A system includes a plurality of aircrafts, each of which has an antenna for forming a communication area on the ground to provide a radio communication service to a user terminal in the communication area, and a management device for managing the plurality of aircrafts. The management device includes a signal transmitting unit that transmits a remote operation signal to an aircraft selected as the remote operation target from the plurality of aircrafts. Each of the plurality of aircrafts includes a remote operation flying control unit that, when an aircraft is selected as the remote operation target, causes the aircraft to fly based on the remote operation signal received from the management device, and a tuned flying control unit that, when the aircraft is not selected as the remote operation target, causes the aircraft to fly in tune with other aircraft selected as the remote operation target.

A system includes a plurality of aircrafts, each of which has an antenna for forming a communication area on the ground to provide a radio communication service to a user terminal in the communication area, and a management device for managing the plurality of aircrafts. The management device includes a signal transmitting unit that transmits a remote operation signal to an aircraft selected as the remote operation target from the plurality of aircrafts. Each of the plurality of aircrafts includes a remote operation flying control unit that, when an aircraft is selected as the remote operation target, causes the aircraft to fly based on the remote operation signal received from the management device, and a tuned flying control unit that, when the aircraft is not selected as the remote operation target, causes the aircraft to fly in tune with other aircraft selected as the remote operation target.

A system for an aircraft that includes a plurality of zones including: a first fiber optic cable routed through a zone of the plurality of zones. The first fiber optic cable is attached to a landing gear of the aircraft in the zone of the plurality of zones; and a first controller configured to provide a first optical signal to the first fiber optic cable and obtain a first optical response signal from the first fiber optic cable. The first controller is further configured to determine at least one temperature within the zone of the plurality of zones based on the first optical response signal, the first optical signal, and coherent optical frequency domain reflectometry (COFDR).

A system for an aircraft that includes a plurality of zones including: a first fiber optic cable routed through a zone of the plurality of zones. The first fiber optic cable is attached to a landing gear of the aircraft in the zone of the plurality of zones; and a first controller configured to provide a first optical signal to the first fiber optic cable and obtain a first optical response signal from the first fiber optic cable. The first controller is further configured to determine at least one temperature within the zone of the plurality of zones based on the first optical response signal, the first optical signal, and coherent optical frequency domain reflectometry (COFDR).

Embodiments of the present invention relate to the field of aerial photography technologies and disclose an aircraft control method and an aircraft. The aircraft control method is applicable to the aircraft, and the aircraft includes a flight control system (FCS) configured to control the aircraft and a gimbal control system (GCS) configured to control a gimbal. The GCS can obtain a yaw control instruction to be inputted into the aircraft and attitude angle information outputted by the gimbal and then control yawing of the gimbal according to the yaw control instruction to be inputted into the aircraft and the attitude angle information outputted by the gimbal, so as to implement high-precision control of aerial photography of the aircraft, thereby ensuring high quality of an aerial video and resolving video freezing during aerial photography at a low rotation speed.

A system for creating thrust for flying machines with Vertical Take Off and Landing (VTOL) including a first propulsion unit, a second propulsion unit, a top winget, a bottom winget, two or more tracks running over said first and second propulsion units, and wherein the two or more tracks are configured to mount said top and bottom wingets.

A system for creating thrust for flying machines with Vertical Take Off and Landing (VTOL) including a first propulsion unit, a second propulsion unit, a top winget, a bottom winget, two or more tracks running over said first and second propulsion units, and wherein the two or more tracks are configured to mount said top and bottom wingets.

The present invention is an Electric servo system which controls and automates gate openings based on GPS speed and position data that results in precise and reliable modern variable and constant rate application. The Electric servo system also allows for Mechanical gate linkages to remain intact, resulting in few changes to the aircraft and redundancy of emergency components. A Mechanical input connect/disconnect is used to effortlessly transfer between the automated Electric servo system and the Mechanical gate system.

The present invention is an Electric servo system which controls and automates gate openings based on GPS speed and position data that results in precise and reliable modern variable and constant rate application. The Electric servo system also allows for Mechanical gate linkages to remain intact, resulting in few changes to the aircraft and redundancy of emergency components. A Mechanical input connect/disconnect is used to effortlessly transfer between the automated Electric servo system and the Mechanical gate system.

A concentric, double hull, damage tolerant airframe vehicle double clad with a lightweight, impact resistant ceramic matrix composite for heat shielding and flame resistance, and fitted with insulation, to provide thermal protection from 35° C. to 1,650° C. of the internal fuselage areas for an extended period of time within an extreme heat environment, that will serve as a semi or fully autonomous vehicle, manned or unmanned, preferably an unmanned aerial vehicle designed as the delivery means to suppress or extinguish flames by repeatedly discharging pressure waves against flames without having to exit the fire environment.