Liebherr-International has filed a patent for control electronics designed for an electromechanical actuator in an aircraft’s primary flight control system. The control electronics can connect an electric motor to an electrical or electronic load and can also deactivate a DC/DC converter that supplies power to the motor. The invention also includes a method for damping the movement of the actuator. GlobalData’s report on Liebherr-International gives a 360-degree view of the company including its patenting strategy. Buy the report here.
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According to GlobalData’s company profile, Liebherr-International's grant share as of September 2023 was 46%. Grant share is based on the ratio of number of grants to total number of patents.
Control electronics for an aircraft's primary flight control system
The filed patent (Publication Number: US20230318513A1) describes control electronics for an electromechanical actuator, specifically designed for use in a primary flight control system of an aircraft. The control electronics are configured to connect an electric motor to an electrical or electronic load and can deactivate a DC/DC converter that supplies power to the motor.
The control electronics also include detection means for detecting the counter voltage of the electric motor. Additionally, the control electronics can be activated in the event of an electrical failure or loss of supply voltage.
The patent also covers an electromechanical actuator that incorporates the control electronics described in claim 1. This actuator is intended for use in the primary flight control system of an aircraft.
Furthermore, the patent mentions an aircraft that includes a primary flight controller formed with the electromechanical actuator described in claim 7.
The patent also discloses a method for damping the movement of the electromechanical actuator. This method involves activating the control electronics in the event of an electrical failure or loss of supply voltage, and switching the phases of the electric motor to an electrical or electronic load. It also includes deactivating the DC/DC converter that supplies power to the motor.
Claims 10-20 of the patent describe variations of the control electronics, emphasizing their ability to be activated in the event of an electrical failure or loss of supply voltage. These claims highlight different combinations of features, such as the control electronics being supplied with the counter voltage of the electric motor, or only the counter voltage or no voltage being applied to the control electronics.
In summary, the filed patent describes control electronics for an electromechanical actuator used in the primary flight control system of an aircraft. These electronics have various features, including the ability to connect the electric motor to an electrical or electronic load, deactivate a DC/DC converter, and be activated in the event of electrical failure or loss of supply voltage. The patent also covers the electromechanical actuator itself, an aircraft incorporating the actuator, and a method for damping the actuator's movement.
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GlobalData, the leading provider of industry intelligence, provided the underlying data, research, and analysis used to produce this article.
GlobalData Patent Analytics tracks bibliographic data, legal events data, point in time patent ownerships, and backward and forward citations from global patenting offices. Textual analysis and official patent classifications are used to group patents into key thematic areas and link them to specific companies across the world’s largest industries.
