Abstract: A system of an electric aircraft with pitch control using an elevator is presented. In some embodiments, the electric aircraft may include an elevator configured to deflect. In some embodiments, the electric aircraft may further include a lift lever configured to generate a lift command upon activation by a pilot. In some embodiments, the electric aircraft may further include a flight controller communicatively connected with the lift lever and the elevator, wherein the flight controller is configured to receive the lift command from the lift lever and adjust the elevator as a function of the lift command.

Abstract: A system and method for management of propulsors for an electric aircraft, where the electric aircraft is configured to transition between a hover state and a fixed-wing flight state. The electric aircraft may include at least one set of a plurality of propulsors coupled to the electric aircraft. A flight controller may be coupled to the electric aircraft and configured to detect a state transition of the electric aircraft from the hover state to the fixed-wing flight state and send a parking command to the at least one set of a plurality of propulsors.

Abstract: An electric aircraft for generating a yaw force includes a fuselage, a plurality of laterally extending elements secured to the fuselage, a plurality of lift components attached to the plurality of laterally extending elements, and at least a longitudinal thrust component attached to the plurality of laterally extending elements, wherein the longitudinal thrust component is configured to generate a yaw force.

Abstract: An electrical propulsor motor may include a stator having a hollow cylinder with an inner cylindrical surface and an outer cylindrical surface, rotor incorporated in a hub of a propulsor and mounted to the stator, including a first cylindrical surface facing the inner cylindrical surface, where the inner cylindrical surface and first cylindrical surface form a first air gap, a second cylindrical surface facing the outer cylindrical surface, wherein the outer cylindrical surface and the second cylindrical surface form a second air gap, and a plurality of axial impeller vanes mounted to at least one of the first cylindrical surface and the second cylindrical surface and within at least one of the first air gap and the second air gap and positioned to force air through the at least one of the first air gap and the second air gap when the rotor rotates about the axis of rotation.

Abstract: A selectively deployable heated propulsor system which may be integrated into vehicles, airplanes, or any other machinery configured for flight. The system includes a structural feature that includes a mounted propulsor including a rotor and a motor mechanically coupled to the rotor allowing the rotor to rotate when in an activated mode. The mounted propulsor includes a chamber configured to support a first configuration where the propulsor and the rotor are stowed and heated in an enclosed environment, and a second configuration where the rotor is deployed.

Abstract: An electrical propulsor motor includes a stator having a hollow cylinder with an inner cylindrical surface and an outer cylindrical surface, rotor incorporated in a hub of a propulsor and mounted to the stator, including a first cylindrical surface facing the inner cylindrical surface, where the inner cylindrical surface and first cylindrical surface form a first air gap, a second cylindrical surface facing the outer cylindrical surface, wherein the outer cylindrical surface and the second cylindrical surface form a second air gap, and a plurality of axial impeller vanes mounted to at least one of the first cylindrical surface and the second cylindrical surface and within at least one of the first air gap and the second air gap and positioned to force air through the at least one of the first air gap and the second air gap when the rotor rotates about the axis of rotation.

Abstract: Aspects relate to systems and methods for orienting a thrust propulsor in response to a failure event of a vertical take-off and landing (VTOL) aircraft. An exemplary system includes a plurality of lift propulsors mechanically connected to a VTOL aircraft, wherein each of the plurality of lift propulsors are configured to produce lift, a plurality of sensors, wherein at least a sensor is configured to detect a failure of at least a lift propulsor, and transmit a failure datum, a thrust propulsor mechanically attached to the VTOL aircraft with an orientable joint, wherein the thrust propulsor is configured to produce thrust and orient the thrust propulsor as a function of a thrust orientation datum, and a flight controller configured to receive the failure datum, generate a thrust orientation datum as a function of the failure datum, and transmit the thrust orientation datum to the orientable joint.

Abstract: Aspects relate to systems and methods for orienting a thrust propulsor in response to a failure event of a vertical take-off and landing (VTOL) aircraft. An exemplary system includes a plurality of lift propulsors mechanically connected to a VTOL aircraft, wherein each of the plurality of lift propulsors are configured to produce lift, a plurality of sensors, wherein at least a sensor is configured to detect a failure of at least a lift propulsor, and transmit a failure datum, a thrust propulsor mechanically attached to the VTOL aircraft with an orientable joint, wherein the thrust propulsor is configured to produce thrust and orient the thrust propulsor as a function of a thrust orientation datum, and a flight controller configured to receive the failure datum, generate a thrust orientation datum as a function of the failure datum, and transmit the thrust orientation datum to the orientable joint.

Abstract: An electric aircraft for generating a yaw force includes a fuselage, a plurality of laterally extending elements secured to the fuselage, a plurality of lift components attached to the plurality of laterally extending elements, and at least a longitudinal thrust component attached to the plurality of laterally extending elements, wherein the longitudinal thrust component is configured to generate a yaw force.

Abstract: A system and method for management of propulsors for an electric aircraft, where the electric aircraft is configured to transition between a hover state and a fixed-wing flight state. The electric aircraft may include at least one set of a plurality of propulsors coupled to the electric aircraft. A flight controller may be coupled to the electric aircraft and configured to detect a state transition of the electric aircraft from the hover state to the fixed-wing flight state and send a parking command to the at least one set of a plurality of propulsors.

Abstract: An aircraft for vectoring a plurality of propulsors includes a longitudinal component attached to a fuselage, a plurality of downward directed propulsors attached to a plurality of laterally extending elements secured to the fuselage, a sensor attached to the plurality of downward directed propulsors, a flight controller, wherein the flight controller is configured to receive a flight datum as a function of the sensor, and vector the plurality of downward directed propulsors along a boom axis as a function of the flight datum.

Abstract: A system for airspeed estimation utilizing propulsor data in electric vertical takeoff and landing (eVTOL) aircraft is provided. The system generally comprises at least a propulsor, at least one sensor and a flight controller. The at least a propulsor is mechanically coupled to a body of an eVTOL aircraft, wherein the at least a propulsor is configured to propel the eVTOL aircraft. The at least one sensor is configured to detect a torque of the at least a propulsor, and transmit the torque of the at least a propulsor. The flight controller is configured to receive the torque of the at least a propulsor and determine an airspeed of the eVTOL aircraft as a function of the torque of the at least a propulsor. A method for airspeed estimation utilizing propulsor data in electric vertical takeoff and landing (eVTOL) aircraft is also provided.

Abstract: An integrated electric propulsion assembly includes a stator including at least a first magnetic element generating first magnetic field. The assembly includes a propulsor with an integrated rotor, the propulsor further including a hub rotatably mounted to the stator and at least a second magnetic element affixed to the hub, the at least a second magnetic element generating a second magnetic field. At least one of the first magnetic field and the second magnetic field varies with respect to time, wherein the varied magnetic field includes generating a magnetic force between the at least a first magnetic element and the at least a second magnetic element, and the magnetic force causes the hub to rotate with respect to the stator.

Abstract: In an aspect a system for loading and securing a payload in an electrical vertical take-off and landing (eVTOL) aircraft may comprise a fuselage further comprising structural elements configured to provide physical support for the aircraft fuselage. An eVTOL aircraft may also comprise a swing nose, where a portion of the nose of the aircraft may swing on a hinge in a radial direction orthogonal to the longitudinal axis of the aircraft. The hinge may be coupled to at least a portion of the fuselage and at least a portion of the nose of the aircraft. A latching mechanism may be configured to secure a payload in an aircraft fuselage. A conveyor mechanism may be configured to transport a payload into the fuselage from the opening of the aircraft.

Abstract: A system for propulsion management of an electric aircraft. The system includes an electric aircraft that is configured to transition between a hover state and a fixed-wing flight state. The electric aircraft includes at least one set of a plurality of propulsors that are coupled to the electric aircraft. The system includes a flight controller that is coupled to the electric aircraft. The flight controller is configured to detect a state transition of the electric aircraft from the hover state to the fixed-wing flight state. The flight controller is configured to send a parking or unparking command to the at least one set of a plurality of propulsors to reduce air drag.

Abstract: Aspects relate to systems and methods for orienting a thrust propulsor in response to a failure event of a vertical take-off and landing (VTOL) aircraft. An exemplary system includes a plurality of lift propulsors mechanically connected to a VTOL aircraft, wherein each of the plurality of lift propulsors are configured to produce lift, a plurality of sensors, wherein at least a sensor is configured to detect a failure of at least a lift propulsor, and transmit a failure datum, a thrust propulsor mechanically attached to the VTOL aircraft with an orientable joint, wherein the thrust propulsor is configured to produce thrust and orient the thrust propulsor as a function of a thrust orientation datum, and a flight controller configured to receive the failure datum, generate a thrust orientation datum as a function of the failure datum, and transmit the thrust orientation datum to the orientable joint.

Abstract: A selectively deployable heated propulsor system which may be integrated into vehicles, airplanes, or any other machinery configured for flight. The system includes a structural feature that includes a mounted propulsor including a rotor and a motor mechanically coupled to the rotor allowing the rotor to rotate when in an activated mode. The mounted propulsor includes a chamber configured to support a first configuration where the propulsor and the rotor are stowed and heated in an enclosed environment, and a second configuration where the rotor is deployed.

Abstract: A selectively deployable heated propulsor system which may be integrated into vehicles, airplanes, or any other machinery configured for flight. The system includes a structural feature that includes a mounted propulsor including a rotor and a motor mechanically coupled to the rotor allowing the rotor to rotate when in an activated mode. The mounted propulsor includes a chamber configured to support a first configuration where the propulsor and the rotor are stowed and heated in an enclosed environment, and a second configuration where the rotor is deployed.

Abstract: A gimbal stabilizing system for an aircraft having an airframe is disclosed. The gimbal stabilizing system may comprise a gimbal apparatus having at least one gimbal actuator to adjust a position of the gimbal apparatus about an axis, wherein the gimbal apparatus is positioned on the airframe, an angular acceleration apparatus positioned on the airframe to generate an angular acceleration signal reflecting an angular acceleration of the airframe, and a gimbal controller operatively coupled to each of said angular acceleration apparatus and said gimbal apparatus. The gimbal controller may be configured to generate a gimbal control signal to compensate for the angular acceleration of the airframe based at least in part on a feedback control loop and a feedforward control loop, the feedforward control loop having the angular acceleration signal as an input thereto.

Abstract: An aerial vehicle comprising an airframe, an aircraft flight controller to provide an output control signal, and a planar printed circuit board positioned on the airframe. The printed circuit board may include coupled thereto a processor, a rate gyroscope, and at least three accelerometers. The processor is configured to generate an actuation signal based at least in part on a feedback signal received from at least one of said rate gyroscope and the at least three accelerometers. The processor communicates the actuation signal to said aircraft flight controller, which is configured to adjust the output control signal based on said actuation signal.