An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. The UAVDC may comprise a fuselage, at least one wing, and at least one control surface. In some embodiments, the UAVDC may further comprise a propulsion means and/or a modular payload. The UAVDC may be configured in a plurality of arrangements. For example, in a compact arrangement, the UAVDC may comprise the at least one wing stowed against the fuselage and the at least one control surface stowed against the fuselage. In a deployed arrangement, the UAVDC may comprise the at least one wing deployed from the fuselage and the least one control surface deployed from the fuselage. In an expanded arrangement, the UAVDC may comprise the at least one wing telescoped to increase a wingspan of the deployed arrangement.

The present invention extends to a container venting system. A wall portion of a container includes a (e.g., thermo-sensitive) panel. Any portion of the panel exposed to sufficient heat crumbles or ruptures (e.g., without burning) creating an opening in the wall portion. In one aspect, a container is included in a vehicle (e.g., an Unmanned Aerial Vehicle (UAV)). The container includes a panel in an external wall of the vehicle. Any portion of the panel exposed to sufficient heat crumbles to create an opening in the external wall of the vehicle. A container can be a sealed container with the panel sealed to the wall portion or to the external wall of the vehicle. The interior of the sealed container can contain a battery cell. Creating an opening allows gases to vent out of the sealed container and/or to vent outside of the vehicle.

An unmanned aerial vehicle includes a housing, at least one driving module, and at least one driving module. The housing includes an outer structure made of shock-absorbing material, and an inner structure made of rigid material, the inner structure partially embedded into the outer structure. The at least one driving module is assembled to the housing. The at least one detecting module is fixed on the inner structure and surrounded by the outer structure.

A propeller-enclosed airlifting air tube apparatus contains a unique multi air-tube structure that functions as a plurality of air outtakes to produce stable lift force with one or more propellers enclosed in the apparatus. By encapsulating the propellers within the outer shells, the airlifting air tube apparatus is able to reduce potential bodily harm and property damage risks during a flight operation in a densely-populated environment or in another environment involving tight spaces. The airlifting air tube apparatus encapsulates one or more pairs of contra-rotating propellers inside a drone casing to enhance operational safety while minimizing the overall footprint of the apparatus. Furthermore, the airlifting air tube apparatus incorporates a novel airflow control dish-based flight control steering unit configured to change directions and altitudes of the apparatus by dynamically adjusting the airflow to each outtake air tube with the airflow control dish.

Antennas configuration for unmanned aerial vehicle (UAV) comprising at least one pair of patch antennas. Each patch antenna having a patch mounted on a ground plane. A UAV body having at least one portion constructed of material that minimally attenuates the electromagnetic signal transmitted or received by said plurality of antennas. Wherein the at least one pair of patch antennas are mounted within the UAV body and near the inner surface of the UAV body. Each antenna from the pair of patch antennas further installed opposite to one another and each of the patches facing outside from the UAV body.

In some embodiments, systems and methods are provided that limit the change in temperature and/or control a temperature of a product during delivery. Some embodiments provide systems comprising an unmanned delivery vehicle (UDV) comprising: a body comprising a nanotechnology insulation material, wherein the nanotechnology insulation material comprises material having been manipulated at a molecular level during the macroscale fabrication of the nanotechnology insulation material to enhance insulation effectiveness; at least one propulsion system; a control circuit coupled with the at least one propulsion system to control the operation of the at least one propulsion system and control a direction of travel of the UDV, wherein the body physically supports the propulsion system and the control circuit; and a product cavity defined within the body and configured to receive at least one product while the at least one product is transported by the UDV to a delivery location.

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.

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.

A remote piloted aircraft comprising a secondary flight assembly adapted to intervene in case of failure or an emergency of the aircraft, said secondary flight assembly being provided with an additional control unit configured to process flight relevant data and which includes an additional receiver configured to receive commands from the remote pilot by means of a remote control unit, in case of failure or emergency said additional control unit being configured to generate, as a response, an activation command adapted to activate a first device to expel an upper wing placed in a first compartment of the aircraft and to inflate a lower wing housed in a second compartment of the aircraft, and also to generate an interdiction command of the primary propulsion unit, said upper wing being maneuverable by means of a further remote control unit.

The present disclosure is directed to controlling, reducing, and/or altering sound generated by an aerial vehicle, such as an unmanned aerial vehicle (UAV), while the aerial vehicle is airborne. For example, one or more transducers, such as piezoelectric thin-film transducers, or carbon nanotube transducers may be applied or incorporated into or on the surface of propeller blades that are used to aerially navigate the aerial vehicle. As the propeller blade rotates and generates sound, the transducers may be activated to generate one or more anti-sounds that cancel, reduce, or otherwise modify the sound generated by the rotation of the propeller blade. The anti-sound combines with the sound and causes interference such that the combined, or net-effect, is an overall cancellation, reduction, or other modification of the sound.