A system of fall back flight control configured for use in electric aircraft includes an input control configured to receive a pilot input and generate a control datum. System includes a flight controller communicatively coupled to the input control and configured to receive the control datum and generate an output datum. The system includes the actuator having a primary mode in which the actuator is configured to move the at least a portion of the electric aircraft as a function of the output datum and a fall back mode in which the actuator is configured to move the at least a portion of the aircraft as a function of the control datum. The actuator configured to receive the control datum, receive the output datum, detect a loss of communication with the flight controller, and select the fall back mode as a function of the detection.

A rotary actuator, including a manifold block and a rotor assembly that includes a rotor shaft and a plurality of arcuate pistons attached to the rotor shaft, each arcuate piston curving at a set radial distance from the rotor shaft, and each piston attached to the rotor shaft via a crank arm. A pressure chamber assembly coupled to the manifold block defines a plurality of piston pressure chambers that receive and at least partially enclose each arcuate piston, including a plurality of gland seals disposed adjacent the entrance of each piston pressure chamber to create a seal between the inner surface of the pressure chamber and the outer surface of the arcuate piston. Each gland seal includes an inner seal that engages the piston surface of the arcuate piston, and plural outer seals that engage the inner surface of the piston pressure chamber, forming a hydraulic seal.

A system of fall back flight control configured for use in electric aircraft includes an input control configured to receive a pilot input and generate a control datum. System includes a flight controller communicatively coupled to the input control and configured to receive the control datum and generate an output datum. The system includes the actuator having a primary mode in which the actuator is configured to move the at least a portion of the electric aircraft as a function of the output datum and a fall back mode in which the actuator is configured to move the at least a portion of the aircraft as a function of the control datum. The actuator configured to receive the control datum, receive the output datum, detect a loss of communication with the flight controller, and select the fall back mode as a function of the detection.

Aircraft fly-by-wire systems and related vehicle electrical systems are provided. A vehicle electrical system includes a bus arrangement having a plurality of buses, a first control module coupled to a first subset of the buses, a second control module coupled to a second subset of the buses, and a third control module coupled to a third subset of the buses. The first subset includes a first bus, a second bus, a third bus, and a fourth bus, the second subset includes the third bus, the fourth bus, a fifth bus, and a sixth bus, and the third subset includes the first bus, the second bus, the fifth bus and the sixth bus.

A system for distributed control of an aircraft. The system includes a plurality of flight components, an aircraft control located within the aircraft, and an aircraft component attached to a flight component of the plurality of flight components. The aircraft component is configured to receive, from a command sensor attached to the aircraft control, an aircraft command, obtain, from an attitude sensor, an aircraft orientation, and command the flight component to produce a response command.

The invention relates to a force application device for a control stick of an aircraft, said stick comprising a control lever that is connected to a motor comprising a drive shaft, said device having: a first pin connected to the drive shaft, a housing, a second pin secured to the housing, an electromagnet secured in relation to the housing, a movable actuator which comprises a magnetic material such that said actuator can be displaced depending on a supply of current of the electromagnet, and means for clamping the first pin and the second pin which comprise a first tooth and a second tooth, said device having an operating configuration in which the electromagnet is active and the actuator separates the teeth away from the first pin and the second pin, and a blocking configuration in which the electromagnet is inactive, with the first tooth and the second tooth coming into contact with the first pin and the second pin.

An electromechanical rudder system control using electromagnetic actuators provides dual redundancy to comply with safety demands. Diversity of possible interconnection distribution allows the manufacturer to choose the proper configuration to satisfy aircraft safety design, hardware savings and overall system quality improvements.

Aircraft fly-by-wire systems and related vehicle electrical systems are provided. In one embodiment, an electrical system suitable for use with a control surface of a vehicle, such as an aircraft, is provided. The electrical system includes a plurality of communications buses and a plurality of control modules, wherein each of the plurality of control modules is connected to a respective subset of the plurality of communications buses that is unique among the plurality of control modules, and a plurality of actuation control modules associated with the control surface, wherein each of the plurality of actuation control modules is connected to a respective subset of the plurality of communications buses that is unique among the plurality of actuation control modules. Thus, each of the control modules is isolated from at least one of the communications buses.

A manual brake override system includes a gear system, an electric motor in operative communication with the input of the gear system, a holding brake in operative communication with the input of the gear system. The holding brake is configured to prevent movement within the gear system when engaged. A manual handwind is provided in operative communication with the input of the gear system and the manual handwind and holding brake are configured such that the input of the gear system can be driven, with the manual handwind, whilst the holding brake is engaged.

A system includes a computing system and a cable connector. The computing system includes a plurality of processors and an interconnect circuit configured to connect the plurality of processors to each other. The cable connector is configured to connect to the interconnect circuit and provide a channel identifier to the computing system, and the interconnect circuit is configured to set one of the plurality of processors as a system controller based on the channel identifier.