首页> 外国专利> LOW-WIND-RESISTANCE TUBULAR TRACK, STRATOSPHERE-SIMULATING LOW-WIND-RESISTANCE TUBE HAVING BUILT-IN TRACK, CARRIER ROCKET SPACECRAFT LAUNCHING SYSTEM, AND METHOD FOR REDUCING RESISTANCE OF TUBULAR TRACK

LOW-WIND-RESISTANCE TUBULAR TRACK, STRATOSPHERE-SIMULATING LOW-WIND-RESISTANCE TUBE HAVING BUILT-IN TRACK, CARRIER ROCKET SPACECRAFT LAUNCHING SYSTEM, AND METHOD FOR REDUCING RESISTANCE OF TUBULAR TRACK

机译:低风阻管轨迹,具有内置履带的层流模拟低风阻管,运载火箭航天发射系统以及降低风管阻力的方法

摘要

A low-wind-resistance tubular track, a stratosphere-simulating low-wind-resistance tube having a built-in track, a carrier rocket spacecraft launching system, and a method for reducing resistance of a tubular track, relating to the technical field of carrier rocket spacecraft launching. The low-wind-resistance tubular track comprises a roadbed (1) and a plurality of tube bodies (2) fixedly provided on the roadbed (1); the plurality of tube bodies (2) are sequentially and continuously fixedly connected; tracks (3) are laid on the roadbed (1); each tube body (2) is provided across the top of the tracks (3) along the laying direction of the tracks (3); the tube body (2) comprises a first fixing piece (21) and a second fixing piece (22) provided at two ends thereof, a plurality of air ducts (23), and a plurality of heating units (24); the plurality of air ducts (23) of two adjacent tube bodies (2) are correspondingly communicated; the plurality of air ducts (23) are correspondingly communicated with a plurality of air blowers (4); the plurality of air ducts (23) are provided with a plurality of air outlets (231) at equal intervals in an axial direction; and the airflows of the plurality of air outlets (231) can intersect with each other. Said low-wind-resistance tubular track has characteristics of enabling a rocket transporting device to travel at a high speed from a lower altitude region to a higher altitude region.
机译:低风阻管状轨道,具有内置轨道的平流层模拟低风阻管,运载火箭航天器发射系统以及用于减小管状轨道阻力的方法,涉及一种风阻技术运载火箭航天器发射。低风阻管状轨道包括路基(1)和固定设置在路基(1)上的多个管体(2)。多个管体(2)依次连续地固定连接。轨道(3)铺设在路基(1)上;每个管体(2)沿轨道(3)的铺设方向横穿轨道(3)的顶部。管体(2)包括设置在其两端的第一固定件(21)和第二固定件(22),多个风道(23)和多个加热单元(24)。相邻的两个管体(2)的多个风道(23)对应连通。多个风道(23)与多个鼓风机(4)相对应地连通。多个风路(23)在轴向上等间隔地设有多个出风口(231)。并且,多个空气出口(231)的气流可以相互交叉。所述低风阻管状轨道具有使得火箭运输装置能够从较低海拔区域向较高海拔区域高速行进的特征。

著录项

  • 公开/公告号WO2018133640A1

    专利类型

  • 公开/公告日2018-07-26

    原文格式PDF

  • 申请/专利权人 QIN ZHAOXIU;

    申请/专利号WO2017CN119375

  • 发明设计人 QIN ZHAOXIU;

    申请日2017-12-28

  • 分类号B64F1/10;

  • 国家 WO

  • 入库时间 2022-08-21 12:43:18

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