An unmanned aircraft includes: a processor; and at least two generators that generate thrust for the unmanned aircraft to fly, the at least two generators each including a corresponding one of rotor blades that produce airflows. In the unmanned aircraft, the processor generates a control request for changing a rotational speed of at least one of the rotor blades of the at least two generators to reduce a difference between rotational speeds, in response to start of sound recording by a microphone, and the at least two generators rotate the rotor blades in accordance with the control request.

A system comprising an unmanned aerial vehicle (UAV) configured to transition from a terminal homing mode to a target search mode, responsive to an uplink signal and/or an autonomous determination of scene change.

A system comprising an unmanned aerial vehicle (UAV) configured to transition from a terminal homing mode to a target search mode, responsive to an uplink signal and/or an autonomous determination of scene change.

Example implementations may relate to self-deployment of operational infrastructure by an unmanned aerial vehicle (UAV). Specifically, a control system may determine operational location(s) from which a group of UAVs is to provide aerial transport services in a geographic area. For at least a first of the operational location(s), the system may cause a first UAV from the group to perform an infrastructure deployment task that includes (i) a flight from a source location to the first operational location and (ii) installation of operational infrastructure at the first operational location by the first UAV. In turn, this may enable the first UAV to operate from the first operational location, as the first UAV can charge a battery of the first UAV using the operational infrastructure installed at the first operational location and/or can carry out item transport task(s) at location(s) that are in the vicinity of the first operational location.

Wings do not produce lift. It is the thrust provided by an engine (or engines) that enable an aircraft to rise off the ground.

The Multi-Rotor Safety Shield (MRSS) provides a complete and substantial encasement system which can be secured about a Drone, protecting a multitude of aircraft components from contact with any outside disturbance and which can protect the sensitive components from dust, water, wind, rain, snow, fingers, toes, appendages of any kind, and atmospheric changes as example, from disabling the Drone and can protect people, places or things from high velocity spinning exposed rotor/propellers. The MRSS provides rigid non-permeable platform for attaching or incorporating additional safety devices as found in the Drone industry (or other industries) resulting in a safety device that completely prevents the loss a Drone due to the catastrophic failure of any Drone system or combination of systems which would typically result in rapid decent, and/or uncontrolled flight. The MRSS makes Drones safe near humans and safe to use around public gatherings, stadium events, accident scenes, disaster search and rescue and disaster relief, and indoors for the security and communications markets among others expanding the availability of Drones to further assist humanity.

An aerial vehicle is programmed or configured to respond to reports of events or conditions within spaces of a facility. The aerial vehicle travels to a location of a reported event or condition and captures data using onboard sensors. The aerial vehicle independently determines whether the reported event or condition is occurring, or is otherwise properly addressed by resources that are available at the location, using images or other data captured by the onboard sensors. Alternatively, the aerial vehicle transmits a request for additional resources to be provided at the location, where necessary. A map of the location generated based on images or other data captured by the onboard sensors may be utilized for any purpose, such as to make one or more recommendations of products that are appropriate for use at the facility.

This disclosure is directed to varying a speed of one or more motors in an unmanned aerial vehicle (UAV) to reduce unwanted sound (i.e., noise) of the UAV. A UAV may include motors coupled with propellers to provide lift and propulsion to the UAV in various stages of flight, such as while ascending, descending, hovering, or transiting. The motors and propellers may generate noise, which may include a number of noise components such as tonal noise (e.g., a whining noise such as a whistle of a kettle at full boil) and broadband noise (e.g., a complex mixture of sounds of different frequencies, such as the sound of ocean surf). By varying the controls to the motors, such as by varying the speed or revolutions per minute (RPM) of a motor during operation by providing random or pseudo-random RPM variations, the UAV may generate a noise signature with reduced tonal noise.

The present invention discloses an unmanned aerial vehicle including a main body, a plurality of arms, a propulsion assembly and a battery assembly, where each arm is coupled to the main body and the propulsion assembly is disposed on the each arm. The battery assembly is accommodated in a battery compartment of the main body. The battery assembly includes a shell, a battery body substantially disposed in the shell, a clamp button, and a restorable elastic piece. An end of the clamp button is mounted or connects to the shell, and the other end of the clamp button is detachably coupled to the main body. An end of the restorable elastic piece is disposed on the shell or connect to the shell, and the other end of the restorable elastic piece contacts the clamp button.

The invention relates to a propulsion system concept that is a propulsion system that is integrated in the hull of an aerial vehicle (1), which propulsion concept comprises at least one differential velocity fan (4), which is arranged on a shaft driven by one or more power units (2). The propulsion concept is intended to provide short takeoff and landing distances, high flight speed (high subsonic to transsonic) and to be able to provide low IR signature, low radar signature, a small cross section and low air resistance. The propulsion concept is called HPVO (High Performance Optimized Versatile propulsion). The invention is useful both for air vehicles of the type for conventional takeoff and landing, “CTOL” (Conventional Take Off and Landing), “Chair” and for vertical takeoff and landing, “V (t) OL” (Vertical (Take) Off and Landing’) and the flying wing (blended-body). The concept is applicable to both large and small aircraft, manned as well as unmanned aerial vehicles.