9results about "Canard-type aircraft" patented technology

This present invention relates to the field of aircraft and discloses an aircraft and a method for connecting a canard to an arm. The connection method is used to couple a canard and an arm. The canard comprises a coupling insertion portion, which comprises a plurality of fixing portions. The arm comprises an arm insertion cavity, and an insertion opening is provided at one end of the arm insertion cavity. The coupling insertion portion is configured to be inserted into the arm insertion cavity through the insertion opening and is fixed within the arm via the fixing portions. In the present invention a detachable structure is enabled between the canard and the arm, allowing the position of the center of lift to be adjusted by exchanging canards featuring different designs, thereby adapting to aircraft cabins with different centers of gravity.

According to the present disclosure, a vehicle configured to travel on roads and fly through the air is provided. The vehicle of the present disclosure includes a fuselage extending from a forward end to an aft end along a roll axis of the vehicle, a pair of main wings attached to the aft end of the fuselage, a pair of canards attached to the fuselage forward of the main wings, a plurality of wheels configured to enable travel on roads, and a rotor system including a plurality of rotors. Each of the main wings and the canards is configured to be displaced from the fuselage to a position extending along the pitch axis of the vehicle when deployed, and to be displaced to a position overlapping the fuselage when retracted. The rotor system includes a pair of tiltable main rotors respectively attached to each of the main wings, and each tiltable main rotor is configured to be tiltably displaced to a plurality of tilt positions between a forward position in which its rotation axis is substantially parallel to the roll axis of the vehicle and an upper position in which its rotation axis is substantially parallel to the yaw axis of the vehicle.

An aircraft includes a fuselage and a primary airfoil having a first upper surface. The first upper surface has a recess disposed therein. A conduit is in fluid communication with recess. An ejector is disposed within the recess. The ejector is configured to receive compressed air via the conduit. The ejector is further configured to produce a propulsive efflux stream. A secondary airfoil is coupled to the primary airfoil and has a second upper surface. The ejector is positioned such that the efflux stream flows over the second surface. The second surface is oriented so as to entrain the efflux stream to flow in a direction substantially perpendicular to the first upper surface.

An aircraft apparatus is disclosed that has a fuselage; and a wing coupled to the fuselage, where the wing comprises a port outboard wing section and a starboard outboard wing section; where each of the port outboard wing section and the starboard outboard wing section comprise at least one of: curved leading edges of varying radii and curved trailing edges of varying radii.

A VTOL aircraft, including: at least one wing mechanically coupled to a fuselage; at least four variable-speed tilt rotors, together designed and dimensioned to support a payload of at least 500 pounds; at least one first and at least one second motor, wherein the first and / or second motor is configured to drive a first of the at least four variable-speed tilting rotors; and at least one third and at least one fourth motor, wherein the third and / or fourth motor is configured to drive a second of the at least four variable-speed tilting rotors, wherein in a rotor-supported flight the at least four variable-speed tilt rotors are arranged together to lift the VTOL aircraft, wherein three of the at least four variable-speed tilt rotors are capable of providing at least 70% of the lift required to lift the VTOL aircraft carrying a payload of at least 500 pounds.

A vehicle, includes a main body. A fluid generator is coupled to the main body and produces a fluid stream. At least one tail conduit is fluidly coupled to the generator. First and second fore ejectors are coupled to the main body and respectively coupled to a starboard side and port side of the vehicle. The fore ejectors respectively comprise an outlet structure out of which fluid flows. At least one tail ejector is fluidly coupled to the tail conduit. The tail ejector comprises an outlet structure out of which fluid flows. A primary airfoil element includes a closed wing having a leading edge and a trailing edge. The leading and trailing edges of the closed wing define an interior region. The at least one propulsion device is at least partially disposed within the interior region.

The present invention provides a power system for aircraft and a corresponding operating method that enables sufficient resilience to electrical failures in an efficient manner. [Solution] The power distribution network (306) of the aircraft's power system (300) operates in at least one normal operating mode such that it provides load balancing with respect to electrical loads (AA, BB, CC, DD) across power sources (A, B, C, D), and the power distribution network (306) operates in at least one electrical fault mitigation operating mode such that in the event of an electrical fault, the network portion of the power distribution network (306) having the electrical fault is isolated from at least one other network portion of the power distribution network.