FLYING QUALITIES OF PILOTED AIRCRAFT - CAFE Foundation

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MIL–STD–1797AAPPENDIX AVERIFICATION GUIDANCEWorst–case flight conditions should be identified and tested. High control effectiveness, authority and gain;low or negative static stability or damping; low weight and inertia will tend to make the transients larger.Generally a dynamic analysis is needed, but constant speed can be assumed for the two–second period oftime.M q S c C m = C y m c/2(C K L y 1where C L1 = W/qS, K y is the radius of gyration (dimensional) in pitch.VERIFICATION LESSONS LEARNED284
MIL–STD–1797AAPPENDIX A4.2.6.2 Pitch axis response to configuration or control mode change. The transient motions and trimchanges resulting from configuration changes or the intentional engagement or disengagement of any portionof the primary flight control system in equilibrium flight due to pilot action shall be such that dangerous flyingqualities never result. With controls free, the motion transients resulting from these situations shall not exceedthe following limits for at least_________seconds following the transfer:_________. These requirementsapply only for Aircraft Normal States (4.1.6).REQUIREMENT RATIONALE (4.2.6.2)Pitch transients due to intentional mode switching are distracting. If the transients are too large, pilots object.REQUIREMENT GUIDANCEThe related MIL–F–8785C paragraphs are 3.5.6 and 3.5.6.1.Recommended values for transient motion limits within the first 2 seconds following transfer:Within the Operational Flight Envelope: 0.05 g normal acceleration at the pilot’s stationWithin the Service Flight Envelope: 0.05 g at the pilot’s station.Since the intent of a flight control system is to improve the aircraft response characteristics––whethermeasured by improved flying qualities or by increased mission effectiveness––any system which can bechosen by the pilot should not cause noticeable transient motions. There has been some speculation as towhether a small transient motion is or is not desirable. The argument for an intentional transient is thatinadvertent pilot switching of autopilot modes is less likely if accompanied by a noticeable transient motion.MIL–F–8785B allowed 0.05 g normal acceleration. This was increased to 0.10 g in MIL–F–8785C, in order toallow if not encourage designers to provide some noticeable transient (see AFWAL–TR–81–3109). InAFWAL–TR–81–3109 an accident was cited wherein the pilot inadvertently bumped off the altitude hold mode(which automatically disengaged when a small force was applied to the control column). The flight recordershowed a 0.04 g transient which went unnoticed by the crew, who were deeply involved in trying to lower amalfunctioning landing gear. However, it is our contention that the undesirable features of transient motionsdue to mode switching are significant. Furthermore, a distracted crew would probably not notice a transientconsiderably larger than 0.04 g, especially if there were any turbulence at all. Therefore, we arerecommending that the maximum allowable transient of 0.05 g used in MIL–F–8785B be utilized as inMIL–F–8785B and C; two seconds is deemed a reasonable time to allow for the pilot to resume control.REQUIREMENT LESSONS LEARNED5.2.6.2 Pitch axis response to configuration or control mode change —verification. Verification shallbe by analysis, simulation and flight test.VERIFICATION RATIONALE (5.2.6.2)Configuration changes and control mode changes are to be made by normal means.285
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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 AFIGURE 42. A
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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 AGiven some v
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MIL-STD-1797AAPPENDIX A4.2.8.6 Pitc
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MIL-STD-1797AAPPENDIX A4.2.8.6.2 Pi
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MIL-STD-1797AAPPENDIX A4.2.9 Pitch
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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 AFIGURE 125.
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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 AReduction of
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MIL-STD-1797AAPPENDIX AC L 1___ 1-
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MIL-STD-1797AAPPENDIX ACRUISE CONDI
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MIL-STD-1797AAPPENDIX ABearing in m
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MIL-STD-1797AAPPENDIX Alanding appr
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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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MIL-STD-1797AAPPENDIX Aand in a ste
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MIL-STD-1797AAPPENDIX A5.5.5 Roll c
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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 AAψ= V o β+
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MIL-STD-1797AAPPENDIX Aroll respons
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MIL-STD-1797AAPPENDIX AClass IV air
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MIL-STD-1797AAPPENDIX Anondivergent
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MIL-STD-1797AAPPENDIX AwhereC nδ
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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 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 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 AβC nδa C C
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MIL-STD-1797AAPPENDIX A4.6.5.2. Yaw
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MIL-STD-1797AAPPENDIX A4.6.6 Yaw ax
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MIL-STD-1797AAPPENDIX A4.6.6.3 Yaw
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MIL-STD-1797AAPPENDIX AC yβCβ0δa
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MIL-STD-1797AAPPENDIX Ato augment Y
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MIL-STD-1797AAPPENDIX AUse of such
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MIL-STD-1797AAPPENDIX AMultiaxis, n
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MIL-STD-1797AAPPENDIX ATABLE LI. Di
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MIL-STD-1797AAPPENDIX AA critical d
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MIL-STD-1797AAPPENDIX Aand make air
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MIL-STD-1797AAPPENDIX Aof high α d
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MIL-STD-1797AAPPENDIX A4.8.4.2.4 On
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MIL-STD-1797AAPPENDIX A4.8.4.3.1 De
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MIL-STD-1797AAPPENDIX Amight influe
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MIL-STD-1797AAPPENDIX AThe AFWAL-TR
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MIL-STD-1797AAPPENDIX A4.8.4.3.2 Re
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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 AHoh et al. (
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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 A3. Low-altit
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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 AThe two most
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MIL-STD-1797AAPPENDIX AA survey of
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MIL-STD-1797AAPPENDIX ATABLE LVI. A
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MIL-STD-1797AAPPENDIX A5.9.2 Defini
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MIL-STD-1797AAPPENDIX BDETERMINING
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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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MIL-STD-1797AAPPENDIX CMIL-F-8785C
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STANDARDIZATION DOCUMENT IMPROVEMEN
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