Embraer S.a.

Eve Uam, LLC

Other

Alberto Dei Castelli

Wanderley Montoro

Clovis Augusto Eça Ferreira

Rodrigo Takashi Lourenco Kawasaki

Yasser Mahmud Abdallah

Igor Miranda Rodrigues

Ricardo Takeshi Demizu

Luiz Felipe Ribeiro Valentini

Rafael Desideri De Freitas

Fernando Rodrigues Vianna

Marcelo Nogueira

Fabio Zaroni

Flavia Renata Dantas Alves Silva

Adilson Melo

Felipe Nahime Cursino

Julio Cesar Graves

Julio Antonio Beltrami Da Silva

Cleber Soares

Rafael Estefano Reis Cleto

Vinicius Magalhaes Cunha

Thalerson Augusto Mortari Alves

Geraldo Carvalho

Aldemiro Lorenzini Filho

Jose Roberto Ferreira De Camargo Clark Reis

José Darci Flor Junior

José Darci Flor, Jr

Luiz Antonio Madeira, Jr

Carlos Alberto Bones, Jr

Rodrigo Takashi Lourenço Kawasaki

Juliano De Oliveira

Luiz Antonio Madeira Junior

Vasser Mahmud Abdallah

Vertical takeoff and landing (VTOL) aircraft, especially electric VTOL (e-VTOL) aircraft include a fuselage (which may include a pair of ground-engaging skids) defining a longitudinal axis of the aircraft, forward and aft pairs of port and starboard aerodynamic wings extending laterally outwardly from the fuselage and forward and aft pairs of port and starboard rotor pods each being in substantial alignment with the longitudinal axis of the fuselage. In specific embodiments, each of the forward and aft pairs of port and starboard rotor pods comprises a forward and aft pair of rotor assemblies.

Vertical take-off and landing (VTOL) aircraft

Vertical take-off and landing (VTOL) aircraft include a fuselage having a center of gravity (CG) and defining mutually orthogonal X-, Y- and Z-axes. An even number of positionally mirror imaged port and starboard side rotors are provided laterally of the fuselage in spaced relationship to a plane established by the XZ axes while an even number of fuselage rotors are positioned along an X-axis centerline of the fuselage. Improved stability during failure of an engine/motor/rotor is achieved by causing one-half of the side rotors to rotate in one direction about the Z-axis and a remaining one-half of the side rotors rotate in a counter direction relative thereto, while one-half of the fuselage rotors rotate in one direction about the Z-axis and a remaining one-half of the fuselage rotors rotated in a counter direction relative thereto.

Vertical take-off and landing (VTOL) aircraft with rotor configurations tolerant to rotor failure

A hovercraft including imaginary longitudinal, transverse and vertical axes; a propulsion system (), configured to generate airflow; a base () and, a skirt () wherein the skirt () further including air permeable regions () and at least two set of outflow nozzles (); wherein the air permeable regions () and the set of outflow nozzles () are in fluid communication; wherein each set of nozzles () comprises, at least, one outflow nozzle (), said outflow nozzle () including two opposing ends, a first end () and a second end (); the hovercraft further including actuating means () suitable to control the opening of at least one end (or) of the nozzles () managing the passage of airflow through the end (or). The technical features and functionalities described herein are applicable to the field of hovercrafts. More particularly, to controllable outflow nozzles and controlling systems for hovercrafts.

Nozzles and control systems for hovercrafts

Vertical take-off and landing craft

Pylon mounting assemblies are provided for mounting an engine (e.g., a turbojet engine) to a wing of an aircraft. The pylon mounting assemblies include an upper pylon connection member, and a lower pylon connection box, wherein the upper pylon connection member and the lower pylon connection box respectively include multiple opposed pairs of connection lobes. At least one pair of the connection lobes includes a pin connection to restrict degrees of freedom thereat along an x-axis and a mutually perpendicular z-axis, while at least one other pair of connection lobes includes a connection rod to restrict degrees of freedom thereat along the z-axis.

Aircraft engine pylon to wing mounting assembly

It is described a movable pylon, associated with a lower portion of aircraft wing and with an aircraft engine to change the height of this engine between a flying position and a ground position, the movable pylon comprising: a main unique structure formed by a first movable structure pivoted to a second fixed structure, the first movable structure associated with the engine, the second fixed structure associated with the wing, and a pivot mechanism connecting the first movable structure to at least one point on the wing.

Movable pylon

Pylon mounting assemblies are provided for mounting an engine (e.g., a turbojet engine) to a wing of an aircraft. The pylon mounting assemblies include an upper pylon connection member, and a lower pylon connection box. The upper pylon connection member and the lower pylon connection box respectively define opposed lower and upper mounting surfaces which establish a mounting plane that slopes downwardly and rearwardly relative to aircraft travel direction. At least one connector assembly connects the upper pylon connection member and a lower pylon connection box to one another at the opposed respective lower and upper mounting surfaces thereof.

Growing community of inventors

São Paulo, Brazil

Alberto Dei Castelli