-
公开(公告)号：WO2009138773A1
公开(公告)日：2009-11-19
申请号：PCT/GB2009/050471
申请日：2009-05-06
Applicant: AIRBUS UK LIMITED , MING, Xiao
Inventor： MING, Xiao
CPC classification number: B64C3/28 , B64C3/58 , B64C21/02 , B64C2230/20 , F01D5/145 , Y02T50/166 , Y02T50/673
Abstract: An airfoil (3) comprising a high pressure surface (4); a low pressure surface (5); a leading edge (6) where the high and low pressure surfaces meet at the front of the airfoil; and a trailing edge (7) where the high and low pressure surfaces meet at the back of the airfoil. A porous flow deflector (8) extends from the low pressure surface. The porous flow deflector is attached to the low pressure surface at a position which is closer in a chord-wise sense to the leading edge than to the trailing edge. That is, the percentage chord distance between the leading edge and the position where the flow deflector is attached is less than 50%. The porous flow deflector comprises a plurality of flow deflection members (8) each spaced progressively further from the low pressure surface in a direction away from the low pressure surface, and each flow deflection member is angled down to the rear relative to a local tangent of the low pressure surface. The porous flow deflector deflects air towards the low pressure surface as it passes through the porous flow deflector.
Abstract translation: 包括高压表面（4）的翼型件（3）; 低压表面（5）; 前缘（6），其中高低压表面在翼型的前部相交; 和后缘（7），其中高低压表面在翼型的后部相交。 多孔流向偏转器（8）从低压表面延伸。 多孔流动偏转器在与前缘相比更靠近前缘的位置附接到低压表面。 也就是说，前缘与导流板相连的位置之间的弦弦距离小于50％。 多孔流动偏转器包括多个流动偏转构件（8），每个流动偏转构件（8）在远离低压表面的方向上从低压表面进一步间隔开，并且每个流动偏转构件相对于局部切线 低压表面。 当多孔导流板通过多孔导流板时，空气朝向低压表面偏转。
-
公开(公告)号：WO2009067319A3
公开(公告)日：2009-05-28
申请号：PCT/US2008/081472
申请日：2008-10-28
Applicant: THE BOEING COMPANY , LEE, Robert Michael , EVANS, Brian G.
Inventor： LEE, Robert Michael , EVANS, Brian G.
Abstract: A multi- segment flap fence (106) is incorporated into the wing such that a lower fence structure (202) is attached to the underside of the fixed wing (102), an upper fence structure '(212) is attached to the main flap (108) (e.g., at the outboard end). The two flap segments (202, 212) are configured to slideably articulate with respect to each other when the flap (108) is extended to form a composite flap fence having an area that is substantially equal to the sum of the surface areas of the upper (212) and lower (202) flap fence structures. In one embodiment, the area of the upper fence (212) is less than that of the lower fence (202).
-
公开(公告)号：WO2008097325A2
公开(公告)日：2008-08-14
申请号：PCT/US2007/071237
申请日：2007-06-14
Applicant: LOCKHEED MARTIN CORPORATION , NOVAK, Charlie , BERRY, Owen, T. , HARDIN, Chris, J. , MCALLISTER, Bobby, D.
Inventor： NOVAK, Charlie , BERRY, Owen, T. , HARDIN, Chris, J. , MCALLISTER, Bobby, D.
Abstract: An airfoil for use with an aircraft having an engine positioned such that exhaust from the engine flows under an underside of the airfoil. The airfoil includes an upper surface and a movable control element. The upper surface has a leading edge and a trailing edge. The movable control element is positioned adjacent the trailing edge and is selectively controlled for movement between a first position and a second position. In the first position, the movable control element does not mix fluid flowing over the top of the airfoil with engine exhaust under the airfoil. In the second position, at least some of the fluid flowing over the top of the airfoil mixes under the airfoil with engine exhaust.
Abstract translation: 一种与飞机一起使用的翼型件，其具有定位成使得来自发动机的排气在翼型的下侧流动。 翼型件包括上表面和可移动控制元件。 上表面具有前缘和后缘。 可移动控制元件定位成与后缘相邻，并且被选择性地控制用于在第一位置和第二位置之间移动。 在第一位置，可移动控制元件不将在翼型件顶部流动的流体与在翼型下的发动机排气混合。 在第二位置，流过翼型顶部的至少一些流体在机翼下方与发动机排气混合。
-
公开(公告)号：WO2021053846A1
公开(公告)日：2021-03-25
申请号：PCT/JP2020/005093
申请日：2020-02-10
Applicant: 三菱重工業株式会社
Abstract: 制動力発生装置（１）は、ディフレクタ（３）及びブロッカードア（４）が翼（１０）に対して格納された第１モードと、ディフレクタ（３）の前縁（３ａ）及び後縁（３ｂ）が翼（１０）から離隔され、かつ、ブロッカードア（４）が格納された状態で、ディフレクタ（３）の前縁（３ａ）側の開口部から後縁（３ｂ）側の開口部にわたってクロスフローファン（２）を経て流体が流れる第２流路が形成される第３モードと、ディフレクタ（３）の後縁（３ｂ）が翼（１０）に近接したまま前縁（３ａ）が翼（１０）から離隔され、かつ、ブロッカードア（４）が展開された状態で、ブロッカードア（４）側の開口部（１２ａ）からディフレクタ（３）の前縁（３ａ）側の開口部（１２ｂ）にわたってクロスフローファン（２）を経て流体が流れる第１流路（１２）が形成される第２モードとを有する。
-
5.发明申请
公开(公告)号：WO2009058488A1
公开(公告)日：2009-05-07
申请号：PCT/US2008/076950
申请日：2008-09-19
Applicant: THE BOEING COMPANY , SHMILOVICH, Arvin , YADLIN, Yoram , GREGG, Robert, D., III , CLARK, Roger, W.
Inventor： SHMILOVICH, Arvin , YADLIN, Yoram , GREGG, Robert, D., III , CLARK, Roger, W.
CPC classification number: B64C9/38 , B64C3/58 , B64C7/00 , B64C21/04 , B64C2230/04 , Y02T50/166
Abstract: Lift produced by an airfoil of an aircraft is increased by suppressing fluid detachment from the surface of the airfoil. An engine cowling (102) extends outwardly from the surface of the airfoil that has an exit plane (202) configured for directing exhaust gases toward a rear of the aircraft. Fences (106, 107, 108, 109) extending outwardly from the surface and proximate to the exit plane of the engine cowling are configured to guide the exhaust gases along at least a portion of the airfoil surface, thereby restricting spanwise movement of the gases and increasing the Coanda Effect exhibited by the gases, thereby increasing the amount of lift produced along the surface of the airfoil. Such techniques may be used in short take-off and landing (STOL) aircraft.
Abstract translation: 由飞机的翼型产生的升力通过抑制从翼型的表面的流体分离而增加。 发动机整流罩（102）从具有出口平面（202）的翼型件的表面向外延伸，该出口平面（202）构造成用于将废气引导到飞行器的后部。 从表面向外延伸并靠近发动机整流罩的出口平面的围栏（106,107,108,109）构造成沿着翼面表面的至少一部分引导废气，从而限制气体的翼展运动， 增加气体所展示的附壁效应，从而增加沿翼面表面产生的升力量。 这种技术可以用于短时起飞（STOL）飞机。
-
Patent Agency Ranking
公开(公告)号：WO2006004570B1
公开(公告)日：2006-04-20
申请号：PCT/US2005001350
申请日：2005-01-18
Applicant: NORTHROP GRUMMAN CORP , REYNOLDS ROSS STEVEN , SHULTZ DOUG ELLWOOD
Inventor： REYNOLDS ROSS STEVEN , SHULTZ DOUG ELLWOOD
Abstract: An aircraft motion control mechanism for regulating aircraft motion from a location remote from an aircraft body portion. The aircraft auxiliary control mechanism has at least one control surface support arm connected to and extending from the aircraft body portion, and an auxiliary flow control surface connected to the support arm. By pivotally controlling the movement of the support arm, the auxiliary flow control surface is operative to deflect airflow to regulate orientation of the aircraft. In addition, the auxiliary flow control surface may further deflect the airflow by deflecting about the support arm.
Abstract translation: 一种用于从远离飞机主体部分的位置调节飞机运动的飞机运动控制机构。 飞机辅助控制机构具有至少一个控制表面支撑臂和辅助流动控制表面，所述控制表面支撑臂连接到飞机主体部分并从飞行器主体部分延伸，辅助流动控制表面连接到支撑臂。 通过枢转地控制支撑臂的运动，辅助流动控制表面可操作以偏转气流以调节飞行器的定向。 另外，辅助流动控制表面可以通过围绕支撑臂偏转来进一步偏转气流。
-
公开(公告)号：WO2007117260A3
公开(公告)日：2008-05-22
申请号：PCT/US2006029455
申请日：2006-07-27
Applicant: UNIV SOUTHERN CALIFORNIA , BLACKWELDER RON , PAGE MARK , STAELENS YANN
Inventor： BLACKWELDER RON , PAGE MARK , STAELENS YANN
CPC classification number: B64C9/02 , B64C9/18 , B64C9/32 , B64C9/326 , B64C9/36 , B64C25/16 , B64C2025/003 , B64C2039/105
Abstract: A blended wing body aircraft may include a blended wing configured to house a person, payload and/or cargo within the wing, a surface structure, and an actuator. The actuator may be configured to controllably cause the planar structure to extend downwardly from an underside surface of the wing oriented such that the planar structure forms a sweep angle with the aircraft between -70 and 70 degrees. Substantially each point on the planar structure may be behind a leading edge of the wing and in front of a trailing edge of the wing by at least 5% of the length of the chord of the wing that passes through the point. The actuator may be configured to controllably cause the planar structure to extend downwardly from an underside surface of the wing with an orientation that causes an increase in static pressure ahead of the hinge line of the planar structure and a decrease aft of the hinge line during forward movement of the aircraft, as compared to when the planar structure is not extended. Deployment of all planar structures may increase the aircraft's control pitching moment and/or lift by more than 5 percent as compared to when they are not deployed.
Abstract translation: 混合翼体飞机可以包括配置成容纳机翼内的人，有效载荷和/或货物的混合翼，表面结构和致动器。 致动器可以被配置成可控制地使平面结构从机翼的下侧表面向下延伸，使得平面结构与飞行器在-70度和70度之间形成一个扫掠角。 基本上，平面结构上的每个点可以在机翼的前缘的后面，并且在机翼的后缘的前方是穿过该点的翼的弦的长度的至少5％。 致动器可以被配置成可控制地使平面结构从机翼的下侧表面向下延伸，其方向使得平面结构的铰链线之前的静压增加，并且在向前的铰链线的后方减小 与平面结构未延伸相比，飞机的运动。 所有平面结构的部署可能会将飞机的控制俯仰力矩和/或升力与未部署时相比增加5％以上。
-
公开(公告)号：WO2004094227A1
公开(公告)日：2004-11-04
申请号：PCT/CA2004/000581
申请日：2004-04-19
Applicant: WEIR, Frederick, C.
Inventor： WEIR, Frederick, C.
IPC: B64C3/58
CPC classification number: B64C21/02 , B64C39/08 , B64C39/10 , Y02T50/12 , Y02T50/166
Abstract: The present invention relates to an apparatus for reducing drag of an aircraft utilized in combination with an aircraft surface (12), where the local airflow has an upward momentum due to the free air stream being deflected upward by the aircraft surface. The apparatus comprises an ancillary airfoil (1) having a cambered top surface (10), a leading edge (14) and a trailing edge (17) and a generally concave louver surface (9); mounting members for mounting the ancillary airfoil above the aircraft surface (12) in a spaced apart manner and at a positive angle of attack with respect to the local airflow (3); and an expansion chamber (11) formed between the lower surface (9) of the ancillary airfoil and the aircraft surface (12). The expansion chamber (11) is located where a distance (13) between the louver surface of the ancillary airfoil and the aircraft surface gradually increases.
Abstract translation: 本发明涉及一种用于减少与飞行器表面（12）结合使用的飞行器的阻力的装置，其中局部气流由于空气流被飞机表面向上偏转而具有向上的动量。 该装置包括具有弧形顶表面（10），前缘（14）和后缘（17）和大致凹形百叶窗表面（9）的辅助翼型件（1）。 安装构件，用于以相对于局部气流（3）以间隔开的方式并且以正的迎角将翼型件安装在飞行器表面（12）上方。 以及形成在辅助翼型件的下表面（9）和飞行器表面（12）之间的膨胀室（11）。 膨胀室（11）位于辅助翼型件的百叶窗表面和飞行器表面之间的距离（13）逐渐增加。
-
公开(公告)号：WO00063071A1
公开(公告)日：2000-10-26
申请号：PCT/FR2000/000864
申请日：2000-04-06
CPC classification number: B64C3/14 , B64C3/58 , B64C2003/145 , Y02T50/12
Abstract: The present invention relates to an aerodynamic surface (1) such as a wing, empennage, angle of drift, nacelle pylon etc. for an aircraft. According to the invention, said aerodynamic surface (1) comprises at least one lightening hole (7) pertaining to the trailing edge of the underwing; at least one hinged baffle (8) that can be mounted in the lightening hole (7) of the underwing, whereby the chord thereof is equal to a several hundredths of the chord (C) of the aerodynamic surface (1); and means for actuating the moveable baffle (8) so that it can rotate around the hinge line (9).
Abstract translation: 本发明涉及一种用于飞机的空气动力学表面（1），例如翼，尾翼，漂移角，机舱塔等。 根据本发明，所述空气动力学表面（1）包括至少一个与所述底翼的后缘相关的减重孔（7）; 至少一个铰链挡板（8），其可以安装在所述下摆的减光孔（7）中，由此所述弦线等于所述空气动力学表面（1）的弦（C）的几百分之一。 以及用于致动可移动挡板（8）使得其能够围绕铰链线（9）旋转的装置。
-
公开(公告)号：WO99050141A1
公开(公告)日：1999-10-07
申请号：PCT/US1999/006753
申请日：1999-03-29
CPC classification number: B64C3/58 , B64C23/06 , Y02T50/162
Abstract: A deployable flow control device for a flow surface (10) over which fluid having a fluid boundary layer flows which fluid boundary layer exhibits certain dynamics is disclosed. The deployable flow control device comprises a flow effector (20) which is movably attached to a housing (12) which is attachable, either initially or retrofitably, to a flow surface (10). The flow effector (20) is deployed into and retracted out of the boundary layer on the flow surface (10) and thereby controls the boundary dynamics. Devices (including devices utilizing a sealable, flexible element (60)) operably connect to the flow effector (20) and deploy and retract it. The sealable, flexible element (60) has two elastic states defined as quiescent and deformed such that, when the sealable, flexible element (60) is utilized, the flow effector (20) is deployed into and retracted out of the fluid boundary layer based upon the elastic state of the sealable, flexible element (60).
Abstract translation: 公开了一种用于流动表面（10）的可展开的流量控制装置，流体边界层流过具有流体边界层的流体，流体边界层表现出某种动态。 可展开的流量控制装置包括流动执行器（20），其可移动地附接到壳体（12），壳体（12）可初始地或可更新地附接到流动表面（10）。 流动执行器（20）展开到流动表面（10）上的边界层中并从中缩出，从而控制边界动力学。 装置（包括利用可密封的柔性元件（60）的装置）可操作地连接到流动执行器（20）并且展开和缩回它。 可密封的柔性元件（60）具有定义为静止和变形的两个弹性状态，使得当使用可密封的柔性元件（60）时，流动执行器（20）基于流体边界层展开和退出 在可密封的柔性元件（60）的弹性状态下。
-
-
-
-
-
-
-
-
-
Search Results
23
records
(took 0.006 seconds)
