18th annual conference on manual control.pdf - Acgsc.org

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I ! Pilot No 1 1 2 3 4 5 6 7 8 9 10 11 12 (s.E)2 .. -, .- .'ONDITION Rail-Rail 1 Vazlabilit_ _rror,x,f_ 9.5+5.8 7.3+3_0 9.3+4.9 12.2+6.6 8.9+3.8 10.2+4.3 10.9+4.8 7.9+3.3 10.3+5.0 11.0+5.3 8.7+3.4 10.1+3.8 5.41 3ow-Stern H _rror,y,ft 9.8+5.3 8.3+3.7 9.5+4.6 12.4+5.6 10.1+4.2 10.9+5.1 12.0+5.7 8.4+3.5 10.7+5.1 10.9+4.4 9.8+3.8 10.8+4.1 5.52 _ititude Z •"rror,h,f_ 4.3+1.9 3.9+1.7 4.1+1.5 5.i__i.9 4.2+1.6 4.6+i.3 4_3+i.4 3.8_i.2 5.0+_2.2 5.0+1.9 4.4+1.9 4.9+1.7 2.05 _3 _oli Angle _ _, rad. .073+.023 .066+.012 1.071+.016 .080+.019 .072+.019 .080+_.018 .070+__.013.071+.016 .073+.014 .081+_.022 .072+.017 .081+_.020 .021 k_ _itch _ngle,8, ___ _ad i .083+_013 .083+.012 .082+.010 085+.014 .081+.009 .083+.009 .082+.010 .083+.012 .084+.012 .086+.012 086+.011 .086+.013 .015 U_ • I_Il_tive [-_ KAOS,in. .42+.21 .46+.25 .36+.14 .54+.36 .53+.35 .46+.20 .45+.19 .50+.28 .48+.24 .50+.38 .48+.28 .53+.29 .343 _ _ii Cyclic £CS,in. .41+.13 .33+.12 .41+.16 .41+.13 .36+.14 .43+.14 .38+.12 .37+.15 .40+.13 .45+.15 .36+.12 .43+.17 .246 ,-, PitchCyclic KCS,in. .44+.16 .45+.13 .48+.24 .46+.14 .47+.16 .50+.14 .41+.14 .49+.17 .47+.17 .51+.17 .49+.13 .50+.21 .276 Rudder, " ,in. 063+.019 .068+.019 _062+.016 .0V3_/.022 .071+.018 .070+.016 .069+.017 067+.020 i.070+.022 .069+.024 1.075+.0211.073+.018 .020 I - l+ i. Condition numbers•refer to Table 2. Standard Error attributabl_ to pilot variability alone, independent of condition. • _ _D
Table 5. MODEL PREDICTIONS FOR DIFFERENT EXPERIMENTAL CONFIGURAT] ONS co %o h_ m _ _ _ o o _ _ _ o _ _ _ "_"_"_ "_ , _ _ _ ° ° _ _ 198
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AFWAL-TR'83-3021 PROCEEDINGS OFTHEE
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UNCLASS I FI ED SECURITY CLASSIFiCA
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CONFERENCE CHAIRMAN : FrankL. Georg
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Eleventh Annual Conference on Manua
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CONTENTS(Cont' d) PAGE 6. A FUZZY M
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CONTENTS(Concluded) PAGE 4. DEXTERO
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AN INFORMATIONTHEORETICMODELOF THE
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RISK AND DECISION PROCESSES IN MANU
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In order to investigate manual cont
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may represent particularly efficien
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Results are summarized in Fig.7: In
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TABLE 1 "..,_BORDER- ABOV_ ' BELOW
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0.25, !/% 0.25 " I)'I I 1 1 ' I -5.
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FIG .6 PERFORMANCE OPERATING CURVE
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TIMEDOMAIN IDENTIFICATIONOFPILOT DY
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The human limitationsmodeled includ
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RATING FROM SIMULATION I I , I I I
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The identificationmethod proposed i
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With regard to the remainingterms i
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The algorithm is as follows: 1) Sel
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CLASSICALRESULTS Up(S) " ' - YP Yc
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EXAMPLE PLANT: = 11,7 S ec(s) 3,67
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m m oo --_ ::_ ---I oo o
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Conversely, the "corrected" set use
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Although improvedmethods are curren
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A TEST OF FITTS' LAW IN TWO DIMENSI
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INTRODUCTION We have undertaken a m
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ecomes smaller as the tonic pupil s
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i i i • 1 .......................
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FIGURE 3 : Test conditions for pupi
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k_ (A) : [,'J o_:. \ -80- [_J [....
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DISCUSSION Before attempting anothe
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Edinger-Westphal nucleus. CONCLUSIO
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COMPUTATIONALPROBLEMSIN HUMAN OPERA
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These time series analysismethods h
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The parametersn and m were chosen u
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models with m > I, m = 1 is chosen
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SAMPLING INTERVAL 0.1 SEC Fig. 3-a
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where H(z) is the transfer function
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TABLE 1. TRANSFERFUNCTION.MODEL:WIT
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Although the time series analysis i
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(10) Jex, H. R., and Allen, R. W.,
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CL{ANGES IN HUMAN JOINT COMPLIANCE
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esponse, but what that might be rem
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esulting angular position and stret
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mechanical consequences of the myot
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Merton, P.A. Speculations on the se
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p_ 10.0 FREQUENCY (HZ) 1.0 II111 "o
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...... E RJR042/056 ANGLE TA EMG SO
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aooT I- jU >_ EO '__ o i// V_. - \m
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-100 300 AO UJ GLG589 .J O Z -100 J
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- 22 MIN CO um UJ • - -500 JLEO 3
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RECORD f (hZ) _ J B K CONTROL 1 1.8
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ABSTRACT for 18th
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4). For example,in order to optimal
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For example, when system error and
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REFERENCES I. Birmingham, H.P,, and
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Ar ea 2 / A1 Area 2_ -A2 -A1 X Theo
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determinedboth by his interfacewith
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Procedure The subject sat before th
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e used in designingdiscrete-timetas
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Factor Beta-weight Beta-weight Cour
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SUSTAINEDTURN POSITIONING EXTENDING
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DEVELOPMENT OF PERFORMANCE MEASURES
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performed all nine conditions. Ther
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REFERENCES Moray, N. 1979. Mental W
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|'0 _L_ o.S, K _/.s K/5" K/S_ - - -
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RATING CONSISTENCY AND COMPONENT SA
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also mounted on the left arm of the
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necessitating continued attention b
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4_4 4_4141 4_4_0 00 OVERALLWORKLQAD
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whereas increasing the bandwidth fr
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Figure 3. He.an ratings and signifi
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Figure 4.. Hean ratings and signifi
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Figure 5. Mean ratings and signific
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._ o ,.,_m F-_rt o :1 ,-q x €:._
Page 155 and 156: Level (_-.585, E
Page 157 and 158: ing related to Overall Workload or
Page 159 and 160: Steinlnger, K. Subjective ratings o
Page 161 and 162: discriminable changes in the score
Page 163 and 164: RESULTS The computed scores for eac
Page 165 and 166: In general, the results of the expe
Page 167 and 168: TABLE 2 Workload Assessment Techniq
Page 169 and 170: TABLE 4 Logical Classification of T
Page 171 and 172: 1.0 1 Q.S N z_ = -O,S = _€ -1,0 L
Page 173 and 174: SESSION3: SIMULATIONAND MODELBASEDA
Page 175 and 176: _ation For Time DelaysIn FlightSimu
Page 177 and 178: AN AUTOMOBILEAND SIMULATORCOMPARISO
Page 179 and 180: particularilycritical during the ac
Page 181 and 182: performanceduring productionruns wa
Page 183 and 184: using roadway cues from the left la
Page 185 and 186: epresentingan automobilefor a later
Page 187 and 188: PerformanceParameters D OVER C - T
Page 189 and 190: TRANSFEROF LEARNING GROUP 1 (SIMULA
Page 191 and 192: 5.25m l.Tm _- --- I / _ I I ! i i 0
Page 193 and 194: FIGURE4 INSTRUMENTEDVEHICLEDURING O
Page 195 and 196: AN OPTIMAL CONTROL MODEL ANALYSIS O
Page 197 and 198: current standards) could result in
Page 199 and 200: ft/sec and 1.42 ft/sec, respectivel
Page 201 and 202: Table i. PERCEPTUAL THRESHOLDS* Var
Page 203 and 204: m Variable "Maximum" Allowable Devi
Page 205: given in Table 4. Also shown in the
Page 209 and 210: ii A io o _ 9 Delay = 133 ms i .,-4
Page 211 and 212: i0 _. Delay = 133 ms o 1.4 I .,,4 _
Page 213 and 214: sensitivity of the OCM to increases
Page 215 and 216: [6] Ricard, G.L., R.V. Parrish, B.R
Page 217 and 218: Air Force Aerospace Medical Researc
Page 219 and 220: III. TASK ANALYSIS USING SAINT In o
Page 221 and 222: equired to detect the target, The c
Page 223 and 224: Examination of histograms of these
Page 225 and 226: EXP: SClII COND 19 (FLYBY 1, EW, EC
Page 227 and 228: conditions corresponding to particu
Page 229 and 230: o 0 _ oD _ • eo olo ooee ee I I I
Page 231 and 232: • oeo_ eeee eoJo 0 0 0 0 0 0 0 0
Page 233 and 234: REFERENCES I. Kleinman, D.L. and To
Page 235 and 236: screen according to a pre-defined t
Page 237 and 238: error signal. The error signal repr
Page 239 and 240: Similarly Fig. 11 ,12, and 13 prese
Page 241 and 242: .OO3- ,0_. .O01 Figure 6. Tracking
Page 243 and 244: (sNnaoot) _._aoa.LV 6U_M paxk:l ,aO
Page 245 and 246: 2_ T v TRACK AZIMUTH ANGULAR RATECO
Page 247 and 248: itl ,ii11 i _l,lJl]illJ_ , i,'i , .
Page 249 and 250: manual control data to determine th
Page 251 and 252: elative cost penalty on control-rat
Page 253 and 254: pilot parameters. Conversely, a mat
Page 255 and 256: these changes to parameters that ar
Page 257 and 258:
TABLE 2 Significance Test of Practi
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TABLE 3 Effects of Practice on Pilo
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variable(s) of interest. After para
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subjects, trained initially fixed-b
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A MODERNAPPROACHTO PILOTVEHICLEANAL
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Unfortunately,the methodology suffe
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DISTURBANCES lqw _ I ! i I MOTOR LA
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By validatingthat the OCM can be us
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SESSION4: MODELBASEDDESIGNAND CONTR
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VALIDATION OF AN ADVANCED COCKPIT D
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experimental program was conducted
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0 1 0 0 0 0 0 0 0 1 0 0 0 0 _2U° 3
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is repeatedfor several values of co
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assumption. Indeed, including the Y
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Display System Synthesis STATUS DIS
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THREE _IMENSIONAL PERSPECTIVE TUNNE
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Implementation of the flight direct
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Using these numerical results, the
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which will not be addressed at this
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move towards the observer, but the
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absolute levels of control performa
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REFERENCES (continued) i0. Grunwald
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and healthand safety data are accur
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DESIGN ISSUES IN EMERGING AUTOMATIO
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complacent. The second issueisa dir
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_ ' ': _ _: _:_i ¸ i_:_ ,:>_:_ _ '
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One of the difficulties of the mult
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overview, the other, detailed views
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Figures 8 and 9 depict displayedinf
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REFERENCES Ackoff,RusselL.,"Managem
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HUMAN - COMPUTER DIALOGUE FRAGMENT
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FTGURE 4 3i3
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FIGURE 6 ENTRY_CONTROL INFORMATION
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HIERARCHICINTEGRATEDINFORHATIONDISP
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GROUPEDPRIMITIVESINTEGRATEDDISPLAY
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of functions to be displayed; (3) t
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APPARATUS The mode selection task w
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CONCLUSIONSAND RECOMMENDATIONS The
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AN ANALYSIS OF CONTROL RESPONSES AS
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The data suggest the need for rethi
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The ideal flight display is one tha
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140 WIND- SHEAR z 12_0 CP \ k 0_ I0
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.6 ELEVATOR POWER SPECTRAL ANALYSIS
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left hand) on the right side of the
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the presentation of the stimulus wi
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at the bottom/center of the oscillo
Page 351 and 352:
References Hartzell, E. J., Dunbar,
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typically located near the top of t
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7.1 ¸ It can be argued ni'ng,: e,x
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effect control. The two hands are p
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amplitude (A) and the narrowest tar
Page 361 and 362:
Figure 5. The subject station with
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equal to 0.5 degrees per second ove
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CYCLIC MT IPSI CONT l m 1,155 1.387
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in the contralateral condition for
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slopes for the two conditions are s
Page 371 and 372:
References 1. Fitts, P.M. & Seeger,
Page 373 and 374:
CHARACTERISTICS OF A COMPENSATORY M
Page 375 and 376:
of a subject via two sets of wet el
Page 377 and 378:
experimental system contained an ad
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signals which are band-limitedat la
Page 381 and 382:
are equal to McRuer and Elkind's av
Page 383 and 384:
23. K. Tanie, S. Tachi, K. Komoriya
Page 385 and 386:
I0 _ -...../..._ n, o.5 v_ x/,,,.._
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-(9- Fc=0.3 Hz Pl=10ms -_- Fc=0.5 H
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Fc=0.3Hz Fc=0.5Hz 10 Fc=0.8Hz 201 "
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e 20 20 em 10 •m ------ ------._.
Page 393 and 394:
SESSION5: HUMAN-MACHINESYSTEMSAND C
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3. Model mimic techniques use a fai
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SOURCEHEAD PENDULUM _ LO\ I?_(_ =TC
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This Configuration Space with its C
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Y 6 Xo-- _ --_'-e s× C [BY,, to ,.
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In either the analytic or projectiv
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no longer holds. \ \ \ \\ \ \ ! \
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geometric machine with many moving
Page 409 and 410:
Yo P w_ _ _ _7p t / , °p # # ; / i
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B. Minimum Information Storage Traj
Page 413 and 414:
Each machine degree of freedom, as
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AXIS I FALSE ALARM" IAL ZONE TRUE C
Page 417 and 418:
3. Kreifeldt,J., Kiel, R., Richichi
Page 419 and 420:
PERCEPTUAL SCALING OF MOMENT OF INE
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DATA ANALYSIS Starting at the cente
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REFERENCES I. Kreifeldt,John G. and
Page 425 and 426:
DEXTEROUS MANIPULATOR LABORATORY PR
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deviation appears to increase for T
Page 429 and 430:
Fig. 2 Manipulator Task Board 424
Page 431 and 432:
A DIRECTMEAN CTV MEAN • 3.3 TO 1
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which occur in the AFTI/F-16. In fi
Page 435 and 436:
Table I - Newman-Keuls Multiple Com
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,_ Teta!Score MJ TrackingRelated _=
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(b co I 10 ;K FEED THROUGH H (Degre
Page 441 and 442:
l, 4 Fo _.CE ST LC._,< l,d O,_ Figu
Page 443:
i 1.:2 b l sPi..A¢ 9_.1"-!, EklT C
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proportional or preselected fixed r
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three microswitches. To latch safel
Page 450 and 451:
Claw Control Three methods were imp
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C) Sensor display and visual access
Page 454 and 455:
Note that the most time consuming s
Page 456 and 457:
Table I. Time Performance Data of P
Page 458 and 459:
CONTROL -_ BIAS POSITION BUTTON INP
Page 460 and 461:
L_ Figure 3. Cylinderand Box Module
Page 462 and 463:
A C B Figure 5. Latching Mechanism
Page 464 and 465:
Ca) (b) (c) U"l Figure7. BerthingSe
Page 471 and 472:
HELICOPTER INTEGRATED CONTROLLER RE
Page 473 and 474:
METHOD Subjects. Subjects will be n
Page 475 and 476:
illustrated in Figure 2. Subjects w
Page 477 and 478:
amp. amp. amp. 4._ rrl _ -.4 --E [_
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TENTATIVE CRITERIA FOR CONTROLLERS
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simulator. Most soldiers who comple
Page 483:
makes a mistake and is otherwise si
Page 486 and 487:
The major future effort, other than
Page 488 and 489:
FACTORSAFFECTINGIN-TRAIL FOLLOWINGU
Page 491 and 492:
DISPLAY CONSIDERATIONS Location Our
Page 493 and 494:
The three types of spacing cues ill
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that it tends to smooth out speed v
Page 497 and 498:
symbology section, can also shed so
Page 499 and 500:
If we apply the 50-second,5-percent
Page 501 and 502:
REFERENCES I. Abbott, Terence S.; M
Page 503 and 504:
TRAFFIC [ SELECTION CDTI ] SENSOR "
Page 505 and 506:
cZ) P_ Figure6.- Conventionalcockpi
Page 507 and 508:
\ 8_ Jacoxwaypoint"'_z_ JAC /kS_IG
Page 509:
Figure I0.- Advanced cockpit CDTI f
Page 512 and 513:
300 r--- ,,. f 250- _/_j' _ GROUNDS
Page 514 and 515:
CHARACTERISTICSOF LEADAIRCRAFT STEA
Page 516 and 517:
_ ' i ' ' ' 300- GROUNDSPEED, 250-
Page 518 and 519:
An informal analysis of projective
Page 520 and 521:
on the metric line at the end of th
Page 522 and 523:
Special thanks to Fumei "Amy" Wu of
Page 524 and 525:
fig. 2 Tag Placement I _ EYE -_ ' E
Page 526 and 527:
d.ing A'I"C.,c:harts, maps, weather
Page 528 and 529:
- I _£2__ , r .I // !-Tr-\ \ \
Page 530 and 531:
_'_Lm _ 030 . d 195 0S6 Figure 2: A
Page 532 and 533:
Four instrument-rated general aviat
Page 534 and 535:
TABLE I: Separation Violations that
Page 536 and 537:
statist.ic:al analysis. Averages fo
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than without for" the pilots of the
Page 540 and 541:
Figure 4 depicts the frequency of s
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Simulator Pilot Opinion At the conc
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communications with the addition of
Page 546 and 547:
cared that the addition of CDTI int
Page 548 and 549:
AIR TRAFFIC CONTROL OF SIMULATED AI
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joystick for the control yoke and a
Page 552 and 553:
shown by a hexagon if the aircraft
Page 554 and 555:
The number of seconds between an ai
Page 556 and 557:
LIST OF AUTHORS 553
Page 558:
AUTHORS CONCLUDED J. L. Lewis 440 E
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