Low-altitude low-speed unmanned aerial vehicle with sweepforward wing configuration and wing body fusion layout

By combining a forward-swept wing configuration with a blended wing-body layout, the problem of airflow separation in low-speed UAVs at low speeds and high angles of attack is solved, improving the lift-to-drag ratio and maneuverability, while also achieving lightweight design and enhancing the UAV's endurance.

CN223934991UActive Publication Date: 2026-02-24XI AN JIAOTONG UNIV
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Patent Information

Application Number
CN202520719897.7
Authority / Receiving Office
CN · China
Patent Type
Utility models(China)
Current Assignee / Owner
Filing Date
2025-04-16
Publication Date
2026-02-24
Estimated Expiration
2035-04-16

AI Technical Summary

Technical Problem

Traditional low-altitude, low-speed UAVs are prone to airflow separation and stall at low speeds and high angles of attack. Traditional wing-body separation structures result in excessive turbulence, uneven aerodynamic load distribution, and low lift-to-drag ratio, making it difficult to achieve a balance between lightweight design and high maneuverability.

Method used

It adopts a forward-swept wing configuration and a blended wing-body layout, with the main wing and fuselage forming an integrated lifting body design. It uses carbon fiber and linden wood composite materials, combined with a carbon fiber rod support structure, to optimize aerodynamic performance and enhance structural strength.

Benefits of technology

It effectively suppresses airflow separation, improves lift-to-drag ratio, reduces structural redundancy, achieves lightweight design, and enhances maneuverability and range.

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Abstract

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.
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