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.

A thrust generator comprising: a motor (17), and a wing mounting (10), comprising a base (11) and a wing (2, 20), the base connected to the motor and configured to rotate the wing mounting about a stroke axis (13) within an angular stroke range, wherein the wing comprises a wing panel (24) having a first longitudinal edge (5) and a second longitudinal edge (6), the wing panel defining a wing surface (4) between the first and second longitudinal edges, and wherein the wing panel is configurable between: a first configuration in which the first longitudinal edge of the wing panel defines a leading edge and the second longitudinal edge of the wing panel defines a trailing edge; and a second configuration in which the second longitudinal edge of the wing panel defines a leading edge and the first longitudinal edge of the wing panel defines a trailing edge, the thrust generator being configured to rotate the wing mounting about the stroke axis in a first direction when the wing panel is in the first configuration and to rotate the base about the stroke axis in a second direction when the wing panel is in the second configuration.

Piston Wings has high lift airfoils mounted on a linear reciprocal motion mechanism for a propeller driven propulsion engine. Piston Wings, in linear reciprocal motion shuttling back and forth in a generally horizontal plane, has airfoils oriented at optimum angle of attack to generate maximum lift forces; and the lift forces, when vectored, are turned into variable thrust forces for takeoffs, landings, and flights of vehicles. Piston Wings in flight has the appearance of legendary magic or flying carpets.

A cycloidal rotor air vehicle includes an airframe, a first cycloidal rotor assembly supported by the airframe and configured to rotate about a first axis of rotation relative to the airframe, the first cycloidal rotor assembly including a blade having a longitudinal axis oriented parallel to the first axis of rotation, a first motor configured to rotate the first cycloidal rotor assembly about the first axis of rotation, a first servo coupled to the blade of the first cycloidal rotor assembly and configured to adjust the pitch of the blade, and a control system supported on the airframe and configured to control the operation of the first motor and the first servo.

The invention relates to a propulsion device for an aircraft, comprising a blade (2) which can be rotated about an axis of rotation (51) of the propulsion device along a circular path (52) and is mounted for pivoting about a blade bearing axis parallel to the axis of rotation; a pitch mechanism having a coupling device (31) and a bearing device (33); and an offset device (4) to which the blade is coupled, the offset device defining an eccentric bearing axis (41) which is mounted at an adjustable offset distance. The coupling device is coupled to the blade at a coupling point (32) which is positioned in such a way that the plane that comprises the blade bearing axis and the coupling point and the tangential plane to the circular path through the blade bearing axis include a certain, non-vanishing angle (w.sub.α) when the offset distance is set to zero. According to a second aspect the blade bearing axis is shifted toward the axis of rotation by a certain distance relative to the plane that extends through the center of mass of the blade and that extends parallel to the axis of rotation and to the chord of the blade.

A wing ring flying saucer is disclosed, which is operative to be driven to fly fast without needing an extra engine, and can turn, brake and fly backwards. The method of flying the wing ring flying saucer is as follows: airfoils of the wing ring or flow generators are enabled to repeat the same inclining process while passing by a specific section in circular motions of two times or more than three times in succession, so that a force perpendicular to the axial direction is created from an original resultant force in line with the axial direction of the wing ring (that is, a resultant force created by lift produced by all the airfoils), thereby enabling the wing ring flying saucer to fly, turn and go backwards at a relatively high speed.

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.

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.

An autonomous thrust vectoring ring wing pod is disclosed. A plurality of distributed propulsion element (thruster) layout within a self-articulating ring wing pod allows the pod to selectively control its thrust vector by controlling each propulsion element in the pod. This arrangement allows autonomous and independent control of the tilting of the ring wing relative to the aircraft. The ring wing pod acts as both a nacelle to house the propulsion elements as well as a lifting surface when in wing-borne flight. The autonomous thrust vectoring ring wing pod also provides superior aircraft attitude control in wing-borne flight, thus negating the need for conventional surface controls.

V2 Pipe Prop Rotary Wing (PPRW) incorporates a general PPRW documented in patent application Ser. No. 16/128,537 filed on Sep. 12, 2018; and both V2 PPRW and the general PPRW are each a propeller driven propulsion engine in a pipe profile with props or propellers rotating in part as rotary wings. V2 PPRW enhances propulsion performances through the shaping of fluid flow field patterns around props and by the increased relative fluid flow velocities between props of interacting planet and sun airfoils. V2 PPRW props in rotations propel directional fluid for thrusts of lift and drag forces transversely through and across the pipe along the length of the pipe; and when vectored, the thrust forces are turned into variable thrust forces for vehicles in air, on ground, and above or below water.