JPS6323598U - - Google Patents

Description

[Brief explanation of the drawing]

Fig. 1 is a schematic block diagram showing an embodiment of this invention, and Fig. 2 is a schematic block diagram of a conventional pitch or yaw autopilot for flying vehicles. is a controller, 3 is a pitch or yaw system steering angle command signal, 4 is a steering servo device, 5 is a steering angle, 6 is an airframe transmission characteristic, 7 is a pitch or yaw system angular velocity and acceleration, 8 is an inertial sensor, 9 is an inertial sensor output, 10 is a variable parameter controller, 11 is an aircraft transfer function parameter identifier, and 12 is a controller parameter calculator. It should be noted that the same or corresponding parts in the figures are indicated by the same reference numerals.

Claims (1)

[Scope of utility model registration request] In a pitch system or yaw system autopilot system for a flying object, there is a variable parameter controller that performs control compensation to achieve desired characteristics, and a rudder angle command signal output from the controller is input to control the steering blades according to the rudder angle command. A steering servo device that controls the steering angle so that it has the same magnitude as the signal, and a pitch of the flying object based on an output having a flying object transmission characteristic using the steering angle of one end of the output of the above-mentioned steering servo device as input. an inertial sensor that detects the angular velocity and acceleration of the system or the yaw system, and an aircraft transfer function parameter identifier that identifies the aircraft transfer function parameter in real time using the other end of the output of the steering servo device and the output of the inertial sensor as input. , and a controller parameter calculator that calculates based on the aircraft transfer function parameters identified by the above-described identifier, forming a closed loop.