Fuselage structure for accommodating tails and canards of different sizes and shapes
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-001/26
B64C-039/12
B64C-003/18
출원번호
US-0975115
(2015-12-18)
등록번호
US-9849966
(2017-12-26)
발명자
/ 주소
Schmidt, Gregory M.
Walton, Samuel Thomas
출원인 / 주소
The Boeing Company
대리인 / 주소
Miller, Matthias & Hull LLP
인용정보
피인용 횟수 :
0인용 특허 :
8
초록▼
An aircraft includes a fuselage with structural interfaces for connection to any one or more of a variety of vertical tails, horizontal tails and canards. Vertical tails, horizontal tails and/or canards of different sizes, shapes, sweep angles, box chords, and/or root chords may connect to the fusel
An aircraft includes a fuselage with structural interfaces for connection to any one or more of a variety of vertical tails, horizontal tails and canards. Vertical tails, horizontal tails and/or canards of different sizes, shapes, sweep angles, box chords, and/or root chords may connect to the fuselage without changing the structural layout or configuration of the fuselage structural interfaces.
대표청구항▼
1. An aircraft comprising: a fuselage comprising an aft portion,the aft portion including at least one front vertical structural interface and at least one rear vertical structural interface,the at least one front vertical structural interface connected to a front spar of a first vertical tail or to
1. An aircraft comprising: a fuselage comprising an aft portion,the aft portion including at least one front vertical structural interface and at least one rear vertical structural interface,the at least one front vertical structural interface connected to a front spar of a first vertical tail or to a front spar of a second vertical tail,the at least one rear vertical structural interface connected to a rear spar of a first vertical tail or to a rear spar of a second vertical tail,wherein the first and second vertical tails are of different sizes. 2. The aircraft of claim 1, wherein the front spars of the first and second vertical tails each define a sweep angle, the rear spars of the first and second vertical tails each define a sweep angle, the first and second vertical tails each have a leading edge that defines a sweep angle, the first and second vertical tails each have at least one trailing edge that defines a sweep angle, the first and second vertical tails each have a vertical box chord, the first and second vertical tails each have a vertical root chord, wherein the first and second vertical tails have at least one structural difference selected from the group consisting of different sweep angles of the front spars, different sweep angles of the rear spars, different sweep angles of the leading edges, different sweep angles of the trailing edges, different vertical box chords, and different vertical root chords. 3. The aircraft of claim 1 wherein the front spar of the first vertical tail is connected to a first front vertical structural interface and the front spar of the second vertical tail is connected to a second front vertical structural interface, the first front vertical structural interface being different from the second front vertical structural interface. 4. The aircraft of claim 1 wherein the rear spar of the first vertical tail is connected to a first rear vertical structural interface and the rear spar of the second vertical tail is connected to a second rear vertical structural interface, the first rear vertical structural interface being different from the second rear vertical structural interface. 5. The aircraft of claim 1 wherein the aft portion of the fuselage includes at least one front horizontal structural interface and at least one rear horizontal structural interface, the at least one front horizontal structural interface connected to a front spar of a first horizontal tail or to a front spar of a second horizontal tail,the at least one rear horizontal structural interface connected to a rear spar of the first horizontal tail or to a rear spar of the second horizontal tail,wherein the front spars of the first and second horizontal tails each define a sweep angle, the rear spars of the first and second horizontal tails each define a sweep angle, the first and second horizontal tails each have a leading edge that defines a sweep angle, the first and second horizontal tails each have at least one trailing edge that each defines a sweep angle, the first and second horizontal tails each have a horizontal box chord, the first and second horizontal tails each have a horizontal root chord, and the first and second horizontal tails each have a size,wherein the first and second horizontal tails have at least one structural difference selected from the group consisting of different sweep angles of the front spars, different sweep angles of the rear spars, different sweep angles of the leading edges, different sweep angles of the trailing edges, different horizontal box chords, different horizontal root chords, and/or different sizes. 6. The aircraft of claim 5 wherein the front spar of the first horizontal tail is connected to a first front horizontal structural interface and the front spar of the second horizontal tail is connected to a second front horizontal structural interface, the first front horizontal structural interface being different from the second front horizontal structural interface. 7. The aircraft of claim 5 wherein the rear spar of the first horizontal tail is connected to a first rear horizontal structural interface and the rear spar of the second horizontal tail is connected to a second rear horizontal structural interface, the first rear horizontal structural interface being different from the second rear horizontal structural interface. 8. The aircraft of claim 1 wherein the fuselage further comprises a forward portion, the forward portion including at least one front canard structural interface and at least one rear canard structural interface,the at least one front canard structural interface connected to a front spar of a first canard or to a front spar of a second canard,the at least one rear canard structural interface connected to a rear spar of the first canard or to a rear spar of the second canard,wherein the front spars of the first and second canards each define a sweep angle, the rear spars of the first and second canards each define a sweep angle, the first and second canards each have a leading edge that defines a sweep angle, the first and second canards each have at least one trailing edge that each defines a sweep angle, the first and second canards each have a canard box chord, the first and second canards each have a canard root chord, and the first and second canards each have a size,wherein the first and second canards have at least one structural difference selected from the group consisting of different sweep angles of the front spars, different sweep angles of the rear spars, different sweep angles of the leading edges, different sweep angles of the trailing edges, different canard box chords, different canard root chords, and/or different sizes. 9. The aircraft of claim 8 wherein the front spar of the first canard is connected to a first front canard structural interface and the front spar of the second canard is connected to a second front canard structural interface, the first front canard structural interface being different from the second front canard structural interface. 10. The aircraft of claim 8 wherein the rear spar of the first canard is connected to a first rear canard structural interface and the rear spar of the second canard is connected to a second rear canard structural interface, the first rear canard structural interface being different from the second rear canard structural interface. 11. An aircraft comprising: a fuselage comprising an aft portion,the aft portion including at least one front horizontal structural interface and at least one rear horizontal structural interface,the at least one front horizontal structural interface connected to a front spar of a first horizontal tail or to a front spar of a second horizontal tail,the at least one rear horizontal structural interface connected to a rear spar of the first horizontal tail or to a rear spar of the second horizontal tail,wherein the first and second horizontal tails are of different sizes. 12. The aircraft of claim 11 wherein the front spars of the first and second horizontal tails each define a sweep angle, the rear spars of the first and second horizontal tails each define a sweep angle, the first and second horizontal tails each have a leading edge that defines a sweep angle, the first and second horizontal tails each have at least one trailing edge that each defines a sweep angle, the first and second horizontal tails each have a horizontal box chord, the first and second horizontal tails each have a horizontal root chord, wherein the first and second horizontal tails have at least one structural difference selected from the group consisting of different sweep angles of the front spars, different sweep angles of the rear spars, different sweep angles of the leading edges, different sweep angles of the trailing edges, different horizontal box chords, and/or different horizontal root chords. 13. The aircraft of claim 11 wherein the front spar of the first horizontal tail is connected to a first front horizontal structural interface and the front spar of the second horizontal tail is connected to a second front horizontal structural interface, the first front horizontal structural interface being different from the second front horizontal structural interface. 14. The aircraft of claim 11 wherein the rear spar of the first horizontal tail is connected to a first rear horizontal structural interface and the rear spar of the second horizontal tail is connected to a second rear horizontal structural interface, the first rear horizontal structural interface being different from the second rear horizontal structural interface. 15. The aircraft of claim 11 wherein the aft portion of the fuselage includes at least one front vertical structural interface and at least one rear vertical structural interface, the at least one front vertical structural interface connected to a front spar of a first vertical tail or to a front spar of a second vertical tail,the at least one rear vertical structural interface connected to a rear spar of the first vertical tail or to a rear spar of the second vertical tail,wherein the front spars of first and second vertical tails each define a sweep angle, the rear spars of the first and second vertical tails each define a sweep angle, the first and second vertical tails each have a leading edge that defines a sweep angle, the first and second vertical tails each have at least one trailing edge that each defines a sweep angle, the first and second vertical tails each have a vertical box chord, the first and second vertical tails each have a vertical root chord, the first and second vertical tails each have a size,wherein the first and second vertical tails have at least one structural difference selected from the group consisting of different sweep angles of the front spars, different sweep angles of the rear spars, different sweep angles of the leading edges, different sweep angles of the trailing edges, different vertical box chords, different vertical root chords, and/or different sizes. 16. The aircraft of claim 11 wherein the fuselage further comprises a forward portion that includes at least one front canard structural interface and at least one rear canard structural interface, the at least one front canard structural interface connected to a front spar of a first canard or to a front spar of a second canard,the at least one rear canard structural interface connected to a rear spar of the first canard or to a rear spar of the second canard,wherein the front spars of the first and second canards each define a sweep angle, the rear spars of the first and second canards each define a sweep angle, the first and second canards each have a leading edge that defines a sweep angle, the first and second canards each have at least one trailing edge that each defines a sweep angle, the first and second canards each have a canard box chord, the first and second canards each have a canard root chord, the first and second canards each have a size,wherein the first and second canards have at least one structural difference selected from the group consisting of different sweep angles of the front spars, different sweep angles of the rear spars, different sweep angles of the leading edges, different sweep angles of the trailing edges, different canard box chords, different canard root chords, and/or different sizes. 17. An aircraft comprising: a fuselage comprising a forward portion that includes at least one front canard structural interface and at least one rear canard structural interface,the at least one front canard structural interface connected to a front spar of a first canard or to a front spar of a second canard,the at least one rear canard structural interface connected to a rear spar of the first canard or to a rear spar of the second canard,wherein the first and second canards are of different sizes. 18. The aircraft of claim 17 wherein the front spars of first and second canards each define a sweep angle, the rear spars of the first and second canards each define a sweep angle, the first and second canards each have a leading edge that defines a sweep angle, the first and second canards each have at least one trailing edge that each defines a sweep angle, the first and second canards each have a canard box chord, the first and second canards each have a horizontal root chord, wherein the first and second canards have at least one structural difference selected from the group consisting of different sweep angles of the front spars, different sweep angles of the rear spars, different sweep angles of the leading edges, different sweep angles of the trailing edges, different canard box chords, and/or different canard root chords. 19. The aircraft of claim 17 wherein the front spar of the first canard is connected to a first front canard structural interface and the front spar of the second canard is connected to a second front canard structural interface, the first front canard structural interface being different from the second front canard structural interface. 20. The aircraft of claim 17 wherein the rear spar of the first canard is connected to a first rear canard structural interface and the rear spar of the second canard is connected to a second rear canard structural interface, the first rear canard structural interface being different from the second rear canard structural interface. 21. The aircraft of claim 17 wherein the fuselage further comprises an aft portion that includes at least one front vertical structural interface and at least one rear vertical structural interface, the at least one front vertical structural interface connected to a front spar of a first vertical tail or to a front spar of a second vertical tail,the at least one rear vertical structural interface connected to a rear spar of the first vertical tail or to a rear spar of the second vertical tail,wherein the front spars of the first and second vertical tails each define a sweep angle, the rear spars of the first and second vertical tails each define a sweep angle, the first and second vertical tails each have a leading edge that defines a sweep angle, the first and second vertical tails each have at least one trailing edge that each defines a sweep angle, the first and second vertical tails each have a vertical box chord, the first and second vertical tails each have a vertical root chord, the first and second vertical tails each have a size,wherein the first and second vertical tails have at least one structural difference selected from the group consisting of different sweep angles of the front spars, different sweep angles of the rear spars, different sweep angles of the leading edges, different sweep angles of the trailing edges, different vertical box chords, different vertical root chords, and/or different sizes. 22. The aircraft of claim 17 wherein the fuselage further comprises an aft portion that includes at least one front horizontal structural interface and at least one rear horizontal structural interface, the at least one front horizontal structural interface connected to a front spar of a first horizontal tail or to a front spar of a second horizontal tail,the at least one rear horizontal structural interface connected to a rear spar of the first horizontal tail or to a rear spar of the second horizontal tail,wherein the front spars of the first and second horizontal tails each define a sweep angle, the rear spars of the first and second horizontal tails each define a sweep angle, the first and second horizontal tails each have a leading edge that defines a sweep angle, the first and second horizontal tails each have at least one trailing edge that each defines a sweep angle, the first and second horizontal tails each have a horizontal box chord, the first and second horizontal tails each have a horizontal root chord, and the first and second horizontal tails each have a size,wherein the first and second horizontal tails have at least one structural difference selected from the group consisting of different sweep angles of the front spars, different sweep angles of the rear spars, different sweep angles of the leading edges, different sweep angles of the trailing edges, different horizontal box chords, different horizontal root chords, and/or different sizes. 23. A method of enhancing an aircraft having a fuselage with an aft portion and a forward portion, the aircraft including one or more of a vertical tail, a horizontal tail and a canard, the method comprising: wherein if the aircraft has a vertical tail, providing the aft portion of the fuselage with at least one front vertical structural interface and at least one rear vertical structural interface,wherein if the aircraft has a horizontal tail, providing the aft portion of the fuselage with at least one front horizontal structural interface and at least one rear horizontal structural interface,wherein if the aircraft has a canard, providing the forward portion of the fuselage with at least one front canard structural interface and at least one rear canard structural interface,the method further comprising making at least one enhancement to the aircraft selected from the group consisting of:allowing the at least one front vertical structural interface to connect to a front spar of a first vertical tail and allowing the at least one rear vertical structural interface to connect to a rear spar of the first vertical tail or, in the alternative, allowing the at least one front vertical structural interface to connect to a front spar of a second vertical tail and allowing the at least one rear vertical structural interface to connect a rear spar of the second vertical tail, wherein the first and second vertical tails are of different sizes;allowing the at least one front horizontal structural interface to connect to a front spar of a first horizontal tail and allowing the at least one rear horizontal structural interface to connect to a rear spar of the first horizontal tail or, in the alternative, allowing the at least one front horizontal structural interface to connect to a front spar of a second horizontal tail and allowing the at least one rear horizontal structural interface to connect to a rear spar of the second horizontal tail, wherein the first and second horizontal tails are of different sizes; andallowing the at least one front canard structural interface to connect to a front spar of a first canard and allowing the at least one rear canard structural interface to connect to a rear spar of the first canard or, in the alternative, allowing the at least one front canard structural interface to connect to a front spar of a second canard and allowing the at least one rear canard structural interface to connect to a rear spar of the second canard, wherein the first and second canards are of different sizes.
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이 특허에 인용된 특허 (8)
Vassiliev Anatoli J.,DEX ; Eibel Karl-Heinz,DEX, Aircraft for passenger and/or cargo transport.
Buttgereit Volker (c/o Daimler Benz Aerospace Airbus GmbH ; Patent Dept. 21129 Hamburg DEX) Hempel Joachim (c/o Daimler Benz Aerospace Airbus GmbH ; Patent Dept. 21129 Hamburg DEX) Kiekebusch Burckha, Body tail unit for a commercial aircraft.
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