Aerial vehicle for carrying a payload
The present specification relates generally to unmanned aerial vehicles, and specifically to a vertical take-off and lift unmanned aerial vehicle configured for high speed, long-distance flight, and vertical take-off and lift, while carrying a significant payload. The aerial vehicle includes a first propeller and a second propeller, each comprising at least two blades and each disposed on opposite lateral edges of the aerial vehicle; a tail segment forming a trailing edge of the aerial vehicle, wherein the tail segment comprises: an elevator; and a first wing and a second wing, each comprising an aileron. The aerial vehicle further includes four fins, wherein the four fins are affixed to lateral edges behind the first propeller or the second propeller and configured as endplates; a motor; and a power supply.
1. An aerial vehicle comprising:
a first propeller and a second propeller, each comprising at least two blades and each disposed on opposite lateral edges of a body;
a tail segment extending laterally from the first propeller to the second propeller and forming a trailing edge of the aerial vehicle, the tail segment including:
an elevator; and
a first wing and a second wing, each of the first wing and the second wing including an aileron;
four fins affixed to lateral edges of the first propeller and the second propeller aft of the blades of the first propeller and the second propeller and configured as endplates;
the body extending from the first propeller to the second propeller, the body being configured as a blown primary lifting surface to generate lift along an entire lateral extension between the first propeller and the second propeller;
a motor; and
a power supply.
2. The aerial vehicle of claim 1 , wherein the body includes a removable payload section forming a leading edge of the primary lifting surface.
3. The aerial vehicle of claim 2 , wherein the body is detachable from the first propeller and from the second propeller.
4. The aerial vehicle of claim 2 , wherein the removable payload section is configured to accommodate at least one directional fragmentation mine.
5. The aerial vehicle of claim 1 , wherein each of the fins are positioned to support the aerial vehicle in a tail-sitting configuration.
6. The aerial vehicle of claim 1 , wherein the motor and the power supply are housed in the first propeller or the second propeller.
7. The aerial vehicle of claim 1 , wherein the first propeller and the second propeller are detachably attached to the tail segment.
8. The aerial vehicle of claim 1 , wherein the first wing and the second wing each are back-swept wings.
9. The aerial vehicle of claim 1 , wherein two of the four fins are disposed on opposite faces of the first propeller and wherein another two of the four fins are disposed on opposite faces of the second propeller.
10. The aerial vehicle of claim 1 , wherein an aspect ratio of a wingspan of the aerial vehicle to the chord is less than 2.0.