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    Rocket propelled drone
    2.
    发明授权
    Rocket propelled drone 有权

    公开(公告)号：US11975871B2

    公开(公告)日：2024-05-07

    申请号：US16883838

    申请日：2020-05-26

    申请人： Joseph William Randal Martel

    发明人： Joseph William Randal Martel

    IPC分类号： B64D17/80 ,  B64C37/00 ,  B64D27/02 ,  B64U10/20 ,  B64U30/293 ,  B64U50/15 ,  B64U50/19

    CPC分类号： B64U10/20 ,  B64C37/00 ,  B64D17/80 ,  B64D27/023 ,  B64U30/293 ,  B64U50/15 ,  B64U50/19 ,  B64U2201/10 ,  B64U2201/20

    摘要： Disclosed is a remotely controlled wireless drone which employs a solid fuel rocket engine to propel it quickly to a desired or location. More specifically, an unmanned vehicle including a fuselage and a propulsion unit engaged with the fuselage, the propulsion unit being operable to bring the unmanned vehicle to a desired altitude or location, generally during a launch stage. The fuselage also includes multiple rotors pivotally engaged with the fuselage and a rotor positioning system operable to pivot the multiple rotors between stowed and deployed positions. The stowed position of the propellers minimizes drag and instability during the launch stage, and the deployed position allows the multiple rotors to control the position and altitude of the unmanned vehicle after the fuel of the rocket engine is spent. Submersible/amphibious and other embodiments are also described.

    Aerodynamic and Spatial Composite Flight Aircraft, and Related Piloting Method
    4.
    发明申请
    Aerodynamic and Spatial Composite Flight Aircraft, and Related Piloting Method 审中-公开
    空气动力学和空间复合飞行飞机及相关试飞方法

    公开(公告)号：US20140110530A1

    公开(公告)日：2014-04-24

    申请号：US14086914

    申请日：2013-11-21

    申请人： Astrium SAS

    发明人： Christophe Chavagnac ,  Jerome Bertrand ,  Hugues Laporte-Weywada ,  Olivier Poulain ,  Philippe Matharan ,  Robert Laine

    IPC分类号： B64G1/00

    CPC分类号： B64G1/005 ,  B64D27/023 ,  B64D2027/026 ,  B64G1/002 ,  B64G1/14 ,  B64G1/401 ,  Y02T50/44

    摘要： An aircraft having propulsion units for both conventional aircraft flight in the atmosphere and for high-altitude operation as a rocket. The aircraft is divided into a payload compartment and a compartment containing rocket propulsion unit propellant or fuel, and includes a long transverse wing with a small back-sweep to favour lift in the dense layers of the atmosphere and to thus make it possible to climb to high altitudes at a subsonic speed before using the rocket propulsion units. The return flight portion is performed by gliding or controlled as for a conventional aircraft.

    摘要翻译： 一架飞机具有用于常规飞机在大气中飞行和作为火箭进行高空作战的推进装置。 飞机分为有效载荷舱和包含火箭推进装置推进剂或燃料的舱室，并且包括具有小的反向扫掠的长横翼，以有利于在大气层的致密层中的升力，从而使其可以爬上 在使用火箭推进装置之前，亚音速的高海拔高度。 返回飞行部分通过滑翔或受控于常规飞机执行。

    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

    申请人： Marco Prampolini ,  Yohann Coraboeuf

    发明人： Marco Prampolini ,  Yohann Coraboeuf

    IPC分类号： B64C30/00

    CPC分类号： 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

    摘要： 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).

    摘要翻译： 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 system with integrated rocket accelerator
    6.
    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

    申请人： Stephen A. Beckel ,  James D. Blevins ,  Thomas Verdi

    发明人： Stephen A. Beckel ,  James D. Blevins ,  Thomas Verdi

    IPC分类号： B64C30/00

    CPC分类号： B64C30/00 ,  B64D27/023 ,  Y02T90/44

    摘要： 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.

    摘要翻译： 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。