This paper presents the architecture of flight tracking control system for unmanned autogyro, and designs the control law based on the control characteristics of unmanned autogy-ro. To reduce the lift force loss during turning and maintain the altitude, the feedforward control method of pitching rudder for propeller is adopted (dur-ing rolling); To reduce the influence of propeller anti-twisting effect on the roll attitude and course, feedforward control method of the propeller rolling rudder (during throttle changing is adopted; to reduce the slide slipping and achieve coordinated turning, a hybrid control strategy of the yaw rudder and rolling rudder of propeller is developed. The flying platform is built to verify the flying. It is proved that this control system can effectively control the altitude and horizontal path of the unmanned autogyro, the control accuracy is better than ±5m.

To enhance the propulsion efficiency of near-space high-altitude unmanned aerial vehicle under low-density conditions and to gain a deeper understanding of the aerodynamic characteristics of contra-rotating propellers under complex interference, this study focuses on a high-altitude contra-rotating propeller propulsion system. A systematic investigation is conducted on the influence of design variables and flow characteristics. Considering the distinctive features of high-altitude environments, including low Reynolds numbers, high induced velocity ratios, and strong mutual interference between front and rear rotors, a numerical simulation method for contra-rotating propellers is established. The aerodynamic performance and typical flow structures are analyzed and compared with conventional propeller configurations to elucidate the aerodynamic advantages of contra-rotating propellers. Furthermore, key design variables such as axial distance, pitch angles of the front and rear propellers, and rotational speed matching are systematically examined to assess their effects on aerodynamic characteristics. Comparative analysis of axial velocity distributions reveals the interaction mechanisms between front and rear rotors under different parameter combinations and identifies the dominant factors influencing aerodynamic performance. The results indicate that rational matching of geometric parameters between front and rear rotors can effectively mitigate adverse interference, optimize wake structures, and improve the overall aerodynamic performance of contra-rotating propellers at high altitudes. These findings provide theoretical guidance and engineering references for the aerodynamic design and parameter selection of high-altitude contra-rotating propeller systems.

This article puts forward a new heading system (including heading measurement and heading control) framework of micro air vehicle (MAV) starting from practical application, then designs a plan in which three most popular heading measurement methods, magnetic heading, strapdown heading and GPS heading, are implemented in a mini system, analyzes their strong and weak points one by one, and provides a way to obtain a practical heading based on data fusion. The advantages of this way are appropriately accuracy, little calculation amount, no system model needed, and dynamic online self-calibration. The article also designs a plan for heading control of MAV on the basis of heading measurement, which has been realized in the IFLY30 MGNC (micro guidance, navigation and control) system. IFLY30 is used in the flight control system of a sort of mini fixed wing aircraft. Static and autonomous flight tests prove that the heading system designed in this paper is feasible with excellent performance