IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0274544
(2011-10-17)
|
등록번호 |
US-8814083
(2014-08-26)
|
우선권정보 |
FR-10 04204 (2010-10-26) |
발명자
/ 주소 |
- Lhermenault, Rodolphe
- Meyer, Thomas
- Azeau, Jean
- Guitton, Julien
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
1 인용 특허 :
17 |
초록
▼
An aircraft (1) provided with a tail boom (4) including a tail plane (100) provided with an airfoil surface (5), the airfoil surface (5) being provided with at least one stabilizer portion (11, 12) extending laterally outside the tail boom (4) and with a central portion (13) extending inside the tai
An aircraft (1) provided with a tail boom (4) including a tail plane (100) provided with an airfoil surface (5), the airfoil surface (5) being provided with at least one stabilizer portion (11, 12) extending laterally outside the tail boom (4) and with a central portion (13) extending inside the tail boom (4), said stabilizer portion (11, 12) being implanted in an orifice (6, 7) of the tail boom (4) that is defined by a peripheral wall (6′, 7′), clearance (21, 22) existing between said stabilizer portion (11, 12) and said peripheral wall (6, 7). The aircraft includes combating means (30) for combating the flutter phenomenon, which means are provided with stiffener means (31, 32) exerting predetermined compressive stress on said stabilizer portion (11, 12), said stiffener means (31, 32) being arranged at the root of the stabilizer portion (11, 12).
대표청구항
▼
1. An aircraft comprising: a tail boom extending in a longitudinal direction, the tail boom including a tail plane provided with an airfoil surface extending in a transverse direction;at least one stabilizer portion provided with the airfoil surface and extending laterally outside the tail boom and
1. An aircraft comprising: a tail boom extending in a longitudinal direction, the tail boom including a tail plane provided with an airfoil surface extending in a transverse direction;at least one stabilizer portion provided with the airfoil surface and extending laterally outside the tail boom and with a central portion extending inside the tail boom, the stabilizer portion being implanted in an orifice defined by a peripheral wall of the tail boom;a clearance existing between the stabilizer portion and the peripheral wall;combating means for combating the phenomenon of flutter, which combating means are provided with stiffener means arranged in the clearance; andat least two tabs included on the stiffener means for exerting compression stress on the stabilizer portion; each tab being in contact with an outer covering of the stabilizer portion and the tail boom, each tab being provided with fastener means receiving in a housing,wherein the stiffener means is compressed between the fastener means and the stabilizer portion, the stiffener means then being in contact with the at least one stabilizer portion, the stiffener means being locked in the housing in an elevation direction by a fastener plate of the fastener means and by the stabilizer portion, and in a plane contained between the fastener plate and the stabilizer portion by a side edge of the fastener means and by closure means, the side edge extending from the fastener plate towards the stabilizer portion without reaching the stabilizer portion, said closure means being removable and co-operating with said fastener means,wherein the two tabs are spaced apart in the longitudinal direction. 2. The aircraft according to claim 1, wherein said stiffener means include a filler material arranged in the clearance between a stabilizer portion of the associated peripheral wall, wherein the filler material surrounds said stabilizer portion, said filler material having predetermined stiffness is independent of ambient temperature. 3. The aircraft according to claim 1, wherein said stiffener means are provided with adjustment means suitable for being arranged between said stiffener and a fastener plate of said fastener means. 4. The aircraft according to claim 1, wherein said stiffener includes rigid contact means for making contact with the stabilizer portion. 5. The aircraft according to claim 1, wherein said stiffener comprises contact means prestressed to present determined stiffness. 6. The aircraft according to claim 1, wherein said stiffener includes slide means and contact means, said slide means facilitating arranging the stiffener in said housing, and said contact means bearing against the stabilizer portion. 7. The aircraft according to claim 6, wherein said slide means comprise a receptacle receiving said contact means, said contact means projecting from said receptacle. 8. The aircraft according to claim 1, wherein said airfoil surface is provided with a first stabilizer portion and with a second stabilizer portion extending on either side of the tail boom together with a central portion extending inside the tail boom to interconnect the first and second stabilizer portions, first clearance extending between said first stabilizer portion and a first peripheral wall of the tail boom and second clearance extending between said second stabilizer portion and a second peripheral wall of the tail boom, said aircraft including respective stiffener means for each stabilizer portion, first stiffener means being arranged in the first clearance of the first stabilizer portion and second stiffener means being arranged in the second clearance of the second stabilizer portion. 9. An aircraft comprising: a tail boom extending in a longitudinal direction from an aircraft body and defined by a peripheral wall having an orifice extending in a transverse direction through the tail boom;at least one tail plane stabilizer having an airfoil surface and extending transverse to the tail boom in the transverse direction through the orifice;a clearance region defined between the tail plane stabilizer and the peripheral wall; anda stiffening device positioned in the clearance region for combating flutter of the tail plane stabilizer, the stiffening device including two tabs exerting compression stress on the tail plane stabilizer, each tab being received in a housing and being in contact with an outer covering of the tail plane stabilizer and the tail boom, each tab including a stiffener portion compressed between a fastener and the tail plane stabilizer such that the stiffener portion is in contact with the tail plane stabilizer and locked in the housing in an elevation direction between the fastener and the tail plane stabilizer, and the stiffener portion is locked in the transverse direction between the fastener and a removable closure,wherein the two tabs are positioned on an upper suction side surface of the tail plane stabilizer. 10. The aircraft according to claim 9, further comprising a filler material arranged in the clearance the filler material having predetermined stiffness that is independent of ambient temperature. 11. The aircraft according to claim 9, wherein the stiffening device is provided with adjustment means suitable for being arranged between the stiffener and a fastener plate of the fastener. 12. The aircraft according to claim 9, wherein the stiffener portion includes rigid contact portion for making contact with the tail plane stabilizer, wherein the contact portion is pre-stressed to a pre-determined stiffness. 13. The aircraft according to claim 12, wherein the housing defines a receptacle for receiving the stiffener portion, and wherein the contact portion projects from the receptacle to contact the tail plane stabilizer. 14. The aircraft according to claim 9, wherein the tail plane stabilizer includes a first stabilizer portion provided on a first side of the tail boom, a central portion extending inside the tail boom, and a second stabilizer portion provided on a second side of the tail boom, and wherein the clearance region includes a first clearance region extending between the first stabilizer portion and a first peripheral wall of the tail boom and second clearance region extending between the second stabilizer portion and a second peripheral wall of the tail boom, the aircraft including first and second stiffening devices for each of the first and second stabilizer portions, first stiffening device being arranged in the first clearance region and the second stiffening device being arranged in the second clearance region of the second stabilizer portion. 15. The aircraft according to claim 9, wherein the two tabs are spaced apart in the longitudinal direction. 16. An aircraft comprising: a tail boom extending in a longitudinal direction from an aircraft body and defined by a peripheral wall having an orifice extending in a transverse direction through the tail boom;at least one tail plane stabilizer having an airfoil surface and extending transverse to the tail boom in the transverse direction through the orifice;a clearance region defined between the tail plane stabilizer and the peripheral wall; anda stiffening device positioned in the clearance region for combating flutter of the tail plane stabilizer, the stiffening device including two tabs positioned on an upper pressure side of the tail plane stabilizer and exerting compression stress on the tail plane stabilizer, each tab being received in a housing and being in contact with an outer covering of the tail plane stabilizer and the tail boom, each tab including a stiffener portion compressed between a fastener and the tail plane stabilizer such that the stiffener portion is in contact with the tail plane stabilizer and locked in the housing in an elevation direction between the fastener and the tail plane stabilizer, and the stiffener portion is locked in the transverse direction between the fastener and a removable closure,wherein the stiffening device further comprises at least two additional tabs positioned on a lower pressure side surface of the tail plane stabilizer. 17. The aircraft according to claim 1, wherein the stiffener means further comprises at least two additional tabs positioned on a lower pressure side surface of the tail plane stabilizer.
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