$\require{mediawiki-texvc}$
  • 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"

특허 상세정보

Secondary wing system for use on an aircraft

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B64C-003/56   
미국특허분류(USC) 244/045A ; 244/046
출원번호 US-0828826 (1997-03-13)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Bon
인용정보 피인용 횟수 : 12  인용 특허 : 18
초록

A secondary wing system for use on an aircraft augments the lift, stability, and control of the aircraft at subsonic speeds. The secondary wing system includes a mechanism that allows the canard to be retracted within the contour of the aircraft fuselage from an operational position to a stowed position. The top surface of the canard is exposed to air flow in the stowed position, and is contoured to integrate aerodynamically and smoothly within the contour of the fuselage when the canard is retracted for high speed flight. The bottom portion of the canar...

대표
청구항

[ What is claimed is:] [1.] A secondary wing system for use on an aircraft forward fuselage, comprising in combination:a one-piece canard in an elliptical planform shape derived from a waterline cut through the upper portion an area-ruled supersonic fuselage, intermediately positioned between a nose and a main wing; andsaid canard being secured movably relative to the forward fuselage between a stowed position and a deployed position, so that when said canard is deployed, it provides supplementary lift to the aircraft at predetermined speeds, and when sa...

이 특허에 인용된 특허 (18)

  1. Woodcock Robert R. (Sylmar CA). 90 degree rotation aircraft wing. USP1991034998689.
  2. Brown Bruce B. (18323 Soledad Canyon Rd. #23 Canyon Country CA 91351). Aircraft having fixed and pivotal wings. USP1997095671898.
  3. Caldwell, Allan L.; Hardy, Richard; Neumann, Frank D.. Aircraft with directional controlling canards. USP1985094542866.
  4. Kaniut Herbert M. (Orrerweg 33/35 5000 Cologne 71 DT). Aircraft with safety tail unit. USP1977024008867.
  5. Calvert Galen E. (5510 Lake White Ct. Fairfax VA 22032). Airplane with transonic/hypersonic to short take off and landing (STOL) flight capability. USP1990044913378.
  6. Trimbath Thomas E. (Bellevue WA). Body spoiler for yaw control of a supersonic airplane. USP1996105564652.
  7. Lockheed John A. (7925 Dead Indian Rd. Ashland OR 97520). Canard control system for aircraft. USP1989074848700.
  8. Schwaerzler Hans (Taufkirchen DEX) Staudacher Werner (Zorneding DEX). Canard type aircraft. USP1979074161300.
  9. Moorefield William J. (St. Peters MO). Double-pivoting deployment system for aerosurfaces. USP1993035192037.
  10. Bteille Roger H. (Blagnac FRX). Fixed-wing aircraft with tandem supporting surfaces. USP1986074598888.
  11. Pruszenski ; Jr. Anthony (No. 3 ; 44th St. Plum Island MA 01951). Ground-air-water craft. USP1990024899954.
  12. Betts Edward E. (Escondido CA). High lift aircraft. USP1991125071088.
  13. Jensen Duane Lowell (Byron CA). Inflatable deployable control structures for aerospace vehicles. USP1997105681010.
  14. Groutage Frederick D. (Laramie WY) Conjerti Samuel N. (San Diego CA) Shaw Lockburn S. (San Diego CA). Pivotal mono wing cruise missile with wing deployment and fastener mechanism. USP1989064842218.
  15. Cymara Hermann K. (106 Stonehaven Cir. Newfield NY 14867). Retractable canard wing surfaces for airplanes. USP1996035495999.
  16. Gerhardt Heinz A. (Redondo Beach CA). Skewed hinge control surface. USP1995035398888.
  17. Rutan Elbert L. (Hangar 73 ; Mojave Airport Mojave CA 93501). Tandem or multi-winged high performance aircraft. USP1987024641800.
  18. Alvarez Calderon F Albert (410 Fern Glen La Jolla CA 92037). Variable geometry RPV. USP1992065118052.