CN116123243A - Lightweight rotary viscous damper suitable for aerospace field - Google Patents

Abstract

The invention belongs to the field of viscous dampers, and discloses a lightweight rotary viscous damper suitable for the aerospace field, which comprises a rotating shaft, wherein a plurality of grooves are formed in the middle of the rotating shaft at equal intervals in the circumferential direction, blades are connected in each groove in a sliding manner, springs are connected between the blades and the grooves, an upper shell and a lower shell are covered outside the rotating shaft, the upper shell and the lower shell are connected together through bolts, a cavity for the rotation of the blades is formed in the centers of the upper shell and the lower shell, viscous liquid is filled in the cavity, a guide rail which is connected with the blades in a sliding manner is further arranged in the cavity, damping holes are further communicated in the upper shell, end covers are connected to the upper shell or the lower shell through bolts, and a through hole for the rotating shaft to pass through is formed in each end cover. The invention solves the problems that the existing damper needs an external control source to control damping force and cannot change along with speed change, has compact, simple and light structure, does not need an external damping control source, and is suitable for an unfolding buffer device of an aerospace mechanism.

Description

Lightweight rotary viscous damper suitable for aerospace field

Technical Field

The invention relates to the field of viscous dampers, in particular to a lightweight rotary viscous damper suitable for the aerospace field.

Background

At present, large-sized aerospace devices such as solar sails, antennas and battery arrays are all developed towards the trend of flexibility and light weight, and the devices are generally stored in a coiled form before being launched, and are unfolded into a specific shape for working after being launched. In order to prevent excessive acceleration at the end of deployment from generating a large impact load on the whole during deployment, it is generally necessary to introduce a deployment damper. The unfolding buffer device generally acts on the end of unfolding, and the unfolding speed is slowed down by a damper arranged at the end of unfolding so as to reduce impact load, but the currently applied damper has the defects of being capable of rotating a certain angle only, requiring an external control source to control damping force, having complex mechanism, having larger overall mass and the like. Under the trend of light weight development of aerospace mechanisms, how to make the damper simple and light in structure, free from an external control source, realize full-circle rotation and change of damping force along with speed change is an important problem to be considered in the design process of the damper for aerospace application.

Disclosure of Invention

The invention aims to provide a lightweight rotary viscous damper suitable for the aerospace field, so as to solve the problems that the existing damper needs an external control source to control damping force and cannot change along with speed change.

In order to achieve the above object, the present invention provides the following technical solutions:

the utility model provides a lightweight rotation type viscous damper suitable for aerospace field, includes the pivot of being connected with external transmission, a plurality of recesses have been seted up to the epaxial middle part circumference equidistance, every equal sliding connection has the blade in the recess, be connected with the spring between blade and the recess, the pivot exosuit has last casing and lower casing, it is in the same place with lower casing bolted connection to go up the casing, the cavity that supplies blade pivoted has been seted up at the center of going up casing and lower casing, the intussuseption of cavity is filled with viscous liquid, still be equipped with the guide rail with blade sliding connection in the cavity, still communicate in the last casing has the damping hole, equal bolted connection has the end cover on going up casing or the lower casing, every all open the through-hole that supplies the pivot to pass on the end cover.

Further, the shape of the guide rail comprises two circular arc curve sections with concentric centers and different diameters and a transition curve section connected between two ends of the two circular arc curve sections, and the span of each circular arc curve section or each transition curve section is 90 degrees.

Through the arrangement, the rotating shaft can rotate around the whole circle, and meanwhile, the blades can push viscous liquid to flow through the damping holes, so that damping force is provided; the transition curve section has the effect of realizing smooth transition of the blade from a large (small) arc to a small (large) arc, and can effectively prevent impact force caused by abrupt change of pressure or friction force from the guide rail to which the blade is subjected.

Further, the transition curve segment is:

wherein a and b are constants, and the radius r of the circular arc curve with larger diameter in the circular arc curve section ₁ Radius r of smaller diameter arc curve in arc curve segment =a+b ₂ ＝a-b。

Further, the blade is in sliding sealing connection with the groove.

Compared with the prior art, the invention has the beneficial effects that:

the damping force generating device is simple in structure, does not have an external control source, can realize whole rotation, generates damping force which is increased along with speed increase, and is suitable for a buffer device in the aerospace field.

Drawings

FIG. 1 is an exploded view of a lightweight rotary viscous damper of the present invention suitable for use in the aerospace field;

FIG. 2 is a top view of a lightweight rotary viscous damper suitable for use in the aerospace field of the present invention;

FIG. 3 is a cross-sectional view of A-A of FIG. 2;

FIG. 4 is a cross-sectional view of B-B in FIG. 2;

FIG. 5 is a schematic view of a guide rail curve in the present embodiment;

FIG. 6 is a first state diagram of the operation of a lightweight rotary viscous damper suitable for use in the aerospace field of the present invention;

FIG. 7 is a second state diagram of the operation of a lightweight rotary viscous damper suitable for use in the aerospace field of the present invention;

fig. 8 is a third state diagram of the operation of a lightweight rotary viscous damper suitable for use in the aerospace field of the present invention.

Detailed Description

The invention is described in further detail below with reference to the attached drawings and embodiments:

reference numerals in the drawings of the specification include: the lower end cover 101, the upper end cover 102, the lower housing 2, the blades 3, the upper housing 4, the rotating shaft 5, the springs 6, the guide rails 7, the damping holes 8, the first blades 301, the second blades 302, the third blades 303, the fourth blades 304, the high pressure area H and the low pressure area L.

As shown in fig. 1-5, a lightweight rotary viscous damper suitable for aerospace field includes a rotating shaft 5 connected with an external transmission device, four grooves are circumferentially equidistant in the middle of the rotating shaft 5, each groove is internally provided with a blade 3 in a sliding sealing connection manner, each blade 3 is cuboid, and one side of each blade 3 far away from a spring 6 adopts an arc design. A spring 6 is connected between each blade 3 and the closed end of the groove, and one side, far away from the spring 6, of each blade 3 is tightly attached to a guide rail 7 under the action of the spring 6; the four blades 3 are named as a first blade 301, a second blade 302, a third blade 303 and a fourth blade 304, respectively. The pivot 5 cladding has last casing 4 and lower casing 2 outward, goes up casing 4 and lower casing 2 and links together through bolt and nut, and the cavity that supplies blade 3 pivoted has all been seted up at the center of going up casing 4 and lower casing 2, and the cavity intussuseption is filled with viscous liquid, and viscous liquid adopts the dimethyl silicone oil that has certain viscosity in this embodiment. The rotating shaft 5 is respectively sealed with the upper shell 4 or the lower shell 2 in an oil seal mode, and an O-shaped sealing ring is arranged at the joint of the upper shell 4 and the lower shell 2. The cavity is also provided with a guide rail 7 which is in sliding connection with the blade 3, and a damping hole 8 which provides viscous liquid circulation is communicated with the upper shell 4. The upper shell 4 or the lower shell 2 is connected with end covers through bolts, each end cover comprises an upper end cover 102 and a lower end cover 101, each end cover is provided with a through hole for the rotating shaft 5 to pass through, and the rotating shaft 5 is positioned through the end covers, shaft shoulders, deep groove ball bearings and the like.

The shape of the guide rail 7 comprises two circular arc curve sections with concentric centers and different diameters and a transition curve section connected between two ends of the two circular arc curve sections, wherein the two circular arc curve sections with different diameters are a large circular arc section and a small circular arc section which are described below, and the two transition curve sections play a role in connecting the large circular arc section and the small circular arc section. The two arc curve sections and the two transition curve sections are arranged at intervals of 180 degrees, the centers of the two arc curves and the two transition curve sections are positioned on the center of the rotating shaft 5, and the span of each arc curve section or each transition curve section is 90 degrees.

In order to realize smooth transition of the large arc section and the small arc section, the transition curve section is as follows:

wherein a and b are constants, and the radius r of the large arc section ₁ =a+b, radius of small arc segment r ₂ ＝a-b。

The working procedure of this embodiment is:

the rotating shaft 5 is driven to rotate through an external transmission device, the rotating shaft 5 rotates and then drives the blades 3 to slide along the grooves, meanwhile, the blades do telescopic motion along the grooves under the action of the guide rail 7, viscous liquid with certain viscosity in the cavity of the upper shell 4 or the lower shell 2 is pushed to flow, when the viscous liquid flows through the damping holes 8, the flow area is rapidly reduced, the hydraulic pressure is rapidly increased, and damping force for preventing the rotating shaft 5 from rotating is generated.

When the shaft 5 rotates clockwise, the blade 3 is driven to move along the guide rail 7, and three working stages exist.

In the first state, as shown in fig. 6, the first vane 301 is located at the beginning of the large arc section on the guide rail 7 and is also the ending of the transitional curve section, the second vane 302 is located at the ending of the large arc section on the guide rail 7 and is also the beginning of the transitional curve section, the third vane 303 is located at the beginning of the small arc section on the guide rail 7 and is also the ending of the transitional curve section, and the fourth vane 304 is located at the ending of the small arc section on the guide rail 7 and is also the beginning of the transitional curve section. The viscous liquid between the second blade 302 and the third blade 303 is compressed at this time, and this region is in a high pressure state, while the other regions are in a low pressure state. The boundaries of the second blade 302 and the third blade 303 at the high pressure area H and the low pressure area L are subjected to the liquid pressure, wherein the viscous liquid pressure applied to the second blade 302 is opposite to the moving direction, and the pressure is expressed as a damping force.

In the second state, as shown in fig. 7, the first vane 301 slides along the large circular arc section on the guide rail 7, pushing the viscous liquid to flow clockwise toward the damping hole 8, the second vane 302 slides along the transition curve section on the guide rail 7 while the second vane 302 contracts, the third vane 303 slides along the small circular arc section on the guide rail 7, and the fourth vane 304 slides along the transition curve section on the guide rail 7 while the fourth vane 304 extends. At this time, the viscous liquid between the first blade 301, the second blade 302, and the third blade 303 is compressed, and this region is in a high-pressure state, while the other regions are in a low-pressure state. The boundaries of the first vane 301 and the third vane 303 at the high pressure area H and the low pressure area L are subjected to the liquid pressure, wherein the liquid pressure applied to the first vane 301 is opposite to the movement direction, and the pressure is expressed as a damping force.

In a third state, as shown in fig. 8, the first vane 301 slides to the end of the large arc segment on the rail 7, the second vane 302 slides to the end of the transition curve segment on the rail 7, the third vane 303 slides to the end of the small arc segment on the rail 7, the fourth vane 304 slides to the end of the transition curve segment on the rail 7, at this time, the liquid between the first vane 301 and the second vane 302 is compressed, the region is in a high pressure state, and the other regions are in a low pressure state. The boundaries of the first vane 301 and the second vane 302 located at the high pressure area H and the low pressure area L are subjected to the liquid pressure, wherein the liquid pressure applied to the first vane 301 is opposite to the movement direction, and the pressure is expressed as a damping force.

When the rotating shaft 5 rotates all the time, the blades 3 always repeat the above three working states to continuously push liquid to move in the cavity, and a stable high-pressure area H and a stable low-pressure area L are kept in the rotating process, so that uninterrupted damping force is provided in the whole rotation.

The damping force provided by the damper consists of three parts: the friction force applied when the vane 3 slides on the guide rail 7, the damping force generated by the abrupt change of the flow cross section when the viscous liquid passes through the damping hole 8, and the viscous friction force of the viscous liquid flow.

The foregoing is merely exemplary of the present invention and embodiments of the present invention are not described herein in any way with reference to common general knowledge of the particular technical scheme or characteristics. It should be noted that, for those skilled in the art, several variations and modifications can be made without departing from the technical solution of the present invention, and these should also be regarded as the protection scope of the present invention, which does not affect the effect of the implementation of the present invention and the practical applicability of the patent. The protection scope of the present application shall be subject to the content of the claims, and the description of the specific embodiments and the like in the specification can be used for explaining the content of the claims.

Claims (4)

1. A lightweight rotary viscous damper suitable for aerospace field, its characterized in that: including the pivot of being connected with external transmission, a plurality of recesses have been seted up to the epaxial middle part circumference equidistance, every equal sliding connection has the blade in the recess, be connected with the spring between blade and the recess, the pivot outer cladding has last casing and lower casing, it is in the same place with lower casing bolted connection to go up the casing, the cavity that supplies blade pivoted has been seted up at the center of going up casing and lower casing, the cavity intussuseption is filled with viscous liquid, still be equipped with in the cavity with blade sliding connection's guide rail, still the intercommunication has the damping hole in the epitheca, equal bolted connection has the end cover on last casing or the lower casing, every all open the through-hole that supplies the pivot to pass on the end cover.

2. The lightweight rotary viscous damper for use in the aerospace field of claim 1, wherein: the guide rail comprises two circular arc curve sections with concentric centers and different diameters and a transitional curve section connected between two ends of the two circular arc curve sections, wherein the span of each circular arc curve section or the transitional curve section is 90 degrees.

3. The lightweight rotary viscous damper for use in the aerospace field of claim 2, wherein: the transition curve section is as follows:

wherein a and b are constants, and the radius r of the circular arc curve with larger diameter in the circular arc curve section ₁ Radius r of smaller diameter arc curve in arc curve segment =a+b ₂ ＝a-b。

4. The lightweight rotary viscous damper for use in the aerospace field of claim 1, wherein: the blade is in sliding sealing connection with the groove.

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