Intelligent flight control system software#

However, this method only carries out a weight criterion, while the optimization of the flight control system is a discrete multi-objective optimization problem. Paper analyzes the combinatorial complexity of flight control architecture and introduces an optimization process with the method of branch-and-bound. However, there is no scientific design method or optimization method in the paper. The requirements of the flight control actuation system are analyzed. Paper introduces the working principle of the flight control actuation system and the design experience of Airbus and Boeing. Paper analyzes the application and development of flight control actuator system for large aircraft, and designs a more electrical aircraft flight control system with experience on the basis of summarizing the characteristics of the current classic aircraft flight control actuation system. The more complex composition and the application of various types of actuators make the design of flight control actuation system be an extremely complex work.Īccording to the investigation of this area, most of the researches of the design and optimization of the flight control actuation system are based on the experience of the traditional aircraft models, without exploring design principles. In addition, the technologies of actuators are also developing continuously, , and now the applicable actuators include hydraulic actuator(HA), electro-hydrostatic actuator(EHA) and electro-backup-hydraulic actuator(EBHA). The flight control actuation system has not only a large number of components, but also a large number of combinations. At the same time, the design of flight control actuation system architecture is facing higher challenges. In recent years, the higher demand for the economy and safety promotes the development of more electrical aircraft (MEA) and all electrical aircraft (AEA). The architecture of flight control actuation system is a combination of redundant flight computers, power sources, control surfaces, actuators. The function of actuation system is to control the flight attitude by operating the aircraft aileron, elevator, rudder, flap, slit and spoiler. This method deals with the problem in the design of flight control actuation system.įlight control actuation system with high performance and high reliability is an important guarantee of air safety, which has great significance to the development of large passenger aircraft and transport aircraft. At the same time, the optimal architecture is found in less than 30 minutes among 10 75 candidates, which greatly reduces the design cycle. Compared to the traditional hydraulic architecture, the optimal architecture is more competitive in weight, power and cost. Furthermore, within the paper a case study for A350 flight control actuation system is presented to testify the application of this methodology.

Intelligent flight control system software#

And the design method is implemented in python and a software platform is developed. This study proposes an intelligent design method which has steps of design space exploration of actuation system architectures by constraint satisfaction problem (CSP) method, safety assessment process to exclude unsafety solution, multi-objectives optimization to get Pareto optimal front and comprehensive decision for final architecture via analytic hierarchy process. Therefore, the need for new methodology for actuation system architecture design emerges.

It is impossible to determine optimal architecture by traditional trial-and-error method within acceptable time. The task is to find the combinations of power sources, actuators and computers, which becomes more complex because of the new power sources and actuator types of more electrical aircraft. The design of flight control actuation system is facing major challenge due to the development of more electrical aircraft.