气压，高度，飞行，速度

航空发表于 2010-7-25 15:57:40

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航空发表于 2010-7-25 15:57:59

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: P = 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

忙盲忙 发表于 2010-7-28 08:55:49

楼主辛苦啦！

凌晨一点 发表于 2010-7-31 15:49:46

辛苦啦楼主

f214216709 发表于 2010-8-2 13:52:42

飞行气象？

21372770 发表于 2010-8-16 17:10:04

check it out

胖子发表于 2010-9-2 00:02:15

非常感谢:) :)

wangchen 发表于 2010-9-2 11:58:08

接收新回复邮件通知

gjsx 发表于 2010-9-9 07:55:28

A project supported by AIRBUS and the CAAC

desperado 发表于 2010-9-9 15:22:49

桂林民航气象预报的现状

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航空论坛_航空翻译_民航英语翻译_飞行翻译's Archiver

气压，高度，飞行，速度

楼主辛苦啦！