Composite materials, with their specific load adaptable properties, and their high degree of integration in terms of one-shot manufacturing and function integration. Grid structures seem to combine all these advantages. In this dissertation, an Anisogrid structure concept is developed, analysed and tested under consideration of the requirements for civil primary airframe structures. The developed Anisogrid structure concept consists of intersecting integral manufactured ribs with different orientations (helical, circumferential), a load-bearing skin and a special interface, connecting the grid structure and the skin. The manufacturing approach is based on prepreg material under consideration of full automation and high-quality assurance demands (Advanced Fibre Placement). In order to overcome the lack of available material properties in the special intersecting rib design, static compression and tension tests are performed and analysed to characterise the stiffness and strength properties as well as basic structural failure behaviour. In the next step, the triangular stiffened grid architecture is compared to the conventional rectangular stiffened structure in terms of minimum weight on panel level. In this structural- mechanical investigation, the focus is deliberately placed on the isolated effect of the skew of the stiffeners and performed under uniaxial compression, pure shear and the combination of both. Subsequently, the observed different buckling behaviour and the functionality of interface layers between the skin and the grid are validated by means of a compression panel test. With these test results, a perspective for this integral structural design concept is presented considering a specific further development step.