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1. 发明申请

US20160229528A1 WINGLET SYSTEM HAVING UPPER AND LOWER WINGLET 有权
标题翻译：具有更高和更低的WINGLET的WINGLET系统
公开(公告)号：US20160229528A1
公开(公告)日：2016-08-11
申请号：US15134379
申请日：2016-04-20
申请人： The Boeing Company
发明人： Dino L. Roman , John C. Vassberg , Douglas M. Friedman , Adam P. Malachowski , Christopher A. Vegter
IPC分类号： B64C23/06 , B64C5/10
CPC分类号： B64C5/10 , B64C5/08 , B64C23/069 , Y02T50/164
摘要： A winglet system for an aircraft wing includes an upper winglet and a lower winglet mounted to a wing. The lower winglet has a static position when the wing is subject to an on-ground static loading. The lower winglet may be substantially straight in the static position. The lower winglet is configured such that upward deflection of the wing under an approximate 1-g flight loading causes the lower winglet to move upwardly and outwardly from the static position to an in-flight position resulting in an effective span increase of the wing under the approximate 1-g flight loading relative to the span of the wing under the on-ground static loading.
摘要翻译：用于飞机机翼的小翼系统包括安装到机翼上的上小翼和下小翼。当机翼受到地面静载时，下小翼具有静止位置。下小翼可以在静止位置上基本上是直的。下小翼被构造成使得翼在约1g飞行载荷下的向上偏转导致下小翼从静态位置向上和向外移动到飞行位置，导致翼下的有效跨度增加在地面静载荷下相对于机翼跨度的大约1-g飞行载荷。

2. 外观设计

USD924119S1 Split winglet 有权
公开(公告)号：USD924119S1
公开(公告)日：2021-07-06
申请号：US29617368
申请日：2017-09-13
申请人： The Boeing Company
设计人： Dino L. Roman , John C. Vassberg , Douglas M. Friedman , Adam P. Malachowski , Christopher A. Vegter

3. 发明申请

US20170203830A1 SPLIT WINGLET 审中-公开
公开(公告)号：US20170203830A1
公开(公告)日：2017-07-20
申请号：US15477940
申请日：2017-04-03
申请人： The Boeing Company
发明人： Dino L. Roman , John C. Vassberg , Douglas M. Friedman , Adam P. Malachowski , Christopher A. Vegter
IPC分类号： B64C5/10 , B64C5/08 , B64C23/06
CPC分类号： B64C5/10 , B64C3/58 , B64C5/08 , B64C23/069 , Y02T50/164
摘要： A winglet system for an aircraft wing includes an upper winglet and a lower winglet mounted to a wing. The lower winglet has a static position when the wing is subject to an on-ground static loading. The lower winglet is configured such that upward deflection of the wing under an approximate 1-g flight loading causes the lower winglet to move upwardly and outwardly from the static position to an in-flight position resulting in an effective span increase of the wing under the approximate 1-g flight loading relative to the span of the wing under the on-ground static loading. The lower winglet is configured to aeroelastically deflect upwardly under the approximate 1-g flight loading and further increase the effective span of the wing beyond the effective span increase that is caused by the upward deflection of the wing.

4. 发明授权

US09463871B2 Winglet system having upper and lower winglet 有权
标题翻译： Winglet系统具有上，下小翼
公开(公告)号：US09463871B2
公开(公告)日：2016-10-11
申请号：US15134379
申请日：2016-04-20
申请人： The Boeing Company
发明人： Dino L. Roman , John C. Vassberg , Douglas M. Friedman , Adam P. Malachowski , Christopher A. Vegter
IPC分类号： B64C23/06 , B64C5/10
CPC分类号： B64C5/10 , B64C5/08 , B64C23/069 , Y02T50/164
摘要： A winglet system for an aircraft wing includes an upper winglet and a lower winglet mounted to a wing. The lower winglet has a static position when the wing is subject to an on-ground static loading. The lower winglet may be substantially straight in the static position. The lower winglet is configured such that upward deflection of the wing under an approximate 1-g flight loading causes the lower winglet to move upwardly and outwardly from the static position to an in-flight position resulting in an effective span increase of the wing under the approximate 1-g flight loading relative to the span of the wing under the on-ground static loading.
摘要翻译：用于飞机机翼的小翼系统包括安装到机翼上的上小翼和下小翼。当机翼受到地面静载时，下小翼具有静止位置。下小翼可以在静止位置上基本上是直的。下小翼被构造成使得翼在约1g飞行载荷下的向上偏转导致下小翼从静态位置向上和向外移动到飞行位置，导致翼下的有效跨度增加在地面静载荷下相对于机翼跨度的大约1-g飞行载荷。

5. 发明申请

US20160009380A1 WINGLET SYSTEM AND METHOD 有权
标题翻译： WINGLET系统和方法
公开(公告)号：US20160009380A1
公开(公告)日：2016-01-14
申请号：US14566483
申请日：2014-12-10
申请人： The Boeing Company
发明人： Dino L. Roman , John C. Vassberg , Douglas M. Friedman , Adam P. Malachowski , Christopher A. Vegter
IPC分类号： B64C23/06 , B64C5/10
CPC分类号： B64C5/10 , B64C5/08 , B64C23/069 , Y02T50/164
摘要： A winglet system for an aircraft wing may include an upper winglet and a lower winglet mounted to a wing tip. The lower winglet may have a static position when the wing is subject to an on-ground static loading. The lower winglet may be configured such that upward deflection of the wing under an approximate 1-g flight loading causes the lower winglet to move upwardly and outwardly from the static position to an in-flight position resulting in an effective span increase of the wing under the approximate 1-g flight loading relative to the span of the wing under the on-ground static loading. The lower winglet may have a length of approximately 50-80 percent of a length of the upper winglet.
摘要翻译：用于飞机机翼的小翼系统可以包括安装到翼尖的上小翼和下小翼。当机翼受到地面静载荷时，下小翼可能具有静止位置。下小翼可以被配置为使得在大约1g飞行载荷下翼的向上偏转导致下小翼从静态位置向上和向外移动到飞行位置，导致翼的有效跨度增加在地面静载荷下相对于机翼跨度的大约1-g飞行载荷。下小翼的长度可以为上小翼长度的大约50-80％。

6. 发明申请

US20170015406A1 SPLIT WINGLET SYSTEM 有权
标题翻译：分体WINGLET系统
公开(公告)号：US20170015406A1
公开(公告)日：2017-01-19
申请号：US15259509
申请日：2016-09-08
申请人： The Boeing Company
发明人： Dino L. Roman , John C. Vassberg , Douglas M. Friedman , Adam P. Malachowski , Christopher A. Vegter
IPC分类号： B64C23/06 , B64C5/10
CPC分类号： B64C5/10 , B64C5/08 , B64C23/069 , Y02T50/164
摘要： A winglet system for an aircraft wing includes an upper winglet and a lower winglet mounted to a wing. The lower winglet has a static position when the wing is subject to an on-ground static loading. The lower winglet is configured such that upward deflection of the wing under an approximate 1-g flight loading causes the lower winglet to move upwardly and outwardly from the static position to an in-flight position resulting in an effective span increase of the wing under the approximate 1-g flight loading relative to the span of the wing under the on-ground static loading. The lower winglet is configured to aeroelastically deflect upwardly under the approximate 1-g flight loading and further increase the effective span of the wing beyond the effective span increase that is caused by the upward deflection of the wing.
摘要翻译：用于飞机机翼的小翼系统包括安装到机翼上的上小翼和下小翼。当机翼受到地面静载时，下小翼具有静止位置。下小翼被构造成使得翼在约1g飞行载荷下的向上偏转导致下小翼从静态位置向上和向外移动到飞行位置，导致翼下的有效跨度增加在地面静载荷下相对于机翼跨度的大约1-g飞行载荷。下翼小翼被配置为在大约1-g飞行载荷下气动弹性地向上偏转，并进一步增加机翼的有效跨度超过由机翼的向上偏转引起的有效跨度增加。

7. 发明授权

US09346537B2 Winglet system 有权
标题翻译： Winglet系统
公开(公告)号：US09346537B2
公开(公告)日：2016-05-24
申请号：US14942988
申请日：2015-11-16
申请人： The Boeing Company
发明人： Dino L. Roman , John C. Vassberg , Douglas M. Friedman , Adam P. Malachowski , Christopher A. Vegter
IPC分类号： B64C23/06
CPC分类号： B64C5/10 , B64C5/08 , B64C23/069 , Y02T50/164
摘要： A winglet system for an aircraft wing may include an upper winglet and a lower winglet mounted to a wing tip. The upper winglet root chord and the lower winglet root chord may each have a length of no greater than 100 percent of the wing tip chord. The lower winglet may have a static position when the wing is subject to an on-ground static loading. The lower winglet may be configured such that upward deflection of the wing under an approximate 1-g flight loading causes the lower winglet to move upwardly and outwardly from the static position to an in-flight position resulting in an effective span increase of the wing under the approximate 1-g flight loading relative to the span of the wing under the on-ground static loading.
摘要翻译：用于飞机机翼的小翼系统可以包括安装到翼尖的上小翼和下小翼。上小翼根弦和下小翼根弦可以各自具有不大于翼尖弦的100％的长度。当机翼受到地面静载荷时，下小翼可能具有静止位置。下小翼可以被配置为使得在大约1g飞行载荷下翼的向上偏转导致下小翼从静态位置向上和向外移动到飞行位置，导致翼的有效跨度增加在地面静载荷下相对于机翼跨度的大约1-g飞行载荷。

8. 发明授权

US09637226B2 Split winglet system 有权
公开(公告)号：US09637226B2
公开(公告)日：2017-05-02
申请号：US15259509
申请日：2016-09-08
申请人： The Boeing Company
发明人： Dino L. Roman , John C. Vassberg , Douglas M. Friedman , Adam P. Malachowski , Christopher A. Vegter
IPC分类号： B64C23/06 , B64C5/10
CPC分类号： B64C5/10 , B64C5/08 , B64C23/069 , Y02T50/164
摘要： A winglet system for an aircraft wing includes an upper winglet and a lower winglet mounted to a wing. The lower winglet has a static position when the wing is subject to an on-ground static loading. The lower winglet is configured such that upward deflection of the wing under an approximate 1-g flight loading causes the lower winglet to move upwardly and outwardly from the static position to an in-flight position resulting in an effective span increase of the wing under the approximate 1-g flight loading relative to the span of the wing under the on-ground static loading. The lower winglet is configured to aeroelastically deflect upwardly under the approximate 1-g flight loading and further increase the effective span of the wing beyond the effective span increase that is caused by the upward deflection of the wing.

9. 发明申请

US20160068259A1 WINGLET SYSTEM 有权
标题翻译： WINGLET系统
公开(公告)号：US20160068259A1
公开(公告)日：2016-03-10
申请号：US14942988
申请日：2015-11-16
申请人： The Boeing Company
发明人： Dino L. Roman , John C. Vassberg , Douglas M. Friedman , Adam P. Malachowski , Christopher A. Vegter
IPC分类号： B64C23/06
CPC分类号： B64C5/10 , B64C5/08 , B64C23/069 , Y02T50/164
摘要： A winglet system for an aircraft wing may include an upper winglet and a lower winglet mounted to a wing tip. The upper winglet root chord and the lower winglet root chord may each have a length of no greater than 100 percent of the wing tip chord. The lower winglet may have a static position when the wing is subject to an on-ground static loading. The lower winglet may be configured such that upward deflection of the wing under an approximate 1-g flight loading causes the lower winglet to move upwardly and outwardly from the static position to an in-flight position resulting in an effective span increase of the wing under the approximate 1-g flight loading relative to the span of the wing under the on-ground static loading.
摘要翻译：用于飞机机翼的小翼系统可以包括安装到翼尖的上小翼和下小翼。上小翼根弦和下小翼根弦可以各自具有不大于翼尖弦的100％的长度。当机翼受到地面静载荷时，下小翼可能具有静止位置。下小翼可以被配置为使得在大约1g飞行载荷下翼的向上偏转导致下小翼从静态位置向上和向外移动到飞行位置，导致翼的有效跨度增加在地面静载荷下相对于机翼跨度的大约1-g飞行载荷。

10. 发明授权

US09216817B1 Winglet system and method 有权
标题翻译： Winglet系统和方法
公开(公告)号：US09216817B1
公开(公告)日：2015-12-22
申请号：US14566483
申请日：2014-12-10
申请人： The Boeing Company
发明人： Dino L. Roman , John C. Vassberg , Douglas M. Friedman , Adam P. Malachowski , Christopher A. Vegter
IPC分类号： B64C23/06
CPC分类号： B64C5/10 , B64C5/08 , B64C23/069 , Y02T50/164
摘要： A winglet system for an aircraft wing may include an upper winglet and a lower winglet mounted to a wing tip. The lower winglet may have a static position when the wing is subject to an on-ground static loading. The lower winglet may be configured such that upward deflection of the wing under an approximate 1-g flight loading causes the lower winglet to move upwardly and outwardly from the static position to an in-flight position resulting in an effective span increase of the wing under the approximate 1-g flight loading relative to the span of the wing under the on-ground static loading. The lower winglet may have a length of approximately 50-80 percent of a length of the upper winglet.
摘要翻译：用于飞机机翼的小翼系统可以包括安装到翼尖的上小翼和下小翼。当机翼受到地面静载荷时，下小翼可能具有静止位置。下小翼可以被配置为使得在大约1g飞行载荷下翼的向上偏转导致下小翼从静态位置向上和向外移动到飞行位置，导致翼的有效跨度增加在地面静载荷下相对于机翼跨度的大约1-g飞行载荷。下小翼的长度可以为上小翼长度的大约50-80％。

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