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航空

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航空

A project supported by AIRBUS and the CAAC
Date of the module
• Table of contents
• Flight operations duties
• European Applicable Regulation
• General
• General aircraft limitations
• Payload Range
• Operating limitations
• In flight performance
• One engine inoperative performance
• Flight planning
• weight and balance
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
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
-60 -40 -20 0 20 40 60
2
4
6
8
10
12
Altitude
Sea level
TROPOSPHERE
TROPOPAUSE
STRATOSPHERE
-56.5°C 15°C
Temperature
(°C)
(km)
5000
10000
15000
20000
25000
30000
35000
40000
(ft)
subsonic jet
transport
cruise level
International Standard Atmosphere
A project supported by AIRBUS and the CAAC
Date of the module
A project supported by AIRBUS and the CAAC
Date of the module
International Standard Atmosphere
pressure altitude (Zp)
500 850 1013.25
Ps
200 250 300 (hPa)
Zp = f(P) ISA table
2
4
6
8
10
12
5000
10000
15000
20000
25000
30000
35000
40000
(ft) (km)
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
Zi
Zpamb
Zpset
Zp
pressure altitude
0
Pamb Pset 1013.25 (hPa)
Ps
Zp = f(Ps) ISA Table
Altimetry principle
A project supported by AIRBUS and the CAAC
Date of the module
A project supported by AIRBUS and the CAAC
Date of the module
Altimeter function on PFD
A project supported by AIRBUS and the CAAC
Date of the module
Standard setting: 1013.25 hPa
QNH setting
QFE setting
Radio
height
(AAL)
Height
Altitude Flight
Level
QNH QFE 1013
Altimeter setting
A project supported by AIRBUS and the CAAC
Date of the module
A project supported by AIRBUS and the CAAC
Date of the module
QNH
1013 hPa
sea level
descent
approach
1013 1013
take-off
climb
QNH
QNH
Altimeter setting
Transition
altitude
Transition
level
A project supported by AIRBUS and the CAAC
Date of the module
A project supported by AIRBUS and the CAAC
Date of the module
A project supported by AIRBUS and the CAAC
Date of the module
Zi
(QNH)
Za
ISA
ISA + 30°
ISA - 30°
Temperature effect on true altitude
A project supported by AIRBUS and the CAAC
Date of the module
A project supported by AIRBUS and the CAAC
Date of the module
1013
STD + Za > Zi
1013
STD Za = Zi
1013
STD - Za < Zi
Temperature effect on true altitude
A project supported by AIRBUS and the CAAC
Date of the module
A project supported by AIRBUS and the CAAC
Date of the module
OM
Za = cst
STD + STD STD -
Zi = Za
Zi < Za Zi > Za
Temperature effect on the altimeter indication
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
Impact pressure pick-off
(Stby + Capt.)
F/O on the other side
Static ports
(Stby + F/O + Capt.)
symmetrical on the other side,
to avoid yaw errors
Pitot and static probes
A project supported by AIRBUS and the CAAC
Date of the module
P0
Pi P0
Dynamic:  = Pi - PS Static: PS
Air flow: V
Impact pressure pick-off: Pi Static port
Vi
Speed measurement
A project supported by AIRBUS and the CAAC
Date of the module
Wind TAS
GS DA
GS = Ground Speed
DA = Drift Angle
TAS = True Air Speed
Ground speed and drift angle
A project supported by AIRBUS and the CAAC
Date of the module
A project supported by AIRBUS and the CAAC
Date of the module
Speed conversion summary
DENSITY CORRECTION = 120
TAS = 445 kt
COMPRESSIBILITY
CORRECTION = -10 kt
POSITION ERROR
CORRECTION = +2 kt
CAS = 335 kt
IAS = 333 kt
FL 200
IAS = 333 kt
POSITION ERROR
CORRECTION = -1 kt
TAS = CAS = 332 kt
SEA
LEVEL
Air speed (kt)
250 300 350 400 450
Altitude
A project supported by AIRBUS and the CAAC
Date of the module
True Air Speed variation
300 / 0.78 climb
200 250 300 350 400 450 500
50
100
150
200
250
300
350
400
450
tropopause
iso CAS 300
FL
TAS (kt)
iso Mach 0.78
A project supported by AIRBUS and the CAAC
Date of the module
when thrust = drag
 level flight
when thrust < drag
 descent
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

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A project supported by AIRBUS and the CAAC

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