CN-224211283-U - Unmanned aerial vehicle pneumatic layout and unmanned aerial vehicle

CN224211283UCN 224211283 UCN224211283 UCN 224211283UCN-224211283-U

Abstract

The utility model discloses a pneumatic layout of an unmanned aerial vehicle, which comprises a fuselage, wings and a tail wing, wherein the wings are arranged on the fuselage, the tail wing is connected with the wings, the wings comprise a middle wing, an outer wing and wing tip winglets, the middle wing is connected to the upper end of the middle part of the fuselage, the outer wings are symmetrically arranged on two sides of the middle wing, the wing tip winglets are arranged on the edges of the outer wings, the plane shape of the middle wing is rectangular, the plane shape of the outer wing is trapezoid, the sweepback angles of 1/4 chord lines of the middle wing and the outer wing are both 0 degrees, the dihedral angle of the middle wing is 0 degree, the dihedral angle of the outer wing is 0.5 degrees, and the tail wing comprises a vertical tail and a horizontal tail, and the vertical tail is connected to the wings and is arranged behind the fuselage. The combined design of the specific structures of the rectangular middle wing and the trapezoid outer wing can form a stable laminar flow field in a low-speed cruising state, the trapezoid design of the outer wing enables span load distribution to be in an elliptical trend, and the design of the wing tip winglet structure can reduce the generation of induced resistance, and the design that sweep angles are all 0 degrees eliminates additional resistance brought by the sweep angles.

Inventors

CHEN BIAO
XU LEI
ZHAO YONGFEI
LIU LUANMIN
DAI YUNLONG
CHEN XIANG

Assignees

扬州金航达航空智能科技有限公司

Dates

Publication Date: 20260508
Application Date: 20250522

Claims (5)

1. The utility model provides a unmanned aerial vehicle pneumatic layout which characterized in that includes: a body; The wing comprises a middle wing, an outer wing and a wing tip winglet, wherein the middle wing is connected to the upper end of the middle part of the fuselage, the outer wings are symmetrically arranged on two sides of the middle wing, the wing tip winglet is arranged at the edge of the outer wing, the plane shape of the middle wing is rectangular, the plane shape of the outer wing is trapezoid, the sweepback angles of 1/4 chord lines of the middle wing and the outer wing are 0 degrees, the dihedral angle of the middle wing is 0 degree, and the dihedral angle of the outer wing is 0.5 degrees; the tail wing comprises a vertical tail and a horizontal tail, wherein the vertical tail is connected to the wing and arranged behind the fuselage.
2. The unmanned aerial vehicle aerodynamic layout of claim 1, further comprising landing gear cabins and connecting pipes, wherein the landing gear cabins are connected below two sides of the middle wing, the connecting pipes are connected to the rear ends of the landing gear cabins, and the tail wings are mounted to the rear ends of the connecting pipes.
3. The unmanned aerial vehicle aerodynamic layout of claim 1, wherein the outer wing is fitted with a flap, aileron, the vertical tail is fitted with a rudder, and the horizontal tail is fitted with an elevator.
4. The unmanned aerial vehicle aerodynamic layout of claim 1, wherein the pigtail is disposed at the pigtail upper end such that the pigtail is located above the rear end of the unmanned aerial vehicle propeller.
5. A drone comprising the drone aerodynamic layout of any one of claims 1-4.

Description

Unmanned aerial vehicle pneumatic layout and unmanned aerial vehicle Technical Field The utility model relates to the technical field of unmanned aerial vehicles, in particular to a pneumatic layout of an unmanned aerial vehicle. Background Unmanned aerial vehicle is unmanned aircraft that utilizes wireless remote control or autonomous program control flight, and by virtue of its advantages such as nimble deployment, low cost and low risk, it has extensively penetrated to many fields such as military reconnaissance, disaster monitoring, geographical survey, express delivery transportation. Along with the complicating of application scene, put forward higher requirement to unmanned aerial vehicle's duration, load efficiency and environmental suitability, impel the aircraft design to high efficiency and multi-functional orientation evolution. Pneumatic layout is used as a core link of unmanned aerial vehicle design, and aerodynamic performance of the aircraft is directly determined by defining geometric configurations and relative position relations of components such as a fuselage, wings, a tail wing and the like. The reasonable aerodynamic layout can optimize lift force generation, reduce flight resistance, enhance control stability, influence structural weight distribution and task load configuration, and is a key technical foundation for improving comprehensive flight efficiency of the unmanned aerial vehicle. Disclosure of utility model The application provides a pneumatic layout of an unmanned aerial vehicle, which enables the unmanned aerial vehicle to have good flight performance. The application also provides an unmanned aerial vehicle, and the pneumatic layout of the unmanned aerial vehicle is adopted. The first aspect of the application provides a pneumatic layout of a unmanned aerial vehicle, comprising: a body; The wing comprises a middle wing, an outer wing and a wing tip winglet, wherein the middle wing is connected to the upper end of the middle part of the fuselage, the outer wings are symmetrically arranged on two sides of the middle wing, the wing tip winglet is arranged at the edge of the outer wing, the plane shape of the middle wing is rectangular, the plane shape of the outer wing is trapezoid, the sweepback angles of 1/4 chord lines of the middle wing and the outer wing are 0 degrees, the dihedral angle of the middle wing is 0 degree, and the dihedral angle of the outer wing is 0.5 degrees; the tail wing comprises a vertical tail and a horizontal tail, wherein the vertical tail is connected to the wing and arranged behind the fuselage. The embodiment has the beneficial effects that the combined design of the specific structures of the rectangular middle wing and the trapezoid outer wing can form a stable laminar flow field in a low-speed cruising state, the trapezoid design of the outer wing enables span load distribution to be in an elliptical trend, the design of the wing tip winglet structure is combined, the generation of induced resistance can be reduced, the sweepback angles are all 0-degree designs, the additional resistance caused by the sweepback angles is eliminated, meanwhile, the structural complexity is simplified by 0-degree dihedral angles, the additional torque caused by asymmetric load is avoided, the structural design of the dihedral angles can improve the lateral stability and the lateral wind resistance, and experiments prove that the unmanned aerial vehicle has good lift performance and flight performance. On the basis of the above embodiment, the embodiment of the present application may be further modified as follows: In one embodiment of the application, the aircraft further comprises a landing gear cabin and a connecting pipe, wherein the landing gear cabin is connected below two sides of the middle wing, the rear end of the landing gear cabin is connected with the connecting pipe, and the tail wing is arranged at the rear end of the connecting pipe. The landing gear cabin has the beneficial effects that the landing gear cabin is integrated below the middle wing, and through the cabin accommodating design, the landing gear is prevented from being exposed, so that parasitic resistance is reduced, and a streamline transition structure formed by the connecting pipes can guide the tail flow of the middle wing to be smoothly transited to the tail wing, so that the pneumatic efficiency is optimized. In one embodiment of the application, the outer wing is provided with a flap and an aileron, the vertical tail is provided with a rudder, and the horizontal tail is provided with an elevator. In one embodiment of the application, the horizontal tail is arranged at the upper end of the vertical tail, so that the horizontal tail is positioned above the rear end of the unmanned aerial vehicle propeller. The method has the beneficial effect of avoiding the slip flow area of the propeller. The second aspect of the application provides a unmanned aerial vehicle, comprising the