Synthetic aisle configuration for an aircraft
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64D-011/06
출원번호
US-0147731
(2008-06-27)
등록번호
US-8220741
(2012-07-17)
발명자
/ 주소
Barmichev, Sergey D.
Eckert, David W.
출원인 / 주소
The Boeing Company
대리인 / 주소
Yee & Associates, P.C.
인용정보
피인용 횟수 :
3인용 특허 :
11
초록
A method may be present for configuring an aircraft. A design may be identified for the aircraft. A passenger area may be configured using a set of synthetic aisles to meet a desired passenger density for the design.
대표청구항▼
1. A method for configuring an aircraft, the method comprising: identifying a design for the aircraft;positioning an aisle along a length of a fuselage of the aircraft;configuring a first set of rows of seats on a first side of the aisle, the set of rows comprising rows of three seats;configuring a
1. A method for configuring an aircraft, the method comprising: identifying a design for the aircraft;positioning an aisle along a length of a fuselage of the aircraft;configuring a first set of rows of seats on a first side of the aisle, the set of rows comprising rows of three seats;configuring a second set of rows of seats on a second side of the aisle, the second set of rows comprising alternating rows of four seats and rows of three seats, such that the rows of three seats define an empty space proximate the aisle; andconfiguring a passenger area to meet a desired passenger density for the design responsive to a policy, wherein the policy specifies at least one of a seat width and an orientation for the seats. 2. The method of claim 1, wherein the policy specifies at least one of a maximum time to reach an exit from any seat within the passenger area and a pitch for seats. 3. The method of claim 1, wherein the desired passenger density is a maximum passenger density. 4. The method of claim 1, wherein the configuring step comprises: selecting a sequence of seats and spaces to meet the desired passenger density. 5. The method of claim 1, wherein a configuration of seats in the passenger area are described using a discrete aisle code. 6. The method of claim 1, wherein the desired passenger density is one of a selected density and a maximum passenger density for the design on the aircraft. 7. The method of claim 1 wherein a configuration includes at least one row of four seats wherein three seats have a substantially similar alignment and a fourth seat is offset from the three seats. 8. The method of claim 1 wherein a configuration includes at least one row of three seats wherein two seats have a substantially similar alignment and a third seat, proximate an aisle, is wider than the two seats. 9. The method of claim 1 wherein a configuration includes at least one row of seats offset from a fuselage wall. 10. The method of claim 1 wherein a configuration includes alternating rows of three seats and four seats on a first side of a central aisle and rows of three seats on a second side of the central aisle, wherein each of the sets of seats includes a first seat positioned substantially proximate a wall of the fuselage. 11. A method for configuring an aircraft, the method comprising: varying a set of structural design parameters for a fuselage of the aircraft responsive to a set of performance parameters including an area of a cross section of the fuselage;positioning a single aisle along a length of a fuselage of the aircraft;configuring a first set of rows of seats on a first side of the aisle, the set of rows comprising rows of three seats; andconfiguring a second set of rows of seats on a second side of the aisle, the second set of rows comprising alternating rows of four seats and rows of three seats, such that the rows of three seats define an empty space proximate the aisle. 12. The method of claim 11, wherein a passenger area has a set number of seats. 13. The method of claim 11, wherein the set of performance parameters includes a shape of a cross section of the fuselage, represented by the equation: (1-h/w*100), where h represents fuselage height and w represents fuselage width, is between about −5 to about 5. 14. The method of claim 11, wherein the varying step is performed to meet a set of design goals for at least one of a passenger density and a set of performance parameters for the fuselage. 15. An aircraft comprising: a fuselage;a passenger area within the fuselage;a plurality of seats in the passenger area;a conventional aisle along a length of the fuselage; anda discrete aisle in the passenger area, positioned proximate the conventional aisle, wherein the discrete aisle includes a space defined between alternating rows of seats wherein a first row of alternating seats has our seats and a second row of alternating seats has three seats. 16. The vehicle of claim 15 wherein a configuration of the seats includes alternating rows of three seats and four seats on a first side of a central conventional aisle and rows of three seats on a second side of the central conventional aisle. 17. A method for configuring an aircraft, the method comprising: varying a set of structural design parameters for a fuselage of the aircraft to meet a set of performance parameters;positioning a single aisle running substantially along a length of the aircraft;configuring a first set of seats on a first side of the aisle, wherein the first set of seats comprises a plurality of rows of three seats;configuring a second set of seats on a second side of the aisle, wherein the second set of seats comprises a plurality of rows of four seats alternating with a plurality of rows of three seats, wherein the plurality of rows of three seats in the second set of seats have a substantially similar alignment beginning proximate a wall of the fuselage such that the rows of three seats define an empty space proximate the aisle. 18. The method of claim 17, wherein the step of varying a set of structural design parameters comprises: varying a fuselage design, wherein a fuselage height to width ratio, represented by the equation: (1-h/w*100), where h represents fuselage height and w represents fuselage width, is between about −5 to about 5. 19. The method of claim 17, wherein the varying is performed to incorporate a set of design goals for a passenger density. 20. An aircraft comprising: a fuselage;an aisle positioned along a length of the fuselage;a first set of rows of seats positioned on a first side of the aisle; anda second set of rows of seats positioned on a second side of the aisle, the second set of rows of seats comprising alternating rows of n seats and alternating rows of n+1 seats, and wherein the rows of n seats define a space proximate the aisle. 21. The aircraft of claim 20 wherein a fuselage height to width ratio, represented by the equation: (1-h/w*100), where h represents fuselage height and w represents fuselage width, is between about −5 to about 5.
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