The “Composite Wing New Technology – CTNT” project, funded by the German Federal Ministry of Economic Affairs and Climate Action, aimed to create verification methods for weight‑ and geometry‑optimised composite structural components made from thermoplastic matrix materials. The effort was organised into several work packages covering design guidelines, topology optimisation, manufacturing selection, structural verification strategies, and virtual or hybrid testing approaches. The consortium was led by GROB Aircraft SE, with partners DLR Institute for Fiber Composite Lightweight and Adaptronics, HA‑CO Carbon GmbH, and IMA Materialforschung und Anwendungstechnik GmbH. Work began on 1 June 2021 and was scheduled to run until 31 August 2024, but the project was terminated on 4 August 2022.

Technical progress focused on establishing a generic wing structure in thermoplastic composite form to serve as a test case. Using industry norms, empirical data, and finite‑element simulations, the team defined realistic load profiles for various operating conditions. A Python script was developed to generate typical load sequences, incorporating different load levels and probability of occurrence. A second program translated local interface loads and distributed aerodynamic forces into test‑ready load configurations, laying the groundwork for future simulation‑test comparisons. Although the full validation loop was not completed before the project’s end, these tools provide a reusable framework for rapid load generation and assessment.

A comprehensive requirement catalogue was produced, summarising key design and specification criteria drawn from FAA, MIL‑HDBK, and other regulatory sources. This catalogue serves as a reference for future design and testing of similar composite wing components. The work also produced preliminary results in topology optimisation of the wing box and in selecting suitable manufacturing routes for the target structures. Strategies for structural verification and hybrid testing were outlined, though detailed implementation was curtailed by the project’s early termination.

Collaboration within the consortium was tightly coordinated through regular project meetings and shared documentation. IMA contributed consulting services on test and verification concepts, while GROB Aircraft SE provided overall project leadership. DLR supplied expertise in composite lightweight design, and HA‑CO Carbon GmbH offered manufacturing insights. No external partners beyond the consortium were involved. The project’s early conclusion meant that many planned milestones—particularly the full integration of simulation and test data—remained incomplete. Nonetheless, the deliverables produced, including load‑generation tools and a regulatory requirement framework, represent a solid foundation for future research and development in thermoplastic composite wing structures.