"Airbus" Compression Impact Fixture to AITM 1-0010
CP105079 | "Airbus" Compression After Impact Fixture
Meets AITM 1-0010
Fabricated from stainless steel with hardened end loading plates.
Design conforms to the requirements of AITM 1-0010.
Max. Static Load 150kN (15,000 kgf, 33,000 lbf)
Temperature Range: -75 to +250 °C (-103 to +482 °F)
Specimen Dimensions: 100x150 mm and from 1 to 10 mm thick.
Upper Interface: Requires compression platen diameter 50 mm (2 in) or larger. Lockable spherical seat recommended to ensure parallelism.
Lower interface : Requires compression platen diameter 150 mm (6 in) or larger.
Platens not included.
Includes storage case.
|Hauteur||200 mm (8 in)|
|Masse||15 kg (32 lb)|
|Largeur||220 mm (8.4 in)|
|Capacité||150 kN (33000 lbf)|
|Fixation inférieure||Requires platen 100 mm (4 in) or larger|
|Gamme de températures||-75 to +250°C (-103 to +482°F)|
|Normes d'essais||AITM 1-0010|
|Upper Fitting||Requires platen 50 mm (2 in) or larger|
The “Airbus CAI” fi xture is used to test the impact resistance of carbon and other fi ber-reinforced plastic (CFRP) composite laminates. These materials are prone to great reduction in compressive strength even when the impact load is insuffi cient to cause visible damage. The post-impact compression test is used widely to assess the relative performance of different composite laminates with different fi ber matrix combinations. In the fi rst part of the test the laminates are subjected to low-velocity impact loading simulating tool drops and fl ying debris. Specimens then undergo a compression after impact(CAI) test on an electromechanical or servohydraulic testing machine.
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