JP7454364B2 - 航空機の床に取り付けられる造作物の試験方法 - Google Patents
航空機の床に取り付けられる造作物の試験方法 Download PDFInfo
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- G01M7/00—Vibration-testing of structures; Shock-testing of structures
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- G01M99/00—Subject matter not provided for in other groups of this subclass
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Description
前記航空機(100)の前記床(20)、及び、前記航空機(100)の前記床(20)に造作物(30)が取り付けられる取り付け箇所の、コンプライアンス行列を取得し、
試験造作物(79)における、前記取り付け箇所に対応する取り付け位置に、伸張部材(71)及びロードセル(72)を配置し、
試験期間において、前記試験造作物(79)に試験負荷を徐々に付与し、
前記試験期間において、所定の試験負荷に達するまで、指定された試験頻度で、
前記試験造作物(79)の前記取り付け位置の各々における反応負荷を、ロードセル(72)で測定し、
前記コンプライアンス行列を用いて、前記取り付け位置の各々における前記床(20)の変位を計算し、
前記伸張部材(71)の各々を、対応する前記変位分、調節する、方法。
構造体及び前記構造体に造作物(30)が取り付けられる取り付け箇所のコンプライアンス行列を取得し、その際に、前記構造体は、前記造作物(30)より大きく、
試験造作物(79)における、前記取り付け箇所に対応する取り付け位置に、油圧シリンダ及びロードセル(72)を配置し、
試験期間において、前記試験造作物(79)に試験負荷を付与し、
前記試験期間において、指定された試験頻度で、
前記試験造作物(79)に付与される前記試験負荷を増大させ、
前記試験造作物(79)の前記取り付け位置の各々における反応負荷を、ロードセル(72)で測定し、
前記コンプライアンス行列を用いて、前記取り付け位置の各々における前記構造体の変位を計算し、
前記油圧シリンダの各々を、対応する前記変位分、調節する、方法。
航空機(100)の床(20)、及び、前記航空機(100)の前記床(20)に造作物(30)が取り付けられる取り付け箇所の、コンプライアンス行列を取得するように構成された通信インターフェース回路、及び、
処理回路を含み、前記処理回路は、
前記取り付け箇所に対応する前記試験造作物(79)における取り付け位置における反応負荷を示す信号を受信すること、
前記コンプライアンス行列、及び、前記位置の各々における測定された反応負荷を用いて、前記取り付け位置の各々における、前記床(20)の変位を計算すること、及び、
前記取り付け位置の各々における伸張部材(71)を、対応する前記変位分、調節すること、を行うように構成されている、演算装置。
Claims (15)
- 航空機の床に取り付けられる造作物の試験方法であって、
前記航空機(100)の前記床(20)、及び、前記航空機(100)の前記床(20)に造作物(30)が取り付けられる取り付け箇所の、コンプライアンス行列を取得し、
試験造作物(79)における、前記取り付け箇所に対応する取り付け位置に、伸張部材(71)及びロードセル(72)を配置し、
試験期間において、前記試験造作物(79)に試験負荷を徐々に付与し、
前記試験期間において、所定の試験負荷に達するまで、指定された試験頻度で、
前記試験造作物(79)の前記取り付け位置の各々における反応負荷を、ロードセル(72)で測定し、
前記コンプライアンス行列を用いて、前記取り付け位置の各々における前記床(20)の変位を計算し、
前記伸張部材(71)の各々を、対応する前記変位分、調節する、方法。 - 前記試験期間において、前記取り付け位置における前記反応負荷が所定量を超えたかどうかを判定することをさらに含む、請求項1に記載の方法。
- 前記試験造作物(79)における、前記取り付け箇所に対応する前記取り付け位置に、前記伸張部材(71)及び前記ロードセル(72)を配置することは、前記試験造作物(79)における、前記取り付け箇所に対応する前記取り付け位置に、油圧シリンダ及びロードセル(72)を配置することを含む、請求項1又は2に記載の方法。
- 前記試験造作物(79)における、前記取り付け箇所に対応する前記取り付け位置に、前記伸張部材(71)及び前記ロードセル(72)を配置することは、前記試験造作物(79)における前記取り付け位置の各々に、前記伸張部材(71)のうちの1つ及び前記ロードセル(72)のうちの1つを取り付けることを含む、請求項1~3のいずれか1つに記載の方法。
- 前記取り付け箇所の各々は、前記伸張部材(71)及びロードセル(72)のうちの1つを含む、請求項1~4のいずれか1つに記載の方法。
- 前記コンプライアンス行列を用いて、前記取り付け位置の各々における前記床(20)の前記変位を計算することは、前記取り付け位置の各々における前記変位の間の相互依存性に基づいて、前記床(20)の前記変位を求めることを含む、請求項1~5のいずれか1つに記載の方法。
- 前記試験期間において、前記所定の試験負荷に達するまで、前記指定された試験頻度で、前記伸張部材(71)の各々を、床の大域変位に基づく追加量分、調節することをさらに含む、請求項1~6のいずれか1つに記載の方法。
- 前記造作物(30)は、前記航空機(100)の前記床(20)に取り付けられるように各々が構成されたギャレー又は化粧室のいずれかである、請求項1~7のいずれか1つに記載の方法。
- 支持構造体に取り付けられる造作物の試験方法であって、
構造体及び前記構造体に造作物(30)が取り付けられる取り付け箇所のコンプライアンス行列を取得し、その際に、前記構造体は、前記造作物(30)より大きく、
試験造作物(79)における、前記取り付け箇所に対応する取り付け位置に、油圧シリンダ及びロードセル(72)を配置し、
試験期間において、前記試験造作物(79)に試験負荷を付与し、
前記試験期間において、指定された試験頻度で、
前記試験造作物(79)に付与される前記試験負荷を増大させ、
前記試験造作物(79)の前記取り付け位置の各々における反応負荷を、ロードセル(72)で測定し、
前記コンプライアンス行列を用いて、前記取り付け位置の各々における前記構造体の変位を計算し、
前記油圧シリンダの各々を、対応する前記変位分、調節する、方法。 - 前記試験期間中において、前記取り付け位置における前記反応負荷が所定量を超えたかどうかを判定することをさらに含む、請求項9に記載の方法。
- 前記取り付け箇所の各々は、伸張部材(71)及び前記ロードセル(72)のうちの1つを含む、請求項9又は10に記載の方法。
- 行及び列を有する前記コンプライアンス行列をさらに含み、前記行及び列の各々の数は、前記取り付け箇所の数と等しい、請求項9~11のいずれか1つに記載の方法。
- 前記造作物(30)は、ギャレー又は化粧室のうちの1つであり、前記構造体は、航空機(100)の床(20)である、請求項9~12のいずれか1つに記載の方法。
- 前記コンプライアンス行列を用いて、前記位置の各々における前記構造体の前記変位を計算することは、前記取り付け位置の各々における前記変位の間の相互依存性に基づいて、前記変位を計算することを含む、請求項9~13のいずれか1つに記載の方法。
- 前記試験期間において、前記試験負荷が所定値に達するまで、前記指定された試験頻度で、前記油圧シリンダの各々を、床の大域変位に基づく追加量分、調節することをさらに含む、請求項9~14のいずれか1つに記載の方法。
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US16/210,154 US10633119B1 (en) | 2018-12-05 | 2018-12-05 | Methods of testing a monument that is to be attached to a floor of an aircraft |
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EP3667282A1 (en) | 2020-06-17 |
RU2019139687A (ru) | 2021-06-07 |
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KR20200069248A (ko) | 2020-06-16 |
CA3063867A1 (en) | 2020-06-05 |
CN111268167A (zh) | 2020-06-12 |
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US10633119B1 (en) | 2020-04-28 |
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