A noise reduction apparatus, an aircraft, and a noise reduction method capable of increasing the amount of noise reduction are provided. The noise reduction apparatus 1 includes a porous plate 2 disposed to face a fluid flow, the porous plate 2 including a bend region 5 bent toward an upstream side of the fluid flow. The bend region 5 is provided at the end portion 6 of the porous plate 2, and has a concave R-shape on an upstream side of the fluid flow.

The present invention relates to the auxiliary spare landing equipment for the aircraft to be used in the events of emergency landings. Each spare landing set consists of relatively small sized wheels; these sets are located at the bottom of the Aircraft, specifically in the centers of gravity on which the aircraft rests on the ground. The wheels are fully covered and concealed by airfoil casings to ensure efficient airflow and maintain optimal ratios during flights. The uniqueness of the present invention is in the casing of the gear which is designed in a manner of shatters and scatters upon impact with the ground while landing, whenever malfunction on the main landing system. In case of such malfunction, the aircraft initiates the landing process, resulting in casings to break upon hitting the runway, while the spare wheels appear and carry the aircraft.

The present invention relates to the auxiliary spare landing equipment for the aircraft to be used in the events of emergency landings. Each spare landing set consists of relatively small sized wheels; these sets are located at the bottom of the Aircraft, specifically in the centers of gravity on which the aircraft rests on the ground. The wheels are fully covered and concealed by airfoil casings to ensure efficient airflow and maintain optimal ratios during flights. The uniqueness of the present invention is in the casing of the gear which is designed in a manner of shatters and scatters upon impact with the ground while landing, whenever malfunction on the main landing system. In case of such malfunction, the aircraft initiates the landing process, resulting in casings to break upon hitting the runway, while the spare wheels appear and carry the aircraft.

Aspects related to aircraft for commercial air travel and methods of manufacture. An aircraft includes a blended wing body, a single deck located within the blended wing body, wherein the single deck additionally includes a passenger compartment located in a lateral middle portion of the blended wing body and at least a cargo store located laterally outside the passenger compartment, and a landing gear, wherein the landing gear includes at least a nose gear located substantially forward of the single deck and at least a main gear located substantially aft of the single deck, wherein one or more of the at least a nose gear and the at least a main gear occupies a gear housing that overlaps with a plane coincident with at least a portion of the single deck.

Aspects related to aircraft for commercial air travel and methods of manufacture. An aircraft includes a blended wing body, a single deck located within the blended wing body, wherein the single deck additionally includes a passenger compartment located in a lateral middle portion of the blended wing body and at least a cargo store located laterally outside the passenger compartment, and a landing gear, wherein the landing gear includes at least a nose gear located substantially forward of the single deck and at least a main gear located substantially aft of the single deck, wherein one or more of the at least a nose gear and the at least a main gear occupies a gear housing that overlaps with a plane coincident with at least a portion of the single deck.

An unmanned aerial vehicle (UAV) includes a body that supports one or more rotors, the one or more rotors each driven by a motor and configured to provide lift to the body. The UAV further includes a parts handler coupled to the body, the parts handler configured to grasp a payload, and rotate the payload with respect to an external structure to couple the payload to, or decouple the payload from, the external structure. The UAV includes a stabilizing mechanism extending from the body, the stabilizing mechanism configured to contact the external structure without transferring entire weight of the UAV to the external structure and prevent rotation of the body when the part-handler rotates the payload.

We describe an aircraft design, which is capable of vertical takeoff and landing and also high-speed cruise on a fixed wing. The aircraft comprises a fuselage with a probe-deployment mechanism, which deploys a sample-gathering probe, located at a front end of the fuselage. A main wing is coupled to a middle section of the fuselage, wherein a right motor and right propeller are coupled to a right side of the main wing, and a left motor and left propeller are coupled to a left side of the main wing. The right and left propellers are angled with respect to the fuselage enabling the aircraft to pitch up to a vertical-takeoff mode and pitch down a horizontal-cruising mode. A pitch motor and pitch propeller are located at the rear end of the fuselage, wherein the pitch propeller is angled to provide substantially vertical thrust to control a pitch of the fuselage.

A module includes two main landing gears and a landing gear bay containing the landing gears. The bay has two lateral walls, a roof wall, a front wall and a rear wall. The roof wall, the front wall and the rear wall together form a pressurization barrier between the bay and a pressurized compartment. By virtue of the landing gear module, it is now possible to assemble and test the main landing gears and the one or more doors and the fairing before they are installed on the aircraft.

A VTOL (vertical take-off and landing) box-wing aerial vehicle with multirotor to provide VTOL flight includes a detachable cabin, centered fuselage, a pair of first wings extending outward from the upper portion of the fuselage and a pair of second wings extending outwardly and from the lower portion of the fuselage. The first and second wings are spaced apart longitudinally and vertically. The pylon joints the first wing and second wing at the tip to form the box-wing. The pylon includes heading control rudder. Secured to the wing or pylon or both wing and pylon, an overhead boom extending longitudinally to support a plurality of lift rotors or tiltable rotors for VTOL flight. Finally, the fuselage mounted push rotor or the overhead boom mounted tiltable rotors propel the vehicle forward to generate lift from the wings. Furthermore, the wings are equipped with elevators and ailerons for flight control.

A coupled landing gear apparatus for an aircraft including at least a nose gear disposed forward of a neutral point of an aircraft by a first distance and at least a main gear disposed aft of the neutral point of the aircraft by a second distance. The at least a nose gear and the at least a main gear are in communication with one another.