A system for swarm communication for an electric aircraft fleet, wherein the system includes a plurality of electric aircrafts connected by a mesh network. The system further includes a computing device communicatively connected to the mesh network, wherein the computing device includes an authentication module configured to authenticate each electric aircraft and facilitate communication of a plurality of aircraft data between the plurality of electric aircrafts. The computing device includes a plurality of communication components, each assigned to an electric aircraft of the electric aircraft fleet, wherein each communication component is configured to transmit the aircraft data to the communication component of its assigned electric aircraft. The system further includes a cloud database configured to record the plurality of aircraft data.

An apparatus for generating an electric aircraft flight plan, where the apparatus includes a sensor and controller. The electric aircraft includes a sensor that is configured to detect a position of an electric aircraft, generate a position datum, and transmit the position to a flight controller. The electric aircraft also includes a database of recommended flights. The recommended flight plan is displayed on a display in the electric aircraft.

An apparatus for generating an electric aircraft flight plan, where the apparatus includes a sensor and controller. The electric aircraft includes a sensor that is configured to detect a position of an electric aircraft, generate a position datum, and transmit the position to a flight controller. The electric aircraft also includes a database of recommended flights. The recommended flight plan is displayed on a display in the electric aircraft.

A tailsitter aircraft includes an airframe having first and second wings with first and second pylons extending therebetween, a thrust array attached to the airframe, payloads and payload saddle assemblies coupled to the pylons each configured to secure a respective payload. The thrust array includes propulsion assemblies configured to transition the airframe between a forward flight orientation for wing-borne lift and a VTOL orientation for thrust-borne lift. Each payload saddle assembly includes a latch assembly and a retainer configured to secure the respective payload against a respective pylon. A latch assembly is movable between various positions including an open position and a closed position and is configured to secure the respective payload in the closed position and release the respective payload in the open position. Each latch assembly is configured to move from the closed position to the open position to release the respective payload in the VTOL orientation.

A tandem wing aircraft that uses electric ducted fans to propel itself. The positioning of the electrical ducted fans allows the aircraft to take off and land vertically when the electrical ducted fans have their airflow outlet in a vertical position and to fly horizontally when a pair of electrical ducted fans are rotated so that their airflow outlet are in a horizontal position. The tandem wing aircraft uses an electric power source to power the aircraft and is controlled by a logic and electronic controller. The aircraft uses flaps, vertical stabilizers, ailerons, and an elevator to control its orientation and position during horizontal flight. The aircraft is designed to fly in urban spaces because of its wing and propulsion design. In addition, this design guarantees the stability of the aircraft on all flight stages, as well as the emergency landing in case the electrical ducted fans fail.

An electric reaction control system that can selectively expel a “burst” or “puff” of air to alter the orientation of the aircraft during flight. An aircraft incorporating ducting, an air compressor, an electric motor, and a plurality of nozzles can facilitate in-flight trajectory modifications. When an air burst is needed to provide thrust for the purposes of reaction control, nozzles are selectively opened and closed to provide roll, pitch, and yaw of the aircraft. The ERCS can facilitate an electric aircraft that would be very agile and very light, utilizing electric power, as opposed to jet power.

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 may be noisy. To accommodate this, the aircraft may utilize onboard sensors, offboard sensing, network, and predictive temporal data for noise signature mitigation. By building a composite understanding of real data offboard the aircraft, the aircraft can make adjustments to the way it is flying and verify this against a predicted noise signature (via computational methods) to reduce environmental impact. This might be realized via a change in translative speed, propeller speed, or choices in propulsor usage (e.g., a quiet propulsor vs. a high thrust, noisier propulsor). These noise mitigation actions may also be decided at the network level rather than the vehicle level to balance concerns across a city and relieve computing constraints on the aircraft.

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 may be noisy. To accommodate this, the aircraft may utilize onboard sensors, offboard sensing, network, and predictive temporal data for noise signature mitigation. By building a composite understanding of real data offboard the aircraft, the aircraft can make adjustments to the way it is flying and verify this against a predicted noise signature (via computational methods) to reduce environmental impact. This might be realized via a change in translative speed, propeller speed, or choices in propulsor usage (e.g., a quiet propulsor vs. a high thrust, noisier propulsor). These noise mitigation actions may also be decided at the network level rather than the vehicle level to balance concerns across a city and relieve computing constraints on the aircraft.

An aircraft in the form of an electrically driven, vertical take-off and landing, preferably people-carrying and/or load-carrying multicopter (1) is provided, in which a multiplicity of rotors are arranged in a common rotor plane (R), in which a tail unit (6), protruding upward or downward with respect to the rotor plane (R), is provided above or below the rotor plane (R), preferably in a rear region of the aircraft (1) with respect to a forward flying direction.

A hybrid aircraft system uses a combination of direct propeller driven gas engine and electric motor power to provide vertical thrust and control for hover of the aircraft. Furthermore, a portable launch/recovery system is configured for use with an aircraft such as a Vertical Takeoff and Landing (VTOL) Unmanned Air Vehicle (UAV). The system is configured to enable ships with limited available deck space to become UAV-compatible.