| 1. | A variable pitching moment is provided by moving the elevator .
俯仰力矩的变化由升降舵的偏转来提供。 |
| 2. | Attached to the stabilizers are two movable surface called "elevator" .
与水平安定面相连的是两个称为“升降舵”的可动操纵面。 |
| 3. | The taper of elevators is usually slight, and the difference between the two values is generally small .
升降舵的根梢比通常较小，因而两个值之间的差别一般不大。 |
| 4. | The rudder hinge moment and control force are treated in a manner similar to that employed for the elevator .
研究方向舵铰链力矩和操纵力的方法与研究升降舵所采用的方法相似。 |
| 5. | For any c.g. position, an increase in trim speed from any initial value to a larger one requires a downward deflection of the elevator .
对于任意一个重心位置，平衡速度由它的初始值变化到较大的值时要求升降舵向下偏转。 |
| 6. | F72785 - 572 elevator rudder aileron power control unit test equipment
F72785 - 572型升降舵方向舵副翼动力控制装置测试仪 |
| 7. | Repeat push forward cyclic completing a minimum of two ( 2 ) forward tumbles
将升降舵打降舵，重覆步骤3 ，向前翻滚至少二圈。 |
| 8. | Further , the reconfigurable control law is designed undergoing the elevator and aileron failures
并研究了升降舵、副翼发生失效和卡死时的控制律重构方法。 |
| 9. | Time the input of the cyclic & collective commands such that the helicopter path is that of loop
安排副翼、升降舵及主旋翼螺距的打舵时机，使得直升机的飞行轨迹形成一个圆圈。 |
| 10. | Time the input of the cyclic & collective commands such that the helicopter path is that of a loop
安排副翼、升降舵及主旋翼螺距的打舵时机，使得直升机的飞行轨迹形成一个圆圈。 |
