Boeing Compression After Impact Fixture to ASTM D-7137M
CP103712 | "Boeing" Compression After Impact Fixture
Meets ASTM D 7137M Standard
For edgewise compression of damaged composite specimens.
Fabricated from stainless steel with hardened end loading plates.
SI Version as detailed in ASTM D 7137M-05.
Temperature Range: -75 to 250 °C (-103 to +482 °F)
Max. Static Load 150kN (15,000 kgf, 33,000 lbf)
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 100 mm (4 in) or larger
Platens not included.
Includes storage case.
|Accessory Height||203 mm (8 in)|
|Accessory Weight||15 kg (32 lb)|
|Accessory Width||356 mm (14 in)|
|Capacity||150 kN (30000 lbf)|
|Lower Fitting||Requires platen 100 mm (4 in) or larger|
|Temperature Rating||-75 to +250 °C (-103 to +482 °F)|
|Testing Standards||ASTM D 7137M|
|Upper Fitting||Requires platen 50 mm (2 in) or larger|
The “Boeing CAI” fixture is used to test the impact resistance of carbon and other fiber-reinforced polymer composite laminates. These materials are prone to great reduction in compressive strength, even when the impact load is insufficient to cause visible damage. The post-impact compression test is used to assess the relative performance of different composite laminates with different fiber matrix combinations. Laminates are subjected to low-velocity impact loading simulating tool drops and flying debris or may be subjected to an out-of-plane static indentation (ASTM D 6264 / D 6264M). Specimens then undergo a compression after impact (CAI) test on an electromechanical or servohydraulic testing machine.
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