First Korea Space Launch Vehicle Kick Motor Movable Nozzle Motion

著录项

• 来源
  《Journal of Spacecraft and Rockets》 |2010年第1期|153-168|共16页
• 作者

  Jae-Seok Yoo;

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• 作者单位

  Korea Aerospace Research Institute, Daejeon 305-333, Republic of Korea;

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• 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);
• 原文格式 PDF
• 正文语种 eng
• 中图分类
• 关键词

  D =projected distance of each displacement gauge as shown in Fig. 1 (right-hand side), mm; E_(ai.pitch) =ith percent relative error for the compensated pitch rotational angle,; E_(ai.yaw) =ith percent relative error for the compensated yaw rotational angle,; L_(INCL-P) =linear coefficient of the inclinometer angle for the thrust vector control input voltage on pitch actuating, deg /V; L_(INCL-Y) =linear coefficient of the inclinometer angle for the thrust vector control input voltage on yaw actuating, deg /V;

  机译：D =每个位移计的投影距离;如图1所示（右侧）;mm;E_（ai.pitch）=补偿螺距旋转角的第i个相对误差百分比;％;E_（ai.yaw）=补偿偏航旋转角的第i个相对误差百分比;％;L_（INCL-P）=俯仰致动时推力矢量控制输入电压的测斜仪角度的线性系数;度/ V;L_（INCL-Y）=偏航驱动时推力矢量控制输入电压的测斜仪角度的线性系数;度/ V;