[특허]Lifting body aircraft and reentry vehicle

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

특허 상세정보

MyON담기

내보내기

Lifting body aircraft and reentry vehicle

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-007/00
미국특허분류(USC)	244/036; 244/160
출원번호	US-0458142 (2003-06-10)
발명자 / 주소	Stephenson, Jon Bayer, John C. Froeschner, James G.
대리인 / 주소	Roy, Kiesel, Keegan &
인용정보	피인용 횟수 : 3 인용 특허 : 3

초록
▼

A lifting body aircraft suitable for atmospheric flight and/or as a reentry vehicle. The craft has a substantially flat upper surface, a lower surface with a doubly convex first section and a flat sloping second section. The doubly convex first section allows the craft to have its center of gravity forward of its longitudinal center line. The flat sloping second half of the lower surface and the substantially flat upper surface form the aft end of an airfoil. A pair of vertical stabilizers enhance stability and include rudders which, along with a pair of elevons, provide steerage. The craft may glide or it may have an engine or rockets for thrust. The result is an extremely stable lifting body design that is well suited for launch or conventional take off, insertion, orbital operations, reentry, atmospheric flight, and conventional landings.

대표
청구항
▼

1. A lifting body aircraft having a length, a width, a depth, and a longitudinal center line, said aircraft comprising:a substantially flat upper surface having a nose end and a tail end and edges extending therebetween; a lower surface having a first section and a second section, said first section extending from said nose end and said edges of said upper surface to about said longitudinal center line of said aircraft, said first section being convex between said nose end and said longitudinal center line and between said edges of said upper surface, said second section extending from said tail end of said upper surface to about said longitudinal center line of said aircraft, said second section having a substantially flat central section, whereby said second section of said lower surface and said tail end of said upper surface form a drag reducing airfoil; and a plurality of vertical stabilizers extending from said craft proximate to said tail end, wherein at least one of said vertical stabilizers extends from said lower surface. 2. A lifting body aircraft according to claim 1 having a center of gravity forward of said longitudinal center line.3. A lifting body aircraft according to claim 2 wherein said center of gravity is forward of said longitudinal center line by a distance of about five percent of said length of said aircraft.4. A lifting body aircraft according to claim 1 wherein the ratio of said length to said width is about 4:2.5. A lifting body aircraft according to claim 1 wherein the ratio of said length to said depth is about 4:1.6. A lifting body aircraft according to claim 1 wherein the ratio of said length to said width and to said depth is about 4:2:1.7. A lifting body aircraft according to claim 1 wherein at least one of said vertical stabilizers is proximate to each of said edges of said upper surface.8. A lifting body aircraft according to claim 1 wherein two of said vertical stabilizers extend from said upper surface.9. A lifting body aircraft according to claim 8 wherein each of said two vertical stabilizers are proximate to one of said edges of said upper surface.10. A lifting body aircraft according to claim 8 wherein each of said two vertical stabilizers extend from said upper surface at opposite angles, wherein the angle of each of said two vertical stabilizers are opposite in direction with respect to the other.11. A lifting body aircraft according to claim 1 wherein said at least two of said vertical stabilizers extend from said lower surface.12. A lifting body aircraft according to claim 1 wherein said at least two of said vertical stabilizers have a retracted position wherein said at least two vertical stabilizers are contained within said aircraft and a deployed position in which said at least two vertical stabilizers extend from said lower surface.13. A lifting body aircraft according to claim 12 wherein said at least two of said vertical stabilizers further comprise landing gear.14. A lifting body aircraft according to claim 11 wherein said at least two of said vertical stabilizers further comprise landing gear.15. A lifting body aircraft according to claim 1 further comprising an elevon at said tail end of said upper surface.16. A lifting body aircraft according to claim 1 wherein said lower surface further comprises an elevon proximate to said tail end of said upper surface.17. A lifting body aircraft according to claim 1 further comprising a plurality of elevons at said tail end of said upper surface.18. A lifting body aircraft according to claim 1 wherein said lower surface further comprises a plurality of elevons proximate to said tail end of said upper surface.19. A lifting body aircraft according to claim 1 further comprising a cargo bay door in said upper surface, said cargo bay door configured to provide access the interior of said aircraft when said cargo bay door is open.20. A lifting body aircraft according to claim 19 further comprising at least one module within said aircraft, said module sized to be removed from said aircraft via said cargo bay door.21. A lifting body aircraft according to claim 1 further comprising an ejectable control module sized to house at least one crew member and containing instruments and controls necessary to operate said aircraft, said control module configured to be ejected from said aircraft in the event of failure of said aircraft.22. A lifting body aircraft according to claim 1 further comprising a thrust source configured to provide thrust to said aircraft.23. A lifting body aircraft according to claim 22 wherein said thrust source is a jet engine.24. A lifting body aircraft according to claim 22 wherein said thrust source is a rocket.25. A lifting body aircraft according to claim 1 wherein said aircraft further comprises a robotic arm.26. A lifting body aircraft according to claim 1 wherein said aircraft further comprises a ventral body flap configured to provide pitch control to said aircraft.27. A lifting body aircraft according to claim 1 wherein said upper surface has an aft end, and wherein said aft end is angled toward said lower surface.28. A lifting body aircraft having a length, a width, a depth, and a longitudinal center line, said aircraft comprising:a substantially flat upper surface having a nose end and a tail end and edges extending therebetween; a lower surface having a first section and a second section, said first section extending from said nose end and said edges of said upper surface to about said longitudinal center line of said aircraft, said first section being convex between said nose end and said longitudinal center line and between said edges of said upper surface, said first section of said lower surface containing substantially no flat portions between said edges, said second section extending from said tail end of said upper surface to about said longitudinal center line of said aircraft, said second section having a substantially flat central section, whereby said second section of said lower surface and said tail end of said upper surface form a drag reducing airfoil; and having a center of gravity forward of said longitudinal center line. 29. A lifting body aircraft according to claim 28 wherein said center of gravity is forward of said longitudinal center line by a distance of about five percent of said length of said aircraft.30. A lifting body aircraft according to claim 28 wherein the ratio of said length to said width is about 4:2.31. A lifting body aircraft according to claim 28 wherein the ratio of said length to said depth is about 4:1.32. A lifting body aircraft according to claim 28 wherein the ratio of said length to said width and to said depth is about 4:2:1.33. A lifting body aircraft according to claim 28 further comprising a plurality of vertical stabilizers extending from said craft proximate to said tail end, wherein said vertical stabilizers have a leading edge and a trailing edge and at least one of said vertical stabilizers has a rudder attached to said trailing edge.34. A lifting body aircraft according to claim 33 wherein two of said vertical stabilizers extend from said upper surface.35. A lifting body aircraft according to claim 34 wherein each of said two vertical stabilizers are proximate to one of said edges of said upper surface.36. A lifting body aircraft according to claim 28 wherein each of said two vertical stabilizers extend from said upper surface at opposite angles, wherein the angle of each of said two vertical stabilizers are opposite in direction with respect to the other.37. A lifting body aircraft according to claim 33 wherein at least one of said vertical stabilizers extends from said lower surface.38. A lifting body aircraft according to claim 33 wherein at least two of said vertical stabilizers extend from said lower surface.39. A lifting body aircraft according to claim 38 wherein said at least two of said vertical stabilizers have a retracted position wherein said at least two vertical stabilizers are contained within said aircraft and a deployed position in which said at least two vertical stabilizers extend from said lower surface.40. A lifting body aircraft according to claim 39 wherein said at least two of said vertical stabilizers further comprise landing gear.41. A lifting body aircraft according to claim 38 wherein said at least two of said vertical stabilizers further comprise landing gear.42. A lifting body aircraft according to claim 28 further comprising an elevon at said tail end of said upper surface.43. A lifting body aircraft according to claim 28 wherein said lower surface further comprises an elevon proximate to said tail end of said upper surface.44. A lifting body aircraft according to claim 28 wherein said lower surface further comprises a plurality of elevons proximate to said tail end of said upper surface.45. A lifting body aircraft according to claim 28 further comprising a cargo bay door in said upper surface, said cargo bay door configured to provide access the interior of said aircraft when said cargo bay door is open.46. A lifting body aircraft according to claim 45 further comprising at least one module within said aircraft, said module sized to be removed from said aircraft via said cargo bay door.47. A lifting body aircraft according to claim 28 further comprising an ejectable control module sized to house at least one crew member and containing instruments and controls necessary to operate said aircraft, said control module configured to be ejected from said aircraft in the event of failure of said aircraft.48. A lifting body aircraft according to claim 28 further comprising a thrust source configured to provide thrust to said aircraft.49. A lifting body aircraft according to claim 48 wherein said thrust source is a jet engine.50. A lifting body aircraft according to claim 48 wherein said thrust source is a rocket.51. A lifting body aircraft according to claim 28 wherein said aircraft further comprises a robotic arm.52. A lifting body aircraft according to claim 28 wherein said aircraft further comprises a ventral body flap configured to provide pitch control to said aircraft.53. A lifting body aircraft according to claim 28 wherein said upper surface has an aft end, and wherein said aft end is angled toward said lower surface.

이 특허에 인용된 특허 (3)

이 특허를 인용한 특허 피인용횟수: 3

IPC 상위 출원인

내보내기

상세정보
내보내기 구분	파일저장 인쇄 메일전송
구성항목	관리번호, 국가코드, 자료구분, 상태, 출원번호, 출원일자, 공개번호, 공개일자, 등록번호, 등록일자, 발명명칭(한글), 발명명칭(영문), 출원인(한글), 출원인(영문), 출원인코드, 대표IPC 관리번호, 국가코드, 자료구분, 상태, 출원번호, 출원일자, 공개번호, 공개일자, 공고번호, 공고일자, 등록번호, 등록일자, 발명명칭(한글), 발명명칭(영문), 출원인(한글), 출원인(영문), 출원인코드, 대표출원인, 출원인국적, 출원인주소, 발명자, 발명자E, 발명자코드, 발명자주소, 발명자 우편번호, 발명자국적, 대표IPC, IPC코드, 요약, 미국특허분류, 대리인주소, 대리인코드, 대리인(한글), 대리인(영문), 국제공개일자, 국제공개번호, 국제출원일자, 국제출원번호, 우선권, 우선권주장일, 우선권국가, 우선권출원번호, 원출원일자, 원출원번호, 지정국, Citing Patents, Cited Patents
저장형식	Text(ASCII format) Excel format PIAS분석(.xls)
메일정보	받는사람 (필수) @ 보내는사람 (선택) @ 제목 내용 KISTI 검색결과 이메일 서비스
안내	> 총 건의 자료가 검색되었습니다. > 다운받으실 자료의 인덱스를 입력하세요. (1-10,000) > 검색결과의 순서대로 최대 10,000건 까지 다운로드가 가능합니다. > 데이타가 많을 경우 속도가 느려질 수 있습니다.(최대 2~3분 소요) > 다운로드 파일은 UTF-8 형태로 저장됩니다. 파일의 내용이 제대로 보이지 않을실 때는 웹브라우저 상단의 보기 -> 인코딩 -> 자동선택 여부를 확인하십시오 > ~ > Text(ASCII format) Excel format

과학기술 지식인프라 ScienceON

ScienceON Chatbot

특허 상세정보

Lifting body aircraft and reentry vehicle

초록
▼

대표
청구항
▼

이 특허에 인용된 특허 (3)

이 특허를 인용한 특허 피인용횟수: 3

IPC 상위 출원인

과제정보

상세정보조회

원문조회

IPC 상세정보(version : 201201)

연구과제 성과물(0)

참여연구원의 다른 문헌(0)

처리중입니다.

잠시만 기다려주세요.

ScienceON Chatbot

특허 상세정보

Lifting body aircraft and reentry vehicle

초록 ▼

대표청구항 ▼

이 특허에 인용된 특허 (3)

이 특허를 인용한 특허 피인용횟수: 3

IPC 상위 출원인

과제정보

상세정보조회

원문조회

IPC 상세정보(version : 201201)

연구과제 성과물(0)

참여연구원의 다른 문헌(0)

처리중입니다.

잠시만 기다려주세요.

초록
▼

대표
청구항
▼