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    • 7. 发明授权
    • Rising and moving apparatus and manufacturing method thereof
    • 上升移动装置及其制造方法
    • US07219855B2
    • 2007-05-22
    • US10618301
    • 2003-07-11
    • Masaki HamamotoYoshiji OhtaKeita Hara
    • Masaki HamamotoYoshiji OhtaKeita Hara
    • B64C33/02
    • B64C33/02
    • A fluid-structure interactive analysis is performed while n types of wing structure models are caused to flap in accordance with a prescribed model of flapping manner. Based on an analysis, data 1, data 2, . . . data n of physical values related to fluid behavior and physical values related to structural behavior are calculated. Among data 1, data 2, . . . data n, a data having a prescribed parameter such as the lift force optimized is extracted. A prototype of a wing portion is formed, which has such a structure that is specified by various parameter values of the numerical model of wing structure corresponding to the extracted data. A driving unit 905 drives the prototype of the wing portion in a manner of flapping that is represented by the flapping motion model equivalent to the manner of flapping of an insect. At this time, the wing has a stiffness that is suitable for flapping flight so that prescribed parameters come to have optimal values.
    • 进行流体结构交互分析,同时根据规定的拍打模式使n种类型的翼结构模型进行折翼。 基于分析,数据1,数据2,。 。 。 计算与流体行为和与结构行为相关的物理值相关的物理值的数据n。 在数据1中,数据2,。 。 。 数据n,提取具有规定参数的数据,例如优化的提升力。 形成翼部的原型,其具有由对应于提取的数据的机翼结构的数值模型的各种参数值指定的结构。 驾驶单元905以与扑灭昆虫的方式等效的扑动运动模型所表示的扑动方式驱动机翼部分的原型。 此时,机翼具有适合拍打飞行的刚度,使规定的参数达到最佳值。
    • 9. 发明授权
    • Moving apparatus
    • 移动装置
    • US08210470B2
    • 2012-07-03
    • US11166743
    • 2005-06-23
    • Yoshiji OhtaKeita HaraMasaki Hamamoto
    • Yoshiji OhtaKeita HaraMasaki Hamamoto
    • B64C33/02
    • B64C33/00
    • In a moving apparatus, flapping angle of a front wing shaft is γ+Δγ/2, and the flapping angle of rear wing shaft is γ−Δγ/2. Specifically, amplitude difference between front wing shaft and rear wing shaft is Δγ. Further, the flapping motion of front wing shaft is represented by sin (τ+φ/2), and the flapping motion of rear wing shaft is represented by sin (τ−φ/2). In other words, phase difference between the front and rear wing shafts is φ. Further, amplitude difference Δγ and phase difference φ are each represented by a function using a common parameter. Therefore, a control portion can independently change the amplitude difference Δγ and phase difference φ, so as to variously change a torsion angle formed by a tip end portion of the wing and a prescribed phantom plane. Thus, a moving apparatus that can make an efficient transition from hovering to forward or backward flight can be provided.
    • 在移动装置中,前翼轴的拍击角为γ+&Dgr;γ/ 2,后翼轴的拍打角为γ&Dgr;γ/ 2。 具体来说,前翼轴和后翼轴之间的振幅差为&Dgr;γ。 此外,前翼轴的拍击运动由sin(τ+&phgr; / 2)表示,后翼轴的扑动运动由sin(τ-&phgr; / 2)表示。 换句话说,前翼和后翼轴之间的相位差是&phgr。 此外,振幅差Dgr;γ和相位差 各自由使用公共参数的函数表示。 因此,控制部分可以独立地改变振幅差Dgrγ和相位差phgr,以便不同地改变由翼的末端部分形成的扭转角和规定的幻影平面。 因此,可以提供可以从盘旋到向前或向后飞行的有效过渡的移动装置。