6 results about "Forward-swept wing" patented technology

The invention discloses a vertical take-off and landing aircraft with improved linked wing tilting ducted fan layout, and belongs to the technical field of pneumatic and power systems of vertical take-off and landing aircrafts. The aircraft comprises an improved joined wing structure layout and a tilting ducted fan system integrally designed with the improved joined wing structure layout. The improved joined wing structure layout comprises a front wing, a rear wing, a vertical connecting wing surface, a vertical stabilizer and a fuselage. The front wing is divided into a front wing inner side wing surface and a front wing outer side wing surface by a vertical connecting wing surface, and adopts a sweepback wing belt dihedral structure; two ends of the rear wing are respectively arranged above the front wing through a vertical connecting wing surface, the middle part of the rear wing is arranged above the tail part of the fuselage through a vertical stabilizer, and the rear wing adopts a forward swept wing structure; the tilting ducted fan system comprises a front wing integrated ducted fan flap 7, a rear wing integrated ducted fan lifting control surface 9 and a tail propelling ducted fan 16. The core problems that pitching of a traditional connected wing is out of control, the weight of a tilting structure is large, and the energy efficiency is low are solved.

A vertical take-off and landing aircraft which uses fixed rotors for both VTOL and forward flight operations. Some of the rotors are forward canted, while some of the rotors are forward facing. The forward canted rotors are tilted forward slightly from vertical and provide some forward propulsion during horizontal flight. The forward facing rotors may be fixed in a forward facing configuration. Forward swept wings allow for rotor placement which brings efficiency during hover operations.

The invention relates to a novel wingtip winglet of an aircraft. The installation angle of the winglet is a forward swept wing, and the winglet is a dihedral winglet. Compared with other winglets, the novel winglet has more excellent aerodynamic characteristics, the vortex phenomenon of the wingtip of a large wing of an aircraft can be reduced, the resistance of the aircraft is reduced, and the lift force of the aircraft is increased.

The present application relates to a kind of horizontal axis fan blade, comprising: blade body, and winglet connected in the end of the blade body, winglet is extended from the windward surface of the blade body to form rear-swept wing structure or forward to extend and form front-swept wing structure, the outer surface of winglet is provided with the protruding portion of strip shape, which is generally along the chord length direction of the winglet extends.When the blade body rotates, the flow wind generates protruding vortex behind the protruding portion, and part of the flow appears backflow vortex, the two vortexes generate an induced velocity perpendicular to the winglet upward, the induced velocity makes the subsequent flow trajectory further spread in centrifugal direction, so that the flow pipe area behind the fan becomes larger.Using the protruding portion of strip shape as an example, which is generally along the chord length direction of the winglet, the flow wind to the fan generates an induced velocity in centrifugal direction when passing through the protruding portion, so that the flow pipe area behind the fan expands, thereby improving the wind energy utilization coefficient of the fan.

The utility model discloses a low-altitude and low-speed unmanned aerial vehicle with a sweepforward wing configuration and a wing body fusion layout. The low-altitude and low-speed unmanned aerial vehicle comprises main wings, a fuselage and an empennage, the main wing adopts a forward swept wing structure, so that spanwise flow is effectively weakened, and the wingtip airflow speed is increased; the main wings and the fuselage adopt a wing body fusion layout, redundant connecting mechanisms are reduced, the lift force of the unmanned aerial vehicle is effectively improved, turbulence is weakened, the lift-drag ratio is increased, and aerodynamic load distribution is improved; the fuselage is provided with a cabin and an equipment mounting platform, can be used for carrying power, control and monitoring equipment, and is suitable for various task requirements; the empennage is fixedly connected to the rear end of the fuselage; the main wing is provided with a motor and an aileron; the empennage is provided with a horizontal tail and vertical tails, the vertical tails are fixedly connected to two sides of the horizontal tail, and the rear ends of the horizontal tail and the vertical tails are hinged to an elevator and a rudder. The low-speed aerodynamic performance of the unmanned aerial vehicle is effectively improved, the aerodynamic load layout of the unmanned aerial vehicle is optimized, and the maneuverability and the loading capacity of the unmanned aerial vehicle are remarkably improved. The utility model is applied to the technical field of aircraft structures.

1. The name of the design product: unmanned aerial vehicle frame. 2. The use of the design product: unmanned aerial vehicle frame, namely unmanned aerial vehicle body frame main body. Take the whole body flat plate design. Take the integration design of forward swept wing and backward swept wing. 3. The design points of the design product: in shape. 4. The picture or photo that can best show the design points: perspective view.