並列タイトル等Calibration of Turbine Flowmeters for Storable Bipropellant Engines
タイトル（掲載誌）航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-1091
一般注記アポジエンジンに用いられる貯蔵性推進薬系の流量の測定精度の要求値は,ノミナル流量値に対して±0.25％である。この要求値を実現するためにタービン式流量計の実液インプレースによる″END-TO-END″較正装置を開発し,較正方法及び較正精度の検討を行った。その結果,流量計の較正精度は要求値の±0.25％以内を満足することが確認された。
Propellant flow rate measurement is one of the most important factors in rocket engine evaluations. In the development of the apogee engine for the engineering test satellite-IV(ETS-IV), the mass flow rate measurement uncertainty requirement for the propellants is less than ±0.25％, thus ensuring the overall uncertainty of the measured specific impulse is less than 1 second. The engine′s propulsion system design adopted a complete blowdown system(blowdown ratio=2:1), thus it is important to ensure the measurement accuracy for a wide range of flow rates, i.e., from about 30-120％ of the minimum flow rate(corresponding to a 0.85 MPa chamber pressure and a mixture ratio of 1.0). To achieve this uncertainty level, an "IN-PLACE/END-TO-END" turbine flowmeter calibration system was developed. The caliblations were conducted with actual propellants under pressures and temperatures similar to those in firing tests, thereby reducing errors caused by variations in fluid physical properties and densities. The characteristics and accuracies of the flow calibration system are described, as well as the method and results of a flow calibration using both hydrazine(N2H4) and nitrozen tetroxide(NTO). The uncertainty of the calibration factors, K-factors(pulse per unit volume), was generally estimated to be within ±0.25％ of the nominal flow rate(185cc/sec for NTO and 265cc/sec for N2H4).
資料番号: NALTR1091000
レポート番号: NAL TR-1091
一次資料へのリンクURLhttps://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=45350&item_no=1&attribute_id=31&file_no=1
連携機関・データベース国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）
提供元機関・データベース宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ