JPS6394832A - Vibration-damping panel - Google Patents
Vibration-damping panelInfo
- Publication number
- JPS6394832A JPS6394832A JP24045386A JP24045386A JPS6394832A JP S6394832 A JPS6394832 A JP S6394832A JP 24045386 A JP24045386 A JP 24045386A JP 24045386 A JP24045386 A JP 24045386A JP S6394832 A JPS6394832 A JP S6394832A
- Authority
- JP
- Japan
- Prior art keywords
- vibration damping
- vibration
- panel
- core
- skin
- 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 35
- 239000000463 material Substances 0.000 claims description 30
- 210000003491 skin Anatomy 0.000 description 11
- 230000000694 effects Effects 0.000 description 9
- 238000005452 bending Methods 0.000 description 6
- 230000000452 restraining effect Effects 0.000 description 3
- 239000000853 adhesive Substances 0.000 description 2
- 230000001070 adhesive effect Effects 0.000 description 2
- 210000002615 epidermis Anatomy 0.000 description 2
- 238000010008 shearing Methods 0.000 description 2
- 238000005516 engineering process Methods 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ｆｃ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２図は例えば刊行物（５ｏｕｎｄ ａｎｄ Ｖｉｂ
−ｒａｔ ｉｏｎ、 Ｊｕｌｙ １９８３ ｒ Ｐ
２８−３６ ） 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、 ｆｌｌｉ！ハニカム
パネル、（２１はこのハニカムパネル（１１に接着され
た振動減衰材−（３１Ｖ：ｊこの振動減衰材（２）に接
着された拘束材、（４）はコア（５）ヲ介して相対向し
て配置された表皮である。コア（５）はこれらの表皮ｆ
４１ ′ｔ−その両端面に接着している。（６）はこの
コア（５）に上記表皮（４１を固定している接着剤であ
り、上記ハニカムパネルｍｕ、上記宍皮（４）。Figure 2 shows, for example, publications (5ound and Vib
-ration, July 1983 r P
28-36) is a sectional view showing the conventional vibration damping panel shown in FIG. A honeycomb panel, (21 is a vibration damping material bonded to this honeycomb panel (11) - (31V:j a restraining material bonded to this vibration damping material (2), (4) is opposed to each other via a core (5) The core (5) is the epidermis f
41't-Glued to both end faces. (6) is an adhesive that fixes the skin (41) to this core (5), the honeycomb panel mu and the shishi skin (4).
上記コア（５）、および、上記接着剤（６）によ＃）ｗ
成されている。By the core (5) and the adhesive (6)
has been completed.
次に動作について説明する。人工衛星などの強度部材、
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、振動減衰材（２）ハニカムパネルｆｉｌ
と比べ、縦方向とせん断方向の剛性が小さく、拘束材（
３）は振動減衰材（２）と比べ縦方向剛性が大きいので
、振動減衰材（２）にはせん断変形が生じる。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８
上記曲げ振動によシ振動減衰材（２）がせん断変形？受
けた場合、この曲げ振動を減衰させる効果がある。Next, the operation will be explained. Strength components such as artificial satellites,
The honeycomb panel (1), which is used as a rigid member and to which mission equipment is attached, receives a vibration load during launch or engine operation, and out-of-plane bending vibration occurs. At this time, vibration damping material (2) honeycomb panel fil
Compared to
Since the material 3) has greater longitudinal rigidity than the vibration damping material (2), shear deformation occurs in the vibration damping material (2). The vibration damping material (2) is a material that has viscoelasticity against shear deformation, that is, a material with a complex transverse elastic modulus and a relatively large imaginary component of this transverse elastic modulus.
Did the vibration damping material (2) undergo shear deformation due to the bending vibration mentioned above? It has the effect of damping this bending vibration when it is received.
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、振動減衰材（２）のせん断変形が大きくなるように
、拘束材（３１の縦方向剛性を確保する必要があり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６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、
その部分で振動減衰材（２）のせん断変形が生じにくく
なシ、減衰効果が低下すること、１だ、同様にミッショ
ン機器全取付けた場合、ミッション機器内部で発生する
熱がハニカムパネルに伝達しにりく、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 (31) so that the shear deformation of the vibration damping material (2) becomes large. If the same material is used for the skin, the restraining material must be thicker than the skin and the weight will increase;
If the mission equipment is attached to the top of the restraint material (3),
Shearing deformation of the vibration damping material (2) is difficult to occur in that area, and the damping effect is reduced.1. Similarly, when all mission equipment is installed, the heat generated inside the mission equipment is transferred to the honeycomb panel. There were problems such as the temperature of the mission equipment increasing.
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０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 has a small zero weight, a large amount of heat transfer from mission equipment, and a high vibration damping effect.
この発明に係る振動減衰パネルは、ハニカムパネルにお
いて、コアと表皮との接合に粘弾性振動減衰材を用いた
ものである。The vibration damping panel according to the present invention is a honeycomb panel in which a viscoelastic vibration damping material is used to join the core and the skin.
この発明における粘弾性振動減衰材はハニカムパネルに
曲げ振動が発生した場合せん断変形を受けるため１この
振動エネルギを吸収する。The viscoelastic vibration damping material in this invention undergoes shear deformation when bending vibration occurs in the honeycomb panel, so it absorbs this vibration energy.
（実施例〕 以下この発明の実施例を図について説明する。(Example〕 Embodiments of the present invention will be described below with reference to the drawings.
第１図において、（１）はハニカムパネル、（４）は表
皮。In Figure 1, (1) is the honeycomb panel, and (4) is the skin.
（５）はコア・ （６１）は粘弾性振動減衰材であシ、
上記表皮（４）と上記コア（５）は上記粘弾性振動減衰
材（６１）に工す接合され上記ハニカムパネル（１）全
構成する。(5) is a core, (61) is a viscoelastic vibration damping material,
The skin (4) and the core (5) are joined to the viscoelastic vibration damping material (61) to form the entire honeycomb panel (1).
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１強度部材として使用され。Next, the operation of this invention will be explained. Used as a rigid member 1 strength member for artificial satellites, etc.
また、ミッション機器が搭載されるノ＼ニカムバネルｆ
ｌｌＶｉ−打上げ時、あるいは、エンジンの動作時など
に振動荷重を受け１面外の曲げ振動が発生する。ハニカ
ムパネル（１）に曲げ変形が発生すると・表皮（４）と
コア（５）の間には表皮（４）の面内方向のせん断力が
生じ、粘弾性振動減衰材（６１）はせん断ひずみを起こ
す。粘弾性振動減衰材（６１）ハその横弾性係数が複素
数であり、虚数成分を有しているから１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として消散さ
せる作用があり１振動減衰効果を発揮する。従ってこの
実施例に係る振動減衰パネルは、従来の構造で必要とさ
れた拘束材（３）が不要のため軽量で高い振動減衰効果
を得るこ七ができ１寸た。ミッション機器はハニカムパ
ネル（１１に直接取付けることができるのでミッション
機器の熱エネルギがハニカムパネル（１）に伝達しやす
く、温度特性の優れた振動減衰パネルを提供できる。In addition, the mission equipment will be mounted on the Nikumbanel f.
llVi - Bending vibration outside one plane occurs due to vibration loads during launch or engine operation. When bending deformation occurs in the honeycomb panel (1), a shearing force is generated between the skin (4) and the core (5) in the in-plane direction of the skin (4), and the viscoelastic vibration damping material (61) undergoes shear strain. wake up The viscoelastic vibration damping material (61) has a complex transverse elastic modulus and an imaginary component, so when dynamic shear strain occurs, it has the effect of dissipating this strain energy as heat, resulting in vibration damping. be effective. Therefore, the vibration damping panel according to this embodiment does not require the restraining material (3) required in the conventional structure, so it is lightweight and has a high vibration damping effect. Since the mission equipment can be directly attached to the honeycomb panel (11), the thermal energy of the mission equipment is easily transmitted to the honeycomb panel (1), and a vibration damping panel with excellent temperature characteristics can be provided.
なお・上記実施例ではミッション機器が取付けられる人
工衛星用の構造材としてのパネルについて説明したが、
宇宙構造物の構成する他の構造材としてのパネルでもよ
く、また、地上で用いられるパネルであってもよく一上
記実施例と同様の効果を奏する。In addition, in the above example, a panel was explained as a structural material for an artificial satellite to which mission equipment is attached.
The present invention may be a panel as another structural material constituting a space structure, or may be a panel used on the ground, 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１表皮とコアで構成さ
れるハニカムパネルにおいて１表皮とコアとの間に粘弾
性振動減衰材を設けるという構造により、高い振動減衰
効果が得られ、また、軽量のものが得られ、熱伝達特性
の良いものが得られるという効果がある。As described above, according to the present invention, a high vibration damping effect can be obtained by providing a viscoelastic vibration damping material between one skin and the core in a honeycomb panel composed of one skin and a core. This has the advantage 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、（４）・・・表皮、 ＋
５１・・・コア。
（６１）・・・粘弾性振動減衰材。
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, and FIG. 2 is a sectional view showing a conventional vibration damping panel. (1)... Honeycomb panel, (4)... Epidermis, +
51...Core. (61)...Viscoelastic vibration damping material. In addition, in FIG. 1, the same reference numerals indicate the same or corresponding parts.
Claims (1)
れたコアによりハニカム構造を構成するものにおいて、
上記表皮と上記コアとの間に粘弾性振動減衰材を設けた
ことを特徴とする振動減衰パネル。In a honeycomb structure constituted by skins arranged facing each other and a core provided between these skins,
A vibration damping panel characterized in that a viscoelastic vibration damping material is provided between the skin and the core.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP24045386A JPS6394832A (en) | 1986-10-09 | 1986-10-09 | Vibration-damping panel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP24045386A JPS6394832A (en) | 1986-10-09 | 1986-10-09 | Vibration-damping panel |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS6394832A true JPS6394832A (en) | 1988-04-25 |
Family
ID=17059723
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP24045386A Pending JPS6394832A (en) | 1986-10-09 | 1986-10-09 | Vibration-damping panel |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS6394832A (en) |
-
1986
- 1986-10-09 JP JP24045386A patent/JPS6394832A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US4778028A (en) | Light viscoelastic damping structure | |
| JP3078854B2 (en) | Internal anti-vibration type thin composite longitudinal member | |
| US5087491A (en) | Vibration-damping structural member | |
| US4053943A (en) | Technique for damping electronic module printed wiring board | |
| Wang et al. | Free in-plane vibration of rectangular plates | |
| JP2952257B2 (en) | Attenuation instrument kinematic mount | |
| US5338599A (en) | Vibration-damping structural component | |
| Bhimaraddi et al. | Generalized finite element analysis of laminated curved beams with constant curvature | |
| Thamburaj et al. | Effect of material and geometry on the sound and vibration transmission across a sandwich beam | |
| JP3133333B2 (en) | Improved damping in composite structures by stress coupling | |
| JPS6394832A (en) | Vibration-damping panel | |
| JPS6394831A (en) | Vibration-damping panel | |
| JP4370731B2 (en) | Composite vibration brace | |
| JPS6394830A (en) | Vibration-damping panel | |
| Bamford et al. | Long stroke precision PZT actuator | |
| JP2000145889A (en) | Fastening structure of on-board mounted apparatus | |
| Rajagopal et al. | Large-deflection and nonlinear vibration of multilayered sandwich plates | |
| JPH01150038A (en) | Vibration damping panel | |
| CN101327848A (en) | Damping flexible connecting method for spacecraft | |
| JP3053994B2 (en) | Coupling device | |
| Yu | Variational equation of motion for coupled flexure and torsion of bars of thin-walled open section including thermal effect | |
| JPH02214649A (en) | Viscoelastic damping structure and manufacture thereof | |
| JPH0235066Y2 (en) | ||
| Said | Theoretical and numerical study of vibrations of structures induced by pyrotechnic shocks | |
| Sloss et al. | Applications of a maximum principle for the structural control of laminated composite plates |