Aerodynamic lifting structures having embedded engines, and associated systems and methods
Aerodynamic lifting structures, such as aircraft wings, having embedded engines and associated methods and systems are disclosed herein. A wing assemblies configured in accordance with embodiments of the present technology can include, for example, an upper wing portion, a lower wing portion, and a plurality of independent ducts positioned between the upper wing portion and the lower wing portion. Each duct can extend between a corresponding inlet positioned toward a leading portion of the wing assembly and a corresponding outlet positioned toward a trailing portion of the wing assembly. The wing assembly can further include a plurality of fans and a plurality of electric motors operably coupled to the plurality of fans. The fans and electric motors are positioned in the corresponding individual ducts and the fan is rotatable to propel fluid received in the inlet through the duct to create lift.
1. An aircraft comprising a fuselage and a wing extending transversely from the fuselage, the wing having a leading portion and a trailing portion positioned opposite the leading portion along a chord of the wing, the wing further comprising:
an upper wing portion having an upper leading edge, an upper trailing edge, and an upper exterior surface extending between the upper leading edge and the upper trailing edge, the upper exterior surface positioned to face exterior airflow above the wing;
a lower wing portion having a lower leading edge spaced apart from the upper leading edge, a lower trailing edge, and a lower exterior surface extending between the lower leading edge and the lower trailing edge, the lower exterior surface positioned to face exterior airflow below the wing;
a plurality of spars extending laterally along at least part of a span of the wing wherein each spar of the plurality of spars comprises a spar web;
a plurality of independent ducts positioned between the upper wing portion and the lower wing portion, wherein each duct extends between a corresponding inlet positioned toward the leading portion and a corresponding outlet positioned toward the trailing portion, and wherein each duct extends through an opening in each spar web;
a fan positioned in each duct of the plurality of ducts, wherein the fan is rotatable to propel air received in the inlet through the duct and to the outlet; and
an electric motor operably connected to each fan to rotate the fan.
2. The aircraft of claim 1 , wherein, for each duct of the plurality of ducts, the wing further comprises one or more movable structures configured to change at least one of a size or a shape of at least one of the inlet or the outlet.
3. The aircraft of claim 1 , wherein the lower wing portion carries a lower rear control surface, wherein the lower rear control surface is movable relative to the wing to move the lower trailing edge and change a backpressure in each duct of the plurality of ducts.
4. The aircraft of claim 3 , further comprising a lower intermediate control surface positioned between the lower rear control surface and the lower wing portion, wherein the lower intermediate control surface is spaced apart from the lower rear control surface to form a slotted flap of the wing.
5. The aircraft of claim 1 , wherein the upper wing portion carries an upper rear control surface, wherein the upper rear control surface is movable relative to the wing to move the upper trailing edge and change a backpressure in each duct of the plurality of ducts.
6. The aircraft of claim 1 , wherein the upper leading edge is positioned on an upper movable structure, wherein the upper movable structure is movable from a stowed position to a deployed position, and wherein the deployed position comprises the upper movable structure being at least one of rotated relative to the upper wing portion or extended forward of the upper wing portion.
7. The aircraft of claim 1 , wherein the lower leading edge is positioned on a lower movable structure that is at least one of pivotable relative to the lower wing portion or extendable forward of the lower wing portion.
8. The aircraft of claim 1 , wherein, for each duct of the plurality of ducts, a cross section of the duct varies along a chordwise length of the duct.
9. The aircraft of claim 1 , wherein for each duct of the plurality of ducts a cross section of the duct includes a rounded rectangular shape toward the inlet, a circular shape adjacent to the fan, and a rounded rectangular shape toward the outlet.
10. The aircraft of claim 1 , wherein, for each duct of the plurality of ducts, the duct diverges from the inlet to the fan, and converges from the fan to the outlet.
11. The aircraft of claim 1 , wherein each spar of the plurality of spars extends straight along the span of the wing.
12. The aircraft of claim 1 , further comprising a plurality of ribs connecting adjacent spars and wing skins.
13. The aircraft of claim 1 , wherein the plurality of spars comprises a forward spar, a forward-mid spar positioned aft of the forward spar, an aft-mid spar positioned aft of the forward-mid spar, and an aft spar positioned aft of the aft-mid spar.
14. The aircraft of claim 1 , wherein, for each duct of the plurality of ducts, the electric motor operably connected to the fan is positioned in the duct.
15. The aircraft of claim 14 , wherein the wing further comprises for each duct of the plurality of ducts, a plurality of supports connected to one of the spar webs for supporting the electric motor in the duct.
16. The aircraft of claim 1 , wherein the plurality of ducts are positioned in a first portion of the wing, and wherein the wing comprises a second portion that does not include ducts.
17. The aircraft of claim 1 , wherein the plurality of ducts are positioned in a first portion of the wing, and wherein the wing comprises a second portion that is rotatable relative to the first portion via a wing folding mechanism.
18. The aircraft of claim 17 , wherein the first portion is an inboard portion positioned between the fuselage and the second portion.
19. The aircraft of claim 1 , wherein the wing comprises a plurality of vertical splitter elements extending between the upper wing portion and the lower wing portion, and wherein each vertical splitter element forms a side of an adjacent duct of the plurality of ducts.
20. The aircraft of claim 19 , wherein the vertical splitter elements are structural ribs of the wing extending between the leading portion and the trailing portion.
21. The aircraft of claim 1 , wherein the plurality of independent ducts comprises greater than ten independent ducts.
22. The aircraft of claim 21 , wherein the plurality of independent ducts comprises sixteen independent ducts.
23. The aircraft of claim 1 , wherein a portion of the upper exterior surface adjacent to the upper leading edge has a uniformly smooth shape extending between multiple ducts along a spanwise direction.
24. An aircraft comprising a fuselage and a wing extending transversely from the fuselage, the wing having a leading portion and a trailing portion positioned opposite the leading portion along a chord of the wing, the wing further comprising:
an upper wing portion having an upper leading edge, an upper trailing edge, and an upper exterior surface extending between the upper leading edge and the upper trailing edge, the upper exterior surface positioned to face exterior airflow above the wing;
a lower wing portion having a lower leading edge, a lower trailing edge, and a lower exterior surface extending between the lower leading edge and the lower trailing edge, the lower exterior surface positioned to face exterior airflow below the wing;
one or more spars extending along at least part of a span of the wing between the upper wing portion and the lower wing portion, wherein each spar of the one or more spars comprises a spar web;
a plurality of independent ducts positioned between the upper wing portion and the lower wing portion, wherein each duct extends through an opening in at least one of the spar webs between a corresponding inlet positioned toward the leading portion and a corresponding outlet positioned toward the trailing portion, and wherein for each duct of the plurality of ducts, a cross section of the of the duct varies along a chordwise length of the duct;
a fan positioned in each duct of the plurality of ducts, wherein the fan is rotatable to propel air received in the inlet through the duct and to the outlet; and
for each fan, an electric motor or combustion engine operably connected to the fan to rotate the fan.
25. The aircraft of claim 24 , wherein each spar of the one or more spars extends linearly along the at least part of the span of the wing with uniform thickness along the at least part of the span of the wing.
26. The aircraft of claim 24 , wherein each electric motor or combustion engine is positioned in a corresponding duct of the plurality of independent ducts.
27. The aircraft of claim 24 , wherein the wing further comprises one or more movable structures configured to change at least one of a size, shape, or position of at least one of the inlet or the outlet.
28. The aircraft of claim 24 , wherein, for each duct of the plurality of ducts, at least a portion of the duct has a non-circular cross-section.
29. The aircraft of claim 24 , wherein, for each duct of the plurality of ducts, at least a portion of the duct forward of a forward-most spar of the one or more spars has a cross-section along a span-wise direction having a straight portion.
30. The aircraft of claim 24 , wherein, for each duct of the plurality of ducts, the duct forms a converging-diverging nozzle for air propelled by the fan.
31. An aircraft comprising a fuselage and a wing extending transversely from the fuselage, the wing having a leading portion and a trailing portion positioned opposite the leading portion along a chord of the wing, the wing further comprising:
an upper wing portion extending along at least part of a span of the wing;
a lower wing portion extending along at least part of the span of the wing;
a plurality of spars extending along at least a portion of the span of the wing;
a plurality of independent ducts positioned between the upper wing portion and the lower wing portion, wherein each duct extending-extends between an inlet positioned toward a leading portion of the wing and an outlet positioned toward a trailing portion of the wing, and wherein each duct of the plurality of independent ducts extends through an opening in each spar of the plurality of spars;
a fan positioned in each duct of the plurality of ducts, wherein the fan is positioned between a first spar of the plurality of spars and a second spar of the plurality of spars along a chordwise direction, and wherein the fan is rotatable to propel air received in the inlet through the duct and to the outlet to create thrust for the aircraft; and
an aerodynamic control surface carried by the lower wing portion at the trailing portion of the wing;
wherein:
the aerodynamic control surface and at least part of the upper wing portion form a nozzle throat for airflow passing through at least one of the ducts; and
the aerodynamic control surface is movable to change at least one of a size, shape, or position of the nozzle throat.
32. The aircraft of claim 31 , further comprising a plurality of electric motors, wherein each electric motor of the plurality of electric motors is positioned in one of the ducts of the plurality of ducts and connected to the fan to rotate the fan.
33. The aircraft of claim 31 , further comprising one or more additional aerodynamic control surfaces carried by the upper wing portion or the lower wing portion.
34. The aircraft of claim 31 , wherein, for each duct of the plurality of ducts, the duct comprises a converging portion between a first spar of the plurality of spars and a second spar of the plurality of spars.
35. The aircraft of claim 31 , wherein the wing further comprises one or more vertical splitter elements, wherein each vertical splitter element of the one or more vertical splitter elements is positioned between adjacent inlets and extends between the upper wing portion and the lower wing portion.
36. The aircraft of claim 35 , wherein the one or more vertical splitter elements are one or more structural ribs of the wing.
37. A wing assembly comprising:
an upper wing portion having an upper leading edge, an upper trailing edge, and an upper exterior surface extending between the upper leading edge and the upper trailing edge, the upper exterior surface positioned to face exterior fluid flow above the wing;
a lower wing portion having a lower leading edge spaced apart from the upper leading edge, a lower trailing edge, and a lower exterior surface extending between the lower leading edge and the lower trailing edge, the lower exterior surface positioned to face exterior fluid flow below the wing;
a plurality of spars extending laterally along at least part of a span of the wing assembly, wherein each spar of the plurality of spars comprises a spar web;
a plurality of independent ducts positioned between the upper wing portion and the lower wing portion, wherein each duct extends between a corresponding inlet positioned toward the leading portion and a corresponding outlet positioned toward the trailing portion, and through an opening in each spar web;
a fan positioned in each duct of the plurality of ducts, wherein the fan is rotatable to propel fluid received in the inlet through the duct and to the outlet; and
an electric motor operably connected to the fan to rotate the fan.
38. The wing assembly of claim 37 , further comprising one or more movable structures configured to change at least one of a size or a shape of at least one of the inlets or one of the outlets.
39. The wing assembly of claim 37 , wherein the lower wing portion carries a lower rear control surface, and wherein the lower rear control surface is configured to move the lower trailing edge and change a backpressure in at least one of the ducts of the plurality of ducts.
40. The wing assembly of claim 37 , wherein the lower wing portion carries a lower rear control surface configured to move the lower trailing edge, and the wing assembly further comprises a lower intermediate control surface positioned between the lower rear control surface and the lower wing portion, wherein the lower intermediate control surface is spaced apart from the lower rear control surface to form a slotted flap of the wing assembly.
41. The wing assembly of claim 37 , wherein the upper wing portion carries an upper rear control surface, and wherein the upper rear control surface is configured to move the upper trailing edge and change a backpressure in at least one of the ducts of the plurality of ducts.
42. The wing assembly of claim 37 , wherein the upper leading edge is positioned on an upper movable structure, wherein the upper movable structure is configured to move from a stowed position to a deployed position, and wherein the deployed position comprises the upper movable structure being at least one of rotated relative to the upper wing portion or extended forward of the upper wing portion.
43. The wing assembly of claim 37 , wherein the lower leading edge is positioned on a lower movable structure that is at least one of pivotable relative to the lower wing portion or extendable forward of the lower wing portion.
44. The wing assembly of claim 37 , wherein for each duct of the plurality of ducts, a cross section of the duct varies along a chordwise length of the duct.
45. The wing assembly of claim 44 , wherein, for each duct of the plurality of ducts the cross section of the duct includes a rounded rectangular shape toward the inlet, a circular shape adjacent to the fan, and a rounded rectangular shape toward the outlet.
46. The wing assembly of claim 37 , wherein for each duct of the plurality of ducts, the duct diverges from the inlet to the fan and converges from the fan to the outlet.
47. The wing assembly of claim 37 , wherein each spar of the plurality of spars extends straight along the span of the wing assembly.
48. The wing assembly of claim 37 , further comprising a plurality of ribs connecting adjacent spars and wing skins.
49. The wing assembly of claim 37 , wherein the plurality of spars comprises a forward spar, a forward-mid spar positioned aft of the forward spar, an aft-mid spar positioned aft of the forward-mid spar, and an aft spar positioned aft of the aft-mid spar.
50. The wing assembly of claim 37 , wherein the electric motor is in one of the ducts.
51. The wing assembly of claim 50 , wherein the wing assembly further comprises, for each duct of the plurality of ducts, a plurality of supports connected to one of the spar webs for supporting the electric motor in the duct.
52. The wing assembly of claim 37 , wherein the plurality of ducts are positioned in a first portion of the wing, and wherein the wing assembly comprises a second portion that does not include ducts.
53. The wing assembly of claim 37 , wherein the plurality of ducts are positioned in a first portion of the wing, and wherein the wing assembly further comprises a second portion that is rotatable relative to the first portion via a wing folding mechanism.
54. The wing assembly of claim 37 , further comprising a plurality of vertical splitter elements extending between the upper wing portion and the lower wing portion, and wherein each vertical splitter element forms a side of an adjacent duct.
55. The wing assembly of claim 54 , wherein the vertical splitter elements are structural ribs of the wing assembly extending between the leading portion and the trailing portion.
56. The wing assembly of claim 37 , wherein the plurality of independent ducts comprises greater than ten independent ducts, and wherein the electric motor is one of a plurality of electric motors, each motor being positioned within individual ones of the independent ducts.