A ferromagnetic actuator is disposed between first and second semiconductor devices that include first and second inductors. Each inductor is disposed on top of a multilevel wiring structure. Current flows through the first inductor to generate a first magnetic field that attracts the ferromagnetic actuator towards the first inductor causing the ferromagnetic actuator to transition from a first state to a second state. In the second state, a portion of the ferromagnetic actuator is disposed closer to the first inductor than it is in the first state. Current flows through the second inductor to generate a second magnetic field that attracts the ferromagnetic actuator towards the second inductor causing the ferromagnetic actuator to transition from the first or second state to a third state. In the third state, a portion of the ferromagnetic actuator is disposed closer to the first inductor than it is in the first state.

A diversity receiver synchronizes and mixes multiple input signals. In one embodiment, the receiver demodulates the multiple input signals prior to synchronizing, converts the demodulated multiple input signals from analog signals to digital signals, synchronizes the demodulated digital signals, converts the synchronized demodulated digital signals to analog signals and mixes the synchronized demodulated analog signals based on a characteristic of the input signals existing prior to the demodulating.

The invention discloses a hand-launched unmanned aerial vehicle, and belongs to the technical field of unmanned aerial vehicles. The hand-launched unmanned aerial vehicle comprises a body, a tail, at least one power source and a lens bin, wherein the body comprises a middle section, a first side section and a second side section; two sides of the middle section are respectively detachably connected with the first side section and the second side section correspondingly; the tail is fixed to the middle section; the power source is fixed to the middle section; and the lens bin is fixed to the middle section and provided with a flexible cushion. The invention overcomes the technical defects in the prior art that the body maintenance cost of the hand-launched unmanned aerial vehicle is high and the lens bin is very likely to be damaged due to collision between the lens bin of the hand-launched unmanned aerial vehicle and the ground.

The invention relates to a launched aerial surveillance vehicle, more specifically to a grenade or under-slung grenade launcher (UGL) aerial surveillance vehicle, a surveillance system and methods of providing rapid aerial surveillance. The vehicle once deployed is capable of autonomous flight paths, with basic inputs to change the circular flight paths, so as to build up surveillance for an area of interest. The vehicle comprises at least one optical sensor, which may be IR or visible range, to survey the area of interest, and feed the images back to at least one remote user.

The present application discloses a flying device designed in the shape of a bee. The flying device comprises a body with a head and a pointed tail, two wings attached to either side of the body, and one or more sensors. The one or more sensors may be located on the outer surface of the device. The sensors may include cameras for capturing pictures or videos of the environment. The sensors may also include temperature sensors (thermometers), GPS readers, and/or wind sensors (anemometer). The body of the device comprises one or more transducers and one or more processors. The device is configured to identify a type of flower or plant and to perform pollination.

An autonomous catapult-assisted take-off, recycling, and reuse device and method of a flapping-wing unmanned aerial vehicle (UAV) are provided. The device includes a base, an attitude adjusting mechanism, a catapult mechanism, a recycling mechanism, a control processing unit, a power supply module, and a sensor unit, where the attitude adjusting mechanism includes a connector, a counterweight, an adjusting motor, an attitude adjusting input gear, an attitude adjusting output gear, an attitude adjusting output gear shaft, and an installation platform; the catapult mechanism includes a catapult motor, a catapult motor frame, a pulley, a pull rope, a winch, a pull rope fixing part, a flapping-wing aircraft fixing part, two slide bars, two compression springs, and a catapult gear set; and the recycling mechanism includes a recycling motor, a recycling mechanical arm, a recycling platform, two sprockets, and a recycling gear set.

A vehicle, such as a micro-aerial vehicle or underwater vehicle, includes at least one lift structure, such as a low-aspect-ratio wing or a fin, respectively. The at least one lift structure comprises one or more alulas. A leading surface of each alula is (a) flush with a leading surface of the lift structure or (b) offset from the leading edge of the lift surface by up to approximately 10% of the chord length of the lift structure. The length of each alula is no more than approximately 20% of a lift structure length corresponding to the lift structure. In various embodiments, the alula is deflected or canted with respect to a plane defined by the lift structure. In an example embodiment, the alulas may be slid or translated along at least a portion of the span of the lift structure.

A quadrotor UAV including ruggedized, integral-battery, load-bearing body, two arms on the load-bearing body, each arm having two rotors, a control module mounted on the load-bearing body, a payload module mounted on the control module, and skids configured as landing gear. The two arms are replaceable with arms having wheels for ground vehicle use, with arms having floats and props for water-surface use, and with arms having pitch-controlled props for underwater use. The control module is configured to operate as an unmanned aerial vehicle, an unmanned ground vehicle, an unmanned (water) surface vehicle, and an unmanned underwater vehicle, depending on the type of arms that are attached.

A lightweight, pocket-sized unmanned aerial vehicle (UAV) that can be held in an outstretched hand by a user for take-off and landing of the UAV. The UAV comprises a semi-toroidal or a substantially toroidal hollow body that defines a duct. The UAV further comprises a motor for rotating a fan that directs air into and out of the duct enabling UAV to take flight. The UAV comprises a flight-control system that comprises at least two flight control surfaces that can alter the directed air as it flows through the duct for controlling the roll and pitch and optionally the yaw of the UAV during flight. The flight control system may be controlled by a microprocessor controller. The UAV further comprises a payload, with at least a wireless transmitter and receiver unit.

An indoor autonomous aerial system and method that uses micro aerial vehicle/s (MAV/s). Said system is configured to be deployable and operable in reduced GPS signal reception expansive spaces and the MAV/s is/are configured to be automatically guided and perform tasks at desired location/s, transmit/receive data, present various signs, etc. Said system and method can be used for various purposes such as, advertisement, inventory management, guidance, warning, search and rescue, etc.