flight operation 飞行运行概述(21)

曝光台 注意防骗 网曝天猫店富美金盛家居专营店坑蒙拐骗欺诈消费者

when thrust > drag
 climb
Thrust and drag
A project supported by AIRBUS and the CAAC
Date of the module
1 - International standard atmosphere
2 - Altimetry principle
3 - Operating speeds
4 - Flight mechanics
Table of Contents
A project supported by AIRBUS and the CAAC
Date of the module
Balance of forces for steady level flight at
constant speed
lift
thrust
weight = mg
drag
lift = weight
thrust = drag
A project supported by AIRBUS and the CAAC
Date of the module
 Lift equation :
 Weight = ½  S (TAS)2 CL
 Drag equation :
 Thrust = ½  S (TAS)2 CD
 Power equation :
 Power = Thrust × TAS = ½  S (TAS)3 CD
A project supported by AIRBUS and the CAAC
Date of the module
 As a function of Mach number :
 Weight = 0.7 S PS M2 CL
 Thrust = 0.7 S PS M2 CD
 As a function of P0 :
the pressure ratio  = PS/P0 is introduced
(P0 pressure at ZP = 0) :
 Weight /  = 0.7 S P0 M2 CL
 Thrust /  = 0.7 S P0 M2 CD
A project supported by AIRBUS and the CAAC
Date of the module
Balance of forces in climb Gza
TAS
Gx
Gxa
W= mg
Gz
L
T D

ground
datum line
aerodynamics
datum line
aircraft
datum line

 : climb angle
 : angle of attack
flight attitude
A project supported by AIRBUS and the CAAC
Date of the module
angle of attack
climb angle 
climb
Thrust
climb angle 
TAS



 flight attitude
TAS

TAS
Rate of
climb
(RC)
Climb Angle and Rate of Climb
Angle of attack 
Thrust
  0    
climb angle
RC = TAS sin
A project supported by AIRBUS and the CAAC
Date of the module
 Longitudinal axis :
 Thrust = Drag + weight sin
 Vertical axis :
 Lift = Weight cos
 if  is small  sin tan   cos  1
 Thrust = Drag + Weight 
 Lift = Weight
 = Thrust - Drag
Weight
A project supported by AIRBUS and the CAAC
Date of the module
Thrust as a function of speed
D,T
Speed
thrust
drag
Given
m, t°C, Zp,
thrust lever position
A project supported by AIRBUS and the CAAC
Date of the module
 Expression of the climb angle :
 Expression of the rate of climb
RC = TAS . 
 = 100 Thrust
Weight
1
L/D
RC (ft/mn)  TAS (kt) .  (%)
A project supported by AIRBUS and the CAAC
Date of the module
Balance of forces in descent

TAS
Gx
Gxa
Gza Gz
L
W= mg
T D
ground
datum line
aerodynamics
datum line
aircraft
datum line

 : descent angle
 : angle of attack
flight attitude
A project supported by AIRBUS and the CAAC
Date of the module
 Gradient of descent :
 if Thrust  0 (Idle)
 Rate of descent :
 = Thrust - Drag
Weight
< 0
 = - 100 1
L/D
RC (ft/mn)  TAS (kt) .  (%)
A project supported by AIRBUS and the CAAC
Date of the module
D/ 
M
increasing W/ 
D/as a function of Mach number
A project supported by AIRBUS and the CAAC
Date of the module
gradient
D,T
Speed
thrust
drag
climb
Speed
max
L/Dmax
Given
m, t°C, Zp
cruise speed
climb speeds
Climb gradient
versus speed
Climb gradient is maximum
when the Drag is minimum
or L/D maximum
A project supported by AIRBUS and the CAAC
Date of the module
• Table of contents
• Flight operations duties
• European Applicable Regulation
　
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