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WO1986003172A1 - Conception graduee d'aeronefs et procede de construction - Google Patents

Conception graduee d'aeronefs et procede de construction Download PDF

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Publication number
WO1986003172A1
WO1986003172A1 PCT/US1985/002284 US8502284W WO8603172A1 WO 1986003172 A1 WO1986003172 A1 WO 1986003172A1 US 8502284 W US8502284 W US 8502284W WO 8603172 A1 WO8603172 A1 WO 8603172A1
Authority
WO
WIPO (PCT)
Prior art keywords
airfoil
constructing
tooling means
size
series
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.)
Ceased
Application number
PCT/US1985/002284
Other languages
English (en)
Inventor
William W. Fox
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Fox Brothers LP
Original Assignee
Fox Brothers LP
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Fox Brothers LP filed Critical Fox Brothers LP
Priority to BR8507073A priority Critical patent/BR8507073A/pt
Publication of WO1986003172A1 publication Critical patent/WO1986003172A1/fr
Priority to PCT/US1986/001324 priority patent/WO1987003265A1/fr
Priority to JP61504012A priority patent/JPS63501787A/ja
Priority to EP19860904540 priority patent/EP0247063A4/fr
Priority to AU61403/86A priority patent/AU587058B2/en
Priority to HU863545A priority patent/HUT47487A/hu
Priority to NO864609A priority patent/NO864609L/no
Anticipated expiration legal-status Critical
Priority to FI873214A priority patent/FI873214A0/fi
Ceased legal-status Critical Current

Links

Classifications

    • 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
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/12—Canard-type aircraft
    • 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
    • B64C2001/0018—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like comprising two decks adapted for carrying passengers only
    • B64C2001/0027—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like comprising two decks adapted for carrying passengers only arranged one above the other
    • 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
    • B64C2001/0045—Fuselages characterised by special shapes
    • 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
    • B64C2001/0054—Fuselage structures substantially made from particular materials
    • B64C2001/0072—Fuselage structures substantially made from particular materials from composite materials
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C2211/00—Modular constructions of airplanes or helicopters
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/10—Drag reduction
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction

Definitions

  • the present invention relates to design and construction methods for aircraft, and especially to those aimed at building a size-graduated series of aircraft having a consistent scale relationship between aircraft of different sizes with a minimum of development and production costs.
  • the first object of the present invention is to reduce aircraft development and certification costs by utilizing a graduated aircraft design approach to produce a series of individual point designs for a wide variety of different-size aircraft that all look alike, fly alike and perform alike because each model is a scale equivalent of other models in the series with respect to airfoil shape and configuration. Models of a series utilize unique cabin arrangements and propulsion systems selected to match the specific mission requirements for the particular model.
  • the second object of the invention is to reduce aircraft manufacturing costs by maximizing reuseability of molds, jigs, templates, or other tooling for the production of airfoils and fuselage nose and tail cones between the various models of a size-graduated series.
  • Figure 1A is a top plan view of the ideal configuration
  • Figure IB is a side elevational view of the ideal configuration
  • Figure 1C is a front elevational view of the ideal configuration
  • Figure 2 is a graph of wing area vs. wing span for a wing with an aspect ratio of 10. Points on the graph indicate wing area and span for various models within the illustrated series of aircraft;
  • Figure 3 is a top plan view showing a mold for the production of the main wing airfoil semi-span of any model within the graduated series of aircraft;
  • Figure 4 is a side elevational view showing the mold for the production of the vertical airfoil -6-
  • Figure 5 is a top plan view showing the mold for the production of the canard airfoil semi-span of any model within the graduated series of aircraft;
  • Figures 6A through 6H are top plan views of the tail section of different models showing the mounting of various types of propulsion systems;
  • Figures 7A through 7H ar.e elevational front views of the fuselages for the different-sized models within a suggested series of aircraft, in order of ascending size;
  • Figures 8A through 8H are elevational side views of the different sized models within a suggested series of aircraft whose fuselages are shown in Figures 7A through 7H;
  • Figures 9ft through 9H are perspective views of each of the conceptual point designs, corresponding respectively to the aircraft of Figures 8A through
  • the forward-swept wing has several aerodynamic advantages well-known in the art.
  • Adverse yaw while banking, as well as the tendency to roll while slipping are both greatly reduced or altogether eliminated.
  • the forward-swept wing combined with aft-mounted power make possible the exclusion of all fuel and fuel lines from the crew and passenger fuselage envelope.
  • the canard will eliminate "deep stall" problems because it is never in the wake of the main wing airfoil- At high angles of attack, the canard creates high- energy vortices that wash over the center section of the main wing, delaying boundary separation in airflow over that section. therefore delaying a stall of that section. Additionally, if the canard's fixed angle of attack is greater than that of the aft-mounted wing, the canard will stall first. causing the nose of the aircraft to drop before the aft-mounted wing reaches its critical angle of attack. Since low-altitude stalls are .the single largest cause of fatal civil aviation crashes. ah aircraft utilizing a canard-type. horizontal surface offers an important safety advantage over aircraft of conventional design.
  • Fiqure 1 is especially suited for far-aft-mounted engines, with maximum safety in the event of a powerplant- related fire- since flames and other hot gasses cannot impinge directly on the primary aircraft structure, but are dissipated in the free airstream.
  • the forward-swept, aft-mounted wing 12 of the ideal configuration of Fig. 1 can accomodate leading edge flaps or slats 14 and full-span flaps 15 to improve the coefficient of lift for shorter takeoff and landings if the mission requirements of a specific model so dictate.
  • Lateral control can be achieved through the use of spoilers 16 or by differential use of the wing flaps 15.
  • the canard airfoil 11 mounted on the forward fuselage, provides the necessary longitudinal stability and control.
  • Longitudinal control can be obtained by means of a conventional elevator 17 or by movement of the entire surface as a slab.
  • Longitudinal trim can be achieved by means of a conventional trim tab 18 or by trimming the stabilizer surface.
  • the vertical airfoil 13 mounted on the aft-end of the fuselage provides the necessary directional stability and control.
  • Directional control is achieved through the use of a conventional rudder 19 and directional trim is achieved by means of a conventional trim tab 20.
  • the graduated design method is illustrated in
  • Fig. 2 with a graph of wing area vs. wing span for an aspect ratio of ten.
  • Points 21, 22, 23 and 24 represent proposed wing areas and wing spans for single-engine models of two, four, six and eight-place capacity, respectively.
  • Points 25, 26, 27 and 28 represent proposed wing areas and wing spans for twin-engine models of eight, ten, twelve and fourteen-place capacity, respectively.
  • FIGs 3, 4 and 5 The high degree of reuseability of the manufacturing molds for the wing, horizontal and vertical surfaces for the eight specific models chosen to illustrate the graduated design and consruction method is shown in Figures 3, 4 and 5, respectively.
  • Each mold is capable of producing a universal airfoil 31, 41 and 51, which would be the length of the entire mold, and which accomodates all models in the size graduated series.
  • the surfaces for the two-place airplane 32, 42 and 52 are those with the smallest tip and root chords.
  • the surfaces for the four-place airplane 33, 43 and 53 do not use a small portion of the tip of the two-place airplane 'surfaces 34, 44 and 54.
  • the surfaces"'for the four-place airplane are lengthened and enlarged at the inboard end to obtain the desired four-place airplane root chord 35, 45 and 55.
  • This step by step process is repeated in a like manner for each successive model in the entire product line.
  • the degree of reuseability of the manufacturing molds, jigs, templates or other tooling for airfoil surfaces is dictated by the magnitude of step increase in size from one model to the next.
  • required design loads are also increased.
  • it will be necessary, in the case of an airfoil manufactured of composite materials to increase the reinforcing material in the composite layup for the airfoil structures.
  • the cross sectional area of the load-supporting elements such as spars or stressed skin will require augmentation over the length of the span-
  • This graduated scale construction method applies to any tapered surface. without regard to its sweep angle-
  • a canard, main wing, or vertical airfoil could be constructed from several sets of universal molds, jigs, templates or other tooling.
  • Various propulsion systems may be conveniently installed on the ideal configuration of Fig. 1- as shown in Figures 6A through 6H, to meet the specific mission requirements for each model in a size-graduated series of aircraft-
  • the power plants for the single-engine aircraft are housed in a nacelle that is part of the fuselage tail cone.
  • FIGS 6A and 6B illustrate single and twin mountings of conventional piston engines, respectively.
  • Figures 6C and 6D illustrate single and twin mountings of turbo-prop engines, respectively.
  • Figures 6E and 6F illustrate single and twin mountings of fan-jet engines, respectively.
  • Figures 6G and 6H illustrate single and twin mountings of future prop-fan engines, respectively.
  • Figures 7A through 7H are elevational front views of the fuselages for the eight models chosen to illustrate the graduated design and construction method, in order of ascending size-
  • Figures 8A through 8H are elvational side views of the same eight models in the same ascending order.
  • Figures 9A through 9H are perspective views of the same eight models in the same ascending order.
  • the high degree of commonality between the fuselages of different models is significant.
  • the eight aircraft utilize nose cones 81A through 81H fabricated in identical molds, with additional reinforcement added for larger models in areas of increased stress.
  • the four single-engine aircraft utilize fuselage tail sections 82A through 82D fabricated in a common mold, with additional composite material reinforcement added for larger models in areas of increased stress.
  • the four twin-engine aircraft utilize fuselage tail sections 83E through 83H fabricated in a common mold, with additional composite material reinforcement added for larger models in the areas of increased stress.
  • the twin engine aircraft all utilize fuselage cockpit sections 84E through 84H fabricated in a common mold. Only the passenger- carrying fuselage sections vary significantly from one model to the next, increasing both in width and length as seating capacity increases.
  • the fuselage is depicted as comprising three sections in Figures 8A through 8H, the process of manufacturing such sections could just as easily be broken down into the manufacture of smaller subunits such as longerons, stringers, frames, skin panels, etc. which could later be used to build an entire fuselage section. While the preferred embodiment- of the invention has been disclosed, other embodiments may be devised and modifications made within the spirit of the invention and within the scope of the appended claims.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Manufacturing & Machinery (AREA)
  • Transportation (AREA)
  • Mechanical Engineering (AREA)
  • Moulding By Coating Moulds (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Compounds Of Unknown Constitution (AREA)
  • Diaphragms For Electromechanical Transducers (AREA)
  • Control Of Motors That Do Not Use Commutators (AREA)

Abstract

Une conception et un procédé de construction d'une série graduée d'aéronefs de plusieurs tailles différentes permettant de minimiser les coûts de développement en maintenant une échelle consistante de modède à modède, et de minimiser les coûts de production en réutilisant au maximum des moules, des calibres, des gabarits et autres outils de fabrication des parties détaillées, des sous-ensembles et des composants des cellules. L'application à part entière de la conception et du procédé de construction est rendue possible en utilisant des matériaux composites connus qui ont une rigidité de flexion et de torsion suffisante pour que l'on puisse continuer une aile (12) montée à l'arrière et inclinée en avant avec un allongement élevé mais un poids modéré. L'aile inclinée vers l'avant et à allongement élevé à son tour permet de construire une cellule ayant, outre une aile principale à profil incliné vers l'avant (12), un profil d'aile en canard (11), une aile montée en arrière du fuselage et à profil vertical (13) et un système de propulsion (6A-6H). L'élimination des points d'attache de l'aile principale à la section centrale du fuselage facilite la conception et la fabrication de cette section et permet d'utiliser des sections de proue (81A-81H) et de queue (82A-82D et 83E-83H) de fuselage avec un haut degré d'interchangeabilité entre les modèles. L'aile principale, l'aile en canard et l'aile à profil vertical de tous les modèles de la série sont produits avec un sous-ensemble de moules, calibres, gabarits ou autres outils communs dans une large mesure à tous les modèles de la série.
PCT/US1985/002284 1984-11-23 1985-11-22 Conception graduee d'aeronefs et procede de construction Ceased WO1986003172A1 (fr)

Priority Applications (8)

Application Number Priority Date Filing Date Title
BR8507073A BR8507073A (pt) 1984-11-23 1985-11-22 Projeto de aeronave graduado e processo de construcao
PCT/US1986/001324 WO1987003265A1 (fr) 1985-11-22 1986-06-20 Procede de dessin et de construction d'aeronefs de dimensions graduees
JP61504012A JPS63501787A (ja) 1985-11-22 1986-06-20 段階付航空機設計及び製造方法
EP19860904540 EP0247063A4 (fr) 1985-11-22 1986-06-20 Procede de dessin et de construction d'aeronefs de dimensions graduees.
AU61403/86A AU587058B2 (en) 1985-11-22 1986-06-20 Graduated aircraft design and construction method
HU863545A HUT47487A (en) 1985-11-22 1986-06-20 Method for economic constructing and manufacturing series of airframes according to size scale
NO864609A NO864609L (no) 1985-11-22 1986-11-19 Fremgangsmaate for stoerrelses-gradert konstruksjon av luftfartoeyer.
FI873214A FI873214A0 (fi) 1985-11-22 1987-07-22 Foerfarande foer planering och konstruktion av flygplan av gradvis olika storlek.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US67440784A 1984-11-23 1984-11-23
US674,407 1984-11-23

Publications (1)

Publication Number Publication Date
WO1986003172A1 true WO1986003172A1 (fr) 1986-06-05

Family

ID=24706475

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US1985/002284 Ceased WO1986003172A1 (fr) 1984-11-23 1985-11-22 Conception graduee d'aeronefs et procede de construction

Country Status (6)

Country Link
EP (1) EP0202324A4 (fr)
JP (1) JPS62501408A (fr)
AU (1) AU5207386A (fr)
BR (2) BR8507073A (fr)
IL (1) IL77125A0 (fr)
WO (1) WO1986003172A1 (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2270666A (en) * 1992-09-21 1994-03-23 Gen Electric 5ow cost, selectable configuration spacecraft.
GB2328918A (en) * 1997-09-04 1999-03-10 British Aerospace Selecting modules to produce aircraft variants
EP0857648A3 (fr) * 1997-02-05 1999-11-24 Anatoli J. Prof. Dr. Vassiliev Aéronef pour le transport des passagers et du fret
WO2005002961A3 (fr) * 2003-04-15 2005-07-28 Adam Aircraft Ind Inc Procedes de fabrication de pieces d'avion composites et famille d'avion composite
EP2017051B2 (fr) † 2005-11-01 2015-08-26 The Boeing Company Procédé pour fabriquer une série d'ailes d'avion
US11338927B2 (en) * 2018-12-14 2022-05-24 Bombardier Inc. Forward swept wing aircraft with boundary layer ingestion and distributed electrical propulsion system

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
HUT47487A (en) * 1985-11-22 1989-03-28 Fox Brothers Ltd Method for economic constructing and manufacturing series of airframes according to size scale

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1524059A (en) * 1923-07-03 1925-01-27 Bertram P Scott Template for making organ pipes
GB515562A (en) * 1938-07-01 1939-12-07 Fairey Aviat Co Ltd Improvements in or relating to the structure of aircraft
US2417189A (en) * 1942-07-27 1947-03-11 Cornelius Aircraft Corp Tailless airplane
US2639876A (en) * 1947-09-03 1953-05-26 Misfeldt Charles Clayton Molded structure
US2666933A (en) * 1954-01-26 Sectional boat
FR1059020A (fr) * 1952-04-05 1954-03-22 Machine volante perfectionnée
US3604077A (en) * 1968-12-18 1971-09-14 Sea Ferro Inc Apparatus for making molded bodies
US3887952A (en) * 1973-12-03 1975-06-10 Jr Frank S Nicoll Modular constructed fiberglass reinforced paperboard boat
US4417708A (en) * 1982-05-12 1983-11-29 Grumman Aerospace Corporation Interchangeable wing aircraft

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1380288A (fr) * 1964-01-24 1964-11-27 Hirtenberger Patronen Corps aérien constitué par l'assemblage d'un grand nombre d'éléments de base de section aérodynamique ayant la forme de barres ou de tubes
DE1756499A1 (de) * 1968-05-30 1970-04-09 Bede James R Flugzeug-Tragflaeche

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2666933A (en) * 1954-01-26 Sectional boat
US1524059A (en) * 1923-07-03 1925-01-27 Bertram P Scott Template for making organ pipes
GB515562A (en) * 1938-07-01 1939-12-07 Fairey Aviat Co Ltd Improvements in or relating to the structure of aircraft
US2417189A (en) * 1942-07-27 1947-03-11 Cornelius Aircraft Corp Tailless airplane
US2639876A (en) * 1947-09-03 1953-05-26 Misfeldt Charles Clayton Molded structure
FR1059020A (fr) * 1952-04-05 1954-03-22 Machine volante perfectionnée
US3604077A (en) * 1968-12-18 1971-09-14 Sea Ferro Inc Apparatus for making molded bodies
US3887952A (en) * 1973-12-03 1975-06-10 Jr Frank S Nicoll Modular constructed fiberglass reinforced paperboard boat
US4417708A (en) * 1982-05-12 1983-11-29 Grumman Aerospace Corporation Interchangeable wing aircraft

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2270666A (en) * 1992-09-21 1994-03-23 Gen Electric 5ow cost, selectable configuration spacecraft.
US5344104A (en) * 1992-09-21 1994-09-06 General Electric Co. Low cost, selectable configuration spacecraft
GB2270666B (en) * 1992-09-21 1996-09-18 Gen Electric Low cost, selectable configuration spacecraft
EP0857648A3 (fr) * 1997-02-05 1999-11-24 Anatoli J. Prof. Dr. Vassiliev Aéronef pour le transport des passagers et du fret
GB2328918A (en) * 1997-09-04 1999-03-10 British Aerospace Selecting modules to produce aircraft variants
US6065720A (en) * 1997-09-04 2000-05-23 British Aerospace Public Limited Company Manufacture of aircraft
WO2005002961A3 (fr) * 2003-04-15 2005-07-28 Adam Aircraft Ind Inc Procedes de fabrication de pieces d'avion composites et famille d'avion composite
EP2017051B2 (fr) † 2005-11-01 2015-08-26 The Boeing Company Procédé pour fabriquer une série d'ailes d'avion
US11338927B2 (en) * 2018-12-14 2022-05-24 Bombardier Inc. Forward swept wing aircraft with boundary layer ingestion and distributed electrical propulsion system

Also Published As

Publication number Publication date
BR8606990A (pt) 1987-12-01
IL77125A0 (en) 1986-04-29
EP0202324A4 (fr) 1989-02-20
EP0202324A1 (fr) 1986-11-26
JPS62501408A (ja) 1987-06-11
BR8507073A (pt) 1987-07-14
AU5207386A (en) 1986-06-18

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