US 2026/0249989 A1Published application

Advanced V/STOL Aircraft with Lip-Wing Blended Body Configuration

OwnerDusan Milivoi Staninventor

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Abstract

The present invention introduces a vertical/short takeoff and landing (V/STOL) aircraft with a lip-wing blended body configuration, enhancing aerodynamic performance, control, stability, and redundancy. A key innovation is the blended-lip-wing, which enhances aerodynamic surfaces for improved lift and efficiency during hover, transition, and enabling optimized thrust-providing devices for wing-borne level flight. A coupling mechanism adjusts the thrust-providing devices, positioning its inflow region adjacent to the blended-lip-wing, optimizing hover lift and flight transition. The thrust-providing devices are mounted on aerodynamically shaped support structures that also function as control surfaces, integrating vectored thrust for simplified control, enhancing maneuverability, authority, and redundancy. A sophisticated control system dynamically adjusts thrust and aerodynamic controls for stability, maneuverability, and redundancy. This aircraft achieves a unique balance of hover efficiency, cruise performance, and flight stability, making it ideal for military, commercial, and emergency applications.

Claims15

Dependent claims

1) An aircraft comprising:

a) a fuselage with a blended wing-body configuration;
b) at least one pair of wings positioned on opposite sides of the fuselage, each wing comprising:
i) at least one thrust-providing device, the thrust-providing device comprising:
a propulsion device comprising a propeller, rotor, fan, or equivalent air-accelerating mechanism, the propulsion device including an inflow region;
and
a power source configured to drive the propulsion device, the power source comprising an electric motor, internal combustion engine, or other device configured to supply power;
ii) a coupling and adjustment mechanism, the coupling and adjustment mechanism comprising at least one bearing, joint, or similar pivoting device, and an actuator configured to provide controlled rotation or repositioning, the coupling and adjustment mechanism configured to modify the position and orientation of the thrust-providing device;
and
iii) an aerodynamic structure comprising a section of the wing and a portion of the fuselage, the aerodynamic structure comprising a channel having a predetermined curvature configured to aerodynamically conform to the inflow region to capture, accelerate, direct, and enhance airflow toward the inflow region, wherein the coupling and adjustment mechanism is operable to position the thrust-providing device to a predetermined orientation, such that the inflow region is substantially adjacent to the aerodynamic structure, and the predetermined orientation of the thrust-providing device and the predetermined curvature of the aerodynamic structure are cooperatively configured to optimize thrust augmentation during hover and low-speed flight.

6 more elements

9) A method for augmenting performance and enhancing control authority of an aircraft having a blended wing-body fuselage and at least one pair of wings positioned on opposite sides of the aircraft, comprising the steps of:

a) providing each wing with:
i) at least one thrust-providing device, the thrust-providing device comprising:
a propulsion device, the propulsion device comprising a propeller, rotor, fan, or other air-accelerating mechanism, the propulsion device including an inflow region;
and
a power source configured to drive the propulsion device, the power source comprising an electric motor, internal combustion engine, or other device configured to supply power;
ii) a coupling and adjustment mechanism, the coupling and adjustment mechanism comprising at least one bearing, joint, or similar pivoting device, and an actuator configured to provide controlled rotation or repositioning, the coupling and adjustment mechanism configured to modify the position and orientation of the thrust-providing device;
and
iii) an aerodynamic structure comprising a section of the wing and a portion of the fuselage, the aerodynamic structure comprising a channel having a predetermined curvature configured to aerodynamically conform to the inflow region to capture, accelerate, direct, and enhance airflow toward the inflow region;
wherein the coupling and adjustment mechanism is operable to position the thrust-providing device to a predetermined orientation, such that the inflow region is substantially adjacent to the aerodynamic structure, and the predetermined orientation of the thrust-providing device and the predetermined curvature of the aerodynamic structure are cooperatively configured to optimize hover thrust augmentation;
and
b) providing a control system, configured to individually adjust each coupling and adjustment mechanism.

8 more elements

Dependencies are inferred from the claim text.