A control system for a multi-rotor aircraft is described that results in lower operating noise. Allowing blades to flap during flight reduces aerodynamic interference as blades pass by other aircraft components, such as wings or the fuselage. Pitch links coupled to a rotational swashplate can be used to allow flapping during flight. The swashplates can allow the canting of the rotors to change a rotational or out-of-plane angle of the blades to decrease noise.

A system for disconnecting a battery from an electric aircraft upon impact. The system includes an electric aircraft and a battery assembly electrically coupled to the electric aircraft. The battery assembly is configured to include at least a sensor. The at least a sensor is configured to detect impacts to the electric aircraft. The battery assembly is configured to include a connector. The connector attaches the battery assembly to the electric aircraft. The connector includes an electrically actuating disconnection mechanism. The battery assembly is configured to include a control circuit. The control circuit is electrically connected to the electrically actuating disconnection mechanism. The control circuit is configured to detect, using the at least a sensor, an impact to the aircraft. The control sensor disconnects the connector from the electric aircraft using the electrically actuating disconnection mechanism as a function of the detection of impacts to the electric aircraft.

A system for disconnecting a battery from an electric aircraft upon impact. The system includes an electric aircraft and a battery assembly electrically coupled to the electric aircraft. The battery assembly is configured to include at least a sensor. The at least a sensor is configured to detect impacts to the electric aircraft. The battery assembly is configured to include a connector. The connector attaches the battery assembly to the electric aircraft. The connector includes an electrically actuating disconnection mechanism. The battery assembly is configured to include a control circuit. The control circuit is electrically connected to the electrically actuating disconnection mechanism. The control circuit is configured to detect, using the at least a sensor, an impact to the aircraft. The control sensor disconnects the connector from the electric aircraft using the electrically actuating disconnection mechanism as a function of the detection of impacts to the electric aircraft.

In an aspect of the present disclosure is a system for cooling a high voltage (HV) cable on an electric aircraft, including a fuselage configured to receive the HV cable, including a first side comprising a first venting closure movable between an open position and a closed position. The fuselage may further comprise a second side opposite the first side, the second side comprising a second venting closure movable between an open position and a closed position; wherein the first and second venting closures are configured to create a cooling channel between the first and second venting closures when the first and second venting closures are in the open position, wherein the cooling channel contacts the HV cable.

In an aspect of the present disclosure is a system for cooling a high voltage (HV) cable on an electric aircraft, including a fuselage configured to receive the HV cable, including a first side comprising a first venting closure movable between an open position and a closed position. The fuselage may further comprise a second side opposite the first side, the second side comprising a second venting closure movable between an open position and a closed position; wherein the first and second venting closures are configured to create a cooling channel between the first and second venting closures when the first and second venting closures are in the open position, wherein the cooling channel contacts the HV cable.

An apparatus for guiding a transition between flight modes of an electric aircraft is illustrated. The apparatus comprises at least a sensor configured to detect a movement datum of the electric aircraft and a flight controller communicatively connected to the at least sensor, wherein the flight controller is configured to receive the movement datum from the at least a sensor, determine a current flight mode of the electric aircraft as a function of a pilot input and the movement datum, generate a guidance datum as a function of a change in flight mode and the movement datum, and communicate the guidance datum to a pilot indicator in communication with the at least a sensor and flight controller communicatively connected to the at least a sensor.

A vertical takeoff and landing aircraft is disclosed having a fuselage ending with a tail, a first wing fixedly attached to the fuselage, and a second wing fixedly attached to the fuselage and located between the first wing and the tail. The first wing is provided with four tilting propulsion units forwards of the first wing and attached to the first wing. There may be four tilting propulsion units forwards of the second wing or two tilting propulsion units forwards of the second wing and two non-tilting propulsion units behind the first wing. Each propulsion unit is provided with propeller blades. The propeller blades forwards of the first wing are at least 10% longer than the propeller blades on the second wing and/or behind the first wing and the propeller blades of the tilting propulsion units have variable pitch.

An aircraft safety system includes impact energy reduction systems including: an aircraft parachute, at least one rotor configured for autorotation, and an energy absorbing system. An automatic control system uses data from speed and altitude sensors to selectively and sequentially deploy the impact energy reduction systems depending on the portion of the aircraft speed and altitude flight envelope in which the aircraft is operating when an emergency is detected.

Vertical take-off and landing (VTOL) aircraft can provide opportunities to incorporate aerial transportation into transportation networks for cities and metropolitan areas. However, VTOL aircraft can be sensitive to uneven weight distributions, e.g., the payload of an aircraft is primarily loaded in the front, back, left, or right. When the aircraft is loaded unevenly, the center of mass of the aircraft may shift substantially enough to negatively impact performance of the aircraft. Thus, in turn, there is an opportunity that the VTOL may be loaded unevenly if seating and/or luggage placement is not coordinated. Among other advantages, dynamically assigning the VTOL aircraft payloads can increase VTOL safety by ensuring the VTOL aircraft is loaded evenly and meets all weight requirements; can increase transportation efficiency by increasing rider throughput; and can increase the availability of the VTOL services to all potential riders.

A proximity detection system for facilitating charging of electric aircraft. The proximity detection system includes at least a computing device. The at least a computing device is configured to receive a detection datum from at least a sensor, determine a proximal element as a function of the detection datum, and communicate a notification as a function of the proximal element to at least one of the electric aircraft and a charging structure. The detection datum includes information on at least one of the electric aircraft and the charging structure. The proximal element includes information on a spacing between the electric aircraft and the charging structure. A proximity detection method for facilitating charging of an electric aircraft is also provided.