The Curtis Protocol, an aircraft control interface, is provided. The Curtis Protocol standardizes the division and selection of aircraft flight regimes and flight modes within the selected flight regime.

In an aspect of the present disclosure is a system for in-flight re-routing of an electric aircraft including a battery pack configured to provide electrical power to the electric aircraft; a sensor configured to detect at least a temperature metric of the battery pack and generate a temperature datum based on the at least a temperature metric; a controller communicatively connected to the sensor, the controller configured to: receive the temperature datum from the sensor; and re-route the electric aircraft based on the temperature datum.

A power control unit includes power modules, and a positive bus bar connected to positive connection terminals disposed on connection surfaces provided on the power modules. The positive bus bar includes power module connection portions connected to the respective positive connection terminals and extending in the X direction, and standing portions extending along the power module connection portions and standing from the respective power module connection portions.

A magnetic locking system and methods for restricting movement of an electric aircraft motor is provided. A locking system may include a magnetic lock, which includes a first magnetic component and a second magnetic component. First and second magnetic components may be configured to attract each other and thus lock rotor in a certain position. The first or second magnetic component may include an electromagnet so that magnetic lock may be engaged or disengaged based on one or more parameters, such as a detection by a sensor or a signal generated by a controller.

Provided is a process that includes: obtaining, using one or more surface tension sensors, one or more surface tension measurements of a surface, determining a reaction force for an aircraft using the one or more surface tension measurements and a weight of the aircraft. The process includes causing one or more engines included in the aircraft to generate thrust based on the reaction force.

An input attitude associated with an input device of an aircraft is received. A supplemental attitude is generated, including by selecting a position-based supplemental attitude to be the supplemental attitude in the event the input device is in a disengaged state and selecting a velocity-based supplemental attitude to be the supplemental attitude in the event the input device is in an engaged state. The input attitude and the supplemental attitude are combined in order to obtain a combined attitude. The aircraft is controlled using the combined attitude.

A door roller mechanism for cooperation with a roller track including a carriage member having a door attachment feature; at least one roller disposed for rotation on a first side of the carriage member when the carriage member moves in the rolling direction; at least one roller disposed for rotation on an opposite second side of the carriage member when the carriage member moves in the rolling direction; a first rub member disposed on the first side of the carriage; a second rub member disposed on the second side of the carriage; and at least one biasing element disposed on the carriage member for resiliently biasing the first rub member and the second rub member in opposite lateral directions so as to contact a respective first track surface and a second track surface in a manner to dampen lateral vibration of a door connected to the roller mechanism.

A door track assembly for cooperation with a door roller mechanism, including a housing having a longitudinal channel along a length of the housing, wherein the channel descends at an end of the housing to form a stowage recess for the door roller mechanism, and a first track and a second track that are disposed on the housing along a length of the channel and that descend into the stowage recess and along which the door roller mechanism traverses.

An apparatus for determining a movement direction of a component of a mechanism. The apparatus includes an acoustic emission sensor arranged to detect acoustic emission from the mechanism, and a processor arranged to determine a Doppler shift in a frequency characteristic of the measured acoustic emission and to determine a movement direction of a component of the mechanism on the basis of the determined Doppler shift. A method of determining a movement direction of a component of a mechanism including detecting acoustic emission from the mechanism and determining a Doppler shift in a frequency characteristic of the measured acoustic emission and, determining, based on the Doppler shift in the frequency characteristic, a movement direction of the component of the mechanism.

Embodiments of the present disclosure provide a blade-stator system and the vertical take-off and landing flight apparatus comprising the blade-stator system, the blade-stator system including a duct disposed inside a flight body, upper and lower sides of the duct being open, and an inside of the duct being hollow; a blade assembly installed rotatably inside the duct and including a blade body of which an angle is changeable; a stator assembly connected to the blade assembly and the duct, supporting the blade assembly, and rotatable by a predetermined angle; a controller electrically connected to the blade assembly and the stator assembly and configured to control driving of the blade body and the stator assembly, wherein the angle of the stator assembly is changed in response to receiving an electrical signal from the controller so as to be interlocked with a change of the angle of the blade body.