Fire / Flight / Propulsion Control System

One of the most important branch in modern military aircraft development is control system integration. It first been studied by U.S in 1970s and were employed in the 3rd, 4th generation aircraft nowadays, such as F-15, F-16, F-22 aircraft. Domestic research on control integration started in 1990s and mostly limited to theory and digital simulation research while engineering application still not in sight. Control integration can make efficient coupling and information sharing between different systems and improve the overall mission capacity of aircraft. We believe that the tide of control system development are integration, automatization and intelligentization. The future attacking system will be a high performance uninhabited weapon platform which can perform full automated attack with high mission efficiency. The flight control and propulsion system will become a single smart aircraft movement control system which incorporate all kind of control capability of aircraft and was highly integrated with command, control, sensor, navigation and attacking system.With above principles, take domestic and abroad research works as foundation, this paper try to improve the degree of integration and automatization of aircraft based on currently available technology and equipment. The study focus on how to realize auto-flight and auto-attack through the integration of flight control, fire control and propulsion control system, a satisfied result wold be feasible system integration schemas that could improve the mission performance and enhance the aircraft combat automation. Major research in this paper listed as following:1) Design and developing of a hi-fidelity digital simulation/design platform. The fidelity of this platform is an insurance for the practical value of research result. Take advantage of modern software design concepts and developing tools, along with efficient task management and control laws tailor, the system configuration can achieve extraordinary flexibility so that simulation platform and design platform can be integrated into one, and the integration, testing, simulation of different systems can be done on one platform. In this way, the code can be more efficient and the future extension, application and maintenance could be more convenient.2) The study of complex nonlinear system controller design. A hi-fidelity analysis model was built and, a optimization method named Extrem and a nonlinear decoupling method was applied successfully. Optimization method is feasible over various model which is just the need of engineering application. The nonlinear decoupling method applied on full, hi-fidelity aircraft analysis model was unprecedented, many technique, such as disassemble-design, assemble-apply, multi-grade decoupling, were used so that the nonlinear decoupling method can be used on such a complex model. The successful design of a roll angle and overload decoupling controller show that the nonlinear decoupling is a feasible method for engineering application.3) Definition of Input Designer concept for Flight Control System(FCS). A input designer was successfully constructed which can provide a effect almost the same as directly control over aerodynamic control surface through the careful design of inputs of FCS. This input design concept is very important for in-service aircraft upgrade where change of the original PCS is not allowed.4) Definition of a Integrated Aircraft Motion Control System concept. This concept is defined as a solution for the problem that new control capabilities, such as direct force control, are difficult to integrated into old PCS. A Integrated Flight/Propulsion Control (IFPC) theoretical schema was designed based on this concept and a engineering schema was developed after take consideration of currently engineering condition and the requirements of in-service aircraft upgrade. A Auto-Flight System was designed which can achieve accurate flight movement control and increase performance of flight task such as ascend, cruise, te...