$\require{mediawiki-texvc}$
  • 검색어에 아래의 연산자를 사용하시면 더 정확한 검색결과를 얻을 수 있습니다.
  • 검색연산자
검색연산자 기능 검색시 예
() 우선순위가 가장 높은 연산자 예1) (나노 (기계 | machine))
공백 두 개의 검색어(식)을 모두 포함하고 있는 문서 검색 예1) (나노 기계)
예2) 나노 장영실
| 두 개의 검색어(식) 중 하나 이상 포함하고 있는 문서 검색 예1) (줄기세포 | 면역)
예2) 줄기세포 | 장영실
! NOT 이후에 있는 검색어가 포함된 문서는 제외 예1) (황금 !백금)
예2) !image
* 검색어의 *란에 0개 이상의 임의의 문자가 포함된 문서 검색 예) semi*
"" 따옴표 내의 구문과 완전히 일치하는 문서만 검색 예) "Transform and Quantization"

과학기술 지식인프라 ScienceON

상세검색 다국어 입력
도움말도움말

특허 상세정보

MyON담기
내보내기

Pitch control of swept wing aircraft

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B64C-023/06   
미국특허분류(USC) 244/199 ; 244/45A ; 244/75R
출원번호 US-0452815 (1982-12-23)
발명자 / 주소
출원인 / 주소
인용정보 피인용 횟수 : 9  인용 특허 : 6
초록
▼

A pair of vanes (26, 28) extend laterally outwardly from the fuselage (10) of a swept wing aircraft immediately forwardly of the wings (12, 14). The preferred vanes (26, 28) have a trapezoidal plan form, an outwardly tapering thickness and an airfoil cross-sectional configuration. The vanes (26, 28) are substantially aligned with streamlines (46) during level flight. In a maneuver the vanes generate vortices which flow rearwardly over the upper surfaces of the inboard portions of the wings (12, 14), causing the inboard portions of the wings (12, 14) to s...

대표
청구항
▼

An aircraft comprising a fuselage, a pair of swept-back wings attached to the fuselage, each having a swept-back leading edge and upper and lower surfaces; a tail section including a pair of horizontal stabilizers connected to the fuselage rearwardly of the wings; and the improvement comprising apparatus for modulating the stall characteristics of the inboard portions of the wings, comprising: at least one pitch control vane means on each side of the fuselage, each said vane means being attached to the fuselage forwardly of the wing on its side of the fu...

이 특허에 인용된 특허 (6)

  1. Pierce, Donald. Aircraft having improved strake configuration. USP1983044378922.
  2. Schwaerzler Hans (Taufkirchen DEX) Staudacher Werner (Zorneding DEX). Canard type aircraft. USP1979074161300.
  3. Mohn Larry W. (Edmonds WA). Flow deflector for fluid inlet. USP1979114174083.
  4. Erwin John R. (Paradise Valley AZ). Method and apparatus for controlling tip vortices. USP1976123997132.
  5. Headley Jack W. (Rancho Palos Verdes CA) Skow Andrew M. (Hermosa Beach CA) Titiriga ; Jr. Andrew (Torrance CA). Shark nose for aircraft. USP1979124176813.
  6. Calhoun John T. (10396 Rainier Ave. South Seattle WA 98178) Hall Sherman E. (20816-18th Place South Seattle WA 98188). Spoiler control system. USP1977084039162.

이 특허를 인용한 특허 피인용횟수: 9

  1. Roland Stuff DE; Heinrich Vollmers DE. Aircraft with means for a premature breakdown of the wing vortex pair. USP2002076422518.
  2. Parikh, Pradip G.. Combined cabin air and heat exchanger RAM air inlets for aircraft environmental control systems, and associated methods of use. USP2010127849702.
  3. Dixon, Charles J.; Hughes, Arthur C.. Method and apparatus for inducing controlled vortices to reduce afterbody drag. USP2004046715717.
  4. Batcho Paul F.. Method and apparatus for mitigating junction flows. USP2001026186445.
  5. Oudin, Simon; Puyou, Guilhem; Delannoy, Stephane. Method and device for estimating an unwanted pitch moment of an aircraft, and applications to the pitch control of the aircraft. USP2015099120556.
  6. Skow Andrew M. (Rolling Hills Estates CA). Method of extending the performance of a specific jet aircraft. USP1989094869443.
  7. Parikh, Pradip G.; Hastings, E. Dale. Ram air inlets for use with aircraft environmental control systems and other aircraft and non-aircraft systems. USP2009117618006.
  8. McGrath Brian E. ; Wood Richard M.. Serrated-planform lifting-surfaces. USP1999055901925.
  9. Robertson, Paul E.. Wing root leading edge extension. USP201604D754053.

IPC 상위 출원인