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    Weight-optimizing internally pressurized composite-body aircraft fuselages having near-elliptical cross sections
    1.
    发明授权
    Weight-optimizing internally pressurized composite-body aircraft fuselages having near-elliptical cross sections 有权
    具有近椭圆截面的重量优化内加压复合体飞机机身

    公开(公告)号：US08292226B2

    公开(公告)日：2012-10-23

    申请号：US12624322

    申请日：2009-11-23

    申请人： Mithra M. K. V. Sankrithi ,  Kevin Retz

    发明人： Mithra M. K. V. Sankrithi ,  Kevin Retz

    IPC分类号： B64C1/06

    CPC分类号： B64C1/061 ,  B64C1/068 ,  B64C1/08 ,  B64C2001/0045 ,  B64C2001/0072 ,  B64C2001/0081 ,  Y02T50/12 ,  Y02T50/43

    摘要： A method for minimizing the weight of an internally pressurized aircraft fuselage of a type that includes an elongated tubular shell having a near-elliptical cross-section with a radius R(φ)- and a curvature Curv(φ), where φ is a roll elevation angle of the shell, includes tailoring at least one structural attribute of the shell as a function of at least one of the elevation angle φ, R(φ) and Curv(φ) so as to reduce the weight of the fuselage relative to an identical fuselage shell in which the same at least one structural attribute has not been so tailored.

    摘要翻译： 一种用于最小化内部加压的飞行器机身的重量的方法，其包括具有半径R（＆phgr）的近椭圆形横截面的细长管状壳体和曲率Curv（＆phgr），其中， 是壳的卷轴仰角，包括作为至少一个仰角＆phgr; R（＆phgr;）和Curv（＆phgr）的函数来调整壳的至少一个结构属性，以便减小重量 的机身相对于相同的机身外壳，其中相同的至少一个结构属性尚未如此定制。

    Weight optimized pressurizable aircraft fuselage structures having near elliptical cross sections
    2.
    发明授权
    Weight optimized pressurizable aircraft fuselage structures having near elliptical cross sections 有权
    重量优化的加压飞机机身结构具有近椭圆截面

    公开(公告)号：US07621482B2

    公开(公告)日：2009-11-24

    申请号：US11273966

    申请日：2005-11-15

    申请人： Mithra M. K. V. Sankrithi ,  Kevin Retz

    发明人： Mithra M. K. V. Sankrithi ,  Kevin Retz

    IPC分类号： B64C1/06

    CPC分类号： B64C1/061 ,  B64C1/08 ,  B64C2001/0045 ,  B64C2001/0072 ,  B64C2001/0081 ,  Y02T50/12 ,  Y02T50/43

    摘要： An aircraft fuselage includes a tubular shell having a centerline axis, opposite ends, and a cross-section having a radius R(φ), where φ is the angular coordinate of a cylindrical coordinate system, a curvature Curv(φ), where Curv(φ) is the inverse of a local radius of curvature of a surface of the shell, and a circumferential shape that varies radially by no more than ±7% from that of an elliptical cross-section at substantially every station along the centerline axis between the nose and tail ends thereof. The weight of the shell is minimized by “tailoring,” i.e., optimizing, at least one structural attribute, expressed as a function of φ, associated with every element of the shell, such that the weight of the shell required to react a design load incident thereon is less than that required to react the same design load, but wherein the same structural attribute has not been so tailored.

    摘要翻译： 飞机机身包括具有中心线轴线，相对端部和具有半径R（phi）的横截面的管状壳体，其中，phi是圆柱坐标系的角坐标，曲率Curv（phi），其中Curv（ phi）是壳体的表面的局部曲率半径的倒数，并且圆周形状沿着沿着中心线轴线的基本上每个站处的椭圆形截面的径向变化不超过±7％ 鼻子和尾端。 通过与外壳的每个元件相关联的“定制”，即优化至少一个表示为与phi的函数的结构属性的至少一个结构属性，使得壳体的重量最小化，使得反应设计负载所需的壳的重量 其上的事件小于反应相同设计负载所需的事件，但是其中相同的结构属性尚未如此定制。

    Weight-Optimizing Internally Pressurized Composite-Body Aircraft Fuselages Having Near-Elliptical Cross Sections
    3.
    发明申请
    Weight-Optimizing Internally Pressurized Composite-Body Aircraft Fuselages Having Near-Elliptical Cross Sections 有权
    重量优化具有近椭圆截面的内部加压复合体飞机机身

    公开(公告)号：US20100200697A1

    公开(公告)日：2010-08-12

    申请号：US12624322

    申请日：2009-11-23

    申请人： Mithra M.K.V. Sankrithi ,  Kevin Retz

    发明人： Mithra M.K.V. Sankrithi ,  Kevin Retz

    IPC分类号： B64C1/00

    CPC分类号： B64C1/061 ,  B64C1/068 ,  B64C1/08 ,  B64C2001/0045 ,  B64C2001/0072 ,  B64C2001/0081 ,  Y02T50/12 ,  Y02T50/43

    摘要： A method for minimizing the weight of an internally pressurized aircraft fuselage of a type that includes an elongated tubular shell having a near-elliptical cross-section with a radius R(φ)- and a curvature Curv(φ), where φ is a roll elevation angle of the shell, includes tailoring at least one structural attribute of the shell as a function of at least one of the elevation angle φ, R(φ) and Curv(φ) so as to reduce the weight of the fuselage relative to an identical fuselage shell in which the same at least one structural attribute has not been so tailored.

    摘要翻译： 一种用于最小化内部加压的飞行器机身的重量的方法，其包括具有半径R（＆phgr）的近椭圆形横截面的细长管状壳体和曲率Curv（＆phgr），其中， 是壳的卷轴仰角，包括作为至少一个仰角＆phgr; R（＆phgr;）和Curv（＆phgr）的函数来调整壳的至少一个结构属性，以便减小重量 的机身相对于相同的机身外壳，其中相同的至少一个结构属性尚未如此定制。

    Weight optimized pressurizable aircraft fuselage structures having near elliptical cross sections
    4.
    发明申请
    Weight optimized pressurizable aircraft fuselage structures having near elliptical cross sections 有权
    重量优化的加压飞机机身结构具有近椭圆截面

    公开(公告)号：US20070108347A1

    公开(公告)日：2007-05-17

    申请号：US11273966

    申请日：2005-11-15

    申请人： Mithra Sankrithi ,  Kevin Retz

    发明人： Mithra Sankrithi ,  Kevin Retz

    IPC分类号： B64C1/00

    CPC分类号： B64C1/061 ,  B64C1/08 ,  B64C2001/0045 ,  B64C2001/0072 ,  B64C2001/0081 ,  Y02T50/12 ,  Y02T50/43

    摘要： An aircraft fuselage includes a tubular shell having a centerline axis, opposite ends, and a cross-section having a radius R(φ), where φ is the angular coordinate of a cylindrical coordinate system, a curvature Curv(φ), where Curv(φ) is the inverse of a local radius of curvature of a surface of the shell, and a circumferential shape that varies radially by no more than ±7% from that of an elliptical cross-section at substantially every station along the centerline axis between the nose and tail ends thereof. The weight of the shell is minimized by “tailoring,” i.e., optimizing, at least one structural attribute, expressed as a function of φ, associated with every element of the shell, such that the weight of the shell required to react a design load incident thereon is less than that required to react the same design load, but wherein the same structural attribute has not been so tailored.

    摘要翻译： 飞机机身包括具有中心线轴线，相对端部和具有半径R（phi）的横截面的管状壳体，其中，phi是圆柱坐标系的角坐标，曲率Curv（phi），其中Curv（ phi）是壳体的表面的局部曲率半径的倒数，并且圆周形状沿着沿着中心线轴线的基本上每个站处的椭圆形截面的径向变化不超过±7％ 鼻子和尾端。 通过与外壳的每个元件相关联的“定制”，即优化至少一个表示为与phi的函数的结构属性的至少一个结构属性，使得壳体的重量最小化，使得反应设计负载所需的壳的重量 其上的事件小于反应相同设计负载所需的事件，但是其中相同的结构属性尚未如此定制。

    Independent power generation in aircraft
    8.
    发明授权
    Independent power generation in aircraft 有权
    飞机独立发电

    公开(公告)号：US08657227B1

    公开(公告)日：2014-02-25

    申请号：US12558177

    申请日：2009-09-11

    申请人： Andrew J. Bayliss ,  John T. Paterson ,  Kevin Retz

    发明人： Andrew J. Bayliss ,  John T. Paterson ,  Kevin Retz

    IPC分类号： B64D41/00

    CPC分类号： B64D41/00 ,  B64D13/00 ,  B64D13/06 ,  B64D37/04 ,  B64D37/20 ,  B64D41/007 ,  B64D2013/0603 ,  B64D2013/0644 ,  B64D2041/002 ,  B64D2041/005 ,  B64D2221/00 ,  H02J4/00 ,  H02J2001/004 ,  Y02T50/44 ,  Y02T50/56 ,  Y02T90/36

    摘要： Systems and methods of independent power generation are disclosed. A particular system includes an aircraft having at least one engine and a plurality of independent power units. Each power unit of the plurality of independent power units generates electricity independently of the at least one engine. The plurality of independent power units include at least a first independent power unit that generates first electricity having a first set of electrical characteristics and a second independent power unit that generates second electricity having a second set of electrical characteristics concurrently with the first power unit generating the first electricity. The first set of electrical characteristics is different than the second set of electrical characteristics.

    摘要翻译： 公开了独立发电的系统和方法。 特定系统包括具有至少一个发动机和多个独立动力单元的飞行器。 所述多个独立动力单元中的每个动力单元独立于所述至少一个发动机发电。 所述多个独立动力单元至少包括产生具有第一组电特性的第一电的第一独立功率单元和第二独立功率单元，所述第二独立功率单元产生与所述第一功率单元同时产生第二组电特性的第二电， 第一电 第一组电气特性与第二组电气特性不同。