An Independent Flying Control System Applied for Unmanned Air Vehicle

摘要

With the advent of the Future Combat System and the 'system of systems' approach to development of a deployable and lethal medium force, unmanned systems are viewed as essential contributors to provide the necessary capabilities while at the same time improving soldier survivability. One of the most critical missions for Unmanned Air Vehicle (UAV) is Reconnaissance, Surveillance, and Target Acquisition (RSTA). The systems must, however, be designed to be affordable to enable aggressive use that may result in loss or damage during operations. Advances in sensors, micro-machine perception, and advanced computer architectures have made an autonomous UAV a reality. Otherwise the expansion of the roles for UAV also has demonstrated a need for increasingly sophisticated navigation and guidance reference equipment. Because total avionics weight, size and power are critical for UAV, the desire is to use a single unit to meet all navigation and guidance (N-G) needs. An overview of an integral N-G system now in researching at Tsinghua Univ. is presented. It is small, low-power, lightweight, fast response and excellent control performances. The navigation subsystem is a micro-attitude-detector based on micro-electromechanical system (MEMS), which is composed of micro-polysilicon accelerometers and magnetometers. The subsequent guidance is in fact a flight control system, which provides the autonomy necessary to meet mission requirements and to maintain around-the-clock reliability according to the reference attitude. A fuzzy logic is exploited in the flight control system to provide a robust solution to the control of the aircraft's dynamic, nonlinear system. Straightforward, common sense fuzzy rules governing flight are processed instead of complex mathematical models. This has resulted in a simplified solution to the complexities of flight. Incorporation of fuzzy logic not only reduced the cost of development and should also reduce the cost of maintenance of the system. It possesses, also, significant adaptive properties. The general approach is demonstrated by solving a real-life roll control problem. Results of simulation and flight tests are presented.