飞机一般限制

航空

飞机一般限制

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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 - Limit load factors
2 - Maximum speed
3 - Minimum speed
4 - Other limitations ( environmental envelope and engine
limitations )
5 - Maximum structural weights
Table of Contents
A project supported by AIRBUS and the CAAC
Date of the module
1 - Limit load factors
2 - Maximum speed
3 - Minimum speed
4 - Other limitations ( environmental envelope engine limitations )
5 - Maximum structural weights
Table of Contents
A project supported by AIRBUS and the CAAC
Date of the module
 Aerodynamics loads
nz (load factor) g m
Acceleration
m
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
 Manoeuvering limit load factors
 - (JAR /FAR 25.1531, 25.333)
 Flaps retracted or slats extended:
 - 1 nz < + 2.5
 Flaps and slats extended:
 0 < nz < + 2
A project supported by AIRBUS and the CAAC
Date of the module
1 - Limit load factors
2 - Maximum speed
3 - Minimum speed
4 - Other limitations ( environmental envelope engine limitations )
5 - Maximum structural weights
Table of Contents
A project supported by AIRBUS and the CAAC
Date of the module
 Maximum operating limit speed (or Mach number)
- VMO (or MMO) - (JAR/FAR 25.1505)
Pressure
Altitude
CAS
VMO = 350
MMO = 0.82
A 320 - 200
24 600 ft
A project supported by AIRBUS and the CAAC
Date of the module
A project supported by AIRBUS and the CAAC
Date of the module
 Maximum manoeuvering speed: VA -
 (JAR/FAR 25.1507,25.335)
 Maximum speed at which the flight controls can be fully
deflected without structural damage
VA
full
SPEED
deflection
A project supported by AIRBUS and the CAAC
Date of the module
 Maximum manoeuvering speed: VA - (JAR /FAR 25.1507)
CAS
VMO = 350
MMO = 0.82
A 320 - 200
24 600 ft
VA
M = 0.78
250 350
Pressure
Altitude
A project supported by AIRBUS and the CAAC
Date of the module
 Maximum flaps extended operating speeds: VFE
(JAR/FAR 25.1511)
F la p s
le v e r
p o s itio n
E C AM
in d ic a tio n
S la ts
p o s itio n
F la p s
p o s itio n
V F E F lig h t
p h a s e
1 1 8 0 2 3 0 A p p ro a c h
1
1 + F 1 8 1 0 2 1 5 T a k e o ff
2 2 2 2 1 5 2 0 0
A p p ro a c h
T a k e o ff
3 3 2 2 2 0 1 8 5
L a n d in g
A p p ro a c h
T a k e o ff
F U L L F u ll 2 7 3 5 1 7 7 L a n d in g
A project supported by AIRBUS and the CAAC
Date of the module
 Maximum landing gear speeds: (JAR /FAR 25.1515)
 VLE (In flight: landing gear extended): 280 kt/ M 0.67
available when the landing gear is in the fully extended
position
A project supported by AIRBUS and the CAAC
Date of the module
 Maximum landing gear speeds: (JAR/FAR 25.1515)
 VLE (In flight: landing gear extended): 280 kt/ M 0.67
 VLO RET: (landing gear operating: retraction) : 220 kt
 VLO EXT: (landing gear operating: extension): 250 kt
 Maximum tyre speed:
 195 kt (ground speed)
A project supported by AIRBUS and the CAAC
Date of the module
1 - Limit load factors
2 - Maximum speed
3 - Minimum speed
4 - Other limitations ( environmental envelope engine limitations )
5 - Maximum structural weights
Table of Contents
A project supported by AIRBUS and the CAAC
Date of the module
 Definition - Reference stall
speed VSR (JAR 25.103)
 VSR  Vs1g
 Vs1g is the stall speed
under load factor (nz)
equal to 1:
(The aeroplane
can develop a lift equal to its
weight)
Remark: In JAR 25 VSR is
expressed as:
VCLMAX is the stall speed
under a load factor equal
to nzw
Vs g mg
oSCz
1  2
 max
zw
CLMAX
SR
n
V  V
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
 Vs1g
Stall condition 1
n=1
No altitude loss
Suitable for
VsFAR < Vs1g
A320,A330,A340,B777….
 VsFAR
Stall condition 2
n <1
Altitude loss
Suitable for swept wing aircraft
VsFAR < Vs1g
A300,A310,B757,B767….
A project supported by AIRBUS and the CAAC
Date of the module
A project supported by AIRBUS and the CAAC
Date of the module
 Minimum control speed, take off climb: VMCA -
(JAR/FAR 25.149)
 It is the calibrated airspeed, at which, when the critical engine
is suddenly made inoperative; it is possible to maintain the
control of the aeroplane (that engine remaining inoperative)
and maintain straight flight with angle of bank of not more than
5°
A project supported by AIRBUS and the CAAC
Date of the module
A project supported by AIRBUS and the CAAC
Date of the module
Minimum control speed on the ground :
VMCG - (JAR/FAR 25.149)
 It is the calibrated airspeed, during the take off ,at
which, when the critical engine is suddenly made
inoperative; it is possible to maintain the control of
the aeroplane with the use of the primary
aerodynamics controls alone
A project supported by AIRBUS and the CAAC
Date of the module
A project supported by AIRBUS and the CAAC
Date of the module
1 - Limit load factors
2 - Maximum speed
3 - Minimum speed
4 - Other limitations ( environmental envelope and engine
limitations )
5 - Maximum structural weights
Table of Contents
A project supported by AIRBUS and the CAAC
Date of the module
-5000
0
5000
10000
15000
20000
25000
30000
35000
40000
45000
-80 -60 -40 -20 0 20 40 60
ISA.
ISA + 35°C
Take off and landing
39 100 ft
8 000 ft
A 320 - 200 Environmental envelop
A project supported by AIRBUS and the CAAC
Date of the module
 Engine limitations - (JAR/FAR 25.1521)
Example: CFM56 - 5A1
Operating
Condition
Time
Limit
EGT
°C
MAXIMUM ROTOR
SPEED
N1% N2%
STARTING 725
MAX CONTINUOUS Continu 855
TAKE OFF
and
5 mn
(normal)
890 102 105
GO AROUND 10 mn
(one engine
out)
890 102 105
A project supported by AIRBUS and the CAAC
Date of the module
1 - Limit load factors
2 - Maximum speed
3 - Minimum speed
4 - Other limitations ( environmental envelope engine limitations )
5 - Maximum structural weights
Table of Contents
A project supported by AIRBUS and the CAAC
Date of the module
Structure
Systems
Propulsion
Empty weight
A project supported by AIRBUS and the CAAC
Date of the module
Empty weight
Cabin
equipment
Crew
Catering
Dry operating weight
(Dow)
Basic weight
(BW)
A project supported by AIRBUS and the CAAC
Date of the module
Dow
Traffic load
Zero fuel weight
(ZFW)
Take-off weight
(TOW)
Landing weight
Trip fuel
Reserve
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
Parking
Trip fuel Alternate fuel
Touchdown
Brakes release
En route
reserve
Go around
PROC
DEP Alternate
Holding
DEST
Taxi
fuel
A project supported by AIRBUS and the CAAC
Date of the module
 JAR OPS
 Route: GREATER of (5% of the
planned trip fuel or an amount
subject to the approval of the
authority) or (quantity to fly for 5
min at holding speed at 1500 ft
above destination)
 Alternate: Calculated to the most
distant alternate airport
 Holding: quantity to fly for 30 mn
at holding speed at 1500 ft above
the alternate airport
 FAR 121 - international flight
 Route: a quantity to fly during a
period equivalent to 10% of the
total flight time
(departure/destination)
 Alternate: idem
 Holding: idem
A project supported by AIRBUS and the CAAC
Date of the module
 Maximum weights
 Maximum structural take-off weight: MTOW
FAR/JAR 25: R/C= - 360ft/mn
tow <= MTOW (1)
A project supported by AIRBUS and the CAAC
Date of the module
 Maximum weights
 Maximum structural take-off weight: MTOW
 Maximum structural landing weight: MLW
FAR/JAR 25: R/C = - 600ft/mn
lw = tow - TF <= MLW
or tow <= MLW + TF (2)
A project supported by AIRBUS and the CAAC
Date of the module
 Maximum weights
 Maximum structural take-off weight: MTOW
 Maximum structural landing weight: MLW
 Maximum zero fuel weight: MZFW
mg
A project supported by AIRBUS and the CAAC
Date of the module
 Maximum weights
 Maximum zero fuel weight: MZFW
Max efforts at the root for m = const when mWF=0
mg
L/2 L/2
mWFg mWFg
nz > 1
A project supported by AIRBUS and the CAAC
Date of the module
 Maximum weights
 Maximum structural take-off weight: MTOW
 Maximum structural landing weight: MLW
 Maximum zero fuel weight: MZFW
zfw <= MZFW
tow <= MZFW + take-off fuel
( tow = zfw + take-off fuel )
(3)
A project supported by AIRBUS and the CAAC
Date of the module
 Effects on fueling
1 -Wing tanks
2 - Fuselage tanks
mg
mFFg
A project supported by AIRBUS and the CAAC
Date of the module
 Effects on fuel management
1 - Fuselage tanks
2 -Wing tanks
mg
A project supported by AIRBUS and the CAAC
Date of the module
 Effects on fuel management
mg
mFFg
Opposite case
when mWF = 0 zfw = dow + load + mFF <= MZFW
A project supported by AIRBUS and the CAAC
Date of the module
 Maximum weights
» Maximum structural take-off weight: MTOW
» Maximum structural landing weight: MLW
» Maximum zero fuel weight: MZFW
» Maximum ground-taxiing weight: MGTW

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