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Patent

Configuration for vertical take-off and landing system for aerial vehicles

10 Mar 2017-
TL;DR: In this article, a vehicle is coupled to a main body and a fluid generator, and at least one fore and one tail conduit are fluidly coupled to the generator and the primary airfoil element.
Abstract: A vehicle, includes a main body. A fluid generator is coupled to the main body and produces a fluid stream. At least one fore conduit and at least one tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the fore conduit, 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 is coupled to the tail portion. A surface of the primary airfoil element is located directly downstream of the first and second fore ejectors such that the fluid from the first and second fore ejectors flows over the such surface.
Citations
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Patent
27 Jul 2016
TL;DR: In this article, a propulsion system coupled to a vehicle is described, which consists of a convex surface, a diffusing structure coupled to the convex surfaces, and at least one conduit coupled with the vehicle.
Abstract: A propulsion system coupled to a vehicle. The system includes a convex surface, a diffusing structure coupled to the convex surface, and at least one conduit coupled to the convex surface. The conduit is configured to introduce to the convex surface a primary fluid produced by the vehicle. The system further includes an intake structure coupled to the convex surface and configured to introduce to the diffusing structure a secondary fluid accessible to the vehicle. The diffusing structure comprises a terminal end configured to provide egress from the system for the introduced primary fluid and secondary fluid.

5 citations

Patent
27 Jul 2016
TL;DR: In this paper, a propulsion system coupled to a vehicle is described, which includes an ejector having an outlet structure out of which propulsive fluid flows at a predetermined adjustable velocity.
Abstract: A propulsion system coupled to a vehicle. The system includes an ejector having an outlet structure out of which propulsive fluid flows at a predetermined adjustable velocity. A control surface having a leading edge is located directly downstream of the outlet structure such that propulsive fluid from the ejector flows over the control surface.

2 citations

Patent
03 Mar 2020

1 citations

Patent
18 Oct 2016
TL;DR: In this paper, a drone with a wind guide, including a body, a single central inlet unit accommodated in the body, and configured to introduce wind therein, at least two pairs of wind guides, and at least four connecting ducts.
Abstract: The present disclosure relates to a drone with a wind guide, including a body, a single central inlet unit accommodated in the body, and configured to introduce wind therein, at least two pairs of wind guides, and at least four connecting ducts. Each wind guide is spaced apart from the body, and each connecting duct is connected with a respective wind guide of the at least two pairs of wind guides. The connecting duct is configured to transmit the wind introduced from the single central inlet unit to the connected respective wind guide.
References
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Patent
Koichiro Jinnai1, Masanori Horike1
16 Jun 1982
TL;DR: In this article, the authors present an ink-jet printer with two modes of operation: deflection error compensation mode and printing mode, in which interactive effects with other ink droplets are compensated as well.
Abstract: The present ink-jet printer is of the type in which ink droplets are charged under control and deflected by passing through an electric field, and it has two modes of operation: deflection error compensation mode and printing mode. In accordance with the present invention, deflection error is first compensated to determine an optimum amplification gain, which is then used in the printing operation, in which interactive effects with other ink droplets are compensated as well.

226 citations

Patent
11 Sep 2002
TL;DR: A personal aircraft capable of vertical take-off and landing (VTOL) comprises a fixed wing and a fuselage with a passenger compartment having a front, a rear and two sides, and a plurality of independently powered thrusters, preferably integrated into the wing, on each side of the fuselage as mentioned in this paper.
Abstract: A personal aircraft (PAC) capable of vertical take-off and landing (VTOL) comprises a fixed wing and a fuselage with a passenger compartment having a front, a rear and two sides, and a plurality of independently powered thrusters, preferably integrated into the wing, on each side of the fuselage. The aircraft has a lift to drag ratio equal to or greater than 2. The thrusters, which are ducted fan units capable of providing a vertically upward force to the aircraft, are provided with such redundancy that the aircraft can hover with at one thruster inoperative on each side of the fuselage. At least one thruster on each side of the fuselage preferably comprises a “levitator” which creates lift from the airfoil-like air inlet as well as from the acceleration of air from inlet to outlet.

223 citations

Journal ArticleDOI
TL;DR: In this paper, various conventional and novel means of boundary layer and flow control applied to moderate-to-large aspect ratio wings, delta wings and bodies with the specific objectives of drag reduction, lift enhancement, separation suppression and the improvement of air-vehicle control effectiveness are discussed.

204 citations

Patent
24 Jan 2011
TL;DR: In this article, a fixed wing Vertical Take-Off and Landing (VTOL) aircraft for use as a Personal Air Vehicle (PAV) or unmanned vehicle is presented, where a double-ended drive shaft engine is mounted sideways in the front of the fuselage to serve a first pair of ducted fans mounted at the ends of the front wing.
Abstract: A fixed wing Vertical Take-Off and Landing (VTOL) aircraft for use as a Personal Air Vehicle (PAV) or unmanned vehicle. A first double-ended drive shaft engine is mounted sideways in the front of the fuselage to serve a first pair of ducted fans mounted at the ends of the front wing. A second double-ended drive shaft engine is mounted sideways in the rear of the fuselage to serve a second pair of ducted fans mounted on the rear fuselage. The ducted fans are rotatable from a horizontal orientation to a vertical orientation to permit the aircraft to take off and land as a VTOL or conventional aircraft, and to be flown as a conventional aircraft. A parachute is provided with inflation assistance to permit rapid low altitude deployment for a controlled descent of the aircraft in an emergency.

186 citations

Patent
31 Oct 2002
TL;DR: In this paper, a vertical takeoff and landing (VTOL) aircraft is constructed with turbofan engines with separate core engines with biaxial support so that the fan engines are rotatable in the direction of pitching and rolling.
Abstract: A vertical takeoff and landing (VTOL) aircraft is superior in maneuverability, safety, and mobility. The aircraft has turbofan engines with separate core engines having fan engines used commonly for cruising and lifting up. The thrust from the fan engines can be directed to all directions by supporting the fan engines of the turbofan engines with separate core engines with biaxial support so that the fan engines are rotatable in the direction of pitching and rolling. The fan engines are mounted on both sides of each of front and rear sings. With this construction, the VTOL aircraft can cruise and hover by tilting the fan engines about the two axes while using the fan engines commonly for cruising and hovering.

180 citations