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    Rocket Launch System and Supporting Apparatus
    3.
    发明申请
    Rocket Launch System and Supporting Apparatus 审中-公开
    火箭发射系统和配套装置

    公开(公告)号：US20130007935A1

    公开(公告)日：2013-01-10

    申请号：US13577813

    申请日：2011-02-10

    申请人： Howard M. Chin ,  Kimberly A. Carraha

    发明人： Howard M. Chin ,  Kimberly A. Carraha

    IPC分类号： B64G6/00 ,  B64G1/14 ,  B64G5/00 ,  B64F1/04 ,  F41F3/04

    CPC分类号： F41F3/06 ,  B64G1/005 ,  B64G6/00 ,  B64G2001/643 ,  F41F3/04

    摘要： A rocket launch system (1) includes a tubular rocket launcher carriage (2) with electromotive cableway traction drives (26) conveyed beneath a two axis pivot (63) anchored to the earth, elevated into a co-axial transfer tube (124, 143) leading to three primary tether cables (27) whose weight is offset by balloons (164). The carriage is conveyed to a docking station (166) supported into the stratosphere by a pair of secondary cables (184) suspended under an attachment frame (162) for tensioning balloons. The carriage is engaged by a carriage end gripper (196) guided by two secondary and two tertiary cables (186) and lifted by a lower hoist (198) guided by the secondary cables. This lower hoist is supported by an upper hoist (168) suspended from the tensioning balloons attachment frame. The carriage, which engages a lift ring (183) guided by two secondary cables, is elevated further, rotated as desired, with rocket release and nearly recoilless ejection during freefall of the carriage, with engine ignition occurring at a safe distance.

    摘要翻译： 火箭发射系统（1）包括管状火箭发射器托架（2），其具有在锚定到地球的两轴枢轴（63）下传送的电动索道牵引驱动器（26），升高到同轴传送管（124,143 ），其通过气球（164）偏移重量的三个主系绳电缆（27）。 托架通过悬挂在用于张紧气球的附接框架（162）下方的一对辅助电缆（184）被传送到支撑到平流层的坞站（166）。 滑架由两个辅助和两个第三电缆（186）引导的托架端部夹持器（196）接合，并由辅助电缆引导的下部起重机（198）提升。 该下部起重机由悬挂在张紧气球附件架上的上部起重机（168）支撑。 与两个辅助电缆引导的提升环（183）相接合的滑架进一步升高，随着火箭的释放而进行旋转，并在滑架自由下降期间几乎无后坐弹射，发动机点火发生在安全的距离。

    CARRIAGE FOR ROCKET LAUNCH SYSTEM
    4.
    发明申请
    CARRIAGE FOR ROCKET LAUNCH SYSTEM 审中-公开

    公开(公告)号：US20170284768A1

    公开(公告)日：2017-10-05

    申请号：US15627558

    申请日：2017-06-20

    申请人： Howard M. Chin ,  Kimberly A. Carraha

    发明人： Howard M. Chin ,  Kimberly A. Carraha

    IPC分类号： F41F3/06 ,  F41F3/04 ,  B64G1/00 ,  B64G6/00

    CPC分类号： F41F3/06 ,  B64G1/005 ,  B64G6/00 ,  B64G2001/643 ,  F41F3/04

    摘要： A carriage for use in a rocket launch system for cooperating with an electromotive cableway traction drives conveyed beneath a two axis pivot anchored to the earth, elevated into a co-axial transfer tube leading to three primary tether cables whose weight is offset by balloons. The carriage has traction drives which grip cables from which they derive power and rotate to drive the carriage from the low altitude to the high altitude. The traction drives rotate in the opposite direction as the carriage descends the cable following the launch of a rocket under gravitational force. The kinetic energy of the traction drive is converted to electrical energy which is fed back to the cables during descent of the carriage.

    Carriage for rocket launch system
    5.
    发明授权
    Carriage for rocket launch system 有权

    公开(公告)号：US10443976B2

    公开(公告)日：2019-10-15

    申请号：US15627558

    申请日：2017-06-20

    申请人： Howard M. Chin ,  Kimberly A. Carraha

    发明人： Howard M. Chin ,  Kimberly A. Carraha

    IPC分类号： B64G1/00 ,  F41F3/06 ,  B64G6/00 ,  F41F3/04 ,  B64G1/64

    摘要： A carriage for use in a rocket launch system for cooperating with an electromotive cableway traction drives conveyed beneath a two axis pivot anchored to the earth, elevated into a co-axial transfer tube leading to three primary tether cables whose weight is offset by balloons. The carriage has traction drives which grip cables from which they derive power and rotate to drive the carriage from the low altitude to the high altitude. The traction drives rotate in the opposite direction as the carriage descends the cable following the launch of a rocket under gravitational force. The kinetic energy of the traction drive is converted to electrical energy which is fed back to the cables during descent of the carriage.

    Rocket launch system and supporting apparatus
    8.
    发明授权
    Rocket launch system and supporting apparatus 有权

    公开(公告)号：US09739567B2

    公开(公告)日：2017-08-22

    申请号：US13577813

    申请日：2011-02-10

    申请人： Howard M. Chin ,  Kimberly A. Carraha

    发明人： Howard M. Chin ,  Kimberly A. Carraha

    IPC分类号： B64G1/00 ,  F41F3/06 ,  B64G6/00 ,  F41F3/04 ,  B64G1/64

    CPC分类号： F41F3/06 ,  B64G1/005 ,  B64G6/00 ,  B64G2001/643 ,  F41F3/04

    摘要： A rocket launch system includes a tubular rocket launcher carriage with electromotive cableway traction drives conveyed beneath a two axis pivot anchored to the earth, elevated into a co-axial transfer tube leading to three primary tether cables whose weight is offset by balloons. The carriage is conveyed to a docking station supported into the stratosphere by a pair of secondary cables suspended under an attachment frame for tensioning balloons. The carriage is engaged by a carriage end gripper guided by two sets of secondary cables and two sets of tertiary cables and lifted by a lower hoist guided by the secondary cables to a lift ring assembly. This lower hoist is supported by an upper hoist suspended from the tensioning balloons attachment frame. The carriage, which engages a lift ring guided by two secondary cables, is elevated further, rotated in azimuth and elevation, and rocket ejection occurs from a launch tube during freefall of the carriage, with engine ignition occurring at a safe distance. The carriages have traction drives which grip cables from which they derive power and rotate to drive the carriage from the low altitude to the high altitude. The traction drives rotate in the opposite direction as the carriage descends the cable following the launch of a rocket under gravitational force. The kinetic energy of the traction drive is converted to electrical energy which is fed back to the cables during descent of the carriage.