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1. 发明公开

EP3213991A1 AIRCRAFT WING ROUGHNESS STRIP 有权转让
标题翻译：飞机WING ROUGHNESS STRIP
公开(公告)号：EP3213991A1
公开(公告)日：2017-09-06
申请号：EP17158776.9
申请日：2017-03-01
申请人： Airbus Group Limited
发明人： ROLSTON, Stephen
IPC分类号： B64C21/10 , B64C30/00 , B64C3/00 , B64C3/26
CPC分类号： B64C21/10 , B64C3/00 , B64C3/10 , B64C3/26 , B64C30/00 , B64C39/024 , B64C2003/148 , B64C2003/149 , B64C2230/08 , Y02T50/12 , Y02T50/166
摘要： A fixed wing aircraft has a wing with an aerofoil cross-section defining an upper geometric surface and a lower geometric surface which meet at a geometric leading edge of the wing at the intersection with the aerofoil geometric chord. The wing is configured to define an upper aerodynamic surface and a lower aerodynamic surface when the wing is moved through air. The upper aerodynamic surface and the lower aerodynamic surface meet at an aerodynamic leading edge of the wing at the intersection with an attachment line dividing the air that passes over the upper aerodynamic surface from the air that passes over the lower aerodynamic surface. The lower geometric surface adjacent the geometric leading edge has a roughness strip with a step height of at least 50 microns over the lower geometric surface. The roughness strip is located on the lower aerodynamic surface of the wing when the aircraft is flown at a load factor -the ratio of the lift of the aircraft to its weight - of 1g, and the roughness strip is located on the upper aerodynamic surface when the aircraft is flown at a load factor of 1.2g or more.
摘要翻译：固定翼飞机具有机翼横截面，所述机翼横截面限定上部几何表面和下部几何表面，所述上部几何表面和下部几何表面在与机翼几何弦的相交处的机翼的几何前缘处相交。机翼被配置成当机翼通过空气移动时限定上部空气动力学表面和下部空气动力学表面。上部空气动力学表面和下部空气动力学表面在机翼的空气动力学前缘处与连接线相遇，所述连接线将穿过上部空气动力学表面的空气与经过下部空气动力学表面的空气分开。邻近几何前缘的下几何表面具有在下几何表面上具有至少50微米的台阶高度的粗糙带。当飞机以负载系数（飞机升力与其重量之比）为1g飞行时，粗糙带位于机翼的下部空气动力学表面上，并且粗糙带位于上部空气动力学表面上时该飞机以1.2g或更高的载荷系数飞行。

2. 发明授权

EP2466288B1 Method of designing natural laminar flow wing for reynolds numbers equivalent to actual supersonic aircraft 失效
标题翻译：与雷诺数，这是目前的超音速飞机等效自然层设计一个机翼的方法
公开(公告)号：EP2466288B1
公开(公告)日：2016-10-19
申请号：EP11192278.7
申请日：2011-12-07
申请人： Japan Aerospace Exploration Agency
发明人： Yoshida, Kenji , Matsushima, Kisa , Ueda, Yoshine , Ishikawa, Hiroaki
IPC分类号： G06F17/50 , B64F5/00 , B64C3/14 , B64C30/00
CPC分类号： B64C3/14 , B64C30/00 , B64C2003/149 , B64F5/00 , G06F17/5095 , Y02T50/12

3. 发明公开

EP2250086A2 SHOCK BUMP 有权
标题翻译：冲击产生隆起
公开(公告)号：EP2250086A2
公开(公告)日：2010-11-17
申请号：EP09714018.0
申请日：2009-02-17
申请人： Airbus Operations Limited
发明人： WOOD, Norman
IPC分类号： B64C23/04 , B64C7/00
CPC分类号： B64C23/04 , B64C2003/148 , B64C2003/149
摘要： A shock bump (10) comprising a diverging nose (20) and a converging tail. The tail has at least one plan-form contour line with a pair of concave opposite sides (22, 23). The shock bump provides an improved shape with relatively low drag. Furthermore, the concave shape of the tail tends to promote the development of longitudinal vortices which can reduce shock induced buffet at certain operating conditions.

4. 发明公开

EP2247497A2 AERODYNAMIC STRUCTURE WITH ASYMMETRICAL SHOCK BUMP 有权
标题翻译：不对称SHOCK动力学结构
公开(公告)号：EP2247497A2
公开(公告)日：2010-11-10
申请号：EP09715399.3
申请日：2009-02-17
申请人： Airbus Operations Limited
发明人： WOOD, Norman
IPC分类号： B64C23/04
CPC分类号： B64C23/04 , B64C23/00 , B64C2003/148 , B64C2003/149
摘要： An aerodynamic structure comprising a shock bump (3) extending from its surface. The shock bump is asymmetrical about a plane of asymmetry, and the plane of asymmetry: passes through a centre (6) of the shock bump, is parallel with a principal direction of air flow over the structure, and extends at a right angle to the surface of the structure.

5. 发明授权

EP0076936B1 Profile, insbesondere Tragflügelprofile für Luftfahrzeuge 失效
标题翻译： AIR FOIL，特别是空中飞机
公开(公告)号：EP0076936B1
公开(公告)日：1986-06-04
申请号：EP82108579.2
申请日：1982-09-17
申请人： DORNIER GMBH
发明人： Schmidt, Wolfgang, Dr.-Ing. , Longo, José Maria
IPC分类号： B64C3/14
CPC分类号： B64C3/14 , B64C2003/149

6. 发明授权

EP2247497B1 AERODYNAMIC STRUCTURE WITH ASYMMETRICAL SHOCK BUMP 有权
标题翻译：不对称SHOCK动力学结构
公开(公告)号：EP2247497B1
公开(公告)日：2015-07-01
申请号：EP09715399.3
申请日：2009-02-17
申请人： Airbus Operations Limited
发明人： WOOD, Norman
IPC分类号： B64C23/04
CPC分类号： B64C23/04 , B64C23/00 , B64C2003/148 , B64C2003/149
摘要： An aerodynamic structure comprising a shock bump (3) extending from its surface. The shock bump is asymmetrical about a plane of asymmetry, and the plane of asymmetry: passes through a centre (6) of the shock bump, is parallel with a principal direction of air flow over the structure, and extends at a right angle to the surface of the structure.

7. 发明公开

EP2466288A3 Method of designing natural laminar flow wing for reynolds numbers equivalent to actual supersonic aircraft 失效
标题翻译：设计一个天然鳞片状河翼为与当前超声波相当于飞机相关的雷诺数的方法
公开(公告)号：EP2466288A3
公开(公告)日：2013-08-28
申请号：EP11192278.7
申请日：2011-12-07
申请人： Japan Aerospace Exploration Agency
发明人： Yoshida, Kenji , Matsushima, Kisa , Ueda, Yoshine , Ishikawa, Hiroaki
IPC分类号： G01M9/06 , G01M9/08 , B64C3/14 , B64C23/00 , B64F5/00 , B64C30/00
CPC分类号： B64C3/14 , B64C30/00 , B64C2003/149 , B64F5/00 , G06F17/5095 , Y02T50/12
摘要： In designing supersonic aircrafts, a method of designing a natural laminar flow wing is provided which reduces friction drag by delaying boundary layer transition under flight conditions of actual aircrafts. A target Cp distribution on wing upper surface, suited to natural laminarization in which boundary layer transition is delayed rearward in desired Reynolds number states, is defined by a functional type having as coefficients parameters depending on each spanwise station, a sensitivity analysis employing a transition analysis method is applied to the parameters, and a search is performed for the optimum combination of parameters to delay transition rearward.

8. 发明公开

EP2466288A2 Method of designing natural laminar flow wing for reynolds numbers equivalent to actual supersonic aircraft 失效
标题翻译：与雷诺数，这是目前的超音速飞机等效自然层设计一个机翼的方法
公开(公告)号：EP2466288A2
公开(公告)日：2012-06-20
申请号：EP11192278.7
申请日：2011-12-07
申请人： Japan Aerospace Exploration Agency
发明人： Yoshida, Kenji , Matsushima, Kisa , Ueda, Yoshine , Ishikawa, Hiroaki
IPC分类号： G01M9/06 , G01M9/08 , B64C3/14 , B64C23/00
CPC分类号： B64C3/14 , B64C30/00 , B64C2003/149 , B64F5/00 , G06F17/5095 , Y02T50/12
摘要： In designing supersonic aircrafts, a method of designing a natural laminar flow wing is provided which reduces friction drag by delaying boundary layer transition under flight conditions of actual aircrafts. A target Cp distribution on wing upper surface, suited to natural laminarization in which boundary layer transition is delayed rearward in desired Reynolds number states, is defined by a functional type having as coefficients parameters depending on each spanwise station, a sensitivity analysis employing a transition analysis method is applied to the parameters, and a search is performed for the optimum combination of parameters to delay transition rearward.
摘要翻译：在设计超音速飞机，提供了一种设计自然层流机翼的方法，该方法通过延迟实际飞机条件下边界层过渡飞行降低摩擦阻力。上翼上表面上的目标CP分布，适合于天然层流，其中边界层转变在所需的雷诺数状态向后延迟，由具有作为系数的参数取决于每个翼展站的功能类型定义的，敏感性分析采用过渡分析方法被应用到的参数，并执行搜索有关参数以延迟过渡向后的最佳组合。

9. 发明公开

EP1558493A2 SLOTTED AIRCRAFT WING 有权转让
标题翻译： SLOT翼飞机
公开(公告)号：EP1558493A2
公开(公告)日：2005-08-03
申请号：EP03799834.1
申请日：2003-10-09
申请人： The Boing Company , The United States of America, represented by the Administrator of the National Aeronautics and Space Administration (NASA)
发明人： GEA, Lie-Mine , McLEAN, James, D. , WITKOWSKI, David, P. , KRIST, Steven, E. , CAMPBELL, Richard, L. , VASSBERG, John, C.
IPC分类号： B64C3/10
CPC分类号： B64C3/28 , B64C21/02 , B64C2003/149 , B64C2230/20 , Y02T50/12 , Y02T50/166
摘要： An aircraft wing includes a leading airfoil element (36) and a trailing airfoil element (38). At least one slot (12) is defined by the wing during at least one transonic condition of the wing. The slot (12) may either extend spanwise along only a portion of the wingspan, or it may extend spanwise along the entire wingspan. In either case, the slot (12) allows a portion of the air flowing along the lower surface (18) of the leading airfoil element (36) to split and flow over the upper surface (20) of the trailing airfoil element (38) so as to achieve a performance improvement in the transonic condition.

10. 发明公开

EP0047319A1 IMPROVEMENTS IN AEROFOILS 失效
标题翻译：改进的翅膀。
公开(公告)号：EP0047319A1
公开(公告)日：1982-03-17
申请号：EP81901905.0
申请日：1981-03-13
申请人： The Secretary of State for Defence in Her Britannic Majesty's Government of the United Kingdom of Great Britain and
发明人： ASHILL, Patrick Ralph , TAYLOR, Cyril Richard , WOOD, Ruth Frances , TREADGOLD, Desmond Arthur
IPC分类号： B64C3
CPC分类号： B64C3/14 , B64C2003/149
摘要： Un profil de voilure utilise sur un avion dans lequel le nombre de mach du dessin de la section est 0,7-0,77 et un rapport de la corde d'epaisseur d'environ 0,14, avec t/c max en avant de la mi-corde, une courbure minimum de la surface superieure a ou en avant de t/c max, et un rayon et une cambrure du bord d'attaque telle que la crete locale M soit obtenue en avant du 10% de la corde et l'ecoulement supersonique soit maintenu en arriere de 40% de la corde, lorsqu'il peut se terminer en un choc faible. La surface inferieure possede une cambrure arriere et est concue pour rendre la sustentation maximum mais avec une distribution qui permette d'altenaer le coefficient du moment de tangage de la section dans sa totalite.

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