FLYING QUALITIES OF PILOTED AIRCRAFT - CAFE Foundation

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MIL–STD–1797AAPPENDIX AFIGURE 165. Flight phase Category C data (from Princeton Univ Rpt 727).FIGURE 166. Category C data (approach and wave–off); Cooper–Harper pilotratings (from AFFDL–TR–70–145).414
MIL–STD–1797AAPPENDIX Aa) Positive dihedral, proverse yaw due to aileron.b) Positive dihedral, adverse yaw due to aileron.c) Negative dihedral, proverse yaw due to aileron.d) Negative dihedral, adverse yaw due to aileron.These configurations, which all had very light dutch roll damping and large |φ/β|d response ratios, are plottedon figure 167. The parameters posc/pav , and p/β were obtained from time histories of the responses tostep aileron inputs. Configuration a, which falls well outside the Level 2 boundary of figure 167, wasuncontrollable, attempts by the pilot to control the oscillation resulted in excursions of increasing magnitudefor both sideslip angle and the roll rate.Configuration b, which also falls well outside the Level 2 boundary of figure 167, was unacceptable because ofthe oscillatory response. However, it is significant that the pilot was able to control the aircraft, and, in fact,damp the oscillations when they occurred using only normal aileron control movements.FIGURE 167. Positive and negative dihedral data of Princeton Univ Rpt 604.Configuration c, which marginally falls in the good area of figure 167, was controllable and it was found thatattempts to control the roll angle in a normal manner also helped to reduce the excursions of the sideslip angle.Configuration d, which falls in an area of marginal acceptability on figure 167, was uncontrollable because ofpilot–induced oscillations.Thus, with the possible exception of Configuration d, the pilot comments pertaining to the configurations werecompatible with those expected from their roll–sideslip coupling characteristics as indicated by figure 167.415
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NOTE: MIL-STD-1797A has been redesi
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MIL-STD-1797AFOREWORDThis standard
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MIL-STD-1797ACONTENTS - ContinuedPa
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MIL-STD-1797A1. SCOPE1.1 Purpose. T
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MIL-STD-1797AT 2 Time to double amp
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MIL-STD-1797AV end Speed for maximu
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MIL-STD-1797Aω spUndamped natural
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MIL-STD-1797Awhere p , p and p are
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MIL-STD-1797AFIGURE 1. Roll-sidesli
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MIL-STD-1797AFIGURE 2. Roll-sidesli
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MIL-STD-1797AExamples showing measu
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MIL-STD-1797Aσ, RMS Root-mean-squa
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MIL-STD-1797A4. REQUIREMENTS4.1 Gen
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MIL-STD-1797Athe selected configura
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MIL-STD-1797Ab. For these calculati
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MIL-STD-1797Aindicate to the pilot
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MIL-STD-1797Aaccessibly located, co
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MIL-STD-1797ATABLE IV. Pitch trim c
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MIL-STD-1797Aspeed range by the mos
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MIL-STD-1797Ato designated flight p
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MIL-STD-1797Ainputs are simple, eas
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MIL-STD-1797ARight yaw-control-peda
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MIL-STD-1797Ad. Yaw axis control po
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MIL-STD-1797ADuring combat-type man
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MIL-STD-1797A4.9 Flying qualities r
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MIL-STD-1797A5. VERIFICATION5.1 Gen
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MIL-STD-1797A5.1.12.4 Rate of contr
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MIL-STD-1797A5.2.8.6.5 Pitch axis c
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MIL-STD-1797A5.5.9.3 Roll axis cont
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MIL-STD-1797A5.8 Flying qualities r
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MIL-STD-1797A1st Tier References2nd
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MIL-STD-1797AAPPENDIX AFLYING QUALI
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MIL-STD-1797AAPPENDIX AASD-TDR-63-3
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MIL-STD-1797AAPPENDIX AAFFDL-TR-70-
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MIL-STD-1797AAPPENDIX AAFWAL-TR-81-
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MIL-STD-1797AAPPENDIX AFAA-RD-70-65
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MIL-STD-1797AAPPENDIX ANASA-TM-X-62
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MIL-STD-1797AAPPENDIX AAIAA Paper 6
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MIL-STD-1797AAPPENDIX ABoeing D6-10
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MIL-STD-1797AAPPENDIX AAGARD-CP-333
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MIL-STD-1797AAPPENDIX ANeal, T. Pet
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MIL-STD-1797AAPPENDIX AFor military
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MIL-STD-1797AAPPENDIX AFIGURE 3. Cl
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MIL-STD-1797AAPPENDIX Ab. Cruise (C
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MIL-STD-1797AAPPENDIX AWhile the or
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MIL-STD-1797AAPPENDIX A3.3 Levels a
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MIL-STD-1797AAPPENDIX AFractional r
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MIL-STD-1797AAPPENDIX A40. REQUIREM
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MIL-STD-1797AAPPENDIX AREQUIREMENT
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MIL-STD-1797AAPPENDIX AVERIFICATION
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MIL-STD-1797AAPPENDIX ASome Flight
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MIL-STD-1797AAPPENDIX ATABLE I. Ope
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MIL-STD-1797AAPPENDIX AIf design tr
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MIL-STD-1797AAPPENDIX Ac. The speed
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MIL-STD-1797AAPPENDIX A4.1.4.3 Perm
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MIL-STD-1797AAPPENDIX A4.1.5 Config
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MIL-STD-1797AAPPENDIX A4.1.6 Aircra
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MIL-STD-1797AAPPENDIX A4.1.7.1 Allo
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MIL-STD-1797AAPPENDIX Aart can supp
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MIL-STD-1797AAPPENDIX ATABLE VIII.
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MIL-STD-1797AAPPENDIX AP(Level 2) =
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MIL-STD-1797AAPPENDIX ASee also REQ
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MIL-STD-1797AAPPENDIX Ademonstrated
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MIL-STD-1797AAPPENDIX A4.1.7.4 Gene
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MIL-STD-1797AAPPENDIX A5.1.7.4 Gene
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MIL-STD-1797AAPPENDIX A4.1.7.6 Fail
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MIL-STD-1797AAPPENDIX A4.1.10 Inter
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MIL-STD-1797AAPPENDIX A4.1.11.2 Rel
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MIL-STD-1797AAPPENDIX A4.1.11.4 Fai
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MIL-STD-1797AAPPENDIX ATABLE IX. Su
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MIL-STD-1797AAPPENDIX A4.1.11.5 Con
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MIL-STD-1797AAPPENDIX Aone must con
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MIL-STD-1797AAPPENDIX AUnless deact
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MIL-STD-1797AAPPENDIX ATABLE X. Con
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MIL-STD-1797AAPPENDIX A4.1.11.6 Pil
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MIL-STD-1797AAPPENDIX A4.1.11.7 Res
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While some functions that might be
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MIL-STD-1797AAPPENDIX A4.1.12.4 Rat
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LevelMIL-STD-1797AAPPENDIX ATABLE X
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MIL-STD-1797AAPPENDIX Athunderstorm
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MIL-STD-1797AAPPENDIX AThe irrevers
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MIL-STD-1797AAPPENDIX A4.2 Flying q
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MIL-STD-1797AAPPENDIX Achanges sign
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MIL-STD-1797AAPPENDIX A4.2.1.2 Shor
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MIL-STD-1797AAPPENDIX Apilot pitch
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THE EQUIVALENT SYSTEMS CONCEPTMIL-S
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MIL-STD-1797AAPPENDIX AIt is assume
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MIL-STD-1797AAPPENDIX AThe problem
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MIL-STD-1797AAPPENDIX AFIGURE 15. E
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MIL-STD-1797AAPPENDIX AFIGURE 16. C
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MIL-STD-1797AAPPENDIX AFIGURE 19. P
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MIL-STD-1797AAPPENDIX AFor many air
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MIL-STD-1797AAPPENDIX AFIGURE 22. T
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MIL-STD-1797AAPPENDIX AFIGURE 24. R
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MIL-STD-1797AAPPENDIX AThe last fac
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MIL-STD-1797AAPPENDIX AShort-period
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MIL-STD-1797AAPPENDIX AFIGURE 36. A
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MIL-STD-1797AAPPENDIX Aimposed on l
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MIL-STD-1797AAPPENDIX ALAHOS data (
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C. Transient peak ratio, rise time,
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MIL-STD-1797AAPPENDIX Acriteria do
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MIL-STD-1797AAPPENDIX AThe AFFDL-TR
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MIL-STD-1797AAPPENDIX AD. Bandwidth
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MIL-STD-1797AAPPENDIX AFIGURE 58. S
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MIL-STD-1797AAPPENDIX AFIGURE 59. D
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MIL-STD-1797AAPPENDIX AE. Closed-Lo
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MIL-STD-1797AAPPENDIX AThe criteria
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MIL-STD-1797AAPPENDIX AConfiguratio
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MIL-STD-1797AAPPENDIX AFIGURE 76. H
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MIL-STD-1797AAPPENDIX A* Pitch rate
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MIL-STD-1797AAPPENDIX APHASE LAGFor
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MIL-STD-1797AAPPENDIX Ahorizontal t
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MIL-STD-1797AAPPENDIX Aa. AnalysisA
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MIL-STD-1797AAPPENDIX ACare must be
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MIL-STD-1797AAPPENDIX AFIGURE 89a.
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MIL-STD-1797AAPPENDIX A4.2.2 Pilot-
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MIL-STD-1797AAPPENDIX Afeature at t
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MIL-STD-1797AAPPENDIX AThe correspo
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MIL-STD-1797AAPPENDIX AωBWτ p= 1.
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MIL-STD-1797AAPPENDIX A275
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MIL-STD-1797AAPPENDIX A4.2.5 Pitch
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4.2.6. Pitch axis response to other
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MIL-STD-1797AAPPENDIX A4.2.6.2 Pitc
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MIL-STD-1797AAPPENDIX A5.2.7.2.1 Lo
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MIL-STD-1797AAPPENDIX AFIGURE 96. N
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MIL-STD-1797AAPPENDIX AIt must be s
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MIL-STD-1797AAPPENDIX ATABLE XVII.
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MIL-STD-1797AAPPENDIX AFIGURE 100.
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MIL-STD-1797AAPPENDIX Aratings show
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MIL-STD-1797AAPPENDIX AAccording to
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MIL-STD-1797AAPPENDIX A[The Citabri
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MIL-STD-1797AAPPENDIX AFor a revers
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MIL-STD-1797AAPPENDIX Arequirements
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MIL-STD-1797AAPPENDIX ASome additio
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MIL-STD-1797AAPPENDIX ATABLE XVIII.
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MIL-STD-1797AAPPENDIX AGiven some v
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4.3.1 Flight path response to attit
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MIL-STD-1797AAPPENDIX ATABLE XXIII.
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MIL-STD-1797AAPPENDIX Adγdδe γ
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MIL-STD-1797AAPPENDIX AThe third sk
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MIL-STD-1797AAPPENDIX AThe LATHOS r
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MIL-STD-1797AAPPENDIX Apound). It c
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MIL-STD-1797AAPPENDIX A4.5.9.5.2 Ro
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MIL-STD-1797AAPPENDIX AIt should al
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MIL-STD-1797AAPPENDIX AIn the fligh
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MIL-STD-1797AAPPENDIX AIt has long
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MIL-STD-1797AAPPENDIX A4.6.1.3 Wing
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MIL-STD-1797AAPPENDIX AThe bandwidt
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MIL-STD-1797AAPPENDIX AConfiguratio
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MIL-STD-1797AAPPENDIX Arestraint wi
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MIL-STD-1797AAPPENDIX ATABLE XLIII.
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MIL-STD-1797AAPPENDIX ASUPPORTING D
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MIL-STD-1797AAPPENDIX AP-3B (Class
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MIL-STD-1797AAPPENDIX AThe ability
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MIL-STD-1797AAPPENDIX AHowever, bef
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C. r o/po Near ZeroMIL-STD-1797AAPP
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MIL-STD-1797AAPPENDIX Aand the time
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MIL-STD-1797AAPPENDIX Ato augment Y
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in terms of the uncoupled approxima
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MIL-STD-1797AAPPENDIX Amight influe
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MIL-STD-1797AAPPENDIX AThe low mode
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MIL-STD-1797AAPPENDIX ATABLE LIII.
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MIL-STD-1797AAPPENDIX AAt low altit
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MIL-STD-1797AAPPENDIX A4.9.2 Defini
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MIL-STD-1797AAPPENDIX ATABLE LIV. D
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MIL-STD-1797AAPPENDIX Aa. Turbulenc
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MIL-STD-1797AAPPENDIX Ac. Periodic
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MIL-STD-1797AAPPENDIX AThis require
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MIL-STD-1797AAPPENDIX BThese envelo
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MIL-STD-1797AAPPENDIX BFIGURE 272.
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MIL-STD-1797AAPPENDIX B687
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MIL-STD-1797AAPPENDIX CThe framewor
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MIL-STD-1797AAPPENDIX CAdditional i
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MIL-STD-1797AAPPENDIX CVerification
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