Fuselage panel combined load test device

The invention relates to an aircraft fuselage panel test device, in particular to a fuselage panel combined load test device. The fuselage panel combined load test device comprises an axial load applying assembly (100), a shear load applying assembly (200), an air pressure and circumferential load b...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser:	DENG FANCHEN, CHEN LIMIN, LI CHONG, CHEN XIANGMING, CHAI YA'NAN
Format:	Patent
Sprache:	eng
Schlagworte:	INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIRCHEMICAL OR PHYSICAL PROPERTIES MEASURING PHYSICS TESTING
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Beschreibung
Zusammenfassung:	The invention relates to an aircraft fuselage panel test device, in particular to a fuselage panel combined load test device. The fuselage panel combined load test device comprises an axial load applying assembly (100), a shear load applying assembly (200), an air pressure and circumferential load balance assembly (300) and a counterweight assembly (400), wherein single load can be applied among the assemblies, and the assemblies can be freely combined to apply load. Stretching/compressing, shearing and airtight load can be applied to a fuselage panel at the same time for static force and fatigue experiments, and static force, fatigue and damage tolerance tests related to the fuselage panel can be performed, so that the design level is promoted, and the design period is shortened.