Systems and method for creating, modifying, and utilizing a virtual 360-degree view of a telecommunications site obtaining data capture from the telecommunications site, wherein the data capture comprises one or more of photos and video; processing the data capture to create a three-dimensional (3D) model of the telecommunications site in a first state, buildings, and constructions therein; importing the 3D model into modification software and adding one or more objects to the 3D model utilizing the modification software, wherein the one or more objects comprise one or more of geography, buildings, and constructions planned as possible additions to the telecommunications sites; creating a modified 3D model with the one or more objects and the 3D model in the first state such that the modified 3D model represents the telecommunications site in a second state; and utilizing the modified 3D model for one or more of planning, engineering, and installation.

The dual inlet exhaust design for the flying device incorporates easy-to-assemble designs with low number of components, suitable for limited space and small volume requirements, good performance. The exhaust is designed as a three-chamber cylinder with two coaxial inlet pipes running through the two chambers on both sides, extending into the middle compartment. The width of the two inlet tubes in the middle compartment is different. The inlet pipe at the two compartments on both sides has a bore. The outlet tube is located in the middle compartment, deviating to the side with a smaller expansion inlet, with the longitudinal axis of the outlet tube passing through the inlet tube.

A functionality utilizing a centrally controlled strategy for continuous communication to specific autonomous vehicles, or drones, that are designed for extreme conditions and assigned specific missions with the ability to be replaced during the mission. This functionality is an improvement on existing swarm and leader-follower tactics as it retains control of the drones at a central command center, allowing the drones to both receive individual commands from the hub but also operate independently of it with direct pilot control. This direct communication allows for real time process of ordered substitution to replace any drone during the mission.

A functionality utilizing a centrally controlled strategy for continuous communication to specific autonomous vehicles, or drones, that are designed for extreme conditions and assigned specific missions with the ability to be replaced during the mission. This functionality is an improvement on existing swarm and leader-follower tactics as it retains control of the drones at a central command center, allowing the drones to both receive individual commands from the hub but also operate independently of it with direct pilot control. This direct communication allows for real time process of ordered substitution to replace any drone during the mission.

A multimodal unmanned aerial system includes a fuselage forming a payload bay, a control wing forward of the fuselage including a first plurality of propulsion assemblies and a primary wing aft of the fuselage including a second plurality of propulsion assemblies. The primary wing has a greater wingspan than the control wing. The multimodal unmanned aerial system includes linkages rotatably coupling the fuselage to the control wing and the primary wing. The fuselage, the control wing and the primary wing are configured to synchronously rotate between a vertical takeoff and landing flight mode and a forward flight mode. The fuselage, the control wing and the primary wing are substantially vertical in the vertical takeoff and landing flight mode and substantially horizontal in the forward flight mode.

An unmanned aerial vehicle (UAV) includes a fuselage, a pair of wings attached to the fuselage, and a propulsion system mounted to the wings to provide propulsion to the UAV. The fuselage has an outer fuselage shell that is a first mechanical support structure for an airframe of the UAV. The pair of wings is attached to the fuselage and shaped to provide aerodynamic lift. The wings have outer wing shells that are second mechanical support structures for the airframe. The outer fuselage shell or the outer wing shells comprise one or more formed-metal sheets.

An unmanned aerial vehicle (UAV) includes a fuselage, a pair of wings attached to the fuselage, and a propulsion system mounted to the wings to provide propulsion to the UAV. The fuselage has an outer fuselage shell that is a first mechanical support structure for an airframe of the UAV. The pair of wings is attached to the fuselage and shaped to provide aerodynamic lift. The wings have outer wing shells that are second mechanical support structures for the airframe. The outer fuselage shell or the outer wing shells comprise one or more formed-metal sheets.

Embodiments of the present invention enable a user of a drone to operate it more quietly. Embodiments of the present invention relate to such a system, apparatus, and a method of and for a drone that may be quiet, that can fly far while minimizing the need to recharge, that may have protective shells, that may employ operational redundancy, that may provide stealth capabilities due, for example, to the design of the shell, and that may allow a drone to stay in position at, for example, 329,999 feet for months. In one embodiment of the present invention, electro-magnetism is used to propel a drone while another embodiment uses an expandable outer shell. The embodiments, while also increasing a drone's range, provide enhanced maneuverability due to the unique shape and drive and steering systems of the drone. Embodiments may provide stealth and overall convenience, together potentially resulting in increased safety to creating a class of sub-space vehicles.

A small flying vehicle capable of mitigating the shock at the time of falling and colliding with the ground or the like is provided.

A small flying vehicle equipped with an airbag device, capable of flying by radio control or autonomously flying by autopilot, and having a maximum length of 2 m or less, wherein the small flying vehicle has a main body part including a controller and a battery, a frame, a propeller, a motor, and a transmitting and receiving antenna; the airbag device has gas supply means, a sensor, a control device and an airbag, and is attached to the main body part; and the gas supply means is provided with a gas cylinder capable of releasing an internal gas when a closure member is broken and opened, breaking means including an electric igniter for opening the closure member of the gas cylinder, and introduction means for introducing the pressurized gas in the gas cylinder into the airbag to inflate the airbag.

An aerial system, preferably including one or more housings. A housing for an aerial system, preferably including: a first and second piece that cooperatively surround one or more propellers of the aerial system; and a retention mechanism that removably couples the first piece to the second piece. A method for aerial system operation, preferably including attaching and/or detaching housing pieces of the aerial system.