FLYING QUALITIES OF PILOTED AIRCRAFT - CAFE Foundation

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MIL–STD–1797AAPPENDIX AFIGURE 21. Pitch acceleration response to a unit step force input.NADC–81186–60 accounts for time delay explicitly by defining flying qualities Levels in the CAP – plane, asshown on figures 22 and 23. The boundaries shown for each flying quality Level were defined by correlationsof data from DiFranco (AFFDL–TR–66–63), Neal and Smith (AFFDL–TR–70–74), and the LAHOS study(AFFDL–TR–78–122). These boundaries do seem to correlate the data that Bischoff plotted slightly betterthan does the present requirement based on CAP (compare to figures 36 and 38), and Bischoff showsexcellent correlation between CAP and CAP e for these data. However, the CAP parameter is subjectto all the limitations for equivalent systems noted in this requirement. Hence most of the points that do notcorrelate with CAP or ω sp Tθ 2 will also be missed by CAP e and CAP . The bandwidth specificationappears to do a somewhat better job than CAP .LEVEL 3All the suggested short–term pitch response requirements share a common Level 3 floor in recognition of (a)the demonstrated controllability of somewhat unstable airplanes and helicopters from their beginning daysand (b) our inability to come up with anything better at this time.A first–order divergence (T 2 = 6 sec) is allowed for the Level 3 pitch attitude dynamics. This is consistent withthe Level 3 static stability requirement in 4.4.1. The 6–second limit on instability was derived from in–flight andground–based simulator studies which have documented the degree of instability that is safely flyable.AFFDL–TR–72–143, for example indicated a Level 2 boundary with T 2 (based on the unstable aperiodicroot) of 2.5 seconds in light turbulence and 4.25 seconds in moderate turbulence. Pilot ratings were fairlyconstant at 5 to 6 until the time to double amplitude was reduced below 6 seconds, when significantdeterioration began.Some margin is allowed in order to account for pilot distraction, design uncertainties, etc. In this region nearneutral stability, the root locations generally are extremely sensitive to static margin. On the other hand,Schuler (AFWAL–TR–82–3014) concludes from his ground–based simulations that for light total damping(small value of the other, stable short–term pole) the 6 second limit can be unconservative.SUPPORTING DATASupporting data for both CAP and ω sp Tθ 2 forms of equivalent–system criteria, and for the Level 3requirements, are presented in the discussion of the ω sp Tθ 2 criteria which follows.188
MIL–STD–1797AAPPENDIX AFIGURE 22. Time delay versus CAP’ – Neal–Smithdata (from NADC–81186–60).FIGURE 23. Time delay versus CAP’ – LAHOS data(from NADC–81186–60).189
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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 AThe criteria
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MIL-STD-1797AAPPENDIX AFIGURE 69. A
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MIL-STD-1797AAPPENDIX AConfiguratio
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MIL-STD-1797AAPPENDIX AFIGURE 73. P
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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 AFIGURE 86. A
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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 AFIGURE 94. E
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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 AFIGURE 98. E
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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 A4.3.1.2 Stea
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MIL-STD-1797AAPPENDIX Adγdδe γ
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MIL-STD-1797AAPPENDIX ACombinations
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MIL-STD-1797AAPPENDIX A4.3.2 Flight
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MIL-STD-1797AAPPENDIX AFor all but
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MIL-STD-1797AAPPENDIX AThe accelera
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MIL-STD-1797AAPPENDIX A4.4.1.1 Spee
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4.5 Flying qualities requirements f
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MIL-STD-1797AAPPENDIX APrinceton Un
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MIL-STD-1797AAPPENDIX AExamination
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MIL-STD-1797AAPPENDIX AC L 1___ 1-
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MIL-STD-1797AAPPENDIX ABearing in m
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MIL-STD-1797AAPPENDIX AHowever, NAS
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MIL-STD-1797AAPPENDIX A2 ζ ωRS RS
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MIL-STD-1797AAPPENDIX Aallowed to b
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MIL-STD-1797AAPPENDIX ASUPPORTING D
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MIL-STD-1797AAPPENDIX Aa) Positive
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MIL-STD-1797AAPPENDIX A5.5.1.4 Roll
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MIL-STD-1797AAPPENDIX A5.5.1.5 Time
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MIL-STD-1797AAPPENDIX A4.5.3 Linear
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MIL-STD-1797AAPPENDIX ANOTES:1. Fla
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4.5.7 Roll axis response to other i
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MIL-STD-1797AAPPENDIX ATABLE XXVIII
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MIL-STD-1797AAPPENDIX ATABLE XXX. R
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MIL-STD-1797AAPPENDIX ADiscussion o
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MIL-STD-1797AAPPENDIX Aroll respons
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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 AIn the fligh
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MIL-STD-1797AAPPENDIX AThe bandwidt
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MIL-STD-1797AAPPENDIX AConfiguratio
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MIL-STD-1797AAPPENDIX AThe low mode
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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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STANDARDIZATION DOCUMENT IMPROVEMEN
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FLYING QUALITIES OF PILOTED AIRCRAFT - CAFE Foundation

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