A system and method for conducting electronic warfare on a target site includes the use of a small unmanned aircraft system (SUAS) having a fuselage and a Prandtl wing, wherein at least two electric ducted fans are positioned on the fuselage. A power system of the SUAS has a plurality of hydrogen fuel cells positioned within the Prandtl wing. An electronic warfare payload is carried by the fuselage, wherein the electronic warfare payload and the at least two electric ducted fans are powered by at least a portion of the plurality of hydrogen fuel cells. During an operation, the SUAS may launch near an IAD site and initiate an electronic warfare effect on an integrated air defense site with electronic warfare payload carried by the SUAS to interfere with at least one surface-to-air missile (SAM) system.

A system and method for conducting electronic warfare on a target site includes the use of a small unmanned aircraft system (SUAS) having a fuselage and a Prandtl wing, wherein at least two electric ducted fans are positioned on the fuselage. A power system of the SUAS has a plurality of hydrogen fuel cells positioned within the Prandtl wing. An electronic warfare payload is carried by the fuselage, wherein the electronic warfare payload and the at least two electric ducted fans are powered by at least a portion of the plurality of hydrogen fuel cells. During an operation, the SUAS may launch near an IAD site and initiate an electronic warfare effect on an integrated air defense site with electronic warfare payload carried by the SUAS to interfere with at least one surface-to-air missile (SAM) system.

The aircraft can include: an airframe, a tilt mechanism, a payload housing, and can optionally include an impact attenuator, a set of ground support members (e.g., struts), a set of power sources, and a set of control elements. The airframe can include: a set of rotors and a set of support members.

The aircraft can include: an airframe, a tilt mechanism, a payload housing, and can optionally include an impact attenuator, a set of ground support members (e.g., struts), a set of power sources, and a set of control elements. The airframe can include: a set of rotors and a set of support members.

An air mobility device improves propulsion due to the Coandă effect when flying so as to increase a flying range and reduces noise when flying.

An aircraft includes a fuselage, a wing attached thereto, a wing tip device attached to a wing end of the wing (2), a wing-like element having a wing root, a wing leading edge and a wing trailing edge, and a torque control device having a rotatable interface means. The torque control device is adapted for rotatably supporting the wing root of the wing-like element on the interface means about a rotational axis extending from the interface means into the wing-like element and to limit the degree of rotation depending on a torque introduced into the interface means by the wing-like element. The wing-like element is adapted to induce a rotation around the rotational axis in an air flow. The wing root is coupled with the wing tip device, the wing or the fuselage through the torque control device such that the leading edge extends into an airflow surrounding the aircraft.

An insect-like jumping-flying robot is provided, which includes a flying module, a driving module and biomimetic bouncing legs. The flying module provides flying power via a propeller and a miniature model airplane motor, and front wings and rear wings provide lift, and moment required for attitude change. The driving module provides power with high power density via a brushless motor and is provided with two stages of deceleration to amplify the torque provided by the brushless motor. The first stage of deceleration is performed by a synchronous wheel set, and the second stage of deceleration is performed by a gear set. A driving push rod is used to transmit the power provided by the brushless motor to the biomimetic bouncing legs.

An aircraft has a boom, a propulsion assembly coupled to a first end of the boom, and a first wing coupled to a second end of the boom. The propulsion assembly is coupled to the boom by a rotating joint. A second wing is optionally coupled to the rotating joint. The first wing is coupled to the boom by a rotating joint. The first wing is coupled to the rotating joint by a hinge. A vehicle with roll, pitch, and yaw maneuverability able to mirror the aircraft movements may be coupled to the second end of the boom. The vehicle body may be picked up with a vehicle chassis disconnected from the vehicle body. The boom houses an energy source to power the propulsion assembly. A rudder is coupled to the second end of the boom. A paddle is disposed between the propulsion assembly and the boom.

An aircraft has a boom, a propulsion assembly coupled to a first end of the boom, and a first wing coupled to a second end of the boom. The propulsion assembly is coupled to the boom by a rotating joint. A second wing is optionally coupled to the rotating joint. The first wing is coupled to the boom by a rotating joint. The first wing is coupled to the rotating joint by a hinge. A vehicle with roll, pitch, and yaw maneuverability able to mirror the aircraft movements may be coupled to the second end of the boom. The vehicle body may be picked up with a vehicle chassis disconnected from the vehicle body. The boom houses an energy source to power the propulsion assembly. A rudder is coupled to the second end of the boom. A paddle is disposed between the propulsion assembly and the boom.

A vertical take-off and landing (VTOL) aircraft (10) includes a fuselage and first and second forward wings (20, 22), each wing (20, 22) having a fixed leading edge and a trailing control surface (50) which is pivotal about a generally horizontal pivot axis. The aircraft (10) includes first and second electric motors (60) each having rotors (70), the electric rotors (70) being pivotal with the trailing control surface (50) between a first position in which each rotor (70) has a generally vertical axis of rotation, and a second position in which each rotor (70) has a generally horizontal axis of rotation, a control system (90) is configured to selectively operate the first electric motor (60) and the second electric motor (60) at different rotational speeds to generate a turning moment to pivot the control surface (50) about the pivot axis (33).