CN111059206A - Piezoelectric active vibration damper of flexible solar wing supporting structure - Google Patents
Piezoelectric active vibration damper of flexible solar wing supporting structure Download PDFInfo
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- CN111059206A CN111059206A CN201911383488.XA CN201911383488A CN111059206A CN 111059206 A CN111059206 A CN 111059206A CN 201911383488 A CN201911383488 A CN 201911383488A CN 111059206 A CN111059206 A CN 111059206A
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- flexible solar
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- 230000001133 acceleration Effects 0.000 claims abstract description 20
- 238000013016 damping Methods 0.000 claims abstract description 16
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 4
- 229910000831 Steel Inorganic materials 0.000 claims description 4
- 239000004917 carbon fiber Substances 0.000 claims description 4
- 230000002708 enhancing effect Effects 0.000 claims description 4
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 4
- 239000010959 steel Substances 0.000 claims description 4
- 239000002033 PVDF binder Substances 0.000 claims description 3
- 239000000919 ceramic Substances 0.000 claims description 3
- 229920002981 polyvinylidene fluoride Polymers 0.000 claims description 3
- 239000000853 adhesive Substances 0.000 description 2
- 230000001070 adhesive effect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 241000282414 Homo sapiens Species 0.000 description 1
- 238000004026 adhesive bonding Methods 0.000 description 1
- 230000003321 amplification Effects 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 239000013065 commercial product Substances 0.000 description 1
- 238000002788 crimping Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 238000003199 nucleic acid amplification method Methods 0.000 description 1
- 230000008092 positive effect Effects 0.000 description 1
- 239000000047 product Substances 0.000 description 1
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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
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
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- 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
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
- B64G1/443—Photovoltaic cell arrays
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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
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/002—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion characterised by the control method or circuitry
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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
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/005—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion using electro- or magnetostrictive actuation means
- F16F15/007—Piezo-electric elements being placed under pre-constraint, e.g. placed under compression
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B19/00—Programme-control systems
- G05B19/02—Programme-control systems electric
- G05B19/04—Programme control other than numerical control, i.e. in sequence controllers or logic controllers
- G05B19/042—Programme control other than numerical control, i.e. in sequence controllers or logic controllers using digital processors
- G05B19/0423—Input/output
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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
- F16F2224/00—Materials; Material properties
- F16F2224/02—Materials; Material properties solids
- F16F2224/0283—Materials; Material properties solids piezoelectric; electro- or magnetostrictive
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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
- F16F2230/00—Purpose; Design features
- F16F2230/08—Sensor arrangement
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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
- F16F2230/00—Purpose; Design features
- F16F2230/18—Control arrangements
Abstract
The invention relates to a piezoelectric active vibration damping device of a flexible solar wing supporting structure, which comprises a flexible solar wing supporting structure and a control module, wherein the flexible solar wing supporting structure comprises a solar wing base station and a flexible solar wing supporting structure body; the control module comprises a controller, acceleration sensors, piezoelectric sensors and piezoelectric actuators, the controller is arranged on the solar wing base station, the acceleration sensors are arranged on the supporting short rods, and each supporting long rod is provided with the piezoelectric actuator and the piezoelectric sensor; the acceleration sensor, the piezoelectric sensor and the piezoelectric actuator are all electrically connected with an external power supply through the controller. The invention has reasonable design and can effectively solve the problem of vibration of the flexible solar wing.
Description
Technical Field
The invention belongs to the field of active vibration reduction, and particularly relates to a piezoelectric active vibration reduction device of a flexible solar wing supporting structure.
Background
In recent years, as the space exploration activities of human beings are increased, various spacecrafts are widely applied, and higher requirements are put forward on solar wings. Because the traditional rigid solar wing has great limitation, in order to meet the requirement of space tasks, the flexible solar wing with the advantages of small furling envelope, light weight, high specific power and the like is a necessary development trend.
Space vehicles that are space-mission often induce vibrations because of their own reduced stiffness due to their large, light-damped structure. In the late middle of the 19 th century, the 12 space vehicles launched in the united states occurred 88 times because of vibration problems; the 'Hubo' space telescope transmitted in 1990 is maintained for many times due to the vibration of the solar wing; the united states "terrestrial satellite No. 4" also works abnormally due to solar wing vibration; the "seeker No. 1" even rolls over due to vibration, causing the task to fail.
Compared with a rigid spacecraft main body, the flexible solar wing has the characteristics of large span, low structural rigidity, large deflection, small modal damping and the like, and can generate the problem of difficult self-damping vibration when the spacecraft is subjected to orbital transfer and attitude adjustment and the mechanical motion of internal parts, thereby influencing the normal work of the whole spacecraft and even causing the structural damage of the spacecraft. Therefore, it is necessary to study the vibration control of the flexible solar wing.
Disclosure of Invention
In view of the above-mentioned drawbacks of the prior art flexible solar wings, the present invention provides a piezoelectric active vibration damping device for a flexible solar wing support structure, which effectively solves the problem of vibration of the flexible solar wing.
The purpose of the invention is realized by the following technical scheme:
the invention comprises a flexible solar wing support structure and a control module for damping vibration of the flexible solar wing support structure, wherein
The flexible solar wing supporting structure comprises a solar wing base station and a flexible solar wing supporting structure body, wherein the flexible solar wing supporting structure body comprises a plurality of supporting short rods and two flexible and crimpable supporting long rods, the two supporting long rods are respectively arranged on the solar wing base station, and the two supporting long rods are connected through the plurality of supporting short rods;
the control module comprises a controller, acceleration sensors, piezoelectric sensors and piezoelectric actuators, the controller is arranged on the solar wing base station, the acceleration sensors are mounted on the supporting short rods, and each supporting long rod is provided with the piezoelectric actuator and the piezoelectric sensor; the piezoelectric sensor is arranged on the rod section of the long supporting rod close to the solar wing base station, and the piezoelectric actuator is arranged on the rod section of the long supporting rod close to the solar wing base station and positioned between the piezoelectric sensor and the solar wing base station; the acceleration sensor, the piezoelectric sensor and the piezoelectric actuator are all electrically connected with an external power supply through the controller.
Wherein: the solar wing base station is a connecting part of the satellite body and the solar wing and is used as a fixing foundation of the flexible solar wing supporting structure body.
Two ends of each supporting short rod are fixedly connected with the two supporting long rods respectively, and the two supporting long rods and the supporting short rods form a ladder shape.
The long supporting rod is a carbon fiber bistable rod, and the space occupied by the vibration damper is reduced by the long supporting rod in a curled state.
The supporting short rod is a steel rod for enhancing the structural stability.
The acceleration sensor is arranged in the middle of one supporting short rod farthest from the solar wing base station.
The piezoelectric sensor adopts a PVDF piezoelectric film.
The piezoelectric actuator adopts PZT piezoelectric ceramic pieces.
The controller adopts stm 32-ARM processor.
The controller is fixed on the solar wing base station through bolts.
The invention has the advantages and positive effects that:
1. the invention has reasonable design and can effectively solve the problem of vibration of the flexible solar wing.
2. The long supporting rod is a carbon fiber bistable rod, and the curling state of the long supporting rod is favorable for reducing the space occupied by the vibration damper during launching.
3. The supporting short rod is a steel rod, and is beneficial to enhancing the structural stability of the vibration damper.
Drawings
FIG. 1 is a schematic view of the overall structure of the present invention;
wherein: the solar wing base station is 1, the piezoelectric actuator is 2, the piezoelectric sensor is 3, the long supporting rod is 4, the short supporting rod is 5, the acceleration sensor is 6 and the controller is 7.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings.
As shown in fig. 1, the present invention includes a flexible solar wing support structure and a control module for effectively damping vibration of the flexible solar wing support structure;
the flexible solar wing supporting structure comprises a solar wing base station 1 and a flexible solar wing supporting structure body, wherein the solar wing base station 1 is a connecting part of the satellite body and the solar wing and is used as a fixing base of the flexible solar wing supporting structure body. The flexible solar wing supporting structure body comprises a plurality of supporting short rods 5 and two flexible and rollable supporting long rods 4, the two supporting long rods 4 are respectively arranged on the solar wing base platform 1, and the two supporting long rods 4 are connected through the plurality of supporting short rods 5. Two long supporting rods 4 of the embodiment are fixedly connected with the solar wing base station 1 in a clamping manner; two ends of each short supporting rod 5 are fixedly connected with the two long supporting rods 4 through bolts respectively; two long support rods 4 and a plurality of (five in the embodiment) short support rods 5 form a ladder shape. The long supporting rod 4 is made of flexible and crimpable materials, the long supporting rod 4 of the embodiment is a carbon fiber bistable rod, and the space occupied by the vibration damper is reduced by the long supporting rod 4 in a crimping state. The supporting short rod 5 is made of rigid material, and the supporting short rod 5 of the embodiment is made of steel rod, which is beneficial to enhancing the structural stability.
The control module comprises a controller 7, an acceleration sensor 6, a piezoelectric sensor 3 and a piezoelectric actuator 2, wherein the controller 7 is arranged on the solar wing base platform 1, and the controller 7 of the embodiment is embedded and fixed on the solar wing base platform 1 by adopting bolt connection. The acceleration sensor 6 is attached to the support short bar 5, and the acceleration sensor 6 of the present embodiment is attached to the middle position of the one support short bar 5 farthest from the solar wing base 1. Every supporting pole 4 is last all to install piezoelectric actuator 2 and piezoelectric sensor 3, and piezoelectric sensor 3 installs in the pole section that supporting pole 4 is close to sun wing base station 1, and piezoelectric actuator 2 also installs in the pole section that supporting pole 4 is close to sun wing base station 1, and is located between piezoelectric sensor 3 and the sun wing base station 1. The two piezoelectric actuators 2 of the embodiment are respectively fixedly arranged at the root parts of the two long supporting rods 4 by adopting an adhesive way; the two piezoelectric sensors 3 are respectively fixed at the root parts of the two long supporting rods in an adhesive way, wherein the piezoelectric actuator 2 is closer to the root part of the long supporting rod 4 than the piezoelectric sensors 3 (namely, one end of the long supporting rod 4 close to the solar wing base station 1); the acceleration sensor 6 is fixedly mounted at the middle position of the uppermost supporting short rod 5 by gluing. Acceleration sensor 6, piezoelectric sensor 3 and piezoelectric actuator 2 all pass through controller 7 and external power electric connection, and the piezoelectric sensor 3 of this embodiment adopts PVDF piezoelectric film, and piezoelectric actuator 2 adopts PZT piezoceramics piece, and controller 7 adopts stm 32-ARM treater.
The piezoelectric actuator 2 of the invention is a commercial product, and is purchased from PZT piezoelectric ceramic sheets of Suzhou maike Rong Automation company Limited; the piezoelectric sensor 3 is a commercially available product, which is purchased from SDT1-028k of taike electronics corporation; the acceleration sensor 6 is a commercially available acceleration sensor available from denmark bika (B & K).
The working principle of the invention is as follows:
the controller comprises a charge amplification module, a main control module and a piezoelectric driving power supply module. When the flexible solar wing supporting structure body formed by the long supporting rods 4 and the short supporting rods 5 is interfered by the outside to generate vibration, the root parts of the long supporting rods 4 can generate deformation at the vibration moment, so that the piezoelectric sensors 3 glued at the root parts of the long supporting rods 4 generate transverse bending deformation, thereby causing the charge in the piezoelectric sensors 3 to flow, a charge amplifier of the controller 7 filters and amplifies the charge signals into voltage signals representing the vibration of the root parts of the long supporting rods 4, the acceleration sensor 6 also detects the voltage signals representing the vibration of the tail ends of the flexible solar wing supporting structure body at the vibration moment, a main control module of the controller 7 converts the two signals into digital signals, then converts the obtained output signals into analog signals, and outputs control signals to the piezoelectric actuators 2 through a piezoelectric driving module of the controller 7, in response, the piezoelectric actuator 2 applies a counter-vibration to the support rods, thereby canceling the vibration of the flexible solar wing support structure body.
Claims (10)
1. A piezoelectric active vibration damper of a flexible solar wing supporting structure is characterized in that: comprising a flexible solar wing support structure and a control module for damping vibrations of the flexible solar wing support structure, wherein
The flexible solar wing supporting structure comprises a solar wing base station (1) and a flexible solar wing supporting structure body, wherein the flexible solar wing supporting structure body comprises a plurality of supporting short rods (5) and two flexible and crimpable supporting long rods (4), the two supporting long rods (4) are respectively installed on the solar wing base station (1), and the two supporting long rods (4) are connected through the plurality of supporting short rods (5);
the control module comprises a controller (7), an acceleration sensor (6), piezoelectric sensors (3) and piezoelectric actuators (2), the controller (7) is arranged on the solar wing base station (1), the acceleration sensor (6) is arranged on a supporting short rod (5), and each supporting long rod (4) is provided with the piezoelectric actuator (2) and the piezoelectric sensor (3); the piezoelectric sensor (3) is arranged on a rod section of the long supporting rod (4) close to the solar wing base station (1), and the piezoelectric actuator (2) is arranged on a rod section of the long supporting rod (4) close to the solar wing base station (1) and is positioned between the piezoelectric sensor (3) and the solar wing base station (1); the acceleration sensor (6), the piezoelectric sensor (3) and the piezoelectric actuator (2) are electrically connected with an external power supply through the controller (7).
2. A piezoelectric active damping device for a flexible solar wing support structure according to claim 1, wherein: the solar wing base station (1) is a connecting part of the satellite body and the solar wing and is used as a fixing foundation of the flexible solar wing supporting structure body.
3. A piezoelectric active damping device for a flexible solar wing support structure according to claim 1, wherein: two ends of each supporting short rod (5) are fixedly connected with the two supporting long rods (4) respectively, and a ladder shape is formed between the two supporting long rods (4) and the supporting short rods (5).
4. A piezoelectric active damping device for a flexible solar wing support structure according to claim 1, wherein: the long supporting rod (4) is a carbon fiber bistable rod, and the space occupied by the vibration damper is reduced through the long supporting rod (4) in a curling state.
5. A piezoelectric active damping device for a flexible solar wing support structure according to claim 1, wherein: the supporting short rod (5) is a steel rod for enhancing the structural stability.
6. A piezoelectric active damping device for a flexible solar wing support structure according to claim 1, wherein: the acceleration sensor (6) is arranged in the middle of one supporting short rod (5) which is farthest away from the solar wing base station (1).
7. A piezoelectric active damping device for a flexible solar wing support structure according to claim 1, wherein: the piezoelectric sensor (3) adopts a PVDF piezoelectric film.
8. A piezoelectric active damping device for a flexible solar wing support structure according to claim 1, wherein: the piezoelectric actuator (2) adopts PZT piezoelectric ceramic pieces.
9. A piezoelectric active damping device for a flexible solar wing support structure according to claim 1, wherein: the controller (7) adopts stm 32-ARM processor.
10. A piezoelectric active damping device for a flexible solar wing support structure according to claim 1, wherein: the controller (7) is fixed on the solar wing base platform (1) through bolts.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911383488.XA CN111059206A (en) | 2019-12-28 | 2019-12-28 | Piezoelectric active vibration damper of flexible solar wing supporting structure |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201911383488.XA CN111059206A (en) | 2019-12-28 | 2019-12-28 | Piezoelectric active vibration damper of flexible solar wing supporting structure |
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| CN111059206A true CN111059206A (en) | 2020-04-24 |
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| CN201911383488.XA Pending CN111059206A (en) | 2019-12-28 | 2019-12-28 | Piezoelectric active vibration damper of flexible solar wing supporting structure |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112444365A (en) * | 2020-11-30 | 2021-03-05 | 哈尔滨工业大学 | Satellite solar wing substrate unfolding low-frequency modal testing method based on force hammer swing method and laser Doppler method |
| CN113428386A (en) * | 2021-06-30 | 2021-09-24 | 北京空间飞行器总体设计部 | On-orbit overlong truss structure deformation control device |
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| US20020096603A1 (en) * | 2001-01-24 | 2002-07-25 | Eurocopter Deutschland Gmbh | Supporting structure for a solar sail of a satellite |
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| CN108709631A (en) * | 2018-07-12 | 2018-10-26 | 华南理工大学 | Flexible truss vibration detection device and method |
| CN109720605A (en) * | 2019-02-27 | 2019-05-07 | 南京航空航天大学 | A kind of planetary probe device |
| CN109795721A (en) * | 2018-12-11 | 2019-05-24 | 上海航天控制技术研究所 | A kind of passive racemization device and racemization method of the spacecraft that fails |
| CN211398408U (en) * | 2019-12-28 | 2020-09-01 | 中国科学院沈阳自动化研究所 | Piezoelectric active vibration damper of flexible solar wing supporting structure |
-
2019
- 2019-12-28 CN CN201911383488.XA patent/CN111059206A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5631421A (en) * | 1994-11-10 | 1997-05-20 | Temic Telefunken Microelectronic Gmbh | Piezoelectric acceleration transducer |
| US20020096603A1 (en) * | 2001-01-24 | 2002-07-25 | Eurocopter Deutschland Gmbh | Supporting structure for a solar sail of a satellite |
| CN106896851A (en) * | 2017-03-27 | 2017-06-27 | 华南理工大学 | It is a kind of to rotate and the mobile double-flexibility beam control device and method for directly driving |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112444365A (en) * | 2020-11-30 | 2021-03-05 | 哈尔滨工业大学 | Satellite solar wing substrate unfolding low-frequency modal testing method based on force hammer swing method and laser Doppler method |
| CN112444365B (en) * | 2020-11-30 | 2023-08-29 | 哈尔滨工业大学 | Satellite solar wing substrate unfolding low-frequency mode testing method |
| CN113428386A (en) * | 2021-06-30 | 2021-09-24 | 北京空间飞行器总体设计部 | On-orbit overlong truss structure deformation control device |
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