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

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TABLE I Primary Task Load Conditions LOAD CONDITION Low Medium High RANDOM GUST LEVEL Low Medium High Estimated Std. Dev. (mph) 0 2.7 5.9 PITCH STABILITY High Medium Low a. Control input to pitch rateoutput equivalent gain (degrees/s per % of control range) 0.°522 3.560 7.83 b. Control input to pitch rate output equivalent time constant(s) 0.097 0.660 1.45 156
TABLE 2 Workload Assessment Techniques Which Were Tested in the Present Experiment OPINION I. Cooper-Harper Scale 2. WCI!TE Scale SPARE MENTAL CAPACITY 3. Digit Shadowing (% errors) 4. Memory Scanning (Mean time) 5. Mental Arithmetic (% errors) 6. Time Estimation Mean (Seconds) 7o Time Estimation Standard Deviation (Seconds) 8. Time Estimation Absolute Error (Seconds) 9. Time Estimation RMS error (Seconds) PHYSIOLOGICAL i0. Pulse Rate Mean (Pulses per minute) ii. Pulse Rate Variability (Pulses per minute) 12. Respiration Rate (Breath cycles per minute) 13. Pupil Diameter (Normalizedunits) 14. Voice Pattern (Digit ShadowingTask) 15. Voice Pattern (MentalArithmeticTask) EYE BEHAVIOR 16. Eye TransitionFrequency (Transitionsperminute) 17. Eye Blink Frequency (Blinks per minute) PRIMARY TASK 18. LocalizerRMS Angular PositionError (Degrees) 19. Glide Slope RMS Angular PositionError (Degrees) 20. Control Movementsper second (Aileron+ Elevator+ Rudder) 157
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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
Page 115 and 116: REFERENCES I. Birmingham, H.P,, and
Page 117 and 118: Ar ea 2 / A1 Area 2_ -A2 -A1 X Theo
Page 119 and 120: determinedboth by his interfacewith
Page 121 and 122: Procedure The subject sat before th
Page 123 and 124: e used in designingdiscrete-timetas
Page 125 and 126: Factor Beta-weight Beta-weight Cour
Page 127 and 128: SUSTAINEDTURN POSITIONING EXTENDING
Page 129 and 130: DEVELOPMENT OF PERFORMANCE MEASURES
Page 131 and 132: performed all nine conditions. Ther
Page 133 and 134: REFERENCES Moray, N. 1979. Mental W
Page 135 and 136: |'0 _L_ o.S, K _/.s K/5" K/S_ - - -
Page 137 and 138: RATING CONSISTENCY AND COMPONENT SA
Page 139 and 140: also mounted on the left arm of the
Page 141 and 142: necessitating continued attention b
Page 143 and 144: 4_4 4_4141 4_4_0 00 OVERALLWORKLQAD
Page 145 and 146: whereas increasing the bandwidth fr
Page 147 and 148: Figure 3. He.an ratings and signifi
Page 149 and 150: Figure 4.. Hean ratings and signifi
Page 151 and 152: Figure 5. Mean ratings and signific
Page 153 and 154: ._ 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: In general, the results of the expe
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 and 206: given in Table 4. Also shown in the
Page 207 and 208: Table 5. MODEL PREDICTIONS FOR DIFF
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
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III. TASK ANALYSIS USING SAINT In o
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equired to detect the target, The c
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Examination of histograms of these
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EXP: SClII COND 19 (FLYBY 1, EW, EC
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conditions corresponding to particu
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o 0 _ oD _ • eo olo ooee ee I I I
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• oeo_ eeee eoJo 0 0 0 0 0 0 0 0
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REFERENCES I. Kleinman, D.L. and To
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screen according to a pre-defined t
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error signal. The error signal repr
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Similarly Fig. 11 ,12, and 13 prese
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.OO3- ,0_. .O01 Figure 6. Tracking
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(sNnaoot) _._aoa.LV 6U_M paxk:l ,aO
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2_ T v TRACK AZIMUTH ANGULAR RATECO
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itl ,ii11 i _l,lJl]illJ_ , i,'i , .
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manual control data to determine th
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elative cost penalty on control-rat
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pilot parameters. Conversely, a mat
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these changes to parameters that ar
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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
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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
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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
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References 1. Fitts, P.M. & Seeger,
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CHARACTERISTICS OF A COMPENSATORY M
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of a subject via two sets of wet el
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experimental system contained an ad
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signals which are band-limitedat la
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are equal to McRuer and Elkind's av
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23. K. Tanie, S. Tachi, K. Komoriya
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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 ------ ------._.
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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
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Yo P w_ _ _ _7p t / , °p # # ; / i
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B. Minimum Information Storage Traj
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Each machine degree of freedom, as
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AXIS I FALSE ALARM" IAL ZONE TRUE C
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3. Kreifeldt,J., Kiel, R., Richichi
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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
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DEXTEROUS MANIPULATOR LABORATORY PR
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deviation appears to increase for T
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Fig. 2 Manipulator Task Board 424
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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
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l, 4 Fo _.CE ST LC._,< l,d O,_ Figu
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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
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Claw Control Three methods were imp
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C) Sensor display and visual access
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Note that the most time consuming s
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Table I. Time Performance Data of P
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CONTROL -_ BIAS POSITION BUTTON INP
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L_ Figure 3. Cylinderand Box Module
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A C B Figure 5. Latching Mechanism
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Ca) (b) (c) U"l Figure7. BerthingSe
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HELICOPTER INTEGRATED CONTROLLER RE
Page 473 and 474:
METHOD Subjects. Subjects will be n
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illustrated in Figure 2. Subjects w
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amp. amp. amp. 4._ rrl _ -.4 --E [_
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TENTATIVE CRITERIA FOR CONTROLLERS
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simulator. Most soldiers who comple
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makes a mistake and is otherwise si
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The major future effort, other than
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FACTORSAFFECTINGIN-TRAIL FOLLOWINGU
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DISPLAY CONSIDERATIONS Location Our
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The three types of spacing cues ill
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that it tends to smooth out speed v
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symbology section, can also shed so
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If we apply the 50-second,5-percent
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REFERENCES I. Abbott, Terence S.; M
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TRAFFIC [ SELECTION CDTI ] SENSOR "
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cZ) P_ Figure6.- Conventionalcockpi
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\ 8_ Jacoxwaypoint"'_z_ JAC /kS_IG
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Figure I0.- Advanced cockpit CDTI f
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300 r--- ,,. f 250- _/_j' _ GROUNDS
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CHARACTERISTICSOF LEADAIRCRAFT STEA
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_ ' 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
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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
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statist.ic:al analysis. Averages fo
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than without for" the pilots of the
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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
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cared that the addition of CDTI int
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AIR TRAFFIC CONTROL OF SIMULATED AI
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joystick for the control yoke and a
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shown by a hexagon if the aircraft
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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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