The Composite Tool Design Technologies of Aircraft Composite Parts in Autoclave Forming

Ying Guang Li; C.Y. Fu; D.S. Li; S.M. Wan

doi:10.4028/www.scientific.net/AMR.426.330

Paper Titles

Structure Design and Simulation of Viscometer Based on Velocity Attenuation
p.313

Study on the Life of High Speed Steel Taps with Cryogenic Treatment
p.317

Surface Integrity Analysis on High Speed End Milling of 7075 Aluminum Alloy
p.321

Surface Residual Stress Analysis Based on the Molecular Dynamics on Micro/Nano Scale
p.325

The Composite Tool Design Technologies of Aircraft Composite Parts in Autoclave Forming
p.330

Tooth Profile Modification of Sprocket in Dual Meshing Silent Chain
p.335

Wear Behavior of Carbide Inserts in Face Milling TA19 Alloy
p.339

Wear Behavior of PCBN Tool in High Speed Turning TC4
p.344

A Method for Enhancing the Accuracy of On-Machine Inspection for Five-Axis CNC Machines
p.351

HomeAdvanced Materials ResearchAdvanced Materials Research Vol. 426The Composite Tool Design Technologies of Aircraft...

The Composite Tool Design Technologies of Aircraft Composite Parts in Autoclave Forming

Abstract:

Aiming at the problems of composites of anisotropic, poor in dimensional and uneven temperature field in the designing of composite tool in autoclave, the techniques of designing the composite tool of aircraft components were constructed, involving in the following aspects: Taking advantage of design flexibility of composites, the thermal expansion coefficient between the moulding board and composite components matched. By analyzing the cure process curve of fiber-reinforced composites, the result that the crisis point without stress between component and tool, which the shape of composite component decided was concluded. By the temperature field analysis, and contrasted with the experimental results, the maximum difference was 4.95°C，after analysis, optimized the structure of the tool, obtaining the relatively uniform temperature field of the board.