Novel Flight Control Devices integrated control surfaces, gurations are under investigation. In the including new technologies, configurations field of active flow control a separation/ circulation control concept is assessed and tive flight control system architectures. for highly dynamic flight control purposes. Since the early 1970s this ‘Coandă flap’ To design efficient flight controls systems concept has been successfully tested with highly integrated flight control sur- faces, under laboratory conditions and it was ture – the flight control system implemented on a few general aviation regarding power systems, actuators and test carriers and unmanned prototypes. others – flight control computers, among For the investigation of the application plays a special role and has to be Illustration of Coandă flap concept potential on modern (unmanned) considered too. Therefore, a tool for the scale aircraft a novel numerical toolset pre-design of flight control system has been developed, combining tectures for a given flight control system fied 2d CFD-models with extrapolation configuration is developed, considering the wings. tion techniques for finite low aspect ratio main functional, safety and Overall system performance is assessed aspects. by including all relevant system interfaces Finally it can be stated, that this and dependencies in a approach flight dynamic simulation implemented in enables new design spaces for flight MATLAB/Simulink combining all submodels The Institute of Aircraft Design has for performance analysis. Trim calculations control systems and the capability of achieved major progress in the and dynamic simulations gave evidence development of efficiency improvements in any phase of for the feasibility in terms of sufficient a tool for a functional driven design the flight. effectiveness of the studied Coandă flap system of In parallel, novel technologies for flight advanced flight control systems. for the given low aspect ratio flying wing control devices on modern agile UAVs Here, advanced flight control systems configuration. consist of multifunctional, or even new concepts of aircraft (AFCS) Research Focus and future analysis n Aircraft design n Analysis & evaluation of aircraft n concepts Competence Szenario technique n Aircraft design (manned/unmanned, n military & civil) Aircraft and system integration and n verification (UAVs, prototypes) Propulsion integration, electrical and n hybrid propulsion systems Operational assessment: noise, airport n capacity, cost Infrastructure Integrated aircraft design environment n Laboratory for demonstrator aircraft n Experimental UAS (e.g. IMPULLS UAV) n Propulsion integration lab n Mission simulation n Airport simulation n
Novel Flight Control Devices Illustration of Coandă flap concept The Institute of Aircraft Design has achieved major progress in the development of a tool for a functional driven design of advanced flight control systems. Here, advanced flight control systems (AFCS) consist of multifunctional, integrated control surfaces, including new technologies, configurations and tive flight control system architectures. To design efficient flight controls systems with highly integrated flight control sur- faces, the flight control system ture – regarding power systems, actuators and flight control computers, among others – plays a special role and has to be considered too. Therefore, a tool for the pre-design of flight control system tectures for a given flight control system configuration is developed, considering the main functional, safety and tion aspects. Finally it can be stated, that this approach enables new design spaces for flight control systems and the capability of efficiency improvements in any phase of the flight. In parallel, novel technologies for flight control devices on modern agile UAVs or even new concepts of aircraft gurations are under investigation. In the field of active flow control a separation/ circulation control concept is assessed for highly dynamic flight control purposes. Since the early 1970s this ‘Coandă flap’ concept has been successfully tested under laboratory conditions and it was implemented on a few general aviation test carriers and unmanned prototypes. For the investigation of the application potential on modern (unmanned) scale aircraft a novel numerical toolset has been developed, combining fied 2d CFD-models with extrapolation techniques for finite low aspect ratio wings. Overall system performance is assessed by including all relevant system interfaces and dependencies in a flight dynamic simulation implemented in MATLAB/Simulink combining all submodels for performance analysis. Trim calculations and dynamic simulations gave evidence for the feasibility in terms of sufficient effectiveness of the studied Coandă flap system for the given low aspect ratio flying wing configuration. Research Focus n and future analysis n Aircraft design n Analysis & evaluation of aircraft concepts Competence n Szenario technique n Aircraft design (manned/unmanned, military & civil) n Aircraft and system integration and verification (UAVs, prototypes) n Propulsion integration, electrical and hybrid propulsion systems n Operational assessment: noise, airport capacity, cost Infrastructure n Integrated aircraft design environment n Laboratory for demonstrator aircraft n Experimental UAS (e.g. IMPULLS UAV) n Propulsion integration lab n Mission simulation n Airport simulation