2 aircraft flight instruments
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2 aircraft flight instruments
- 1. Aircraft Flight Instruments SOLO HERMELIN Updated: 04.12.12 1
- 2. Table of Content SOLO Aircraft Avionics 2
- 3. McDonnell Douglass F-4B Phantom Instrument Panel 3
- 4. McDonnell Douglass F-4 Phantom Cockpit 4
- 8. The basic variables representing the thermodynamics state of the gas are the Density, ρ, Temperature, T and Pressure, p. SOLO 8 Earth Atmosphere • The Density, ρ, is defined as the mass, m, per unit volume, v, and has units of kg/m3 . v m v ∆ ∆ = →∆ 0 limρ • The Temperature, T, with units in degrees Kelvin ( ͦ K). Is a measure of the average kinetic energy of gas particles. • The Pressure, p, exerted by a gas on a solid surface is defined as the rate of change of normal momentum of the gas particles striking per unit area. It has units of N/m2 . Other pressure units are millibar (mbar), Pascal (Pa), millimeter of mercury height (mHg) S f p n S ∆ ∆ = →∆ 0 lim kPamNbar 100/101 25 == ( ) mmHginHgkPamkNmbar 00.7609213.29/325.10125.1013 2 === The Atmospheric Pressure at Sea Level is:
- 9. Speed of Sound (a) This is the speed of sound waves propagation in ambient air. The speed of sound is given by SOLO 9 Earth Atmosphere Sa TRa ⋅⋅= γ γ air = 1.4 Ra =287.0 J/kg--ͦ K TS – Static Air Temperature True Airspeed (TAS) The True Airspeed is the speed of the aircraft’s center of mass with respect to the ambient air through which is passing. Indicated Airspeed (IAS) The Indicated Airspeed is the speed indicated by a differential-pressure airspeed indicator.
- 10. Mach Number (M) Is the ratio of the TAS to the speed of sound at the flight condition. SOLO 10 Earth Atmosphere aTASM /= Dynamic Pressure (q) The force per unit area required to bring an ideal (incompressible) fluid to rest: q=1/2∙ρ∙VT 2 (where VT is True Air Speed-TAS, and ρ is the density of the fluid). Impact Pressure (QC) The force per unit area required to bring moving air to rest. It is the pressure exerted at the stagnation point on the surface of a body in motion relative to the air. PT – Total Pressure, PS – Static Pressure 2 2/1 TSTC VPPQ ⋅⋅=−= ρ
- 11. SOLO Aircraft Avionics 11 Air Data Computer Air Data Computer uses Total and Static Pressure and Static Temperature of the external Air Flow, to compute Flight Parameters.
- 12. 12 Earth Atmosphere Atmospheric Constants Definition Symbol Value Units Sea-level pressure P0 1.013250 x 105 N/m2 Sea-level temperature T0 288.15 ͦ K Sea-level density ρ0 1.225 kg/m3 Avogadro’s Number Na 6.0220978 x 1023 /kg-mole Universal Gas Constant R* 8.31432 x 103 J/kg-mole -ͦ K Gas constant (air) Ra=R*/M0 287.0 J/kg--ͦ K Adiabatic polytropic constant γ 1.405 Sea-level molecular weight M0 28.96643 Sea-level gravity acceleration g0 9.80665 m/s2 Radius of Earth (Equator) Re 6.3781 x 106 m Thermal Constant β 1.458 x 10-6 Kg/(m-s-ͦ K1/2) Sutherland’s Constant S 110.4 ͦ K Collision diameter σ 3.65 x 10-10 m
- 13. SOLO Aircraft Avionics 13 Flight Instruments Air Data Calculation (Collison) Geopotential Pressure Altitude • Low Altitude (Troposphere) : H< 11000 m (36.089 ft ), ( ) kPaHPS 255879.55 1025577.21325.101 ⋅⋅−⋅= − • Medium Altitude: 11000 m ≤ H ≤ 20000m (36.089 ft - 65.617 ft ) ( ) kPaeP H S 000,1110576885.1 4 6325.22 −⋅⋅− − ⋅= Air Density Ratio ρ/ρ0 S S T P ⋅ = 35164.00ρ ρ
- 14. SOLO Aircraft Avionics 14 Flight Instruments Air Data Calculation (Collison) Mach Number • Subsonic Speeds (M ≤ 1), ( ) 2/72 2.01 M P P S T ⋅+= • Supersonic Speeds (M ≥ 1), Static Air Temperature TS ͦ K 10 2.01 2 << ⋅⋅+ = r Mr T T m S ( ) 2/52 7 17 9.166 −⋅ ⋅ = M M P P S T True Airspeed (TAS) VT m/s smTMV ST /0468.20 ⋅⋅=
- 15. SOLO Aircraft Avionics 15 Flight Instruments Air Data Calculation (Collison) Speed of Sound a m/s • Subsonic Speeds (VC ≤ a), • Supersonic Speeds (VC ≥ a), Sa TRa ⋅⋅= γ γ air = 1.4, Ra =287.0 J/kg--ͦ K Calibrated Airspeed (CAS) VC m/s kPa V Q C C − ⋅+⋅= 1 294.340 2.01325.101 2/72 kPa V V Q C C C − − ⋅ ⋅ ⋅= 1 1 294.340 7 294.340 92.166 325.101 2/7 2/52 2
- 16. 16 Central Air Data Computer Earth Atmosphere
- 17. 17 Central Air Data Computer Earth Atmosphere
- 18. Flight Instruments SOLO Aircraft Avionics 18 The Flight Panel - Understand Your Aircraft, Youtube
- 21. Flight Instruments SOLO Aircraft Avionics 21 zdgpd ⋅⋅−= ρ TRp ⋅⋅= ρ KsmR 22 /287= zdaTd ⋅−= aR g T za p p ⋅ ⋅ −= 00 1
- 23. SOLO Aircraft Avionics 23 Flight Instruments Airspeed Indicators
- 24. SOLO Aircraft Avionics Flight Instruments Airspeed Indicators Centurion T210 AirSpeed Gauge
- 25. SOLO Aircraft Avionics 25 Flight Instruments Airspeed Indicators 2 2 1 vpp StatTotal ⋅+= ρ The airspeed directly given by the differential pressure is called Indicated Airspeed (IAS). This indication is subject to positioning errors of the pitot and static probes, airplane altitude and instrument systematic defects. The airspeed corrected for those errors is called Callibrated Airspeed (CAS). Depending on altitude, the critic airspeeds for maneuvre, flap operation etc change because the aerodynamic forces are function of air density. An equivalent airspeed VE (EAS) is defined as follows: 0ρ ρ VVE = V – True Airspeed ρ – Air Density ρ0 – Air Density at Sea Level
- 26. SOLO Aircraft Avionics 26 Flight Instruments Airspeed Indicators 2 2 1 VPQPP StatCStatTotal ⋅+=+= ρ V – True Airspeed ρ – Air Density ρ0 – Air Density at Sea Level Air Density changes with altitude. Assuming an Adiabatic Flow, the relation between Pressure and Density is given by constC P ==γ ρ γ = Cp/CV= 1.4 for air Momentum differential equation for the Air Flow is VdV C P PdVdVPd C P γρ γ ρ /1 /1 0 +=+= = Subsonic Speeds SoundofSpeed P a S ρ γ ⋅ =
- 27. SOLO Aircraft Avionics 27 Flight Instruments Airspeed Indicators In the free stream P = PS and V = VT, At the Probe face P = PT and V=0 0 1 0 /1 /1 =+ ∫∫ T T S V P P VdV C PdP γ γ Subsonic Speeds (continue) 2 1 1 2 /1 11 T ST V C PP γ γ γ γ γ γ γ = − − −− γγ ρ /1/1 1 SPC = 1 2 12 2 1 1 2 1 1 2 − = − ⋅ − += ⋅⋅ − += γ γ ρ γ γ γ γ γ ργ a V V PP P T P a T SS T S − ⋅ − += −=−= − 1 2 1 11 1 2 γ γ γ a V P P P PPPQ T S S T SSTC
- 28. SOLO Aircraft Avionics 28 Flight Instruments Airspeed Indicators In the free stream P = PS and V = VT, At the Probe face P = PT and V=0 Supersonic Speeds 1 1 2 12 1 1 1 2 2 1 − − + − − ⋅ + ⋅ + = γ γ γ γ γ γ γ γ a V a V P P T T S T − + − − ⋅ + ⋅ + = −=−= − − 1 1 1 1 2 2 1 1 1 1 2 12 γ γ γ γ γ γ γ γ a V a V P P P PPPQ T T S S T SSTC Assume Supersonic Adiabatic Air Flow we obtain
- 29. SOLO Aircraft Avionics 29 Flight Instruments Airspeed Indicators Mach Number 1 1 2 1 2 1 1 1 2 2 1 − − + − −⋅ + ⋅ + = γ γ γ γ γ γ γ γ M M P P S T Subsonic Speeds (M ≤ 1) γ γ γ 1 1 2 1 − ⋅ − −== S TT P P a V M 12 2 1 1 2 − = ⋅ − += γ γρ γ γ M P P SP a S T From Supersonic Speeds (M ≥ 1)
- 30. SOLO Aircraft Avionics 30 Flight Instruments Airspeed Indicators (Calibrated Airspeed) Calibrated Airspeed is obtained by substituting the Sea Level conditions, that is PS = PS0 , VT = VC , a0 = 340.294 m/s. Subsonic Speeds (VC < a0=340.294 m/s) − ⋅ − += − 1 2 1 1 1 2 0 0 γ γ γ a V PQ C SC 2 0 00 2 0 2 0 2 1 /2 1 2 1 C S C S C S aV C V P V P a V PQ C ⋅⋅= ⋅ ⋅⋅= − ⋅+≈ << ρ ργ γγ Supersonic Speeds (VC > a0=340.294 m/s) − + − − ⋅ + ⋅ + = − − 1 1 1 1 2 2 1 1 1 2 0 12 0 0 γ γ γ γ γ γ γ γ a V a V PQ C C SC ( ) mmHginHgkPamkNmbarPS 00.7609213.29/325.10125.1013 2 0 ==== γ air = 1.4
- 31. SOLO Aircraft Avionics 31 Flight Instruments Airspeed Indicators By measuring (TT) the Temperature of Free Airstream TS, we can compute the local Speed of Sound Sa TRa ⋅⋅= γ True Airspeed (TAS) By using the Mach Number computation we can calculate the True Airspeed (TAS) M M T RMTRMaV T aSaT ⋅ ⋅ − + ⋅⋅=⋅⋅⋅=⋅= 2 2 1 1 γ γγ
- 32. SOLO Aircraft Avionics 32 Flight Instruments Goodrich Air Data Handbook – Basic Air Data Calculation Altitude • Low Altitude: h<36.089 ft = 11000 m, PS > 6.6832426 in Hg ( ) ( ) 190255.0 1 190255.0 190255.0190255.0 140000131252.092126.29 140000131252.0 92126.29 hP P h S S ⋅−= − = • Medium Altitude: 36.089 ft = 11000 m ≤ h ≤ 65.617 ft = 20000m 6.6832426 in Hg> PS > 1.6167295 in Hg ( )h S S eP P h ⋅− ⋅= − = 30000480635.07345726.1 6832426.6 30000480635.0 6832426.6 ln7345726.1 163156.34 163156.34 1 96.710793 16.645177 6167295.116.645177 6167295.1 96.710793 − − + ⋅=− ⋅= h P P h S S • High Altitude: h >65.617 ft = 20000m, PS < 1.6167295 in Hg
- 33. SOLO Aircraft Avionics 33 Flight Instruments Goodrich Air Data Handbook – Basic Air Data Calculation Impact Pressure STC PPQ −= where: QC=½∙ ρ∙V2 = Impact Pressure PT = Total Pressure PS = True Static Pressure Indicated Airspeed (IAS) 11 92126.29 1026.1479 7/2 − +⋅= CQ IAS Subsonic Flight (M ≤ 1) − +⋅= 1 1026.1479 192126.29 2/72 IAS QC Supersonic Flight (M ≥ 1) − − ⋅ ⋅= 1 1 4748.661 7 6 8411.603 92126.29 2/5 2 7 IAS IAS QC where: IAS = Indicated Airspeed in knots QC = PT – PS Impact Pressure in Hg
- 34. SOLO Aircraft Avionics 34 Flight Instruments Goodrich Air Data Handbook – Basic Air Data Calculation Mach Number M = TAS/a − ⋅= − +⋅= 15115 7/27/2 S T S C P P P Q M Subsonic Flight (M ≤ 1) Supersonic Flight (M ≥ 1) 1 17 2.7 2.11 2/5 2 2 2 − −⋅ ⋅ ⋅=−= M M M P P P Q S T S C where: TAS = True Airspeed in knots a = Speed of Sound in knots where: QC=½∙ ρ∙V2 = Impact Pressure in Hg PT = Total Pressure in Hg PS = True Static Pressure in Hg
- 35. SOLO Aircraft Avionics 35 Flight Instruments Goodrich Air Data Handbook – Basic Air Data Calculation Mach Number M = TAS/a Altitude (feet) 75 KIAS (Qc=0.2701 In Hg) 100 KIAS (Qc=04814 In Hg) 200 KIAS (Qc=1.9589 In Hg) 300 KIAS (Qc=4.5343 In Hg) 400 KIAS (Qc=8.3850 In Hg) 500 KIAS (Qc=13.7756 In Hg) 600 KIAS (Qc=21.0749 In Hg) 700 KIAS (Qc=30.7642 In Hg) S.L. .113 .151 .302 .454 .605 .756 .907 1.058 10,000 .137 .182 .363 .541 .716 .888 1.057 1.230 20,000 .167 .222 .440 .651 .854 1.047 1.242 1.453 30,000 .207 .276 .541 .791 1.023 1.248 1.489 1.754 40,000 .262 .347 .672 .965 1.236 1.520 1.829 2.171 50,000 .331 .438 .831 1.171 1.509 1.875 2.276 2.717 60,000 .418 .549 1.014 1.426 1.862 2.335 2.852 3.419 70,000 .524 .684 1.230 1.754 2.318 2.928 3.592 4.318 80,000 .653 .842 1.497 2.172 2.897 3.678 4.526 5.450
- 36. SOLO Aircraft Avionics 36 Flight Instruments Goodrich Air Data Handbook – Basic Air Data Calculation Static Temperature 2 2.01 M T T T S ⋅+ = True Airspeed (TAS) where: TS = Static Temperature ͦK TT = Total Temperature ͦK ⋅+ ⋅⋅== 2 2.01 96695.38 M T MMTAS T a where: TAS = True Airspeed M = Mach a = Speed of Sound TT = Total Temperature ͦK
- 37. SOLO Aircraft Avionics 37 Flight Instruments Airspeed Indicators
- 38. Vertical Speed Indicator SOLO 38 Aircraft Avionics Flight Instruments
- 39. SOLO 39 Aircraft Avionics Flight Instruments Airspeed Indicator (ASI) White Arc – Flaps Operation Range VSO – Stalling Speed Flaps Down VSI - Stalling Speed Flaps Up VFE – Maximum Speed Flaps Down (Extendeed) Green Arc – Normal Operation Range VNO – Maximum Speed Normal Operation Yellow Arc - Caution Range VNE – Not to Exceed Speed Private Pilot Airplane – Flight Instruments ASA, Movie
- 42. SOLO 42 Aircraft Avionics Flight Instruments Gyroscopic Flight Instruments Turn Indicator
- 43. SOLO 43 Aircraft AvionicsFlight Instruments Attitude Indicator
- 44. SOLO 44 Aircraft AvionicsFlight Instruments Attitude Indicator
- 45. SOLO 45 Aircraft Avionics Flight Instruments Turn Coordinator
- 46. SOLO 46 Aircraft Avionics Flight Instruments Turn-and Slip Indicator
- 47. SOLO 47 Aircraft Avionics Flight Instruments Attitude Heading Reference
- 48. SOLO 48 Aircraft Avionics Flight Instruments Heading Indicator The Magnetic Compass is sensitive to Inertia Forces. It is a reliable Heading Instrument in the long yerm, but during maneuvers it may swing and be hardly reliable. To provide a more precise Heading Instrument a Directional Gyro is used.
- 50. SOLO 50 Aircraft Avionics Flight Instruments Flux Gate Compass System The Gate Compass System is connected to Radio Magnetic Indicator (RMI) and to Heading Situation Indicator (HSI). Heading Situation Indicator (HSI).Radio Magnetic Indicator (RMI)
- 56. SOLO 56 Aircraft Avionics Flight Displays Chelton’s Flight Logic Reconfigurable Panel Display
- 57. SOLO 57 Aircraft Avionics Flight Displays Avidyne’s Entegra Reconfigurable Panel Display
- 61. SOLO 61 Aircraft Avionics Flight Instruments Automatic Dependent Surveillance (ADS)
- 68. SOLO 68 Aircraft Avionics Navigation Instrument Landing System (ILS)
- 74. SOLO 74 Aircraft Avionics To be replaced
- 75. SOLO 75 Aircraft Avionics Aerodynamics of Flight
- 76. 76 SOLO Technion Israeli Institute of Technology 1964 – 1968 BSc EE 1968 – 1971 MSc EE Israeli Air Force 1970 – 1974 RAFAEL Israeli Armament Development Authority 1974 – 2013 Stanford University 1983 – 1986 PhD AA
- 77. 77 SOUND WAVESSOLO Disturbances propagate by molecular collision, at the sped of sound a, along a spherical surface centered at the disturbances source position. The source of disturbances moves with the velocity V. -when the source moves at subsonic velocity V < a, it will stay inside the family of spherical sound waves. -when the source moves at supersonic velocity V > a, it will stay outside the family of spherical sound waves. These wave fronts form a disturbance envelope given by two lines tangent to the family of spherical sound waves. Those lines are called Mach waves, and form an angle μ with the disturbance source velocity: a V M M = = − & 1 sin 1 µ
- 78. 78 SOUND WAVESSOLO Sound Wave Definition: ∆ p p p p p1 2 1 1 1= − << ρ ρ ρ2 1 2 1 2 1 = + = + = + ∆ ∆ ∆ p p p h h h For weak shocks u p 1 2 = ∆ ∆ρ 1 1 11 1 1 1 1 1 2 1 2 1 1 uuuuuu ρ ρ ρ ρρρ ρ ρ ρ ∆ −≅ ∆ + = ∆+ ==)C.M.( ( ) ( ) ppuuupuupu ∆++ ∆ −=+=+ 11 1 11122111 2 11 ρ ρ ρρρ)C.L.M.( Since the changes within the sound wave are small, the flow gradients are small. Therefore the dissipative effects of friction and thermal conduction are negligible and since no heat is added the sound wave is isotropic. Since au =1 s p a ∂ ∂ = ρ 2 valid for all gases
- 79. 79 SPEED OF SOUND AND MACH NUMBERSOLO Speed of Sound is given by 0= ∂ ∂ = ds p a ρ RT p C C T dT R C p T dT R C d dp d R T dT Cds p dp R T dT Cds v p v p ds v p γ ρ ρ ρ ρ ρ === ⇒ =−= =−= =00 0 but for an ideal, calorically perfect gas ρ γγ ρ p RTa TChPerfectyCaloricall RTpIdeal p == = = The Mach Number is defined as RT u a u M γ == ∆ 1 2 1 1 111 −− = = = γ γ γ γ γ ρ ρ a a T T p p The Isentropic Chain: a ad T Tdd p pd sd 1 2 1 0 − = − ==→= γ γ γ γ ρ ρ γ
- 80. 80 NORMAL SHOCK WAVESSOLO Normal Shock Wave ( Adiabatic), Perfect Gas G Q= =0 0, Mach Number Relations (1) ( ) ( ) ( ) ( ) 12 2 2 2 1 2 1 2 2 22 2 2 1 22 1 2 2 2 2 22 1 1 2 1 12 22 2 11 1 2 2 221 2 11 2211 2 1 2 1 2 1 2 1 * 12 1 2 1 12 1 1 4.. ... .. uu u a u a uaa uaa au h a u h a EC uu u p u p pupuMLC uuMC p a −=− − − + = − − + = → − + =+ − =+ − →−=−→ +=+ = ∗ ∗ = γγ γγ γγ γ γ γγ ρρρρ ρρ ρ γ Field Equations: 122 2 2 1 1 2 2 1 2 1 2 1 2 1 uuu u a u u a −= − + + − − − + ∗∗ γ γ γ γ γ γ γ γ u u a1 2 2 = ∗ u a u a M M1 2 1 21 1∗ ∗ ∗ ∗ = → = Prandtl’s Relation u p ρ T e u p ρ T e τ 11 q 1 1 1 1 1 2 2 2 2 2 1 2 ( ) γ γ γ γ γ γ γ γ γ γ 2 1 2 1 1 2 1 2 1 2 1 21 2 1212 2 21 12 + = − −= + →−=− − + −+ ∗ ∗ uu a uuuua uu uu Ludwig Prandtl (1875-1953)
- 81. 81 NORMAL SHOCK WAVESSOLO Normal Shock Wave ( Adiabatic), Perfect Gas G Q= =0 0, Mach Number Relations (2) ( ) ( ) ( ) ( ) ( ) ( ) ( ) ( ) ( )[ ] ( )( ) ( ) M M M M M M M M M 2 2 2 2 1 1 2 1 2 1 2 1 2 1 2 2 1 1 2 1 1 2 1 1 1 2 1 2 1 2 1 1 1 1 1 1 2 = + − − = + − − = + + − + − − = − + + / + − / / + − / + − − ∗ = ∗ ∗ ∗ γ γ γ γ γ γ γ γ γ γ γ γ γ γ or ( ) M M M M M H H A A 2 1 2 1 2 1 2 1 21 2 1 2 1 1 2 1 2 2 1 1 1 2 1 2 1 1 = + − − − = + + − + + − = = γ γ γ γ γ γ γ ( ) ( ) ρ ρ γ γ 2 1 1 2 1 2 1 2 1 2 2 1 2 1 2 1 2 1 2 1 1 2 = = = = = + − + = ∗ ∗ A A u u u u u u a M M M u p ρ T e u p ρ T e τ 11 q 1 1 1 1 1 2 2 2 2 2 1 2
- 82. 82 NORMAL SHOCK WAVESSOLO Normal Shock Wave ( Adiabatic), Perfect Gas G Q= =0 0, Mach Number Relations (3) ( ) ( ) ( ) ( ) ( ) p p u p u u u a M M M M M M M 2 1 1 2 1 1 2 1 1 2 1 2 1 2 1 2 1 2 1 2 1 2 1 2 1 2 1 2 1 1 1 1 1 1 1 2 1 1 1 1 2 1 = + − = + − = + − − + + = + / + − / − − + ρ γ ρ ρ γ γ γ γ γ γ γ or (C.L.M.) ( ) p p M2 1 1 2 1 2 1 1= + + − γ γ ( ) ( ) ( ) h h T T p p M M M a a h C T p RTp 2 1 2 1 2 1 1 2 1 2 1 2 1 2 2 1 1 2 1 1 1 2 1 = = = + + − − + + = = = ρ ρ ρ γ γ γ γ ( ) ( ) ( ) s s R T T p p M M M 2 1 2 1 1 2 1 1 1 2 1 1 1 2 1 2 1 1 2 1 1 1 2 1 − = = + + − − + + − − − − ln ln γ γ γ γ γ γ γ γ γ γ ( ) ( ) ( ) ( ) s s R M M M 2 1 1 1 2 1 2 3 2 2 1 2 41 2 2 3 1 1 2 1 1 − ≈ + − − + − + − << γ γ γ γ K Shapiro p.125 u p ρ T e u p ρ T e τ 11 q 1 1 1 1 1 2 2 2 2 2 1 2
- 83. 83 STEADY QUASI ONE-DIMENSIONAL FLOWSOLO STAGNATION CONDITIONS )C.E.( constuhuh =+=+ 2 22 2 11 2 1 2 1 The stagnation condition 0 is attained by reaching u = 0 2 / 21202 020 2 1 1 1 2 1 2 1 22 1 2 M TR u Tc u T T c u TTuhh TRa auM Rc pp Tch p p − += − +=+=→+=→+= = = − = = γ γ γ γγ γ Using the Isentropic Chain relation, we obtain: 2 1 0102000 2 1 1 M p p a a h h T T − += = = == − − γ ρ ρ γ γ γ Steady , Adiabatic + Inviscid = Reversible, , ( ) q Q= =0 0, ( )~ ~ τ = 0 ( ) G = 0 ∂ ∂ t = 0
- 84. SOLO 84 Civilian Aircraft Avionics Flight Cockpit CIRRUS PERSPECTIVE Cirrus Perspective Avionics Demo, Youtube Cirrus SR22 Tampa Landing in Heavy Rain, Movie
- 85. SOLO 85 Flight Displays CIRRUS PERSPECTIVE Civilian Aircraft Avionics
- 86. SOLO 86 Flight Displays CIRRUS PERSPECTIVE Civilian Aircraft Avionics
- 87. SOLO 87 Flight Displays CIRRUS PERSPECTIVE Civilian Aircraft Avionics
- 88. SOLO 88 Flight Displays CIRRUS PERSPECTIVE Civilian Aircraft Avionics
- 89. SOLO 89 Flight Displays CIRRUS PERSPECTIVE Civilian Aircraft Avionics
- 90. SOLO 90 Flight Displays CIRRUS PERSPECTIVE Civilian Aircraft Avionics
- 91. SOLO 91 Flight Displays CIRRUS PERSPECTIVE Civilian Aircraft Avionics
- 92. SOLO 92 Flight Displays CIRRUS PERSPECTIVE Civilian Aircraft Avionics
- 93. 93 New integrated flight control system, Movie https://www.youtube.com/watch?v=D3cH5ydHMzw Civilian Aircraft Avionics
Hinweis der Redaktion
- http://aviation.watergeek.eu/f4b-panel.html
- http://aviation.watergeek.eu/f4b-panel.html
- George M. Siouris, “Aerospace Avionics Systems, A Modern Synthesis”, Academic Press, Inc., 1993
- George M. Siouris, “Aerospace Avionics Systems, A Modern Synthesis”, Academic Press, Inc., 1993
- Collinson, R.,P.,G., “Introduction to Avionics”, Chapman & Hall, 1996
- Frank J, Regan, Satya M. Anandakrishnan, “Dynamics of Atmospheric Re-Entry”, AIAA Education Series, 1993
- Collinson, R.,P.,G., “Introduction to Avionics”, Chapman & Hall, 1996
- Collinson, R.,P.,G., “Introduction to Avionics”, Chapman & Hall, 1996
- Collinson, R.,P.,G., “Introduction to Avionics”, Chapman & Hall, 1996
- Collinson, R.,P.,G., “Introduction to Avionics”, Chapman & Hall, 1996
- Chapter 7 Flight Instruments http://www.gov/library/manuals/aviation/pilot_handbook/media/PHAK%20-%20Chapter%2007.pdf
- Chapter 7 Flight Instruments http://www.gov/library/manuals/aviation/pilot_handbook/media/PHAK%20-%20Chapter%2007.pdf
- Chapter 7 Flight Instruments http://www.gov/library/manuals/aviation/pilot_handbook/media/PHAK%20-%20Chapter%2007.pdf
- Chapter 7 Flight Instruments http://www.gov/library/manuals/aviation/pilot_handbook/media/PHAK%20-%20Chapter%2007.pdf
- Chapter 7 Flight Instruments http://www.gov/library/manuals/aviation/pilot_handbook/media/PHAK%20-%20Chapter%2007.pdf
- Chapter 7 Flight Instruments http://www.gov/library/manuals/aviation/pilot_handbook/media/PHAK%20-%20Chapter%2007.pdf
- http://fsxtimes.wordpress.com/category/hardware/
- Chapter 7 Flight Instruments http://www.gov/library/manuals/aviation/pilot_handbook/media/PHAK%20-%20Chapter%2007.pdf
- Chapter 7 Flight Instruments http://www.gov/library/manuals/aviation/pilot_handbook/media/PHAK%20-%20Chapter%2007.pdf
- Chapter 7 Flight Instruments http://www.gov/library/manuals/aviation/pilot_handbook/media/PHAK%20-%20Chapter%2007.pdf
- Chapter 7 Flight Instruments http://www.gov/library/manuals/aviation/pilot_handbook/media/PHAK%20-%20Chapter%2007.pdf http://www.youtube.com/watch?v=vICokuUAVAM
- Chapter 7 Flight Instruments http://www.gov/library/manuals/aviation/pilot_handbook/media/PHAK%20-%20Chapter%2007.pdf
- USNavy-Instrument Flightmanual.pdf
- Chapter 7 Flight Instruments http://www.gov/library/manuals/aviation/pilot_handbook/media/PHAK%20-%20Chapter%2007.pdf
- Chapter 7 Flight Instruments http://www.gov/library/manuals/aviation/pilot_handbook/media/PHAK%20-%20Chapter%2007.pdf
- Chapter 7 Flight Instruments http://www.gov/library/manuals/aviation/pilot_handbook/media/PHAK%20-%20Chapter%2007.pdf
- Chapter 7 Flight Instruments http://www.gov/library/manuals/aviation/pilot_handbook/media/PHAK%20-%20Chapter%2007.pdf Flight Instruments, Chapter 3, FAA-H-8083
- Chapter 7 Flight Instruments http://www.gov/library/manuals/aviation/pilot_handbook/media/PHAK%20-%20Chapter%2007.pdf Flight Instruments, Chapter 3, FAA-H-8083
- Chapter 7 Flight Instruments http://www.gov/library/manuals/aviation/pilot_handbook/media/PHAK%20-%20Chapter%2007.pdf Flight Instruments, Chapter 3, FAA-H-8083
- Chapter 7 Flight Instruments http://www.gov/library/manuals/aviation/pilot_handbook/media/PHAK%20-%20Chapter%2007.pdf
- Chapter 7 Flight Instruments http://www.gov/library/manuals/aviation/pilot_handbook/media/PHAK%20-%20Chapter%2007.pdf
- Chapter 7 Flight Instruments http://www.gov/library/manuals/aviation/pilot_handbook/media/PHAK%20-%20Chapter%2007.pdf
- Chapter 7 Flight Instruments http://www.gov/library/manuals/aviation/pilot_handbook/media/PHAK%20-%20Chapter%2007.pdf Flight Instruments, Chapter 3, FAA-H-8083
- Chapter 7 Flight Instruments http://www.gov/library/manuals/aviation/pilot_handbook/media/PHAK%20-%20Chapter%2007.pdf Flight Instruments, Chapter 3, FAA-H-8083
- Chapter 7 Flight Instruments http://www.gov/library/manuals/aviation/pilot_handbook/media/PHAK%20-%20Chapter%2007.pdf Flight Instruments, Chapter 3, FAA-H-8083
- Chapter 7 Flight Instruments http://www.gov/library/manuals/aviation/pilot_handbook/media/PHAK%20-%20Chapter%2007.pdf
- Chapter 7 Flight Instruments http://www.gov/library/manuals/aviation/pilot_handbook/media/PHAK%20-%20Chapter%2007.pdf
- Chapter 7 Flight Instruments http://www.gov/library/manuals/aviation/pilot_handbook/media/PHAK%20-%20Chapter%2007.pdf
- Chapter 7 Flight Instruments http://www.gov/library/manuals/aviation/pilot_handbook/media/PHAK%20-%20Chapter%2007.pdf
- Chapter 7 Flight Instruments http://www.gov/library/manuals/aviation/pilot_handbook/media/PHAK%20-%20Chapter%2007.pdf
- Chapter 7 Flight Instruments http://www.gov/library/manuals/aviation/pilot_handbook/media/PHAK%20-%20Chapter%2007.pdf
- Chapter 7 Flight Instruments http://www.gov/library/manuals/aviation/pilot_handbook/media/PHAK%20-%20Chapter%2007.pdf
- Chapter 7 Flight Instruments http://www.gov/library/manuals/aviation/pilot_handbook/media/PHAK%20-%20Chapter%2007.pdf
- Chapter 7 Flight Instruments http://www.gov/library/manuals/aviation/pilot_handbook/media/PHAK%20-%20Chapter%2007.pdf
- Chapter 7 Flight Instruments http://www.gov/library/manuals/aviation/pilot_handbook/media/PHAK%20-%20Chapter%2007.pdf
- Chapter 7 Flight Instruments http://www.gov/library/manuals/aviation/pilot_handbook/media/PHAK%20-%20Chapter%2007.pdf
- Chapter 7 Flight Instruments http://www.gov/library/manuals/aviation/pilot_handbook/media/PHAK%20-%20Chapter%2007.pdf
- Chapter 7 Flight Instruments http://www.gov/library/manuals/aviation/pilot_handbook/media/PHAK%20-%20Chapter%2007.pdf
- Chapter 7 Flight Instruments http://www.gov/library/manuals/aviation/pilot_handbook/media/PHAK%20-%20Chapter%2007.pdf
- Chapter 7 Flight Instruments http://www.gov/library/manuals/aviation/pilot_handbook/media/PHAK%20-%20Chapter%2007.pdf
- Chapter 7 Flight Instruments http://www.gov/library/manuals/aviation/pilot_handbook/media/PHAK%20-%20Chapter%2007.pdf
- Chapter 10 Aircraft Performance http://www.gov/library/manuals/aviation/pilot_handbook/media/PHAK%20-%20Chapter%2010.pdf
- Chapter 7 Flight Instruments http://www.gov/library/manuals/aviation/pilot_handbook/media/PHAK%20-%20Chapter%2007.pdf
- Chapter 7 Flight Instruments http://www.gov/library/manuals/aviation/pilot_handbook/media/PHAK%20-%20Chapter%2007.pdf
- Chapter 7 Flight Instruments http://www.gov/library/manuals/aviation/pilot_handbook/media/PHAK%20-%20Chapter%2007.pdf
- Chapter 4 Aerodynamics of Flight http://www.gov/library/manuals/aviation/pilot_handbook/media/PHAK%20-%20Chapter%2004.pdf
- http://cirrusaircraft.com/multimedia/#primary http://www.youtube.com/watch?v=2-DZIysbrx0 http://www.youtube.com/watch?v=tq7eS1wXTeo
- http://cirrusaircraft.com/multimedia/#primary
- http://cirrusaircraft.com/multimedia/#primary
- http://cirrusaircraft.com/multimedia/#primary
- http://cirrusaircraft.com/multimedia/#primary
- http://cirrusaircraft.com/multimedia/#primary
- http://cirrusaircraft.com/multimedia/#primary
- http://cirrusaircraft.com/multimedia/#primary
- http://cirrusaircraft.com/multimedia/#primary
- http://www.youtube.com/watch?v=D3cH5ydHMzw