[특허]Method for producing a leading edge skin by baking a stack incorporating heating elements and layers of pre-impregnated fibres

SONACA S.A.

검색어에 아래의 연산자를 사용하시면 더 정확한 검색결과를 얻을 수 있습니다.
검색연산자

검색도움말
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

연합인증

연합인증 가입 기관의 연구자들은 소속기관의 인증정보(ID와 암호)를 이용해 다른 대학, 연구기관, 서비스 공급자의 다양한 온라인 자원과 연구 데이터를 이용할 수 있습니다.

이는 여행자가 자국에서 발행 받은 여권으로 세계 각국을 자유롭게 여행할 수 있는 것과 같습니다.

연합인증으로 이용이 가능한 서비스는 NTIS, DataON, Edison, Kafe, Webinar 등이 있습니다.

한번의 인증절차만으로 연합인증 가입 서비스에 추가 로그인 없이 이용이 가능합니다.

다만, 연합인증을 위해서는 최초 1회만 인증 절차가 필요합니다. (회원이 아닐 경우 회원 가입이 필요합니다.)

연합인증 절차는 다음과 같습니다.

최초이용시에는
ScienceON에 로그인 → 연합인증 서비스 접속 → 로그인 (본인 확인 또는 회원가입) → 서비스 이용

그 이후에는
ScienceON 로그인 → 연합인증 서비스 접속 → 서비스 이용

연합인증을 활용하시면 KISTI가 제공하는 다양한 서비스를 편리하게 이용하실 수 있습니다.

특허 상세정보

MyON담기

내보내기 페이스북 공유 트위터 공유 카카오톡 공유

Method for producing a leading edge skin by baking a stack incorporating heating elements and layers of pre-impregnated fibres

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B29C-070/48 B29C-070/68 B29D-099/00 B64C-009/22 B64D-015/12 B29C-070/46 B29C-070/88 B29C-070/02 B29L-031/30
출원번호	US-0380588 (2013-02-22)
등록번호	US-9604425 (2017-03-28)
우선권정보	BE-2012/0107 (2012-02-24)
국제출원번호	PCT/EP2013/053519 (2013-02-22)
국제공개번호	WO2013/124397 (2013-08-29)
발명자 / 주소	Crepin, Jean-Philippe Gueuning, Dimitri
출원인 / 주소	SONACA S.A.
대리인 / 주소	Oblon, McClelland, Maier & Neustadt, L.L.P.
인용정보	피인용 횟수 : 0 인용 특허 : 6

초록
▼

A method for producing a skin of a leading edge for an aircraft wing element, including an assembly of resistive heating elements designed to form an integral part of a system for de-icing and/or anti-icing of the leading edge. The method includes curing a stack in a mold between two molding surfaces facing each other. The stack includes the resistive heating elements assembly, two adhesive films arranged respectively on either side of the assembly so that the heating elements adhere to each of these two adhesive films, two layers of electrically insulat...

대표
청구항
▼

1. A method for producing a skin of a leading edge for an aircraft wing element, comprising an assembly of resistive heating elements designed to form an integral part of a system for de-icing and/or anti-icing of the leading edge, said method comprising: curing a stack in a mould between two moulding surfaces facing each other, said stack comprising: said assembly of resistive heating elements;two adhesive films arranged respectively on either side of said assembly so that the resistive heating elements adhere to each of these two adhesive films;two layers of electrically insulating pre-impregnated fibres adhering respectively to said two adhesive films on the sides opposite those receiving said resistive heating elements; anda plurality of layers of pre-impregnated carbon fibres, wherein said curing is achieved by an implementation of following successive operations:keeping on circulating an injection resin in said mould so as to generate and keep a counter-pressure at a periphery of the stack for pressurization of the injection resin contained in said stack until the injection resin of the stack has set; thenstopping the circulating of the injection resin after the injection resin of the stack has set, leading to the injection resin being introduced between the stack and each of the two mould surfaces in order to apply a surface pressure on said stack until the said injection resin in said stack sets. 2. The method according to claim 1, wherein said assembly of resistive heating elements further comprises a plurality of electrical connection terminals which pass through one or more holes made through the stack elements located on one side of said resistive heating elements, said connection terminals protruding from said stack in such a way as to be inserted into recesses made on one of the two moulding surfaces. 3. The method according to claim 1, wherein said stack also comprises a metal panel at each end of the stack. 4. The method according to claim 1, wherein said resistive heating elements are placed flat on the corresponding adhesive film before being placed in the mould. 5. The method according to claim 1, wherein the keeping keeps on circulating the injection resin such that the counter-pressure does not decrease until the injection resin of the stack has set. 6. A method for producing a skin of a leading edge for an aircraft wing element, comprising an assembly of resistive heating elements designed to form an integral part of a system for de-icing and/or anti-icing of the leading edge, said method comprising: curing a stack in a mould between two moulding surfaces facing each other, said stack comprising: said assembly of resistive heating elements;two adhesive films arranged respectively on either side of said assembly so that the resistive heating elements adhere to each of these two adhesive films;two layers of electrically insulating pre-impregnated fibres adhering respectively to said two adhesive films on the sides opposite those receiving said resistive heating elements; anda plurality of layers of pre-impregnated carbon fibres, whereinsaid assembly of resistive heating elements further comprises a plurality of electrical connection terminals which pass through one or more holes made through the stack elements located on one side of said resistive heating elements, said connection terminals protruding from said stack in such a way as to be inserted into recesses made on one of the two moulding surfaces, andeach recess is filled with a block of silicone through which one or more of said electrical connection terminals pass. 7. A method for producing a skin of a leading edge for an aircraft wing element, comprising an assembly of resistive heating elements designed to form an integral part of a system for de-icing and/or anti-icing of the leading edge, said method comprising: curing a stack in a mould between two moulding surfaces facing each other, said stack comprising: said assembly of resistive heating elements;two adhesive films arranged respectively on either side of said assembly so that the resistive heating elements adhere to each of these two adhesive films;two layers of electrically insulating pre-impregnated fibres adhering respectively to said two adhesive films on the sides opposite those receiving said resistive heating elements; anda plurality of layers of pre-impregnated carbon fibres, whereinsaid layers of pre-impregnated carbon fibres form a core of said stack, the elements of the latter being arranged symmetrically in relation to said core, except for the assembly of resistive heating elements present on only one side of said core. 8. A method for producing a skin of a leading edge for an aircraft wing element, comprising an assembly of resistive heating elements designed to form an integral part of a system for de-icing and/or anti-icing of the leading edge, said method comprising: curing a stack in a mould between two moulding surfaces facing each other, said stack comprising: said assembly of resistive heating elements;two adhesive films arranged respectively on either side of said assembly so that the resistive heating elements adhere to each of these two adhesive films;two layers of electrically insulating pre-impregnated fibres adhering respectively to said two adhesive films on the sides opposite those receiving said resistive heating elements; anda plurality of layers of pre-impregnated carbon fibres, whereinsaid curing is achieved by an implementation of following successive operations:heating the mould by a heated plate press designed to apply a pressure on the stack via the mould, the heated plates being brought to a temperature T1, and heating of an injection resin designed to be circulated in the mould, the injection resin being heated to a temperature T0;after stabilisation of the temperature of the heating plates at temperature T1 and ageing of the stack resin, circulating at a time t1 the injection resin in the mould, so as to generate a counter-pressure at the periphery of the stack, for pressurization of the resin contained in the latter, said circulating the injection resin being carried out at a pressure P′1 with an increase in temperature from the temperature T0 to temperature T1;at a time t′1, bringing the pressure of the injection resin and the pressure on the stack applied by the press via the mould to a value P1;at a time t″1, increasing temperature of the injection resin and of the press up to a temperature T2 reached at a time t2 which corresponds to the setting of the stack resin;after the stack resin has set, stopping the circulating the injection resin, which remains present in the mould, it being introduced between the stack and each of the two mould surfaces in order to apply a surface pressure on said stack, until the injection resin sets at a time t3; andafter the injection resin has set, maintaining the temperature of the press at a temperature T2 until a time t4, whereas the pressure on the stack applied by the press via the mould falls to a value P0. 9. The method according to claim 8, wherein the operation for raising the temperature of the injection resin and of the press initiated at time t″1 is achieved at a speed which is between 1.5 and 2.5° C./minute. 10. A method for manufacturing a leading edge of an aircraft wing element using a leading edge skin obtained by an implementation of a method for producing a skin of a leading edge for an aircraft wing element, comprising an assembly of resistive heating elements designed to form an integral part of a system for de-icing and/or anti-icing of the leading edge, said method for manufacturing a leading edge of an aircraft wing element comprising:curing a stack in a mould between two moulding surfaces facing each other; andmounting one or more terminal blocks onto an internal surface of said skin and connecting thereon connection terminals for the resistive heating elements;wherein said stack comprising: said assembly of resistive heating elements;two adhesive films arranged respectively on either side of said assembly so that the resistive heating elements adhere to each of these two adhesive films;two layers of electrically insulating pre-impregnated fibres adhering respectively to said two adhesive films on the sides opposite those receiving said resistive heating elements; anda plurality of layers of pre-impregnated carbon fibres, andwherein said curing is achieved by an implementation of following successive operations:keeping on circulating an injection resin in said mould so as to generate and keep a counter-pressure at a periphery of the stack for pressurization of the injection resin contained in said stack until the injection resin of the stack has set; thenstopping the circulating of the injection resin after the injection resin of the stack has set, leading to the injection resin being introduced between the stack and each of the two mould surfaces in order to apply a surface pressure on said stack until the said injection resin in said stack sets. 11. The method according to claim 10, wherein the keeping keeps on circulating the injection resin such that the counter-pressure does not decrease until the injection resin of the stack has set.

이 특허에 인용된 특허 (6)

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

연합인증

특허 상세정보

Method for producing a leading edge skin by baking a stack incorporating heating elements and layers of pre-impregnated fibres

초록
▼

대표
청구항
▼

이 특허에 인용된 특허 (6)

IPC 상위 출원인

과제정보

상세정보조회

원문조회

IPC 상세정보(version : 201201)

연구과제 성과물(0)

참여연구원의 다른 문헌(0)

처리중입니다.

잠시만 기다려주세요.

ScienceON Chatbot

연합인증

특허 상세정보

Method for producing a leading edge skin by baking a stack incorporating heating elements and layers of pre-impregnated fibres

초록 ▼

대표청구항 ▼

이 특허에 인용된 특허 (6)

IPC 상위 출원인

과제정보

상세정보조회

원문조회

IPC 상세정보(version : 201201)

연구과제 성과물(0)

참여연구원의 다른 문헌(0)

처리중입니다.

잠시만 기다려주세요.

초록
▼

대표
청구항
▼