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1. 发明专利

DE102008035423A1 未知
公开(公告)号：DE102008035423A1
公开(公告)日：2010-02-04
申请号：DE102008035423
申请日：2008-07-30
申请人： AIRBUS UK LTD , EADS DEUTSCHLAND GMBH
发明人： BAUER KARIN , WOOD NORMAN , RIEDL XAVER , WAGNER ROLAND
IPC分类号： G01M9/06 , G01F1/28 , G01P5/01

2. 发明申请

WO2009106869A2 AERODYNAMIC STRUCTURE WITH SERIES OF SHOCK BUMPS 审中-公开
标题翻译：具有冲击波段的气动结构
公开(公告)号：WO2009106869A2
公开(公告)日：2009-09-03
申请号：PCT/GB2009050150
申请日：2009-02-17
申请人： AIRBUS UK LTD , WOOD NORMAN
发明人： WOOD NORMAN
IPC分类号： B64C23/04
CPC分类号： B64C23/04 , B64C2003/148 , B64C2003/149 , Y02T50/12
摘要： An aerodynamic structure comprising a series of shock bumps extending from its surface. The shock bumps are distributed along a line with a smaller mean angle of sweep than an unperturbed shock which would form adjacent to the surface during transonic movement of the structure in the absence of the shock bumps. Instead of being distributed along the line of the unperturbed shock, the shock bumps are distributed along a line which is less swept than the mean angle of sweep of the unperturbed shock. When the structure is moved at a transonic speed; a shock forms adjacent to its surface and the shock bumps perturb the shock so as to reduce its angle of sweep.
摘要翻译：包括从其表面延伸的一系列冲击凸起的空气动力学结构。撞击突起沿着具有较小的平均扫掠角度的线分布，而不是在没有冲击凸起的结构的跨音速运动期间将形成为与表面相邻的不受干扰的冲击。沿着不受扰动的冲击线的分布而不是沿着不受干扰的冲击的平均扫掠角度的扫描线的分布。当结构以跨音速移动时; 在其表面附近产生冲击，并且冲击震荡扰乱冲击，以减小其扫掠角度。

3. 发明申请

WO2009106873A3 SHOCK BUMP ARRAY 审中-公开
标题翻译：冲击阵列
公开(公告)号：WO2009106873A3
公开(公告)日：2009-10-22
申请号：PCT/GB2009050154
申请日：2009-02-17
申请人： AIRBUS UK LTD , WOOD NORMAN
发明人： WOOD NORMAN
IPC分类号： B64C23/04
CPC分类号： B64C23/04
摘要： An aerodynamic structure comprising an array shock bumps (3, 10) extending from its surface, the array comprising: a first series of shock bumps; and one or more shock bumps positioned aft of the first series. Preferably at least one of the one or more shock bumps positioned aft of the first series is offset so that it is not positioned directly aft of any of the shock bumps in the first series. By providing an array of shock bumps instead of a single line, the first series of shock bumps and the one or more shock bumps positioned aft of the first series can be positioned to modify the structure of a shock which forms under a different respective condition.
摘要翻译：一种空气动力学结构，包括从其表面延伸的阵列冲击凸起（3,10），所述阵列包括：第一系列的冲击凸块; 以及位于第一系列后方的一个或多个撞击凸起。优选地，位于第一系列后面的一个或多个冲击凸起中的至少一个偏移，使得其不位于第一系列中的任何冲击凸块的直接后方。通过提供一组冲击凸块而不是一条线，可以将第一系列的冲击和第一系列后面的一个或多个冲击凸起定位，以改变在不同的相应条件下形成的冲击的结构。

4. 发明专利

CA2728368A1 OSCILLATING ELEMENT SENSOR FOR DETECTING BOUNDARY LAYER TRANSITION1 未知
公开(公告)号：CA2728368A1
公开(公告)日：2010-02-04
申请号：CA2728368
申请日：2009-07-27
申请人： AIRBUS OPERATIONS LTD , EADS DEUTSCHLAND GMBH
发明人： WOOD NORMAN , BAUER KARIN , RIEDL XAVER , WAGNER ROLAND
IPC分类号： G01H3/10 , G01H13/00
摘要： The invention relates to a flow state sensor (10) for detecting a flow state at a body (16) that may be impinged on by a flow (12). A flow state sensor (10) that is of a simple construction and that is simple to evaluate is characterised in accordance with the invention by at least one frequency detecting device (20) for detecting at least one predefined frequency characteristic of the flow state. The frequency detecting device (20) has at least one oscillation element (22; 22a, 22b, 22c) excitable to resonant oscillatory movement (30) by a flow (12) and having a resonant frequency or natural frequency adapted to the predefined frequency characteristic, especially corresponding to the predefined frequency characteristic. Uses of the flow state sensor (10) in a flow measuring device (62) and in a flow measuring method, and an advantageous production method for the flow state sensor (10) are also proposed.

5. 发明专利

BRPI0916553A2 sensor de elemento oscilante para detectar transição de camada limite 未知
公开(公告)号：BRPI0916553A2
公开(公告)日：2015-11-10
申请号：BRPI0916553
申请日：2009-07-27
申请人： AIRBUS OPERATIONS LTD , EADS DEUTSCHLAND GMBH
发明人： BAUER KARIN , WOOD NORMAN , WAGNER ROLAND , RIEDL XAVER
IPC分类号： G01H3/10 , G01H13/00

6. 发明申请

WO2009106871A2 AERODYNAMIC STRUCTURE WITH NON-UNIFORMLY SPACED SHOCK BUMPS 审中-公开
标题翻译：具有非均匀空间冲击波的空气动力学结构
公开(公告)号：WO2009106871A2
公开(公告)日：2009-09-03
申请号：PCT/GB2009050152
申请日：2009-02-17
申请人： AIRBUS UK LTD , WOOD NORMAN
发明人： WOOD NORMAN
IPC分类号： B64C23/04
CPC分类号： B64C23/04 , B64C2003/148 , B64C2003/149 , Y02T50/12
摘要： An aerodynamic structure comprising a series of shock bumps extending from its surface. The shock bumps are distributed across the structure with a non-uniform spacing between the centres and/or edges of adjacent bumps. The non-uniform spacing between the bumps can be arranged to give maximum wave drag alleviation for the minimum number of bumps as a function of the shock strength across the span, leading to minimum wing weight penalties for a given amount of wave drag alleviation.
摘要翻译：包括从其表面延伸的一系列冲击凸起的空气动力学结构。冲击突起分布在结构上，在相邻凸块的中心和/或边缘之间具有不均匀的间隔。凸块之间的不均匀间距可以被布置成为跨越跨度的冲击强度的函数给出最小数量的凸起的最大波浪减轻，导致给定量的波浪减轻的最小翼重惩罚。

7. 发明专利

CA2728368C OSCILLATING ELEMENT SENSOR FOR DETECTING BOUNDARY LAYER TRANSITION1 未知
公开(公告)号：CA2728368C
公开(公告)日：2015-06-23
申请号：CA2728368
申请日：2009-07-27
申请人： AIRBUS OPERATIONS LTD , EADS DEUTSCHLAND GMBH
发明人： WOOD NORMAN , BAUER KARIN , RIEDL XAVER , WAGNER ROLAND
IPC分类号： G01H3/10 , G01H13/00
摘要： The invention relates to a flow state sensor (10) for detecting a flow state at a body (16) that may be impinged on by a flow (12). A flow state sensor (10) that is of a simple construction and that is simple to evaluate is characterised in accordance with the invention by at least one frequency detecting device (20) for detecting at least one predefined frequency characteristic of the flow state. The frequency detecting device (20) has at least one oscillation element (22; 22a, 22b, 22c) excitable to resonant oscillatory movement (30) by a flow (12) and having a resonant frequency or natural frequency adapted to the predefined frequency characteristic, especially corresponding to the predefined frequency characteristic. Uses of the flow state sensor (10) in a flow measuring device (62) and in a flow measuring method, and an advantageous production method for the flow state sensor (10) are also proposed.

8. 发明申请

WO2009106872A3 AERODYNAMIC STRUCTURE WITH ASYMMETRICAL SHOCK BUMP 审中-公开
标题翻译：不对称冲击波的空气动力学结构
公开(公告)号：WO2009106872A3
公开(公告)日：2009-10-22
申请号：PCT/GB2009050153
申请日：2009-02-17
申请人： AIRBUS UK LTD , WOOD NORMAN
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 ofthe structure.
摘要翻译：包括从其表面延伸的冲击凸起（3）的气动结构。撞击不对称关于不对称平面，并且不对称平面：通过冲击凸块的中心（6），平行于结构上的空气流动的主要方向，并且以直角延伸到表面的结构。

9. 发明申请

WO2009106870A3 SHOCK BUMP 审中-公开
标题翻译：冲击波
公开(公告)号：WO2009106870A3
公开(公告)日：2009-10-22
申请号：PCT/GB2009050151
申请日：2009-02-17
申请人： AIRBUS UK LTD , WOOD NORMAN
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.
摘要翻译：包括发散鼻（20）和会聚尾部的冲击突起（10）。尾部具有至少一个具有一对凹入相对侧（22,23）的平面轮廓线。冲击突起提供了具有相对较低阻力的改进形状。此外，尾部的凹形趋向于促进纵向涡流的发展，这可以在某些操作条件下减少冲击诱发的自助餐。

10. 发明专利

AT535786T 未知
公开(公告)号：AT535786T
公开(公告)日：2011-12-15
申请号：AT09785404
申请日：2009-07-27
申请人： AIRBUS OPERATIONS LTD , EADS DEUTSCHLAND GMBH
发明人： WOOD NORMAN , BAUER KARIN , RIEDL XAVER , WAGNER ROLAND
IPC分类号： G01H3/10 , G01H13/00

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