签派执照考试书V3 飞机性能载重平衡部分 A319/B737为例 4.32水平安定面配平

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1 签派执照考试书V3 飞机性能载重平衡部分 A319/B737为例 4.32水平安定面配平

2 Takeoff Horizontal Stabilizer Trim Setting
A horizontal stabilizer trim setting is used during all takeoffs. These settings are designed to produce: The proper all-engines operating climb-out attitude at V to 25 kts The proper one-engine inoperative climb-out attitude at V2 Reasonable column forces for the pilots Trim setting is provided as a function of the airplane weight, C.G., flap setting, and engine thrust level.

3 Takeoff Horizontal Stabilizer Trim Setting
Lift Lift (downward) Thrust Weight Downward force from the horizontal tail is used to rotate the airplane about the main gear for takeoff rotation, and to hold the airplane in the correct pitch attitude for the climb-out from the airport after liftoff. (Drag contribution to moment about CG is negligible)

4 Horizontal Stabilizer Movement

5 Horizontal Stabilizer Jackscrew

6 Trim Setting on Flight Deck
Example

7 Takeoff Horizontal Stabilizer Trim Setting
ER Example AND = Airplane Nose Down ANU = Airplane Nose Up Increasing downward tail force Decreasing downward tail force

8 Takeoff Horizontal Stabilizer Trim Setting
ER With High Thrust Engines (>90K)

9 Determining the Stabilizer Trim Setting
Takeoff weight = 220,000 kg Center of gravity = 39%MAC ER Example Stab Trim Units = 3.0

10 Determining the Stabilizer Trim Setting
ER Example AIRPLANE GROSS WEIGHT - KILOGRAMS 110000 120000 130000 140000 150000 160000 170000 180000 190000 200000 210000 220000 230000 240000 250000 7 9 18 20 22 24 26 28 30 32 34 36 38 40 42 44 %MA C 8 5 4 3 6 Stabilizer Trim Units Flaps 15 & 20 Full Thrust to 15% Derate kg 39

11 力矩 The influence of an item depends on 2 factors : 力 Weight
力臂 Harm（ARM） : item CG position 力矩Moment = Weight  Harm

12 The Mean Aerodynamic Chord and the CG index
Airplane c.g. is often expressed in terms of %m.a.c. BA of airplane c.g. Datum for B.A. lemac Where: BA is the balance arm of the airplane’s c.g. c.g. is in terms of %m.a.c.

13 重心的表示方法

14 Definition of the Reference Chord
Z 25%RC 18.850m 4.1935m m 2.540m H-arm 0 X

15 Definition of the Reference Chord
Z 25%RC MAC LEMAC H-arm 0 X

16 4.32 水平安定面 问题(P170)： ,P141,R-1条件, 重量=90,000 KG, CG= INCH, LEMAC=625, MAC=134 解:CG - LEMAC = – 625 = 10.7 %MAC=10.7 / 134 =8.0 % (P138) 查表=7 ¾ ANU

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19 Data in the （M）CDU 43,500 43,750 + 3,700 + 10,080 57,530 71,530 3 2 8 3 6 3

20 MANIFEST1-成图

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23 平衡图 （ 表 ）各项注释

24 WB例题平衡图填写过程

25 根据飞机起飞襟翼和起飞重心%MAC的位置查出相应尾翼配平数值
WB例题平衡图填写过程 根据飞机起飞襟翼和起飞重心%MAC的位置查出相应尾翼配平数值 FLAP5

26 WB划线法平衡图图样

27 WB平衡图划线法填写过程 根据无油和起飞的总指数、总重量划出飞机重心位置%MAC
TOW ZFW 17.9 16.5 5

28 问题？讨论？ 谢谢