• 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

Aircraft wing with flexible skins

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B64C-003/38   
미국특허분류(USC) 244/046; 244/123.1; 244/123.8; 244/123.11; 244/123.14; 244/210
출원번호 US-0278493 (2011-10-21)
등록번호 US-8714476 (2014-05-06)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Renner, Otto, Boisselle & Sklar, LLP
인용정보 피인용 횟수 : 1  인용 특허 : 17

A wing includes a spar, and a pair of flexible skins that are attached to the spar. The spar is at the leading edge of the wing, and the skins extend toward the trailing edge of the wing. The wing deploys from a stowed condition, in which the skins are curved in the same direction around a fuselage of an aircraft, to a deployed condition, in which the skins provide the wing with an airfoil cross-sectional shape, for example with the skins curve in opposite direction. A lock is used to maintain the skins in the deployed state, with the lock for example lo...


1. A wing comprising: a pair of flexible skins; anda lock;in a combination with a fuselage to which the wing is coupled;wherein the skin portions each have a first end and a second end opposite the first end;wherein the first ends are spatially separated from one another by a gap;wherein the lock is able to selectively lock the skins together at a location that is closer to the second ends than it is to the first ends;wherein the lock includes a pair of lock parts that engage in a ratcheting fashion, with one of the parts having teeth, barbs, or tabs, th...

이 특허에 인용된 특허 (17)

  1. Kota,Sridhar; Hetrick,Joel A.. Adaptive compliant wing and rotor system. USP2008067384016.
  2. Gruenewald Michael,DEX ; Moeser Clemens,DEX ; Steigenberger Josef,DEX ; Mueller Guenther,DEX. Adaptive flow body. USP2001086276641.
  3. Velez, Javier; Klestadt, Ralph H.. Aerodynamic flight termination system and method. USP2013028367993.
  4. Mabe, James H.; Calkins, Frederick T.; Bushnell, Glenn S.; Bieniawski, Stefan R.. Aircraft systems with shape memory alloy (SMA) actuators, and associated methods. USP2011027878459.
  5. Rowarth Ralph (South Cave GB2). Aircraft wing drooping leading edge device. USP1980044200253.
  6. Frost Richard C. (Fort Worth TX) Gomez Eduardo W. (Fort Worth TX) McAnally Robert W. (Fort Worth TX). Airfoil variable cambering device and method. USP1981014247066.
  7. Statkus Frank D. (Woodinville WA). Continuous skin, variable camber airfoil edge actuating mechanism. USP1982094351502.
  8. Dryer, Richard; Eisentraut, Rudolph Adolph; Kebschull, Martin Allen; Parine, John Christopher. Deployment mechanism for stowable fins. USP2005066905093.
  9. Magno, Jr.,Joey D.; Cai,Xueming. High performance cable tie. USP2006037017237.
  10. Grip, Robert Erik. Mechanism for changing the shape of a control surface. USP2013048418968.
  11. Sanderson, Terry M.; Clark, Jamie W.. Methods and apparatus for adjustable surfaces. USP2010067728267.
  12. Eisentraut, Rudy A.; Sanderson, Terry M.; Gowler, Brian J.. Reconfigurable wing and method of use. USP2011118056853.
  13. Grohmann, Boris; Maucher, Christoph; Altmikus, Andree; Mangelsdorf, Stephan. Rotor blade for a rotary wing aircraft. USP2012048162607.
  14. Manley, David J.; Grip, Robert E.. Shape-changing control surface. USP2013028382045.
  15. Parine, John C.; Koessler, Jeffrey H.; Gogineni, Purnachandra R.; Perez, Juan A.; Kebschull, Martin A.. Single-axis fin deployment system. USP2010017642492.
  16. Cole James B. (Mercer Island WA). Variable camber airfoil. USP1976113994452.
  17. Roglin Robert L. (Duluth GA) Hanagud Sathyanaraya (Atlanta GA). Variable camber control of airfoil. USP1992095150864.