CN115045944B - Adjustable viscous damper for spacecraft - Google Patents
Adjustable viscous damper for spacecraft Download PDFInfo
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- CN115045944B CN115045944B CN202210848679.4A CN202210848679A CN115045944B CN 115045944 B CN115045944 B CN 115045944B CN 202210848679 A CN202210848679 A CN 202210848679A CN 115045944 B CN115045944 B CN 115045944B
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- 230000000903 blocking effect Effects 0.000 claims abstract description 106
- 238000013016 damping Methods 0.000 claims abstract description 54
- 239000007788 liquid Substances 0.000 claims abstract description 21
- 239000000463 material Substances 0.000 claims abstract description 12
- 238000007789 sealing Methods 0.000 claims description 91
- 230000004888 barrier function Effects 0.000 claims description 37
- 230000003287 optical effect Effects 0.000 claims description 16
- 230000008859 change Effects 0.000 claims description 10
- 230000000149 penetrating effect Effects 0.000 claims description 6
- 239000012530 fluid Substances 0.000 abstract description 21
- 230000007246 mechanism Effects 0.000 abstract description 20
- 230000002596 correlated effect Effects 0.000 abstract description 3
- 230000001105 regulatory effect Effects 0.000 abstract 2
- 230000000875 corresponding effect Effects 0.000 description 11
- 238000000926 separation method Methods 0.000 description 9
- 230000000694 effects Effects 0.000 description 5
- 229920001971 elastomer Polymers 0.000 description 3
- 239000000806 elastomer Substances 0.000 description 3
- 238000003780 insertion Methods 0.000 description 3
- 230000037431 insertion Effects 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 238000010008 shearing Methods 0.000 description 3
- 238000010521 absorption reaction Methods 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 2
- 230000001276 controlling effect Effects 0.000 description 2
- 208000002925 dental caries Diseases 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000004458 analytical method Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 230000000452 restraining effect Effects 0.000 description 1
- 230000001629 suppression Effects 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F9/00—Springs, vibration-dampers, shock-absorbers, or similarly-constructed movement-dampers using a fluid or the equivalent as damping medium
- F16F9/10—Springs, vibration-dampers, shock-absorbers, or similarly-constructed movement-dampers using a fluid or the equivalent as damping medium using liquid only; using a fluid of which the nature is immaterial
- F16F9/12—Devices with one or more rotary vanes turning in the fluid any throttling effect being immaterial, i.e. damping by viscous shear effect only
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F9/00—Springs, vibration-dampers, shock-absorbers, or similarly-constructed movement-dampers using a fluid or the equivalent as damping medium
- F16F9/10—Springs, vibration-dampers, shock-absorbers, or similarly-constructed movement-dampers using a fluid or the equivalent as damping medium using liquid only; using a fluid of which the nature is immaterial
- F16F9/12—Devices with one or more rotary vanes turning in the fluid any throttling effect being immaterial, i.e. damping by viscous shear effect only
- F16F9/125—Devices with one or more rotary vanes turning in the fluid any throttling effect being immaterial, i.e. damping by viscous shear effect only characterised by adjustment means
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F9/00—Springs, vibration-dampers, shock-absorbers, or similarly-constructed movement-dampers using a fluid or the equivalent as damping medium
- F16F9/32—Details
- F16F9/3207—Constructional features
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F9/00—Springs, vibration-dampers, shock-absorbers, or similarly-constructed movement-dampers using a fluid or the equivalent as damping medium
- F16F9/32—Details
- F16F9/34—Special valve constructions; Shape or construction of throttling passages
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F9/00—Springs, vibration-dampers, shock-absorbers, or similarly-constructed movement-dampers using a fluid or the equivalent as damping medium
- F16F9/32—Details
- F16F9/36—Special sealings, including sealings or guides for piston-rods
- F16F9/369—Sealings for elements other than pistons or piston rods, e.g. valves
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Fluid-Damping Devices (AREA)
Abstract
An adjustable viscous damper for a spacecraft does not need external energy driving and generates damping force (moment) by means of the damper moving along with a mechanism; the stator blocking piece and the main rotor blocking piece divide the interior of the stator shell into two cavities; the two cavities are communicated through the throttle hole; viscous liquid damping materials are injected into the two cavities, the area of the throttle hole is regulated through the sub-rotor blocking piece or the plugboard, the rotation damping is positively correlated with the flow velocity in the throttle hole, the flow velocity of fluid is influenced by the flow area of the throttle hole, and further the regulation of the damping can be realized by regulating the flow area of the throttle hole, so that the application range of the damper is expanded, and the consistency of products is improved; the solar energy solar array can be applied to various application scenes in the aerospace fields such as solar array expansion, space manipulator rotation, satellite antenna rotation and the like; simple structure, low cost, small volume and adjustable damping force.
Description
Technical Field
The invention belongs to the technical field of aerospace, and particularly relates to an adjustable viscous damper for a spacecraft.
Background
Vibration induced by various reasons in a spacecraft during multiple dynamic processes such as launching, mechanism unfolding, attitude adjustment, changing of flight orbits and the like is a main factor affecting structural strength, system reliability and safety, task completion quality, system stability and satellite life. In particular, for large flexible spacecraft structures, in addition to the large-amplitude low-frequency vibrations occurring during the launching process, the low-frequency vibrations generated during the on-orbit operation due to posture adjustment or mechanism deployment are also not negligible.
At present, many disposable unfolding mechanisms on a spacecraft adopt elastic elements as power sources and are unfolded in a rotating mode, if restraining measures cannot be carried out, certain impact is inevitably generated on the spacecraft when the mechanisms are unfolded in place, the working performance and control precision of high-precision and high-resolution equipment on the spacecraft are affected, and failure or even damage of key components is caused.
Because the dynamic environments are random and cannot be avoided in structural design, corresponding vibration suppression or vibration isolation measures are needed to improve the dynamic performance, the reliability and the safety of the spacecraft, and a known effective solution in the related art is to increase the damping level of the whole or partial structure of the spacecraft by adopting a damping enhancement structure and absorb or dissipate the vibration energy transmitted from a vibration source to a payload through the structure of the spacecraft by adopting a damper.
The existing viscous damper is mainly applied to the control of linear reciprocating motion, is a gap type fluid damper, fluid flows through an annular gap, and the main reason for the resistance is fluid shearing force. The requirement of controlling vibration absorption by a large amount of rotation exists in the spacecraft mechanism, and the application expansion direction of the viscous damper is realized.
CN213808580U discloses a rotary viscous damper, which is axially arranged at intervals of multiple groups, and has a complicated mechanical structure, high cost, high requirement on manufacturing process and non-adjustable damping moment.
CN112797105a discloses a rotary viscous damper, in which viscous liquid flows between a screw and an internal thread gap of a fitting hole after being extruded, thereby achieving a damping effect. The damper and the existing viscous damper with linear motion are gap type fluid dampers, and fluid flows through the annular gap to generate shearing force, so that a damping effect is achieved. The contact area between the damper moving part and the cavity is large, so that the volume in the length direction is large, the damping moment is not adjustable, and the application occasion is greatly limited.
CN103403388A discloses a rotary damper which resists the damping moment of the applied rotational force by opening and closing of check valves on the rotary blades, which structure causes the damping force direction of the damper to be unidirectional only, limiting the application of the damper. Meanwhile, a check valve is added on the side face of the rotary blade, an elastomer and a valve needle structure are arranged in the check valve, the elastomer is opened through the rotary force, viscous fluid passes through the check valve, the check valve can be opened only under the condition that the rotary force is larger than the preset elastic force of the spring due to the fact that the elastomer has a certain elastic force, and when the rotary force is smaller than the preset elastic force, the check valve is closed, the damper cannot play a damping role at the moment, and the risk of damage to adjacent mechanisms is seriously caused. Meanwhile, the processing difficulty of forming the special-shaped holes on the blade parts is high, the assembly is difficult, the structure is complex, and the damping force is not adjustable.
Disclosure of Invention
The invention provides an adjustable viscous damper for a spacecraft, which aims at overcoming the defects in the prior art and solves or partially solves the problems pointed out in the background art.
The technical scheme for solving the technical problems is as follows: in a first aspect, an adjustable viscous damper for a spacecraft is provided, comprising a stator housing, a sealing cover plate, a stator barrier, a main rotating shaft, a main rotor barrier, a sub rotating shaft and a sub rotor barrier;
the top end of the stator shell is connected with the sealing cover plate; the stator blocking piece is positioned in the stator shell, and the edge of the stator blocking piece is fixedly connected with the inner wall of the stator shell;
the top end of the main rotating shaft extends out of the stator housing from the center of the sealing cover plate, and the bottom end of the main rotating shaft extends out of the stator housing from the bottom center of the stator housing;
the main rotor blocking piece comprises a rotary cylinder and a blocking part, the main rotating shaft passes through the center of the rotary cylinder, one side of the blocking part is connected with the side part of the rotary cylinder, and the other side of the blocking part contacts the inner wall of the stator shell;
the stator blocking piece is provided with an orifice, the rotor blocking piece is positioned at the orifice, and the rotor blocking piece is connected with the rotor rotating shaft;
the stator barrier and the main rotor barrier divide the interior of the stator housing into two cavities; the two cavities are communicated through the throttling hole; viscous liquid damping material is injected into the two cavities.
As a preferable scheme of the adjustable viscous damper for the spacecraft, the sealing cover plate is disc-shaped, and the stator shell is cylindrical; the edge contact part of the sealing cover plate and the stator shell is fixed through screws.
As a preferable scheme of the adjustable viscous damper for the spacecraft, the sealing cover plate is provided with a first through hole and a second through hole; the top end of the main rotating shaft extends out from the first through hole to the upper part of the sealing cover plate;
the stator blocking piece is provided with a third through hole; the sub-rotating shaft is inserted into the third through hole through the second through hole, and the third through hole and the throttling hole are in a penetrating and conducting state;
and a fourth through hole is formed in the bottom end of the stator shell, corresponding to the main rotating shaft.
As the preferable scheme of the adjustable viscous damper for the spacecraft, two throttle holes are arranged, and two sub-rotor blocking pieces are arranged corresponding to the throttle holes.
As a preferable scheme of the adjustable viscous damper for the spacecraft, a first sealing ring is arranged at the contact part of the top end of the main rotating shaft and the sealing cover plate; a second sealing ring is arranged at the contact part between the bottom end of the main rotating shaft and the bottom of the stator shell;
and a third sealing ring is arranged at the contact part of the sub rotating shaft and the sealing cover plate.
As the preferable scheme of the adjustable viscous damper for the spacecraft, the side face of the sub-rotating shaft is provided with a groove, and the sub-rotor blocking piece is embedded into the groove.
As the preferable scheme of the adjustable viscous damper for the spacecraft, the main rotating shaft adopts symmetrical stepped shafts, and the middle part of the main rotating shaft forms an optical axis part for installing the rotating cylinder;
the rotary cylinder is fixedly connected with the optical axis part of the main rotating shaft, and the blocking part rotates along with the main rotating shaft through the rotary cylinder.
As the preferable scheme of the adjustable viscous damper for the spacecraft, the sub-rotor blocking piece is driven to rotate by rotating the sub-rotating shaft so as to change the opening amplitude of the throttle hole, and the opening amplitude of the throttle hole is changed so as to change the rotation damping of the main rotor blocking piece.
In a second aspect, the invention also provides an adjustable viscous damper for a spacecraft, which belongs to the technical scheme of deformation of the first aspect, and comprises a stator shell, a sealing cover plate, a stator blocking piece, a main rotating shaft, a main rotor blocking piece and an inserting plate;
the top end of the stator shell is connected with the sealing cover plate; the stator blocking piece is positioned in the stator shell, and the edge of the stator blocking piece is fixedly connected with the inner wall of the stator shell;
the top end of the main rotating shaft extends out of the stator housing from the center of the sealing cover plate, and the bottom end of the main rotating shaft extends out of the stator housing from the bottom center of the stator housing;
the main rotor blocking piece comprises a rotary cylinder and a blocking part, the main rotating shaft passes through the center of the rotary cylinder, one side of the blocking part is connected with the side part of the rotary cylinder, and the other side of the blocking part contacts the inner wall of the stator shell;
a clamping groove is vertically formed in the stator blocking piece, an orifice is formed in the longitudinal direction of the stator blocking piece, and the clamping groove and the orifice are in a penetrating state; the adjusting part is arranged at the position of the plugboard corresponding to the throttling hole, the plugboard is inserted into the stator blocking piece through the clamping groove, and the adjusting part is used for adjusting the shielding amplitude of the throttling hole according to the insertion depth of the plugboard;
the stator barrier and the main rotor barrier divide the interior of the stator housing into two cavities; the two cavities are communicated through the throttling hole; viscous liquid damping material is injected into the two cavities.
As a preferable scheme of the adjustable viscous damper for the spacecraft, the sealing cover plate is disc-shaped, and the stator shell is cylindrical; the edge contact part of the sealing cover plate and the stator shell is fixed through a screw;
the sealing cover plate is provided with a first through hole and a second through hole; the top end of the main rotating shaft extends out from the first through hole to the upper part of the sealing cover plate;
the plugboard is inserted into the clamping groove through the second through hole;
the number of the throttling holes is two, and the number of the adjusting parts is two corresponding to the number of the throttling holes;
a first sealing ring is arranged at the contact part between the top end of the main rotating shaft and the sealing cover plate; a second sealing ring is arranged at the contact part between the bottom end of the main rotating shaft and the bottom of the stator shell;
a third sealing ring is arranged at the contact part of the plugboard and the sealing cover plate;
the main rotating shaft adopts symmetrical stepped shafts, and an optical axis part for installing the rotating drum is formed in the middle part of the main rotating shaft;
the rotary cylinder is fixedly connected with the optical axis part of the main rotating shaft, and the blocking part rotates along with the main rotating shaft through the rotary cylinder.
The invention has the advantages that external energy drive is not needed, and damping force (moment) is generated by the damper moving along with the mechanism; the stator blocking piece and the main rotor blocking piece divide the interior of the stator shell into two cavities; the two cavities are communicated through the throttle hole; viscous liquid damping materials are injected into the two cavities, and the area of the throttling holes is adjusted through the sub-rotor blocking piece or the plugboard, so that the damping is adjusted, the application range of the damper is expanded, and the consistency of products is improved; the solar energy solar array can be applied to various application scenes in the aerospace fields such as solar array expansion, space manipulator rotation, satellite antenna rotation and the like; simple structure, low cost, small volume and adjustable damping force.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below. It will be apparent to those of ordinary skill in the art that the drawings in the following description are exemplary only and that other implementations can be obtained from the extensions of the drawings provided without inventive effort.
The structures, proportions, sizes, etc. shown in the present specification are shown only for the purposes of illustration and description, and are not intended to limit the scope of the invention, which is defined by the claims, so that any structural modifications, changes in proportions, or adjustments of sizes, which do not affect the efficacy or the achievement of the present invention, should fall within the ambit of the technical disclosure.
FIG. 1 is an exploded schematic view of an adjustable viscous damper for a spacecraft according to embodiment 1 of the present invention;
FIG. 2 is a schematic longitudinal section view of an adjustable viscous damper for a spacecraft according to embodiment 1 of the present invention;
FIG. 3 is a schematic cross-sectional view of an adjustable viscous damper for a spacecraft provided in embodiment 1 of the present invention;
FIG. 4 is a schematic longitudinal section of an adjustable viscous damper for a spacecraft according to embodiment 2 of the present invention;
fig. 5 is a schematic cross-sectional view of an adjustable viscous damper for a spacecraft according to embodiment 2 of the present invention.
In the figure, 1, a stator housing; 2. sealing the cover plate; 3. a stator barrier; 4. a main rotating shaft; 5. a primary rotor barrier; 6. a sub-rotating shaft; 7. a sub-rotor barrier; 8. a rotary drum; 9. a blocking portion; 10. an orifice; 11. a cavity; 12. a first through hole; 13. a second through hole; 14. a third through hole; 15. a fourth through hole; 16. a first seal ring; 17. a second seal ring; 18. a third seal ring; 19. inserting plate; 20. a clamping groove; 21. an adjusting part.
Detailed Description
In order that the above objects, features and advantages of the invention will be readily understood, a more particular description of the invention will be rendered by reference to the appended drawings. In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present invention. The present invention may be embodied in many other forms than described herein and similarly modified by those skilled in the art without departing from the spirit of the invention, whereby the invention is not limited to the specific embodiments disclosed below.
Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. The terminology used herein in the description of the invention is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. The term "and/or" as used herein includes any and all combinations of one or more of the associated listed items.
Damping technology is an important component of structural dynamics, has important application in the aerospace field, and is mainly used for reducing impact loads in various space mechanism movements. In order to realize the precise control of various movements of the space mechanism, technicians develop various types of dampers such as viscous dampers, vortex dampers, mechanical friction dampers and the like by combining different application scenes in the aerospace field.
The viscous damper is driven by no external energy source, generates damping force (moment) only by virtue of the damper moving along with the mechanism, has the characteristics of simple structure, lower cost and reliable performance, is widely applied to a spacecraft unfolding mechanism, and is a general product of the aerospace mechanism. The working principle is that part of energy in the motion process of the mechanism is dissipated by using the viscous energy consumption effect of the viscous liquid damping material, so that the purpose of reducing impact is achieved.
The existing viscous damper is mainly applied to the control of linear reciprocating motion, is a gap type fluid damper, fluid flows through an annular gap, and the main reason for the resistance is fluid shearing force. The requirement of controlling vibration absorption by a large amount of rotation exists in the spacecraft mechanism, and the application expansion direction of the viscous damper is realized. The following embodiments are provided for this purpose.
Example 1
Referring to fig. 1, 2 and 3, embodiment 1 of the present invention provides an adjustable viscous damper for a spacecraft, which comprises a stator housing 1, a sealing cover plate 2, a stator barrier 3, a main rotating shaft 4, a main rotor barrier 5, a sub rotating shaft 6 and a sub rotor barrier 7;
the top end of the stator shell 1 is connected with the sealing cover plate 2; the stator blocking piece 3 is positioned in the stator housing 1, and the edge of the stator blocking piece 3 is fixedly connected with the inner wall of the stator housing 1;
the top end of the main rotating shaft 4 extends out of the stator housing 1 from the center of the sealing cover plate 2, and the bottom end of the main rotating shaft 4 extends out of the stator housing 1 from the bottom center of the stator housing 1;
the main rotor blocking piece 5 comprises a rotary cylinder 8 and a blocking part 9, the main rotating shaft 4 passes through the center of the rotary cylinder 8, one side of the blocking part 9 is connected with the side part of the rotary cylinder 8, and the other side of the blocking part 9 contacts the inner wall of the stator housing 1;
the sub-rotating shaft 6 is inserted into the stator blocking piece 3 through the sealing cover plate 2, the stator blocking piece 3 is provided with an orifice 10, the sub-rotor blocking piece 7 is positioned at the orifice 10, and the sub-rotor blocking piece 7 is connected with the sub-rotating shaft 6;
the stator barrier 3 and the main rotor barrier 5 divide the interior of the stator housing 1 into two cavities 11; the two cavities 11 are communicated through an orifice 10; the inside of the two cavities 11 is filled with a viscous liquid damping material.
In the embodiment, the sealing cover plate 2 is disc-shaped, and the stator housing 1 is cylindrical; the edge contact portion of the sealing cover plate 2 and the stator housing 1 is fixed by screws. The sealing cover plate 2 is provided with a first through hole 12 and a second through hole 13; the top end of the main rotating shaft 4 extends out from the first through hole 12 to the upper part of the sealing cover plate 2; the stator barrier 3 is provided with a third through hole 14; the sub-rotating shaft 6 is inserted into the third through hole 14 through the second through hole 13, and the third through hole 14 and the throttle hole 10 are in a penetrating and conducting state; a fourth through hole 15 is arranged at the bottom end of the stator housing 1 corresponding to the position of the main rotating shaft 4. A first sealing ring 16 is arranged at the contact part between the top end of the main rotating shaft 4 and the sealing cover plate 2; a second sealing ring 17 is arranged at the contact part between the bottom end of the main rotating shaft 4 and the bottom of the stator housing 1; the contact part of the sub-rotating shaft 6 and the sealing cover plate 2 is provided with a third sealing ring 18.
Specifically, the shape of the sealing cover plate 2 is disc-shaped, two first through holes 12 and second through holes 13 with different specifications are formed in the sealing cover plate, annular grooves are distributed in the first through holes 12, the second through holes 13 and fourth through holes 15 at the bottom of the stator housing 1, the annular grooves of the first through holes 12 seal the contact part between the top end of the main rotating shaft 4 and the sealing cover plate 2 through a first sealing ring 16, the annular grooves of the second through holes 13 seal the contact part between the top end of the sub rotating shaft 6 and the sealing cover plate 2 through a third sealing ring 18, and the annular grooves of the fourth through holes 15 at the bottom of the stator housing 1 seal the contact part between the bottom of the stator housing 1 and the main rotating shaft 4 through a second sealing ring 17. The first, second and third sealing rings 16, 17 and 18 are designed to prevent leakage of viscous liquid from the interior cavity 11 of the stator housing 1.
Specifically, the stator housing 1 is cylindrical, a mounting hole site is formed in the side surface of the stator housing 1 and is used for mounting the stator blocking piece 3, a series of mounting screw holes are formed in the corresponding peripheral parts of the sealing cover plate 2 and the stator housing 1, and the stator housing 1 is connected with the sealing cover plate 2 through screws in the mounting screw holes. The stator housing 1, the stator barrier 3 and the spatial structure remain relatively motionless as stator parts.
In the present embodiment, the number of the orifices 10 is two, and the number of the sub-rotor barriers 7 is two corresponding to the number of the orifices 10. The side of the sub-rotating shaft 6 is provided with a groove, and the sub-rotor blocking piece 7 is embedded into the groove.
Specifically, the stator blocking member 3 is mounted on a side mounting hole of the stator housing, two orifices 10 are formed in the stator blocking member 3, a cylindrical hole is formed in the length direction of the stator blocking member 3, and the stator blocking member 3 and the stator housing are kept stationary by penetrating through the two orifices 10. The side surface of the sub-rotating shaft 6 is provided with a groove for installing the sub-rotor blocking piece 7, and the sub-rotating shaft 6 passes through a second through hole 13 at the periphery of the sealing cover plate 2 and a cylindrical hole in the length direction of the stator blocking piece 3 to be installed on the stator blocking piece 3. The sub-rotor blocking piece 7 is in a semicircular disc shape and is embedded in a groove on the side face of the sub-rotating shaft 6, and the opening amplitude of the throttle hole 10 can be adjusted along with the rotation of the sub-rotating shaft 6.
In the embodiment, the main rotating shaft 4 adopts symmetrical stepped shafts, and the middle part of the main rotating shaft 4 forms a light shaft part for installing the rotating cylinder 8; the rotary drum 8 is fixedly connected with the optical axis part of the main rotating shaft 4, and the blocking part 9 rotates along with the main rotating shaft 4 through the rotary drum 8.
Specifically, the main rotating shaft 4 is a symmetrical stepped shaft, and the middle section is an optical axis, so that the main rotor blocking piece 5 is conveniently sleeved on the optical axis through the rotary cylinder 8. The main rotating shaft 4 is vertically arranged on the device through a first through hole 12 in the middle of the sealing cover plate 2 and a fourth through hole 15 at the bottom of the stator housing 1. The rotary cylinder 8 is formed with a cylindrical hole through which the intermediate optical axis portion of the main rotation shaft 4 is fitted and fixed (the fixing means may be welding) to the intermediate optical axis portion as a rotor portion. The two ends of the main rotating shaft 4 can be connected with a space mechanism (spacecraft rotating assembly) to transmit the impact generated by the spacecraft into the damper.
In this embodiment, the sub-rotor barrier 7 is rotated by rotating the sub-shaft 6 to change the opening width of the orifice 10, and the opening width of the orifice 10 is changed to change the rotation damping of the main rotor barrier 5.
In particular, the damping force of viscous damping is mainly due to the flow of fluid in the valve or damping orifice, and fluid damping is generally assumed to be viscous damping in an ideal situation. In the technical solution of this embodiment, the stator blocking member 3 may be regarded as a thin wall, the orifice 10 is regarded as a hole on the thin wall, when the fluid flows through the thin wall hole, the fluid viscosity is larger, the aperture is smaller, the fluid may become turbulent flow in the damping hole, and may become laminar flow, and because there is a sudden change of the section to form the restriction, at this time, the on-way resistance and the local resistance in the hole pipe exist at the same time, which causes the pressure of the fluid cavity 11 to be compressed to be greater than the pressure of the fluid cavity 11 to be released, and a pressure difference is formed on both sides of the orifice 10 to generate damping, so that the damping force linearly increases with the increase of the fluid velocity during the flow of the fluid flowing through the thin wall hole, as known from theoretical analysis. I.e., rotational damping is positively correlated to the flow rate within the orifice 10, while fluid flow rate is affected by the flow area of the orifice 10, and thus damping can be adjusted by adjusting the flow area of the orifice 10.
In this embodiment, the stator blocking member 3 may be seen as a thin wall, the orifice 10 may be seen as a hole on the thin wall, the stator blocking member 3 and the main rotor blocking member 5 divide the interior of the stator housing 1 into two cavities 11, the two cavities 11 are connected by the orifice 10, and the opening size of the orifice 10 may be driven by the sub-rotating shaft 6 to adjust the rotation of the sub-rotor blocking member 7 to change the opening width of the orifice 10. The two cavities 11 are filled with viscous liquid damping material, and when the main shaft 4 rotates along with the space mechanism, the main rotor barrier 5 rotates along with the main shaft 4, and a pressure difference is generated in the two cavities 11, so that viscous liquid is forced to flow from one cavity 11 to the other cavity 11 through the orifice 10. Because of the throttling effect, the faster the rotation speed of the main rotating shaft 4, the larger the flow velocity of liquid in the throttling hole 10 and the larger the pressure difference between the two cavities 11, the larger the reaction moment received by the rotor is, so that the rotation damping is generated, and the external force is slowly consumed under the condition of absorbing the kinetic energy of the viscous damping liquid.
In summary, the present invention is provided with a stator housing 1, a sealing cover plate 2, a stator barrier 3, a main shaft 4, a main rotor barrier 5, a sub shaft 6 and a sub rotor barrier 7; the top end of the stator shell 1 is connected with the sealing cover plate 2; the stator blocking piece 3 is positioned in the stator housing 1, and the edge of the stator blocking piece 3 is fixedly connected with the inner wall of the stator housing 1; the top end of the main rotating shaft 4 extends out of the stator housing 1 from the center of the sealing cover plate 2, and the bottom end of the main rotating shaft 4 extends out of the stator housing 1 from the bottom center of the stator housing 1; the main rotor blocking piece 5 comprises a rotary cylinder 8 and a blocking part 9, the main rotating shaft 4 passes through the center of the rotary cylinder 8, one side of the blocking part 9 is connected with the side part of the rotary cylinder 8, and the other side of the blocking part 9 contacts the inner wall of the stator housing 1; the sub-rotating shaft 6 is inserted into the stator blocking piece 3 through the sealing cover plate 2, the stator blocking piece 3 is provided with an orifice 10, the sub-rotor blocking piece 7 is positioned at the orifice 10, and the sub-rotor blocking piece 7 is connected with the sub-rotating shaft 6; the stator barrier 3 and the main rotor barrier 5 divide the interior of the stator housing 1 into two cavities 11; the two cavities 11 are communicated through an orifice 10; the inside of the two cavities 11 is filled with a viscous liquid damping material. The sealing cover plate 2 of the invention is disc-shaped, a first through hole 12 and a second through hole 13 with two different specifications are arranged on the sealing cover plate 2, annular grooves are distributed in the first through hole 12, the second through hole 13 and a fourth through hole 15 at the bottom of the stator housing 1, the annular grooves of the first through hole 12 seal the contact part between the top end of the main rotating shaft 4 and the sealing cover plate 2 through a first sealing ring 16, the annular grooves of the second through hole 13 seal the contact part between the top end of the sub rotating shaft 6 and the sealing cover plate 2 through a third sealing ring 18, and the annular grooves of the fourth through hole 15 at the bottom of the stator housing 1 seal the contact part between the bottom of the stator housing 1 and the main rotating shaft 4 through a second sealing ring 17. The first, second and third sealing rings 16, 17 and 18 are designed to prevent leakage of viscous liquid from the interior cavity 11 of the stator housing 1. The stator housing 1 is cylindrical, mounting holes are formed in the side face of the stator housing 1 and are used for mounting the stator blocking piece 3, a series of mounting screw holes are formed in the corresponding portions of the peripheries of the sealing cover plate 2 and the stator housing 1, and the stator housing 1 is connected with the sealing cover plate 2 through screws. The stator housing 1, the stator barrier 3 and the spatial structure remain relatively motionless as stator parts. The stator separation member 3 is arranged on a side mounting hole of the stator housing, two orifices 10 are formed in the stator separation member 3, a cylindrical hole is formed in the length direction of the stator separation member 3, the stator separation member 3 penetrates through the two orifices 10, and the stator separation member 3 and the stator housing are kept stationary. The side surface of the sub-rotating shaft 6 is provided with a groove for installing the sub-rotor blocking piece 7, and the sub-rotating shaft 6 passes through a second through hole 13 at the periphery of the sealing cover plate 2 and a cylindrical hole in the length direction of the stator blocking piece 3 to be installed on the stator blocking piece 3. The sub-rotor blocking piece 7 is in a semicircular disc shape and is embedded in a groove on the side face of the sub-rotating shaft 6, and the opening amplitude of the throttle hole 10 can be adjusted along with the rotation of the sub-rotating shaft 6. The main rotating shaft 4 is a symmetrical stepped shaft, and the middle section is an optical axis, so that the main rotor blocking piece 5 is conveniently sleeved on the optical axis through the rotary cylinder 8. The main rotating shaft 4 is vertically arranged on the device through a first through hole 12 in the middle of the sealing cover plate 2 and a fourth through hole 15 at the bottom of the stator housing 1. The rotary cylinder 8 is formed with a cylindrical hole through which the intermediate optical axis portion of the main rotation shaft 4 is fitted and fixed with the intermediate optical axis portion as a rotor portion. The two ends of the main rotating shaft 4 can be connected with a space mechanism (spacecraft rotating assembly) to transmit the impact generated by the spacecraft into the damper. Through seeing stator separation piece 3 as the thin wall, orifice 10 sees the hole on the thin wall, and stator separation piece 3 and main rotor separation piece 5 divide into two cavitys 11 with stator shell 1 inside, and two cavitys 11 pass through orifice 10 to be connected, and orifice 10's opening size can be through sub-pivot 6 drive to adjust sub-rotor separation piece 7 rotation and change orifice 10's opening range. The two cavities 11 are filled with viscous liquid damping material, and when the main shaft 4 rotates along with the space mechanism, the main rotor barrier 5 rotates along with the main shaft 4, and a pressure difference is generated in the two cavities 11, so that viscous liquid is forced to flow from one cavity 11 to the other cavity 11 through the orifice 10. Because of the throttling effect, the faster the rotation speed of the main rotating shaft 4, the larger the flow velocity of liquid in the throttling hole 10 and the larger the pressure difference between the two cavities 11, the larger the reaction moment received by the rotor is, so that the rotation damping is generated, and the external force is slowly consumed under the condition of absorbing the kinetic energy of the viscous damping liquid. The invention does not need external energy source driving, and generates damping force (moment) by the damper moving along with the mechanism; the stator barrier 3 and the main rotor barrier 5 divide the interior of the stator housing 1 into two cavities 11; the two cavities 11 are communicated through an orifice 10; viscous liquid damping materials are injected into the two cavities 11, and the area of the throttle hole 10 is adjusted through the sub-rotor blocking piece 7 or the plugboard 19, so that the damping adjustment is realized, the application range of the damper is expanded, and the consistency of products is improved; the solar energy solar array can be applied to various application scenes in the aerospace fields such as solar array expansion, space manipulator rotation, satellite antenna rotation and the like; simple structure, low cost, small volume and adjustable damping force.
Example 2
The principle of damping is based on the fact that rotational damping is positively correlated to the flow rate in the orifice 10, while the fluid flow rate is affected by the flow area of the orifice 10, and thus damping can be adjusted by adjusting the flow area of the orifice 10. Embodiment 2 of the present invention provides a modification of embodiment 1.
Referring to fig. 4 and 5, an adjustable viscous damper for a spacecraft includes a stator housing 1, a sealing cover plate 2, a stator barrier 3, a main rotating shaft 4, a main rotor barrier 5, and an insert plate 19;
the top end of the stator shell 1 is connected with the sealing cover plate 2; the stator blocking piece 3 is positioned in the stator housing 1, and the edge of the stator blocking piece 3 is fixedly connected with the inner wall of the stator housing 1;
the top end of the main rotating shaft 4 extends out of the stator housing 1 from the center of the sealing cover plate 2, and the bottom end of the main rotating shaft 4 extends out of the stator housing 1 from the bottom center of the stator housing 1;
the main rotor blocking piece 5 comprises a rotary cylinder 8 and a blocking part 9, the main rotating shaft 4 passes through the center of the rotary cylinder 8, one side of the blocking part 9 is connected with the side part of the rotary cylinder 8, and the other side of the blocking part 9 contacts the inner wall of the stator housing 1;
a clamping groove 20 is vertically formed in the stator blocking piece 3, an orifice 10 is formed in the longitudinal direction of the stator blocking piece 3, and the clamping groove 20 and the orifice 10 are in a penetrating state; the adjusting part 21 is arranged at the position of the plugboard 19 corresponding to the throttle hole 10, the plugboard 19 is inserted into the stator blocking piece 3 through the clamping groove 20, and the adjusting part 21 is used for adjusting the shielding amplitude of the throttle hole 10 according to the insertion depth of the plugboard 19;
the stator barrier 3 and the main rotor barrier 5 divide the interior of the stator housing 1 into two cavities 11; the two cavities 11 are communicated through an orifice 10; the inside of the two cavities 11 is filled with a viscous liquid damping material.
In the embodiment, the sealing cover plate 2 is disc-shaped, and the stator housing 1 is cylindrical; the edge contact part of the sealing cover plate 2 and the stator housing 1 is fixed by a screw; the sealing cover plate 2 is provided with a first through hole 12 and a second through hole 13; the top end of the main rotating shaft 4 extends out from the first through hole 12 to the upper part of the sealing cover plate 2; the plugboard 19 is inserted into the clamping groove 20 through the second through hole 13; the number of the throttle holes 10 is two, and the number of the adjusting parts is two corresponding to the number of the throttle holes 10; a first sealing ring 16 is arranged at the contact part between the top end of the main rotating shaft 4 and the sealing cover plate 2; a second sealing ring 17 is arranged at the contact part between the bottom end of the main rotating shaft 4 and the bottom of the stator housing 1; a third sealing ring 18 is arranged at the contact part of the plugboard 19 and the sealing cover plate 2; the main rotating shaft 4 adopts symmetrical stepped shafts, and the middle part of the main rotating shaft 4 forms a light shaft part for installing the rotary drum 8; the rotary drum 8 is fixedly connected with the optical axis part of the main rotating shaft 4, and the blocking part 9 rotates along with the main rotating shaft 4 through the rotary drum 8.
The principle of embodiment 2 of the present invention is the same as that of embodiment 1, and only the shielding amplitude of the orifice 10 is changed by adjusting the insertion depth of the insert plate 19, so as to change the flow area of the orifice 10, and other structural designs and principles are the same as those of embodiment 1, and will not be described herein.
The technical features of the above-described embodiments may be arbitrarily combined, and all possible combinations of the technical features in the above-described embodiments are not described for brevity of description, however, as long as there is no contradiction between the combinations of the technical features, they should be considered as the scope of the description.
The above examples illustrate only a few embodiments of the invention, which are described in detail and are not to be construed as limiting the scope of the invention. It should be noted that it will be apparent to those skilled in the art that several variations and modifications can be made without departing from the spirit of the invention, which are all within the scope of the invention. Accordingly, the scope of protection of the present invention is to be determined by the appended claims.
Claims (5)
1. The adjustable viscous damper for the spacecraft is characterized by comprising a stator shell (1), a sealing cover plate (2), a stator blocking piece (3), a main rotating shaft (4), a main rotor blocking piece (5), a sub rotating shaft (6) and a sub rotor blocking piece (7);
the top end of the stator shell (1) is connected with the sealing cover plate (2); the stator blocking piece (3) is positioned in the stator shell (1), and the edge of the stator blocking piece (3) is fixedly connected with the inner wall of the stator shell (1);
the top end of the main rotating shaft (4) extends out of the stator housing (1) from the center of the sealing cover plate (2), and the bottom end of the main rotating shaft (4) extends out of the stator housing (1) from the bottom center of the stator housing (1);
the main rotor blocking piece (5) comprises a rotary cylinder (8) and a blocking part (9), the main rotating shaft (4) passes through the center of the rotary cylinder (8), one side of the blocking part (9) is connected with the side part of the rotary cylinder (8), and the other side of the blocking part (9) contacts the inner wall of the stator housing (1);
the sub-rotating shaft (6) is inserted into the stator blocking piece (3) through the sealing cover plate (2), an orifice (10) is formed in the stator blocking piece (3), the sub-rotor blocking piece (7) is positioned at the orifice (10), and the sub-rotor blocking piece (7) is connected with the sub-rotating shaft (6);
the stator barrier (3) and the main rotor barrier (5) divide the interior of the stator housing (1) into two cavities (11); the two cavities (11) are communicated through the throttle hole (10); viscous liquid damping material is injected into the two cavities (11);
a groove is formed in the side face of the sub-rotating shaft (6), and the sub-rotor blocking piece (7) is embedded into the groove;
the main rotating shaft (4) adopts symmetrical stepped shafts, and an optical axis part for installing the rotating cylinder (8) is formed in the middle part of the main rotating shaft (4);
the rotating cylinder (8) is fixedly connected with the optical axis part of the main rotating shaft (4), and the blocking part (9) rotates along with the main rotating shaft (4) through the rotating cylinder (8);
the sub-rotor blocking piece (7) is driven to rotate by rotating the sub-rotating shaft (6) so as to change the opening amplitude of the throttle hole (10), and the opening amplitude of the throttle hole (10) is changed so as to change the rotation damping of the main rotor blocking piece (5).
2. An adjustable viscous damper for a spacecraft according to claim 1, wherein the sealing cover plate (2) is disc-shaped and the stator housing (1) is cylindrical; the edge contact part of the sealing cover plate (2) and the stator housing (1) is fixed through screws.
3. An adjustable viscous damper for a spacecraft according to claim 1, characterized in that the sealing cover plate (2) is provided with a first through hole (12) and a second through hole (13); the top end of the main rotating shaft (4) extends out from the first through hole (12) to the upper part of the sealing cover plate (2);
the stator blocking piece (3) is provided with a third through hole (14); the sub-rotating shaft (6) is inserted into the third through hole (14) from the second through hole (13), and the third through hole (14) and the throttle hole (10) are in a penetrating and conducting state;
a fourth through hole (15) is formed in the bottom end of the stator housing (1) corresponding to the main rotating shaft (4).
4. A viscous damper with adjustability for spacecraft according to claim 3, characterized in that the number of orifices (10) is two and the number of sub-rotor barriers (7) is two corresponding to the number of orifices (10).
5. An adjustable viscous damper for a spacecraft as claimed in claim 3, wherein a first sealing ring (16) is provided at a contact portion between the top end of the main rotating shaft (4) and the sealing cover plate (2); a second sealing ring (17) is arranged at the contact part between the bottom end of the main rotating shaft (4) and the bottom of the stator housing (1);
and a third sealing ring (18) is arranged at the contact part of the sub rotating shaft (6) and the sealing cover plate (2).
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210848679.4A CN115045944B (en) | 2022-07-19 | 2022-07-19 | Adjustable viscous damper for spacecraft |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210848679.4A CN115045944B (en) | 2022-07-19 | 2022-07-19 | Adjustable viscous damper for spacecraft |
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| CN115045944B true CN115045944B (en) | 2024-01-16 |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN101067430A (en) * | 2001-11-27 | 2007-11-07 | 株式会社索密克石川 | Rotary damper, auto part having rotary damper and rotational motion assistant mechanism |
| CN102840263A (en) * | 2011-06-21 | 2012-12-26 | 株式会社利富高 | Rotary damper |
| CN103527027A (en) * | 2013-09-18 | 2014-01-22 | 陈朝朗 | Rotary damper capable of adjusting torque force |
| CN105769395A (en) * | 2016-04-12 | 2016-07-20 | 上海理工大学 | Electric control hydraulic damping cylinder structure for intelligent knee joint |
| WO2017121418A1 (en) * | 2016-01-11 | 2017-07-20 | Čvut V Praze, Fakulta Strojni | Hydraulic damper |
| CN110382904A (en) * | 2017-03-15 | 2019-10-25 | 奥依列斯工业株式会社 | Rotary type damper |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6899208B2 (en) * | 2001-12-17 | 2005-05-31 | Charles N. VanValkenburgh | Rotary damper |
| US7048098B1 (en) * | 2002-11-12 | 2006-05-23 | Moradian Norick B | Toroidal rotary damper apparatus |
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2022
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Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101067430A (en) * | 2001-11-27 | 2007-11-07 | 株式会社索密克石川 | Rotary damper, auto part having rotary damper and rotational motion assistant mechanism |
| CN102840263A (en) * | 2011-06-21 | 2012-12-26 | 株式会社利富高 | Rotary damper |
| CN103527027A (en) * | 2013-09-18 | 2014-01-22 | 陈朝朗 | Rotary damper capable of adjusting torque force |
| WO2017121418A1 (en) * | 2016-01-11 | 2017-07-20 | Čvut V Praze, Fakulta Strojni | Hydraulic damper |
| CN105769395A (en) * | 2016-04-12 | 2016-07-20 | 上海理工大学 | Electric control hydraulic damping cylinder structure for intelligent knee joint |
| CN110382904A (en) * | 2017-03-15 | 2019-10-25 | 奥依列斯工业株式会社 | Rotary type damper |
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