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Start Over Descriptor "有限要素法" Publisher 宇宙科学研究所
12 results on '"有限要素法"'

1. 太陽発電実証衛星の運用時における振動特性

Author

Senda, Kei, Kanafuki, Mitsuhiro, and Okuizumi, Nobukatsu

Subjects
実証衛星, vibrational characteristic, solar power satellite, finite element method, truss, 静止負荷, static load, 数学モデル, 有限要素法, トラス, antenna, research and development, 振動特性, USEF, SSPS, アンテナ, Physics::Space Physics, 太陽パワー衛星, structural strength, demonstration satellite, mathematical model, 研究開発, 構造強度
Abstract

There is a concept of a space solar power system (SSPS) using solar power satellites (SPS), which is discussed at the institute for unmanned space experiment free flyer (USEF). Before realizing the actual SSPS, a solar power demonstration satellite will be conducted. This study discusses the structural and dynamical feasibility of the demonstration SPS. For the purpose, this study formulates the structural and dynamical model of the demonstration SPS using a finite element model. The mathematical model enables some analysis and derives the following results. Operational static loads are negligible for the system structural strength. Orbit keeping thrusts causes the worst dynamic loads to the structure. Truss part has critical load and additional strength may be requested to an existing Japanese truss structures. The requirements of the antenna shape accuracy will be satisfied., 資料番号: AA0045915013

Published
2003

2. Damping design for controlling flutter bound of free-free beams subjected to rocket thrust

Author

Hamatani, Masaya and Sugiyama, Yoshihiko

Subjects
cantilever beam, free-free beam, finite element method, 振動減衰, rocket thrust, Beckの柱, Beck's column, 数学モデル, 有限要素法, ロケット打上げ, ロケット推力, rocket launching, フラッター限界, flutter bound, dynamic stability, 動安定性, 自由・自由梁, vibration damping, 片持ち梁, mathematical model
Abstract

資料番号: AA0045440033

Published
2003

3. Measurement of mode displacement by an optimal arrangement of strain gauges

Author

Kawabata, Nariyuki, Hayata, Hiroki, and Fukunaga, Hisao

Subjects
構造歪み, large space structure, strain distribution, 歪み測定, finite element method, mode sensor, 最適配置, structural vibration, 振動減衰, optimal arrangement, モードセンサー, 大型宇宙構造物, vibration measurement, 有限要素法, 数値シミュレーション, 振動測定, numerical simulation, 構造振動, structural strain, vibration damping, strain measurement, 歪み分布
Abstract

資料番号: AA0045440036

Published
2003

4. Fracture mechanism of an FWCFRP hoop-winding layer rocket-motor casing

Author

Yamada, Masahiro and Suemasu, Hiroshi

Subjects
炭素繊維強化樹脂, トランスバースクラック, carbon fiber reinforced plastic, hoop width, motor case, finite element method, 固体燃料ロケットエンジン, interlaminar stress, composite material, delamination, 有限要素法, モーターケース, solid propellant rocket engine, transverse crack, 複合材料, 層間応力, 層間剥離, フープ幅
Abstract

資料番号: AA0045440005

Published
2003

5. Establishing a structure health monitoring method by means of smart structures with piezoelectric elements

Author

Miyashita, Tsuyoshi, Abe, Masato, and Fujino, Yozo

Subjects
スマート構造, 構造ヘルスモニタリング, 非破壊試験, finite element method, piezoelectric element, 振動試験, structure health monitoring, 構造信頼性, 有限要素法, forced vibration, Euler-Bernoulli beam, impedance analyzer, structural analysis, 圧電素子, 構造解析, ピエゾインピーダンス法, インピーダンスアナライザー, structural reliability, nondestructive test, smart structure, 数学モデル, piezo-impedance method, 強制振動, Euler-Bernoulli梁, mathematical model, vibration test
Abstract

資料番号: AA0045440037

Published
2003

6. The effect of folds on the vibration of membrane surface with one-dimensional deployment

Author

Ienaka, Yoshihiro and Furuya, Hiroshi

Subjects
折畳み構造, large space structure, resonant frequency, finite element method, structural vibration, rigid structure, 振動減衰, fold, 大型宇宙構造物, 剛体構造, 折り目, 有限要素法, 数値シミュレーション, 展開構造物, 共鳴周波数, membrane structure, numerical simulation, 構造振動, folding structure, vibration damping, 膜構造物, deployable structure
Abstract

資料番号: AA0045440023

Published
2003

7. Identification of the impact load of laminates by using imbedded piezoelectric sensors

Author

Tajima, Masanori, Matsumoto, Satoshi, and Fukunaga, Hisao

Subjects
衝撃荷重同定, 加速度計, スマート構造, 圧電センサー, 炭素繊維強化樹脂, 衝撃ハンマー, impact load identification, 超高速飛翔体, carbon fiber reinforced plastic, 積層板, finite element method, 電荷増幅器, smart structure, 有限要素法, accelerometer, impulse hammer, load distribution, piezoelectric sensor, 宇宙機製造材料, laminate, 荷重分布, spacecraft construction material, hypervelocity projectile, charge amplifier
Abstract

資料番号: AA0045440035

Published
2003

8. Dynamics analysis of a solar power satellite

Author

Senda, Kei, Kanafuki, Mitsuhiro, and Okuizumi, Nobukatsu

Subjects
太陽電池, H-2A rocket, large space structure, solar power satellite, finite element method, rectenna, elastic deformation, 有限要素法, dynamic structural analysis, 構造振動, H-2Aロケット, vibration damping, レクテナ, 太陽発電衛星, space solar power system, トラス展開機構, structural vibration, 振動減衰, 衛星姿勢制御, truss deployment mechanism, 大型宇宙構造物, solar cell, 動力学的構造解析, 弾性変形, 宇宙太陽発電システム, satellite attitude control
Abstract

資料番号: AA0045440030

Published
2003

9. On the improvement of a bending vibration model of a solid rocket motor with incorporation of propellant behavior

Author

Kosetsu, Yuji

Subjects
H-2A rocket, 推薬消費, resonant frequency, Craig-Bampton method, finite element method, ポアソン比, 固体燃料ロケットエンジン, 3次元モデル, propellant consumption, three dimensional model, 有限要素法, solid propellant rocket engine, 共鳴周波数, Poisson ratio, H-2Aロケット, 固体ロケット燃料, 横振動, Craig-Bampton法, solid rocket propellant, lateral vibration
Abstract

本論文は、ロケットの振動荷重を予測する解析法の信頼性を向上させるため、固体ロケット・モータ(SRM: Solid Rocket Motor)の振動モデルの改善について提案するものである。SRMは、ロケットを構成する主要なコンポーネントの1つであり、ロケット全機の振動特性に影響を及ぼす。しかし、SRMのモデル化には、従来の簡便なはりモデルが適用されており、固体推進薬の連成は考慮されていない。本研究ではSRMの曲げ振動を対象として、固体推進薬の連成効果を組入れたモデルの改善を行った。改善モデルの特徴は、1)固体推進薬の非圧縮性が考慮できる混合法FEMを適用した点、2)新しく開発した非圧縮材用の固有値計算法を適用した点、3)Craig-Bampton法によりサイズを縮小した固体推進薬モデルとモータ・ケース・モデルとを結合してSRMモデルを作成した点である。本改善モデルと従来のモデルによる固有振動解析結果の比較から、SRMの曲げ振動に従来のはりモデルでは予測できない固体推進薬の連成振動が現れることが明らかになった。, 資料番号: AA0045440034

Published
2003

10. 太陽発電実証衛星の運用時における振動特性

Author

Senda, Kei, Kanafuki, Mitsuhiro, Okuizumi, Nobukatsu, 泉田 啓, 金吹 光浩, 奥泉 信克, Senda, Kei, Kanafuki, Mitsuhiro, Okuizumi, Nobukatsu, 泉田 啓, 金吹 光浩, and 奥泉 信克

Abstract

There is a concept of a space solar power system (SSPS) using solar power satellites (SPS), which is discussed at the institute for unmanned space experiment free flyer (USEF). Before realizing the actual SSPS, a solar power demonstration satellite will be conducted. This study discusses the structural and dynamical feasibility of the demonstration SPS. For the purpose, this study formulates the structural and dynamical model of the demonstration SPS using a finite element model. The mathematical model enables some analysis and derives the following results. Operational static loads are negligible for the system structural strength. Orbit keeping thrusts causes the worst dynamic loads to the structure. Truss part has critical load and additional strength may be requested to an existing Japanese truss structures. The requirements of the antenna shape accuracy will be satisfied.

Published
2015

12. 18th Symposium on Aerospace Structure and Materials

Author

Institute of Space and Astronautical Science

Subjects
large space structure, inflatable space structure, finite element method, hypervelocity impact, ソーラーセイル, 有限要素法, research and development, liquid propellant rocket engine, membrane structure, 膜構造物, solar sail, 液体燃料ロケットエンジン, 通信衛星, 超高速衝突, graphite, 燃料ターボポンプ, インフレータブルな宇宙構造物, グラファイト, 炭素・炭素複合材料, scanning electron microscope, 大型宇宙構造物, 疲労き裂, 展開構造物, 走査型電子顕微鏡, carbon-carbon composite, fuel turbopump, fatigue crack, deployable structure, communication satellite, 研究開発
Abstract

20021108, 資料番号: AA0045440000

Published
2003

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