US20040195454A1

US20040195454A1 - Variable size blended wing body aircraft

Info

Publication number: US20040195454A1
Application number: US10/629,219
Authority: US
Inventors: Mark Page; Jennifer Whitlock; Matthew Wilks
Original assignee: Individual
Current assignee: Individual
Priority date: 2001-04-04
Filing date: 2003-07-29
Publication date: 2004-10-07
Also published as: US6708924B2; US20030192986A1; US6568632B2; EP1247734B1; EP1247734A2; EP1247734A3; US20020145075A1

Abstract

A method for forming a blended wing body aircraft with a modular body. In one embodiment, the configuration or cargo capacity of the aircraft can be varied by adding or subtracting intermediate body structures rather than by adding or subtracting segments from the lateral sides of the aircraft body. Configuration in this manner preserves key aerodynamic parameters and permits several major components to be used in several aircraft configurations, each of which having a different cargo capacity.

Description

CROSS-REFERENCE TO RELATED APPLICATIONS

This application is a divisional application of U.S. patent application Ser. No. 10/437,763 filed May 14, 2003, which is a continuation of U.S. application Ser. No. 09/826,031 filed Apr. 4, 2001 entitled “Variable Size Blended Wing Body Aircraft”, which issued as U.S. Pat. No. 6,568,632 on May 27, 2003.[0001]

FIELD OF THE INVENTION

The present invention generally relates to aircraft and more particularly to an aircraft having a body that is at least partially constructed from a plurality of longitudinally or laterally extending body structures to provide a family of aircraft with each family member having a different cargo capacity.

BACKGROUND OF THE INVENTION

Purchasers of modern airline and cargo aircraft typically require a wide range of capacities to suit the diverse needs of their markets. One option for satisfying these needs is to provide several uniquely designed aircraft, with each design being optimized for an equally unique market. This approach, however, is extremely costly, not only in terms of development and manufacture, but also in terms of their operation, maintenance and servicing. Instead, capacity variations in conventional airline and cargo aircraft are achieved by adding or removing pieces of a constant diameter tubular fuselage section.

In contrast, blended wing body aircraft designs, also known as flying wing designs, lack a “constant” section whose length can be varied so as to provide the desired variation in capacity. Furthermore, the careful shaping of these designs to permit efficient flight at transonic Mach speeds and adequate internal volume negates the incorporation of simplistic changes to the design that add capacity yet unacceptably effect the balance of the aircraft due to the wing sweep that is required at high transonic cruise speeds. Such changes also tend to negatively effect the lofting and aerodynamics of alternate capacity versions.

U.S. Pat. No. 5,909,858 to Hawley discloses on solution for varying the capacity of a blended wing body aircraft. The Hawley design employs a variable size body, a pair of wing assemblies and a pair of transition sections. The body is broken up into a plurality of longitudinally extending segments that are based on a single design but which are mirrored across the centerline of the aircraft. Variable capacity is achieved by simply adding or subtracting pairs the segments from the body. The transition section has a negative sweep angle and couples each side of the body of the aircraft to one of the wing assemblies. While the identically configured segments permit the preservation of a common wing assembly and greatly reduce costs associated with the design, tooling, manufacture and maintenance of the aircraft, several drawbacks of this configuration have been noted.

One such drawback concerns the sharp discontinuity in the wing chord between the wing and the body of the aircraft. This results in a lift distribution that can be unfavorable to drag and stall characteristics. Furthermore, the balance of the aircraft is unlikely to be retained over several differently sized configurations. Accordingly, there remains a need in the art for a blended wing body aircraft having a modular construction that permits easy and cost-effective variations in the size of the aircraft yet which retains balance, aerodynamic loft and aerodynamic performance.

SUMMARY OF THE INVENTION

In one preferred form, the present invention provides a blended wing body aircraft having a pair of aircraft wings and an aircraft body. The aircraft body has a centerbody cabin formed from a plurality of body structures that include a pair of end body structures and at least one intermediate body structure. Each of the plurality of body structures defines a cargo compartment and are arranged about a centerline of the centerbody cabin such that each of the end body structures are juxtaposed between the at least one intermediate body structure and one of the aircraft wings.

In another preferred form, the present invention provides a blended wing body aircraft having a pair of aircraft wings and an aircraft body that is at least partially formed from a plurality of longitudinally-extending body structures. Each of the body structures on a first side of a centerline of the aircraft body is uniquely configured and arranged generally parallel to the centerline of the aircraft body. Each of the body structures on a second side of the centerline of the aircraft body is a mirror-image of an associated one of the body structures on the first side of the centerline of the aircraft body.

In another preferred form, the present invention provides a blended wing body aircraft having a pair of aircraft wings, an aircraft body and a propulsion unit. The aircraft body has a centerbody cabin, which is constructed from a plurality of body structures, and an aft centerbody cabin, which is coupled to a rearward end of the centerbody cabin. The propulsion unit is coupled to the aft centerbody cabin.

In another preferred form, the present invention provides a blended wing body aircraft having a pair of aircraft wings and an aircraft body that is at least partially formed from a plurality of longitudinally-extending body structures. Each of the body structures that are positioned such that their body structure centerline is not coincident with a centerline of the aircraft body includes a tip portion that forms a portion of the leading edge of the blended wing body aircraft. The tip portion has an inner edge with a first portion that extends outwardly away from a centerline of an associated one of the body structures and a second portion that is coupled to the first portion and extends forwardly and outwardly toward the leading edge of the blended wing body aircraft.

In yet another preferred form, the present invention provides a blended wing body aircraft having a pair of aircraft wings and an aircraft body that is at least partially formed from a plurality of longitudinally-extending body structures and a pair of leading edge panels. Each of the body structures that are positioned such that their body structure centerline is not coincident with a centerline of the aircraft body includes a tip portion that terminates rearwardly of a leading edge of the blended wing body aircraft. The tip portion has an inner edge with a first portion that extends outwardly away from a centerline of the aircraft body. Each leading edge panel is coupled to a portion of the body structures and one of the aircraft wings and forms at least a portion of a leading edge of the blended wing body aircraft.

Further areas of applicability of the present invention will become apparent from the detailed description provided hereinafter. It should be understood that the detailed description and specific examples, while indicating the preferred embodiment of the invention, are intended for purposes of illustration only and are not intended to limit the scope of the invention.

BRIEF DESCRIPTION OF THE DRAWINGS

Additional advantages and features of the present invention will become apparent from the subsequent description and the appended claims, taken in conjunction with the accompanying drawings, wherein: [0013]
FIG. 1 is a perspective view of a blended wing body aircraft constructed in accordance with the teachings of the present invention; [0014]
FIG. 2 is an exploded perspective view of the blended wing body aircraft of FIG. 1; [0015]
FIG. 3 is a top view of a portion of the blended wing body aircraft of FIG. 1; [0016]
FIG. 4 is a side view of a portion of the blended wing body aircraft of FIG. 1 illustrating the landing gear in an extended position and a retracted position; [0017]
FIGS. 5A through 5D illustrate a family of differently sized blended wing body aircraft that are based upon the design of the aircraft of FIG. 1; [0018]
FIG. 6 is a top view of a portion of a blended wing body aircraft constructed in accordance with the teachings of another aspect of the present invention; [0019]
FIGS. 7A through 7B are top views of a portion of a family of differently sized blended wing body aircraft that are based upon the design of the aircraft of FIG. 6; [0020]
FIG. 8 is a perspective view of a blended wing body aircraft constructed in accordance with the teachings of another aspect of the present invention; [0021]
FIGS. 9A and 9B are perspective views of a portion of a pair of blended wing body aircraft constructed in accordance with the teachings of yet another aspect of the present invention; [0022]
FIG. 10 is an exploded perspective view of a blended wing body aircraft constructed in accordance with the teachings of another aspect of the present invention; [0023]
FIG. 11 is a top view of a blended wing body aircraft constructed in accordance with the teachings of another aspect of the present invention; [0024]
FIG. 12 is a top view of an aircraft that is similar in construction to that of FIG. 11 but smaller in capacity; [0025]
FIG. 13 is an exploded perspective view of an aircraft that is similar in construction to that of FIG. 11 but larger in capacity; and [0026]
FIG. 14 is an exploded perspective view of an aircraft constructed in accordance with the teachings of yet another aspect of the present invention.[0027]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

With reference to FIGS. 1 through 3 of the drawings, a blended wing body aircraft constructed in accordance with the teachings of the present invention is generally indicated by [0028] reference numeral 10. Aircraft 10 is illustrated to include an aircraft body 12, a pair of aircraft wings 14, a propulsion system 16 which is shown to include a plurality of jet engines, a leading edge 18, which is cooperatively defined by the aircraft-wings 14 and the aircraft body 12 and a centerline 20. The aircraft body 12 and aircraft wings 14 are each illustrated to have positive sweep angles.
In the particular embodiment illustrated, the [0029] aircraft body 12 is shown to include a cockpit 30, a transition section 32, a centerbody cabin 34 and an aft centerbody cabin 36. The transition section 32 is unique to the configuration of the aircraft 10, thereby ensuring that the aircraft 10 will be provided with a smooth aerodynamic and structural transition between the cockpit 30 and the centerbody cabin 34. The transition section 32 is also employed for housing the front aircraft landing gear 38 as illustrated in FIG. 4 and as such, its construction may also be tailored as necessary in response to the space and structural demands imposed by the front aircraft landing gear 38.
The [0030] centerbody cabin 34 is formed from a plurality of longitudinally-extending body structures 50, with each of the body structures 50 on a first side of the centerline 20 of the aircraft 10 being uniquely configured and oriented generally parallel to the centerline 20 of the aircraft 10 and each of the body structures 50 on the other side of the centerline 20 of the aircraft 10 being a mirror-image its associated body structure 50 on the first side of the centerline 20 of the aircraft 10. Each of the body structures 50 defines a cargo compartment 52 that may be used to transport passengers or cargo.
More specifically, the plurality of [0031] body structures 50 includes a pair of end body structures 60 and 60′ and a plurality of intermediate body structures 62 a, 62 a′ and 62 d. Those skilled in the art will understand that the body structures 50 having a primed reference numeral (e.g., 60′) are mirror images of an associated body structure that is located on an opposite side of the centerline 20 of the aircraft 10 and that is designated by a similar but unprimed reference numeral (e.g., 60). As illustrated, the centerbody cabin 34 is configured such that each of the end body structures (e.g., end body structure 60′) is juxtaposed between one of the intermediate body structures (e.g., intermediate body structure 60 a′) and one of the aircraft wings 14. Accordingly, the aircraft 10 does not include a transition section having a negative sweep angle for interconnecting the aircraft body 12 and aircraft wing 14 and as such, there is no sharp discontinuity in the wing chord between the aircraft wing 14 and the centerbody cabin 34. Preferably, each of the body structures 50 terminates at its rearward point at the rear spar 70 of the aircraft 10, thereby forming the aft pressure bulkhead for the aircraft 10 at the intersection between the centerbody cabin 34 and the aft centerbody cabin 36.
In the particular embodiment illustrated, the [0032] outer edge 72 of the end body structures 60 and 60′ includes a first portion 74 that is generally parallel to the centerline 20 of the aircraft 10 and a second portion 76 that is angled outwardly toward the aircraft wing 14 and forwardly toward the leading edge 18 of the aircraft 10. The outwardly and forwardly depending second portion 76 of the outer edge 72 reduces the length of the joint 78 between the end body sections 60 and 60′ and its mating aircraft wing 14 and improves the strength of the leading edge 18 of the aircraft 10. As shown, the second portion 76 of the outer edge 72 and the leading edge 18 of the aircraft 10 are substantially perpendicular to one another.
In the particular embodiment illustrated, each of the [0033] body structures 50 that is positioned such that its centerline 80 is not coincident with the centerline 20 of the aircraft 10 includes a tip portion 82. The tip portion 82 includes a forward portion 84 that forms a portion of the leading edge 18 of the aircraft 10. The tip portion 82 includes an inner edge 86 that is configured to mate with a forwardly positioned portion of the aircraft body 12. For example, the inner edge 86 of the tip portion 82 of end body structure 60′ is configured to mate with the forwardly positioned portion of intermediate body structure 62 a′. Similarly, the inner edge 86 of the tip portion 82 of the intermediate body structure 62 a is configured to mate with the forwardly positioned transition section 32 to create a smooth loft at the intersection therebetween.
The [0034] aft centerbody cabin 36 fairs out the body of the aircraft 10 and into the aircraft wings 14 and forms a portion of the trailing edge 88 of the aircraft 10. In the particular embodiment illustrated, the aft centerbody cabin 36 serves at the mounting point for the propulsion system 16. Preferably, the aft centerbody cabin 36 is unique to the configuration of the aircraft 10, thereby permitting the structural and aerodynamic characteristics of the aft centerbody cabin 36 to be tailored in a desired manner so as to better integrate the propulsion system 16 into the aircraft 10.
In the embodiment illustrated, a [0035] portion 90 of each of the outboard sides 92 of the aft centerbody cabin 36 is shown to be skewed to the centerline 20 of the aircraft body 12, angling forwardly and outwardly from the trailing edge 88 of the aircraft 10. Another portion 94 of each of the outboard sides 92 is shown to be skewed to the forwardly and outwardly angled portion 90 by an angle that is less than 180 degrees. The forwardly and outwardly angled portion 90 of the aft centerbody cabin 36 is complementary to the inwardly and rearwardly angled portion 96 of the aircraft wings 14 and aids in locking the aft centerbody cabin 36 and aircraft wings 14 together.
With additional reference to FIGS. 5A through 5D, the modular design of the [0036] aircraft 10 is employed to provide a family of differently configured aircraft which includes the aircraft 10 and the aircraft designated by reference numerals 100, 110, 120 and 130. The aircraft 100, for example, includes the aircraft wings 14, the end body structures 60 and 60′ and the cockpit 30 that are common to aircraft 10. The aircraft 100, however, includes an intermediate body structure 62 c, a transition section 32 a, an aft centerbody cabin 36 a and a propulsion system 16 a that are unique to this configuration.
A relatively higher degree of similarity is found between the [0037] aircraft 110, 120 and 130 and the aircraft 10 as the aircraft wings 14, the end body structures 60 and 60′, the intermediate body structures 62 a and 62 a′ and the cockpit 30 that are common to all of these aircraft. The aircraft 120 includes a pair of intermediate body structures 62 b and 62 b′ that are not employed by any of the smaller aircraft but which are employed by the larger aircraft 130. The aircraft 110 and 120 each include unique transition sections 32 b and 32 c, respectively, unique aft centerbody cabins 36 b and 36 c, respectively, unique propulsion systems 16 b and 16 c, respectively. The aircraft 130 includes a unique intermediate body structure 62 e, a unique transition section 32 d, a unique aft centerbody cabin 36 d and a unique propulsion system 16 d. Those skilled in the art will understand that although the transition sections are described herein as being unique to each aircraft configuration, it is within the scope of the present invention to employ a transition section that is common to each of the aircraft configurations. Unique transition sections are presently preferred to provide the aircraft configuration with a smooth aerodynamic and structural transition between the cockpit 30 and the centerbody cabin 34 since in some instances it may be necessary to shift the cockpit 30 up or down relative to the centerbody cabin 34.
From the foregoing, it should be apparent to those skilled in the art that the capacity of the [0038] aircraft 10 is varied by adding or subtracting body structures 50 from the middle of the centerbody cabin 34, rather than by adding or subtracting body structures 50 from the lateral sides of the centerbody cabin 34. Construction in this manner permits the intermediate body structures 62 a, 62 a′, 62 b, 62 b′, 62 c, 62 d and 62 e to be tailored to the handle the progressively larger wing bending loads that are associated with the larger aircraft configurations. In this regard, the construction of each of the body structures 50 on a first side of the centerline 20 of the aircraft 10 varies-such that the maximum wing bending load of a body structure 50 located closer to the centerline 20 (e.g., intermediate body structure 62 a) is greater than the maximum wing bending load of a body structure 50 located further from the centerline 20 (e.g., end body structure 60). The aircraft wings 14, being common across the entire family of aircraft 10, 100, 110, 120 and 130, are designed to handle the highest wing bending loads. The smallest aircraft in the family (i.e., aircraft 100) would then suffer a modest weight penalty, but this could be reduced or eliminated by re-gauging the aircraft wings 14 in the manner in which conventional wings are sometimes re-gauged today.
While the [0039] aircraft 10 has been described thus far as having a plurality of body structures 50 that cooperate to define both a centerbody cabin and a portion of the leading edge 18 of the aircraft 10, those skilled in the art will appreciate that the invention, in its broader aspects, may be constructed somewhat differently. For example, the body structures 50 may be configured to terminate rearwardly of the leading edge of the aircraft 10 a as illustrated in FIG. 6. In this arrangement, the portion of the leading edge 18 that had formerly been associated with the centerbody cabin 34 is defined by a pair of leading edge panels 150 and 150′ that are coupled to the aircraft body 12 a and the aircraft wings 14. With additional reference to FIGS. 7A through 7B, the length of the leading edge panels 150 and 150′ is illustrated to change in accordance with variations in the capacity of the aircraft.
Another example is illustrated in FIG. 8 wherein the [0040] aircraft 10 b is shown to be substantially similar to aircraft 10 except for the construction of the aft end of the aircraft body 12 b. In this regard, the body structures 50 b that form a portion of the aircraft body 12 b are lengthened to form the trailing edge 88 of the aircraft, eliminating the need for the aft centerbody cabin 36.
Yet another example is illustrated in FIGS. 8A and 8B wherein the [0041] aircraft 10 c and 10 d is shown to be substantially similar to aircraft 10 except with regard to the connection of the centerbody cabin 34 to the cockpit 30. As discussed above, the aircraft 10 includes a transition section 32 that is disposed between the centerbody cabin 34 and the cockpit 30. The aircraft 10 c, however, includes an intermediate body structure 160 having a cockpit transition portion 162, which permits the cockpit 30 to be coupled directly to the centerbody cabin 34. Similarly, the aircraft 10 d includes intermediate body structures 170 and 170′, each of which having a cockpit transition portion 172, which, after the intermediate body structures 170 and 170′ are coupled to one another, permits the cockpit 30 to be coupled directly to the centerbody cabin 34.
A further example is illustrated in FIG. 10 wherein an aircraft constructed in accordance with the teachings of another alternate embodiment is generally indicated by [0042] reference numeral 210. Aircraft 210 is generally similar to aircraft 10 in that it includes an aircraft body 212, a pair of aircraft wings 14, a propulsion system 16, a leading edge 218 and a centerline 20. The aircraft body 212 includes a cockpit 30, a transition section 232, a centerbody cabin 234 and an aft centerbody cabin 36. The centerbody cabin 234 differs from the centerbody cabin 34 in that it is formed from a plurality of longitudinally extending body structures 250 a, an upper body skin assembly 250 b and a lower body skin assembly 250 c, as opposed to the set of body structures 50 wherein each of the body structures 50 includes both its structural framing and its upper and lower skins. The body structures 250 a essentially form a frame or skeleton onto which the upper and lower body skins 250 b and 250 c are attached.
The [0043] transition section 232 likewise differs from the transition section 32 in that it is formed from a transition frame assembly 232 a, an upper skin assembly 232 b and a lower skin assembly 232 c. A pair of leading edge skins 218 a cover the leading edge ribs 218 b that are formed into the body structures 250 a and the transition frame assembly 232 a. In the particular embodiment illustrated, upper skin assembly 232 b is shown to be coupled to upper body skin assembly 250 b to form a portion of the upper outer body surface 212 b. Similarly, the lower skin assembly 232 c is shown to be coupled to lower body skin assembly 250 c to form a portion of the lower outer body surface 212 c. Those skilled in the art will understand, however, that while the portions of the upper and lower outer body surfaces 212 b and 212 c are shown as a complete assembly that is exploded from the body structures 250 a and the transition frame assembly 232 a, the upper and lower outer body surfaces 212 b and 212 c are preferably coupled to the body structures 250 a and the transition frame assembly 232 a in segments 212 d, rather than as a complete assembly.
Construction in this manner permits the [0044] segments 212 d to run span-wise (i.e., perpendicular to the centerline 20) to thereby reinforce the structure of the aircraft body 212 while permitting a relatively high degree of flexure. Accordingly, the aircraft body 212 is relatively stronger and lighter in weight than aircraft body 12.
Another example is illustrated in FIG. 11, wherein an aircraft constructed in accordance with the teachings of another alternate embodiment is generally indicated by [0045] reference numeral 310. Aircraft 310 is generally similar to aircraft 10 in that it includes an aircraft body 312, a pair of aircraft wings 14, a propulsion system 16, a leading edge 18 and a centerline 20. The aircraft body 312 includes a cockpit 30, a transition section 32, a centerbody cabin 334 and an aft centerbody cabin 36. The centerbody cabin 334 differs from the centerbody cabin 34 in that it is formed from a plurality of laterally extending (i.e., spanwise) body structures 350, as opposed to a set of longitudinally extending body structures 50 (FIG. 1). The body structures 350 a and 350 b are shown to abut the lateral sides 14 a of the aircraft wings 14 and do not form any portion of the leading edge 18 of the aircraft 310. The body structure 350 c abuts the forward surface 14 b of the aircraft wings 14, as well as the forward surface 350 bf of the body structure 350 b and defines a portion of the leading edge 18.
With additional reference to FIGS. 12 and 13, the capacity of the [0046] aircraft 310 is varied by altering the configuration of the body structures 350. FIG. 12, for example, illustrates an aircraft 310′ having a relatively smaller capacity than that of aircraft 310. As shown, the width of the body structures 350 a′ and 350 b′ is relatively smaller than that of the body structures 350 a and 350 b, and both the length and width of the body structure 350 c′ are relatively smaller than the length and width of the body structure 350 c. FIG. 13 similarly illustrates an aircraft 310″ having a relatively larger capacity than that of aircraft 310. As shown, the width of the body structures 350 a″ and 350 b″ is relatively larger than that of the body structures 350 a and 350 b, and both the length and width of the body structure 350 c″ are relatively larger than the length and width of the body structure 350 c. While the configuration of the aircraft 310 in this manner prevents multiple the body structures 350 from being used across a family of aircraft, the use of spanwise extending body structures 350 is structurally efficient, permitting the overall weight of the aircraft 310 to be reduced as compared to that of aircraft 10.
In FIG. 14, an aircraft constructed in accordance with the teachings of yet another alternate embodiment is generally indicated by [0047] reference numeral 410. Aircraft 410 is generally similar to aircraft 10 in that it includes an aircraft body 412, a pair of aircraft wings 14, a propulsion system 16, a leading edge 18. The aircraft body 412 includes a cockpit 30, a transition section 432, a centerbody cabin 434 and an aft centerbody cabin 36. Unlike the previously described embodiments, the transition section 432 and the centerbody cabin 434 are not modular in their form, but rather are formed from a plurality of components that are collectively assembled when the aircraft 410 is being assembled. The centerbody cabin 434 is shown to include a lower cover panel 500, a cargo floor 502, a plurality of lower ribs 504, an intermediate spar 506, a rear spar 508, a floor 510, a plurality of upper ribs 512, an upper cover panel 514, a pair of leading edge frames 516 and a pair of leading edge skins 518. The transition section 432 includes a transition frame 520 and lower and upper cover panels 522 and 524, respectively.
The construction of the [0048] lower ribs 504 is such that their cross-sections are identical, and that the overall length of each of the lower ribs 504 is adjusted according to its placement within the centerbody cabin 434 as well as the overall capacity of the aircraft 410. Similarly, the construction of the upper ribs 512 is such that their cross-sections are identical, and that the overall length of each of the upper ribs 512 is adjusted according to its placement within the centerbody cabin 434 as well as the overall capacity of the aircraft 410.
In varying the capacity of the [0049] aircraft 410, the length and width of the centerbody cabin 434 will grow or shrink as necessary, in much the same manner as the centerbody cabin 34 grows or shrinks when the capacity of aircraft 10 is changed. To accommodate these changes, the spars 506 and 508, the ribs 504 and 512, the leading edge frames 516 and the leading edge skins 518 will grow or shrink in length as necessary, and the length and width of the panels 500 and 514 and the floors 502 and 510 will grow or shrink in length and width as necessary. Additionally, it may also be necessary to add or delete one or more spars 506 and ribs 504 and 512.
While the invention has been described in the specification and illustrated in the drawings with reference to a preferred embodiment, it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted for elements thereof without departing from the scope of the invention as defined in the claims. In addition, many modifications may be made to adapt a particular situation or material to the teachings of the invention without departing from the essential scope thereof. Therefore, it is intended that the invention not be limited to the particular embodiment illustrated by the drawings and described in the specification as the best mode presently contemplated for carrying out this invention, but that the invention will include any embodiments falling within the foregoing description and the appended claims. [0050]

Claims

What is claimed is:

1. A method for manufacturing a blended wing aircraft, the blended wing aircraft including a centerbody cabin and being a member of a family of blended wing aircraft wherein each other member of the family has an associated centerbody cabin with a different capacity, the method comprising:

segregating the centerbody cabin into a plurality of body modules, the body modules being arranged about a centerline of the center body cabin such that a configuration on a first lateral side of the centerbody cabin is a mirror image of a configuration of the body modules on a second lateral side opposite the first lateral side of the centerbody cabin; and

coupling a plurality of the body modules to one another to form the centerbody cabin;

wherein each of the body modules wholly disposed on the first lateral side of the centerbody cabin is uniquely configured in at least one of its length, width and capacity; and

wherein each of the body modules wholly disposed on the first lateral side of the centerbody cabin is also employed in a first lateral side of another member of the family of blended wing aircraft having a larger capacity centerbody cabin.

2. The method of claim 1, further comprising:

forming a pair of wings; and

joining a first one of the wings to the first lateral side of the centerbody cabin and a second one of the wings to the second lateral side of the centerbody cabin.

3. The method of claim 2, wherein the pair of wings are common to the family of blended wing aircraft.

4. The method of claim 2, wherein each of the body modules terminates rearwardly of a leading edge of the blended wing aircraft and the blended wing aircraft cabin further includes a pair of leading edge panels, each of the leading edge panels being coupled to the centerbody cabin and one of the aircraft wings.

5. The method of claim 2, wherein the aircraft wings and the centerbody cabin have positive sweep angles.

6. The method of claim 1, further comprising:

forming an aft centerbody cabin; and

coupling the aft centerbody cabin to an aft end of the centerbody cabin.

7. The method of claim 6, further comprising coupling a propulsion source to the aft centerbody cabin.

8. The method of claim 1, wherein each of the body modules has a body structure centerline, and wherein each of the body modules that is positioned such that its body structure centerline is not coincident with a centerline of the centerbody cabin includes a tip portion that forms a portion of the leading edge of the blended wing body aircraft, the tip portion including an inner edge that is configured to mate with a forwardly positioned portion of the aircraft body.

9. The method of claim 8, wherein an outer edge of an end body module includes a first portion that is generally parallel to the centerline of the centerbody cabin and a second portion that is angled outwardly toward a wing of the blended wing aircraft and forwardly toward the leading edge of the blended wing aircraft.

10. The method of claim 9, wherein the second portion of the outer edge of the end body module is substantially perpendicular to the leading edge.

11. The method of claim 1, further comprising coupling an upper skin assembly and a lower skin assembly to the body modules, each of the upper and lower skin assemblies defining at least a portion of an upper outer surface and a lower outer surface, respectively, of the blended wing aircraft.

12. A method for providing a family of blended wing body aircraft, the family including a plurality of aircraft members, each aircraft member having a centerbody cabin with a different capacity, the method comprising:

forming a pair of wings that are common to each of the aircraft members;

segregating the centerbody cabins into a plurality of body modules, the body modules being arranged about a centerline of each center body cabin such that a configuration on a first lateral side of the centerbody cabin is a mirror image of a configuration of the body modules on a second lateral side opposite the first lateral side of the centerbody cabin;

wherein each of the body modules wholly disposed on the first lateral side of a given one of the centerbody cabins is uniquely configured in at least one of its length, width and capacity; and

wherein each of the body modules wholly disposed on the first lateral side of the given one of the centerbody cabins is also employed in a first lateral side of another aircraft member of the family of blended wing body aircraft whose centerbody cabin capacity is larger than the capacity of the given one of the centerbody cabins.

13. The method of claim 12, wherein each of the body modules terminates rearwardly of a leading edge of the blended wing aircraft and the blended wing aircraft cabin further includes a pair of leading edge panels, each of the leading edge panels being coupled to the centerbody cabin and one of the aircraft wings.

14. The method of claim 12, wherein the aircraft wings and the centerbody cabin have positive sweep angles.

15. The method of claim 12, further comprising:

forming an aft centerbody cabin; and

coupling the aft centerbody cabin to an aft end of the centerbody cabin.

16. The method of claim 15, further comprising coupling a propulsion source to the aft centerbody cabin.

17. The method of claim 12, wherein each of the body modules has a body structure centerline, and wherein each of the body modules that is positioned such that its body structure centerline is not coincident with a centerline of the centerbody cabin includes a tip portion that forms a portion of the leading edge of the blended wing body aircraft, the tip portion including an inner edge that is configured to mate with a forwardly positioned portion of the aircraft body.

18. The method of claim 17, wherein an outer edge of an end body module includes a first portion that is generally parallel to the centerline of the centerbody cabin and a second portion that is angled outwardly toward a wing of the blended wing aircraft and forwardly toward the leading edge of the blended wing aircraft.

19. The method of claim 18, wherein the second portion of the outer edge of the end body module is substantially perpendicular to the leading edge.

20. The method of claim 12, further comprising coupling an upper skin assembly and a lower skin assembly to the body modules, each of the upper and lower skin assemblies defining at least a portion of an upper outer surface and a lower outer surface, respectively, of the blended wing aircraft.