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S-520-23号機に搭載されたインフレータブル伸展方式アンテナは全伸展したことが確認され、EVMR(Electric field and VLF/MF band radio Receiver)-ANTとして電場・VLF(Very Low Frequency)/MF(Medium Frequency)帯電波受信に供することができた。, 資料番号: AA0063716020

ドラッグフリー技術に基づいた新しい自由落下カプセルを、2006年5月に高高度気球B200を用いて高度40kmから投下し、微小重力実験が行われた。今回の最初の試験飛行により、3陸大気球観測所の制御室とカプセルとの間での無線通信、ドラッグフリー制御、そして飛行シーケンスを分析するための基本的データを得ることに成功した。, The first microgravity experiment using a new free-fall capsule released from 40 km altitude was performed on May, 2006 based on a drag-free technique. The fundamental data for analyzing the drag-free control, the flight sequence, and the wireless communication between the capsule and a control room were successfully obtained in the first test flight., 資料番号: AA0063732002, レポート番号: JAXA-RR-07-009

Blade-Vortex Interaction (BVI) is known to be one of the most annoying sources of helicopter noise. In order to obtain acoustic waveforms of BVI noise, a series of flight tests was conducted by JAXA's MuPAL-epsilon (Multi-Purpose Aviation Laboratory-epsilon) research helicopter using a microphone mounted on its nose boom. The measured acoustic data of the flight tests shows apparently stronger BVI noise in turning flight than in straight flight at the same airspeed and vertical speed. From the flight conditions, two cases, a straight descent and a descending turn, are chosen to compare the noise pattern with CFD (Computational Fluid Dynamics) computation and to understand the BVI noise characteristics during coordinate turns. Trim data obtained through a flight simulation code are given to CFD computation for two cases. CFD simulation successfully reproduces the tendency of increasing BVI noise due to the turning maneuver at least for the present flight conditions., 資料番号: AA0063742021, レポート番号: JAXA-SP-07-016

航空宇宙技術研究所 17-19 Jan. 2000 東京 日本, National Aerospace Laboratory 17-19 Jan. 2000 Tokyo Japan, 航空機設計は風洞試験に基づいて行い、最終的な検証を飛行試験で行うのが従来の手法であった。1960年代後期にCFD(計算流体力学)が出現した。計算機の速度および記憶容量が増加するにつれて、航空機設計におけるCFDの役割が着実に増加した。今日、CFDは風洞試験および飛行試験とともに主要な空力技術となっている。リスクを減らし、低コストで優れた性能を達成するにはこれらの技術それぞれに最新の技術能力が必要である。本報ではBombardierのビジネスジェットおよび地域ジェットへの応用を例に説明し、高性能ジェット機の空力技術開発におけるCFDの役割を考察した。重点を手法におき、特に、最適形態に到達するためのCFDと目標を絞った風洞試験および飛行試験との組合せに重点を置いた。, The approach to aircraft design has traditionally been based on wind tunnel testing with flight testing being used for final validation. CFD (Computational Fluid Dynamics) emerged in the late 1960's. Its role in aircraft design increased steadily as speed and memory of computers increased. Today CFD is a principal aerodynamic technology along with wind tunnel testing and flight testing. State of the art capabilities in each of these technologies are needed to achieve superior performance with reduced risk and low cost. This paper discusses the role of CFD in the aerodynamic development of high performance jets, as illustrated by the application to Bombardier Business and Regional Jets. Emphasis is put on the methodology, in particular the combination of CFD with targeted wind tunnel tests and flight tests to arrive at optimal configurations., 資料番号: AA0028638007, レポート番号: NAL SP-49T

SST-CFDワークショップ.次世代超音速機の数値シミュレーション利用技術に関する国際ワークショップ: Toward the Future form NEXST-1 Flight Trial 宇宙航空研究開発機構 20061012-20061013 東京 日本, SST-CFD Workshop. International Workshops on Numerical Simulation Technology for Design of Next Generation Supersonic Civil Transport: Toward the Future form NEXST-1 Flight Trial Japan Aerospace Exploration Agency 20061012-20061013 Tokyo Japan, The system of JAXA small supersonic experimental airplane (NEXST-1: National EXperimental Supersonic Transport-1) has been briefly explained. Some design problems that the designers have encountered have also been briefly explained., 資料番号: AA0063609067, レポート番号: JAXA-SP-06-029E

SST-CFDワークショップ.次世代超音速機の数値シミュレーション利用技術に関する国際ワークショップ: Toward the Future form NEXST-1 Flight Trial 宇宙航空研究開発機構 20061012-20061013 東京 日本, SST-CFD Workshop. International Workshops on Numerical Simulation Technology for Design of Next Generation Supersonic Civil Transport: Toward the Future form NEXST-1 Flight Trial Japan Aerospace Exploration Agency 20061012-20061013 Tokyo Japan, This paper describes the outline of the CFD (Computational Fluid Dynamics) analysis workshop on the NEXST-1 (National EXperimental Supersonic Transport-1) flight test, which was held on October 13, 2006. The NEXST-1 flight test was conducted to validate JAXA's CFD-based aerodynamic design concepts on a future supersonic transport aircraft. The comparison of the flight test data and CFD analysis results validated the design concepts qualitatively, but some quantitative differences were also found. To understand the true effects of the design concepts, those differences should be investigated in detail. As one of the best ways for such investigation, present CFD analysis workshop was planned and the validation of JAXA's CFD results was selected as a main theme. In this paper, first of all, several discussion points to be investigated were summarized. Then, analysis subjects are also described. Four parties finally participated in this workshop and compared their original CFD results with the flight test data to investigate the discussion points., 資料番号: AA0063609066, レポート番号: JAXA-SP-06-029E

SST-CFDワークショップ.次世代超音速機の数値シミュレーション利用技術に関する国際ワークショップ: Toward the Future form NEXST-1 Flight Trial 宇宙航空研究開発機構 20061012-20061013 東京 日本, SST-CFD Workshop. International Workshops on Numerical Simulation Technology for Design of Next Generation Supersonic Civil Transport: Toward the Future form NEXST-1 Flight Trial Japan Aerospace Exploration Agency 20061012-20061013 Tokyo Japan, In this study, flow computations were performed on the NEXST-1 (National EXperiment Supersonic Transport-1) with unstructured mesh solver. Two different meshes and two different turbulence models were used. The computational results were compared with NEXST-1's flight data. As a whole, the computational result showed a good agreement with flight data, except the pressure distribution on the lower surface in alpha-sweep cases., 資料番号: AA0063609074, レポート番号: JAXA-SP-06-029E

SST-CFDワークショップ.次世代超音速機の数値シミュレーション利用技術に関する国際ワークショップ: Toward the Future form NEXST-1 Flight Trial 宇宙航空研究開発機構 20061012-20061013 東京 日本, SST-CFD Workshop. International Workshops on Numerical Simulation Technology for Design of Next Generation Supersonic Civil Transport: Toward the Future form NEXST-1 Flight Trial Japan Aerospace Exploration Agency 20061012-20061013 Tokyo Japan, 資料番号: AA0063609068, レポート番号: JAXA-SP-06-029E

SST-CFDワークショップ.次世代超音速機の数値シミュレーション利用技術に関する国際ワークショップ: Toward the Future form NEXST-1 Flight Trial 宇宙航空研究開発機構 20061012-20061013 東京 日本, SST-CFD Workshop. International Workshops on Numerical Simulation Technology for Design of Next Generation Supersonic Civil Transport: Toward the Future form NEXST-1 Flight Trial Japan Aerospace Exploration Agency 20061012-20061013 Tokyo Japan, Flight test of a supersonic experimental airplane was performed by Japan Aerospace Exploration Agency to improve advanced aerodynamic design technologies for the next generation SST (SuperSonic Transport). The experimental airplane was designed to reduce the drag on a supersonic cruise condition. Surface pressure distributions, boundary layer transition locations and aerodynamic forces in the flight test were obtained to demonstrate the aerodynamic design concepts. The flight test results evaluated by comparing with the prediction results obtained by CFD (Computational Fluid Dynamics) based optimum design tools. The flight test results relatively corresponded to the CFD results. Aerodynamic design concepts for drag reduction were demonstrated qualitatively and quantitatively by the NEXST-1 (National EXperimental Supersonic Transport-1) flight test., 資料番号: AA0063609065, レポート番号: JAXA-SP-06-029E

SST-CFDワークショップ.次世代超音速機の数値シミュレーション利用技術に関する国際ワークショップ: Toward the Future form NEXST-1 Flight Trial 宇宙航空研究開発機構 20061012-20061013 東京 日本, SST-CFD Workshop. International Workshops on Numerical Simulation Technology for Design of Next Generation Supersonic Civil Transport: Toward the Future form NEXST-1 Flight Trial Japan Aerospace Exploration Agency 20061012-20061013 Tokyo Japan, Four parties participated in the 4th SST (SuperSonic Transport)-CFD (Computational Fluid Dynamics) Workshop. They analyzed aerodynamic characteristics of the NEXST-1 (National EXperimental Supersonic Transport-1) flight test according to their own CFD analysis plans. After the presentations by four parties, several viewpoints on the future studies were discussed at the workshop. This paper summarizes those discussion points, action items to be studied and JAXA's results on some of the action items after this workshop. As a conclusion, this workshop revealed present JAXA's CFD results were almost valid by comparing them with the flight test data, although some quantitative differences have still remained. Therefore, principal discussion points were focused on turbulence model, transition condition and effect of small parts in the comparison of drag polar curve between the flight test data and CFD results. As concerned with inviscid force characteristics, all CFD results showed a very good agreement., 資料番号: AA0063609076, レポート番号: JAXA-SP-06-029E

資料番号: AA0063330001, レポート番号: JAXA-SP-06-020

SST-CFDワークショップ.次世代超音速機の数値シミュレーション利用技術に関する国際ワークショップ: Toward the Future form NEXST-1 Flight Trial 宇宙航空研究開発機構 20061012-20061013 東京 日本, SST-CFD Workshop. International Workshops on Numerical Simulation Technology for Design of Next Generation Supersonic Civil Transport: Toward the Future form NEXST-1 Flight Trial Japan Aerospace Exploration Agency 20061012-20061013 Tokyo Japan, 資料番号: AA0063609071, レポート番号: JAXA-SP-06-029E

SST-CFDワークショップ.次世代超音速機の数値シミュレーション利用技術に関する国際ワークショップ: Toward the Future form NEXST-1 Flight Trial 宇宙航空研究開発機構 20061012-20061013 東京 日本, SST-CFD Workshop. International Workshops on Numerical Simulation Technology for Design of Next Generation Supersonic Civil Transport: Toward the Future form NEXST-1 Flight Trial Japan Aerospace Exploration Agency 20061012-20061013 Tokyo Japan, A flight test of a supersonic experimental airplane (NEXST-1: National EXperimental Supersonic Transport-1) was conducted successfully by JAXA in October 2005. In this study some aerodynamics design concepts were verified by comparing the flight test results with CFD (Computational Fluid Dynamics) analysis using JAXA's CFD codes, a structured mesh code UPACS (Unified Platform for Aerospace Computation Simulation) and an unstructured mesh code TAS (Tohoku university Aerodynamic Simulation). After the CFD codes was verified using a wind tunnel test results, the CFD results were compared with the flight test results. The aeroelastic deformation and the boundary layer transition data of flight test were taken into account to improve CFD analysis. The effect of the design concept of the NEXST-1 was also confirmed by CFD analysis., 資料番号: AA0063609072, レポート番号: JAXA-SP-06-029E

Tokyo Tech had developed a nano-satellite Cute-1.7 + APD (Avalanche Photo Diode) that was launched by JAXA M-V-8 rocket and conducted its initial missions. We also have developed the succeeding satellite that will be launched on June 2007., 資料番号: AA0063349032

The Japan Space Exploration Agency (JAXA) is developing a hypersonic turbojet engine to realize Mach 5 or 6 cruise vehicles and reusable LEO transportation systems. Design and fabrication of a subscale turbojet engine of 1 kN thrust with an air precooking system have been continued. In 2005, we conducted performance verification test of a newly developed air-precooler, compressor, and a liquid hydrogen supply system for the subscale engine. Test results are briefly reported in this paper., 資料番号: AA0049500023, レポート番号: JAXA-SP-06-006

飛行方向を制御可能なパラフォイルの横風に対する応答性および自然風下での操舵性能の定量的把握を目的として、スパン3mのパラフォイルを用いてスレッド試験・建物屋上からの投下実験を継続的に実施し、データの蓄積を図っている。飛行環境をより実際に近づけるには、より高い高度からの飛行が必須であり、繰り返し実験が可能なゴム気球を利用した実験方法を今回確立した。高度70mから切離し、地上からの手動誘導飛行を3回行い、最後の試験では、予め決定した目標点から3.2mの地点に着地した。, For the purpose of accumulating flight data with emphasis on the lateral-directional stability of a parafoil, the free-flight experiments of the parafoil with 3 m span were conducted from a small balloon filled with helium gas. The parafoil was released from the balloon at the height of 70 m, and it was guided towards the pre-determined target by the manual commands from the ground. In the last experiment, it was landed at the point where the distance from the target was 3.2 m., 資料番号: AA0063480053

小型ジェットエンジンを使った騒音の計測と制御についての実験の需要が高まっている。飛行実験への発展などを視野に入れると、高温排気ジェットや圧縮機音を模擬でき、かつ機動性に富んだ小型ジェットエンジンが必要である。一方、ラジコン飛行機用小型ジェットエンジンは、信頼性、耐久性、操作性が格段に向上し、エンジン運転実験、風洞実験、更に飛行実験に堪えうる有力な実験装置として期待されている。かかる背景の下、小型ジェットエンジンを様々な騒音実験に利用しながら、ノウハウを蓄積してきた。本発表は、小型ジェットエンジンを使った単体運転、能動制御実証、風洞模型、飛行実験について、適用例を紹介する。, 資料番号: AA0049211003, レポート番号: JAXA-SP-05-016

一層の騒音低減には、個々の音源の情報を把握すること、即ち音源探査が必要である。航空機騒音に於いては、エンジン、高揚力装置、脚などの要素のみならず、全機模型についての音源探査が有効である。音源探査法としてマイクロホンアレイ法を採用し、風洞実験や飛行実験に適用して技術向上を図ってきた。本報では、これまでの音源探査例について紹介する。, 資料番号: AA0049211004, レポート番号: JAXA-SP-05-016

柔構造エアロシェルは再突入体や惑星突入する衛星への応用が提案されているが、柔構造体の高速気流中での空力特性に関しては、完全に理解されているとは言えない。そこで、その高速飛行性能を実証するためにJAXAの大気球を用いた柔構造機体の飛行試験が計画され、その第1回目の試験が2003年9月に行われた。本論文は、カプセル形状の本体にフレア型の柔構造エアロシェルを取り付けた機体のフライト試験の概要、機体開発、および、実験結果についての報告を行う。フライト試験では、気球のゴンドラとフライト機体の切り離し機構の不具合によって機体単体での飛行は実現しなかったが、1)風洞実験などの事前試験によって、フレア型の柔構造エアロシェルに関して、その変形形状や空力特性などについて知見を得た、2)直径1.35mサイズの柔構造エアロシェルの収納展開を地上試験で実証した、3)膜展開構造を含むフライト機体とカプセル内部に搭載された機器は飛行中健全に機能していたことが確認された、などの今後の開発につながる様々な成果が得られた。, Membrane aeroshell has a potential for application to re-entry capsules and planetary-entry probes in the future due to its low mass and low storage volume. Its characteristics, however, is not well understood particularly in high speed flow regions. The flight test using the scientific balloon is conducted to demonstrate its high speed flight capability on September 1st, 2003. This paper describes the outline of this project, the development report of the flight model with the flare-type membrane aeroshell, and the results of the flight tests. Despite the flight model dropped with a gondola because of the trouble in the separation device, there are a lot of accomplishments in this project; 1) to obtain the knowledge about the deformation, stability, and aerodynamic characteristics of the flare-type membrane aeroshell by pre-flight wind tunnel test, 2) to demonstrate that 1.35 meter diameter membrane aeroshell can be stowed in a backside of the 0.5 meter capsule and deployed automatically in the ground test, and 3) to verify that the almost all of the sensors installed in the capsule worked normally at the high altitude and the deployed membrane aeroshell can withstand the actual flight environment., 資料番号: AA0048133004, レポート番号: JAXA-RR-04-015

本稿では、完全再使用宇宙輸送系の構築へ向けた最初の1歩として、ロケット複合サイクル推進系の開発が急務であり、それを早期に実現するためには、飛翔実験装置(FTB=Flying Test Bed)の開発・運用こそが優先課題であるとした講演の内容をまとめた。, 資料番号: AA0049122098

資料番号: AA0049122181

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

2003年10月、JAXA能代多目的実験場に於いて「再使用ロケット実験機第3次離着陸実験(RVT-9)」が実施された。再使用ロケット実験機(RVT、 Reusable Vehicle Test)とは、将来繰り返し飛行が可能な完全な再使用型のロケットに関する技術・経験の蓄積を目的とした機体であり、その実現の鍵の1つとして、機体構造の軽量化が挙げられている。本論文は、機体軽量化の一環として開発を進めた複合材極低温タンクの開発過程および得られた成果・知見について報告するものである。, 資料番号: AA0047118051

The University of Queensland successfully achieved a Scramjet flight experiment by using NASA sounding rocket Terrier-Orion. This flight experiment technique for Scramjet research is called HyShot. JAXA has been planning HyShot-based flight experiment aiming for demonstration of JAXA's advanced Scramjet technology based on the ground testing. In the present paper the outline of the flight experiment program, results of the ground testing and progress situation are reported., 資料番号: AA0047118017

東工大松永研究室では、CUTE-1と呼ぶ1kg、10cm立法の超小型衛星の設計と製作を学生主導により進めてきた。そして、2003年6月31日ロシアのプレセツク宇宙基地より成功裏に打ち上げられ、現在も正常に動作している。CUTE-1は、超小型衛星用バスシステムの開発を目的として、通信、姿勢・温度計測およびアンテナ・太陽電池パドルの展開の3つのミッションを行う。本稿では、まずCUTE-1のシステム概要と打ち上げから軌道投入までの流れについて説明する。次にCUTE-1の運用報告として、CUTE-1の軌道上の角速度や温度について述べ、そしてCUTE-1のテレメトリデータを用いた超小型衛星のダイナミクス解析について解説する。特にCUTE-1搭載のジャイロデータよリ計測した角速度を用いたアンテナと太陽電池パドルの展開の影響に対する評価や、太陽セルの発生電流から推測する太陽方向ベクトルに対する運動との比較結果について述べる。, At Laboratory for Space Systems, Tokyo Institute of Technology, students had designed and fabricated a pico-satellite (1 kg, 10 cm cube), named CUTE-1. CUTE-1 was successfully launched at the Plesetsk Cosmodrome, Russia aboard ROCKOT on Jun 30, 2003, and is properly working. CUTE-1 has three missions. First one is communication, second one is attitude and temperature sensing, and third one is deployment of antennas and solar paddle. The objectives of these missions are to establish bus component design for pico-satellites like the CubeSat. At first, this paper mentions the system overview of CUTE-1 and the procedure from launch to injection into the orbit. Second, results of temperature and angular velocity measurement are described as the operation reports. Third, analyses of nano satellite dynamics is explained using CUTE-1's telemetry data. Especially, the effect of deployment of antenna and solar paddle is examined using the angular velocity calculated gyro data on CUTE-1. Furthermore, the angular velocity during steady rotation is compared with the motion of a vector toward Sun, which is estimated using current data of each solar cell array., 資料番号: AA0046652006

資料番号: AA0046651015

資料番号: AA0046651014

Computational analysis of High Speed Flight Demonstrator (HSFD) Phase 2 Vehicle are presented. HSFD Phase 2 is the flight experiment to reduce uncertainties in the HOPE-X transonic aerodynamics. HSFD vehicle is 25 percent scale model of HOPE-X. The phase 2 flight experiment will be scheduled at the Swedish Space Corporation's Esrange site in Sweden in 2003 and conducted in collaboration with Centre National d'Etudes Spatiales (CNES) of France. In this paper, multi-block Navier-Stokes simulations have been performed for the HSFD model and total aerodynamic performance including base regions has been investigated. Especially, study of the base flow effects is focused on for the accurate prediction of total aerodynamic characteristics. Computational results are compared with the experimental data of NAL transonic wind tunnel at M(sub infinity) = 0.8, 1.05 and 1.2., 資料番号: AA0045948026, レポート番号: NAL SP-57

資料番号: AA0045439021

現在、将来型宇宙輸送システムとしてTSTOの第1段に、ISASにより開発されたエクスパンダサイクルエアターボラムジェットエンジン(ATREX)の搭載が提唱されている。ATREXエンジンの開発フェーズは、基礎研究、地上燃焼試験の段階を終え、飛行実証実験による部品やサブシステムの機能、性能評価、試験データ取得が待たれる段階に至っている。本論文では、ATREXエンジンの飛行実証実験を行なうため、既存の固体ロケットブースタを使用したATREXエンジン飛行実証実験を提案する。また、飛翔実証実験機を所定のマッハ数まで加速するための固体ブースタの最適スラストの検討とATRエンジン燃焼実験時に必要とされる誘導制御方式の検討結果の1例について触れその評価を行なう。, Space Transportation Systems for TSTO first stage using expander cycle air-turbo ramjet (ATREX) engine developed by ISAS are proposed. For ATREX engine development, basic study and firing tests on ground is finished, then practical flight demonstration experiments are expected to obtain some parts and subsystem function, ATREX performance and some test dates. In this paper, ATREX practical flight demonstration test by using existing solid rocket motor to accelerate appointed Mach Number is proposed, and where thrust optimization for solid rocket booster is discussed. And a navigation and control method for throwing ATREX test flight vehicle to dynamic pressure constant trajectory is proposed, and evaluate these simulation results., 資料番号: AA0045497017

現在、科学観測ロケットの回収方法として、パラフォイルを用いたシステムが注目されている。本研究では、定点回収を目標にパラフォイルの運動解析を行った。さらに、MATLABを用いてシミュレータを作成し、様々な応答についてシミュレーションを行った。今回、数値データのモデルとして小型のラジオコントロールパラフォイル(キャノピ幅3.7m、ボディ長1m)を用いた。, Today, the parafoil-based system attracts attention as the recovery method of a science observation rocket. In this research, motion of parafoil aiming at recovery in an object fixed point was analyzed. Furthermore, the simulator was created using MATLAB and the simulation was performed about various responses. The numerical data was measured by the small size radio-control parafoil (canopy span of 3.7 m in width, the body of 1 m in length)., 資料番号: AA0045497045

Proposed research project named NOCTARN aims at noise reduction around small airports by using flexible trajectories that are defined by GPS and data link communication system. In the course of the research, functions of the avionics, data-link protocol, operational procedures, airspace design, and functions of ATC console will be investigated and evaluated by conducting flight simulation and flight test., 資料番号: AA0045946002, レポート番号: NAL SP-55

A High-Speed Flight Demonstration (HSFD) program using scaled models is planned as part of NAL/NASDA joint research for the HOPE-X unmanned re-entry vehicle project. The program consists of two phases, and the objective of Phase II is to estimate the transonic aerodynamic characteristics of the HOPE-X configuration. Especially, the base pressure distribution made by the flow behind the base plate, or base flow is watched. The experimental method for Phase II is highly unique: the experiment vehicle is to be lifted to high altitude by a stratospheric balloon, from which it will be released and accelerated in free fall. During data acquisition, the vehicle will fly at a constant Mach number while changing its angle of attack quasi-statically. The aerodynamic data obtained through the flight experiment will be used to reduce the uncertainties in the HOPE-X aerodynamic database, which are greater for the transonic region than for other speed regions, and to contribute reference data to improve wind tunnel testing and CFD (Computational Fluid Dynamics) technologies. In this paper, the concept of data analysis will be stated both from CFD and EFD points of view. The Phase II flight experiment will be conducted by NAL, NASDA and the Centre National d'Etudes Spatiales (CNES) of France in collaboration. The first flight is scheduled for August 2002., 資料番号: AA0032819011, レポート番号: NAL SP-53

Finding CFD/EFD synergism is a critical issue for viable and reliable flight predictions in developing future aerospace vehicles. This paper addresses some problems and strategies towards the unification of CFD/EFD with emphasis being placed on the identification of the meaning of 'EFD for CFD' and 'CFD for EFD'. Joint computational/experimental research programs planned in NAL are also presented., 資料番号: AA0032819018, レポート番号: NAL SP-53

27-28 Sept. 1999 (25th). 27-28 Mar. 2000 (26th), CFD(数値流体力学)手法を用いて自然層流翼に適用することを意図したNALのSST(超音速輸送機)計画に関連して境界層遷移計測を実施した。実験の目的は最先端的な境界層遷移に関するデータベースを構築して翼上の遷移点予測の参考とし、また高度な計測技術を確立して航空機の飛行試験に適用することにある。本論文では、代表的な2つの予備実験の結果を報告した。ひとつはビーチクラフト機を使った飛行試験で、低乱流環境下における遷移過程を把握し、飛行試験の諸課題を明らかにするために実施した。Tollmien-Schlichting波が前縁近傍領域で検出され、スペクトルの振幅分布がSALLY(3次元層流境界層安定性解析)コードを使った数値予測値と非常によく一致したことから、風洞内で行う遷移計測が好結果を得ることが分かった。もうひとつは、超音速風洞内においてSST実験機の半裁模型に対して行った計測である。設計点、すなわち、迎角α=2.7度の時のマッハ数M=2では、層流状態は少なくともX/C=0.5に耐えることが分かった。自然層流翼はSST実験機の飛行試験で実現すると期待されている。, Boundary-layer transition measurements have been conducted associated with the NAL SST (Supersonic Transport) project, which is designed to apply natural laminar flow wing using CFD (Computational Fluid Dynamics) technique. The purpose of experiments is to construct the database on boundary-layer transition most advanced which will be referred to predict the transition point on the wings, and to establish high quality measurement techniques, which will be applied to the flight test of the airplane. In this paper, the results of two typical preliminary experiments are introduced. One is flight tests using Beachcraft airplane, which are performed to grasp the transition process under low disturbance environment and to clarify the problems of flight test. Transition measurement as conducted in wind-tunnel was found to be successful, because Tollmien-Schlichting wave is detected at the region near the leading edge, and its amplitude distribution of the spectrum is in very good agreement with the numerical prediction by SALLY (3D laminar boundary layer stability analysis)-code. Another is the measurement on a half-model of SST experimental airplane in a supersonic wind tunnel. At the design point, i.e. Mach number M = 2 at an angle of attack alpha = 2.7 deg, it is found that the laminar state sustained at least to X/C = 0.5. Natural laminar flow wing is expected to realize on the flight test of SST experimental airplane., 資料番号: AA0028636001, レポート番号: NAL SP-47

航空機の表示画面上に写し出される対象物体の画像は、その物体と航空機との相対位置および姿勢情報を得るために有効で、かつ自律航法システムに不可欠である。ここでは、水平線画像と矩形滑走路の両側平行2直線の画像を使って、空港に対する航空機の相対位置と姿勢を推定する一手法を提案して、さらに飛行実験による評価を実施した。具体的方法としては、入力となる画面へのセンサ情報は、航空機の機首に搭載したカメラにより撮影した着陸時の滑走路画像である。これを画面上で滑走路両側境界線交点の座標および境界線の傾きを求め、航空機の位置および姿勢情報を計算で求める方法を開発した。飛行実験は、Do-228型機を用いて着陸形態で実施し、これを従来のD(差分)GPSやINS航法データと比較した。その結果、姿勢角については、0.2度、位置は、1.5m程度の満足する精度を示したが、さらに、精度向上の可能性について検討する価値がある。, A graphic image on the display in the cockpit of aircraft can be used for providing the pilot with information in respect to the aircraft position and attitude relative to the runway when the aircraft is approaching for landing. This is particularly important for autonomous navigations. In this paper, a method was proposed by photographing the runway with a camera, installed at the cockpit, with a particular attention to the horizontal images and the side lines of the runway strip. Furthermore, validation was made on the accuracy of the method by carrying out the flight tests for landing with a Do-228 aircraft, installing the image processing system. The graphic input for sensor information was provided with the camera, photographing the runway during the approach, the data of which were processed for calculating the cross point coordinates and the gradients of the side lines of the airstrip image into obtaining the aircraft position and attitude relative to the runway. The experimental flights were conducted with Do-228 aircraft during the approach to landing. The data acquired were compared with the other data reference supplied from the conventional landing navigation systems, such as D (Differential) GPS and INS. As a result, the angle of the attitude was turned to be 0.2 deg and the position was 1.5 m each deviated from the conventional system measurements. The accuracy was practically satisfactory, though further improvements could still be valuable to be considered., 資料番号: AA0028656000, レポート番号: NAL TR-1411

スペースプレーン機体下面はスクラムジェットエンジン作動時の予圧縮に使われる。しかしこの予圧縮は、圧力の高くなった機体下面から側方への漏れを生じる。この側方への漏れの効果を調べるために1次元モデルを使ってスクラムジェットのエンジン性能を計算し、またスペースプレーンの飛行シミュレーションによる低軌道へのペイロード計算を行った。シミュレーション計算に先立ち側方への漏れの概要を把握するために、マッハ4風洞においてスクラムジェットインレット模型の実験を行った。機体側方でのインレットに対し角度を持った空気が流入する状態を模擬するために、インレット模型は風洞気流に対し傾けた状態で設置した。実験の結果、気流の傾きはインレット性能にはほとんど影響しないことがわかった。しかし機体側方への漏れ、それに伴なう気流の密度減少のためにインレット流入空気流量は低下した。シミュレーション計算では、機体側方への気流の偏向によるインレット性能の低下は無いと仮定し、流入空気量は機体側方からの膨張波によっと減少させた。その結果、側方からの漏れの影響でエンジン推力は15%減少し、ペイロードは60%減少した。側方からの漏れの防止にはサイドフェンスが有効である。, Pre-compression by the windward surface of the aerospace plane is necessary for scramjet operation. However, this pre-compression causes spillge from the high-pressure windward surface toward the sides of the plane. In rder to examine the effects of this side-spillage, the performance of a scramjet engine was evaluated using a 1-D (one dimensional) flow model, and payload to the low earth orbit estimated using an aerospace plane flight simulation. Prior to the simulation, tests with scramjet inlet models were conducted in a Mach 4 wind tunnel to identify the primary features of the side-spillage to assist in the simulation. The models were inclined from the flow direction to simulate the skewed flow near the side of the plane during side-spillage, and the experiments proved that the aerodynamic performance of the inlet was not affected by the inclination for the entrance Mach number given to the models. However, the mass capture ratio decreased due to reduction in the density of airflow as a results of the expansion. In the numerical estimate, side-spillage was modeled not to reduce the performance of the inlet, but to reduce mass flow to the inlet. The resulting decrease in airflow delivered to the engine due to spillage reduced thrust by 15 percent, while the corresponding payload decreased around 60 percent. Side fences were effective in preventing spillage., 資料番号: AA0028654000, レポート番号: NAL TR-1409T

豪州での小型自動着陸実験(ALFLEX: Automatic Landing Flight Experiment)で、飛行経路の実時間監視のために、トラッキング・レーダが使用された。監視精度向上のための精密な較正を行った後、懸吊飛行試験において、レーザ・トラッカ取得測位データとの比較により、トラッキング・レーダによる測位の精度評価を行った。その結果、実時間監視用として充分な精度であることが確認できた。さらに、自動着陸実験においても測位精度評価を行い、実時間監視が確実に行われていたことを確認した。, ALFLEX (Automatic Landing Flight Experiments) were conducted at Woomera airport in Australia in 1996. In these experiments, an ALFLEX vehicle is lifted by helicopter, released at an altitude of around 1,500 meters and landed on a runway automatically. A tracking radar was employed as a real-time flight path monitor of the vehicle during the experiments. The positioning accuracy of the tracking radar was evaluated by comparing it with that of the laser tracker in the flight tests. In conclusion, it was confirmed that the tracking radar used met the accuracy requirements for a real-time monitor system for ALFLEX., 資料番号: AA0001972000, レポート番号: NAL TM-749

航空宇宙技術研究所では、ドルニエDo228-200型機を母機として、インフライト・シミュレーション機能を持つ実験用航空機MuPAL-αを開発中である。MuPALはMulti Purpose Aviation Laboratory(多目的実証実験機)の略称である。MuPAL-αは、可変安定応答機能を実現するためのフライ・バイ・ワイヤ操縦装置および直接揚力制御装置を整備し、突風応答や機体故障時の運動も含めた様々な航空機の運動を模擬することができる。キャビン内に設置した実験用操縦席は、ディスプレイなどのパイロット・インタフェイスやモーション・キューの影響に対する柔軟な研究環境を提供する。計測システムは、高精度データ計測機能と様々なセンサ・システムに対応できる汎用性を持つ。MuPAL-αは、誘導制御技術の飛行実証、ヒューマン・ファクタに関する研究、航空機搭載用機器の運用評価を始めとする様々な研究課題に貢献することを目指す。本資料では、MuPAL-αの機能および安全性に対する要求、搭載システムの構成、および機能、開発スケジュールなどについて述べる。, National Aerospace Laboratory (NAL) is developing a new in flight simulator named MuPAL-alpha. MuPAL stands for Multi Purpose Aviation Laboratory. MuPAL-alpha is based on a Dornier Do-228. It is equipped with a Fly-By-Wire control system and a Direct Lift Control system to enable variable stability and response capability. MuPAL-alpha can simulate the motion of various types of aircraft, including gust responses and motion in the event of system failures. An experimental cockpit in the cabin provides a flexible environment for research on pilot interfaces and the effects of motion cues. The data acquisition system is characterized by its ability to handle the data from a variety of sensor systems as well as its sensors with a high level of accuracy. MuPAL-alpha is expected to make a major contribution to such areas as flight demonstrations of guidance and control technologies, research on human factors, evaluation of on board equipment and so on. This report deals with the requirements, on board systems and development schedule of MuPAL-alpha., 資料番号: AA0028641000, レポート番号: NAL TM-747