

[0067] It should be understood that the above-described embodiments or examples of this utility model can be combined with each other and have corresponding technical effects.

[0068] The above are merely preferred embodiments of the present utility model and are not intended to limit the present utility model. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present utility model shall be included within the protection scope of the present utility model.

Claims

1. A device for locking rocket landing legs to the rocket body, characterized in that, It includes a first gripper (1), a second gripper (2), a drive mechanism, a first connecting seat (6), and a locking bar (16), wherein: The first gripper (1) and the second gripper (2) are both hinged to one end of the first connecting seat (6) and are arranged symmetrically to each other. The other end of the first connecting seat (6) is used to connect to the outer wall of the rocket body (22). One end of the locking rod (16) is detachably connected between the first gripper (1) and the second gripper (2), and the other end of the locking rod (16) is movably connected to a base connector. The end of the base connector away from the locking rod (16) is used to connect to the landing leg body (23). The drive mechanism is mounted on the first connecting seat (6). The drive mechanism is used to drive the opening and closing of the first gripper (1) and the second gripper (2) to realize the detachable connection of the locking rod (16) between the first gripper (1) and the second gripper (2).

2. The device for locking rocket landing legs to the rocket body according to claim 1, characterized in that, The first connecting seat (6) is equipped with a first hinge shaft (7) and a second hinge shaft (8) at one end away from the rocket body (22). The first gripper (1) is hinged to the first connecting seat (6) through the first hinge shaft (7), and the second gripper (2) is hinged to the first connecting seat (6) through the second hinge shaft (8).

3. The device for locking rocket landing legs to the rocket body according to claim 1, characterized in that, A latch (15) is installed at the end of the locking rod (16) away from the base connector. The latch (15) is perpendicular to the locking rod (16). The end of the locking rod (16) away from the base connector is detachably connected between the first gripper (1) and the second gripper (2) through the latch (15).

4. The device for locking rocket landing legs to the rocket body according to claim 3, characterized in that, The base connector includes a base housing (18), one end of the locking rod (16) near the base housing (18) is movably connected to the base housing (18), and the other end of the base housing (18) away from the locking rod (16) is used to connect to the landing leg body (23). The base housing (18) has a base core (17) installed inside. The base housing (18) has a locking rod through hole (20) with a diameter larger than the cross-sectional diameter of the locking rod (16). The end of the locking rod (16) near the base housing (18) is located in the locking rod through hole (20) and is ball-jointed to the base core (17). The locking rod (16) is movably connected to the base housing (18) through its ball-joint connection with the base core (17).

5. The device for locking rocket landing legs to the rocket body according to claim 4, characterized in that, A vibration isolation filling layer (19) is installed between the base housing (18) and the base core (17), and the damping coefficient of the vibration isolation filling layer (19) is 0.1-1.

0.

6. The device for locking rocket landing legs to the rocket body according to claim 1, characterized in that, The drive mechanism includes a guide block (3), a first link (13), a second link (14), and a power unit, wherein: The guide block (3) is installed on the first connecting seat (6). The guide block (3) has a guide arc hole (4). The guide arc hole (4) is slidably fitted with a fourth hinge shaft (10). One end of the first connecting rod (13) is hinged to one end of the second connecting rod (14) through the fourth hinge shaft (10). A third hinge shaft (9) is installed on the first gripper (1), and the other end of the first connecting rod (13) is hinged to the first gripper (1) through the third hinge shaft (9); a fifth hinge shaft (11) is installed on the second gripper (2), and the fifth hinge shaft (11) is symmetrically arranged with the third hinge shaft (9), and the other end of the second connecting rod (14) is hinged to the second gripper (2) through the fifth hinge shaft (11); When the fourth hinge shaft (10) abuts against the bottom inner wall of the guide arc hole (4), the first connecting rod (13) and the second connecting rod (14) are parallel and the first gripper (1) and the second gripper (2) are in a clamping state; The power unit is mounted on the guide block (3) and is used to make the fourth hinge shaft (10) slide inside the guide arc hole (4) to drive the opening and closing of the first gripper (1) and the second gripper (2).

7. The device for locking rocket landing legs to the rocket body according to claim 6, characterized in that, The ratio of the length of the second link (14) to the length of the first link (13) is 5:14; The center of the guide arc hole (4) is located on the connecting line of the third hinge shaft (9) and the fifth hinge shaft (11) when the first connecting rod (13) and the second connecting rod (14) are parallel, and the ratio of the straight distance between the center of the guide arc hole (4) and the fifth hinge shaft (11) to the straight distance between the center of the guide arc hole (4) and the third hinge shaft (9) is 13:

23.

8. The device for locking rocket landing legs to the rocket body according to claim 6, characterized in that, The power unit includes a drive cylinder (5), the fixed end of which is hinged to the end of the guide block (3) away from the first connecting seat (6), and the output end of the drive cylinder (5) is connected to the fourth hinge shaft (10) to make the fourth hinge shaft (10) slide inside the guide arc hole (4) and drive the opening and closing of the first gripper (1) and the second gripper (2).

9. The device for locking rocket landing legs to the rocket body according to claim 8, characterized in that, The guide block (3) is equipped with a sixth hinge shaft (12) at one end away from the first connecting seat (6), and the fixed end of the drive cylinder (5) is hinged to the end of the guide block (3) away from the first connecting seat (6) through the sixth hinge shaft (12).

10. The device for locking rocket landing legs to the rocket body according to claim 1, characterized in that, The first connecting seat (6) is equipped with a second connecting seat (21) at one end near the rocket body (22). The end of the second connecting seat (21) away from the first connecting seat (6) is used to connect with the outer wall of the rocket body (22). The first connecting seat (6) is connected to the outer wall of the rocket body (22) through the second connecting seat (21).

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