JPS6394830A - Vibration-damping panel - Google Patents
Vibration-damping panelInfo
- Publication number
- JPS6394830A JPS6394830A JP24045486A JP24045486A JPS6394830A JP S6394830 A JPS6394830 A JP S6394830A JP 24045486 A JP24045486 A JP 24045486A JP 24045486 A JP24045486 A JP 24045486A JP S6394830 A JPS6394830 A JP S6394830A
- Authority
- JP
- Japan
- Prior art keywords
- vibration damping
- viscoelastic
- core
- panel
- vibration
- 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.)
- Pending
Links
- 238000013016 damping Methods 0.000 title claims description 40
- 239000000463 material Substances 0.000 claims description 30
- 239000000853 adhesive Substances 0.000 claims description 7
- 230000001070 adhesive effect Effects 0.000 claims description 7
- 239000011888 foil Substances 0.000 claims description 7
- 230000000694 effects Effects 0.000 description 12
- 238000005452 bending Methods 0.000 description 7
- 210000003491 skin Anatomy 0.000 description 7
- 210000002615 epidermis Anatomy 0.000 description 3
- 230000000452 restraining effect Effects 0.000 description 3
- 230000002411 adverse Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 238000010008 shearing Methods 0.000 description 1
- 230000002195 synergetic effect Effects 0.000 description 1
Abstract
(57)【要約】本公報は電子出願前の出願データであるた
め要約のデータは記録されません。(57) [Abstract] This bulletin contains application data before electronic filing, so abstract data is not recorded.
Description
【発明の詳細な説明】
〔産業上の利用分野〕
この発明は１人工衛星または宇宙構造物の構造材として
用いられるハニカムパネルの振動減衰特性の向上に関す
るものである。DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] This invention relates to improving the vibration damping characteristics of a honeycomb panel used as a structural material for an artificial satellite or a space structure.
第３図ｔｉ例えば刊行物（Ｓｏｕｎｄ ａｎｃｌ Ｖｉ
ｂｒａｔｉｏｎ。Figure 3ti For example, publications (Sound ancl Vi
bratio.
Ｊｕｌｙ １９８３． Ｐ ２Ｂ −３６） に示
された従来の振動減衰パネルを示す断面図であり１図に
おいて。July 1983. FIG. 1 is a cross-sectional view of the conventional vibration damping panel shown in FIG.
（ｔｌ Ｂ ／、二カムパネル、（２）はこのハニカム
パネル（１）に接着された粘弾性振動減衰材、（３）は
この粘弾性振動減衰材（２）に接着された拘束材、（４
）は相対向して設けられた表皮、（５）はこの表皮（４
）をその両端面に接着したコア、（６）はこのコア（５
）に上記表皮（４）を固定している接着剤であり、上記
ハニカムパネル（１）は、上記表皮（４）、上記コア（
５）、および、上記接着剤（６）により構成されている
。(tl B /, bicam panel, (2) is a viscoelastic vibration damping material bonded to this honeycomb panel (1), (3) is a restraining material bonded to this viscoelastic vibration damping material (2), (4
) is the epidermis provided facing each other, (5) is this epidermis (4
) is glued to both end faces of the core, (6) is this core (5
), and the honeycomb panel (1) is an adhesive that fixes the skin (4) to the core (
5) and the adhesive (6).
次に動作について説明する。人工衛星などの強度部材お
よび剛性部材として使用され、ミッション機器が取付け
られるハニカムパネル（１）は、打上げ時あるいはエン
ジン動作時などに、振動荷重を受は面外の曲げ振動が発
生する。このとき、粘弾性振動減衰材（２）はノ・ニカ
ムパネル（４１と比べ、縦方向とせん断方向の剛性が小
さく、拘束材（３）は粘弾性振動減衰材（２）と比べ縦
方向剛性が大きいので。Next, the operation will be explained. Honeycomb panels (1) used as strength and rigidity members of artificial satellites and the like, to which mission equipment is attached, are subjected to vibration loads during launch or engine operation, resulting in out-of-plane bending vibrations. At this time, the viscoelastic vibration damping material (2) has lower rigidity in the longitudinal direction and the shear direction than the non-nicum panel (41), and the restraining material (3) has lower rigidity in the longitudinal direction than the viscoelastic vibration damping material (2). Because it's big.
粘弾性振動減衰材（２）にはせん断変形が生じる。粘弾
性振動減衰材（２）はせん断変形に対し粘弾性を有する
材料、すなわち、横弾性係数が複素数で、この横弾性係
数の虚数成分が比較的大きな性質を有する材料が使用さ
れるので、上記曲げ振動によシ粘弾性振動減衰材（２）
がぜん断変形を受けた場合。Shear deformation occurs in the viscoelastic vibration damping material (2). The viscoelastic vibration damping material (2) is a material that has viscoelasticity against shear deformation, that is, a material that has a complex transverse elastic modulus and a relatively large imaginary component of this transverse elastic modulus. Viscoelastic vibration damping material for bending vibration (2)
is subjected to shear deformation.
この曲げ撮動を減衰させる効果がある。This has the effect of attenuating this bending motion.
従来の振動減衰パネルは上記のように構成されているの
で、粘弾性振動減衰材（２）のせん断変形が大きくなる
ように、拘束材（３）の縦方向剛性を確保する必要があ
シ２例えば、拘束材と表皮に同じ材料を用いた場合、拘
束材は表皮に比べ厚くなければならず１重量が増加する
こと、拘束材（３）の上部にミッション機器を取付けた
場合、その部分で粘弾性振動減衰材（２）のせん断変形
が生じに〈〈なシ減衰効果が低下すること、また、同様
にミッション機器を取付けた場合、ミッション機器内部
で発生する熱がハニカムパネルｆｉｌに伝達しに〈〈、
ミッション機器の温度が上昇すること、などの問題点が
あった。Since the conventional vibration damping panel is constructed as described above, it is necessary to ensure the longitudinal rigidity of the restraint material (3) so that the shear deformation of the viscoelastic vibration damping material (2) becomes large. For example, if the same material is used for the restraint material and the skin, the restraint material must be thicker than the skin, which increases the weight by 1. If the mission equipment is attached to the top of the restraint material (3), that part Shearing deformation of the viscoelastic vibration damping material (2) will occur, resulting in a decrease in the damping effect.Also, when mission equipment is installed, the heat generated inside the mission equipment will be transferred to the honeycomb panel. ni〈〈,
There were problems such as the temperature of the mission equipment rising.
この発明は上記のような問題点を解消するためになされ
たもので２重量が小さく、ミッション機器からの熱伝達
量が大きく、振動減衰効果の高い振動減衰パネルを提供
することを目的とする。This invention was made to solve the above-mentioned problems, and it is an object of the present invention to provide a vibration damping panel that is small in weight, transfers a large amount of heat from mission equipment, and has a high vibration damping effect.
この発明に係る振動減衰パネルは、箔と箔との間に粘弾
性振動減衰材を設はコアを構成したものである。The vibration damping panel according to the present invention has a core in which a viscoelastic vibration damping material is provided between foils.
この発明における粘弾性振動減衰材は、ノ・ニカムパネ
ルに曲げ振動が発生した場合にせん断変形を受けるため
、振動エネルギを吸収する。The viscoelastic vibration damping material of the present invention undergoes shear deformation when bending vibration occurs in the no-nicum panel, and thus absorbs vibration energy.
以下にこの発明の実施例を図について説明する。 Embodiments of the invention will be described below with reference to the drawings.
第１図はこの発明の一実施例による振動減衰パネルを示
す断面図であり１図において、（１）はハニカムパネル
、（４）は表皮、（５）はコアであり、上記表皮（４）
と上記コア（５）は上記ハニカムパネルを構成する。FIG. 1 is a sectional view showing a vibration damping panel according to an embodiment of the present invention. In FIG. 1, (1) is a honeycomb panel, (4) is a skin, and (5) is a core.
and the core (5) constitute the honeycomb panel.
また（７）は箔、（２）はこの箔（７）と箔（７）との
間に設けられた粘弾性振動減衰材であり、上記第（））
と上記粘弾性振動減衰材（２）は上記コア（５）を構成
する。Further, (7) is a foil, (2) is a viscoelastic vibration damping material provided between the foils (7), and the above-mentioned item ())
and the viscoelastic vibration damping material (2) constitute the core (5).
次にこの発明の動作について説明する。人工衛星などの
剛性部材および強度部材として使用されるハニカムパネ
ル（１）は、その上にミッション機器が搭載される。こ
のハニカムパネル（１）は人工衛星の打上げ畦、あるい
は、エンジンの動作時などに振動荷重を受け９面外の曲
げ振動を発生し、搭載されたミッション機器等に悪影響
をおよぼすことがある。この実施例では、ハニカムパネ
ル（１）が図示したＸ軸にそった曲げ変形を起こした場
合、箔（７）と箔（７）の間の粘弾性振動減衰材（２）
はせん断変形を受ける。粘弾性振動減衰材（２）は、そ
の横弾性係数が複素数でその虚数成分の比率が大きいの
で。Next, the operation of this invention will be explained. A honeycomb panel (1) used as a rigid member and a strength member of an artificial satellite, etc., has mission equipment mounted thereon. This honeycomb panel (1) is subjected to vibration loads during the launch of an artificial satellite or during engine operation, and may generate bending vibrations outside the nine planes, which may adversely affect on-board mission equipment. In this example, when the honeycomb panel (1) undergoes bending deformation along the illustrated X-axis, the viscoelastic vibration damping material (2) between the foils (7)
undergoes shear deformation. The viscoelastic vibration damping material (2) has a transverse elastic modulus that is a complex number, and the ratio of its imaginary component is large.
動的なせん断ひずみが起こると、このひずみエネルギを
熱エネルギに変換する性質があり、このために振動減衰
効果を発揮中る。したがって、この実施例では、従来の
振動減衰パネルで必要とされた拘束材（３）が不要であ
り、このために軽量のものを得ることができる。また、
ミッション機器等をハニカムパネル（１）に直接取付け
ることができるため、ミッション機器等の熱エネルギを
ハニカムパネルｆｔｌに伝達しやす〈、温度特性の秀れ
たものな得ることができる。When dynamic shear strain occurs, it has the property of converting this strain energy into thermal energy, and therefore exhibits a vibration damping effect. Therefore, in this embodiment, the restraining material (3) required in conventional vibration damping panels is not required, and therefore a lightweight panel can be obtained. Also,
Since the mission equipment, etc. can be directly attached to the honeycomb panel (1), the thermal energy of the mission equipment, etc. can be easily transferred to the honeycomb panel (ftl), and excellent temperature characteristics can be obtained.
第２図はこの発明の他の実施例による振動減衰パネルを
示す断面図であり９図におりて、（１）はハニカムパネ
ル、（４１は表皮、（５）は前述の第１の実施例に示し
たものと同様のコア、ＱＢは上記表皮（４１と上記コア
（５）との間に設けられ１両者を接合してｂる粘弾性接
着剤であり、上記ハニカムパネル（１）は上記表皮（４
１，上記コア（５）、および、上記粘弾性接着剤ＱＩ）
Ｋより構成されている。FIG. 2 is a sectional view showing a vibration damping panel according to another embodiment of the present invention, and in FIG. A core similar to that shown in , QB is a viscoelastic adhesive provided between the skin (41) and the core (5) to bond them together, and the honeycomb panel (1) is Epidermis (4
1, the above core (5), and the above viscoelastic adhesive QI)
It is composed of K.
この実施例では、第１の実施例の場合と同様にハニカム
パネルｆｉｌに曲げ振動が発生した場合、コア（５）を
構成する粘弾性振動減衰材（２）による振動減衰効果に
加え２表皮（４）とコア（５１を接合している粘弾性接
着剤０１）がせん断変形を起こし、この部分で振動エネ
ルギが熱エネルギに変換されることによる振動減衰効果
があり１両者の相乗効果により。In this embodiment, when bending vibration occurs in the honeycomb panel fil as in the case of the first embodiment, in addition to the vibration damping effect by the viscoelastic vibration damping material (2) constituting the core (5), the two skins ( 4) and the core (the viscoelastic adhesive 01 that joins 51) causes shear deformation, and in this part, vibration energy is converted into thermal energy, resulting in a vibration damping effect.1 Due to the synergistic effect of the two.
より高い振動減衰効果を発揮する。Demonstrates higher vibration damping effect.
なお、上記第１および第２の実施例では人工衛星等の構
造部材として用いられるパネルについて説明したが、宇
宙構造物を構成する他の構造材としてのパネルでもよく
、マた。地上用のパネルであってもよく、上記実施例と
同様の効果を奏する。In the first and second embodiments, panels used as structural members of artificial satellites and the like have been described, but the panels may be used as other structural members constituting space structures. A panel for use on the ground may be used, and the same effects as in the above embodiment can be achieved.
以上のように、この発明によれば、箔と箔との間に粘弾
性振動減衰材を設け、コアとすることにより、高す振動
減衰効果が得られる効果がある。As described above, according to the present invention, by providing the viscoelastic vibration damping material between the foils and forming the core, an enhanced vibration damping effect can be obtained.
また、軽量で熱伝達特性の良すものが得られる効果があ
る。Moreover, it has the effect of being lightweight and having good heat transfer characteristics.
第１図はこの発明の一実施例による振動減衰パネルを示
す断面図、第２図はこの発明の他の実施例による振動減
衰パネルを示す断面図、及び第３図は従来の振動減衰パ
ネルを示す断面図である。
（１）・・・ハニカムパネル、（２）・・・粘弾性振動
減衰材。
（４１・・・表皮、（５）・・・コア、（７）・・・箔
、ｅ２υ・・・粘弾性接着剤。
なお１図中、同一符号は同一または相当部分を示す。FIG. 1 is a sectional view showing a vibration damping panel according to an embodiment of the present invention, FIG. 2 is a sectional view showing a vibration damping panel according to another embodiment of the invention, and FIG. 3 is a sectional view showing a conventional vibration damping panel. FIG. (1) Honeycomb panel, (2) Viscoelastic vibration damping material. (41...Skin, (5)...Core, (7)...Foil, e2υ...Viscoelastic adhesive. Note that in Figure 1, the same reference numerals indicate the same or corresponding parts.
Claims (2)
設けられたるコアによりハニカム構造を構成するものに
おいて、上記コアは粘弾性振動減衰材を介して対向する
複数の箔により構成したことを特徴とする振動減衰パネ
ル。(1) In a honeycomb structure constructed of skins arranged facing each other and a core provided between these skins, the core is constructed of a plurality of foils facing each other with a viscoelastic vibration damping material in between. A vibration damping panel characterized by:
徴とする特許請求の範囲第１項記載の振動減衰パネル。(2) The vibration damping panel according to claim 1, wherein the skin and the core are bonded with a viscoelastic adhesive.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP24045486A JPS6394830A (en) | 1986-10-09 | 1986-10-09 | Vibration-damping panel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP24045486A JPS6394830A (en) | 1986-10-09 | 1986-10-09 | Vibration-damping panel |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS6394830A true JPS6394830A (en) | 1988-04-25 |
Family
ID=17059738
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP24045486A Pending JPS6394830A (en) | 1986-10-09 | 1986-10-09 | Vibration-damping panel |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS6394830A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH07164584A (en) * | 1993-02-08 | 1995-06-27 | Kobe Steel Ltd | Vibration-damping section, its manufacture and structural component for carrier |
-
1986
- 1986-10-09 JP JP24045486A patent/JPS6394830A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH07164584A (en) * | 1993-02-08 | 1995-06-27 | Kobe Steel Ltd | Vibration-damping section, its manufacture and structural component for carrier |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US5087491A (en) | Vibration-damping structural member | |
| US3087571A (en) | Apparatus for damping | |
| US8087494B2 (en) | Method of making a composite panel having subsonic transverse wave speed characteristics | |
| US4778028A (en) | Light viscoelastic damping structure | |
| JP3078854B2 (en) | Internal anti-vibration type thin composite longitudinal member | |
| EP2944844B1 (en) | Method and apparatus for reducing structural vibration and noise | |
| Wang et al. | Free in-plane vibration of rectangular plates | |
| JP2009513898A (en) | FORK DAMPER AND METHOD OF USING THE DAMPER | |
| US3327812A (en) | Damping means | |
| US5338599A (en) | Vibration-damping structural component | |
| Lin et al. | Free vibration of bonded plates | |
| Chen et al. | Reducing vibration of sandwich structures using antiresonance frequencies | |
| US3087573A (en) | Damping structure | |
| JP3133333B2 (en) | Improved damping in composite structures by stress coupling | |
| JPS6394830A (en) | Vibration-damping panel | |
| JPS6394831A (en) | Vibration-damping panel | |
| He et al. | Longitudinal vibration and damping analysis of adhesively bonded double-strap joints | |
| JPH11153194A (en) | Damping member integrating elasto-plastic and visco-elastic damper | |
| JPS6394832A (en) | Vibration-damping panel | |
| US20030173467A1 (en) | Satellite deployment structure | |
| Rajagopal et al. | Large-deflection and nonlinear vibration of multilayered sandwich plates | |
| JPS6081511A (en) | Washer | |
| JPH01150038A (en) | Vibration damping panel | |
| JPS6114338A (en) | Vibration attenuator of structure | |
| JPH02214649A (en) | Viscoelastic damping structure and manufacture thereof |