US20040217235A1 - Modular spar tunnel - Google Patents
Modular spar tunnel Download PDFInfo
- Publication number
- US20040217235A1 US20040217235A1 US10/414,390 US41439003A US2004217235A1 US 20040217235 A1 US20040217235 A1 US 20040217235A1 US 41439003 A US41439003 A US 41439003A US 2004217235 A1 US2004217235 A1 US 2004217235A1
- Authority
- US
- United States
- Prior art keywords
- mold
- aircraft
- fuselage
- tunnel
- spar
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000000034 method Methods 0.000 claims abstract description 20
- 230000005484 gravity Effects 0.000 claims abstract description 6
- 238000004519 manufacturing process Methods 0.000 claims description 10
- 239000002131 composite material Substances 0.000 description 4
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000010276 construction Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 238000012508 change request Methods 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/26—Attaching the wing or tail units or stabilising surfaces
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C2211/00—Modular constructions of airplanes or helicopters
Definitions
- the present invention relates to aircraft manufacturing systems and methods.
- the present invention relates to systems and methods for shifting, or repositioning, an aircraft fuselage on a wing during aircraft development or manufacture to adjust the center of gravity (CG) location of a resulting aircraft.
- CG center of gravity
- CG center of gravity
- the CG should not under any condition of fuel loading, passenger loading, cargo loading, or any other type of loading be positioned rearward of a rear stability limit. And, in order to maintain proper control, for example, during take offs and landings, the CG should never be positioned forward of the aerodynamic limit of the aircraft.
- the present invention is directed to systems and methods for adjusting the location of the CG of an aircraft by shifting, or repositioning, the fuselage of an aircraft on its wing without requiring a complete retooling of the fuselage and wing assembly.
- a modular spar tunnel is provided within a mold for constructing a fuselage section of an aircraft.
- the modular spar tunnel is configured to engage, or be mounted within, a main mold for a portion (typically the right or left side) of the fuselage of the aircraft.
- the spar tunnel of an aircraft can be shifted forward or rearward within a fuselage section of an aircraft without a major retooling operation, and without modifying other elements or aspects of the aircraft.
- major retooling of the molds used to manufacture the aircraft may not be required.
- the present invention is directed to a method for assembling a fuselage of an aircraft using a multi-component molding and composite manufacturing process.
- a modular spar tunnel of the type described above is utilized to locate a spar tunnel within a fuselage of an aircraft, and layers of composite fiber are laid up within the mold, and thereafter cured, to form a portion of the fuselage of the aircraft.
- it is possible to accommodate significant design variations between aircraft without engaging in a major retooling process and incurring the costs associated with such retooling.
- FIG. 1 is an illustration of a mold incorporating a modular spar tunnel in accordance with a preferred form of the present invention.
- FIG. 2 is an enlarged illustration of a modular spar tunnel in accordance with a preferred form of the present invention.
- FIG. 1 A preferred form of the modular spar tunnel tool is shown in FIG. 2.
- the mold 20 has provided thereon a plurality of raised members 22 that preferably are designed to engage a corresponding set of recesses 12 provided within the modular spar tunnel tool 10 .
- the location of the spar tunnel of an aircraft can be readily adjusted to adjust for other design criteria, such as modifications to a seating arrangement or substitution of a propulsion system.
- the modular spar tunnel tool 10 preferably is manufactured from composite materials, such as carbon fiber or KEVLARTM, but those skilled in the art will understand that the modular spar tunnel tool 10 also can be manufactured from metal, such as aluminum, or any other material, so long as the material can withstand the conditions present in a typical composite curing process.
- the modular spar tunnel tool 10 preferably includes a pair of raised sections 14 ( a ) and 14 ( b ) for defining the spar tunnel of an aircraft fuselage and a mounting plate 16 for engaging the mold 20 for the main aircraft fuselage.
- the mounting plate 16 preferably has a plurality of recesses 12 formed therein for receiving a corresponding set of raised or protruding members 22 provided on the mold 22 .
- the recesses 12 may have a semi-spherical shape corresponding to a semi-spherical shape of the raised or protruding members 22 .
- the raised or protruding members 22 can take the form of pins
- the recesses 12 can take the form of a plurality of holes provided in the mounting plate 16 of the modular spar tunnel tool 10 .
- main body 18 including the raised sections 14 ( a ) and 14 ( b )
- mounting plate 16 of the modular spar tunnel tool 10 can be manufactured as a single unit or, alternatively, the various portions of the modular spar tunnel tool 10 can be manufactured separately and combined prior to being placed within the main mold 20 .
- the present invention provides, among other things, an improved system and method for manufacturing a series of aircraft and, in particular, an improved system and method for adjusting the CG and/or spar tunnel location within a series of aircraft.
Abstract
Description
- The present invention relates to aircraft manufacturing systems and methods. In particular, but not by way of limitation, the present invention relates to systems and methods for shifting, or repositioning, an aircraft fuselage on a wing during aircraft development or manufacture to adjust the center of gravity (CG) location of a resulting aircraft.
- In the avionics field, proper positioning of the center of gravity (CG) of an aircraft is essential. For example, if the CG of an aircraft is positioned too far forward of the aerodynamic center of the wing, a pilot can experience significant difficulty in attempting to control the aircraft during flight. Similarly, if the CG of the aircraft is positioned to far aft of the aerodynamic center of the wing, the aircraft will become inherently unstable.
- Stated somewhat differently, in order to maintain proper stability of an aircraft, the CG should not under any condition of fuel loading, passenger loading, cargo loading, or any other type of loading be positioned rearward of a rear stability limit. And, in order to maintain proper control, for example, during take offs and landings, the CG should never be positioned forward of the aerodynamic limit of the aircraft.
- One, thus, can readily understand that, when design criteria are altered for an aircraft, such as when a different passenger seating configuration is selected or a different propulsion system is selected, it can become necessary to shift, or reposition, the fuselage of an aircraft on its wing. And, where conventional aircraft manufacturing systems and techniques are employed, this can result in a complete redesign of the aircraft and the tools used to build or assemble it.
- Those skilled in the art of aircraft manufacture and design will appreciate, therefore, that a need exists for an improved method of repositioning a fuselage on a wing, when significant design changes are encountered in an aircraft development process.
- Exemplary embodiments of the present invention that are shown in the drawings are summarized below. These and other embodiments are more fully described in the Detailed Description section. It is to be understood, however, that there is no intention to limit the invention to the forms described in this Summary of the Invention or in the Detailed Description. One skilled in the art can recognize that there are numerous modifications, equivalents and alternative constructions that fall within the spirit and scope of the invention as expressed in the claims.
- In one particularly innovative aspect, the present invention is directed to systems and methods for adjusting the location of the CG of an aircraft by shifting, or repositioning, the fuselage of an aircraft on its wing without requiring a complete retooling of the fuselage and wing assembly.
- In one presently preferred embodiment, a modular spar tunnel is provided within a mold for constructing a fuselage section of an aircraft. The modular spar tunnel is configured to engage, or be mounted within, a main mold for a portion (typically the right or left side) of the fuselage of the aircraft. In this fashion, the spar tunnel of an aircraft can be shifted forward or rearward within a fuselage section of an aircraft without a major retooling operation, and without modifying other elements or aspects of the aircraft. Thus, if a different propulsion system is selected for an aircraft design, major retooling of the molds used to manufacture the aircraft may not be required.
- In another innovative aspect, the present invention is directed to a method for assembling a fuselage of an aircraft using a multi-component molding and composite manufacturing process. A modular spar tunnel of the type described above is utilized to locate a spar tunnel within a fuselage of an aircraft, and layers of composite fiber are laid up within the mold, and thereafter cured, to form a portion of the fuselage of the aircraft. Using methods in accordance with the present invention, it is possible to accommodate significant design variations between aircraft without engaging in a major retooling process and incurring the costs associated with such retooling.
- As previously stated, the above-described embodiments and implementations are for illustration purposes only. Numerous other embodiments, implementations, and details of the invention are easily recognized by those of skill in the art from the following descriptions and claims.
- Various objects and advantages and a more complete understanding of the present invention are apparent and more readily appreciated by reference to the following Detailed Description and to the appended claims when taken in conjunction with the accompanying Drawings wherein:
- FIG. 1 is an illustration of a mold incorporating a modular spar tunnel in accordance with a preferred form of the present invention.
- FIG. 2 is an enlarged illustration of a modular spar tunnel in accordance with a preferred form of the present invention.
- Referring now to the drawings, where like or similar elements are designated with identical reference numerals throughout the several views, and referring in particular to FIG. 1, a modular
spar tunnel tool 10 is shown mounted within amold 20 for a portion of an airplane fuselage. A preferred form of the modular spar tunnel tool is shown in FIG. 2. - As shown in the drawings, the
mold 20 has provided thereon a plurality of raisedmembers 22 that preferably are designed to engage a corresponding set ofrecesses 12 provided within the modularspar tunnel tool 10. Thus, by adjusting the position of the modularspar tunnel tool 10 within themold 20, the location of the spar tunnel of an aircraft can be readily adjusted to adjust for other design criteria, such as modifications to a seating arrangement or substitution of a propulsion system. - Turning now in detail to FIG. 2, the modular
spar tunnel tool 10 preferably is manufactured from composite materials, such as carbon fiber or KEVLAR™, but those skilled in the art will understand that the modularspar tunnel tool 10 also can be manufactured from metal, such as aluminum, or any other material, so long as the material can withstand the conditions present in a typical composite curing process. - The modular
spar tunnel tool 10 preferably includes a pair of raised sections 14(a) and 14(b) for defining the spar tunnel of an aircraft fuselage and amounting plate 16 for engaging themold 20 for the main aircraft fuselage. As noted above, themounting plate 16 preferably has a plurality ofrecesses 12 formed therein for receiving a corresponding set of raised or protrudingmembers 22 provided on themold 22. In a currently preferred form, therecesses 12 may have a semi-spherical shape corresponding to a semi-spherical shape of the raised or protrudingmembers 22. - Those skilled in the art, however, will appreciate that numerous other methodologies can be employed for positioning the modular spar tunnel tool within the
main mold 20, and that the present invention should not be limited to the particular embodiments described herein. For example, in alternative embodiments, the raised or protrudingmembers 22 can take the form of pins, and therecesses 12 can take the form of a plurality of holes provided in themounting plate 16 of the modularspar tunnel tool 10. - Those skilled in the art also will appreciate that the main body18 (including the raised sections 14(a) and 14(b)) and the
mounting plate 16 of the modularspar tunnel tool 10 can be manufactured as a single unit or, alternatively, the various portions of the modularspar tunnel tool 10 can be manufactured separately and combined prior to being placed within themain mold 20. - Finally, those skilled in the art will appreciate that, where a modular
spar tunnel tool 10 in accordance with various forms of the present invention is used to manufacture a series of aircraft, adjustments to the spar location of the aircraft can be made relatively easily without significant retooling of the manufacturing process. This allows aircraft manufacturers using a modularspar tunnel tool 10 in accordance with the present invention to much more quickly respond to customer design change requests and other design and development issues that may arise during the creation of a line of aircraft. - In conclusion, the present invention provides, among other things, an improved system and method for manufacturing a series of aircraft and, in particular, an improved system and method for adjusting the CG and/or spar tunnel location within a series of aircraft. Those skilled in the art can readily recognize that numerous variations and substitutions may be made in the invention, its use and its configuration to achieve substantially the same results as achieved by the embodiments described herein. Accordingly, there is no intention to limit the invention to the disclosed exemplary forms. Many variations, modifications and alternative constructions fall within the scope and spirit of the disclosed invention as expressed in the claims.
Claims (5)
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/414,390 US6811120B1 (en) | 2003-04-15 | 2003-04-15 | Modular spar tunnel |
PCT/US2004/011516 WO2005002961A2 (en) | 2003-04-15 | 2004-04-15 | Methods for manufacturing composite aircraft, parts and a family of composite aircraft |
US11/249,502 US7478780B2 (en) | 2003-04-15 | 2005-10-14 | Methods for manufacturing composite aircraft, parts and a family of composite aircraft |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/414,390 US6811120B1 (en) | 2003-04-15 | 2003-04-15 | Modular spar tunnel |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/US2004/011516 Continuation WO2005002961A2 (en) | 2003-04-15 | 2004-04-15 | Methods for manufacturing composite aircraft, parts and a family of composite aircraft |
Publications (2)
Publication Number | Publication Date |
---|---|
US6811120B1 US6811120B1 (en) | 2004-11-02 |
US20040217235A1 true US20040217235A1 (en) | 2004-11-04 |
Family
ID=33298379
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US10/414,390 Expired - Fee Related US6811120B1 (en) | 2003-04-15 | 2003-04-15 | Modular spar tunnel |
US11/249,502 Expired - Fee Related US7478780B2 (en) | 2003-04-15 | 2005-10-14 | Methods for manufacturing composite aircraft, parts and a family of composite aircraft |
Family Applications After (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US11/249,502 Expired - Fee Related US7478780B2 (en) | 2003-04-15 | 2005-10-14 | Methods for manufacturing composite aircraft, parts and a family of composite aircraft |
Country Status (2)
Country | Link |
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US (2) | US6811120B1 (en) |
WO (1) | WO2005002961A2 (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20100032521A1 (en) * | 2005-11-21 | 2010-02-11 | Airbus France | Landing gear casing provided with a dissociated structure |
Families Citing this family (10)
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US8029642B2 (en) | 2007-07-27 | 2011-10-04 | The Boeing Company | Tape removal apparatus and process |
US7809454B2 (en) * | 2007-09-17 | 2010-10-05 | The Boeing Company | Method and apparatus for simulating composite panel manufacturing |
US8345269B2 (en) | 2007-09-22 | 2013-01-01 | The Boeing Company | Method and apparatus for measuring the width of composite tape |
US7922856B2 (en) | 2008-01-02 | 2011-04-12 | The Boeing Company | Graphite tape supply and backing paper take-up apparatus |
US8557074B2 (en) | 2008-02-27 | 2013-10-15 | The Boeing Company | Reduced complexity automatic fiber placement apparatus and method |
US8986482B2 (en) | 2008-07-08 | 2015-03-24 | The Boeing Company | Method and apparatus for producing composite structures |
US8308101B2 (en) | 2009-03-09 | 2012-11-13 | The Boeing Company | Simplified fiber tensioning for automated fiber placement machines |
US8454788B2 (en) | 2009-03-13 | 2013-06-04 | The Boeing Company | Method and apparatus for placing short courses of composite tape |
GB201110973D0 (en) * | 2011-06-28 | 2011-08-10 | Airbus Operations Ltd | Bracket |
CN104229157B (en) * | 2014-08-26 | 2017-11-03 | 中国直升机设计研究所 | A kind of helicopter limit center of gravity stowage method |
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US4901950A (en) * | 1986-12-31 | 1990-02-20 | Judge Richard J | Aircraft fuselage |
US5062589A (en) * | 1989-02-28 | 1991-11-05 | Dornier Luftfahrt Gmbh | Fiber reinforced pressure bulkhead with integrated frame |
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US5975464A (en) * | 1998-09-22 | 1999-11-02 | Scaled Composites, Inc. | Aircraft with removable structural payload module |
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-
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-
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- 2005-10-14 US US11/249,502 patent/US7478780B2/en not_active Expired - Fee Related
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US5223067A (en) * | 1990-02-28 | 1993-06-29 | Fuji Jukogyo Kabushiki Kaisha | Method of fabricating aircraft fuselage structure |
US5216799A (en) * | 1990-11-09 | 1993-06-08 | British Aerospace Public Limited Company | Carbon fibre composite wing manufacture |
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US20100032521A1 (en) * | 2005-11-21 | 2010-02-11 | Airbus France | Landing gear casing provided with a dissociated structure |
US8336819B2 (en) * | 2005-11-21 | 2012-12-25 | Airbus Operations Sas | Landing gear casing provided with a dissociated structure |
Also Published As
Publication number | Publication date |
---|---|
US20060169400A1 (en) | 2006-08-03 |
US6811120B1 (en) | 2004-11-02 |
WO2005002961A3 (en) | 2005-07-28 |
WO2005002961A2 (en) | 2005-01-13 |
US7478780B2 (en) | 2009-01-20 |
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Legal Events
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Owner name: ADAM AIRCRAFT INDUSTRIES, INC., COLORADO Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:WILDING, JOSEPH RAY;OLCOTT, DENNIS D.;REEL/FRAME:014330/0096;SIGNING DATES FROM 20030509 TO 20030519 |
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Owner name: VECTRA BANK COLORADO, N.A., COLORADO Free format text: NOTICE OF GRANT OF SECURITY INTEREST;ASSIGNOR:ADAM AIRCRAFT INDUSTRIES, INC.;REEL/FRAME:016226/0547 Effective date: 20050104 |
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