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    • 2. 发明申请
    • Crossover motor vehicle with a cargo bed
    • 交叉机动车与货床
    • US20070273177A1
    • 2007-11-29
    • US11440394
    • 2006-05-25
    • Mithra M.K.V. SankrithiSiva Usha Mithra Sankrithi
    • Mithra M.K.V. SankrithiSiva Usha Mithra Sankrithi
    • B62D33/00
    • B62D47/003B60P3/423B62D33/04
    • The invention provides an innovative and practical new class of crossover motor vehicles for carrying passengers and for carrying cargo in a cargo or pickup bed, while still being of sufficiently small dimensions as to be garage-able in many home garages. Representative embodiments can carry 6 or 7 or 9 persons in comfortable seats all with adjacent or facing seats for companions; plus substantial varied cargos, which can potentially include sporting or recreational equipment such as bicycles or a powered waterscooter or snowmobile or motorcycle; camping gear including a 9-person tent; furniture such as a Queen bed set; appliances such as a washer and dryer; utility equipment such as a snowblower or riding lawnmower; or substantial quantities of items such as lumber, bark or fertilizer.
    • 本发明提供了一种创新和实用的新型交叉机动车辆,用于携带乘客和在货物或皮卡床上运送货物,同时仍然具有足够小的尺寸以便在许多家庭车库中可车库。 代表性的实施例可以携带6或7或9人在舒适的座位中,全部与相邻或面对的同伴座位; 加上各种各样的货物,其中可能包括运动或休闲设备,如自行车或动力滑水车或雪地摩托车或摩托车; 露营装备包括一个9人帐篷; 家具如大床套; 电器如洗衣机和烘干机; 实用设备,如吹雪机或骑马割草机; 或大量的物品,如木材,树皮或肥料。
    • 3. 发明申请
    • Wing load alleviation apparatus and method
    • 翼载减轻装置及方法
    • US20070114327A1
    • 2007-05-24
    • US11283586
    • 2005-11-18
    • Paul DeesMithra Sankrithi
    • Paul DeesMithra Sankrithi
    • B64C39/06
    • B64C13/16B64C9/323Y02T50/44
    • A wing load alleviation system and method for alleviating the lift-inducing structural-bending force (i.e., moment) experienced by each of the wings of an aircraft. The apparatus includes a deployable panel and an actuator mounted in each wing. The actuators are responsive to a command generator. The actuator is mounted inside the wing and the panel is mounted flush with an outer surface of its respective wing. Each panel can be moved between a retracted position, where it has no affect on airflow moving over the wing, to a deployed position in which it deflects air off of the wing. Each panel is preferably located at a span-wise location at least about halfway along the length of the wing toward the wing tip, and more preferably at least in part outboardly of the outboard-most trailing edge device in the wing. The apparatus effectively shifts the lift-inducing structural-bending forces experienced by the wing more inboard towards the fuselage.
    • 一种用于减轻由飞行器的每个翼经历的升力诱导结构弯曲力(即,力矩)的机翼加载减轻系统和方法。 该装置包括可展开的面板和安装在每个翼中的致动器。 致动器响应命令发生器。 致动器安装在机翼的内部,并且面板与其相应机翼的外表面齐平地安装。 每个面板可以在缩回位置之间移动,在缩回位置,其对在机翼上移动的气流没有影响,在其中使空气偏离机翼的展开位置移动。 每个面板优选地位于沿着翼的长度的至少大约一半的翼展位置处,并且更优选地至少部分地在机翼中的最外侧后缘装置的外侧。 该装置有效地将机身所经受的升力引起的结构弯曲力更多地转移到机身上。
    • 4. 发明申请
    • Cross section for a supersonic airplane
    • 超音速飞机横截面
    • US20050061916A1
    • 2005-03-24
    • US10668823
    • 2003-09-22
    • Mithra Sankrithi
    • Mithra Sankrithi
    • B64C1/00B64C1/10B64C30/00
    • B64C1/0009B64C1/10B64C30/00B64C2001/0045
    • A fuselage for an airplane comprising a first side of the fuselage having a first curvature; and a second side of the fuselage having a second curvature; wherein the first curvature is different from the second curvature at a substantially vertical cross section of the fuselage. The invention can also be characterized as a cross section of an airplane comprising a first side of a fuselage with a first curvature; a second side of the fuselage with a second curvature that is coupled to the first side of the fuselage; a storage compartment within the fuselage; a seat within the fuselage; and an aisle within the fuselage; wherein the first curvature is different from the second curvature. The invention can reduce or eliminate sonic boom when applied to a supersonic airplane such as a supersonic business jet with a long slender fuselage.
    • 一种用于飞机的机身,包括具有第一曲率的机身的第一侧; 并且所述机身的第二侧具有第二曲率; 其中所述第一曲率在所述机身的基本竖直的横截面处不同于所述第二曲率。 本发明还可以表征为飞机的横截面,其包括具有第一曲率的机身的第一侧; 具有耦合到机身的第一侧的第二曲率的机身的第二侧; 机身内的储藏室; 机身内的一个座位; 机身内的通道; 其中所述第一曲率不同于所述第二曲率。 本发明可以在应用于超音速飞机(例如具有长纤细机身的超音速商用喷气机)时减少或消除声音爆炸。
    • 5. 发明授权
    • Crossover motor vehicle with a cargo bed
    • 交叉机动车与货床
    • US07431366B2
    • 2008-10-07
    • US11440394
    • 2006-05-25
    • Mithra M. K. V. SankrithiSiva Usha Mithra Sankrithi
    • Mithra M. K. V. SankrithiSiva Usha Mithra Sankrithi
    • B62D39/00
    • B62D47/003B60P3/423B62D33/04
    • The invention provides an innovative and practical new class of crossover motor vehicles for carrying passengers and for carrying cargo in a cargo or pickup bed, while still being of sufficiently small dimensions as to be garage-able in many home garages. Representative embodiments can carry 6 or 7 or 9 persons in comfortable seats all with adjacent or facing seats for companions; plus substantial varied cargos, which can potentially include sporting or recreational equipment such as bicycles or a powered waterscooter or snowmobile or motorcycle; camping gear including a 9-person tent; furniture such as a Queen bed set; appliances such as a washer and dryer; utility equipment such as a snowblower or riding lawnmower; or substantial quantities of items such as lumber, bark or fertilizer.
    • 本发明提供了一种创新和实用的新型交叉机动车辆,用于携带乘客和在货物或皮卡床上运送货物,同时仍然具有足够小的尺寸以便在许多家庭车库中可车库。 代表性的实施例可以携带6或7或9人在舒适的座位中,全部与相邻或面对的同伴座位; 加上各种各样的货物,其中可能包括运动或休闲设备,如自行车或动力滑水车或雪地摩托车或摩托车; 露营装备包括一个9人帐篷; 家具如大床套; 电器如洗衣机和烘干机; 实用设备,如吹雪机或骑马割草机; 或大量的物品,如木材,树皮或肥料。
    • 7. 发明申请
    • Weight optimized pressurizable aircraft fuselage structures having near elliptical cross sections
    • 重量优化的加压飞机机身结构具有近椭圆截面
    • US20070108347A1
    • 2007-05-17
    • US11273966
    • 2005-11-15
    • Mithra SankrithiKevin Retz
    • Mithra SankrithiKevin Retz
    • B64C1/00
    • B64C1/061B64C1/08B64C2001/0045B64C2001/0072B64C2001/0081Y02T50/12Y02T50/43
    • 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.
    • 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。