4 results about "Flight control modes" patented technology

The invention belongs to the technical field of amphibious aircraft flight control, and discloses an amphibious aircraft fly-by-wire flight control system and a working method, a cockpit control device is connected with and controls a normal instruction sensor and a backup instruction sensor, the normal instruction sensor transmits a signal to an actuator control electron, and the backup instruction sensor transmits a signal to the actuator control electron; the actuator control electronics and the flight control computer transmit signals mutually, the actuator control electronics and the actuator control module transmit signals mutually, and the actuator control electronics further receive signals of the external signal sensor, the direct angular rate sensor, the flap position sensor and the flight control mode switch; the backup command sensor transmits the signal to the backup flight control computer, and the backup flight control computer transmits the signal to the actuator control module; the actuator control module is connected with and controls the actuator, and the angular displacement sensor is arranged on the actuator and transmits collected signals to the actuator control module. The problem that a current fly-by-wire flight control system is not matched with amphibious aircraft cross-medium application is solved.

The application discloses a kind of shunt thrust control coaxial double-paddle aircraft and flight control mode, it is related to aircraft technical field.The application includes: coaxial double-paddle unit and thrust control unit, thrust control unit, the thrust control unit includes thrust chamber and multiple groups of flow regulating mechanism, the thrust chamber is placed below the lower rotor and is connected with the mounting frame, it is circumferentially spaced apart and is provided with multiple through-flow cavities along the axial direction of the upper rotor, multiple groups of flow regulating mechanism are correspondingly installed in multiple the through-flow cavities, to adjust the flight attitude of aircraft by changing the flow area corresponding to the through-flow cavity to adjust the resistance size when airflow passes through each the through-flow cavity to adjust the thrust distribution in thrust chamber.The application combines the advantages of coaxial double-paddle aircraft and multicopter, so that the aircraft can obtain larger paddle radius and lift action area, and has good controllability, maneuverability and stability.

The application discloses a method and system for enabling flight control of a UAV and a computer storage medium, the method comprising: establishing a gas flow model of associated gas combustion; setting basic control parameters according to the gas flow model and releasing the UAV; collecting flow velocity and temperature information of the ascending gas flow through the UAV, monitoring a real-time state of the associated gas combustion; and calibrating the UAV attitude, predicting the ascending gas flow state and selecting a flight control mode according to the flow velocity and temperature information of the ascending gas flow. The application can adjust the flight state according to the real-time collected gas flow field data, and improve the hovering time. The combustion of the associated gas is directly monitored and the surrounding gas is collected to detect the combustion state.