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WO2005047102A3 - Systems and methods for configuring aircraft to meet performance goals and shock wave disturbance constraints - Google Patents

Systems and methods for configuring aircraft to meet performance goals and shock wave disturbance constraints Download PDF

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Publication number
WO2005047102A3
WO2005047102A3 PCT/US2004/036892 US2004036892W WO2005047102A3 WO 2005047102 A3 WO2005047102 A3 WO 2005047102A3 US 2004036892 W US2004036892 W US 2004036892W WO 2005047102 A3 WO2005047102 A3 WO 2005047102A3
Authority
WO
WIPO (PCT)
Prior art keywords
equivalent area
constraints
aircraft
area distribution
wing
Prior art date
Application number
PCT/US2004/036892
Other languages
French (fr)
Other versions
WO2005047102A2 (en
Inventor
John Morgenstern
Alan Arslan
Joshua Barbieri
James Bach
Original Assignee
John Morgenstern
Alan Arslan
Joshua Barbieri
James Bach
Supersonic Aerospace Internat
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
Priority claimed from US10/713,515 external-priority patent/US6854687B1/en
Priority claimed from US10/714,276 external-priority patent/US8473254B2/en
Application filed by John Morgenstern, Alan Arslan, Joshua Barbieri, James Bach, Supersonic Aerospace Internat filed Critical John Morgenstern
Priority to EP04800783A priority Critical patent/EP1697210A4/en
Publication of WO2005047102A2 publication Critical patent/WO2005047102A2/en
Priority to US11/238,203 priority patent/US7546977B2/en
Publication of WO2005047102A3 publication Critical patent/WO2005047102A3/en

Links

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
    • B64C1/0009—Aerodynamic aspects
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C30/00—Supersonic type aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/16—Aircraft characterised by the type or position of power plants of jet type
    • B64D27/18—Aircraft characterised by the type or position of power plants of jet type within, or attached to, wings
    • 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
    • B64C2001/0045—Fuselages characterised by special shapes
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Mechanical Engineering (AREA)
  • Manufacturing & Machinery (AREA)
  • Transportation (AREA)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

An aircraft (400) for low sonic boom supersonic flight conditions includes a wing (404) with one or more areas of far-field expansion ahead of areas of far-field compression. An equivalent area distribution goal curve is scaled to account for the equivalent area reduction due to excursions below to goal curve. A relaxed constraint allows the equivalent area distribution of the aircraft (400) to be at or below the equivalent area distribution goal curve to enable multiple parameters to be configured to meet the equivalent area distribution constraint, as well as other constraints. The shape of a reflexed portion (424) of the airfoil (302) on the underside of the wing (314), and a corresponding shape for the upper surface of the nacelle (306) provide favorable interaction between the wing (314) and the nacelle (306).
PCT/US2004/036892 2003-07-03 2004-11-04 Systems and methods for configuring aircraft to meet performance goals and shock wave disturbance constraints WO2005047102A2 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP04800783A EP1697210A4 (en) 2003-11-11 2004-11-04 Systems and methods for configuring aircraft to meet performance goals and shock wave disturbance constraints
US11/238,203 US7546977B2 (en) 2003-07-03 2005-09-28 Passive aerodynamic sonic boom suppression for supersonic aircraft

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
US10/713,515 2003-11-11
US10/713,515 US6854687B1 (en) 2003-11-11 2003-11-11 Nacelle integration with reflexed wing for sonic boom reduction
US10/714,276 2003-11-14
US10/714,276 US8473254B2 (en) 2003-11-14 2003-11-14 Methods for configuring aircraft to meet performance goals and shock wave disturbance constraints

Publications (2)

Publication Number Publication Date
WO2005047102A2 WO2005047102A2 (en) 2005-05-26
WO2005047102A3 true WO2005047102A3 (en) 2005-12-22

Family

ID=34595374

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2004/036892 WO2005047102A2 (en) 2003-07-03 2004-11-04 Systems and methods for configuring aircraft to meet performance goals and shock wave disturbance constraints

Country Status (2)

Country Link
EP (1) EP1697210A4 (en)
WO (1) WO2005047102A2 (en)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2956357B1 (en) * 2013-02-14 2019-05-15 Gulfstream Aerospace Corporation Systems and methods for controlling a magnitude of a sonic boom
CN106338399B (en) * 2016-08-16 2019-03-08 中国航空工业集团公司沈阳发动机设计研究所 A kind of calculation method across the total static probe measurement true value of supersonic speed
US10082439B1 (en) * 2016-09-16 2018-09-25 Rockwell Collins, Inc. Event depiction on center of gravity curve
US12017800B2 (en) 2018-03-29 2024-06-25 Japan Aerospace Exploration Agency Method of designing a shape of an airframe of a supersonic aircraft, production method of a supersonic aircraft, and supersonic aircraft
CN118036188B (en) * 2024-04-08 2024-07-02 中国空气动力研究与发展中心空天技术研究所 Ultrasonic low-acoustic-explosion aircraft equivalent area distribution accompanying optimization design method
CN119129481B (en) * 2024-11-13 2025-01-28 西北工业大学 Method for calculating quick equivalent flow field of embedded air inlet channel fused with inlet grid

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2997256A (en) * 1955-01-14 1961-08-22 James H Walker Supersonic aircraft
US3310262A (en) * 1965-05-21 1967-03-21 Augustine W Robins Supersonic aircraft
US4598886A (en) * 1979-08-13 1986-07-08 The Boeing Company Double parasol, favorable interference airplane
US6588703B1 (en) * 2000-02-08 2003-07-08 Lockheed Martin Corporation Passive aerodynamic sonic boom suppression for supersonic aircraft

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6149101A (en) * 1991-07-08 2000-11-21 Tracy; Richard R. Aircraft wing and fuselage contours
AU2002227282A1 (en) * 2000-12-08 2002-06-18 Lockheed Martin Corporation Joined wing supersonic aircraft
CA2474552C (en) * 2002-01-30 2011-07-26 Gulfstream Aerospace Corporation Fuselage shaping and inclusion of spike on a supersonic aircraft for controlling and reducing sonic boom

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2997256A (en) * 1955-01-14 1961-08-22 James H Walker Supersonic aircraft
US3310262A (en) * 1965-05-21 1967-03-21 Augustine W Robins Supersonic aircraft
US4598886A (en) * 1979-08-13 1986-07-08 The Boeing Company Double parasol, favorable interference airplane
US6588703B1 (en) * 2000-02-08 2003-07-08 Lockheed Martin Corporation Passive aerodynamic sonic boom suppression for supersonic aircraft

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
DARDEN C.M.: "Sinic Boom Minimization With Nose Bluntness Relaxation", NASA TECHNICAL PAPER 1348, 1979, pages 1 - 51, XP002369344 *

Also Published As

Publication number Publication date
EP1697210A2 (en) 2006-09-06
EP1697210A4 (en) 2009-02-18
WO2005047102A2 (en) 2005-05-26

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