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    SYSTEMS AND METHODS FOR CONTROLLING A MAGNITUDE OF A SONIC BOOM
    91.
    发明公开
    SYSTEMS AND METHODS FOR CONTROLLING A MAGNITUDE OF A SONIC BOOM 审中-公开
    系统及其控制方法音爆的程度

    公开(公告)号：EP2956357A1

    公开(公告)日：2015-12-23

    申请号：EP14751160.4

    申请日：2014-02-10

    申请人： Gulfstream Aerospace Corporation

    发明人： FREUND, Donald

    IPC分类号： B64C30/00

    CPC分类号： B64C23/00 ,  B64C3/185 ,  B64C3/20 ,  B64C3/38 ,  B64C3/42 ,  B64C9/00 ,  B64C17/10 ,  B64C30/00 ,  B64D37/00 ,  Y02T50/14 ,  Y02T50/44

    摘要： A method of controlling a magnitude of a sonic boom caused by off-design-condition operation of a supersonic aircraft at supersonic speeds includes, but is not limited to the step of operating the supersonic aircraft at supersonic speeds and at an off-design-condition. The supersonic aircraft has a pair of swept wings having a plurality of composite plies oriented at an angle such that an axis of greatest stiffness is non-parallel with respect to a rear spar of each wing of the pair of swept wings. The method further includes, but is not limited to the step of reducing wing twist caused by operation of the supersonic aircraft at supersonic speeds at the off-design condition with the composite plies. The method still further includes, but is not limited to, minimizing the magnitude of the sonic boom through reduction of wing twist.

    AIRCRAFT TAXIING SYSTEMS
    97.
    发明公开
    AIRCRAFT TAXIING SYSTEMS 有权
    面辊系统

    公开(公告)号：EP2288541A1

    公开(公告)日：2011-03-02

    申请号：EP09762918.2

    申请日：2009-06-12

    申请人： The Ashman Group, LLC.

    发明人： BHARGAVA, Brij, B.

    IPC分类号： B64D27/20 ,  B64C30/00

    CPC分类号： B64D27/02 ,  B64C25/405 ,  B64D27/20 ,  B64D41/00 ,  Y02T50/44 ,  Y02T50/823

    摘要： Thrust systems for passenger aircraft provide at least one flight engine (66) and a taxi engine (70) wherein all' flight engines together provide, in total, a takeoff thrust (65) arranged in a takeoff thrust direction and the taxi engine provides a taxi thrust (75) which does not exceed 15% of the takeoff thrust and is directed substantially the same as the. takeoff thrust direction. The taxi thrust is thereby sufficient to taxi the aircraft along a taxi path. In a system embodiment, the taxi thrust does not exceed 7.5% of the flight thrust. In another system embodiment, the flight engines have, in total, a flight engine weight and the taxi engine has a taxi engine weight that does not exceed 10% of the flight engine weight. In a system embodiment, the taxi engine weight does not exceed 7.0% of the flight engine weight. In another system embodiment, the taxi engine has a rated thrust and is configured so that the taxi thrust is within 40% -and 100% of the rated thrust. In another system embodiment, the taxi engine, includes a rotatable engine portion (80) to divert the taxi thrust over an azimuth angle (82) to assist taxiing along the taxi path.

    Integrated inward turning inlets and nozzles for hypersonic air vehicles
    98.
    发明公开
    Integrated inward turning inlets and nozzles for hypersonic air vehicles 审中-公开
    综合内弯的进气口和喷嘴的高超音速飞机

    公开(公告)号：EP1818257A3

    公开(公告)日：2009-12-16

    申请号：EP07102293.3

    申请日：2007-02-13

    申请人： Lockheed Martin Corporation

    发明人： Elvin, John D.

    IPC分类号： B64C30/00 ,  B64D27/20 ,  B64D33/02

    CPC分类号： B64C30/00 ,  B64C2039/105 ,  B64D2033/026 ,  Y02T50/12

    摘要： A hypersonic waverider aircraft is disclosed that includes a first engine (106) and an inlet including a throat (108). The inlet is configured to generate three-dimensional flow compression during hypersonic flight with a weak shock wave that begins at the leading edge surfaces of the inlet and coalesces ahead of the throat, and a weak shock wave that begins at the point of coalescence of the weak shock wave and extends to the throat. The inlet includes a v-shaped lip open to freestream airflow in one side of the inlet.

    FUSELAGE D'AÉRONEF
    99.
    发明公开
    FUSELAGE D'AÉRONEF 有权

    公开(公告)号：EP2106363A2

    公开(公告)日：2009-10-07

    申请号：EP07872431.7

    申请日：2007-12-21

    申请人： Airbus ,  AIRBUS France

    发明人： SAINT-JALMES, Bruno ,  ZANEBONI, Jason ,  BELLEVILLE, Mathieu

    IPC分类号： B64C1/00 ,  B64C30/00 ,  B64D27/00

    CPC分类号： B64C1/0009 ,  B64C2001/0045 ,  B64D27/12

    摘要： The invention relates to an aircraft fuselage comprising a front part (2) with a cockpit, a central part (4) and a rear part (6). The central part of the fuselage includes a first zone (10) which is located at the front part and which increases in width to a maximum width towards the rear of the aircraft, a second zone (12) that decreases in width, and a third zone (14) which has an essentially constant width and which is located behind the second zone (12), width being measured along the pitch axis.

    摘要翻译： 本发明涉及一种飞机机身，其包括具有驾驶舱，中央部分（4）和后部（6）的前部（2）。 机身的中央部分包括位于前部的第一区域（10），其宽度朝向飞机后部增加到最大宽度，宽度减小的第二区域（12）以及第三区域 （14），其具有基本恒定的宽度并且位于第二区域（12）的后面，宽度沿俯仰轴线测量。

    FUSELAGE SHAPING AND INCLUSION OF SPIKE ON A SUPERSONIC AIRCRAFT FOR CONTROLLING AND REDUCING SONIC BOOM
    100.
    发明授权
    FUSELAGE SHAPING AND INCLUSION OF SPIKE ON A SUPERSONIC AIRCRAFT FOR CONTROLLING AND REDUCING SONIC BOOM 有权
    船体教育和顶部安装上的超级平面控制和减少ÜBERSCHALLBANG

    公开(公告)号：EP1478569B1

    公开(公告)日：2009-09-23

    申请号：EP03707587.6

    申请日：2003-01-30

    申请人： Gulfstream Aerospace Corporation

    发明人： HENNE, Preston ,  HOWE, Donald ,  WOLZ, Robert ,  HANCOCK, Jimmy, Jr.

    IPC分类号： B64C23/04 ,  B64C30/00

    CPC分类号： B64C23/04 ,  B64C30/00

    摘要： Method and arrangement for reducing the effects of a sonic boom created by an aerospace vehicle when said vehicle is flown at supersonic speed. The method includes providing the aerospace vehicle with a first spike extending from the nose thereof substantially in the direction of normal flight of the aerospace vehicle, the first spike having a second section aft of a first section that is aft of a leading end portion, the first and second sections having a second transition region therebetween and each of the sections having different cross-sectional areas, the leading end portion of the first spike tapering toward a predetermined cross-section with a first transition region between the predetermined cross-section and the first section. The first transition region is configured so as to reduce the coalescence of shock waves produced by the first spike during normal supersonic flight of the aerospace vehicle. A spike may also be included that extends from the tail of the aerospace vehicle to reduce the coalescence of shock waves produced by the spike during normal supersonic flight of the aerospace vehicle.