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    HIGH-SPEED VEHICLE POWER AND THERMAL MANAGEMENT SYSTEM AND METHODS OF USE THEREFOR
    3.
    发明申请
    HIGH-SPEED VEHICLE POWER AND THERMAL MANAGEMENT SYSTEM AND METHODS OF USE THEREFOR 审中-公开
    高速车辆动力和热管理系统及其使用方法

    公开(公告)号：US20150315971A1

    公开(公告)日：2015-11-05

    申请号：US14519872

    申请日：2014-10-21

    Applicant: Government of the United States as Represented by the Secretary of the Air Force

    Inventor： Thomas L. Reitz ,  Larry Byrd

    IPC: F02C7/224 ,  B64D33/08 ,  B64C30/00

    CPC classification number: B64C30/00 ,  B64C1/38 ,  B64D33/08 ,  B64D37/34 ,  B64D2033/024 ,  B64D2033/026 ,  F01K15/02 ,  F02C7/224 ,  F02C7/236 ,  F02K1/822 ,  F05D2220/323 ,  F05D2220/62 ,  F05D2220/76 ,  F05D2220/80 ,  F05D2260/601 ,  F05D2300/514 ,  Y02T50/675 ,  Y02T90/44

    Abstract: A thermal management and power generation system for a hypersonic vehicle. The thermal management and power generation system comprising a fluid supply having a volatile fluid and a fuel supply having an endothermic fuel. A first heat exchanger, fluidically coupled to the fluid supply, absorbs heat from a first portion of the hypersonic vehicle, which vaporizes the volatile fluid. A mixing apparatus, fluidically coupled to the first heat exchanger and the fuel supply combines the vaporized volatile fuel and endothermic fuel. A second heat exchanger, fluidically coupled to the mixing apparatus, absorbs heat from a second portion of the hypersonic vehicle and decomposes the endothermic fuel by endothermic pyrolysis. A heat engine, fluidically coupled to the first heat exchanger and the mixing apparatus, is configured to generate an electrical power for use by the hypersonic vehicle. The vaporized volatile fluid mixed with the endothermic fuel within the second heat exchanger reduces coking caused by the endothermic pyrolytic decomposition of the endothermic fuel as compared to an endothermic pyrolytic decomposition of an endothermic fuel not having a vaporized volatile fluid mixed therewith.

    Abstract translation: 用于超音速车辆的热管理和发电系统。 热管理和发电系统包括具有挥发性流体的液体供应源和具有吸热燃料的燃料供应。 流体耦合到流体供应源的第一热交换器从超音速车辆的第一部分吸收热量，其使挥发性流体蒸发。 流体耦合到第一热交换器和燃料供应的混合装置将蒸发的挥发性燃料和吸热燃料组合。 流体耦合到混合装置的第二热交换器从超音速车辆的第二部分吸收热量并通过吸热裂解分解吸热燃料。 流体耦合到第一热交换器和混合装置的热引擎被配置为产生用于超音速车辆的电力。 与第一热交换器中的吸热燃料混合的蒸发的挥发性流体与吸热燃料的吸热热分解相比，减少了由吸热燃料的吸热热分解引起的焦化，该吸热燃料不具有与其混合的蒸发的挥发性流体。

    Aircraft power management
    4.
    发明授权
    Aircraft power management 有权
    飞机电源管理

    公开(公告)号：US08457860B2

    公开(公告)日：2013-06-04

    申请号：US13657515

    申请日：2012-10-22

    Applicant: AeroVironment, Inc.

    Inventor： Thaddeus Benjamin Matuszeski ,  Rolland Mitchell Koch ,  Scott Garret Berman ,  Mujahid Abdulrahim

    IPC: F02D9/00

    CPC classification number: B64C39/024 ,  B64C2201/042 ,  B64D27/24 ,  B64D31/02 ,  B64D2221/00 ,  H02J7/1446 ,  H02J7/1476 ,  Y02T10/7005 ,  Y02T10/7258 ,  Y02T50/62 ,  Y02T90/44

    Abstract: An electric power management system of a vehicle may interconnect a power plant, a propeller drive unit, and a battery via a bus. A command limiting controller may direct the operation of the power plant and the propeller drive unit in fast and slow modes of operation, the fast mode of operation operating at a higher bus voltage than at a slow mode of operation. The command limiting controller may generate a bus current to drive the propeller drive unit according to a command limiting, voltage-versus-current curve that adjusts the bus current depending on an amount of voltage on the power bus; where the command limiting curve includes a minimum voltage portion, a maximum voltage portion and a control range therebetween having upper and lower voltage limits and upper and lower current limits for enhanced reliability and stable control of the propeller drive unit.

    Abstract translation: 车辆的电力管理系统可以通过总线互连电厂，螺旋桨驱动单元和电池。 命令限制控制器可以指导发电厂和螺旋桨驱动单元的操作在快速和慢速的操作模式中，快速操作模式在比较慢的操作模式更高的总线电压下操作。 命令限制控制器可以产生总线电流，以根据命令限制，根据电力总线上的电压量调节总线电流的电压 - 电流曲线来驱动螺旋桨驱动单元; 其中命令限制曲线包括最小电压部分，最大电压部分及其间具有上限和下限电压限制的上限和下限电流限制，用于提高螺旋桨驱动装置的可靠性和稳定的控制。

    ULTRA-RAPID AIR VEHICLE AND RELATED METHOD FOR AERIAL LOCOMOTION
    5.
    发明申请
    ULTRA-RAPID AIR VEHICLE AND RELATED METHOD FOR AERIAL LOCOMOTION 有权
    超快速空气车辆及其相关方法

    公开(公告)号：US20120325957A1

    公开(公告)日：2012-12-27

    申请号：US13516878

    申请日：2010-12-20

    Applicant: Marco Prampolini ,  Yohann Coraboeuf

    Inventor： Marco Prampolini ,  Yohann Coraboeuf

    IPC: B64C30/00

    CPC classification number: B64C30/00 ,  B64C3/10 ,  B64C5/08 ,  B64C5/10 ,  B64C23/076 ,  B64D27/023 ,  B64D27/20 ,  B64D27/26 ,  B64D2027/026 ,  B64G1/14 ,  Y02T50/12 ,  Y02T50/164 ,  Y02T50/44 ,  Y02T90/44

    Abstract: The invention concerns an ultra-rapid air vehicle together with a method of aerial locomotion by means of an ultra-rapid air vehicle, where the air vehicle is propelled by a system of motors formed of turbojets (TB1, TB2), ramjets (ST1, ST2) and a rocket motor which can be made streamlined to reduce the drag of the base during the cruise phase, and where the vehicle has a gothic delta wing (A) fitted with moving fins (a1, a2) at both outer ends of the trailing edge of the delta wing (A).

    Abstract translation: 本发明涉及一种超快速空中飞行器以及超快速空中飞行器的空中移动方法，其中，空中交通工具由涡轮喷气发动机（TB1，TB2），冲击器（ST1， ST2）和火箭发动机，其可以被制成流线型以减少在巡航阶段期间底座的阻力，并且其中车辆具有装配有活动翅片（a1，a2）的哥特式三角翼（A），其在两个外端处 三角翼的后缘（A）。

    PROPULSION DEVICE WITH A PLURALITY OF ENERGY CONVERTERS FOR AN AIRCRAFT
    6.
    发明申请
    PROPULSION DEVICE WITH A PLURALITY OF ENERGY CONVERTERS FOR AN AIRCRAFT 审中-公开
    具有多台用于飞机的能量转换器的推进装置

    公开(公告)号：US20110108663A1

    公开(公告)日：2011-05-12

    申请号：US12516907

    申请日：2007-11-26

    Applicant: Andreas Westenberger

    Inventor： Andreas Westenberger

    IPC: B64D27/02 ,  F02K3/02 ,  F02C3/00 ,  F02B53/00

    CPC classification number: B64D27/02 ,  B64D27/24 ,  B64D37/04 ,  Y02T50/44 ,  Y02T50/64 ,  Y02T90/44

    Abstract: The present invention relates to a propulsion device for an aircraft. The propulsion device comprises a first energy converter (4), a second energy converter (5) and a propulsion unit (1). The first energy converter (4) provides first propulsion energy, and the second energy converter (5) provides second propulsion energy. The first energy converter (4) and the second energy converter (5) are adapted to provide the first propulsion energy and the second propulsion energy to the propulsion device (1).

    Abstract translation: 本发明涉及一种用于飞行器的推进装置。 推进装置包括第一能量转换器（4），第二能量转换器（5）和推进单元（1）。 第一能量转换器（4）提供第一推进能，而第二能量转换器（5）提供第二推进能。 第一能量转换器（4）和第二能量转换器（5）适于将第一推进能量和第二推进能量提供给推进装置（1）。

    Propulsion system with integrated rocket accelerator
    7.
    发明申请
    Propulsion system with integrated rocket accelerator 有权
    集成火箭加速器的推进系统

    公开(公告)号：US20090057494A1

    公开(公告)日：2009-03-05

    申请号：US10414321

    申请日：2003-04-15

    Applicant: Stephen A. Beckel ,  James D. Blevins ,  Thomas Verdi

    Inventor： Stephen A. Beckel ,  James D. Blevins ,  Thomas Verdi

    IPC: B64C30/00

    CPC classification number: B64C30/00 ,  B64D27/023 ,  Y02T90/44

    Abstract: The present invention relates to a propulsion system for a vehicle. The propulsion system has an airframe integrated hydrocarbon fueled airbreathing engine, such as a ramjet or a scramjet. The propulsion system further has at least one rocket positioned so as to use the aft body contour of the vehicle directly for flow expansion. In a preferred embodiment, a plurality of rockets are arrayed across the width of the engine nozzle.

    Abstract translation: 本发明涉及一种用于车辆的推进系统。 推进系统具有机身一体化的碳氢化合物燃料空气呼吸引擎，例如冲压式喷气式或冲击式喷气式发动机。 推进系统还具有至少一个火箭，其定位成直接用于车辆的后身轮廓以用于流动膨胀。 在优选实施例中，多个火箭被排列在发动机喷嘴的宽度上。

    HYDROGEN FUELED BLENDED WING BODY RING TANK
    8.
    发明申请
    HYDROGEN FUELED BLENDED WING BODY RING TANK 有权
    氢燃烧混合机身环罐

    公开(公告)号：US20080230654A1

    公开(公告)日：2008-09-25

    申请号：US11559615

    申请日：2006-11-14

    Applicant: Alexander Velicki ,  Daniel A. Hansen

    Inventor： Alexander Velicki ,  Daniel A. Hansen

    IPC: B64D37/04

    CPC classification number: B64D37/04 ,  B64C2039/105 ,  B64D37/06 ,  Y02T50/12 ,  Y02T50/44 ,  Y02T90/44

    Abstract: A toroidal shaped or ring fuel tank located within the loft line of a blended wing body aircraft is disclosed. The ring tank may be used in an aircraft to store liquid hydrogen fuel with a reduced tank weight. The ring tank may be continuous with no tank end domes typically found on cylindrical pressure tanks, reducing tank weight for a given fuel volume. The ring tank configuration avoids increasing the aerodynamic shape of the aircraft and does not encroach on usable passenger or payload areas of the aircraft. In one example the ring tank may be configured in a nose down position such that the forward portion of the ring tank is outside the pressurized cabin area.

    Abstract translation: 公开了一种位于混合翼体飞机的阁楼线内的环形或环形燃料箱。 环形罐可用于飞机中以储存液体重量较低的液体氢燃料。 环形罐可以是连续的，没有通常在圆柱形压力罐上发现的罐端圆顶，减少给定燃料体积的罐重量。 环形罐配置避免了增加飞机的空气动力学形状，并且不会侵犯飞机的有用乘客或有效载荷区域。 在一个示例中，环形罐可以被配置在向下的位置，使得环形罐的前部在加压舱区域的外部。

    Progressive 3-axis multi-variable propulsion vectoring aerial and spacecraft vehicle
    9.
    发明授权
    Progressive 3-axis multi-variable propulsion vectoring aerial and spacecraft vehicle 失效
    逐行三轴多变量推进矢量航空和航天器车辆

    公开(公告)号：US06371406B1

    公开(公告)日：2002-04-16

    申请号：US09444491

    申请日：1999-11-19

    Applicant: Bruce Alan Corcoran

    Inventor： Bruce Alan Corcoran

    IPC: B64C3906

    CPC classification number: B64C39/001 ,  B64C15/02 ,  B64C27/18 ,  B64C29/005 ,  B64D27/20 ,  B64G1/00 ,  B64G1/24 ,  B64G1/26 ,  B64G1/28 ,  B64G1/36 ,  B64G1/401 ,  Y02T90/44

    Abstract: The present embodiments and associated methods provide for a progressive 3-axis multi-variable propulsion vectoring aerial and spaceborne vehicle. One embodiment of the vehicle is comprised of top and side air intakes, a curved sphenoid air accumulator, a compressor section, a diffuser, a plurality of fuel burner cans, a turbine section, a gas plenum, top, side, and bottom exhaust ports, propellant burner cans, gas plenum iris, an onboard flight control computer, and top, side, and bottom exhaust port doors. Combustion gasses are produced which are directed by the gas plenum to the exhaust ports which provide thrust and lift to the vehicle. By selectively opening and closing the exhaust port doors, the vehicle may be made to rise, hover, and accelerate in any direction. Such an embodiment provides a vehicle that can directly ascend through the atmosphere into space.

    Abstract translation: 本实施例和相关方法提供了渐进的3轴多变量推进矢量空中和空间载体。 车辆的一个实施例包括顶部和侧部进气口，弯曲蝶形空气蓄能器，压缩机部分，扩散器，多个燃料燃烧器罐，涡轮部分，气体增压室，顶部，侧部和底部排出端口 ，推进剂燃烧器罐，气体充气虹膜，飞行控制计算机以及顶部，侧面和底部排气口门。 产生燃烧气体，其由气体充气室引导到向车辆提供推力和提升的排气口。 通过选择性地打开和关闭排气口门，可以使车辆上升，悬停并且在任何方向上加速。 这样的实施例提供一种能够直接通过大气上升到空间中的车辆。

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