RU2019103284A - Консоль крыла самолета - Google Patents
Консоль крыла самолета Download PDFInfo
- Publication number
- RU2019103284A RU2019103284A RU2019103284A RU2019103284A RU2019103284A RU 2019103284 A RU2019103284 A RU 2019103284A RU 2019103284 A RU2019103284 A RU 2019103284A RU 2019103284 A RU2019103284 A RU 2019103284A RU 2019103284 A RU2019103284 A RU 2019103284A
- Authority
- RU
- Russia
- Prior art keywords
- specified
- winglet
- wing
- wing console
- console
- Prior art date
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
- B64C23/06—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices
- B64C23/065—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices at the wing tips
- B64C23/069—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices at the wing tips using one or more wing tip airfoil devices, e.g. winglets, splines, wing tip fences or raked wingtips
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
- B64C23/06—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices
- B64C23/065—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices at the wing tips
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/10—Drag reduction
Claims (22)
1. Консоль (2, 3) крыла самолета (1), имеющая
длину (b) консоли крыла от фюзеляжа (7) указанного самолета (1) до наружного конца (15) консоли крыла
и по меньшей мере два винглета (9–12) на указанном наружном конце (15) консоли крыла, соединенных с указанной консолью (2, 3) крыла,
при этом расположенный выше по потоку винглет (9, 11) из указанных винглетов предшествует расположенному ниже по потоку винглету (10, 12) из указанных винглетов в направлении полета указанного самолета (1),
при этом указанный расположенный выше по потоку винглет (9, 11) создает завихрение на концевой части винглета в дополнение к завихрению на концевой части консоли крыла, создаваемому указанной консолью (2, 3) крыла,
при этом указанное завихрение на концевой части винглета и указанное завихрение на концевой части консоли крыла накладываются в плоскости между указанными расположенным выше по потоку и расположенным ниже по потоку винглетами (9–12) и перпендикулярно указанному направлению полета,
при этом воздушный поток в указанной плоскости скошен относительно указанного направления полета, и
при этом указанный расположенный ниже по потоку винглет (10, 12) приспособлен для создания подъемной силы, имеющей положительную составляющую (Fxn) тяги, в указанном воздушном потоке.
2. Консоль (2, 3) крыла по п. 1, отличающаяся тем, что указанная зависимость указанного угла направления скорости воздуха от указанного расстояния имеет промежуточное максимальное значение (18) на некотором расстоянии от указанного наружного конца (15) консоли крыла и не падает до значений указанного угла направления скорости воздуха, которые ниже 25 % меньшего из указанных максимальных значений (17, 18), предпочтительно также большего из указанных максимальных значений (17, 18), между указанным промежуточным максимальным значением (18) и указанным максимальным значением (17) наружного конца консоли крыла.
3. Консоль (2, 3) крыла по п. 1 или 2, отличающаяся тем, что указанный расположенный выше по потоку винглет (9, 11) имеет длину (b1), составляющую от 3 % до 8 % указанной длины (b) консоли крыла.
4. Консоль (2, 3) крыла по любому из предыдущих пунктов, отличающаяся тем, что указанный расположенный выше по потоку винглет (9, 11) имеет относительное удлинение, составляющее от 3 до 7.
5. Консоль (2, 3) крыла по любому из предыдущих пунктов, отличающаяся тем, что указанный расположенный ниже по потоку винглет (10, 12) имеет относительное удлинение, составляющее от 3 до 7.
6. Консоль (2, 3) крыла по любому из предыдущих пунктов, отличающаяся тем, что указанный расположенный ниже по потоку винглет (10, 12) имеет асимметричный профиль консоли крыла для увеличения указанной составляющей (Fxn) тяги.
7. Консоль (2, 3) крыла по любому из предыдущих пунктов, отличающаяся тем, что указанный расположенный выше по потоку и указанный расположенный ниже по потоку винглеты (9–12) имеют направленную вверх ориентацию относительно указанной консоли (2, 3) крыла, как видно в указанном направлении полета.
8. Консоль крыла по любому из предыдущих пунктов, отличающаяся тем, что указанный расположенный ниже по потоку винглет (10, 12) имеет длину (b2) по размаху, составляющую от 105 % до 180 % длины (b1) по размаху указанного расположенного выше по потоку винглета (9, 11).
9. Консоль крыла по любому из предыдущих пунктов, отличающаяся тем, что указанный скошенный воздушный поток в указанной плоскости имеет зависимость угла направления скорости воздуха относительно указанного направления полета от расстояния от области максимального значения (17) угла направления скорости воздуха на указанном наружном конце (15) консоли крыла вследствие указанных наложенных завихрений, при этом указанная зависимость сохраняет значение, составляющее по меньшей мере 25 % указанного максимального значения угла направления скорости воздуха, вплоть до значения указанного расстояния, составляющего по меньшей мере 5 % указанной длины консоли крыла.
10. Консоль крыла по любому из предыдущих пунктов, отличающаяся тем, что указанный первый винглет наклонен вверх относительно указанного второго винглета, и указанный второй винглет наклонен вверх относительно указанного третьего винглета, при наличии такового.
11. Консоль крыла по любому из предыдущих пунктов, отличающаяся тем, что содержит третий винглет, расположенный ниже по потоку относительно указанного расположенного ниже по потоку винглета.
12. Консоль крыла по п. 11, отличающаяся тем, что указанный третий винглет приспособлен для создания подъемной силы, имеющей положительную составляющую тяги.
13. Консоль крыла по п. 11 или 12, отличающаяся тем, что указанный третий винглет имеет длину, составляющую от 60 % до 120 % длины указанного расположенного ниже по потоку винглета, который расположен выше по потоку относительно указанного третьего винглета.
14. Самолет (1), содержащий две взаимно противоположные консоли (2, 3) крыла по любому из предыдущих пунктов.
15. Применение усовершенствованной части, содержащей по меньшей мере два винглета (9–12), для прикрепления к самолету (1) с целью создания консоли (2, 3) крыла по любому из пп. 1–13 или самолета (1) по п. 14.
Applications Claiming Priority (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP16020266.9A EP3269635A1 (en) | 2016-07-12 | 2016-07-12 | Airplane wing |
EP16020266.9 | 2016-07-12 | ||
EP16020445.9A EP3269636A1 (en) | 2016-07-12 | 2016-11-11 | Airplane wing |
EP16020445.9 | 2016-11-11 | ||
PCT/EP2017/025204 WO2018010850A1 (en) | 2016-07-12 | 2017-07-12 | Airplane wing |
Publications (1)
Publication Number | Publication Date |
---|---|
RU2019103284A true RU2019103284A (ru) | 2020-08-12 |
Family
ID=56418352
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
RU2019103284A RU2019103284A (ru) | 2016-07-12 | 2017-07-12 | Консоль крыла самолета |
Country Status (11)
Country | Link |
---|---|
US (1) | US11279469B2 (ru) |
EP (3) | EP3269635A1 (ru) |
JP (1) | JP2019521915A (ru) |
KR (1) | KR20190039707A (ru) |
CN (1) | CN109641650B (ru) |
AR (1) | AR109035A1 (ru) |
BR (1) | BR112019000583A2 (ru) |
CA (1) | CA3030319A1 (ru) |
RU (1) | RU2019103284A (ru) |
TW (1) | TW201808726A (ru) |
WO (1) | WO2018010850A1 (ru) |
Families Citing this family (12)
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KR20200028930A (ko) | 2017-07-12 | 2020-03-17 | 더 에어크래프트 퍼포먼스 컴퍼니 게엠베하 | 적어도 2개의 윙릿을 갖는 항공기 날개 |
ES2819559T3 (es) | 2017-12-15 | 2021-04-16 | The Aircraft Performance Company Gmbh | Ala de aeroplano |
EP3511243B1 (en) | 2018-01-15 | 2021-12-29 | The Aircraft Performance Company GmbH | Airplane wing |
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CN112722237B (zh) * | 2021-02-20 | 2023-08-25 | 江西经济管理干部学院 | 一种航空飞行器翼梢小翼 |
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-
2016
- 2016-07-12 EP EP16020266.9A patent/EP3269635A1/en not_active Withdrawn
- 2016-11-11 EP EP16020445.9A patent/EP3269636A1/en not_active Withdrawn
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2017
- 2017-07-12 TW TW106123552A patent/TW201808726A/zh unknown
- 2017-07-12 AR ARP170101941A patent/AR109035A1/es unknown
- 2017-07-12 BR BR112019000583A patent/BR112019000583A2/pt not_active Application Discontinuation
- 2017-07-12 KR KR1020197003644A patent/KR20190039707A/ko unknown
- 2017-07-12 JP JP2019523165A patent/JP2019521915A/ja active Pending
- 2017-07-12 CA CA3030319A patent/CA3030319A1/en not_active Abandoned
- 2017-07-12 CN CN201780053463.6A patent/CN109641650B/zh active Active
- 2017-07-12 WO PCT/EP2017/025204 patent/WO2018010850A1/en unknown
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- 2017-07-12 EP EP17739878.1A patent/EP3484764B1/en active Active
- 2017-07-12 US US16/317,273 patent/US11279469B2/en active Active
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EP3484764A1 (en) | 2019-05-22 |
JP2019521915A (ja) | 2019-08-08 |
CN109641650A (zh) | 2019-04-16 |
AR109035A1 (es) | 2018-10-24 |
US20190248476A1 (en) | 2019-08-15 |
TW201808726A (zh) | 2018-03-16 |
EP3269635A1 (en) | 2018-01-17 |
BR112019000583A2 (pt) | 2019-04-24 |
KR20190039707A (ko) | 2019-04-15 |
CA3030319A1 (en) | 2018-01-18 |
EP3484764C0 (en) | 2023-10-25 |
EP3269636A1 (en) | 2018-01-17 |
WO2018010850A1 (en) | 2018-01-18 |
CN109641650B (zh) | 2022-09-30 |
EP3484764B1 (en) | 2023-10-25 |
US11279469B2 (en) | 2022-03-22 |
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