Passive Rotary Damper

Abstract

The present invention relates to the technical field of dampers, and provides a passive rotary damper, which includes an outer sleeve component and a damping component arranged in the outer sleeve component; the damping component is configured with a driving input rotor and elastic damping reed pieces arranged circumferentially along the driving input rotor. When the driving input rotor rotates, due to the elastic interference of the elastic damping reed pieces, the driving input rotor is subjected to a damping torque, thereby reducing the movement speed of the driving input rotor. Among them, the elastic interference allows the driving input rotor to rotate through the elastic damping reed pieces. The present invention proposes a brand-new passive rotary damper, which mainly consumes the energy during the rotation process through the extrusion elastic force and sliding friction force of the elastic reed pieces, thereby reducing the relative deployment speed of the antenna or the sailboard. It has the characteristics of simple structure, light weight, and small influence of temperature, etc., and can greatly improve the reliability of the entire spacecraft deployment system.

Description

Technical Field

[0001] The present invention relates to the technical field of dampers, and in particular, to a passive rotary damper. Background Art

[0002] Spacecraft deployment mechanisms include various solar panels, antenna arrays, detection boom mechanisms, and various truss beam support structures with specific requirements. Currently, most one-time deployment mechanisms on spacecraft use elastic elements as power sources and deploy in a rotational manner. To ensure the smooth deployment of the mechanism, torsion springs often apply a large initial torque. If no suppression measures are taken, when these mechanisms are deployed in place, it will inevitably cause a certain impact on the spacecraft, and this impact may damage the surrounding structures and equipment. At the same time, the unstable speed fluctuations during the deployment process of the mechanism may cause vibrations in the system, affecting the stability and reliability of the system.

[0003] According to different energy dissipation mechanisms, currently existing dampers are mainly divided into viscous dampers, eddy current dampers, viscoelastic dampers, mechanical friction dampers, magnetic / rheological dampers, shape memory alloy dampers, piezoelectric friction dampers, etc. According to different impact suppression methods, most dampers can be divided into two categories: passive and semi-active. Passive dampers do not require external energy drive and rely on the damper itself to generate damping force (moment) as it moves with the mechanism, and have good economy and reliability. Semi-active dampers only require a small amount of energy input, and the damping force (moment) is passively generated by the damper itself as it moves with the mechanism; however, the parameters of the damper itself can be actively adjusted by an external energy source, thereby changing the damping force (moment).

[0004] Currently, the technology of passive dampers has been relatively mature. Among them, viscous dampers and eddy current dampers have been widely used in spacecraft deployment mechanisms. However, existing dampers have problems such as being greatly affected by temperature, having a risk of liquid leakage, large weight, and large volume. The technology of semi-active dampers can adjust the damping more precisely, but it is still in the development stage at present. Moreover, semi-active dampers rely on external energy input, which will increase the complexity of the system and reduce the reliability of the system. Summary of the Invention

[0005] Aiming at the defects in the prior art, the purpose of the present invention is to provide a passive rotary damper.

[0006] A passive rotary damper according to the present invention includes an outer sleeve component and a damping component arranged in the outer sleeve component;

[0007] The damping component is configured with a driving input rotor and elastic damping reeds arranged circumferentially along the driving input rotor. When the driving input rotor rotates, due to the elastic interference of the elastic damping reeds, the driving input rotor is subjected to a damping torque, thereby reducing the movement speed of the driving input rotor. Among them, the elastic interference allows the driving input rotor to rotate through the elastic damping reeds.

[0008] Preferably, the outer sleeve component includes an outer sleeve, a rear end cover and a front end cover respectively arranged at both ends of the outer sleeve. Among them, the end of the front end cover is the first fixed end, and the end of the driving shaft of the driving input rotor extends to the outside of the rear end cover as the second fixed end. Both the first fixed end and the second fixed end are used to connect the deployment mechanism.

[0009] Preferably, the damping torque includes frictional interference and magnetic interference force.

[0010] Preferably, the magnetic interference force is that a magnet is arranged on the outer sleeve, thereby generating a magnetic force with the magnet of the driving input rotor.

[0011] Preferably, the elastic damping reeds are made of magnetic material.

[0012] Preferably, the cross-section of the driving input rotor is an elliptical structure, and the cross-section of the elastic damping reeds is any one of the following structures:

[0013] An involute structure with openings arranged opposite to each other;

[0014] An arc structure with openings arranged back to back, where the arc structure is an arc or multiple arcs arranged continuously or discontinuously;

[0015] An elliptical ring structure embedded inside the outer sleeve;

[0016] When the driving input rotor rotates, the middle part of the elastic damping reeds can block and interfere with the long-axis vertices of the driving input rotor.

[0017] Preferably, a second permanent magnet is arranged at the long-axis vertices of the driving input rotor, and a first permanent magnet is arranged on the outer sleeve. The magnetic pole directions of the second permanent magnet and the first permanent magnet are opposite.

[0018] Preferably, the elastic damping reeds are arranged in pairs inside the outer sleeve and the two elastic damping reeds are arranged in a centrosymmetric structure.

[0019] Preferably, fixed bearings are respectively fixed to the rear end cover and the front end cover at both ends of the driving input rotor, and the fixed bearings at the front end cover and the rear end cover are respectively rotationally matched with the front end cover and the rear end cover.

[0020] Preferably, the driving input rotor is of a hollow structure.

[0021] Preferably, damping grooves are provided on the inner wall of the outer sleeve, rotor guide rods are circumferentially arranged on the driving input rotor, magnetic materials are provided at the ends of the rotor guide rods and extend into the damping grooves, there is a gap between the ends of the rotor guide rods and the damping grooves, and the gap is filled with magnetic particles so that when the driving input rotor rotates, the ends of the rotor guide rods move in the damping grooves to generate damping and thus decelerate.

[0022] Preferably, one row or more rows of needle-like protrusions are arranged at intervals on the outer sleeve. When the driving input rotor rotates, it is blocked and interfered by the needle-like protrusions, causing the needle-like protrusions to undergo plastic deformation or be cut off, thereby generating damping for the driving input rotor and thus decelerating.

[0023] Compared with the prior art, the present invention has the following beneficial effects:

[0024] The present invention provides a brand-new passive rotary damper, which mainly consumes the energy during the rotation process through the extrusion elastic force and sliding friction force of the elastic reed, thereby reducing the relative deployment speed of the antenna or sailboard. It has the characteristics of simple structure, light weight, and small influence of temperature, and can greatly improve the reliability of the entire spacecraft deployment system. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] By reading the following detailed description of the non-limiting embodiments with reference to the accompanying drawings, other features, objects, and advantages of the present invention will become more apparent:

[0026] Figure 1 is a schematic structural diagram of the present invention;

[0027] Figure 2 is a schematic side structural diagram of the present invention;

[0028] Figure 3 is Figure 2 a schematic cross-sectional view taken along the line A-A in

[0029] Figure 4 is a schematic structural disassembled diagram of an embodiment;

[0030] Figure 5 is a schematic structural diagram when magnets are arranged on both the outer sleeve and the driving input rotor;

[0031] Figure 6 is a schematic structural diagram when the elastic damping reed is in the form of an asymptote;

[0032] Figure 7 is a schematic diagram when the elastic damping reed adopts a step-by-step segmented structure;

[0033] Figure 8 Schematic diagram of the structure when the elastic damping reed is in an elliptical ring structure;

[0034] Figure 9 Schematic diagram of the arrangement of the needle-like protrusions on the inner wall of the outer sleeve in Embodiment 2;

[0035] Figure 10 Schematic diagram of the damping groove in Embodiment 3;

[0036] Figure 11 is Figure 10 Schematic cross-sectional view of the structure in the B-B direction in

[0037] As shown in the figure:

[0038] Rear end cover 1

[0039] Outer sleeve 2

[0040] First permanent magnet 21

[0041] Needle-like protrusion 22

[0042] Damping groove 23

[0043] Elastic damping reed 3

[0044] Drive input rotor 4

[0045] Second permanent magnet 41

[0046] Rotor guide rod 42

[0047] Front end cover 5

[0048] Rear end cover fixed bearing 6

[0049] Front end cover fixed bearing 7

[0050] Drive shaft 8 Detailed implementation manners

[0051] The present invention will be described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be noted that for those of ordinary skill in the art, without departing from the concept of the present invention, several changes and improvements can still be made. These all belong to the protection scope of the present invention.

[0052] Embodiment 1:

[0053] The present invention provides a passive rotary damper, such as Figure 1 , Figure 2As shown, it includes a jacket component and a damping component arranged within the jacket component; the damping component is configured with a driving input rotor 4 and elastic damping reeds 3 circumferentially arranged along the driving input rotor 4. When the driving input rotor 4 rotates, due to the elastic interference of the elastic damping reeds 3, the driving input rotor 4 is subjected to a damping torque, thereby reducing the movement speed of the driving input rotor 4. Among them, the elastic interference allows the driving input rotor 4 to rotate through the elastic damping reeds 3. Therefore, the setting of the elastic damping reeds 3 makes the rotation speed of the driving input rotor 4 smoother and has a buffering effect.

[0054] As Figure 4 shown, the jacket component includes a jacket cylinder 2 and a rear end cover 1 and a front end cover 5 respectively arranged at both ends of the jacket cylinder 2. Among them, the end of the front end cover 5 is the first fixed end, and the end of the driving shaft 8 of the driving input rotor 4 extends outside the rear end cover 1 as the second fixed end. Both the first fixed end and the second fixed end are used to connect the deployment mechanism. Specifically for the connection with the spacecraft deployment mechanism, this damper can be coaxially installed with the hinge at the deployment mechanism. One of the antennas or solar panels is connected to the front end cover 5 through a preset interface on the front end cover 5 as a fixed part, and the other antenna or solar panel is connected to the driving shaft 8 on the driving input rotor 4 through a preset interface as a relatively movable component. The jacket cylinder 2 is respectively connected to the rear end cover 1 and the front end cover 5 by bolts, serving as the protection support and connection structure of the entire damper.

[0055] Furthermore, the elastic damping reeds 3 are preferably arranged in pairs inside the jacket cylinder 2 and the two elastic damping reeds 3 are arranged in a centrosymmetric structure. The damping component includes a driving input rotor 4 and a pair of elastic damping reeds 3. The elastic damping reeds 3 are fixed on the jacket cylinder 2 through the grooves inside the jacket cylinder 2. The center of the driving input rotor 4 is penetrated by a driving shaft 8. Both ends of the driving shaft 8 are rotationally matched with the rear end cover 1 and the front end cover 5 through a rear end cover fixed bearing 6 and a front end cover fixed bearing 7 respectively. The driving shaft 8 can rotate concentrically inside the jacket cylinder 2.

[0056] In practical applications, the damping torque can be generated only by the frictional interference force between the elastic damping reeds 3 and the driving input rotor 4, or a magnetic interference force can be superimposed. For example, the magnetic interference force is the magnetic force generated by a magnet arranged on the jacket cylinder 2 and a magnet of the driving input rotor 4. The cross-section of the driving input rotor 4 is an elliptical structure. As Figure 5 shown, a second permanent magnet 41 is arranged at the long axis vertex of the driving input rotor 4, and a first permanent magnet 21 is arranged on the jacket cylinder 2. The magnetic pole directions of the second permanent magnet 41 and the first permanent magnet 21 are opposite. Therefore, when the driving input rotor 4 rotates, the rotational damping of the driving input rotor 4 can also be increased under the magnetic attraction of the second permanent magnet 41 and the first permanent magnet 21.

[0057] Further, to enhance the effect of magnetic damping, the elastic damping reed 3 can be made of a magnetic material. When driving the input rotor 4 to rotate, the second permanent magnet 41 on the driving input rotor 4 magnetically attracts the elastic damping reed 3, which can also increase the damping effect.

[0058] As Figure 3 shown, the cross-section of the elastic damping reed 3 is an arc structure. When the driving input rotor 4 rotates, the middle part of the elastic damping reed 3 can block and interfere with the long-axis vertex of the driving input rotor 4. The driving input rotor 4 is a hollow structure, which is beneficial to reducing the weight of the entire damper.

[0059] The working process and principle of the present invention:

[0060] One antenna or solar panel of the spacecraft is connected to the front end cover 5 through the preset interface of the front end cover 5, and the other antenna or solar panel is connected to the preset interface connected to the drive shaft 8 connected to the driving input rotor 4. When the antenna or solar panel unfolds under the action of the elastic element, the driving input rotor 4 will rotate relative to the reed fixed outer sleeve 2. During the rotation process, the driving input rotor 4 will be squeezed by the elastic damping reed 3. At this time, the driving input rotor 4 will be subjected to the elastic force of the elastic damping reed 3 and the sliding friction force formed by this normal elastic force. A pair of elastic damping reeds 3 will generate a damping torque on the driving input rotor 4 under the action of these two forces. The energy of rotation is dissipated through the deformation and friction of the elastic damping reed 3, thereby reducing the speed during the unfolding process of the antenna or solar panel.

[0061] In practical applications, as Figure 2 shown, magnets with opposite polarities are installed at the end of the driving input rotor 4 and at the position of the outer sleeve 2 corresponding to the initial position of the rotor. As Figure 5 shown, at the same time, the elastic damping reeds 3 are all selected as magnetic materials. The beneficial effects of such improvement are: the driving input rotor 4 will have an additional magnetic damping torque under the action of the magnet attraction at the initial position, reducing the initial rotational angular acceleration; there will be an additional magnetic attraction between the driving input rotor 4 and the elastic damping reed 3, which can increase the extrusion stress of their contact, thereby increasing the energy consumption of the frictional damping force; at the end position of the 180° rotation, under the action of the attraction between the first magnet 21 of the outer sleeve 2 and the second magnet 41 at the end of the driving input rotor 4, the driving input rotor 4 can be more accurately positioned to the limit position, preventing the antenna or solar panel from jamming due to over-damping in the later stage of unfolding, and at the same time effectively suppressing the impact load.

[0062] Specifically, the shape and the interaction relationship of the driving input rotor 4 and the elastic damping reed 3 can be optimized according to the torque size change law of the unfolding driving elastic element and the specific size and weight of the antenna or solar panel. For example, the elastic damping reed 3 can be designed in the form of involutes with opposite openings, asFigure 6 As shown, that is, the damping torque of the elastic damping reed 3 acting on the driving input rotor 4 gradually increases, so that the deployment speed of the antenna or the solar panel first increases and then decreases, reducing the end impact load; for another example, the elastic damping reed 4 is designed in a step-by-step segmented structural form, such as an arc structure with the openings facing away from each other. Among them, the arc structure is a section of arc or multiple sections of arcs arranged continuously or discontinuously, as Figure 7 shown, according to the torque change of the driving elastic element, the rotational energy is gradually consumed; for another example, the elastic damping reed 3 can be designed as an elliptical ring structure embedded inside the outer sleeve 2, such as embedding in the outer sleeve in the form of an elliptical ring, as Figure 8 shown, making the change of the damping torque smoother, etc.

[0063] In order to increase the damping energy consumption of the device, in addition to the above-mentioned optimized design of the shape and interaction relationship of the driving input rotor 4 and the elastic damping reed 3, some improvement designs can also be made to the outer sleeve 2. By some special structures acting on the driving input rotor 4 to increase the damping energy consumption, the rotational energy of the driving input rotor 4 can be dissipated through various structural designs such as magnetic damping and friction damping, thereby realizing the mitigation of the rotational trend of the driving input rotor 4, making the entire movement smoother, and achieving the final damping effect. This will be further introduced through Embodiment 2 and Embodiment 3 below.

[0064] Embodiment 2:

[0065] This embodiment is a variant of Embodiment 1.

[0066] This embodiment provides a passive rotary damper. A row or multiple rows of needle-shaped protrusions 22 are arranged at intervals on the inner wall of the outer sleeve 2. When the driving input rotor 4 rotates, it is blocked and interfered by the needle-shaped protrusions 22, causing the needle-shaped protrusions 22 to produce plastic deformation or be cut off, thereby generating damping on the driving input rotor 4 and decelerating it.

[0067] Specifically, as Figure 9 shown, multiple rows of needle-shaped protrusions 22 are arranged at intervals on the inner wall of the outer sleeve component. During the rotation of the driving input rotor 4, it will collide with these needle-shaped protrusions 22, causing these needle-shaped protrusions 22 to produce plastic deformation or be directly cut off (this damper is mostly for one-time use). This can increase the damping energy consumption and thus better play the role of deceleration and buffering; by setting the size and quantity of the needle-shaped protrusions 22 at different positions within one rotation period and selecting appropriate materials, the effect of stepped variable damping energy consumption can be achieved, meeting the damping requirements during the deployment of different spacecraft antennas or solar panels.

[0068] The needle-like protrusions 22 are preferably weakly structured plastic bodies, which either consume the rotational energy of the driving input rotor 4 due to deformation under the extrusion force of the driving input rotor 4, or break or are cut off due to the extrusion force of the driving input rotor 4 to consume the rotational energy of the driving input rotor 4. For example, the needle-like protrusions 22 adopt a needle-like, straightened linear or honeycomb peeling shell array structure to achieve the consumption of the rotational energy of the driving input rotor 4 and achieve the effect of rotational damping.

[0069] Embodiment 3:

[0070] This embodiment is another variant of Embodiment 1.

[0071] This embodiment provides a passive rotational damper. As Figure 10 , Figure 11 shown, a rotor guide rod 42 is circumferentially arranged on the driving input rotor 4, a damping groove 23 is arranged on the inner wall of the outer sleeve 2, the movement locus of the end of the rotor guide rod 42 is located in the damping groove 23, the end of the rotor guide rod 42 extends into the interior of the damping groove 23, and an appropriate amount of magnetic particles are filled in the gap between the rotor guide rod 42 and the damping groove 23. The end of the rotor guide rod 42 is made of a magnet material. Under the action of magnetic force, the rotor guide rod 42 will attract the magnetic particles to gather at the end of the rotor guide rod 42. As the driving input rotor 4 rotates, the gathered magnetic particles will generate a damping force in which magnetic damping and frictional damping are coupled with the end of the guide rod and inside the magnetic particles, which can increase the damping energy consumption and play a role in deceleration and buffering; by optimizing the geometric shapes of the end of the rotor guide rod 42 and the opening of the damping groove 23, as well as the density of the magnetic particles, the role of auxiliary energy consumption can be achieved under the condition of ensuring that the magnetic particles do not leak out, meeting the damping requirements of different spacecraft antennas or sailboard deployment processes.

[0072] The form of rotational energy consumption of the driving input rotor 4 in the present invention is not limited to the above structure, and there are also other various energy consumption structure forms to achieve the effects in the present invention. Compared with the existing dampers, the present invention has the characteristics of simple structure, light weight and high working efficiency, can be flexibly improved and designed according to actual needs, is less affected by temperature, and can greatly improve the reliability of the entire spacecraft deployment system.

[0073] In the description of the present application, it should be understood that the orientation or positional relationship indicated by the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation to the present application.

[0074] The specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Without conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. A passive rotary damper, characterized in that, it includes an outer sleeve member and a damping member disposed in the outer sleeve member; the damping member is configured with a driving input rotor (4) and elastic damping reed pieces (3) arranged circumferentially along the driving input rotor (4). When the driving input rotor (4) rotates, due to the elastic interference of the elastic damping reed pieces (3), the driving input rotor (4) is subjected to a damping torque, thereby reducing the movement speed of the driving input rotor (4). Among them, the elastic interference allows the driving input rotor (4) to rotate through the elastic damping reed pieces (3); the outer sleeve member includes an outer sleeve (2) and a rear end cover (1) and a front end cover (5) respectively disposed at both ends of the outer sleeve (2). Among them, the end of the front end cover (5) is the first fixed end, and the end of the driving shaft (8) of the driving input rotor (4) extends to the outside of the rear end cover (1) as the second fixed end. Both the first fixed end and the second fixed end are used to connect the deployment mechanism; the damping torque includes frictional interference and magnetic interference force; the magnetic interference force is that a magnet is arranged on the outer sleeve (2) to generate a magnetic force with the magnet of the driving input rotor (4).

2. The passive rotary damper according to claim 1, characterized in that, the elastic damping reed pieces (3) are made of magnetic material.

3. The passive rotary damper according to claim 1, characterized in that, the cross-section of the driving input rotor (4) is an elliptical structure, and the cross-section of the elastic damping reed pieces (3) is an involute structure with opposite openings; or an arc structure with opposite openings. Among them, the arc structure is a section of arc or multiple sections of arcs arranged continuously or discontinuously; wherein, when the driving input rotor (4) rotates, the elastic damping reed pieces (3) can block and interfere with the long-axis vertices of the driving input rotor (4).

4. The passive rotary damper according to claim 3, characterized in that, a second permanent magnet (41) is arranged at the long-axis vertex of the driving input rotor (4), and a first permanent magnet (21) is arranged on the outer sleeve (2). The magnetic pole directions of the second permanent magnet (41) and the first permanent magnet (21) are opposite.

5. The passive rotary damper according to claim 1, characterized in that, both ends of the driving input rotor (4) are respectively rotatably matched with the rear end cover (1) and the front end cover (5) by a rear end cover fixed bearing (6) and a front end cover fixed bearing (7).

6. The passive rotary damper according to claim 1, characterized in that, The inner wall of the outer sleeve (2) is provided with damping grooves (23). The circumferential direction of the driving input rotor (4) is provided with rotor guide rods (42). The ends of the rotor guide rods (42) are provided with magnetic materials and extend into the damping grooves (23). There is a gap between the ends of the rotor guide rods (42) and the damping grooves (23). The gap is filled with magnetic particles so that when the driving input rotor (4) rotates, the ends of the rotor guide rods (42) move in the damping grooves (23) to generate damping and thus decelerate.

7. The passive rotary damper according to claim 1, characterized in that one row or multiple rows of needle-shaped protrusions (22) are arranged at intervals on the inner wall of the outer sleeve (2). When the driving input rotor (4) rotates, it is blocked and interfered by the needle-shaped protrusions (22), causing the needle-shaped protrusions (22) to undergo plastic deformation or be cut off, thereby generating damping for the driving input rotor (4) and thus decelerating.

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