IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0428095
(2012-03-23)
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등록번호 |
US-8302908
(2012-11-06)
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발명자
/ 주소 |
- Kismarton, Max
- Kutzmann, Aaron J.
- Lutke, Kevin
|
출원인 / 주소 |
|
대리인 / 주소 |
Hope Baldauff Hartman, LLC
|
인용정보 |
피인용 횟수 :
1 인용 특허 :
31 |
초록
▼
Apparatus and methods provide for a blended wing passenger or cargo aircraft. Aspects of the disclosure provide an aircraft having wings with spars having a thickness at the wing root corresponding to a height of the payload space within the fuselage to which the wings are attached. The wing spars w
Apparatus and methods provide for a blended wing passenger or cargo aircraft. Aspects of the disclosure provide an aircraft having wings with spars having a thickness at the wing root corresponding to a height of the payload space within the fuselage to which the wings are attached. The wing spars within the wings on each side of the aircraft may each be spliced into an aircraft frame that is part of the fuselage. The wing thickness provides mounting locations for aircraft engines and other components within the wing and passing through the wing spars. With this mid-wing configuration, the fuselage provides support for the various loads experienced by the wings without the use of a conventional structural wing box.
대표청구항
▼
1. A mid-wing aircraft, comprising: an aircraft fuselage encompassing a payload space; anda wing spar attached to a side of the aircraft fuselage and having a wing root thickness substantially corresponding to a height of the payload space, the wing spar comprising an upper spar chord terminated at
1. A mid-wing aircraft, comprising: an aircraft fuselage encompassing a payload space; anda wing spar attached to a side of the aircraft fuselage and having a wing root thickness substantially corresponding to a height of the payload space, the wing spar comprising an upper spar chord terminated at and connected to an upper portion of the aircraft fuselage,a lower spar chord terminated at and connected to a lower portion of the aircraft fuselage, anda wing spar web connecting the upper spar chord and the lower spar chord. 2. The mid-wing aircraft of claim 1, wherein the wing spar web comprises at least one aircraft component aperture configured to allow an aircraft component to pass through the wing spar web, and wherein the mid-wing aircraft further comprises a second wing spar attached to a second side of the aircraft fuselage opposite the wing spar, the second wing spar comprising: a second upper spar chord terminated at and connected to the upper portion of the aircraft fuselage opposite a termination location of the upper spar chord;a second lower spar chord terminated at and connected to the lower portion of the aircraft fuselage opposite a termination location of the lower spar chord; anda second wing spar web connecting the second upper spar chord and the second lower spar chord and comprising at least one aircraft component aperture configured to allow a second aircraft component to pass through the second wing spar web. 3. The mid-wing aircraft of claim 1, wherein the upper spar chord penetrates the upper portion of the aircraft fuselage and is spliced to an aircraft body frame. 4. The mid-wing aircraft of claim 3, wherein the lower spar chord penetrates the lower portion of the aircraft fuselage and is spliced to the aircraft body frame. 5. The mid-wing aircraft of claim 1, wherein the wing spar web is connected to a skin of the aircraft fuselage. 6. The mid-wing aircraft of claim 5, wherein the wing spar web is bonded to the skin of the aircraft fuselage. 7. The mid-wing aircraft of claim 5, wherein the wing spar web is secured to the skin of the aircraft fuselage using fasteners. 8. The mid-wing aircraft of claim 7, wherein the wing spar web is secured to the skin of the aircraft fuselage with fasteners through a circumferential clip, the circumferential clip comprising a contact surface shaped to abut the skin of the aircraft fuselage from a location proximate to an entry of the upper spar chord into the aircraft fuselage to a location proximate an entry of the lower spar chord into the aircraft fuselage, and a flange projecting from the surface and configured to abut the wing spar web. 9. The mid-wing aircraft of claim 1, wherein a distance between the upper spar chord and the lower spar chord decreases non-uniformly from the aircraft fuselage to a wing tip. 10. The mid-wing aircraft of claim 9, wherein the wing spar web comprises at least one aircraft engine mounting aperture configured to allow an aircraft engine to pass through the wing spar web, and wherein the upper spar chord extends away from the upper portion of the aircraft fuselage, over the at least one engine mounting aperture, and curves downward toward the lower spar chord on an outboard side of the at least one engine mounting aperture. 11. The mid-wing aircraft of claim 1, wherein the wing spar web comprises at least one aircraft engine mounting aperture configured to provide a mounting location for at least one aircraft engine through the wing spar web. 12. The mid-wing aircraft of claim 11, wherein the at least one aircraft engine mounting aperture comprises two aircraft engine mounting apertures configured to provide a mounting location for two aircraft engines through the wing spar web. 13. The mid-wing aircraft of claim 1, wherein the upper spar chord and lower spar chord each terminate at an aircraft body frame such that opposing sides of the upper spar chord and lower spar chord terminate on opposing sides of an aircraft body frame and taper inwards toward the aircraft body frame for a length of overlap of the aircraft body frame, and wherein a plurality of fasteners penetrate through the opposing sides of the upper spar chord and lower spar chord and the aircraft body frame to secure the upper spar chord to the aircraft body frame and the lower spar chord to the aircraft body frame. 14. A method for providing a mid-wing aircraft, the method comprising: splicing an upper spar chord of a wing spar into an aircraft body frame within an upper portion of an aircraft fuselage; andsplicing a lower spar chord of the wing spar into the aircraft body frame within a lower portion of an aircraft fuselage such that a distance between the upper spar chord and the lower spar chord corresponds to a height of a payload space encompassed within the aircraft body frame. 15. The method of claim 14, further comprising securing a wing spar web connecting the upper spar chord to the lower spar chord to a skin of the aircraft fuselage using a circumferential clip with fasteners. 16. The method of claim 14, further comprising providing a wing spar web connecting the upper spar chord to the lower spar chord, the wing spar web comprising a plurality of aircraft component apertures configured such that a plurality of aircraft components may be mounted within the wing spar web. 17. The method of claim 14, further comprising: splicing a second upper spar chord of a second wing spar into the aircraft body frame within the upper portion of the aircraft fuselage at a location on an opposite side of the aircraft fuselage from the upper spar chord; andsplicing a second lower spar chord of the second wing spar into the aircraft body frame within the lower portion of the aircraft fuselage at a location on the opposite side of the aircraft fuselage from the lower spar chord. 18. A mid-wing aircraft, comprising: an aircraft fuselage encompassing a payload space; anda wing comprising a first wing half and a second wing half connected to opposite sides of the aircraft fuselage, wherein each of the first wing half and the second wing half comprises a wing root thickness substantially corresponding to a height of the payload space,an upper spar chord that penetrates an upper portion of the aircraft fuselage and is spliced into an upper aircraft body frame,a lower spar chord that penetrates a lower portion of the aircraft fuselage and is spliced into a lower aircraft body frame, anda wing spar web connecting the upper spar chord and the lower spar chord, wherein the wing spar web is connected to a skin of the aircraft fuselage. 19. The mid-wing aircraft of claim 18, wherein the upper spar chord of each of the first wing half and the second wing half terminates on opposing sides of the upper aircraft body frame and tapers inwards toward the upper aircraft body frame for a length of overlap with the upper aircraft body frame, and wherein a plurality of fasteners penetrate through the opposing sides of the upper spar chord and the upper aircraft body frame to secure the upper spar chord to the upper aircraft body frame. 20. The mid-wing aircraft of claim 18, wherein the wing spar web comprises at least one aircraft engine mounting aperture within each of the first wing half and the second wing half, and wherein a distance between the upper spar chord and the lower spar chord of each of the first wing half and the second wing half decreases non-uniformly from the aircraft fuselage to a wing tip such that the upper spar chord traverses away from the upper portion of the aircraft fuselage, over the at least one aircraft engine mounting aperture, and curves downward toward the lower spar chord on an outboard side of the at least one aircraft engine mounting aperture.
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