CN203516585U - Large-area compound damping vibration attenuation structure applicable to spacecraft - Google Patents
Large-area compound damping vibration attenuation structure applicable to spacecraft Download PDFInfo
- Publication number
- CN203516585U CN203516585U CN201320554340.XU CN201320554340U CN203516585U CN 203516585 U CN203516585 U CN 203516585U CN 201320554340 U CN201320554340 U CN 201320554340U CN 203516585 U CN203516585 U CN 203516585U
- Authority
- CN
- China
- Prior art keywords
- plate
- mounting plate
- damping
- spacecraft
- damping layer
- 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.)
- Expired - Lifetime
Links
Images
Landscapes
- Vibration Prevention Devices (AREA)
Abstract
一种适用于空间飞行器的大面积复合阻尼减振结构，包括：安装板、约束板、阻尼层、导电胶、螺栓、螺母、待减振设备安装法兰；阻尼层夹在安装板和约束板之间且阻尼层与安装板和约束板粘接为一个整体结构，该整体结构上打有多个灌胶通孔和沉孔，所述灌胶通孔内填充导电胶，螺栓穿过所述沉孔，与螺母相配合将待减振设备安装法兰和安装板固定在一起。本实用新型结构显著增加了整个结构的阻尼效应，使得空间飞行器大面积薄板结构在谐振频率范围内的振动响应峰值降低60%左右，进而有效改善了安装于薄板结构上的单机设备的振动环境。
A large-area composite damping and vibration reduction structure suitable for space vehicles, including: a mounting plate, a restraint plate, a damping layer, conductive glue, bolts, nuts, and a mounting flange for a device to be damped; the damping layer is sandwiched between the mounting plate and the restraining plate The damping layer is bonded with the mounting plate and the restraining plate to form an integral structure. A plurality of glue-filling through holes and counterbores are punched on the integral structure. The glue-filling through-holes are filled with conductive glue, and the bolts pass through the The counterbore is matched with the nut to fix the mounting flange of the equipment to be damped and the mounting plate together. The structure of the utility model significantly increases the damping effect of the entire structure, so that the peak value of the vibration response of the large-area thin-plate structure of the space vehicle within the resonance frequency range is reduced by about 60%, thereby effectively improving the vibration environment of the stand-alone equipment installed on the thin-plate structure.
Description
Technical field
The utility model relates to a kind of large size compostie damp vibration damping structure that is applicable to spacecraft, belongs to spacecraft structural vibration reduction technical field.
Background technique
In the main structure design of spacecraft, conventionally comprise large-area thin plate structure, and instrument and equipment is arranged on thin-slab structure, and aircraft is in transmitting powered phase and autonomous flight process, all bear the dynamics environment load of Various Complex, aerodynamic noise, engine ignition and shutdown etc. that the thrust that mainly comprises motor causes when pulsing, transonic speed flying, above-mentioned reason has caused the comparatively harsh vibration environment of instrument and equipment.In order to improve the vibration environment of product facility, traditional design mainly comprises by ABAP Adapter to be carried out integral vibration damping or stand-alone device is carried out to the basic modes such as local vibration damping rocket useful load.Wherein, integral vibration damping design is mainly that the adapter structure of the aircraft such as satellite is taked to damping vibration attenuation measure, has the problems such as size is large, complex process, and is not suitable for the situation of docking without ABAP Adapter between aircraft and vehicle; And local vibration damping to stand-alone device mounting dampers exists equally because mounting dampers affects Product Precision and product heat dissipation problem.
Model utility content
Technology of the present utility model is dealt with problems and is: overcome the deficiencies in the prior art, solve the integral vibration damping problem of spacecraft large-area thin plate structure, and the equipotential requirement based on spacecraft, design the equipotential structural type of composite damping board, solved the installation precision problem due to the sensitive equipment that uses damping material to cause simultaneously.
Technical solution of the present utility model is:
A large size compostie damp vibration damping structure that is applicable to spacecraft, is characterized in that comprising: mounting plate, restraining plate, damping layer, conducting resinl, bolt, nut, treat dampening apparatus mounting flange;
Damping layer is clipped between mounting plate and restraining plate and damping layer and mounting plate and the bonding as a whole structure of restraining plate, in this overall structure, be equipped with a plurality of encapsulating through holes and counterbore, filled conductive glue in described encapsulating through hole, bolt, through described counterbore, matches with nut and will treat that dampening apparatus mounting flange and mounting plate are fixed together.
Described damping layer adopts viscoelastic material.Described viscoelastic material is ZN-1 butyl rubber.
The utility model beneficial effect is compared with prior art:
(1) the utility model structure has significantly increased the damping effect of total, make the vibrating response peak value of spacecraft large-area thin plate structure in resonant frequency range reduce by 60% left and right, and then effectively improved the vibration environment that is installed on the stand-alone device on thin-slab structure.
(2) the utility model structural design the equipotential structural type of composite damping board, overcome and because nonmetallic material are non-conductive, caused spacecraft structure may have the problem of isolated conductor, countersunk head by composite damping board mounting hole designs simultaneously, has guaranteed that sensitive equipment is in the structural installation precision of composite damping board.
Accompanying drawing explanation
Fig. 1 is the utility model structural representation.
Embodiment
The utility model is for the vibration damping requirement of spacecraft large-area thin plate structure, composite damping board vibration damping structure has been proposed, broken through traditional vibration damping mode, effectively reduced the vibratory response of aircraft key structure, for aircraft environment, improved and proposed brand-new mentality of designing; Meanwhile, the equipotential requirement based on spacecraft, the utility model innovative design the equipotential structural type of compostie damp layer, and solved the installation precision problem of sensitive equipment at compostie damp layer.
For reducing the vibrating response peak value of the large-area thin plate structure in spacecraft, general design idea of the present utility model is on thin-slab structure, to paste damp film and restraining plate, constraint due to restraining plate, while making structural vibration, damping layer bears larger shear deformation and a part of tension and compression deformation, thereby under synthetic alternating stress effect, the destruction of the molecular chain by visco-elastic damping material long-chain molecule and loss vibrational energy, and then effectively reduce thin-slab structure vibratory response.The method reliability is high, strong robustness; In the situation that there is no rigidity and the quality of remarkable change system, effectively reduce the amplitude of vibratory response resonance peak.
Under space plasma environment, spacecraft structure should be taked equipotential design.The utility model is between mounting plate and restraining plate, to take to seal the mode of conducting resinl, makes restraining plate and mounting plate and whole Flight Vehicle Structure meet equipotential requirement.In addition, this method designs simultaneously processes larger-diameter through hole on restraining plate and damp film, and fastening piece countersunk head is installed, and is directly pressed on mounting plate, has guaranteed the installation precision of sensitive equipment at composite damping board.
As shown in Figure 1, the utility model provides a kind of large size compostie damp vibration damping structure that is applicable to spacecraft, comprising: mounting plate 1, restraining plate 2, damping layer 3, conducting resinl 4, bolt 5, nut 6, treat dampening apparatus mounting flange 7; Mounting plate 1, restraining plate 2 and damping layer 3 are thin-slab structure.
Take certain type spacecraft is example, has verified the effectiveness in vibration suppression of this kind of method by ground experiment.Test result shows, is not taking under the condition of the utility model structure, and on mounting plate, the power spectral density maximum value of crucial measuring point in the frequency range of 150Hz-300Hz is 1.3g
2/ Hz; After taking compostie damp oscillation damping method, the power spectral density of mounting plate measuring point is also reduced to 0.4g
2/ Hz.As can be seen here, the utility model structure has significantly been improved the vibratory response of spacecraft key position in low-frequency range, for Flight Vehicle Structure and product facility provide good Environmental Conditions.
Claims (4)
1. a large size compostie damp vibration damping structure that is applicable to spacecraft, is characterized in that comprising:
Mounting plate (1), restraining plate (2), damping layer (3), conducting resinl (4), bolt (5), nut (6), treat dampening apparatus mounting flange (7);
Damping layer (3) is clipped between mounting plate (1) and restraining plate (2) and damping layer (3) and mounting plate (1) and the bonding as a whole structure of restraining plate (2), in this overall structure, be equipped with a plurality of encapsulating through holes (8) and counterbore (9), the interior filled conductive glue of described encapsulating through hole (8) (4), bolt (5), through described counterbore (9), matches with nut (6) and will treat that dampening apparatus mounting flange (7) and mounting plate (1) are fixed together.
2. a kind of large size compostie damp vibration damping structure that is applicable to spacecraft according to claim 1, is characterized in that: described damping layer (3) adopts viscoelastic material.
3. a kind of large size compostie damp vibration damping structure that is applicable to spacecraft according to claim 1 and 2, is characterized in that: described mounting plate (1), restraining plate (2) and damping layer (3) are thin-slab structure.
4. a kind of large size compostie damp vibration damping structure that is applicable to spacecraft according to claim 2, is characterized in that: described viscoelastic material is ZN-1 butyl rubber.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320554340.XU CN203516585U (en) | 2013-09-06 | 2013-09-06 | Large-area compound damping vibration attenuation structure applicable to spacecraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320554340.XU CN203516585U (en) | 2013-09-06 | 2013-09-06 | Large-area compound damping vibration attenuation structure applicable to spacecraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203516585U true CN203516585U (en) | 2014-04-02 |
Family
ID=50375518
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320554340.XU Expired - Lifetime CN203516585U (en) | 2013-09-06 | 2013-09-06 | Large-area compound damping vibration attenuation structure applicable to spacecraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203516585U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104455196A (en) * | 2014-09-30 | 2015-03-25 | 西安空间无线电技术研究所 | Rigidity-adjustable device with characteristics of heat conduction, electric conduction and high damping |
| CN104565716A (en) * | 2014-12-25 | 2015-04-29 | 贵州黔程天力智能科技有限公司 | Receiver vibration attenuation supporting seat |
| CN104595636A (en) * | 2014-12-25 | 2015-05-06 | 贵州黔程天力智能科技有限公司 | Receiver damping supporting base |
| CN105864341A (en) * | 2016-05-23 | 2016-08-17 | 航天材料及工艺研究所 | High-reliability combined type shock absorber |
| CN108626290A (en) * | 2018-05-04 | 2018-10-09 | 南京大学 | A kind of enhancing damping-constraining device |
-
2013
- 2013-09-06 CN CN201320554340.XU patent/CN203516585U/en not_active Expired - Lifetime
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104455196A (en) * | 2014-09-30 | 2015-03-25 | 西安空间无线电技术研究所 | Rigidity-adjustable device with characteristics of heat conduction, electric conduction and high damping |
| CN104455196B (en) * | 2014-09-30 | 2016-06-01 | 西安空间无线电技术研究所 | A kind of rigidity tunable arrangement with heat conduction, conduction, high damping characteristic |
| CN104565716A (en) * | 2014-12-25 | 2015-04-29 | 贵州黔程天力智能科技有限公司 | Receiver vibration attenuation supporting seat |
| CN104595636A (en) * | 2014-12-25 | 2015-05-06 | 贵州黔程天力智能科技有限公司 | Receiver damping supporting base |
| CN105864341A (en) * | 2016-05-23 | 2016-08-17 | 航天材料及工艺研究所 | High-reliability combined type shock absorber |
| CN108626290A (en) * | 2018-05-04 | 2018-10-09 | 南京大学 | A kind of enhancing damping-constraining device |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN203516585U (en) | Large-area compound damping vibration attenuation structure applicable to spacecraft | |
| Sargianis et al. | Core material effect on wave number and vibrational damping characteristics in carbon fiber sandwich composites | |
| CN203464858U (en) | Combined explosive bolt box structure capable of releasing pressure in sliding manner | |
| US9016628B2 (en) | Methods and apparatus for reducing noise in reinforced skin structures | |
| CN104457966B (en) | A kind of piezoelectric type decouples microvibration measuring system | |
| Karpenko et al. | Vibration damping characteristics of the cork-based composite material in line to frequency analysis | |
| Ricciardi et al. | Numerical noise prediction and source identification of a realistic landing gear | |
| Kuriakose et al. | Experimental investigation on the enhancement of vibration and flutter characteristics of damaged composite plates using piezoelectric patches | |
| CN103545594B (en) | A kind of hypersonic aircraft telemetry antenna window erecting device | |
| Hao et al. | Dynamic analysis of the spacecraft structure on orbit made up of honeycomb sandwich plates | |
| CN105221623A (en) | A kind of propeller driven airplane noise reduction multiple resonance points dynamic vibration absorber | |
| CN114001115B (en) | Gradient vibration reduction structure and vibration reduction method based on mechanical-electrical conversion | |
| Chen et al. | Analysis of flutter and nonlinear dynamics of a composite laminated plate | |
| CN203561497U (en) | Cylinder Liner Fatigue Test System Based on High Frequency Fatigue Testing Machine | |
| CN203254894U (en) | Automotive rear axle energy absorber and automobile | |
| Belyaev et al. | Effect of chevrons on the slat noise of straight and swept wings | |
| Magliacano et al. | Active vibration control by piezoceramic actuators of a car floor panel | |
| CN102733953B (en) | Sound arrester applied to engine pedestal | |
| Jayasundara et al. | Aeroacoustic and Aerodynamic Investigation of a Wingtip-Mounted Tractor Propeller | |
| CN115901170A (en) | Vibration inertia actuation suppression device for wind tunnel model | |
| US9033301B1 (en) | Vibration reduction system using an extended washer | |
| Zhu et al. | Numerical simulation and experiment of the piezoelectric de-icing system | |
| Reksoprodjo et al. | Characteristics of vibration propagation on passenger car monocoque body structure at static small turbocharged diesel engine speed variation | |
| CN109131854A (en) | Low noise unmanned plane and its method for noise reduction control | |
| Long et al. | 740. Aeroacoustic testing of the landing gear components |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20140402 |