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部材および構造物の強度実証に対する試験計画について、区間推定およびベイズ理論を応用した評価手法をまとめる。強度の不確定性評価において、部材試験では強度モデルの未知母数推定の精度を上げるために多数標本が用いられる。一方、構造部位や実機構造などの少量生産品では耐荷重性能が重要であり、多くの標本が得られる部材試験とは強度実証法が異なる。本報告では、多数標本による部材強度の実証試験(demonstration test)について区間推定理論を適用し、必要な標本数を設定する汎用の強度実証に向けた評価法を示す。また少量標本の構造物に対する強度実証では、既開発のベイズ法を応用した耐荷重試験(proof load test)計画について、取り扱う情報源の拡大に向けた手法を展開する。, In the evaluation of structural strength uncertainty, a large number of samples are used in the material strength test in order to improve the accuracy of model estimation of strength (estimation of unknown parameters). On the other hand, proof load performance is important for small amount products such as substructures and large-scale structures, and the strength demonstration method differs from the structural material strength test. For the demonstration test of material strength, the statistical intervals theory, which is studied in detail by Meeker et al., is applied, and the definition is unified and formulated for the material strength verification method. For strength verification of small sample structures, an extended Bayesian proof load test method that allows for the expansion of the information sources used is constructed., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA2130006000, レポート番号: JAXA-RM-21-002

形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: PA1920050000

信頼度と信頼水準を統合して、平明な一元評価を可能にする、ベイズ理論を応用した強度の信頼性評価モデルを構築する。ここでは標本や確率分布の未知母数の不確定性に対してベイズ理論を適用して、目的の強度レベル対する一元評価としてのベイズ期待信頼度を定義する。ベイズ法では工学的判断などの事前情報と標本結果を用いて、未知母数をベイズ理論によって推定する。推定された未知母数は事後確率分布として形成されるが、事後分布は未知母数に対する事前分布の設定に影響を受ける。本報告では事前分布の設定に依存しないマルコフチェーン・モンテカルロ(MCMC) 法を用い、得られた事後分布からMIL値に対する信頼度のベイズ期待値を求めて、これをMIL値に対応する一元評価指標とする。, The MIL-A/B (Military specification A and B-basis) values for the reliability assessment of material strength are evaluated by two factors of reliability (0.99 and 0.9 for the A and B values) and confidence level (0.95). Towards this evaluation method, the expected reliability index is modelled as a reliability grasping technique using Bayesian analysis that integrates reliability and confidence level. The Bayesian method is applied to the uncertainty evaluation of unknown parameters to define the Bayesian expected reliability as a unitary reliability index for the allowable material strength. The construction of the Bayesian reliability method and a concrete evaluation example for the MIL value of the material strength are shown in using MCMC (Markov chain Monte Carlo) which is a representative method of calculation statistics., 形態: 図版あり, Physical characteristics: Original contains illustrations, 資料番号: AA1830027000, レポート番号: JAXA-RM-18-011

本資料は、(独)宇宙航空研究開発機構(JAXA)および旧航空宇宙技術研究所(NAL)の複合材技術開発センター(ACETeC)を中心として取得された先進複合材料、特に炭素繊維強化樹脂系複合材料(CFRP)に関する各種力学特性の試験結果を整理したデータベースである。データベース形式としては、Composite Material Handbook(CMH-17)類似の構成となるような収集を進めており、この部分についてはJAXA:HDBKと称している。本データベースについては、現在JAXA-ACDBの呼称にてドメイン名を取得してインターネットを用いて登録ユーザへのデータ提供を行っている*が、活用の利便性をさらに向上させるため、技術研究資料として改めてここに出版する。*本技術資料の公開を踏まえ、インターネットによるデータ提供は2016年3月に終了した。, This database, which has been called 'JAXA: HDBK,' summarizes the mechanical performance for advanced composite materials, especially for carbon fiber reinforced composites (CFRPs). The data have been derived mainly by advanced composite evaluation technology center (ACETeC) at Japan Aerospace Exploration Agency (JAXA) and the predecessor national aerospace lab. (NAL) in the form of Composite Material Handbook(CMH-17). JAXA: HDBK website www.jaxa-acdb.com *has been provided the on-line access database, and this JAXA Research and Development Memorandum(JAXA-RM) has been published in booklet form for the user convenience. *The website has been closed since March 2016, after the publication of this JAXA-RM., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA1730022000, レポート番号: JAXA-RM-17-004

本資料は、(独）宇宙航空研究開発機構(JAXA)および旧航空宇宙技術研究所(NAL)の複合材技術開発センター(ACETeC)を中心として取得された先進複合材料、特に炭素繊維強化樹脂系複合材料(CFRP)に関する各種力学特性の試験結果を整理したデータベースである。データベース形式としては、Composite Material Handbook(CMH-17)類似の構成となるような取集を進めており、この部分についてはJAXA:HDBKと称している。本データベースについては、現在JAXA-ACDBの呼称にてドメイン名を取得してインターネットを用いて登録ユーザへのデータ提供を行っているが、活用の利便性をさらに向上させるため、技術研究資料として改めてここに出版する。, This database, which has been called “JAXA: HDBK,” summarizes the mechanical performance for advanced composite materials, especially for carbon fiber reinforced composites (CFRPs). The data have been derived mainly by advanced composite evaluation technology center (ACETeC) at Japan Aerospace Exploration Agency (JAXA) and the predecessor national aerospace lab. (NAL) in the form of Composite Material Handbook (CMH-17). JAXA: HDBK website www.jaxa-acdb.com has been provided the on-line access database, and this JAXA Research and Development Memorandum (JAXA-RM) has been published in booklet form for the user convenience., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA1530007000, レポート番号: JAXA-RM-14-004

To propose a test method for the out-of plane tensile modulus of laminated carbon fiber-reinforced plastics, 3-point bending tests using a laminated CGRP with the span direction coinciding with out-of-plane (through-the-thickness) direction were performed. It was demonstrated that the apparent bending modulus depends on the length of span to thickness ratio (L/t) and the tensile modulus E to shear modulus G ratio (E/G). Sensitivity analyses were performed to select the length of span to thickness ratio in order to evaluate the bending modulus near material modulus. Consequently, it is predicted that the bending modulus performed with the L/t >25 bending specimen is equivalent to tensile modulus, if the apparent bending modulus were evaluated from 1 to 15GPa, while modified equations for the out-of-plane modulus of QI-CFRP laminates obtained by three-dimensional laminate theory were also derived. This modification took stress condition in consideration of the small in-plane size like bending specimens into account. Moreover, it is demonstrated that apparent bending moduli were evaluated between upper and lower-bound solutions. The upper-bound solution is an out-of-plane modulus based on existing three-dimensional laminate theory, and the other is modified out-of-plane modulus., 資料番号: PA1420046000

資料番号: SA1000949000

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博士（工学）総研大甲第1325号, 資料番号: SA8000026000

The aim of cancer vaccines is induction of tumor-specific cytotoxic T lymphocytes (CTLs) that can reduce the tumor mass. Dendritic cells (DCs) are potent antigen-presenting cells and play a central role in the initiation and regulation of primary immune responses. Thus, DCs-based vaccination represents a potentially powerful strategy for induction of antigen-specific CTLs. Fusions of DCs and whole tumor cells represent an alternative approach to deliver, process, and subsequently present a broad spectrum of antigens, including those known and unidentified, in the context of costimulatory molecules. Once DCs/tumor fusions have been infused back into patient, they migrate to secondary lymphoid organs, where the generation of antigen-specific polyclonal CTL responses occurs. We will discuss perspectives for future development of DCs/tumor fusions for CTL induction.

The goal of cancer vaccines is to induce antitumor immunity that ultimately will reduce tumor burden in tumor environment. Several strategies involving dendritic cells- (DCs)- based vaccine incorporating different tumor-associated antigens to induce antitumor immune responses against tumors have been tested in clinical trials worldwide. Although DCs-based vaccine such as fusions of whole tumor cells and DCs has been proven to be clinically safe and is efficient to enhance antitumor immune responses for inducing effective immune response and for breaking T-cell tolerance to tumor-associated antigens (TAAs), only a limited success has occurred in clinical trials. This paper reviews tumor immune escape and current strategies employed in the field of tumor/DC fusions vaccine aimed at enhancing activation of TAAs-specific cytotoxic T cells in tumor microenvironment.

一方向Carbon/Epoxy複合材料（CFRP (Carbon Fiber Reinforced Plastics)）を対象として、90度方向引張り強度の寸法効果について実験的な検討を行った。2種類の一方向CFRPに対して3点曲げ試験および引張り試験を行い、寸法効果の評価には、最弱リンクモデルに基づくワイブル分布を適用した。曲げ試験によって得られたワイブル係数を用いて有効体積、有効表面積および有効エッジに対する寸法効果を計算し、実験結果との比較を行った。その結果、有効体積と有効表面積の両方を考慮した競合リスクモデルが実験結果と良い対応を示すことがわかった。これらの検討により一方向CFRPの90度引張り強度における曲げ強度と引張り強度の等価性が実験的に示された。, Size effect of the transverse tensile strength of unidirectional carbon fiber / epoxy composites (CFRP (Carbon Fiber Reinforced Plastics)) was examined experimentally. Three point bending tests and tensile tests were carried out for two kinds of carbon/epoxy composites, and the Weibull statistics based on weakest link theory was applied for evaluating the size effect. The size effect was calculated as a function of the effective volume, surface area, or edge length using the Weibull parameters obtained from three point bending tests, and the numerical results were compared with the experimental results. As a result, it was found that competing risk model considering both effective volume and surface area showed good agreement with the experimental results. It was demonstrated that the transverse tensile strengths of unidirectional carbon/epoxy composites are basically equivalent to the bending strengths., 形態: カラー図版あり, 資料番号: AA0064233000, レポート番号: JAXA-RM-08-007

複合材料の面内特性や破壊靱性を評価するための試験は各団体(JIS(Japanese Industrial Standards)、ISO(International Organization for Standardization)、ASTM(American Society for Testing and Materials))により定められているが、面外引張特性(層間引張特性)を評価するための直接負荷試験は未だ規格化されていない。本研究では、炭素繊維強化プラスチック(Carbon Fiber Reinforced Plastic: CFRP)の面外方向の引張特性を取得するための試験方法を検討した。負荷形態はハニカムサンドイッチ板のフラットワイズ試験と同様の直接負荷方式とし、最初に試験片形状の検討のため、有限要素解析を実施した、CFRPの0度1方向積層板を対象とし、供試体形状は円柱と板厚中心部がくびれたスプール状円柱(糸巻き形状)を検討した。有限要素法ソフトABAQUSを使用して供試体内の応力状態や供試体の各位置の歪みによる見かけの弾性率を検討した。解析結果より円柱形状の供試体の場合、治具接着面近傍の特定の位置で応力集中が発生することが予測された。また、スプール状円柱形状供試体の場合、板厚中心部で応力集中が発生し、供試体評定部内での破断が予測された。中心部の直径を減少させることで、この応力集中の度合いが緩和されることが予測された。次に解析で検討した形状の供試体を製作し、検証試験を実施した。スプール状円柱の供試体の各試験結果は応力集中が予測された位置での破断が確認され、最小断面部の直径の違いによる破断強度の違いも解析予測と同様の傾向を得た。なお、円柱形状では試験実施の不安定性が確認され、標準化する試験法としては採用しがたいことも明らかにした。, Although several out-of-plane test methods are proposed in MIL-HDBK-17 (MILitary-HanDBooK-17) and in research publications, their reliability remains to be established. The present study focuses on the flatwise tension test. Finite element analyses and experiments were carried out to find the most suitable specimen configuration to evaluate out-of-plane stiffness and strength. Several variations of specimen configuration (cylindrical column and spool column) were examined. Nine types of cylindrical model were investigated, with the diameter fixed at 25 mm and the thickness varied between 2 mm and 100 mm. The numerical calculations indicated stress concentrations near the adhesive layer and a multi-axial stress state in the cylindrical model. The 'stress ratio' is defined as a representative value in which the nominal stress is divided by the maximum stress in order to describe the apparent strength. Based on stress ratios, the best configuration among the cylindrical column models was determined to be the thinnest. In the case of spool specimens, stress concentration near the minimum diameter at the center of a specimen was predicted. Through these calculations, it was concluded that the degree of multi-axial stress was lower in the spool specimens than in the column specimens, and the stress ratio approaches unity as the minimum diameter approaches zero. This suggests that the strength of a spool specimen increases as the center diameter decreases. Several experimental tests were also carried out on cylindrical and spool specimens. Failure (including delamination in the adhesive layer) was confirmed for cylindrical specimens, whereas failure at the center of the specimen was confirmed for spool specimens., 資料番号: AA0063459000, レポート番号: JAXA-RR-06-025