BR0307340A - forma de fuselagem e inclusão de ponta em um avião supersÈnico para controlar e reduzir estampido sÈnico - Google Patents

forma de fuselagem e inclusão de ponta em um avião supersÈnico para controlar e reduzir estampido sÈnico

Info

Publication number
BR0307340A
BR0307340A BRPI0307340-8A BR0307340A BR0307340A BR 0307340 A BR0307340 A BR 0307340A BR 0307340 A BR0307340 A BR 0307340A BR 0307340 A BR0307340 A BR 0307340A
Authority
BR
Brazil
Prior art keywords
airplane
plane
sonic
crash
flight
Prior art date
Application number
BRPI0307340-8A
Other languages
English (en)
Other versions
BR0307340B1 (pt
BR0307340B8 (pt
Inventor
Preston Henne
Donald Howe
Robert Wolz
Jimmy Hancock Jr
Original Assignee
Gulfstream Aerospace Corp
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 US10/104,403 external-priority patent/US6698684B1/en
Application filed by Gulfstream Aerospace Corp filed Critical Gulfstream Aerospace Corp
Publication of BR0307340A publication Critical patent/BR0307340A/pt
Publication of BR0307340B1 publication Critical patent/BR0307340B1/pt
Publication of BR0307340B8 publication Critical patent/BR0307340B8/pt

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
    • B64C23/04—Influencing air flow over aircraft surfaces, not otherwise provided for by generating shock waves
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C30/00—Supersonic type aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Toys (AREA)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
  • Apparatuses For Generation Of Mechanical Vibrations (AREA)
  • Catching Or Destruction (AREA)
  • Mechanical Engineering (AREA)
  • General Electrical Machinery Utilizing Piezoelectricity, Electrostriction Or Magnetostriction (AREA)

Abstract

"FORMA DE FUSELAGEM E INCLUSãO DE PONTA EM UM AVIãO SUPERSÈNICO PARA CONTROLAR E REDUZIR ESTAMPIDO SÈNICO". A invenção refere-se a um método e aparelho para configurar e operar um avião para minimizar os efeitos do estampido sónico a nível do solo durante o vóo supersónico do avião, que inclui configurar o avião de modo que em vóo, com o trem de pouso recolhido, um perfil inferior do avião seja substancialmente linear ou ligeiramente cóncavo para baixo. Uma porção de nariz do avião está disposta de modo que um seu vértice seja coincidente com o perfil inferior do avião. O avião é voado na velocidade supersónica e orientado durante o vóo supersónico de modo que o perfil inferior substancialmente linear do avião fique orientado substancialmente paralelo ao fluxo de ar estabelecido. Fracos distúrbios de pressão são gerados abaixo do avião, e suas ondas são radiadas abaixo do avião na direção do solo. Estes distúrbios abaixo do avião são de menor magnitude do que os distúrbios de pressão simultaneamente gerados e radiados acima do avião. Os fracos distúrbios de pressão gerados abaixo do avião são controlados de modo que os diferenciais entre os mesmos sejam suficientemente minimizados que os efeitos do estampido sónico a nível do solo sejam minimizados durante o vóo supersónico. Em um segundo aspecto, uma ponta retrátil é incluída no nariz ou na cauda do avião para minimizar os efeitos do estampido sónico a nível do solo durante o vóo supersónico.
BRPI0307340-8A 2002-01-30 2003-01-30 mÉtodo para configurar e operar um aviço para minimizar os efeitos de estampido sânico bem como mÉtodo e veÍculo aeroespacial configurado para reduzir os efeitos de estampido sânico. BR0307340B8 (pt)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US6065602A 2002-01-30 2002-01-30
US10/104,403 US6698684B1 (en) 2002-01-30 2002-03-22 Supersonic aircraft with spike for controlling and reducing sonic boom
PCT/US2003/002631 WO2003064254A2 (en) 2002-01-30 2003-01-30 Fuselage shaping and inclusion of spike on a supersonic aircraft for controlling and reducing sonic boom

Publications (3)

Publication Number Publication Date
BR0307340A true BR0307340A (pt) 2006-04-18
BR0307340B1 BR0307340B1 (pt) 2013-01-08
BR0307340B8 BR0307340B8 (pt) 2013-02-19

Family

ID=27667760

Family Applications (1)

Application Number Title Priority Date Filing Date
BRPI0307340-8A BR0307340B8 (pt) 2002-01-30 2003-01-30 mÉtodo para configurar e operar um aviço para minimizar os efeitos de estampido sânico bem como mÉtodo e veÍculo aeroespacial configurado para reduzir os efeitos de estampido sânico.

Country Status (7)

Country Link
US (5) US20050224630A1 (pt)
EP (1) EP1478569B1 (pt)
JP (1) JP4220393B2 (pt)
AU (1) AU2003209426A1 (pt)
BR (1) BR0307340B8 (pt)
CA (1) CA2474552C (pt)
WO (1) WO2003064254A2 (pt)

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CN112550678B (zh) * 2020-12-10 2021-10-15 西北工业大学 一种基于吹吸气流动控制的超声速飞机声爆抑制方法
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CN114435580B (zh) * 2022-03-25 2023-02-28 西北工业大学 一种针对超声速民机的广义静音锥气动布局构型

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Also Published As

Publication number Publication date
US20050224630A1 (en) 2005-10-13
EP1478569A2 (en) 2004-11-24
CA2474552C (en) 2011-07-26
EP1478569B1 (en) 2009-09-23
US8789789B2 (en) 2014-07-29
US20070145192A1 (en) 2007-06-28
US20110315819A1 (en) 2011-12-29
BR0307340B1 (pt) 2013-01-08
WO2003064254A2 (en) 2003-08-07
US9714084B2 (en) 2017-07-25
WO2003064254A3 (en) 2004-02-05
JP4220393B2 (ja) 2009-02-04
CA2474552A1 (en) 2003-08-07
JP2005525260A (ja) 2005-08-25
AU2003209426A1 (en) 2003-09-02
EP1478569A4 (en) 2008-05-07
US20140306058A1 (en) 2014-10-16
BR0307340B8 (pt) 2013-02-19
US8083171B2 (en) 2011-12-27
US20100012777A1 (en) 2010-01-21

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