Multi-element lifting system with integrated propulsion and aircraft using same
A vertical take-off and landing aircraft with a multi-element lifting system with integrated propulsion. The multi-element lifting system may have an upper wing element, a lower wing element, and a control wing element which is located below the upper wing element and above, and rearward of, the lower wing element. The system uses internal propulsion units, such as internal ducted fans, which flow air below the upper wing element and above the lower wing element such that the air flows through the multi-element lifting system. The control wing element may be articulated to route air vertically downward to allow for short or vertical take-off and landing. An aircraft with a multi-element wing assembly and a multi-element tail assembly raised above the wing assembly. An aircraft which resides on the ground with the wing assembly and the tail assembly pitched up.
1. An aerial vehicle comprising a first wing assembly, said first wing assembly comprising:
an upper wing element;
a lower wing element, said lower element residing below said upper wing element;
a plurality of airflow segments, said airflow segments coupled to said upper wing element on an upper end, said airflow segments coupled to said lower wing segment on a lower end, said airflow segments forming a first airflow passage below said upper wing element and above said lower wing element at a forward end of said airflow segments;
a plurality of thrust units, said thrust units residing in said airflow segments; and
one or more control wing segments, said control wing segments deployable from a forward flight configuration to a vertical flight configuration, said control wing segments residing below said upper wing element and rearward of said lower wing element wherein said first airflow passage at the forward end of said airflow segments splits into a second airflow passage above said control wing segments and below said upper wing element, and a third airflow passage below said control wing segments, while in a forward flight configuration.
2. The aerial vehicle of claim 1 further comprising an aerial vehicle main body.
3. The aerial vehicle of claim 2 wherein said first wing assembly comprises a first right side wing assembly and a left side wing assembly, said first right side wing assembly and said first left side wing assembly coupled to said aerial vehicle main body,
wherein said aerial vehicle further comprises:
an upper spar through the upper wing element of said first right side wing assembly and said first left side wing assembly, said upper spar coupled to said aerial vehicle main body; and
a lower spar through the lower wing element of said first right side wing assembly and said first left side wing assembly, said lower spar coupled to said aerial vehicle main body.
4. The aerial vehicle of claim 3 further comprising one or more control wing segment deployment mechanisms.
5. The aerial vehicle of claim 3 further comprising a tail assembly, said tail assembly comprising a rear wing assembly, said rear wing assembly comprising:
an upper wing element;
a lower wing element, said lower element residing below said upper wing element;
a plurality of airflow segments, said airflow segments coupled to said upper wing element on an upper end, said airflow segments coupled to said lower wing segment on a lower end;
a plurality of thrust units, said thrust units residing in said airflow segments; and
one or more control wing segments, said control wing segments deployable from a forward flight configuration to a vertical flight configuration, said control wing segments residing below said upper wing element and rearward of said lower wing element.
6. The aerial vehicle of claim 5 wherein said first wing assembly is forward of the center of mass of the aerial vehicle, and wherein said rear wing assembly is rearward of the center of mass of the aerial vehicle.
7. The aerial vehicle of claim 3 wherein said rear wing assembly is at a higher elevation than said first wing assembly when said aerial vehicle is in a forward flight configuration.
8. The aerial vehicle of claim 7 wherein said first wing assembly is coupled to an upper portion of said aerial vehicle main body.
9. The aerial vehicle of claim 2 further comprising one or more control wing segment deployment mechanisms.
10. The aerial vehicle of claim 2 wherein said first wing assembly is coupled to an upper portion of said aerial vehicle main body.
11. The aerial vehicle of claim 2 wherein said first wing assembly comprises a first right side wing assembly and a left side wing assembly, said first right side wing assembly and said first left side wing assembly coupled to said aerial vehicle main body, and wherein said aerial vehicle further comprises a second wing assembly, said second wing assembly comprising:
an upper wing element;
a lower wing element, said lower element residing below said upper wing element;
a plurality of airflow segments, said airflow segments coupled to said upper wing element on an upper end, said airflow segments coupled to said lower wing segment on a lower end, said airflow segments forming a first airflow passage below said upper wing element and above said lower wing element at a forward end of said airflow segments;
a plurality of thrust units, said thrust units residing in said airflow segments; and
one or more control wing segments, said control wing segments deployable from a forward flight configuration to a vertical flight configuration, said control wing segments residing below said upper wing element and rearward of said lower wing element, wherein said first airflow passage at the forward end of said airflow segments splits into a second airflow passage above said control wing segments and below said upper wing element, and a third airflow passage below said control wing segments, while in a forward flight configuration, and
wherein said first wing assembly is coupled to said aerial vehicle main body forward of the center of mass of said aerial vehicle, and wherein said second wing assembly is coupled to said aerial vehicle rearward of the center of mass of said aerial vehicle.
12. The aerial vehicle of claim 11 wherein said second wing assembly is at a higher elevation than said first wing assembly when said aerial vehicle is in a forward flight configuration.
13. The aerial vehicle of claim 12 wherein said aerial vehicle main body slopes upward along an underside of said aerial vehicle main body when said aerial vehicle is in a forward flight configuration.
14. The aerial vehicle of claim 13 wherein said first wing assembly and said second wing assembly are pitched upwards when said aerial vehicle resides on the ground.
15. The aerial vehicle of claim 11 wherein said second wing assembly comprises a second right side wing assembly and a second left side wing assembly, said second right side wing assembly and said second left side wing assembly coupled to said aerial vehicle main body.
16. The aerial vehicle of claim 15 wherein said second wing assembly is at a higher elevation than said first wing assembly when said aerial vehicle is in a forward flight configuration.
17. The aerial vehicle of claim 16 wherein said aerial vehicle main body slopes upward along an underside of said aerial vehicle main body when said aerial vehicle is in a forward flight configuration.
18. The aerial vehicle of claim 17 wherein said first wing assembly and said second wing assembly are pitched upwards when said aerial vehicle resides on the ground.
19. The aerial vehicle of claim 2 wherein said first wing assembly comprises a first right side wing assembly and a left side wing assembly, said first right side wing assembly and said first left side wing assembly coupled to said aerial vehicle main body, and wherein said first right side wing assembly and said first left side wing assembly are forward swept, and wherein said first right side wing assembly and said first left side wing assembly are coupled to said aerial vehicle main body rearward of the center of mass of the aerial vehicle, and wherein said first right side wing assembly and said first left side wing assembly protrude forward of the center of mass of the aerial vehicle at an outboard tip.
20. A method for flying a vertical take-off and landing aircraft, wherein said aircraft comprises:
a first wing assembly, said first wing assembly comprising:
an upper wing element;
a lower wing element, said lower element residing below said upper wing element;
a plurality of airflow segments, said airflow segments coupled to said upper wing element on an upper end, said airflow segments coupled to said lower wing segment on a lower end, said airflow segments forming a first airflow passage below said upper wing element and above said lower wing element at a forward end of said airflow segments;
a plurality of thrust units, said thrust units residing in said airflow segments; and
one or more control wing segments, said control wing segments deployable from a forward flight configuration to a vertical flight configuration, said control wing segments residing below said upper wing element and rearward of said lower wing element, wherein said first airflow passage at the forward end of said airflow segments splits into a second airflow passage above said control wing segments and below said upper wing element, and a third airflow passage below said control wing segments, while in a forward flight configuration,
said method comprising the steps of:
deploying said one or more control wing segments to a deployed position,
generating vertical thrust through the use of said plurality of thrust units by deflecting the thrust downwards with said control wing segments;
gaining elevation from the ground;
generating forward speed by beginning to transition said control wing segments from the vertical flight configuration to the forward flight configuration;
transitioning to forward flight with said control wing segments in the forward flight configuration.