Chapter One
A helicopter of central articulated rotor makes a level flight with cruse speed. In this flight condition, the pitching attitude angle is 02?=-, longitudinal cyclic pitching angle is 017
B =, rotor longitudinal flapping angle is 013s a =-. Assuming the tilted angle of rotor shaft is 00δ=, please determining the following angles:
Helicopter climb angle θ=
Fuselage attack angle α=
Rotor attack angle s α=
Rotor flapping due to forward speed 10a =
中心铰式旋翼直升机以巡航速度前飞。俯仰角-2°，纵向周期变距7°，纵向挥舞角-3°，旋翼轴前倾角0°
平飞，爬升角0°
机身迎角-2°
桨盘平面迎角-2°
吹风挥舞4°
Chapter Two
1.For the main/tail rotor configuration helicopter, the pilot applies
which stick or rudder to control what kind of surfaces and corresponding aerodynamic forces?
2.Why the gradient of control stick forces can’t be too large or small?
3.Co-axis, tandem and tilted-rotor helicopters have no tail rotor. How to
change the direction in hover for these helicopters?
1.操纵——气动面——响应P13表2-1
前推/后拉杆——纵向周期变距，桨盘前倾/后倒——前飞/后飞，俯仰左推/右推杆——横向周期变距，桨盘侧倒——侧飞，滚转
油门/总距杆——改变总距——改变垂向速度
脚蹬——改变尾桨总距——改变航向
2.为什么杆力梯度不能太大也不能太小P16
太大时大操纵较吃力，太小了不易感觉当前位移量。杆力梯度适中有利于精确操纵。
3.共轴、纵列、倾转旋翼机如何悬停转弯？
共轴——上下旋翼总距差动
纵列——前后横向周期变距一个向左一个向右
倾转旋翼——一侧后倒一侧前倒
Chapter Three
1.The rotation direction of Black hawk helicopter rotor is anticlockwise
from the top view. Please answer the following questions:
●How the rotor flaps when the helicopter comes up gust in hover?
How to adjust the controller to keep the hover condition?
●How the blade changes its feathering angle following the pilot’s
adjustment?
2.During left and right turn flights with constant speed and altitude, is
there any different for pilot controls?
3.Is there flapping motion for hinge-less rotor?
1.黑鹰直升机旋翼右旋
悬停时遇到阵风旋翼如何挥舞，此时如何操纵
前方来的阵风会导致旋翼后倒，右倒。应向前、向左推杆。
前推杆导致90°桨距变小，270°桨距变大
左推杆导致180°桨距变小，0°桨距变大
2.不改变高度和速度时，左转弯和右转弯有区别没？
以右旋直升机为例，左转时需要增加尾桨总距，为了平衡尾桨拉力的增加需要左推杆以增加侧向力，这却导致了旋翼拉力的降低，进而需要提总距，又导致向前拉力的增加，因而需要后拉杆。总之，右旋直升机前飞左转弯的操纵为，踩脚蹬—左压杆—提总距—后拉杆。
同理，右旋直升机右转弯的操纵为：松脚蹬—减小左压杆—减总距—减小前推杆3.无铰式旋翼有挥舞吗？
没有挥舞铰但是通过桨叶根部的柔性段或者桨榖柔性件的弹性变形实现挥舞运动。