CN211398408U - 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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- CN211398408U CN211398408U CN201922428025.2U CN201922428025U CN211398408U CN 211398408 U CN211398408 U CN 211398408U CN 201922428025 U CN201922428025 U CN 201922428025U CN 211398408 U CN211398408 U CN 211398408U
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Abstract
The utility model relates to a piezoelectric active vibration damper 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 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 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 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 utility model relates to a rationally, can effectively solve flexible solar wing vibration problem.
Description
Technical Field
The utility model belongs to initiative damping field, specifically speaking are flexible solar wing supporting structure's piezoelectricity initiative damping device.
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.
SUMMERY OF THE UTILITY MODEL
In view of the above-mentioned defects of the existing flexible solar wing technology, an object of the present invention is to provide a piezoelectric active vibration damping device of a flexible solar wing supporting structure, which effectively solves the problem of vibration of the flexible solar wing.
The purpose of the utility model is realized through the following technical scheme:
the utility model discloses a flexible solar wing bearing structure and be used for restraining this flexible solar wing bearing structure vibration's control module, 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 utility model discloses an advantage does with positive effect:
1. the utility model relates to a rationally, can effectively solve flexible solar wing vibration problem.
2. The utility model discloses a supporting stock is carbon fiber bistable pole, and its crimping state is favorable to reducing the shared space of vibration damper when the transmission.
3. The utility model discloses a supporting quarter butt is the steel pole, is favorable to strengthening vibration damper's structural stability.
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 detail with reference to the accompanying drawings.
As shown in fig. 1, the present invention comprises a flexible solar wing support structure and a control module, wherein the control module is used for effectively suppressing the 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 utility model is a commercial product, and is purchased from PZT piezoelectric ceramic plate 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 utility model discloses a theory of operation does:
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.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201922428025.2U CN211398408U (en) | 2019-12-28 | 2019-12-28 | Piezoelectric active vibration damper of flexible solar wing supporting structure |
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| CN201922428025.2U CN211398408U (en) | 2019-12-28 | 2019-12-28 | Piezoelectric active vibration damper of flexible solar wing supporting structure |
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| CN211398408U true CN211398408U (en) | 2020-09-01 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111059206A (en) * | 2019-12-28 | 2020-04-24 | 中国科学院沈阳自动化研究所 | Piezoelectric active vibration damper of flexible solar wing supporting structure |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111059206A (en) * | 2019-12-28 | 2020-04-24 | 中国科学院沈阳自动化研究所 | Piezoelectric active vibration damper of flexible solar wing supporting structure |
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