A high-rigidity extension locking mechanism

Abstract

This invention relates to a high-rigidity extension locking mechanism, belonging to the field of extension locking mechanism design; it includes a fixed stage, an extension stage, and four automatic screw-in locking devices; both the fixed stage and the extension stage are hollow cuboid structures; the fixed stage is fitted onto the outer wall of the extension stage; the four automatic screw-in locking devices are respectively installed on the inner walls of the four corners of the extension stage; initially, the fixed stage and the extension stage are aligned, and the extension stage is limited and locked by the four automatic screw-in locking devices; under the action of external force, the extension stage extends axially out of the fixed stage; when the extension stage extends to its full position, the relative position of the fixed stage and the extension stage is locked by the four automatic screw-in locking devices; this invention solves the problem that it is difficult to achieve high-rigidity locking through threaded connections in the unmanned state of spacecraft extension mechanisms in orbit.

Description

Technical Field

[0001] This invention belongs to the field of extension locking mechanism design and relates to a high-rigidity extension locking mechanism. Background Technology

[0002] With the rapid expansion of space missions, the limitations of the overall payload envelope size of launch vehicles necessitate the use of foldable or deformable mechanisms and related technologies to achieve the goal of sending specific payloads into space from folding to unfolding and locking. The demand for large-scale space extension devices, especially those with small folded volume and large unfolded size, is becoming increasingly urgent.

[0003] In unmanned environments such as spacecraft, to achieve high-rigidity locking of extension mechanisms after deployment, or to ensure effective connection and locking of different extension components after deployment, various locking and connection technologies have been developed, including hook-type locking methods, pin-type locking methods, and self-deployment technologies utilizing the elastic deformation of materials. Each locking and connection method has its own characteristics, but all possess the function of automatic locking after deployment.

[0004] Based on the characteristics of methods such as hook-type locking and pin-type locking, it is necessary to increase the contact area of ​​the locking components to improve the connection rigidity of the lock. However, due to factors such as the machining precision of different locking device components and the deformation of the parts themselves, the locking contact of the locking device is usually point contact or line contact, and the locking rigidity is difficult to meet the high rigidity locking requirements of large extension mechanisms.

[0005] Threaded connections, as a classic and reliable form of connection, are widely used in many industries. Because the screwing action in a threaded connection requires both pressing and rotating the screw, these actions must be coordinated to achieve tightening. Therefore, threaded connections are typically performed by operators or robots, who screw the screws and other connecting components into the connected parts to achieve a reliable connection. Consequently, threaded connections are a commonly used high-rigidity, high-reliability connection method on the ground.

[0006] Spacecraft extension mechanisms typically operate unmanned during in-orbit extension and locking, or are otherwise constrained by workspace and environment, making it difficult to perform by astronauts or robots. Furthermore, the significant costs associated with robotic operation, such as weight, development costs, and system complexity, make it impractical. Therefore, achieving high-rigidity extension and locking via threaded connections on spacecraft—that is, realizing a simple and reliable unmanned automatic threading action—remains an unsolved problem. Summary of the Invention

[0007] The technical problem solved by this invention is to overcome the shortcomings of the prior art and propose a high-rigidity extension locking mechanism, which solves the problem that it is difficult to achieve high-rigidity locking of the spacecraft extension mechanism in an unmanned on-orbit state through threaded connection.

[0008] The solution of the present invention is:

[0009] A high-rigidity extension locking mechanism includes a fixed stage, an extension stage, and four automatic screw-in locking devices.

[0010] Both the fixed stage and the extension stage are hollow cuboid structures. The fixed stage is fitted onto the outer wall of the extension stage. Four automatic screw-in locking devices are installed on the inner walls of the four corners of the extension stage. In the initial state, the fixed stage and the extension stage are overlapped, and the extension stage is limited and locked by the four automatic screw-in locking devices. Under the action of external force, the extension stage extends axially out of the fixed stage. When the extension stage extends into place, the relative positions of the fixed stage and the extension stage are locked by the four automatic screw-in locking devices.

[0011] In the aforementioned high-rigidity extension locking mechanism, each side wall of the fixed stage is provided with a release control bracket and a limiting threaded hole; the release control bracket is perpendicular to the inner wall of the corresponding side wall of the fixed stage and located at the corner of the fixed stage; the limiting threaded hole is located at the center of the corresponding side wall of the fixed stage and in the extension direction of the extension stage; the side wall corresponding to the extension stage is located on the inner wall of the side wall of the fixed stage; the corresponding automatic screw-in locking device is installed on the side wall of the extension stage, and the limiting of the release control bracket side wall by the release control bracket side wall achieves the limiting and locking of the extension stage in the initial state.

[0012] In the aforementioned high-rigidity extension locking mechanism, the automatic screw-in locking device includes a loading bracket, a loading support shaft, a loading coil spring, a transmission rod, a locking cylinder, a locking rod, a spring, and a drive rod;

[0013] The loading bracket has a Z-shaped structure; the bottom of the loading bracket is installed on the inner wall of the extension stage sidewall; the top of the loading bracket is suspended; the loading support shaft is vertically positioned on the top of the loading bracket, and the bottom end of the loading support shaft extends downwards from the top of the loading bracket; the loading coil spring is fitted on the outer wall of the loading support shaft; the transmission rod is vertically positioned on the outer edge of the loading coil spring; the locking cylinder is coaxially positioned below the loading support shaft; the locking rod extends coaxially into the locking cylinder; the spring is fitted on the outer wall of the locking rod; the drive rod is a horizontally positioned rod-shaped structure; the drive rod is fitted on the top outer wall of the locking rod; the bottom end of the transmission rod passes through the drive rod.

[0014] In the aforementioned high-rigidity extension locking mechanism, the locking rod has a stepped structure, and the stepped structure is located in the inner cavity of the locking cylinder, so that the top of the spring contacts the lower surface of the top of the locking cylinder, and the bottom of the spring contacts the upper surface of the stepped structure of the locking rod.

[0015] In the aforementioned high-rigidity extension locking mechanism, the extension stage has a through hole on its corresponding side wall, and the bottom end of the locking rod extends into the through hole; the outer wall of the bottom end of the locking rod has a threaded structure, and the thread corresponds to the limiting threaded hole.

[0016] In the aforementioned high-rigidity extension locking mechanism, in the initial state, the bottom end of the locking rod is in contact with the upper surface of the fixed stage, and the spring is in a vertically compressed state.

[0017] In the aforementioned high-rigidity extension locking mechanism, in the initial state, the drive rod is clamped by the left side wall of the release control bracket, thereby limiting the movement between the extension stage side wall and the fixed stage side wall; at this time, the loading coil spring is in a compressed state.

[0018] In the aforementioned high-rigidity extension locking mechanism, under the action of external force, the side wall of the extension stage translates relative to the side wall of the fixed stage until the drive rod disengages from the limit of the release control bracket; in the state of the released coil spring, the drive rod is driven to rotate through the transmission rod.

[0019] In the aforementioned high-rigidity extension locking mechanism, when the drive rod disengages from the limit of the release control bracket, the bottom end of the locking rod moves to the limit threaded hole, and under the action of the spring return force, the bottom end of the locking rod extends into the limit threaded hole.

[0020] In the aforementioned high-rigidity extension locking mechanism, the locking rod is rotated by the drive rod, and the locking rod is pushed down by the spring, so as to achieve threaded engagement between the locking rod and the limiting threaded hole; at the same time, the drive rod is clamped on the right side wall of the release control bracket to achieve limiting.

[0021] The advantages of this invention compared to the prior art are:

[0022] (1) The present invention provides a high-rigidity extension locking mechanism for spacecraft extension components after they are extended into place, through a threaded connection between the extension components and the relatively fixed components.

[0023] (2) The extension locking mechanism of the present invention can realize self-energy storage in the unlocked state, and does not require power supply or external input force or torque during operation;

[0024] (3) When the extension component of the extension mechanism of the present invention is extended into place and high rigidity locking is required, the mechanism automatically presses in and screws in the screw to realize the threaded locking connection between the connecting part and the connected part, which solves the problem that it is difficult to achieve high rigidity locking through threaded connection in the unmanned state of the spacecraft extension mechanism in orbit. Attached Figure Description

[0025] Figure 1 This is a schematic diagram of the retracted state of the extension locking mechanism of the present invention;

[0026] Figure 2 This is a schematic diagram of the extended locking mechanism of the present invention in its extended state;

[0027] Figure 3 This is a schematic diagram of the installation of one of the automatic screw-in locking devices of the present invention;

[0028] Figure 4 This is a schematic diagram of the automatic screw-in locking device of the present invention;

[0029] Figure 5 This is a schematic diagram showing the positions of the fixed-stage sidewall and the extended-stage sidewall in the initial state of the present invention;

[0030] Figure 6 This is a schematic diagram showing the positions of the fixed-stage sidewall and the extended-stage sidewall after the present invention has been extended into place. Detailed Implementation

[0031] The present invention will be further described below in conjunction with the embodiments.

[0032] This invention discloses a high-rigidity extension locking mechanism, which can be used in spacecraft extension mechanisms to achieve high-rigidity extension locking after the extension component has extended to its final position, through a threaded connection between the extension component and a relatively fixed component. The extension mechanism can self-store energy in the unlocked state, requiring no power or external force or torque input during operation. When the extension component of the extension mechanism has extended to its final position and high-rigidity locking is required, the mechanism automatically presses in and screws in a screw, achieving a threaded locking connection between the connecting component and the connected component. This solves the problem of achieving high-rigidity locking through threaded connections in unmanned, on-orbit spacecraft extension mechanisms.

[0033] High-rigidity extension locking mechanisms, such as Figure 1 Specifically, it includes a fixed stage 7, an extension stage 8, and four automatic screw-in locking devices 9. Both the fixed stage 7 and the extension stage 8 are hollow cuboid structures; the fixed stage 7 is fitted onto the outer wall of the extension stage 8; the four automatic screw-in locking devices 9 are respectively installed on the inner walls of the four corners of the extension stage 8; initially, the fixed stage 7 and the extension stage 8 are aligned, and the four automatic screw-in locking devices 9 limit and lock the extension stage 8; under external force, the extension stage 8 extends axially out of the fixed stage 7; when the extension stage 8 is fully extended, the four automatic screw-in locking devices 9 lock the relative positions of the fixed stage 7 and the extension stage 8, as shown below. Figure 2 As shown.

[0034] like Figure 3As shown, each side wall of the fixed stage 7 is provided with a release control bracket 71 and a limiting threaded hole 72; the release control bracket 71 is perpendicular to the inner wall of the corresponding side wall of the fixed stage 7 and is located at the corner of the fixed stage 7; the limiting threaded hole 72 is located at the center of the corresponding side wall of the fixed stage 7 and is located in the extension direction of the extension stage 8; the side wall corresponding to the extension stage 8 is located on the inner wall of the side wall of the fixed stage 7; the corresponding automatic screw-in locking device 9 is installed on the side wall of the extension stage 8, and the release control bracket 71 side wall limits the release control bracket 71 side wall, thereby achieving the limiting and locking of the extension stage 8 in the initial state.

[0035] like Figure 4 As shown, the automatic screw-in locking device 9 includes a loading bracket 91, a loading support shaft 92, a loading coil spring 93, a transmission rod 94, a locking cylinder 95, a locking rod 96, a spring 97, and a drive rod 98. The loading bracket 91 has a Z-shaped structure; its bottom is mounted on the inner wall of the side wall of the extension stage 8; its top is suspended; the loading support shaft 92 is axially vertically positioned at the top of the loading bracket 91, with its bottom end extending downwards from the top of the loading bracket 91; the loading coil spring 93 is fitted onto the outer wall of the loading support shaft 92; the transmission rod 94 is axially vertically mounted at the outer edge of the loading coil spring 93; the locking cylinder 95 is coaxially positioned below the loading support shaft 92; the locking rod 96 extends coaxially into the locking cylinder 95; the spring 97 is fitted onto the outer wall of the locking rod 96; the drive rod 98 is a horizontally positioned rod-shaped structure; it is fitted onto the top outer wall of the locking rod 96; and the bottom end of the transmission rod 94 passes through the drive rod 98.

[0036] The detailed design of this invention is as follows:

[0037] The locking lever 96 has a stepped structure, and the stepped structure is located in the inner cavity of the locking cylinder 95, so that the top of the spring 97 contacts the lower surface of the top of the locking cylinder 95, and the bottom of the spring 97 contacts the upper surface of the stepped structure of the locking lever 96.

[0038] The extension stage 8 has a through hole on its side wall, and the bottom end of the locking rod 96 extends into the through hole; the outer wall of the bottom end of the locking rod 96 has a threaded structure, and the thread corresponds to the limiting threaded hole 72.

[0039] like Figure 5 As shown, in the initial state, the bottom end of the locking lever 96 is in contact with the upper surface of the fixed stage 7, and the spring 97 is in a vertically compressed state. At the same time, in the initial state, the drive lever 98 is clamped by the left side wall of the release control bracket 71, realizing the limitation between the side wall of the extension stage 8 and the side wall of the fixed stage 7; at this time, the loading coil spring 93 is in a compressed state.

[0040] like Figure 6As shown, under the action of external force, the side wall of the extension stage 8 translates relative to the side wall of the fixed stage 7 until the drive rod 98 disengages from the limit of the release control bracket 71; when the loading coil spring 93 is released, it drives the drive rod 98 to rotate through the transmission rod 94.

[0041] When the drive rod 98 disengages from the limit of the release control bracket 71, the bottom end of the locking rod 96 moves to the limit threaded hole 72. Under the action of the spring 97's restoring force, the bottom end of the locking rod 96 extends into the limit threaded hole 72.

[0042] The locking rod 96 is rotated by the drive rod 98 and the locking rod 96 is pushed down by the spring 97, so that the locking rod 96 is threadedly engaged with the limiting threaded hole 72; at the same time, the drive rod 98 is clamped on the right side wall of the release control bracket 71 to achieve the limit.

[0043] The high-rigidity extension locking mechanism provided by this invention can be used to achieve automatic screw-in threaded connection between moving parts of a spacecraft extension mechanism, and complete high-rigidity threaded connection locking. Through extension, energy storage during the extension process, release in place, automatic screwing in and locking, etc., it can realize automatic screwing operation of threads in a small space, forming a high-rigidity connection between moving parts and relatively fixed parts.

[0044] High-rigidity extension locking mechanisms include extension mechanisms and automatic screw-in locking devices.

[0045] Extension mechanisms include fixed and extension types.

[0046] The extension stage and the fixed stage are connected by a sliding joint, and the extension stage can extend relative to the fixed stage.

[0047] The automatic screw-in locking device includes a loading device, a screw-in locking device, a connected component, a release control bracket, etc.

[0048] The loading device includes a loading mounting plate, a loading bracket, a loading support shaft, a loading coil spring, and a transmission rod.

[0049] The loading mounting plate is fixedly connected to the loading bracket. One end of the loading support shaft is fixedly connected to the loading bracket, and the other end of the loading support shaft is fixedly connected to one end of the loading coil spring. The other end of the loading coil spring is fixedly connected to the transmission rod.

[0050] The screw-in locking device includes a locking cylinder, a locking rod, a washer, a spring, a drive rod, etc.

[0051] The locking cylinder and the locking rod are connected by a cylindrical joint. A washer is placed between the locking rod and the spring, and the spring is placed between the washer and the locking cylinder. One end of the drive rod is connected to the locking rod by a sliding joint.

[0052] The locking cylinder of the screw-in locking device and the loading mounting plate of the loading device are fixedly connected, and the drive rod of the screw-in locking device and the transmission rod of the loading device are connected in a planar pair.

[0053] The connected component and the release control bracket are fixedly connected. The loading device and the screw-in locking device are moving parts that move relative to the connected component; the locking rod has threads, and the connected component has threads that mate with the locking rod threads, so the two can be threaded together.

[0054] The shape of the release control bracket is adapted to the relative motion trajectory of the loading device and the screw-in locking device. When the loading device and the screw-in locking device move relative to the connected part, the release control bracket can constrain the drive rod and the loading coil spring of the screw-in locking device, so that the constraint on the drive rod and the loading coil spring will not be released prematurely in the initial state and during the movement.

[0055] In the initial state and during the relative motion of the loading device and the screw-in locking device, the outer surface of the connected part is constrained by the locking rod in the direction of extension of the locking rod, preventing it from extending, and the spring is in a stored energy state, applying a force to the locking rod in the direction of extension.

[0056] When the loading device and the screw-in locking device move to the locked position relative to the connected part, the locking rod is located at the entrance of the thread of the connected part. The constraint of the surface of the connected part on the locking rod along the extension direction is released. Under the action of the spring, the locking rod extends towards the connected part, and the thread of the locking rod and the thread of the connected part enter the mating state. The drive rod moves to the position where it is disengaged from the surface of the release control bracket. The constraint relationship between the release control bracket and the drive rod and the loading coil spring is released. The loading coil spring drives the drive rod to rotate. The rotation direction is consistent with the screw-in direction of the locking rod. The loading coil spring drives the drive rod to screw into the connected part until the screw-in action is completed, thereby realizing the threaded connection between the loading device and the screw-in locking device and the connected part.

[0057] The present invention provides a high-rigidity extension locking mechanism for spacecraft extension components. After the extension components are fully extended, they achieve high-rigidity extension locking through a threaded connection between the extension components and the relatively fixed components. The extension locking mechanism of the present invention can achieve self-energy storage in the unlocked state, and does not require power or external input force or torque during operation.

[0058] When the extension component of the extension mechanism of the present invention is extended into place and high rigidity locking is required, the mechanism automatically presses in and screws in the screw to achieve a threaded locking connection between the connecting component and the connected component. This solves the problem that it is difficult to achieve high rigidity locking through threaded connection in the unmanned state of the spacecraft extension mechanism in orbit.

[0059] This invention can be used to achieve automatic screw-in threaded connection between moving parts of a spacecraft extension mechanism, and to complete a high-rigidity threaded connection locking. Through extension, energy storage during the extension process, release in place, automatic screwing in and locking, etc., it can realize automatic screwing operation of threads in a small space, forming a high-rigidity connection between moving parts and relatively fixed parts.

[0060] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solutions of the present invention by utilizing the methods and techniques disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the protection scope of the technical solutions of the present invention.

Claims

1. A high-rigidity extension locking mechanism, characterized in that: It includes a fixed stage (7), an extended stage (8), and four automatic screw-in locking devices (9); Among them, the fixed stage (7) and the extension stage (8) are both hollow cuboid structures; the fixed stage (7) is fitted on the outer wall of the extension stage (8); four automatic screw-in locking devices (9) are respectively installed on the inner walls of the four corners of the extension stage (8); in the initial state, the fixed stage (7) and the extension stage (8) are in an overlapping state, and the extension stage (8) is limited and locked by the four automatic screw-in locking devices (9); under the action of external force, the extension stage (8) extends out of the fixed stage (7) along the axis; when the extension stage (8) extends into place, the relative position of the fixed stage (7) and the extension stage (8) is locked by the four automatic screw-in locking devices (9); Each side wall of the fixed stage (7) is provided with a release control bracket (71) and a limiting threaded hole (72); the release control bracket (71) is perpendicular to the inner wall of the corresponding side wall of the fixed stage (7) and is located at the corner of the fixed stage (7); the limiting threaded hole (72) is located at the center of the corresponding side wall of the fixed stage (7) and is located in the extension direction of the extension stage (8); the side wall of the extension stage (8) is located on the inner wall of the side wall of the fixed stage (7); the corresponding automatic screw-in locking device (9) is installed on the side wall of the extension stage (8) and limits the release control bracket (71) side wall by limiting the release control bracket (71) side wall, so as to achieve the limiting and locking of the extension stage (8) in the initial state; The automatic screw-in locking device (9) includes a loading bracket (91), a loading support shaft (92), a loading coil spring (93), a transmission rod (94), a locking cylinder (95), a locking rod (96), a spring (97), and a drive rod (98); Among them, the loading bracket (91) is a Z-shaped structure; the bottom of the loading bracket (91) is installed on the inner wall of the side wall of the extension stage (8); the top of the loading bracket (91) is suspended; the loading support shaft (92) is axially vertically set on the top of the loading bracket (91), and the bottom end of the loading support shaft (92) extends downward out of the top of the loading bracket (91); the loading coil spring (93) is fitted on the outer wall of the loading support shaft (92); the transmission rod (94) is axially vertically installed on the outer edge of the loading coil spring (93); the locking cylinder (95) is coaxially set below the loading support shaft (92); the locking rod (96) extends coaxially into the locking cylinder (95); the spring (97) is fitted on the outer wall of the locking rod (96); the drive rod (98) is a horizontally set rod structure; the drive rod (98) is fitted on the top outer wall of the locking rod (96); the bottom end of the transmission rod (94) passes through the drive rod (98).

2. The high-rigidity extension locking mechanism according to claim 1, characterized in that: The locking rod (96) has a stepped structure, and the stepped structure is located in the inner cavity of the locking cylinder (95), so that the top of the spring (97) contacts the lower surface of the top of the locking cylinder (95), and the bottom of the spring (97) contacts the upper surface of the stepped structure of the locking rod (96).

3. The high-rigidity extension locking mechanism according to claim 2, characterized in that: The extension stage (8) has a through hole on its corresponding side wall, and the bottom end of the locking rod (96) extends into the through hole; the outer wall of the bottom end of the locking rod (96) has a threaded structure, and the thread corresponds to the limiting threaded hole (72).

4. The high-rigidity extension locking mechanism according to claim 3, characterized in that: In the initial state, the bottom end of the locking lever (96) is in contact with the upper surface of the fixed stage (7), and the spring (97) is in a vertically compressed state.

5. A high-rigidity extension locking mechanism according to claim 4, characterized in that: In the initial state, the drive rod (98) is clamped by the left side wall of the release control bracket (71), thereby limiting the side wall of the extension stage (8) and the side wall of the fixed stage (7); at this time, the loading coil spring (93) is in a compressed state.

6. A high-rigidity extension locking mechanism according to claim 5, characterized in that: Under the action of external force, the side wall of the extension stage (8) translates relative to the side wall of the fixed stage (7) until the drive rod (98) disengages from the limit of the release control bracket (71); when the loading coil spring (93) is released, the drive rod (98) is driven to rotate through the transmission rod (94).

7. A high-rigidity extension locking mechanism according to claim 6, characterized in that: When the drive rod (98) disengages from the limit of the release control bracket (71), the bottom end of the locking rod (96) moves to the limit threaded hole (72), and under the action of the spring (97) return force, the bottom end of the locking rod (96) extends into the limit threaded hole (72).

8. A high-rigidity extension locking mechanism according to claim 7, characterized in that: The locking rod (96) is rotated by the drive rod (98), and the locking rod (96) is pushed down by the spring (97), so that the locking rod (96) and the limiting threaded hole (72) are threadedly engaged; at the same time, the drive rod (98) is clamped on the right side wall of the release control bracket (71) to achieve the limit.

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