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Japan Aerospace Exploration Agency (JAXA) developed Tuned Dry Gyroscope (TDG), as supreme precision rate sensor for satellite attitude control. JAXA also developed Inertial Reference Unit (IRU) using TDG. This IRU is used on every JAXA satellite. It has passed over fifteen years since the development. It is difficult to purchase some kind of electronics parts nowadays. Meanwhile, satellite system requires higher accuracy, more operation flexibility and so on. So, we decided to redesign IRU. Aiming is high-reliability and high-accuracy. The study has started in FY2001. In FY2005 IRU redesign was completed and we prepared every document needed for Flight Model (FM) production., 資料番号: AA0049500078, レポート番号: JAXA-SP-06-006

Aiming for the application to the future spacecraft attitude control system, we are studying the high performance Fiber Optic Gyro Inertial Reference Unit (FOG-IRU). To fulfill the requirements of low noise, stable bias and stable scale factor, we adopt the high power Fiber Light Source, a long fiber coil (several kilo-meters) and the digital serrodyne closed loop configuration. This paper outlines the result of our FOG-IRU development during FY16 such as evaluation of the FOG Pre-EM model, evaluation of the temperature characteristics of the Pre-EM model, evaluation for the optical error factor, designs and re-fabrication for the performance improvement, and evaluation of the Pre-EM re-fabrication model., 資料番号: AA0049054047, レポート番号: JAXA-SP-05-008

Japan Aerospace Exploration Agency (JAXA), formerly named as National Space Development Agency (NASDA), developed Tuned Dry Gyroscope (TDG), as supreme precision rate sensor for satellite attitude control. JAXA also developed Inertial Reference Unit (IRU) using TDG. This IRU is used on almost every JAXA satellite. It has passed about fifteen years since the development. It is difficult to purchase some kind of electronics parts nowadays. Meanwhile, satellite system requires higher accuracy, more operation flexibility and so on. So, we decided to redesign IRU. Aiming is high-reliability and high-accuracy. The study has started in FY 2001. In FY 2003 IRU redesign was completed and we prepared every document needed. In FY 2004, we built an Engineering Model and qualify its function and performance. In FY 2005, we will complete this study., 資料番号: AA0049054051, レポート番号: JAXA-SP-05-008

本稿は、ファンジェットSTOL(短距離離着陸)実験機(飛鳥)用に開発されたHUD(ヘッドアップディスプレイ)およびIRU(慣性基準装置)を航空宇宙技術研究所(NAL)所有のビーチクラフト65型クインエア実験用航空機に搭載して、HUDの有効性、ならびにIRUを飛行制御、計測のセンサとして用いるための精度、特性を評価するために行った飛行評価試験についてまとめたものである。この評価試験を通じて確認されたことは以下の通りである。(1)HUDが着陸時の飛行援助装置として有効である。(2)HUDが飛行試験の遂行においても有効である。(3)IRUは実環境下において認定基準を満足する性能を有する。また、今後の新しい航空機へのHUD、IRUの適用面においては、以下の点で有用なデータを提供した。(4)HUDを搭載する航空機のための基本的な飛行試験技術を確立した。(5)IRUの実機搭載による性能評価法を確立した。(6)レーダガイダンスなどと組み合わせたHUDによる新しい計器着陸技術の可能性を明らかにした。, A Head-Up Display (HUD) and an Inertial Reference Unit (IRU) were developed by the National Aerospace Laboratory (NAL) for the NAL QSTOL (Quiet Short Take Off and Landing) experimental aircraft (Aska). Flight tests were conducted in the B-65 Queen Air, and the performance of the HUD which provides the pilot with landing aid information, and the accuracy and characteristics of the IRU to be used for flight control and measurements were evaluated. The results indicated that the HUD accuracy and characteristics of the HUD as an approach and landing aid system were good, and also that the IRU was useful as a sensor for flight control and measurements. Furthermore, methods of evaluating HUD characteristics and IRU accuracy in-flight are discussed., 資料番号: AA0004146000, レポート番号: NAL TM-658