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公开(公告)号：US08056852B1
公开(公告)日：2011-11-15
申请号：US13031421
申请日：2011-02-21
IPC分类号： B64C1/00
CPC分类号： B64C39/08 , B64C3/10 , B64C5/02 , B64C2039/105 , B64D27/10 , B64D27/16 , Y02T50/12 , Y02T50/44
摘要： The Longitudinal Flying Wing aircraft idea provides for design of large cargo and passenger aircraft in range from low to high subsonic and transonic speed. Such aircraft would have up to twice lower fuel consumption per unit of payload, higher lift capacity, and a significantly longer range, while having a significantly lower level of noise inside passenger cabin and cockpit relative to classical concept aircraft. This idea is further providing for efficient, reliable, and simple flight controls, hence it may be successfully applied for design of all-size, long range, high-lift-capacity unmanned aircraft throughout the entire range of subsonic speeds.
摘要翻译： 纵向飞翼飞机理念为大型货物和客机的设计提供了从低到高的亚音速和跨音速。 相对于古典概念飞机，这种飞机的单位有效载荷，更高的起重能力和更大范围的燃料消耗量可以降低两倍，同时在客舱和驾驶舱内的噪音水平显着降低。 这个想法进一步提供了有效，可靠和简单的飞行控制，因此可以成功地应用于整个亚音速范围内的全尺寸，长距离，高提升能力的无人机的设计。
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公开(公告)号：US11891171B1
公开(公告)日：2024-02-06
申请号：US18208309
申请日：2023-06-12
CPC分类号： B64C3/14 , B64C3/56 , B64C2003/147
摘要： The present invention “Aircraft Wing with Tiplet” reflects a wing with two distinct sections including inner section for maximized lift production with long chords, high taper, and ultra-thin airfoils for substantial profile drag reduction, as well as a “tiplet” section with minimized area and maximized span to minimize aspect ratio penalty from the standpoint of increased induced drag mitigation due to large inner section lifting area. Long chords and large area of inner section are feasible from the standpoint of flight safety with the application of airfoils with forward center of pressure that provide for dynamic stability of aircraft in flight.
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公开(公告)号：US07793884B2
公开(公告)日：2010-09-14
申请号：US12347997
申请日：2008-12-31
IPC分类号： B64C3/00
CPC分类号： B64C30/00 , B64C1/0009 , B64C3/10 , B64C39/12 , B64C2039/105 , Y02T50/12
摘要： “T-tailed Deltoid Main Wing” idea allows for design of high-subsonic passenger aircraft with a capacity between 200 and 650 passengers with outer dimensions fitting within 80 m box on class VI airports while having more than twice lower fuel consumption per unit of payload when compared to the present classical-concept aircraft with fuselage that have the same passenger capacity. T-tailed deltoid main wing aircraft is satisfying all safety requirements for a passenger aircraft while having over 50% longer range than the aircraft of equivalent capacity with fuselage. Simple aerodynamic and structural solutions of T-tailed deltoid main wing aircraft are resulting with low development risks and production cost. Simple and reliable flight control systems of aircraft that are based on T-tailed deltoid main wing aerodynamic configuration allow for design of all-purpose, high-lift-capacity, and long range unmanned aircraft.
摘要翻译： “T-tailed Deltoid Main Wing”理念允许设计容量在200至650乘客之间的高亚音速客机，其外形尺寸适合VI类机场的80 m箱内，同时每单位有效载荷的燃油消耗量低两倍以上 与目前具有相同乘客容量的机身的古典概念飞机相比。 T型三角体主翼飞机满足客机的所有安全要求，同时具有比机身等效容量超过50％的飞机。 T型三角体主翼飞机的简单空气动力学和结构解决方案，具有较低的开发风险和生产成本。 基于T型三角形主翼空气动力学配置的飞机简单可靠的飞行控制系统，可以设计出多用途，高升力和远程无人驾驶飞机。
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公开(公告)号：US20100163670A1
公开(公告)日：2010-07-01
申请号：US12347997
申请日：2008-12-31
IPC分类号： B64C1/00
CPC分类号： B64C30/00 , B64C1/0009 , B64C3/10 , B64C39/12 , B64C2039/105 , Y02T50/12
摘要： Deltoid Main Wing idea provides for several innovative aerodynamic configurations for large subsonic and supersonic civil and military aircraft including “T-tailed Deltoid Main Wing” configuration that allows for design of high-subsonic jumbo jet passenger aircraft with a capacity between 200 and 700 passengers whose outer dimensions fit within 80 m box on class VI airports while having more than twice lower fuel consumption per unit of payload when compared to the present classical-concept aircraft with the same passenger capacity, while further allowing for design of all-size and all-purpose, high-lift-capacity, and long-range unmanned aircraft.
摘要翻译： Deltoid Main Wing的概念为大型亚音速和超音速民用和军用飞机提供了多种创新的空气动力学配置，包括“T-tailed Deltoid主翼”配置，允许设计高亚音速超大型喷气客机，容量在200到700乘客之间 外部尺寸适合VI类机场的80米箱内，与目前具有相同乘客能力的古典概念飞机相比，每单位有效载荷的燃料消耗降低了两倍以上，同时进一步允许全尺寸和全尺寸的设计， 目的，高能力和远程无人机。
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公开(公告)号：US10640212B1
公开(公告)日：2020-05-05
申请号：US16194366
申请日：2018-11-18
摘要： The present invention is a double wing aircraft with two fixed wings embodied as either a flying wing configuration or a double wing configuration having a fuselage with smaller external dimensions, larger airlifting area, thinner airfoils, and lighter airframe relative to prior art that altogether is resulting with lower drag, fuel consumption, harmful emissions, and noise, as well as higher speed and flight safety, longer range, and shorter runway when compared to prior art.
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公开(公告)号：US07854409B2
公开(公告)日：2010-12-21
申请号：US12764925
申请日：2010-04-21
IPC分类号： B64C39/12
CPC分类号： B64C30/00 , B64C1/0009 , B64C3/10 , B64C39/12 , B64C2039/105 , Y02T50/12
摘要： Canarded deltoid main wing aircraft idea allows for design of large supersonic civil and military aircraft with cruising speeds of up to Mach 3 at the altitude of over 25,000 meters. The fuel consumption per unit of payload of such aircraft would be at least twice lower with a longer range of over 50% when compared to existing supersonic aircraft of the same size. Simultaneously, the flight safety and ride quality during takeoff and landing at low speeds would be similar to the existing subsonic passenger aircraft. A low fuel consumption, long range, high ride quality, and high flight safety of these aircraft are widely opening a door for design of supersonic long range continental and intercontinental passenger aircraft that would be highly competitive with existing long range high subsonic passenger aircraft.
摘要翻译： 拥有三角肌的主翼飞机理念允许设计大型超音速民用和军用飞机，巡航速度高达马赫数3，高度超过2.5万米。 与相同尺寸的现有超音速飞机相比，这种飞机的单位有效载荷的燃油消耗量将至少降低两倍，超过50％的更长的范围。 同时，低速起飞和着陆时的飞行安全和乘坐质量将类似于现有的亚音速客机。 这些飞机的低油耗，长距离，高乘坐质量和高飞行安全性正在广泛开启超音速远程大陆和洲际客机的设计大门，与现有的远程高亚音速客机竞争激烈。
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公开(公告)号：US06578798B1
公开(公告)日：2003-06-17
申请号：US10118839
申请日：2002-04-08
IPC分类号： B64C2306
CPC分类号： B64C23/069 , B64C2039/105 , Y02T50/12 , Y02T50/164
摘要： This airlifting surface division idea provides for division of airlifting surfaces resulting in low induced and interference drag. It can be applied to aircraft wings and helicopter and windmill rotor blades to significantly reduce induced drag when compared to prior art. Also, it can be used for new concepts of large subsonic and hypersonic aircraft to significantly reduce their overall drag and external dimensions when compared to prior art, simultaneously providing for very good pitch maneuver and longitudinal stability of such aircraft.
摘要翻译： 这种空运表面划分方案提供了空运表面的划分，导致低的诱导和干扰阻力。 与现有技术相比，它可以应用于飞机机翼和直升机和风车转子叶片，以显着减少诱发的阻力。 此外，与现有技术相比，它可以用于大型亚音速和超音速飞机的新概念，以显着降低它们的整体阻力和外部尺寸，同时提供这种飞行器的非常好的俯仰操纵和纵向稳定性。
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公开(公告)号：US20200156787A1
公开(公告)日：2020-05-21
申请号：US16194366
申请日：2018-11-18
摘要： The present invention is a double wing aircraft with two fixed wings embodied as either a flying wing configuration or a double wing configuration having a fuselage with smaller external dimensions, larger airlifting area, thinner airfoils, and lighter airframe relative to prior art that altogether is resulting with lower drag, fuel consumption, harmful emissions, and noise, as well as higher speed and flight safety, longer range, and shorter runway when compared to prior art.
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公开(公告)号：US20100224735A1
公开(公告)日：2010-09-09
申请号：US12764925
申请日：2010-04-21
IPC分类号： B64C39/12
CPC分类号： B64C30/00 , B64C1/0009 , B64C3/10 , B64C39/12 , B64C2039/105 , Y02T50/12
摘要： Canarded deltoid main wing aircraft idea allows for design of large supersonic civil and military aircraft with cruising speeds of up to Mach 3 at the altitude of over 25,000 meters. The fuel consumption per unit of payload of such aircraft would be at least twice lower with a longer range of over 50% when compared to existing supersonic aircraft of the same size. Simultaneously, the flight safety and ride quality during takeoff and landing at low speeds would be similar to the existing subsonic passenger aircraft. A low fuel consumption, long range, high ride quality, and high flight safety of these aircraft are widely opening a door for design of supersonic long range continental and intercontinental passenger aircraft that would be highly competitive with existing long range high subsonic passenger aircraft.
摘要翻译： 拥有三角肌的主翼飞机理念允许设计大型超音速民用和军用飞机，巡航速度高达马赫数3，高度超过2.5万米。 与相同尺寸的现有超音速飞机相比，这种飞机的单位有效载荷的燃油消耗量将至少降低两倍，超过50％的更长的范围。 同时，低速起飞和着陆时的飞行安全和乘坐质量将类似于现有的亚音速客机。 这些飞机的低油耗，长距离，高乘坐质量和高飞行安全性正在广泛开启超音速远程大陆和洲际客机的设计大门，与现有的远程高亚音速客机竞争激烈。
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公开(公告)号：US06923403B1
公开(公告)日：2005-08-02
申请号：US10803307
申请日：2004-03-18
CPC分类号： B64C1/0009 , B64C3/10 , B64C39/10 , B64C2039/105 , B64D11/00 , Y02T50/12 , Y02T50/46
摘要： The “Tailed Flying Wing Aircraft” idea represents new aerodynamic concepts for large high subsonic aircraft. Large high subsonic aircraft based on these new aerodynamic concepts are having a significantly higher lift capacity and longer range, as well as a significantly lower fuel consumption of at least two times less than the aircraft based on classical fuselage concept with the same external dimensions. In addition, the aircraft based on the new concepts are having a significantly better longitudinal stability and maneuverability, as well as aerodynamic efficiency at high subsonic speed than aircraft based on “Tailless Flying Wing” concepts. The aircraft based on the “Tailed Flying Wing Aircraft” idea satisfy all safety requirements for civil aircraft. They also have simple shapes for manufacturing, hence this idea provides for new realistic advanced aerodynamic concepts for the next generations of large subsonic aircraft.
摘要翻译： “尾翼飞机”理念代表了大型高亚音速飞机的新型空气动力学概念。 基于这些新的空气动力学概念的大型高亚音速飞机具有显着更高的提升能力和更长的距离，以及基于具有相同外部尺寸的古典机身概念，飞行器的燃料消耗至少比飞机低两倍。 此外，基于新概念的飞机具有比基于“无太空飞翼”概念的飞机基于高亚音速度的显着更好的纵向稳定性和机动性以及空气动力学效率。 基于“尾翼飞机”理念的飞机满足民用飞机的所有安全要求。 它们也具有简单的制造形状，因此这个想法为下一代大型亚音速飞机提供了新的现实先进的空气动力学概念。
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