Device for suppressing on-orbit vibration of long-distance single-folding deployment arms on satellites

Abstract

The present invention provides a device for suppressing on-orbit vibration of a long-distance single-folding deployment arm on a satellite, comprising: one end of the deployment arm being rotatably connected to the deployment mechanism; one end of a limiting straight arm being rotatably connected to the deployment mechanism via a rotating support shaft; and the other end of the limiting straight arm being rotatably connected to the deployment arm via a rotating support shaft; a limiting assembly being provided at the rotational connection between the limiting straight arm and the deployment mechanism, and at the rotational connection between the limiting straight arm and the deployment arm, the limiting assembly comprising a limiting hole, a pin, and a compression spring; the limiting hole being provided on the rotating support shaft, and both the pin and the compression spring being provided on the limiting straight arm. The limiting straight arm is linked to the deployment process of the deployment arm through the limiting straight arm, and when the deployment arm is locked in place, the compression spring pushes the pin into the limiting hole. When the deployment arm is disturbed by the environment and generates a small vibration at its end, the limiting device will, through its own characteristics, suppress and reduce the small vibration of the deployment arm in multiple directions during the vibration of the deployment arm, thereby playing a limiting role.

Description

Technical Field

[0001] The present invention relates to the field of spacecraft technology, and in particular to a device for suppressing on-orbit vibration of a long-distance single-folding and deploying arm on a satellite. Background Art

[0002] With the rapid advancement of aerospace technology, modern satellites are becoming larger, more complex, and feature increasingly sophisticated onboard equipment. This necessitates the deployment of increasingly sophisticated equipment (such as high-precision deployable antennas and high-precision optical instruments) via deployable arms, extending them far from the satellite body. These precision instruments, along with the deployable arms, can be considered flexible appendages of the satellite, characterized by low fundamental frequencies, a high concentration of low frequencies, and susceptibility to disturbances. During on-orbit flight, the motion of attitude control actuators and active components often become sources of disturbance for these flexible appendages, easily coupling with and resonating with them, negatively impacting the reliability and stability of these precision instruments.

[0003] The original deployment mechanism had a certain amount of clearance between its components. This clearance was necessary to prevent the mechanism from getting stuck or even freezing during deployment. Once the satellite is in orbit and the deployment mechanism is deployed and locked, any in-orbit maneuvers or other vibrations from other sources can cause the mechanism to vibrate.

[0004] In order to ensure the stability of these precision equipment deployed into space through extension arms, effective means need to be adopted to enhance the flexibility of the flexible accessories of this long-distance extension arm. When the extension arm is disturbed by the environment and produces small vibrations at its end, the limiting device will use its own characteristics during the vibration process of the extension arm to suppress and reduce the small vibrations of the extension arm, thereby playing a limiting role, which has urgent engineering application value.

[0005] The existing Chinese patent application document with publication number CN103241389A discloses an on-orbit frequency-increasing mechanism for a flexible accessory of a spacecraft, including a driving element, a reduction gear, a support frame, a pull rope webbing, an interface support, a transition shaft segment, a one-way bearing and a winding drum. The driving element, reduction gear, interface support, transition shaft segment, one-way bearing and winding drum are respectively installed on the support frame. The pull rope webbing is wound on the winding drum. The drive of the driving element is transmitted to the winding drum through the reduction gear, the transition shaft segment and the one-way bearing. The rotation of the winding drum drives the rope webbing to tighten and relax. The end of the pull rope webbing is connected to the flexible accessory through the interface support.

[0006] The prior art limits the unfolding mechanism by using a flexible pull rope, which can only withstand tension and can only suppress vibration and limit amplitude along the stretching direction of the pull rope, but cannot suppress vibration and limit amplitude in multiple directions. Summary of the Invention

[0007] In view of the defects in the prior art, the object of the present invention is to provide a device for suppressing on-orbit vibration of a long-distance single-folding and deploying arm on a satellite.

[0008] According to the present invention, a device for suppressing on-orbit vibration of a long-distance single-fold deployment arm on a satellite is provided, which includes a deployment mechanism, a deployment arm and a limiting straight arm; one end of the deployment arm is rotatably connected to the deployment mechanism, one end of the limiting straight arm is rotatably connected to the deployment mechanism through a rotating support shaft, and the other end of the limiting straight arm is rotatably connected to the deployment arm through a rotating support shaft; any of the rotating support shafts is tightly connected to the deployment mechanism or the deployment arm, and any of the rotating support shafts is rotatably connected to the limiting straight arm; a limiting assembly is provided at the rotational connection between the limiting straight arm and the deployment mechanism, and at the rotational connection between the limiting straight arm and the deployment arm, the limiting assembly includes a limiting hole, a pin shaft and a compression spring; the limiting hole is provided on the rotating support shaft, and both the pin shaft and the compression spring are provided on the limiting straight arm, one end of the pin shaft abuts against the compression spring, and the other end of the pin shaft abuts against the outer wall of the rotating support shaft or extends into the limiting hole; when the pin shaft is away from one end of the compression spring and abuts against the outer wall of the rotating support shaft, the compression spring is in a compressed state.

[0009] Preferably, the rotation axis of the deployment arm and the deployment mechanism is colinear with the axis of the rotation support shaft on the deployment mechanism.

[0010] Preferably, the rotation axes of the limiting straight arm and the unfolding arm, and the rotation axes of the unfolding mechanism and the limiting straight arm are located in the same plane.

[0011] Preferably, the shape of the connection section between the rotation support shaft and the amplitude limiting straight arm includes a cylindrical shape, and the rotation support shaft and the amplitude limiting straight arm are clearance-matched; the limiting hole includes a hemispherical countersunk hole.

[0012] Preferably, a cylindrical deep hole is provided inside the limiting straight arm, and the axis of the cylindrical deep hole is perpendicular to the axis of the rotating support shaft; the pin shaft and the compression spring are both arranged in the cylindrical deep hole, one end of the compression spring abuts against the bottom wall of the cylindrical deep hole away from the rotating support shaft, and the other end of the compression spring abuts against the pin shaft; the cylindrical deep hole allows the pin shaft to extend out or retract.

[0013] Preferably, the pin shaft includes a pin sleeve section and a pin head section, the compression spring extends into the pin sleeve section, and the pin head section is plug-fitted into the limiting hole.

[0014] Preferably, a rectangular opening is provided on the limiting straight arm, the rectangular opening connects the cylindrical deep hole with the external environment, and the length direction of the rectangular opening is parallel to the axial direction of the cylindrical deep hole; a through hole is provided on the pin shaft, the axis of the through hole is perpendicular to the axis of the cylindrical deep hole, and the through hole is connected to the rectangular opening.

[0015] Preferably, one limiting straight arm is provided on each side of the unfolding arm.

[0016] Preferably, the limiting straight arms on both sides of the deployment arm are collinear with the rotation axis of the deployment arm, and the limiting straight arms on both sides of the deployment arm are collinear with the rotation axis of the deployment mechanism.

[0017] Preferably, when the deployment arm is deployed into place, the pins in any of the rotational connections between the limiting straight arm and the deployment mechanism and any of the limiting components located at the rotational connection between the limiting straight arm and the deployment arm are inserted into the limiting holes.

[0018] Compared with the prior art, the present invention has the following beneficial effects:

[0019] 1. The present invention cleverly achieves vibration suppression through a limiting assembly inside a rigid limiting straight arm. That is, the limiting straight arm is linked to the deployment process of the deployment arm. When the deployment arm is locked in place, the compression spring in the limiting assembly pushes the pin shaft into the limiting hole on the rotating support shaft. When the deployment arm is disturbed by the environment and produces a small vibration at its end, the limiting device will use its own characteristics to suppress and reduce the small vibration of the deployment arm in multiple directions during the vibration process of the deployment arm, thereby playing a limiting role. This is essentially different from the existing methods such as using pull ropes.

[0020] 2. The present invention is a concealed installation component by installing the pin shaft and the compression spring in the cylindrical deep holes inside the head end and the end of the limiting straight arm; a through hole is opened on the pin shaft, which cooperates with the rectangular openings on the side of the head end and the end of the limiting straight arm to facilitate the process installation of the limit assembly, and no other envelope space is added beyond the conventional deployment mechanism and the limiting straight arm, which is conducive to use under the compact layout space constraints on the satellite. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Other features, objects and advantages of the present invention will become more apparent upon reading the detailed description of non-limiting embodiments with reference to the following drawings:

[0022] Figure 1 This is a top view of the overall structure of the vibration suppression device of the present invention;

[0023] Figure 2 for Figure 1 The cross-sectional diagram at D in the middle is a schematic diagram of the rotation structure of the unfolding arm and the limiting straight arm of the present invention;

[0024] Figure 3 for Figure 1 The cross-sectional diagram at point E in the middle is a schematic diagram of the rotation structure of the unfolding mechanism and the limiting straight arm of the present invention;

[0025] Figure 4 This is a sectional view of the side of the overall structure of the vibration suppression device that mainly embodies the invention;

[0026] Figure 5 This is an external schematic diagram of the invention mainly embodying the rotation structure of the unfolding mechanism and the limiting straight arm;

[0027] Figure 6 This is an external schematic diagram of the rotation structure of the expansion arm and the limiting straight arm;

[0028] Figure 7 This is a schematic diagram of the overall structure of the rotating support shaft that mainly embodies the invention;

[0029] Figure 8 This is a schematic diagram of the overall structure of the limiting straight arm of the invention.

[0030] As shown in the figure:

[0031] DETAILED DESCRIPTION

[0032] The present invention will be described in detail below with reference to specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those skilled in the art, several changes and improvements can be made without departing from the scope of the present invention. These all fall within the scope of protection of the present invention.

[0033] Example 1

[0034] like Figure 1 、 Figure 2 、 Figure 3 as well as Figure 4 As shown, a device for suppressing on-orbit vibration of a long-distance, single-fold deployment arm on a satellite, according to the present invention, comprises a deployment mechanism 1, a deployment arm 2, and a clipping straight arm 3. One end of the deployment arm 2 is rotationally connected to the deployment mechanism 1, one end of the clipping straight arm 3 is rotationally connected to the deployment mechanism 1 via a rotational support shaft 4, and the other end of the clipping straight arm 3 is rotationally connected to the deployment arm 2 via a rotational support shaft 4. Either rotational support shaft 4 is securely connected to the deployment mechanism 1 or the deployment arm 2, and either rotational support shaft 4 is rotationally connected to the clipping straight arm 3.

[0035] Specifically, the limiting straight arm 3 has a certain degree of rigidity, and the rotation axis of the deployment arm 2 and the deployment mechanism 1 is collinear with the axis of the rotary support shaft 4 on the deployment mechanism 1. The rotation axis of the limiting straight arm 3 and the deployment arm 2, and the rotation axis of the deployment mechanism 1 and the limiting straight arm 3 are both located in the same plane.

[0036] A limiting component 5 is provided at the rotational connection between the limiting straight arm 3 and the unfolding mechanism 1, and at the rotational connection between the limiting straight arm 3 and the unfolding arm 2. Since the structure, installation method and working principle of the limiting component 5 at the rotational connection between the limiting straight arm 3 and the unfolding mechanism 1, and at the rotational connection between the limiting straight arm 3 and the unfolding arm 2 are the same, a group of limiting components 5 are first explained as an example.

[0037] The limiting assembly 5 includes a limiting hole 51, a pin 52, and a compression spring 53. The limiting hole 51 is provided on the rotation support shaft 4, and both the pin 52 and the compression spring 53 are provided on the amplitude limiting straight arm 3. One end of the pin 52 abuts the compression spring 53, while the other end of the pin 52 abuts the outer wall of the rotation support shaft 4 or extends into the limiting hole 51. When the end of the pin 52, which is away from the compression spring 53, abuts the outer wall of the rotation support shaft 4, the compression spring 53 is in a compressed state.

[0038] like Figure 4 、 Figure 5 、 Figure 6 、 Figure 7 as well as Figure 8 As shown, specifically, the shape of the connection section between the rotation support shaft 4 and the amplitude limiting straight arm 3 includes a cylindrical shape, and the rotation support shaft 4 and the amplitude limiting straight arm 3 are clearance-matched, thereby ensuring the rotational connection between the rotation support shaft 4 and the amplitude limiting straight arm 3. Furthermore, a shaft sleeve is provided at each end of the amplitude limiting straight arm 3, and the shaft sleeve is coaxially sleeved with the rotation support shaft 4, and the connection surface between the shaft sleeve and the rotation support shaft 4 is lubricated to achieve the rotational fit between the rotation support shaft 4 and the shaft sleeve.

[0039] A cylindrical deep hole 31 is defined within the limiting straight arm 3. The axis of the cylindrical deep hole 31 is perpendicular to the axis of the rotating support shaft 4. A pin 52 and a compression spring 53 are disposed within the cylindrical deep hole 31. One end of the compression spring 53 abuts the bottom wall of the cylindrical deep hole 31, away from the rotating support shaft 4, while the other end of the compression spring 53 abuts the pin 52. The cylindrical deep hole 31 allows the pin 52 to extend or retract.

[0040] The limiting hole 51 comprises a hemispherical countersunk hole, and the limiting hole 51 is plugged into and matched with the pin 52. The pin 52 and the compression spring 53 are both arranged in the cylindrical deep hole 31, belonging to a hidden installation component.

[0041] More specifically, the pin shaft 52 includes a pin sleeve section and a pin head section, and the compression spring 53 extends into the pin sleeve section, and the pin head section is plugged into the limiting hole 51. A rectangular opening 32 is provided on the limiting straight arm 3, and the rectangular opening 32 connects the cylindrical deep hole 31 with the external environment. A through hole 6 is provided on the pin shaft 52, and the axis of the through hole 6 is perpendicular to the axis of the cylindrical deep hole 31, and the through hole 6 is connected to the rectangular opening 32. The cylindrical deep hole 31 cooperates with the rectangular opening 32 to facilitate the installation of the pin sleeve and the compression spring 53. During the assembly process, the compression spring 53 is installed in the pin sleeve section, and the tooling passes through the rectangular opening 32 on the side of the limiting straight arm 3 and the through hole 6 on the pin sleeve to compress the compression spring 53.

[0042] During operation, as the deployment arm 2 deploys, the pin head of the pin sleeve rotates around the rotating support shaft 4, compressing the compression spring 53. Once the deployment arm 2 is deployed and locked into position, the compression spring 53 pushes the pin sleeve into the hemispherical stopper hole 51 on the rotating support shaft 4, limiting the amplitude of the limiter arm 3 at both the front and rear ends.

[0043] Preferred Example 1

[0044] like Figure 1 As shown, based on Example 1, according to the present invention, a device for suppressing on-orbit vibration of a long-distance single-folding deployment arm 2 on a satellite is provided. A limiting straight arm 3 is provided on each side of the deployment arm 2. The limiting straight arms 3 on both sides of the deployment arm 2 are collinear with the rotation axis of the deployment arm 2, and the limiting straight arms 3 on both sides of the deployment arm 2 are collinear with the rotation axis of the deployment mechanism 1.

[0045] When the deployment arm 2 is deployed into place, the pin 52 in any of the rotational connections between the limiting straight arm 3 and the deployment mechanism 1 and any of the rotational connections between the limiting straight arm 3 and the deployment arm 2 are inserted into the limiting hole 51.

[0046] By using the limiting straight arms 3 located on both sides of the deployment arm 2 to act on the deployment arm 2 at the same time, force balance can be achieved, further ensuring the suppression of the on-track vibration of the deployment arm 2.

[0047] In the description of this application, it should be understood that the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings, and are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on this application.

[0048] The above describes specific embodiments of the present invention. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art may make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. The embodiments of this application and the features in the embodiments may be combined with each other in any manner unless there is a conflict.

Claims

1. A device for suppressing on-orbit vibration of a long-distance single-folding and deploying arm on a satellite, characterized in that: It comprises an unfolding mechanism (1), an unfolding arm (2) and a limiting straight arm (3); One end of the unfolding arm (2) is rotatably connected to the unfolding mechanism (1), one end of the limiting straight arm (3) is rotatably connected to the unfolding mechanism (1) via a rotating support shaft (4), and the other end of the limiting straight arm (3) is rotatably connected to the unfolding arm (2) via a rotating support shaft (4); The rotating support shaft (4) is tightly connected to the unfolding mechanism (1) or the unfolding arm (2), and the rotating support shaft (4) is rotatably connected to the limiting straight arm (3); The rotational connection between the limiting straight arm (3) and the unfolding mechanism (1), and the rotational connection between the limiting straight arm (3) and the unfolding arm (2) are both provided with a limiting assembly (5), and the limiting assembly (5) includes a limiting hole (51), a pin (52), and a compression spring (53); The limiting hole (51) is provided on the rotation support shaft (4), the pin shaft (52) and the compression spring (53) are both provided on the limiting straight arm (3), one end of the pin shaft (52) abuts against the compression spring (53), and the other end of the pin shaft (52) abuts against the outer wall of the rotation support shaft (4) or extends into the limiting hole (51); When one end of the pin shaft (52) away from the compression spring (53) abuts against the outer wall of the rotation support shaft (4), the compression spring (53) is in a compressed state.

2. The device for suppressing on-orbit vibration of a long-distance single-folding and deploying arm on a satellite as claimed in claim 1, characterized in that: The rotation axis of the unfolding arm (2) and the unfolding mechanism (1) is collinear with the axis of the rotating support shaft (4) on the unfolding mechanism (1).

3. The device for suppressing on-orbit vibration of a long-distance single-folding and deploying arm on a satellite as claimed in claim 1, characterized in that: The rotation axes of the amplitude limiting straight arm (3) and the unfolding arm (2), and the rotation axes of the unfolding mechanism (1) and the amplitude limiting straight arm (3) are located in the same plane.

4. The device for suppressing on-orbit vibration of a long-distance single-folding and deploying arm on a satellite as claimed in claim 1, characterized in that: The connection section between the rotating support shaft (4) and the amplitude limiting straight arm (3) is cylindrical in shape, and the rotating support shaft (4) and the amplitude limiting straight arm (3) are clearance-matched; The limiting hole (51) comprises a hemispherical countersunk hole.

5. The device for suppressing on-orbit vibration of a long-distance single-folding and deploying arm on a satellite as claimed in claim 1, characterized in that: A cylindrical deep hole (31) is provided inside the amplitude limiting straight arm (3), and the axis of the cylindrical deep hole (31) and the axis of the rotating support shaft (4) are perpendicular to each other; The pin shaft (52) and the compression spring (53) are both arranged in the cylindrical deep hole (31), one end of the compression spring (53) abuts against the bottom wall of the cylindrical deep hole (31) away from the rotation support shaft (4), and the other end of the compression spring (53) abuts against the pin shaft (52); The cylindrical deep hole (31) allows the pin (52) to be extended or retracted.

6. The device for suppressing on-orbit vibration of a long-distance single-folding and deploying arm on a satellite as claimed in claim 5, characterized in that: The pin shaft (52) comprises a pin sleeve section and a pin head section, the compression spring (53) extends into the pin sleeve section, and the pin head section is plug-fitted into the limiting hole (51).

7. The device for suppressing on-orbit vibration of a long-distance single-folding and deploying arm on a satellite as claimed in claim 5, characterized in that: A rectangular opening (32) is provided on the limiting straight arm (3), the rectangular opening (32) connects the cylindrical deep hole (31) with the external environment, and the length direction of the rectangular opening (32) is parallel to the axial direction of the cylindrical deep hole (31); A through hole (6) is provided on the pin shaft (52), the axis of the through hole (6) and the axis of the cylindrical deep hole (31) are perpendicular to each other, and the through hole (6) is connected to the rectangular opening (32).

8. The device for suppressing on-orbit vibration of a long-distance single-folding and deploying arm on a satellite as claimed in claim 1, characterized in that: The limiting straight arm (3) is provided on each side of the unfolding arm (2).

9. The device for suppressing on-orbit vibration of a long-distance single-folding and deploying arm on a satellite as claimed in claim 8, characterized in that: The limiting straight arms (3) located on both sides of the unfolding arm (2) are collinear with the rotation axis of the unfolding arm (2), and the limiting straight arms (3) located on both sides of the unfolding arm (2) are collinear with the rotation axis of the unfolding mechanism (1).

10. The device for suppressing on-orbit vibration of a long-distance single-folding and deploying arm on a satellite as claimed in claim 1, characterized in that: When the unfolding arm (2) is unfolded into position, the pins (52) in any of the rotational connections between the limiting straight arm (3) and the unfolding mechanism (1) and any of the limiting components (5) located at the rotational connections between the limiting straight arm (3) and the unfolding arm (2) are inserted into the limiting holes (51).

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