3 results about "Biplane" patented technology

The application discloses a kind of double-body aircraft's capture trajectory wind tunnel test method, the purpose is to establish simulation in wind tunnel launch weapon from double-body aircraft separation capture trajectory test capability, belong to wind tunnel test technical field.This method includes: using tail support rod and balance to support launch weapon in six-degree-of-freedom mechanism, using double balance and double tail support to support double-body aircraft in half-arm angle of attack mechanism.According to the mass ratio of double-body aircraft and launch weapon, determine to solve six-degree-of-freedom equation for single body (launch weapon) or two bodies (launch weapon and double-body aircraft).Through the motion of six-degree-of-freedom mechanism, realize the displacement and attitude angle of launch weapon, and carry out motion compensation to the displacement of double-body aircraft, realize the pitching motion of double-body aircraft by moving half-arm angle of attack mechanism.This method has the advantages of wide simulation range, high simulation data accuracy and reliable data.

1. The name of the design product: wing gate double-wing movement (link extension mechanism). 2. The use of the design product: wing gate movement for access control barrier. 3. The design points of the design product: in shape. 4. The picture or photo that best indicates the design points: perspective view 1.

This invention relates to a small tandem biplane unmanned aerial vehicle (UAV) configuration with ducted thrust reduction at the wingtip, comprising: a fuselage; a main wing fixedly connected to the middle or front of the fuselage; a horizontal tail fixedly connected to the rear of the fuselage, arranged in tandem with the main wing; and a ducted propulsion unit disposed at the wingtip of the main wing and / or the horizontal tail, the ducted propulsion unit comprising a duct body, ducted blades rotatably disposed within the duct body, and a motor for driving the ducted blades to rotate; wherein the axial direction of the duct body extends in the same direction as the average incoming flow direction at the corresponding wingtip. This invention solves the problems of wingtip drag reduction, propulsion efficiency, and structural adaptability in existing small tandem biplane UAVs, achieving synergistic effects of drag reduction and propulsion, and improving aerodynamic efficiency, endurance, and flight safety.