A vertical take-off and landing aircraft including a propulsion mechanism 2 that generates lift and thrust, a main frame 4 that supports seating 41 and a landing undercarriage 42, a subframe 5 which supports the propulsion mechanism 2 and which is arranged so as to be swingable back and forth relative to the main frame 4, motive power supply means 3 supported by the main frame 4 and supplying motive power to the propulsion mechanism 2, and a control stick 6 connected to the subframe 5, in which the propulsion mechanism 2 includes a pair of ducted fans 21L, 21R arranged on a left side and a right side, respectively, of the main frame 4, swing shafts 22 arranged in the ducted fans 21L, 21R and extending in a horizontal direction, and control vanes 23 connected to the swing shafts 22, and swinging the control vane 23 enables the subframe 5 to move relative to the main frame 4. Maneuverability can be improved with addition of control mechanisms restrained.

Embodiments of the present invention provide an aircraft (200) for vertical take-off and landing. In various embodiments, an aircraft assembly includes at least one first wing portion (210) providing a lift force during a horizontal flight, at least one wing opening disposed on a vertical axis of the at least one first wing portion (210) and at least one thruster (240) positioned inside the at least one wing opening to provide vertical thrust during a vertical flight. The aircraft assembly can further include air vents (2030) positioned inside at least one of the wing openings. The air vents can further include louvres (2040) positioned over or under the air vents (2030) to open and close the wing openings. The thruster can further be used to provide flight control for the aircraft.

The invention relates to a remotely controlled vertical take-off device comprising at least one control unit (1) to which driving arms (3) are joined, wherein the at least one control unit accommodates the supply and control means of the driving arms, while the driving arms (3) comprise a structural element having one or a number of motors mounted on same, on which propellers (4) are mounted, wherein the driving arms (3) can be removed and replaced by another combination of driving arms having different functional or constructive characteristics to the previous driving arms, and the control means act according to the functional or constructive characteristics of the driving arms. As a result of the means according to the invention, the devices can be provided with an increased multi-functionality and versatility, given that, with a single device and different combinations of driving arms, the device can be used in different environmental conditions and with different types of cargo.

The invention relates to aviation technology, specifically to vertical take-off and landing aircraft. The vertical take-off and landing aircraft comprises two turbines, the lower of which is of plate-like shape, and the upper is of flat or plate-like shape. Each turbine comprises a reactive power plant. The body of each turbine is mounted on a metallic disc connected to a vertical shaft of the aircraft, and is equipped with vanes. The vanes are mounted such that the position thereof can be changed. The aircraft can comprise intermediate turbines which are mounted between the upper and lower turbine and are flat or plate-like. The reactive power plant of each turbine comprises an air engine and receivers which are connected to a compressor. The body of each turbine is metallic and comprises two rings, one of which is connected to the disc, and also radial struts which are mounted along the perimeter of the turbine body and are connected to the rings and vanes. The vanes are mounted in a single row along the perimeter of the body or are arranged in a single tier. The result is an increase in the reliability and economy of the aircraft, and the possibility of the latter moving vertically, horizontally or at any inclination.

L'aérodyne à décollage et atterrissage verticaux selon l'invention comprend deux hélices droite et gauche (37) portées chacune par une nacelle (33, 35), et un moyen de commande de roulis à la disposition du pilote. Les nacelles sont montées de façon pivotante pour s'incliner entre des orientations verticale et horizontale, chaque hélice incluant des moyens pour faire varier son pas de façon cyclique suivant l'azimut latéral.

Cet aérodyne est caractérisé en ce que le moyen de commande de roulis constitue l'unique gouverne de roulis et est relié de façon antisymétrique aux moyens de variation cyclique latérale du pas des pales, quelle que soit l'inclinaison des nacelles (33,35), et en ce que le sens de rotation des hélices est le sens supradivergent dans lequel l'hélice droite tourne dans le sens horaire tandis que l'hélice gauche tourne dans le sens antihoraire, l'action en roulis des composantes radiales cycliques des forces aérodynamiques sur les pales étant ainsi dans le même sens que celle des composantes axiales et s'y ajoutant puis s'y substituant à mesure que l'inclinaison des nacelles passe de la verticale à l'horizontale.

Senkrecht startender und landender und in jede Richtung steuerbarer Fliehkraftring in torus­ähnlicher Form mit mittiger Aufnahme von Transport­kapseln für die Fortbewegung in einem beliebigen Medium, bestehend aus übereinander oder inein­ander angeordneten Kreisringschalen, die in einem Abstand konzentrisch um eine Mittelachse rotieren, wobei jede Kreisringschale für sich aus, auf einem Kreisring nebeneinander angeordneten, über Separator­ring (4) und Lagerringe miteinander verbundenen, Verdichter- (1) und Turbinenschaufeln (2) besteht. und die ein oder mehrere Energieaggregate haben, die die Kreisringschalen antreiben, so daß das umgebende Medium von den Kreisringschalen aufgenommen, be­schleunigt und über Düsen (10) ausgestoßen wird, wobei der Fliehkraftring selbst gegenüber der Mittel­achse mittels einer elektronisch gesteuerten Brems­anlage (14) an den gegenläufigen Schalen oder über Düsen oder über eine ausladende Drehmomentstütze drehstabil gehalten wird.

A vertical take-off and landing aircraft includes a propulsion mechanism 2 that generates lift and thrust, a main frame 4 that supports seating 41 and a landing undercarriage 42, a sub-frame 5 which supports the propulsion mechanism 2 and is arranged so as to be swingable back and forth relative to the main frame 4, a motive power supply unit 3 supported by the main frame 4 and supplying motive power to the propulsion mechanism 2, a control stick 6 connected to the sub-frame 5, and a main wing 7 arranged on the propulsion mechanism 2, wherein the main wing 7 is formed to be retracted to a position not interfering with an air flow of the propulsion mechanism 2 in a normal time and to be movable to a position where lift is generated when thrust is lost. Gliding is made possible even if thrust is lost while increasing in size of a fuselage is avoided.