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    System, apparatus, and method for redistributing forces to meet performance goals and shock wave disturbance constraints
    3.
    发明申请
    System, apparatus, and method for redistributing forces to meet performance goals and shock wave disturbance constraints 有权
    用于重新分配力以满足性能目标和冲击波干扰约束的系统，装置和方法

    公开(公告)号：US20050116108A1

    公开(公告)日：2005-06-02

    申请号：US10714276

    申请日：2003-11-14

    申请人： John Morgenstern ,  James Bach ,  Alan Arslan

    发明人： John Morgenstern ,  James Bach ,  Alan Arslan

    IPC分类号： B64C1/00 ,  B64C30/00 ,  B64D27/18 ,  B64C1/38

    CPC分类号： B64C1/0009 ,  B64C30/00 ,  B64C2001/0045 ,  B64D27/18 ,  Y02T50/12 ,  Y02T50/44

    摘要： A system and method for configuring an aircraft for low sonic boom supersonic flight conditions includes redistributing lift of a wing by configuring the wing with one or more areas of far-field expansion ahead of areas of far-field compression. An equivalent area distribution goal curve is scaled to account for the equivalent area reduction due to excursions below to goal curve. A relaxed constraint allows the equivalent area distribution of the aircraft to be at or below the equivalent area distribution goal curve to enable multiple parameters to be configured to meet the equivalent area distribution constraint, as well as other constraints. The system and method can be adapted to aid in the design of any type of vehicle whose surfaces are subject to supersonic fluid flow, especially to reduce sonic boom.

    摘要翻译： 用于配置用于低声波超音速飞行条件的飞行器的系统和方法包括通过在远场压缩区域之前的远场扩展的一个或多个区域配置机翼来重新分配机翼的升力。 将等效区域分布目标曲线缩放以考虑由于低于目标曲线的偏移所引起的等效面积减小。 轻松的约束允许飞机的等效面积分布处于等于或低于等效区域分布目标曲线，以使得可以配置多个参数以满足等效面积分布约束以及其他约束。 该系统和方法可以适用于任何类型的车辆的设计，其表面经受超音速流体流动，特别是减少声波爆震。

    WING EMPLOYING LEADING EDGE FLAPS AND WINGLETS TO ACHIEVE IMPROVED AERODYNAMIC PERFORMANCE
    4.
    发明申请
    WING EMPLOYING LEADING EDGE FLAPS AND WINGLETS TO ACHIEVE IMPROVED AERODYNAMIC PERFORMANCE 失效
    引领领先优势的翅膀和手段，以实现改进的航空动力性能

    公开(公告)号：US20070262207A1

    公开(公告)日：2007-11-15

    申请号：US11059756

    申请日：2005-02-16

    申请人： John Morgenstern ,  Alan Arslan

    发明人： John Morgenstern ,  Alan Arslan

    IPC分类号： B64C3/50

    CPC分类号： B64C3/16 ,  B64C5/02 ,  B64C5/04 ,  B64C5/12 ,  B64C7/00 ,  B64C9/22 ,  B64C9/32 ,  B64C9/323 ,  B64C9/36 ,  B64C23/04 ,  B64C30/00 ,  B64C39/12 ,  Y02T50/12 ,  Y02T50/32 ,  Y02T50/44

    摘要： A wing for use on a supersonic aircraft that includes an inboard section a central section of the wing outboard of the inboard portion, and an outboard section. The outboard section can be a winglet oriented anhedrally relative to a lateral axis of the supersonic aircraft. Leading edge segments on the inboard section, central section and outboard winglet may have mounted thereon leading-edge flaps. These flaps are adjusted by a control system operable to reposition the leading-edge flaps in order to improve the aerodynamic performance of the supersonic aircraft. This winglet promotes sonic boom minimization. Further, the wing tip anhedral allows greater inboard dihedral. This effectively pushes lift aft for sonic boom and control purposes while minimizing the movement of control surfaces.

    摘要翻译： 在超音速飞机上使用的机翼，其包括内侧部分的内侧部分，内侧部分的翼外侧的中心部分和外侧部分。 外侧部分可以是相对于超音速飞行器的横向轴线定向的小翼。 内侧部分，中央部分和外侧小翼上的前缘部分可以安装在前缘翼片上。 这些翼片通过可操作以重新定位前缘翼片的控制系统来调节，以便改善超音速飞机的空气动力学性能。 这个小翼促进了声波的最小化。 此外，翼尖侧面可以更大的内侧二面体。 这样可以有效地将升降机推向震动和控制目的，同时最小化控制面的移动。

    Aircraft lift device for low sonic boom
    5.
    发明申请
    Aircraft lift device for low sonic boom 有权
    飞机升降装置用于低声波

    公开(公告)号：US20050045763A1

    公开(公告)日：2005-03-03

    申请号：US10651410

    申请日：2003-08-29

    申请人： John Morgenstern ,  Alan Arslan

    发明人： John Morgenstern ,  Alan Arslan

    IPC分类号： B64C9/24 ,  B64C30/00 ,  B64C27/22

    CPC分类号： B64C30/00 ,  B64C9/24 ,  Y02T50/32 ,  Y02T50/44

    摘要： An aircraft lift device comprises a strake capable of coupling to an aircraft fuselage and extending to a leading edge of a wing. The strake has a leading edge. The lift device further comprises a leading-edge flap coupled to the strake leading edge.

    摘要翻译： 飞机提升装置包括能够联接到飞行器机身并延伸到机翼的前缘的行星架。 这条线有一个前沿。 升降装置进一步包括连接到前缘的前缘翼片。

    Adjoint-based design variable adaptation
    6.
    发明申请
    Adjoint-based design variable adaptation 审中-公开
    基于相关的设计变量适应

    公开(公告)号：US20060058985A1

    公开(公告)日：2006-03-16

    申请号：US10930375

    申请日：2004-08-31

    申请人： Alan Arslan ,  John Morgenstern ,  Josiah Jordan

    发明人： Alan Arslan ,  John Morgenstern ,  Josiah Jordan

    IPC分类号： G06F17/10

    CPC分类号： G06F17/5095 ,  G06F2217/06 ,  G06F2217/08

    摘要： A method for determining an optimum design includes determining an initial field solution for a design configuration based on an initial set of design variables; determining an adjoint solution to the field solution; determining the regions of interest on the design configuration based on magnitudes and/or gradients of the adjoint solution; and establishing design variables at the regions of interest.

    摘要翻译： 一种用于确定最佳设计的方法包括：基于初始设计变量集确定用于设计配置的初始场解; 确定现场解决方案的伴随解决方案; 基于伴随解的幅度和/或梯度来确定设计配置上的感兴趣区域; 并在感兴趣的地区建立设计变量。

    Area ruling for vertical stabilizers
    7.
    发明申请
    Area ruling for vertical stabilizers 审中-公开
    垂直稳定器的面积统计

    公开(公告)号：US20050116107A1

    公开(公告)日：2005-06-02

    申请号：US10706670

    申请日：2003-11-11

    申请人： John Morgenstern ,  Alan Arslan ,  Garret Moose

    发明人： John Morgenstern ,  Alan Arslan ,  Garret Moose

    IPC分类号： B64C1/38 ,  B64C3/38

    CPC分类号： B64C1/38 ,  B64C3/38

    摘要： A vertical stabilizer is configured to minimize the rate of change of cross-sectional area of the vehicle or device to which the vertical stabilizer is mounted. One or more “waisted” areas can be included at the tip and/or the root of the vertical stabilizers, as well as over the distance from tip to root of the vertical stabilizer. In some situations, a strake is mounted on the vehicle or device, such as an aircraft, and the vertical stabilizer is mounted to the tip of the strake. The strake can also be area ruled with one or more “waisted” sections at the juncture of the vertical stabilizer. Applying area ruling to the vertical stabilizer helps to further reduce the drag of the vehicle or device.

    摘要翻译： 垂直稳定器构造成使安装有垂直稳定器的车辆或装置的横截面面积的变化率最小化。 一个或多个“腰围”区域可以包括在垂直稳定器的尖端和/或根部以及垂直稳定器的尖端到根部的距离处。 在某些情况下，在车辆或装置（例如飞行器）上安装一个行走架，并且垂直的稳定器安装在该行李架的顶端。 在垂直稳定器的接合处，也可以在一个或多个“腰部”区域上划定该区域。 对垂直稳定器施加面积调整有助于进一步减少车辆或设备的阻力。

    SUPERSONIC AIRCRAFT WITH CHANNEL RELIEF CONTROL
    8.
    发明申请
    SUPERSONIC AIRCRAFT WITH CHANNEL RELIEF CONTROL 有权
    具有通道救援控制的超级飞机

    公开(公告)号：US20050103929A1

    公开(公告)日：2005-05-19

    申请号：US10696796

    申请日：2003-10-30

    申请人： Ming Chang ,  Victor Meza ,  John Morgenstern ,  Alan Arslan

    发明人： Ming Chang ,  Victor Meza ,  John Morgenstern ,  Alan Arslan

    IPC分类号： B64C3/16 ,  B64C5/02 ,  B64C9/00 ,  B64C13/50 ,  B64C23/04 ,  B64C30/00 ,  B64C39/06

    CPC分类号： B64C23/04 ,  B64C3/16 ,  B64C5/02 ,  B64C9/00 ,  B64C13/503 ,  B64C30/00 ,  B64C39/068 ,  Y02T50/12 ,  Y02T50/32

    摘要： A supersonic aircraft comprises a fuselage extending forward and aft along a longitudinal axis, the fuselage having a lower surface and an upper surface, a highly swept low aspect ratio wing coupled to the fuselage and having a forward leading edge and an aft trailing edge, an effector flap coupled to the wing trailing edge, and a tail empennage. The tail empennage is coupled to the fuselage aft of the wing on the fuselage upper surface in a position high relative to the wing. The tail empennage forms a channel region subject to complex shock patterns at transonic conditions. The aircraft further comprises an effector coupled to the tail empennage and a controller coupled to the effector flaps and the effectors. The controller further comprises a control process that reduces drag through channel relief by deflecting both the effector flap down and the effector up.

    摘要翻译： 超音速飞机包括沿纵向轴线向前和向后延伸的机身，机身具有下表面和上表面，高度扫掠的低纵横比翼连接到机身并具有前向前缘和后后缘， 耦合到翼后缘的效应翼，以及尾翼。 尾翼尾翼在机身上表面的机翼后部相对于机翼高度位置耦合。 尾翼在跨音速条件下形成了复杂的震动模式的通道区域。 飞行器还包括耦合到尾翼的效应器和耦合到效能翼片和效应器的控制器。 控制器还包括控制过程，该过程通过使效应翼向下偏转和向上升高而减小通过通道释放的阻力。

    Methods for incorporating area rules surfaces in a supersonic aircraft
    10.
    发明申请
    Methods for incorporating area rules surfaces in a supersonic aircraft 失效
    在超音速飞行器中引入面积规则曲面的方法

    公开(公告)号：US20050224640A1

    公开(公告)日：2005-10-13

    申请号：US11078632

    申请日：2005-03-11

    申请人： John Morgenstern ,  Alan Arslan ,  Garret Moose

    发明人： John Morgenstern ,  Alan Arslan ,  Garret Moose

    IPC分类号： B64C1/38 ,  B64C3/38

    CPC分类号： B64C30/00

    摘要： A vertical stabilizer is configured to minimize the rate of change of cross-sectional area distribution of the vehicle or device to which the vertical stabilizer is mounted. One or more “waisted” areas can be included at the tip and/or the root of the vertical stabilizers, as well as over the distance from tip to root of the vertical stabilizer. In some situations, a strake is mounted on the vehicle or device, such as an aircraft, and the vertical stabilizer is mounted to the tip of the strake. The strake can also be area ruled with one or more “waisted” sections at the juncture of the vertical stabilizer. Applying area ruling to the vertical stabilizer helps to further reduce the drag of the vehicle or device.

    摘要翻译： 垂直稳定器构造成使安装有垂直稳定器的车辆或装置的横截面积分布的变化率最小化。 一个或多个“腰围”区域可以包括在垂直稳定器的尖端和/或根部以及垂直稳定器的尖端到根部的距离处。 在某些情况下，在车辆或装置（例如飞行器）上安装一个行走架，并且垂直的稳定器安装在该行李架的顶端。 在垂直稳定器的接合处，也可以在一个或多个“腰部”区域上划定该区域。 对垂直稳定器施加面积调整有助于进一步减少车辆或设备的阻力。