$\require{mediawiki-texvc}$
  • 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

Deployable inlet for aeroplane center boost engine

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B64D-033/02   
미국특허분류(USC) 244/53B ; 244/58 ; 244/55
출원번호 US-0306748 (1981-09-29)
발명자 / 주소
출원인 / 주소
인용정보 피인용 횟수 : 13  인용 특허 : 0
초록

A deployable inlet for use with a center boost engine on a jet propelled aircraft having the capability of aerodynamically fairing the air inlet located in the leading edge of the vertical stabilizer at such times as the center boost engine is shut down and non-operative, thus minimizing drag. More particularly, an inlet construction for use with aircraft of the type commonly employing multiple main power plants and an auxiliary center boost engine of the type which is commonly used only: (i) during take-off; (ii) during air refueling operations; and/or ...

대표
청구항

In combination with an aircraft having a fuselage; an empennage including an empennage body structure and an upstanding vertical stabilizer mounted on said fuselage and having a leading edge and spaced port and starboard skin panels defining smooth, aerodynamically streamlined skin surfaces extending rearwardly from said stabilizer leading edge; and of the type including an auxiliary center boost jet engine having a rearwardly directed exhaust nozzle mounted within said empennage body structure, an air inlet formed in and coincident with said leading edg...

이 특허를 인용한 특허 피인용횟수: 13

  1. Bacon Richard J.. 3X multi-engine jet configuration and method of operation. USP1999015855340.
  2. Guemmer, Volker. Aircraft propulsion unit in multi-fan design. USP2013038402740.
  3. Kelnhofer,Juergen. Aircraft ram air inlet with multi-member closure flap. USP2007057222819.
  4. Bhargava, Brij B.. Aircraft taxiing and secondary propulsion system. USP2012028109464.
  5. Pogosyan, Mihail Aslanovich; Davidenko, Aleksandr Nikolaevich; Strelets, Mihail Yurievich; Runishev, Vladimir Aleksandrovich; Tarasov, Aleksey Zaharovich; Shokurov, Aleksey Kirillovich; Bibikov, Sergey Yurievich; Krylov, Leonid Evgenievich; Moskalev, Pavel Borisovich. Aircraft with an integral aerodynamic configuration. USP2015119180974.
  6. Negulescu, Dimitrie. Aircraft with tail propeller-engine layout. USP2012098256709.
  7. Reysa Gary D. ; Swenson Lynn A. ; Hutchison Robert A. ; Fung Kenny L.. Auxiliary power and thrust unit. USP2001066247668.
  8. Figge ; Sr. Irving E.. Self-deploying air inlet for an air breathing missile. USP2000116142417.
  9. Seidel, Gerhard E.. Separate boundary layer engine inlet. USP2003036527224.
  10. Gatzke, Sten. Signal strength dependent cover unlocking device for a duct housing a secondary power supply device in an aircraft fuselage. USP2015038967530.
  11. Wagenfeld Robert E. (New York NY). System for reducing aircraft noise and hush kit. USP1989064836469.
  12. Howarth,Nicholas; Freeman,Christopher. Turbine engine arrangements. USP2007017165744.
  13. Guering, Bernard. Vertical tail unit for aircraft and aircraft equipped with same. USP2009097581694.