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形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: NAL190017000

ロケットで打ち上げられる宇宙機には、ロケットとの間のインターフェイスを通じて機械振動が加わる。さらに、広い周波数成分をもつ音圧がフェアリングを透過して宇宙機表面に加わることにより振動する。太陽電池パドルやアンテナなど軽量で大きな面積をもつ構造や、比較的高い固有振動数をもつコンポーネントは、音響荷重に影響されやすい。しかし、衛星のコンポーネントやシステムの音響試験は行なわれているが、フェアリングまでを含めた衛星の十分な音響試験及び解析は行なわれていないのが現状である。そこで、解析によって、事前に全系の検討が十分に行われることが期待されている。JAXA では、フェアリングまでを含めた衛星の音響解析手法の確立を目指し、今までに2次元WBM をフェアリング内部の衛星の音響連成問題に適用し、その応用性について検討してきた。また、解析コードの妥当性確認を目的として簡易フェアリング部材を用いた音響透過実験を行なってきた。本報告では、3 次元に拡張されたWBM の解析結果の妥当性を確認するため、アルミ板の垂直及び斜入射音響透過実験結果及び既存手法であるFEMの解析結果との比較を行った。, The mechanical vibration is applied to a spacecraft via the interface to a launch vehicle at lift-off. The spacecraft is also exposed to acoustic pressure with wide frequency range. Lightweight and large area structures, such as solar paddles, antennas, and components with relatively high natural frequencies, are sensitive to acoustic load. Although the acoustic tests are usually conducted for components and system of the spacecraft, acoustic tests and analysis of the spacecraft mounted in a fairing have not been sufficiently done. It is expected that numerical analysis can be applied to the prediction of acoustic environment inside of fairings. Japan Aerospace Exploration Agency (JAXA) has been developing a vibroacoustic prediction tool by the wave based method (WBM), which is one of the deterministic approaches and is proposed for numerical prediction up to the mid-frequency range. The existing deterministic approaches cannot accurately solve vibroacoustic problems in this range. In this report, numerical prediction results of normal and oblique incidence sound transmission through an Aluminum plate by the 3D WBM and FEM are compared with those by an experiment, and the 3D WBM is validated., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA0062293000, レポート番号: JAXA-RM-13-015

平成18年度宇宙輸送シンポジウム（2007年1月18日-19日. 宇宙航空研究開発機構宇宙科学研究本部）, 相模原市, 神奈川県, Space Transportation Symposium FY2006 (January 18-19, 2007. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000005015

Retirement of the space shuttle in 2010 was already decided and there will be some difficulties in transportation from ISS (the International Space Station) from 2010 until the next generation new transportation system CEV (Crew Exploration Vehicle) will be operative. JAXA started concept studies of re-entry systems that will be loaded in HTV (H-2 Transfer Vehicle) and will be ejected after its deorbit. A minimum but affordable capsule with the capability of carrying 50 kg payload was selected from various kinds of concept. System study was conducted and it showed that the capsule is feasible but has some technical problems to be solved., 資料番号: AA0049056018, レポート番号: JAXA-SP-05-010

This paper describes a summary of a conceptual study on a two-stage partially reusable launch vehicle system. The second stage is a conventional expendable vehicle while the first stage is reusable and glides back to a launch site after a powered turnaround maneuver. To realize such a system, several new technologies must be developed and demonstrated. The paper also summarizes the results of a design study on a flight demonstrator for the new technologies. This flight demonstrator is designated as RAFLEX (Reliable Ascent Flight Experiment)., 資料番号: AA0049056004, レポート番号: JAXA-SP-05-010

This research is continued from Research on Planning of Flight Demonstrations for Reusable Space Transportation System in the FY 2002, and is being carried out with the aim of drawing up a flight demonstration project to prove important key technologies necessary for the reusable space transportation system by flight tests in the next medium term. The following research activities were conducted in FY 2003. 1) Feasibility Confirmation of the Next Candidate Flight Demonstration System: It was studied that what kinds of flight demonstrators are effective in the development of the reusable space transportation system and feasibilities studies of those demonstrators were progressed. And to strengthen the flight demonstrations plan, each plan was compared and discussed. 2) The element technology necessary for the next flight experiment system: Important key technologies to realize the flight demonstration plan were selected, and their development researches were conducted. The flight experiment of parafoil guidance technology was carried out under the joint research with Mitsubishi Heavy Industries, Ltd., 資料番号: AA0047944001, レポート番号: JAXA-RM-04-009

In order to investigate the capability of lifting body type atmospheric re-entry by relatively small-size vehicles, basic numerical and experimental study has been performed. The vehicle is based on the blunt nosed delta body with two tip fins. Two elevons are integrated on the fuselage base to enlarge trim capability for a wide range of Mach number flight. In the design of these lifting body type re-entry vehicles, one of the most important problems is that the vehicle has a capability to accomplish the stable flight from supersonic to low subsonic speeds. Aerodynamic characteristics have changed extremely through the transonic speed range. In the present study, conceptual aerodynamic analysis of these lifting re-entry vehicles has been performed by CFD and the wind tunnel experiments at NAL., 資料番号: AA0045948025, レポート番号: NAL SP-57

資料番号: AA0033392020

NAL大型低速風洞において、運動の自由度を与えた全機形態空力弾性模型の能動制御技術(active control technology)の実証研究に使用するために、張力制御式模型支持装置を開発した。本装置では、風洞測定部中央に鉛直に設置したレールに沿って摺動する模型を測定部天井に設置したトルクモータで吊り下げている。空力弾性相似模型に運動の相似性をもたせるために、本装置は模型の吊り線の張力を一定に制御する。さらに、模型が風洞測定部をはみ出すことなく、ほぼ中央付近で安定した運動をさせるために復元力とダンピング力を遠隔操作で任意に設定する機能も有している。本装置を、NAL大型低速風洞で実施した全機形態空力弾性模型の突風荷重軽減実験に使用し有効に作動することを確認した。この報告書は本装置の構成、機能、使用例について記述する。, A tension-controlled model suspension system was developed which is to be used in validation study of active control technology, giving a complete aircraft model a motion degree of freedom in the NAL low speed wind tunnel. A torque motor on the tunnel ceiling suspends a model which moves along a rail vertically supported at the center of the wind tunnel test section. The system controls a cable tension constant against model motion in order to provide an aeroelastic similar model with motion similarity. Furthermore, this model makes it possible to give a restoring and a damping force arbitrarily by remote operation so that a model should fly around a center position without going out of the test section. The system was successfully used in the wind tunnel tests for gust load alleviation of a complete aircraft aeroelastic model, and its effective functions were verified. This report describes the structure, the performance, and the applications of the system., 資料番号: AA0000593000, レポート番号: NAL TR-1299

航空技術研究所(NAL)では実験用航空機を用いて突風荷重軽減技術を飛行実証するための研究準備が進められている。突風荷重軽減システムを設計するためには航空機の構造特性が必要である。そのためにドルニエDo228-200型機の地上振動試験が1994年3月15日から1ケ月間に実施された。本報告にはその地上振動試験および結果を記述した。, NAL (National Aerospace Laboratory) is preparing to conduct flight tests for gust load alleviation technology using an experimental airplane. The structural characteristics of the airplane are needed to design the gust load alleviation system. Ground Vibration Tests (GVT) of the Dornier 228-200 airplane were therefore carried out for one month from March 15, 1994. In this paper, the GVT and the results are described., 資料番号: AA0004266000, レポート番号: NAL TR-1259

遷音速領域でのフラッタ制御技術の風洞実証を行うため、風洞付帯設備としてフラッタ緊急停止装置が新たに必要となった。そこで遷音速風洞に設備可能なフラッタ停止装置を開発するための予備実験を遷音速風洞のパイロット風洞で実施した。風洞壁に片持支持したフラッタ翼模型と反対側の壁に設置した停止板によっても、わずかな立上り角で有効にフラッタを停止することが確認された。装置の概要、試験、結果について報告する。, To prevent damage to both the test model and the wind tunnel, flutter suppressing devices were designed for use in wind tunnel test. Preliminary tests were, therefore, conducted in the transonic pilot wind tunnel to develop devices for the 2m X 2m wind tunnel. The test results confirmed the effectiveness and safety of the flutter suppressing device. This report presents the design, tests, and results of the flutter suppressing devices., 資料番号: AA0004215000, レポート番号: NAL TR-1200

能動制御技術の1つであるフラッタ制御実験に必要となるフラッタを緊急に停止する装置を遷音速風洞に設置するために、NAL(航空宇宙技術研究所)式フラッタ緊急停止装置の遷音速におけるフラッタ停止機能を確認すること、および本装置の作動によって風洞の主送風機や補助送風機の圧力比や振動および気流へ与える影響などを把握することを目的として予備実験を遷音速パイロット風洞を使用して実施した。本装置は緊急停止(多孔)板をフラッタ供試模型の上流に立てることによって、模型周囲の動圧を減少させて発生しかけたフラッタを瞬時に停止させるものである。予備実験の結果、本装置はフラッタ停止にきわめて有効で、緊急停止板の作動角度が所定の垂直に対してわずか10％に満たない角度で供試模型のフラッタは停止するほどであった。実験では、緊急停止板の開口比を変えて、フラッタ停止機能の応答性と有効性、気流への影響、主送風機および補助送風機の振動などを測定し検討した結果、パイロット風洞のフラッタ緊急停止装置として支障のないものであることを確認した。また、本装置を2m×2m遷音速風洞に適用するためには、実機送風機などへの影響を検討する必要がある。, This paper describes the preliminary test results of a flutter halting device to be installed in the NAL 2 m X 2 m Transonic Wind Tunnel. The test was conducted using its 9 percent scale pilot tunnel. The main element of the device is a porous plate which is mounted flush with the wind tunnel test section floor upstream of the test article. When flutter occurrs, the device is raised to a vertical position from the floor causing a decrease in the dynamic pressure around the model and thus suppressing the flutter to prevent the model from being damaged. Tests showed that the device is so effective that flutter was completely suppressed when the angular position of the plate was still less than ten percent of its maximum elevation. Tests were also conducted to evaluate the effects of plate geometry (especially the porosity characteristics) in terms of its ability to suppress flutter as well as its possible adverse effects on the tunnel driving system, i.e. performance degradation or vibration provocation on the main blower the auxiliary blower or the wind tunnel rotor blade. No degrading effects were observed with this device., 資料番号: AA0004212000, レポート番号: NAL TR-1197

宇宙航空研究開発機構では，次世代の再使用宇宙輸送システムの様々なコンセプトについて検討してきたが，その中の有望なものの一つとしてリフティングボディ形状の往還システムがある．これは翼をもたず，胴体の形状によって揚力を発生するタイプの機体であり，構造の軽量化，高い容積効率，極超音速域での空力加熱特性の観点から優位性があるとされている．一方，リフティングボディ形状は揚抗比が小さく，また低速時の安定性/ 制御性が弱いため，ALFLEX（小型自動着陸実験1996）のような翼胴型の機体に比較して滑走路への進入/ 着陸時に困難がある．そこで，リフティングボディ形状の往還システムを実現するうえで最も重要な技術課題の一つとなっている自動着陸技術の蓄積を主目的とした飛行実験を，小規模で低コストな機体を用いて行うことを計画した．本報告では，飛行実験計画および実験システムの概要と，地上試験やヘリコプタを用いた懸吊飛行試験を含む開発のプロセスについて詳述する．, The Japan Aerospace Exploration Agency, JAXA, has investigated various concepts of next generation reusable space transportation systems. Lifting-body re-entry vehicle is one of the most promising concepts among them. This type of vehicle has no wings and derives its lift solely from the shape of its body. Therefore it has the advantages of reduced structural weight, superior volumetric efficiency, and better characteristics against aerodynamic heating at hypersonic speed. On the other hand, the disadvantages of its low lift-drag ratio, poor stability and controllability at low speed make it more diffi cult to land on a conventional runway than in the case of a winged vehicle like in the Automatic Landing Flight Experiment (ALFLEX), which was conducted in 1996. The Lifting-body Flight Experiment (LIFLEX), a fl ight experiment using small low-cost vehicle, was planned to accumulate the knowledge and skills for automatic landing technology, which is one of the largest technology hurdles to realize a lifting body re-entry system. This report describes the outline of the experiment fl ight plan and the experiment system, and the process of development in some detail, including several ground tests and constrained flight tests using a helicopter., 形態: カラー図版あり, 著者人数: 20人, Physical characteristics: Original contains color illustrations, 資料番号: AA0064778000, レポート番号: JAXA-RR-10-004

リフティングボディ型再突入機の空力特性を取得し、形状設計のためのデータや経験を蓄積するために、亜音速から極超音速の範囲で風洞試験を実施した。風試はM=0.5〜1.4についてはNAL 2m×2m遷音速風洞で実施し、M=1.4〜4.0についてはNAL 1m×1m超音速風洞で実施した。またM=10程度の極超音速域についてはNAL 1.27m極超音速風洞で実施した。風洞試験は基本形状の他、形状変更効果を見るために各種変更形状についてもデータを取得した。またエレボンやラダーなどの操舵面の効果を見るため、それぞれの操舵形態についてもデータを取得した。風洞試験の結果、遷音速における基本形状の空力特性は両外舷に取り付けたフィンによる非線形な傾向を示すことが分かった。またフィン前縁後退角を41度から60度へ大きくした場合や胴体上面後縁部を舵面操舵の様に20度切り上げることにより、空力特性の非線形な傾向が改善することも分かった。極超音速では、全形状についてピッチングモーメント特性について迎角範囲が15〜22度で頭下げの傾向が見られた(他の迎角範囲では頭上げ)。また極超音速域で胴体上面変更の効果はほとんどないがフィンキャント角を20度から45度へ変更した場合、高迎角では方向安定性が向上することも分かった。, A series of wind tunnel tests from subsonic to hypersonic speeds were conducted to investigate the aerodynamic characteristics of a lifting-body type configuration for reentry vehicles and to accumulate knowledge and experience for the design of such vehicles. The tests were conducted at the NAL 2 m x 2 m Transonic Wind Tunnel for Mach numbers from 0.5 to 1.4 and at the NAL 1 m x 1 m Supersonic Wind Tunnel for numbers 1.4 to 4.0. For hypersonic speed of about Mach 10, the test was conducted at the 1.27 m Hypersonic Wind Tunnel. Data were obtained for the baseline configuration and several derived configurations to ascertain the effect of configuration modifications. The effectiveness of control surfaces such as elevons and rudders was also investigated. The test data indicated fin-induced nonlinear characteristics for the baseline configuration at transonic speeds. Data also indicated that enlarging the leading edge sweepback angle of the outboard fins from 41 deg. to 60 deg. or upsweeping the upper aft surface of the fuselage 20 deg., like an upward deflection of a control surface, improves the nonlinear characteristics. For the hypersonic test, a pitch down trend at angles of attack from 15 deg. to 22 deg. was observed for all configurations (with a pitch up trend for other angles of attack). No significant effect was observed for upper surface modification at hypersonic speeds, however, enlarging the fin cant angle from 20 deg. to 45 deg., improved the directional stability., 資料番号: AA0047388000, レポート番号: NAL TR-1468

資料番号: NALTM0626000, レポート番号: NAL TM-626

資料番号: NALTM0624000, レポート番号: NAL TM-624

論文タイプ||論説

論文タイプ||論説