The stable motor control was introduced to the maximum thrust control by using this strategy. The velocity control was realized through the control of electromagnetic thrust Angle.

该控制策略将直线电机的稳定控制引入到最大推力控制中，通过控制电机的电磁力角，实现直线电机的速度控制。

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The condition of the existence of solution of functional extreme value problem applied to maximum thrust nozzle is also presented.

同时，还导出了最大推力喷管这个泛函极值问题解存在的条件。

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There exists an optimal exit area of secondary nozzle to result in a maximum thrust of rocket ejector in the light of the investigated ejector chamber structure.

在文中所研究的引射燃烧室结构条件下，存在一个最佳二次喷管出口面积，它能使引射火箭的推力达到最大。

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