Blended wing body tailsitter UAV
The present disclosure relates to an aircraft including two or more propulsive devices, and a fuselage integrated with a pair of wings to create a Blended Wing Body (BWB) structure, wherein an orientation of the fuselage and the pair of wings change based on a transition of the aircraft from a vertical position to a horizontal position. Further, each wing of the pair of wings includes a lower winglet and an upper winglet that are identical and coupled to each other at a wing tip. The aircraft further includes a plurality of elevons controlled by two or more propellers associated with the two or more propulsive devices.
1 . An aircraft comprising:
an airframe including
two or more propellers; a pair of wings; and
a fuselage integrated with the pair of wings to create a Blended Wing Body (BWB) structure having a smoothly blended shape between the fuselage and the pair of wings, wherein the airframe transitions in flight between a vertical flight mode and a horizontal flight mode, wherein the BWB structure is designed such that over fifty percent of lift is generated from the fuselage of the BWB structure to allow for a reduction of a size of the pair of wings with respect to a size of the fuselage.
2 . The aircraft of claim 1 , wherein the pair of wings comprises split scimitar wmgs.
3 . The aircraft of claim 1 further comprises a pair of flaps coupled to the fuselage, wherein the pair of flaps is designed to facilitate at least one of take-off, landing, cargo securement, and a cargo release operation.
4 . The aircraft of claim 1 , further comprises a plurality of elevons, wherein rotations of the propellers control the plurality of elevons to generate a thrust vector to maintain a stability of the aircraft and transitioning the aircraft from a vertical position to a horizontal position.
5 . The aircraft of claim 3 , wherein the pair of flaps exhibits two positions, comprising an extended position and a retracted position.
6 . The aircraft of claim 5 , wherein the pair of flaps is configured to be in the retracted position during take-off and landing, ensuring ground clearance during landing and maintaining a spaced-apart position to prevent contact between the flaps.
7 . The aircraft of claim 5 , wherein the pair of flaps, when in the extended position, protrudes vertically below the pair of wings.
8 . The aircraft of claim 6 , wherein the pair of flaps is configured to be in the extended position when the aircraft is in a horizontal position.
9 . The aircraft of claim 5 , wherein positions of the pair of flaps is controlled by a linkage connected to one or more servo motor.
10 . The aircraft of claim 1 is further configured to function as a tailsitter during vertical take-off and landing.
11 . The aircraft of claim 1 , wherein a wing of the pair of wings comprises a lower winglet and an upper winglet, wherein the lower winglet and the upper winglet are identical, and the lower winglet is attached to the upper winglet at a tip of the wing.
12 . The aircraft of claim 11 , wherein the lower winglet and the upper winglet carry at least sixty percent of a total weight of the aircraft in a vertical position.
13 . The aircraft of claim 1 , wherein the two or more propellers comprise a torque multiplier, wherein the torque multiplier is controlled by one or more servo motors.
14 . An airframe for an aircraft, the airframe comprising:
a fuselage integrated with a pair of wings to create a Blended Wing Body (BWB) structure; and
a pair of flaps coupled to the fuselage, wherein the pair of flaps is designed to facilitate at least one of take-off, landing, cargo securement, and a cargo release operation, wherein the pair of flaps exhibits two positions, comprising an extended position and a retracted position, and wherein the pair of flaps is configured to be in the retracted position during take-off and landing, ensuring ground clearance during landing and maintaining a spaced-apart position to prevent contact between the flaps; and
two or more propellers, wherein the airframe transitions in flight between a vertical flight mode and a horizontal flight mode.
15 . The airframe of claim 14 , wherein a wing of the pair of wings comprises:
a lower winglet and an upper winglet, wherein the lower winglet and the upper winglet are identical, and the lower winglet is attached to the upper winglet at a tip of the wing.
16 . The airframe of claim 14 , further comprise a plurality of elevons coupled to the airframe.
17 . The airframe of claim 14 is further constructed from a composite monocoque, utilizing fiber-reinforced plastic (FRP) materials like carbon fiber, aramid, or fiberglass embedded in a resin matrix.
18 . The airframe of claim 17 , wherein the composite monocoque is reinforced by an internal structure comprising ribs and spars to improve rigidity.
19 . An airframe for an aircraft, the airframe comprising:
a fuselage integrated with a pair of wings to create a Blended Wing Body (BWB) structure; and
a pair of flaps coupled to the fuselage; and
two or more propellers, wherein the airframe transitions in flight between a vertical flight mode and a horizontal flight mode, wherein the BWB structure is designed such that over fifty percent of lift is generated from the fuselage of the BWB structure.
20 . The airframe of claim 19 , wherein the pair of flaps is designed to facilitate at least one of take-off, landing, cargo securement, and a cargo release operation, wherein the pair of flaps exhibits two positions, comprising an extended position and a retracted position, and wherein the pair of flaps is configured to be in the retracted position during take-off and landing, ensuring ground clearance during landing and maintaining a spaced-apart position to prevent contact between the flaps.