中国大学飞行器稳定性与操纵性(英)_1期末答案(mooc2023课后作业答案)
24 min read中国大学飞行器稳定性与操纵性(英)_1期末答案(mooc2023课后作业答案)
Test 1
1、中国作业某飞机纵向受扰动后的大学定性答案答案迎角响应如下图所示，该飞机纵向静 ，飞行动 。器稳期末 The操纵 AOA response of an aircraft after being disturbed is given below. The airplane is statically , and dynamically .
A、稳定，性英稳定 stable,课后 stable
B、稳定，中国作业不稳定 stable,大学定性答案答案 unstable
C、不稳定，飞行稳定 unstable,器稳期末 stable
D、不稳定，操纵不稳定 unstable,性英 unstable
2、如果一架飞机某个试飞科目的课后Cooper-Harper等级评分为4.5, 则该飞机该科目的飞行品质应为几级？ If the average Cooper-Harper rating of an aircraft is 4.5, the flying quality of this aircraft is .
A、一级 level I
B、中国作业二级 level II
C、三级 level III
D、不可控 Uncontrollable
3、目前我国采用的是国际坐标系，又称欧美坐标系，x由重心指向机头，y由重心指向右，根据右手定律，z轴朝下。在上世纪我国曾经采用过前苏联的坐标系，该坐标系x轴由重心指向机头，y轴由重心指向上，那么根据右手定律，z轴是由重心指向 。 At present, China adopts the international coordinate system, where x-axis points from CG to the nose, and y-axis points from CG to the right. According to the right-hand system, the z-axis points downward. In the last century, China used the USSR coordinate system. The x-axis points from CG to the nose, and y-axis points upward. According to the right-hand system, the z-axis points .
A、上 upward
B、下 downward
C、左 to the left
D、右 to the right
4、按照本课程的符号定义习惯（国际坐标系），绕x轴向右滚转为 ，绕z轴向左偏航为 。 According to the sign convention in this course (international coordinate system), roll to the right about the x-axis is , and yaw to the left about the z-axis is .
A、正，正 positive, positive
B、负，正 negative, positive
C、正，负 positive, negative
D、负，负 negative, negative
5、如果垂尾上作用有负侧力，则该侧力会产生 偏航力矩. If the side force acting on the rudder is negative, this side force will generate a yawing moment.
A、左 left
B、右 right
C、上 upward
D、下 downward
6、如果平尾上作用有正升力，则该平尾升力会产生 俯仰力矩. If the lift acting on the horizontal tail is positive, this tail lift will generate a pitching moment.
A、抬头 nose-up
B、低头 nose-down
C、向右 right
D、向左 left
7、对飞行品质要求最高的是哪个飞行阶段？ Which category of flight phases has the highest flying quality requirement?
A、A种 Category A
B、B种 Category B
C、C种 Category C
D、D种 Category D
8、下列飞机中，属于IV类飞机的有哪些？ Which of the following aircraft belong to class IV?
A、J-10
B、J-20
C、H-6
D、Y-20
E、C919
F、J-15
9、下列飞行阶段中，属于A种飞行阶段的有 Which flight phases belong to Category A?
A、起飞 Takeoff
B、着陆 Landing
C、空对空战 Air-to-Air Combat
D、编队飞行 Formation
E、巡航 Cruise
F、爬升 Climb
G、武器投放 Weapon delivery
10、与是两个相同的系数. and are the same coefficient.
11、B种飞行阶段对飞行品质的要求最低。 Category B has the lowest requirement on flying quality.
12、空中加油属于A种飞行阶段。 In-flight refuel is a CAT A flight phase.
2. 纵向静稳定性 (Longitudinal Static Stability)
Test 2
1、平尾对纵向静稳定性的影响与以下哪个因素无关？ Which of the following factors is not related to the tail contribution on longitudinal static stability.
A、平尾面积 Horizontal tail area
B、平尾距重心距离 Distance between CG and horizontal tail
C、平尾下洗角 Downwash angle of the horizontal tail
D、平尾安装角 setting angle of the horizontal tail
2、机翼对纵向静稳定性的贡献取决于重心位置，重心前移，纵向静稳定性将 。 Wing contribution on longitudinal static stability depends on CG location, CG moves forward, the stability .
A、降低 decreases
B、提高 increases
C、不变 doesn't change
D、N/A
3、绝大部分机翼采用的都是正弯度翼型，其零升俯仰力矩系数 。 Most of the wings use positively cambered airfoil, the zero-lift pitching moment is .
A、>0 positive
B、=0 zero
C、<0 negative
D、N/A
4、平尾会提高飞机的纵向静稳定性，鸭翼会 飞机的纵向静稳定性。 Horizontal tails increase the longitudinal stability, while canards the longtitudinal stability.
A、提高 increase
B、不影响 don't affect
C、降低 decrease
D、N/A
5、螺旋桨式发动机的滑流对以下哪个参数没有影响？ Which of the following parameters is not affected by the propeller slipstream?
A、局部动压 local dynamic pressure
B、局部升力 local lift
C、局部阻力 local drag
D、发动机功率 engine power
6、在给定飞行状态下，飞机的纵向静稳定性与以下哪些参数有关？ For a given flight condition, which of the following parameters are related to the longitudinal static stability?
A、机翼弯度 Wing camber
B、平尾尾容比 Tail volume ratio
C、重心位置 CG location
D、飞机升力系数 Lift coefficient
E、下洗角 Downwash angle
F、平尾动压比 Tail dynamic pressure ratio
7、发动机产生的俯仰力矩与哪些因素相关？ Which of the following parameters are related to the pitching moment generated by the engine?
A、发动机类型 Engine type
B、发动机安装角 Engine setting angle
C、发动机推力 Engine thrust
D、发动机安装位置 Engine position
8、机翼对纵向静稳定性起的是增稳作用。 The wing has a stabilizing effect on longitudinal static stability.
9、中性点是飞机纵向中立稳定对应的重心位置. Neutral point is the CG location where the aircraft is neutrally stable.
10、某飞机的Cm~CL曲线如下图所示，该飞机纵向静稳定 The Cm~CL curve of an aircraft is given below, and the aircraft is longitudinal statically stable.
3. 纵向操纵 (Longitudinal Control)
Test 3
1、对于同一架飞机，升降舵效率提高，其重心前限会 。 For a given aircraft, if the control effectiveness of elevator increases, the most forward CG location will .
A、前移 move forward
B、后移 move aftward
C、不变 remain unchanged
D、不确定 uncertain
2、对于静稳定飞机，随着升力系数的增加，为平衡飞机，升降舵需 For a stable aircraft, as CL increases, in order to balance the aircraft, the elevator should .
A、左偏 deflect to the left
B、右偏 deflect to the right
C、上偏 deflect upward
D、下偏 deflect downward
3、某纵向静稳定飞机存在跨音速勺型区现象，则该飞机在从亚音速加速至超音速过程中，飞行员应如何操纵驾驶杆？ There is a Mach tuck phenomenon for a longitudinal statically stable aircraft. How should the pilot control the stick when the aircraft accelerates from subsonic to supersonic?
A、始终推杆 Push the stick all the time.
B、始终拉杆 Pull the stick all the time.
C、先推杆、再拉杆、再推杆 Push, then pull, then push again.
D、先拉杆、再推杆、再拉杆 Pull first, then push, then pull again
4、在地面效应作用下，平尾的效率会 The control effectiveness of elevator will under the ground effect.
A、提高 increase
B、降低 decrease
C、不变 remained unchanged
D、不确定 uncertain
5、舰载机在起飞离舰瞬间，其升力会 。 When carrier-based aircraft take off from a carrier, its lift will .
A、突然增加 increase suddenly
B、突然下降 decrease suddenly
C、不变 remain unchanged
D、不确定 uncertain
6、对于地面效应，以下哪些说法是对的？ About ground effect, Which of the following statements are true?
A、机翼升力线斜率增加 Wing lift-curve slope increases.
B、平尾升力线斜率增加 Tail lift-curve slope increases.
C、中性点前移 Neutral point moves forward.
D、下洗角增加 Downwash angle increases.
E、飞机重心前限后移 Most forward CG location moves aftward.
7、对于既无平尾也无鸭翼的飞机，以下哪些是有效的俯仰操纵方式？ For an aircraft with neither horizontal tail nor canard, which of the following are effective pitch control methods?
A、重心移动 CG movement
B、升降副翼 elevon
C、平尾 horizontal tail
D、推力矢量 thrust vectoring
8、以下哪些气动补偿方式是通过调节压心与铰链轴距离来降低铰链力矩的？ Which of the following aerodynamic balancing methods reduce hinge moment by adjusting the distance between cp and the hingeline?
A、轴式补偿 set-back hingeline
B、角式补偿 horn balance
C、内补偿 internal balance
D、调整片 tab
9、在不考虑空气压缩性的前提下，纵向静不稳定飞机在亚音速状态下加速时，飞行员需要拉杆. For a longitudinal statically unstable aircraft, without considering the air compressibility, the pilot needs to pull the stick to accelerate at subsonic condition.
10、地面效应会使飞机升力增加 Ground effect will increase the lift of the aircraft
11、为降低操纵力，调整片的偏转方向应与操纵面相同 In order to reduce control force, tab should deflect to the same direction with control surface.
4. 重心位置与范围 (CG Locations and Limits)
Test 4
1、拉杆操纵时，升降舵会 ，产生 力矩。 When pull the stick, elevator will deflect , and generate pitching moment.
A、上偏，低头 upward, nose-down
B、上偏，抬头 upward, nose-up
C、下偏，低头 downward, nose-down
D、下偏，抬头 downward, nose-up
2、加速飞行时， 操纵是符合飞行员操纵习惯的。 During acceleration, is consistent with the pilot's control habits.
A、拉杆 pulling the stick
B、推杆 pushing the stick
C、左压杆 deflecting the stick to the left
D、右压杆 deflecting the stick to the right
3、在平均气动弦上，以下四点中，位于最前面的是 。 On the mean aerodynamic chord, among the following four points, the most forward is .
A、握杆中性点 Stick-fixed neutral point
B、松杆中性点 Stick-free neutral point
C、握杆机动点 Stick-fixed maneuver point
D、松杆机动点 Stick-free maneuver point
4、在平均气动弦上，以下四点钟，位于最后面的是 On the mean aerodynamic chord, amont the following four points, the most aftward is .
A、握杆中性点 Stick-fixed neutral point
B、松杆中性点 Stick-free neutral point
C、握杆机动点 Stick-fixed maneuver point
D、松杆机动点 Stick-free maneuver point
5、对于有尾飞机，在做抬头机动时，平尾处的局部迎角会 。 For aircraft with horizontal tail, during nose-up maneuver, the local AOA of the tail will .
A、不变 remain unchanged
B、减小 decrease
C、增加 increase
D、N/A
6、最大操纵力梯度对应的是一个重心 ，为保证操纵性需求，重心应位于该点 。 The maximum control force gradient corresponds to a , in order to satisfy the control requirement, CG should be of that point.
A、前限，之前 forward limit, ahead of
B、前限，之后 forward limit, aft of
C、后限，之前 rear limit, ahead of
D、后限，之后 rear limit, aft of
7、在平衡状态下，纵向静稳定飞机的平尾配平升力为 。 In equilibrium state, the tail trim lift of a stable aircraft is .
A、正 positive
B、负 negative
C、0
D、不确定 uncertain
8、以下哪些说法是对的? Which of the following statements are true?
A、握杆机动点是单位过载所需升降舵偏角为0对应的重心位置 stick-fixed maneuver point is the CG location where elevator per g is 0
B、握杆机动点是单位过载所需杆力为0对应的重心位置 stick-fixed maneuver point is the CG location where control force per g is 0
C、松杆机动点是单位过载所需升降舵偏角为0对应的重心位置 stick-free maneuver point is the CG location where elevator per g is 0
D、松杆机动点是单位过载所需杆力为0对应的重心位置 stick-free maneuver point is the CG location where control per g is 0
9、对于纵向静稳定飞机，以下哪些临界状态是用来确定重心前限的？ Which of the following critical states are used to determine the forward CG limit for the longitudinal static stable aircraft?
A、起飞抬前轮 raise nose wheel off the ground
B、着陆拉平 landing
C、失速配平 stall trim
D、杆力随速度变化梯度为正 Fs~V gradient positive
E、纵向静稳定 longitudinal stable
10、在满足稳定性需求的前提下，重心位置越往后，机动性越高。 In the case of satisfying the stability requirements, CG moves aft will increase maneuverability.
11、同样的飞机，重心适当后移可使飞机的配平性能提高。 For the same aircraft, the trim performance can be improved by moving CG back properly.
5. 航向静稳定性 (Directional Static Stability)
Test 5
1、按照本课程的符号定义习惯，飞机 感受到来流时侧滑角为正，如果飞机能产生 偏航力矩，则飞机航向静稳定。 According to the sign convention of this course, the sideslip angle is positive when the aircraft feels the flow. If the aircraft can generate a yaw moment, the aircraft is statically directional stable.
A、左侧，左 left, left
B、左侧，右 left, right
C、右侧，左 right, left
D、右侧，右 right, right
2、对于下反机翼，在右侧滑情况下，右侧机翼迎角 左侧机翼迎角. For anhedral wings, in right sideslip, the right wing AOA is the left wing AOA.
A、大于 higher than
B、小于 smaller than
C、等于 equal to
D、N/A
3、对于后掠机翼，左侧滑情况下，右侧机翼动压 左侧机翼动压。 For swpet-back wings, in leftsideslip, the right wing dynamic pressure is the left wing dynamic pressure.
A、大于 higher than
B、小于 lower than
C、等于 equal to
D、N/A
4、正常布局飞机的航向静稳定性最大来源是 。 For conventional configuration aircraft, the maximum contributor of directional stability is .
A、垂尾 vertical tail
B、机翼 wing
C、机身 fuselage
D、平尾 horizontal tail
5、当飞机受到左侧滑时，垂尾会产生向 的力和向 偏航力矩。 In left sideslip, the vertical tail will generate a side force and yawing moment.
A、左，左 left, left
B、左，右 left, right
C、右，左 right, left
D、右，右 right, right
6、侧洗会 垂尾前缘处的侧滑角。 Sidewash will the sideslip angle of the vertical tail leading edge.
A、增大 increase
B、减小 decrease
C、不影响 not affect
D、N/A
7、螺旋桨滑流会 航向静稳定性 。 Propeller slip stream will directional static stability.
A、提高 increase
B、减小 decrease
C、不影响 not affect
D、N/A
8、在右侧滑的情况下，无上反的后掠角会改变以下哪些参数？ In right sideslip, which parameters will be changed for swept-back wing with 0 dihedral wing?
A、垂直速度 vertical velocity
B、展向速度 spanwise velocity
C、弦向速度 chordwise velocity
D、局部动压 local dynamic pressure
9、战斗机可采用 布局来保证大迎角和大M数下的航向静稳定性。 Fighters can adopt configuration to satisfy directional static stability at high Mach number and AOA.
A、双垂尾 double vertical tail
B、单垂尾+腹鳍 single vertical tail + ventral fins
C、飞翼式 flying wing
D、无尾 tailless
10、航向静稳定导数为负时飞机航向静稳定。 The aircraft is directionally static stable if the derivative of directional static stability Cnb is negative
11、螺旋桨位于机头还是机尾，对飞机的航向静稳定性没有影响。 Whether the propeller is located at the nose or the tail has no effect on the directional static stability.
6. 航向操纵与横向操稳特性 (Directional Control and Lateral Stability and Control)
Test 6
1、B-2翼梢后缘的操纵面产生偏航力矩的机理是什么？ What is the mechanism of the directinal control surface at the wing-tip trailing edge of B-2?
A、改变局部升力 change local lift
B、改变局部侧力 change local side force
C、改变局部阻力 change local drag
D、N/A
2、方向舵 偏为正，会产生 偏航力矩 Rudder deflect to the is positive, and a yawing moment will be generated.
A、左，左 left, left
B、左，右 left, right
C、右，左 right, left
D、右，右 right, right
3、飞机在做逆时针盘旋时，会由于内外侧机翼速度不等产生 偏航力矩。 When the aircraft is doing a counter-clockwise turn, yaw moments will be generated due to the unequal speed of the inner and outer wings.
A、向左 left
B、向右 right
C、向上 upward
D、向下 downward
4、飞机尾旋时的迎角大于50度，此时下列操纵面中仍可用的是 。 The AOA in spin is greater than 50 degrees. At this time, which of the following control surfaces are still available？
A、升降舵elevator
B、副翼aileron
C、鸭翼canard
D、方向舵rudder
5、垂尾对横向静稳定性的贡献是 。 The vertical tail has a on lateral static stability.
A、增加稳定性 stabilizing effect
B、降低稳定性 destabilizing effect
C、大迎角时增加稳定性，小迎角时降低稳定性 stabilizing effect at high AOA, destabilizing effect at low AOA
D、小迎角时增加稳定性，大迎角时降低稳定性 stabilizing effect at low AOA, destabilizing effect at high AOA
6、以下哪些操纵面不能产生偏航力矩？ Which of the following control surfaces can generate yawing moment?
A、升降舵 elevator
B、方向舵 rudder
C、推力矢量 thrust vectoring
D、阻力方向舵 split drag rudder
7、以下哪些操纵面能产生偏航力矩？ Which of the following control surfaces can generate yawing moment?
A、升降舵 elevator
B、方向舵 rudder
C、推力矢量 thrust vectoring
D、扰流板 spoiler
E、阻力方向舵 split drag rudder
F、升降副翼 elevon
8、下列因素中，对横向静稳定性起增稳作用的有 。 Which of the following factors can increase the lateral static stability?
A、上反角 dihedral angle
B、后掠角 swept-back angle
C、前掠角 swept-forward angle
D、上单翼 high wing
E、下单翼 low wing
9、下列操纵面中，适合作为横向操纵面的有 。 Which of the following control surfaces are suitable as lateral control surfaces?
A、副翼 ailerons
B、升降副翼 elevons
C、升降舵 elevator
D、方向舵 rudder
E、扰流板 spoiler
10、飞机的航向静稳定性越高越好。 The directional static stability is higher better.
11、后掠角对横向静稳定性的贡献仅与后掠角的正弦成正比 The contribution of the sweep angle to lateral static stability is only proportional to the sine of the sweep angle.
12、右侧扰流板打开时，飞机会向右滚转。 When the right spoiler is deployed, the aircraft rolls to the right.
7. 坐标轴系及运动方程 (Axes and Equations of Motion)
Test 7
1、导航轴系的原点为地球表面的某一点，x轴指向正北，y轴指向正东，则z轴指向 。 The Origin of the Navigational System is located on the surface of the Earth. The x axis points towards the local north, the y axis points towards the local east, and the z axis points .
A、正西 towards local west
B、正南 towards local south
C、地心 to the center of the Earth
D、上 upward
2、惯性轴系与地轴系之间相差了一个 。 The difference between the Inertial system and Earth-fixed system is .
A、迎角 AOA
B、侧滑角 sideslip angle
C、地球自转 earth rotation
D、地球公转 earth's revolution
3、坐标变换的顺序非常重要，顺序的不同会导致完全不同的坐标，其正确的变换顺序是 。 The order of rotations is very important, different order would result in a different orientation. The transformation sequence is .
A、先绕x轴，再绕y轴，最后绕z轴 first about the x axis, then the y axis, and last the z axis
B、先绕z轴，再绕y轴，最后绕x轴 first about the z axis, then the y axis, and last the x axis
C、先绕x轴，再绕z轴，最后绕y轴 first about the x axis, then the z axis, and last the y axis
D、先绕z轴，再绕x轴，最后绕y轴 first about the z axis, then the x axis, and last the y axis
4、在建立运动方程时，以下哪个不是假设条件？ Which of the following is not an assumption in establishing the equations of motion?
A、忽略地球曲率 Ignore Earth Curvature
B、忽略地球自转 Ignore the Earth Rotation
C、忽略外力 Ignore external forces
D、飞机视为刚体 The vehicle is treated as a single rigid body
5、初始扰动不为0，操纵输入为0的响应特性被称为自由响应，体现的是飞机的 。 Free response, with a given set of initial conditions, and 0 control input, indicates the .
A、静稳定性 static stability
B、动稳定性 dynamic stability
C、静操纵性 static controllability
D、动操纵性 dynamic controllability
6、飞机的运动方程是以 为参考轴系为基础建立的。 It’s the Axes System used to define the Newton's Laws of Motion.
A、惯性轴系 Inertia
B、地轴系 Earth-fixed
C、体轴系 Body
D、导航轴系 Navigational
7、经过小扰动线化后，纵向和横航向方程均可表示为状态方程形式，其中矩阵B被称为 。 After small-disturbance linearization, the longitudinal and lateral-directional equations can both be written in state space form . Where, B is the .
A、状态变量 state variable
B、控制变量 control variable
C、系统矩阵 system matrix
D、操纵效能矩阵 control effectiveness matrix
8、当特征根是一对实部为负的共轭复根时，可用 描述其响应特性。 If the roots are complex with negative real part, can be used to describe the dynamic stability.
A、响应的半衰时 time to half of the response
B、响应的倍幅时 time to double of the response
C、响应包线的半衰时 time to half of the response envelope
D、响应包线的倍幅时 time to double of the response envelope
9、以下哪些坐标轴系属于体轴系。 Which of the following systems belongs to the Body Axes Systems.
A、惯性轴系 Inertial Axes System
B、地轴系 Earth-Fixed Axes System
C、导航轴系 Navigational System
D、基础体轴系 Basic Body Axes System
E、稳定轴系 Stability Axes System
F、风轴系 Wind Axes System
10、以下哪些角度是基础体轴系与风轴系间的夹角？ Which of the following angles are the angles between the basic body Axes System and the Wind Axes System?
A、迎角 Angle of attack
B、侧滑角 Sideslip angle
C、俯仰角 pitch angle
D、滚转角 roll angle
E、航向角 heading angle
11、以下哪些特征根是动稳定的？ Which of the following eigenvalues are dynamically stable?
A、
B、
C、
D、
12、体轴系和风轴系之间相差了一个迎角和一个侧滑角，从风轴系到体轴系的坐标变换顺序是先绕y轴转一个迎角、再绕z轴转一个侧滑角。 The Body Axes System deviates sideslip angle β and AOA α from the Wind Axes System. The transformation sequence from Wind to Body is first rotate an α about the y axis, then rotate a β the z axis.
13、小扰动假设适用于所有的飞行状态。 The small disturbance assumptions are valid for all kind of flight conditions.
8. 模态及要求 (Modes and Requirements)
Test 8
1、对于常规布局飞机，以下哪个不是横航向的运动模态？ For conventional configuration aircraft, which one is not a lateral-directional mode?
A、滚转收敛模态 Roll-subsidence mode
B、荷兰滚模态 Dutch roll mode
C、螺旋模态 Spiral mode
D、短周期模态 Short-period mode
2、短周期自然频率主要取决于以下哪个参数？ The short period natural frequency mainly depends on which of the following parameters?
A、
B、
C、
D、
3、长周期模态的频率在低速情况下，随前向速度的增加而 。 At low speeds, the phugoid frequency with the increase of forward velocity.
A、减小 decreases
B、增大 increases
C、不变 remains unchanged
D、N/A
4、滚转收敛模态的特征根主要取决于以下哪个参数? The eigenvalue of roll-subsidence mode mainly depends on which of the following parameters.
A、
B、
C、
D、
5、荷兰滚模态的频率主要取决于以下哪个参数？ The Dutch-roll frequency mainly depends on which of the following parameters.
A、
B、
C、
D、
6、当飞机向右滚转时，其右侧机翼的迎角会 。 When the aircraft roll to the right, the right wing AOA will .
A、增加 increase
B、减小 decrease
C、不变 remain unchanged
D、N/A
7、短周期阻尼比主要取决于以下哪些参数？ The short period damping ratio mainly depends on which of the following parameters?
A、
B、
C、
D、
8、短周期模态的主要运动参数包括 。 The main motion parameters of short period mode include .
A、俯仰角 pitch angle
B、俯仰角速度 pitch rate
C、迎角 AOA
D、前向速度 forward velocity
9、以下哪些情况满足一级品质要求 Which of the following situations satisfy the Level I flying quality requirements?
A、战斗机A种飞行阶段Tr=1.2 Fighter at Cat A flight phase, Tr = 1.2
B、战斗机B种飞行阶段Tr=1.2 Fighter at Cat B flight phase, Tr = 1.2
C、战斗机C种飞行阶段Tr=1.2 Fighter at Cat C flight phase, Tr = 1.2
D、运输机B种飞行阶段Tr=1.2 Cargo at Cat B flight phase, Tr = 1.2
E、运输机C种飞行阶段Tr=1.2 Cargo at Cat C flight phase, Tr = 1.2
10、螺旋模态特征根为负时，其飞行品质为一级。 If the spiral mode eigenvalue is negative, Level 1 flying quality is satisfied.
11、随着重心的前移，短周期频率将降低。 As CG moves forward, the short period natural frequency decreases.
12、螺旋模态，A种飞行阶段的要求高于B种和C种 For the spiral mode, the requirements for Category A is higher than those for Category B and C.
期末考试 Final Exam
期末考题 Final Exam
1、某飞机纵向受扰动后的迎角响应如下图所示，该飞机纵向静 ，动 。
A、稳定，稳定
B、稳定，不稳定
C、稳定，中立稳定
D、不稳定，中立稳定
E、不稳定，不稳定
F、不稳定，稳定
2、按照本课程的符号定义习惯（国际坐标系），绕y轴向上俯仰为 ，绕z轴向左偏航为 。
A、正，正
B、负，正
C、负，负
D、正，负
3、A种、B种及C种飞行阶段中，总体来说对飞行品质要求最高的是哪个阶段？
A、A种
B、B种
C、C种
D、D种
4、机翼对纵向静稳定性的贡献取决于重心位置，重心前移，飞机纵向静稳定性将 。
A、降低
B、提高
C、不变
D、可能提高也可能降低
5、对于静稳定飞机，随着升力系数的增加，为平衡飞机，升降舵需 产生 力矩。
A、上偏，抬头
B、下偏，抬头
C、上偏，低头
D、下偏，低头
6、加速飞行时， 操纵是符合飞行员操纵习惯的。
A、拉杆
B、推杆
C、左压杆
D、右压杆
7、在平均气动弦上，以下四个点中，位于最前面的是 。
A、握杆中性点
B、松杆中性点
C、握杆机动点
D、松杆机动点
8、按照本课程符号定义习惯，飞机 感受到来流时侧滑角为正，如果飞机能产生 偏航力矩，则飞机航向静稳定。
A、左侧，左
B、左侧，右
C、右侧，左
D、右侧，右
9、常规布局飞机的航向静稳定性最大来源是 。
A、垂尾
B、机翼
C、机身
D、平尾
10、尾旋时，飞机的迎角将超过50度，此时下列操纵面中仍可用的是 。
A、升降舵
B、副翼
C、鸭翼
D、方向舵
11、是飞机横向静稳定性的最大来源。
A、机身
B、平尾
C、机翼
D、垂尾
12、惯性轴系与地轴系之间相差了一个 。
A、航向角
B、滚转角
C、地球自转
D、地球公转
13、短周期自然频率主要取决于以下哪个参数？
A、
B、
C、
D、
E、
14、对于欧拉法坐标变换来说，变换顺序的不同会导致完全不同的坐标，其正确的变换顺序是 。
A、先x轴，再y轴，最后z轴
B、先z轴，再y轴，最后x轴
C、先x轴，再z轴，最后y轴
D、先z轴，再x轴，最后y轴
15、初始扰动不为0，操纵输入为0，对应的运动方程解即响应特性被称为 ，体现的是飞机的 。
A、自由响应，静稳定性
B、自由响应，动稳定性
C、强迫响应，静稳定性
D、强迫响应，动稳定性
16、滚转收敛模态的特征根主要取决于以下哪个参数？
A、
B、
C、
D、
E、
17、地面效应会使飞机的中性点 。
A、前移
B、后移
C、不变
D、上移
E、下移
18、松/握杆中性点及机动点是纵向的四个重要重心位置，下图标出了握杆中性点的位置，则其它三个重心位置按从前到后的顺序为：
A、
B、
C、
D、
19、垂尾对横向静稳定性的贡献是：
A、提高稳定性
B、降低稳定性
C、大迎角时提高稳定性，小迎角时降低稳定性
D、小迎角时提高稳定性，大迎角时降低稳定性
20、以下哪个气动补偿方式不是通过调节压心与铰链轴距离来降低铰链力矩的？
A、轴式补偿
B、角式补偿
C、内补偿
D、调整片
21、最大操纵力梯度对应的是一个重心 ，重心应位于该点 。
A、前限，之前
B、前限，之后
C、后限，之前
D、后限，之后
22、当飞机受到右侧滑时，垂尾会产生向 的力和向 偏航力矩。
A、右，右
B、右，左
C、左，右
D、左，左
23、螺旋桨滑流对航向静稳定性的影响是 。
A、提高稳定性
B、降低稳定性
C、不影响
D、取决于螺旋桨位置
24、飞机在做顺时针盘旋时，会由于内外侧机翼速度不等产生 偏航力矩。
A、左
B、右
C、上
D、下
25、当特征根是一对实部为负的共轭复根时，可用 描述其响应特性。
A、响应的半衰时
B、响应的倍幅时
C、响应包线的半衰时
D、响应包线的倍幅时
26、由下图的曲线可以判断该飞机纵向 。
A、静稳定
B、静不稳定
C、时静稳定，静不稳定
D、时静不稳定，静稳定
27、平尾对纵向静稳定性的贡献与以下哪个因素无关？
A、平尾面积
B、平尾距重心距离
C、平尾下洗角
D、平尾安装角
28、某纵向静稳定飞机存在跨音速勺型区现象，则该飞机在从亚音速加速至超音速过程中，飞行员应如何操纵驾驶杆？
A、始终推杆
B、始终拉杆
C、先推杆、再拉杆、再推杆
D、先拉杆、再推杆、再拉杆
29、当特征根是一对实部为负的共轭复根时，可用 描述其响应特性
A、响应的半衰时
B、响应的倍幅时
C、响应包线的半衰时
D、响应包线的倍幅时
30、当飞机在较小迎角下向右滚转时，其左侧机翼的迎角会 ，升力会 。
A、增加，增加
B、增加，减小
C、减小，增加
D、减小，减小
31、螺旋模态特征根为负时，其飞行品质为 。
A、一级
B、二级
C、三级
D、不可控
32、荷兰滚模态的频率主要取决于以下哪个参数？
A、
B、
C、
D、
33、机身在失速迎角前对纵向静稳定性的贡献为 。
A、提高
B、降低
C、小迎角时降低，大迎角时提高
D、小迎角时提高，大迎角时降低
34、对于上反无后掠机翼，上反角主要是通过改变 对横向静稳定性产生影响。
A、局部动压
B、弦向速度
C、局部侧滑角
D、局部迎角
35、飞机的纵向静稳定性与以下哪些参数有关？
A、机翼弯度
B、平尾尾容比
C、重心位置
D、飞机升力系数
36、对于纵向静稳定飞机，以下哪些临界状态是用来确定重心前限的？
A、起飞抬前轮
B、着陆拉平
C、
D、纵向静稳定
37、战斗机可采用 布局来保证大迎角和大M数下的航向静稳定性。
A、双垂尾
B、飞翼式
C、单垂尾+腹鳍
D、无尾
38、下列因素中，对横向静稳定性起增稳作用的有 .。
A、上单翼
B、下单翼
C、后掠角
D、上反角
39、基本体轴系与风轴系相差了哪几个角度？
A、迎角
B、侧滑角
C、滚转角
D、俯仰角
E、航迹角
40、对于常规布局飞机，以下哪些模态是横航向的运动模态？
A、滚转收敛模态
B、荷兰滚模态
C、短周期模态
D、长周期模态
E、螺旋模态
41、以下参数中，与荷兰滚模态特性相关的有哪些参数？
A、
B、
C、
D、
42、下列飞行阶段中，属于C种飞行阶段的有 。
A、起飞
B、着陆
C、爬升
D、巡航
E、复飞
F、精确跟踪
43、下列飞机中，属于IV类飞机的有哪些？
A、F-22
B、A-10
C、C-130
D、Tu-160
E、Su27
F、J-20
44、对于地面效应，以下哪些说法是对的？
A、机翼升力线斜率增加
B、平尾升力线斜率增加
C、中性点前移
D、下洗角增加
E、重心前限后移
45、以下哪些操纵面能产生滚转力矩？
A、升降舵
B、方向舵
C、扰流板
D、副翼
E、升降副翼
46、以下哪些情况满足一级品质要求？
A、战斗机A种飞行阶段Tr=1.2
B、战斗机B种飞行阶段Tr=1.2
C、战斗机C种飞行阶段Tr=1.2
D、运输机B种飞行阶段Tr=1.2
E、运输机C种飞行阶段Tr=1.2
47、以下哪些说法是对的？
A、握杆机动点是单位过载所需升降舵偏角为0对应的重心位置
B、握杆中性点是单位过载所需杆力为0对应的重心位置
C、松杆中性点是单位过载所需杆力为0对应的重心位置
D、松杆机动点是单位过载所需升降舵偏角为0对应的重心位置
E、松杆机动点是单位过载所需杆力为0对应的重心位置
48、对于无上反的后掠机翼来说，侧滑角会改变哪些参数？
A、垂直速度
B、展向速度
C、弦向速度
D、局部动压
49、对于实部为负的共轭复根，描述其对应模态的特征参数包括 。
A、半衰时
B、包线的半衰时
C、频率
D、阻尼比
E、包线的倍幅时
50、根据下图中的~曲线可以看出，该飞机纵向静稳定
51、中性点是飞机纵向中立稳定对应的重心位置
52、舰载机在起飞离舰瞬间，升力会突然增加。
53、在满足稳定性需求的前提下，重心位置越往前，机动性越高。
54、对于后掠机翼，左侧滑情况下，右侧机翼动压大于左侧机翼动压。
55、同样的飞机，重心适当后移可使飞机的配平性能提高。
56、螺旋桨滑流会提高航向静稳定性。
57、垂尾对横向静稳定性的贡献是提高。
58、特征方程的解被称为特征根，可以为一个实根或一对共轭复根，每一个实根或一对共轭复根对应的响应特性被称为模态。对于实根来说，特征根为正时，该模态稳定。
59、随着重心的前移，短周期频率将提高。
60、小展弦比的飞机，其滚转收敛模态特性通常要比大展弦比的好。
61、机翼对纵向静稳定性起的是增稳作用。
62、为降低操纵力，调整片应与操纵面同向偏转。
63、螺旋桨位于重心之前时，会起到提高航向静稳定性的作用
64、对于螺旋模态，A种飞行阶段的要求高于B种和C种。
65、右侧扰流板打开时，飞机会向右滚。
66、升力系数越高，后掠角对横向静稳定性的贡献越小。
Stability and Handling of Learning to Fly an Aircraft
Learning to fly an aircraft is an exhilarating and challenging experience. One of the most important aspects of flying is understanding the stability and handling of the aircraft. In this article, we will explore the concepts of stability and handling and how they apply to flying an aircraft.
Stability
Stability refers to the ability of an aircraft to maintain its desired flight path without the need for constant input from the pilot. There are three types of stability: static stability, dynamic stability, and control stability.
Static Stability
Static stability refers to the aircraft's tendency to return to its original position after being disturbed. This stability is essential for the safe operation of an aircraft. There are two types of static stability: positive and negative.
Positive static stability is when the aircraft returns to its original position after being disturbed. This is the desired type of stability for most aircraft. Negative static stability is when the aircraft continues to move away from its original position after being disturbed. This type of stability can be dangerous and requires constant input from the pilot to maintain control of the aircraft.
Dynamic Stability
Dynamic stability refers to the aircraft's ability to return to its original flight path after being disturbed by external forces such as gusts of wind or turbulence. This type of stability is important for maintaining a safe flight path in unpredictable conditions.
Control Stability
Control stability refers to the aircraft's response to pilot inputs. An aircraft with good control stability will respond predictably and smoothly to pilot inputs, making it easier for the pilot to maintain control of the aircraft.
Handling
Handling refers to how the aircraft responds to the pilot's inputs. There are two main components of handling: stability and maneuverability.
Stability
Stability is an essential component of handling. A stable aircraft will respond predictably to the pilot's inputs, making it easier for the pilot to maintain control of the aircraft.
Maneuverability
Maneuverability refers to the aircraft's ability to perform maneuvers such as turns, climbs, and descents. An aircraft with good maneuverability will be able to perform these maneuvers smoothly and efficiently.
Conclusion
Understanding the concepts of stability and handling is essential for learning to fly an aircraft. By understanding these concepts, pilots can maintain control of the aircraft in a variety of conditions, making flying safer and more enjoyable.
