The invention provides an electromechanical servo system with a simple attitude control function. The electromechanical servo system comprises an electromechanical actuator, a servo control driver, a servo power source and a power source converter, the servo control driver is used for receiving a control instruction sent by a central control system of an aircraft and driving the electromechanical actuator, the servo power source powers the whole electromechanical servo system, and the power source converter is used for converting high-voltage direct current of the servo power source to acquire conversion control current for controlling the servo control driver after the servo control driver is separated from the central control system of the aircraft. By arranging the power source converter, after being separated from the central control system of the aircraft, the power source converter converts the high-voltage direct current of the servo power source to acquire the conversion control current for controlling the servo control driver to enable the electromechanical servo system to continue working, an engine after separation is pushed to deviate for a certain angle, and the aircraft on an upper layer is prevented from being chased and attacked.
Electromechanical servo system with simple attitude control function and aircraft
2015-05-20
Patent
Elektronische Ressource
Englisch
SERVO-ACTUATOR ARCHITECTURE WITH ELECTROMECHANICAL-STABILITY AND CONTROL AUGMENTATION SYSTEM
Europäisches Patentamt | 2021
|Europäisches Patentamt | 2022
|SERVO-ACTUATOR ARCHITECTURE WITH ELECTROMECHANICAL-STABILITY AND CONTROL AUGMENTATION SYSTEM
Europäisches Patentamt | 2023
|Servo-actuator architecture with electromechanical-stability and control augmentation system
Europäisches Patentamt | 2023
|