1 Introduction
The increasing demand for high-performance and lightweight structures has promoted the application of fiber metal laminates (FML) in the aircraft industry over the last decades. FMLs consist of thin metal layers alternated with composite layers, e.g. ARALL (aramid fiber reinforced aluminum laminate), GLARE (glass fiber reinforced aluminum laminate), and CARALL (carbon fiber reinforced aluminum laminate) [
1]. By using FML, advantageous properties can be achieved and the disadvantages of monolithic materials or structures can be compensated. Thus, high crack propagation resistance [
2], high absorption energy [
3], good corrosion resistance and resistance to flammability [
4] can be achieved [
5]. Important applications can be found in the transportation sector, e.g., in aviation [
6] or increasingly in the automotive sector [
7]. Structural components made of FMLs were initially produced by the autoclave process [
8]. In this process, metal sheets are stacked alternately with the pre-impregnated fibers. These layers are then evacuated, placed in an autoclave and cured under high pressure (0.5–0.6 MPa) and elevated temperature (about 120 °C) [
9]. Only small curvatures, as in an aircraft fuselage, can be realized in an autoclave process [
10]. Various manufacturing processes have been developed to manufacture FML components of higher complexity: (a) by using a resin injection process with an asymmetrical structure [
11]; (b) by using a preimpregnated (prepreg) and a preformed sheet [
12]; (c) by using a semi-finished product consisting of pre-consolidated prepreg and adhering cover sheets [
13]. Due to these usually expensive fabrication processes and low formability, FMLs have not yet become widely used in large-scale production.
The newly developed in-situ hybridization process for the production of FML shows great potential to produce three-dimensional structural components in the car body-in-white in one step with one forming tool [
14]. During the deep drawing of the dry FML, the fabric layers are infiltrated with a reactive thermoplastic matrix system in a thermoplastic resin transfer molding (T-RTM) process. An advantage of the process is the use of inexpensive semi-finished products and a very low viscosity matrix, which allows infiltration of fibers in regions of low cross-section and high fiber volume content [
15]. Due to the low viscosity of the in-situ injected matrix, the fibers are in direct contact with the sheets throughout the forming process [
16]. The permanent contact of fibers and sheet, as well as the higher contact pressures than in the state of the art, lead to reduced formability of the sheets due to friction [
16]. Therefore, the friction between the fabric and the metal sheet has to be investigated specifically.
Usually, Coulomb friction is assumed. However, Howell [
17] found that the coefficient of friction at low contact pressures for fibers is higher than at high contact pressures. Howell cites the contact state at the surface of the friction partners as the reason. At high contact pressures, plastic contact of the surface irregularities occurs, leading to Coulomb's friction equation
which is a special case of the more general relationship
formulated by Bowden and Young in 1951 [
18]. Here,
F is the friction force,
N the normal load,
µ the coulomb friction value and
k,
n curve fitting parameters for non-linear, normal load dependent friction. For contact with entirely plastic deformation of the friction partners,
n = 1 is assumed to be identical to Coulomb's friction equation. For contact with pure elastic deformation of the friction partners
n = 2/3 is valid. Values between
n = 2/3 and
n = 1 indicate the fraction of plastic contact. According to Howell, the contact state of friction partners depends on the real contact area and the yield strength under compression due to the normal load. The coefficient of friction then results from the shear strength of the welded surface irregularities.
Draping dry or impregnated fibers for the manufacturing of fiber-reinforced composites does not require high normal forces in the direction of fabric thickness. Therefore, metal-fabric friction was previously investigated only under low normal forces to characterize the friction behavior between ply and tool. Sachs et al. [
19] summarized different test methods for characterizing dynamic friction between fabrics and metal surfaces, where the maximum contact pressure was
p = 0.16 MPa. In a common test method, a weighted sled is pulled over a test bed to determine the friction between ply/ply or tool/ply [
20]. Another commonly applied test setup uses a plate with fabric attached to it, that is pulled out of or through two pressure plates where the other friction partner is attached to [
21]. Rigidity of the tool is important, as misalignment of the tool due to the friction force can lead to uneven pressure distribution and therefore wrong measurements [
19]. For dry fabrics, the ply/ply and tool/ply friction can usually assumed to be independent of the drawing velocity and normal load [
22]. When infiltrating the fabric with a viscous matrix, friction decreases as the matrix acts as lubrication. Furthermore, the friction behavior becomes dependent on the drawing velocity and normal load when introducing a viscous matrix. With increasing drawing velocities and decreasing normal loads, the friction increases [
23]. Opposing views exist, whether the influence of the drawing velocity or the normal load on the coefficient of friction is higher [
24]. In the forming of FMLs, much higher normal loads than in the fabrication of fiber-reinforced composites are occurring on the interface between metal sheet and fabric. As the normal pressure increases, the area of the fabric in contact with the friction partner increases [
25]. The area increases due to the reorientation of the fibers as a result of the normal pressure. This process-induced pressure thus affects the movement of the fibers in the semi-finished product (e.g. fabric). This is shown by the investigations of Samadi and Robitaille [
26] with a numerical model, to what extent the contact area increases with increasing compaction of the fibers. From initial point contact, the contact area increases due to compaction and results in a higher fiber volume content. Yousaf et al. [
27] state that the increase in area is caused by reorientations and by superimposed fibers sliding into the free spaces. Thus, when pressure is applied in the direction of fabric thickness, the thickness of the fabric decreases.
So far, there is no standardized strategy to measure the friction between sheet metal and dry or infiltrated fabric under high contact pressures, like p = 2 MPa. This article presents the experimental characterization of the friction coefficient using a modified strip drawing test. In this test setup, high contact pressures can be realized. The aim of the investigations is to find friction pairings that reduce friction and thereby increase formability in the in-situ hybridization process.
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