CN111998028B - Damper for vibration suppression of spacecraft structure - Google Patents
Damper for vibration suppression of spacecraft structure Download PDFInfo
- Publication number
- CN111998028B CN111998028B CN202010798433.1A CN202010798433A CN111998028B CN 111998028 B CN111998028 B CN 111998028B CN 202010798433 A CN202010798433 A CN 202010798433A CN 111998028 B CN111998028 B CN 111998028B
- Authority
- CN
- China
- Prior art keywords
- damper
- damping unit
- unit cell
- laminated sheet
- damping
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 230000001629 suppression Effects 0.000 title description 7
- 238000013016 damping Methods 0.000 claims abstract description 34
- 238000005265 energy consumption Methods 0.000 claims description 3
- 230000000694 effects Effects 0.000 abstract description 8
- 238000010521 absorption reaction Methods 0.000 abstract description 5
- 230000002401 inhibitory effect Effects 0.000 abstract 1
- 238000005516 engineering process Methods 0.000 description 6
- 238000013461 design Methods 0.000 description 3
- 238000011160 research Methods 0.000 description 3
- 230000021715 photosynthesis, light harvesting Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000012141 concentrate Substances 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000000116 mitigating effect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
Images
Classifications
-
- 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
- F16F7/00—Vibration-dampers; Shock-absorbers
- F16F7/08—Vibration-dampers; Shock-absorbers with friction surfaces rectilinearly movable along each other
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/228—Damping of high-frequency vibration effects on spacecraft elements, e.g. by using acoustic vibration dampers
-
- 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
- F16F2222/00—Special physical effects, e.g. nature of damping effects
- F16F2222/04—Friction
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Acoustics & Sound (AREA)
- Vibration Prevention Devices (AREA)
Abstract
The invention discloses a damper for inhibiting structural vibration of a spacecraft, which comprises a damper outer ring (1), a damper inner ring (2) and a plurality of damping unit cells (3), wherein the damping unit cells (3) are uniformly distributed between the damper outer ring (1) and the damper inner ring (2) along the annular direction, and each damping unit cell (3) is stressed along the radial direction. The invention adopts a unit cell structure to be integrally arranged along a ring, overcomes the dead zone effect of the head and the tail boundary, and realizes the effect of circumferential energy absorption of 360 degrees.
Description
Technical Field
The invention belongs to the technical field of vibration impact mitigation, and particularly relates to a damper for suppressing structural vibration of a spacecraft.
Background
The vibration isolation and suppression technology research has very important practical significance. The passive vibration control technology is also called damping control technology, and is a technology which adopts a damper or a damping material, increases the self damping of a spacecraft structure and consumes the structural vibration energy by utilizing the damping energy consumption principle. The method has the advantages of high reliability, easy realization, long service life and relatively mature development. At present, passive damping suppression technology is applied in orbit on various spacecrafts launched abroad. The damper for the spacecraft is the foundation of the passive vibration technology of the spacecraft. Due to the non-maintainability of the spacecraft, the spacecraft damper has extremely high reliability, can adapt to complex environments such as space high vacuum, heat exchange change and the like, and can meet the service life requirement of 5-15 years in orbit. Meanwhile, in order to meet the vibration suppression requirements of different frequency bands and different load environments, various types of damper products need to be developed. The existing damper design and research about the vibration suppression of the aerospace structure concentrates on the aspect of online displacement load, but the research about the suppression of the rotation load is less, and a proper and effective damper design scheme is lacked.
In view of the above, the invention provides a design scheme of a negative-stiffness honeycomb structure of an annular damper, which has the advantages of good structural damping characteristic, high reliability and high robustness, and can be applied to the vibration reduction requirements of relevant mechanical structures of spacecrafts.
Disclosure of Invention
The invention aims to provide a 360-degree circumferential energy absorption damper for suppressing the structural vibration of a spacecraft.
The invention relates to a damper for suppressing structural vibration of a spacecraft, which comprises a damper outer ring 1, a damper inner ring 2 and a plurality of damping unit cells 3; the damping unit cells 3 are uniformly distributed between the outer ring 1 of the damper and the inner ring 2 of the damper along the annular direction; each damping unit cell 3 is stressed in the radial direction.
Further, the damping unit cell 3 is a thin laminated structure and comprises an upper laminated sheet 4, a middle laminated sheet 5 and a lower laminated sheet 6, and the damping unit cell 3 achieves energy dissipation through friction among the upper laminated sheet 4, the middle laminated sheet 5 and the lower laminated sheet 6.
Further, the damping unit cell 3 is formed into a honeycomb shape by coaxially arranging two groups of thin sheet laminated structures.
The invention has the following beneficial effects:
1) according to the annular damping structure, the energy consumption effect is realized by using the damping unit cell, the damping unit cell is of a sheet laminated structure, and the damping effect is realized by using friction energy absorption among the laminated sheets;
2) the annular damping structure provided by the invention adopts a single cell structure to be integrally arranged along an annular shape, so that the blind area effect of the head and the tail boundaries is overcome, and the effect of 360-degree circumferential energy absorption is realized.
Drawings
FIG. 1 is a schematic view of an annular damping structure according to the present invention;
FIG. 2 is a schematic diagram of a damping unit cell structure.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings.
The basic idea of the invention is: the linear damper can only bear plane load in one direction (axial direction) due to the limitation of the structure. For axial surface loads, no force is available. In addition, the linear damper has an end effect at two ends (boundaries), that is, a large stress is generated on a free boundary, which affects the overall energy absorption effect of the structure.
On the basis, the invention provides an annular damper, which comprises a damper outer ring 1, a damper inner ring 2 and a plurality of damping unit cells 3 as shown in figure 1. The damping unit cells 3 are connected end to end and uniformly distributed in the cavities between the outer ring 1 of the damper and the inner ring 2 of the damper along the circumferential direction to form a ring array structure. Each damping unit cell 3 is stressed along the radial direction; radial energy transfer is realized; the number of unit cells and the diameter of the ring can be adjusted according to different application objects.
The damping unit cell 3 is a thin laminated structure and comprises an upper laminated sheet 4, a middle laminated sheet 5 and a lower laminated sheet 6, and the damping unit cell 3 achieves energy dissipation through friction among the upper laminated sheet 4, the middle laminated sheet 5 and the lower laminated sheet 6.
As shown in fig. 2, the damping unit cell 3 is formed in a honeycomb shape by two sets of laminated sheet structures arranged coaxially.
The above embodiments are only for explaining and explaining the technical solution of the present invention, but should not be construed as limiting the scope of the claims. It should be clear to those skilled in the art that any simple modification or replacement based on the technical solution of the present invention may be adopted to obtain a new technical solution, which falls within the scope of the present invention.
Claims (1)
1. The damper for suppressing the structural vibration of the spacecraft is characterized by comprising a damper outer ring (1), a damper inner ring (2) and a plurality of damping unit cells (3); the damper is annular and has a negative-rigidity honeycomb structure, and the damping unit cells (3) are connected end to end and are uniformly distributed between the outer ring (1) and the inner ring (2) of the damper along the annular direction; each damping unit cell (3) is stressed along the radial direction;
the damping unit cell (3) is of a sheet laminated structure and comprises an upper laminated sheet (4), a middle laminated sheet (5) and a lower laminated sheet (6), and the damping unit cell (3) achieves energy consumption through friction among the upper laminated sheet (4), the middle laminated sheet (5) and the lower laminated sheet (6);
the damping unit cell (3) is formed into a honeycomb shape by coaxially arranging two groups of thin sheet laminated structures.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN202010798433.1A CN111998028B (en) | 2020-08-11 | 2020-08-11 | Damper for vibration suppression of spacecraft structure |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN202010798433.1A CN111998028B (en) | 2020-08-11 | 2020-08-11 | Damper for vibration suppression of spacecraft structure |
Publications (2)
Publication Number | Publication Date |
---|---|
CN111998028A CN111998028A (en) | 2020-11-27 |
CN111998028B true CN111998028B (en) | 2022-04-12 |
Family
ID=73462954
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CN202010798433.1A Active CN111998028B (en) | 2020-08-11 | 2020-08-11 | Damper for vibration suppression of spacecraft structure |
Country Status (1)
Country | Link |
---|---|
CN (1) | CN111998028B (en) |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2003042221A (en) * | 2001-07-27 | 2003-02-13 | Tomoe Giken:Kk | Rotational friction damper |
TW200502495A (en) * | 2003-06-06 | 2005-01-16 | George C Lee | A friction damper |
CN103148144A (en) * | 2013-03-14 | 2013-06-12 | 湖南大学 | Energy absorption device |
CN110155375A (en) * | 2018-10-26 | 2019-08-23 | 北京机电工程研究所 | Space debris prevention structure |
CN110985581A (en) * | 2019-12-31 | 2020-04-10 | 北京机电工程研究所 | Repulsion type magnetic force negative stiffness honeycomb structure |
Family Cites Families (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP3572195B2 (en) * | 1998-06-08 | 2004-09-29 | 株式会社日立製作所 | Drum type washing machine |
CN101216087A (en) * | 2008-01-18 | 2008-07-09 | 北京工业大学 | Plate-type friction-changing damper |
AT510239B1 (en) * | 2010-07-29 | 2012-09-15 | Andritz Ag Maschf | DEVICE FOR VIBRATING VIBRATIONS IN A DRIVE TRAIN |
CN202674134U (en) * | 2012-06-12 | 2013-01-16 | 中国科学院工程热物理研究所 | Multi-layer laminated damper |
CN203295962U (en) * | 2013-05-28 | 2013-11-20 | 招商局重庆交通科研设计院有限公司 | Anti-seismic damper for bridge and anti-seismic check block thereof |
CN207538242U (en) * | 2017-06-22 | 2018-06-26 | 蔡崇兴 | Frictional damping formula support pads |
CN109267666B (en) * | 2018-11-07 | 2020-03-13 | 西安建筑科技大学 | Multidirectional laminated variable-stiffness shape memory alloy damper and mounting method thereof |
CN109708214B (en) * | 2018-12-06 | 2020-06-30 | 珠海格力电器股份有限公司 | Vibration reduction structure and compressor vibration reduction assembly |
CN109989610B (en) * | 2019-04-23 | 2024-05-31 | 云南震安减震科技股份有限公司 | Axial damping friction damper |
CN111218998A (en) * | 2020-03-10 | 2020-06-02 | 广州大学 | Metal and composite material laminated damper |
-
2020
- 2020-08-11 CN CN202010798433.1A patent/CN111998028B/en active Active
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2003042221A (en) * | 2001-07-27 | 2003-02-13 | Tomoe Giken:Kk | Rotational friction damper |
TW200502495A (en) * | 2003-06-06 | 2005-01-16 | George C Lee | A friction damper |
CN103148144A (en) * | 2013-03-14 | 2013-06-12 | 湖南大学 | Energy absorption device |
CN110155375A (en) * | 2018-10-26 | 2019-08-23 | 北京机电工程研究所 | Space debris prevention structure |
CN110985581A (en) * | 2019-12-31 | 2020-04-10 | 北京机电工程研究所 | Repulsion type magnetic force negative stiffness honeycomb structure |
Non-Patent Citations (1)
Title |
---|
复合型阻尼器研究进展;颜学渊等;《地震工程与工程振动》;20200615;第40卷(第3期);第54-70页 * |
Also Published As
Publication number | Publication date |
---|---|
CN111998028A (en) | 2020-11-27 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP0886728B1 (en) | Magnus effect wind turbine | |
CN111911333B (en) | High-efficiency piezoelectric control type nanometer friction wave power generation device | |
CN102642611A (en) | Actively deformed stressed-skin structure based on pneumatic muscles | |
CN113737977B (en) | Self-resetting multilayer circular ring spring friction damper | |
CN113374106B (en) | SMA high-energy-consumption self-resetting three-dimensional shock isolation device | |
CN113270210B (en) | Reactor core structure of lightweight heat pipe reactor with low uranium loading capacity | |
CN111998028B (en) | Damper for vibration suppression of spacecraft structure | |
CN112213061A (en) | Multidirectional excitation device and system for helicopter vibration active control system | |
CN110725598A (en) | Friction compound type buckling restrained energy dissipation brace | |
CN207389526U (en) | A kind of flexible covering for deforming aircraft | |
CN110454538B (en) | Composite nested piezodamper for floating offshore wind driven generator | |
CN114524111B (en) | Spacecraft vibration suppression structure and method based on piezoelectric composite material | |
CN213063828U (en) | Fatigue load reduction device for blade of horizontal-axis wind generating set | |
CN110486405B (en) | Vibration isolation system with annular metal rubber vibration isolator | |
CN112886864A (en) | C-type turbulence adjustable series-connection fluid energy piezoelectric energy harvester | |
CN113719412A (en) | Energy collector capable of collecting multiple energy forms | |
CN211622802U (en) | Friction compound type buckling restrained energy dissipation brace | |
CN110081111A (en) | A kind of more ligament chiral structures containing flexible hinge | |
CN109990193A (en) | A kind of multistage concertina honeycomb | |
CN101588116B (en) | Magnetic suspension wind power generator | |
CN110983955A (en) | Anti-seismic support for bridge | |
CN116780939B (en) | Wave power generation floating body based on differential geometric feature nonlinear piezoelectric vibrator | |
CN221257495U (en) | Double-spiral spring and combiner | |
CN214833513U (en) | Laminated rubber vibration isolation connecting device for heat absorption tower and heat absorber steel support | |
CN211404558U (en) | New energy battery safety assembly device |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PB01 | Publication | ||
PB01 | Publication | ||
SE01 | Entry into force of request for substantive examination | ||
SE01 | Entry into force of request for substantive examination | ||
GR01 | Patent grant | ||
GR01 | Patent grant |