Aviation Electronics Technician 1 - Historic Naval Ships Association

More documents

Recommendations

Info

compensation is needed for the longitudinal axis andis provided for by the development of outriggercompensators of Permalloy near the detectingelement.Permanent field compensation must be done inthree dimensions rather than in two, and it isaccomplished by three compensating coils mountedmutually perpendicular to each other (fig. 4-25, viewA). The aircraft is rotated in 5-degree and 10-degreesteps around its three axes. Adjustment of the fieldstrength is accomplished by controlling the amount ofdirect current that flows through a particular coil.Figure 4-25, view B, shows a circuit for a singlecompensating coil.Compensation for the dc magnetic field isaccomplished by using electromagnetic compensatingloops. The loops are arranged to provide horizontal,vertical, and longitudinal fields, and they are adjustedto be equal and opposite to the dc magnetic fieldcaused by the load current. The compensating loopsare connected across a variable resistor for aparticular distribution center, and they are adjusted toallow current flow proportional to the load current forcorrect compensation. Different types of aircrafthave several sets of compensation loops, dependingupon the number of distribution centers. In neweraircraft, production changes have been made to useground return wires to minimize loop size.The procedure for adjustment of the dc compensationsystem makes use of straight and levelflight on the four cardinal headings. For example,actuation of a cowl flap motor will cause dc fieldchanges representative of those caused by any nacelleload. The load is energized, the size and polarity ofthe signal are noted, and the compensation control isadjusted. The load is reenergized, and the compensationcontrol is adjusted again. Adjustments arecontinued until the resulting signals from the dc fieldare minimized.Under ideal conditions, all magnetic fields thattend to act on the magnetometer head would becompletely counterbalanced. In this state the effecton the magnetometer is the same as if there were nomagnetic fields at all. This state exists only when thefollowing ideal conditions exist:1. The aircraft is flying a steady course through amagnetically quiet geographical area.2. Electric or electronic circuits are not turned onor off during compensation.3. Direct current of the proper intensity anddirection has been set to flow through the compensationcoils, so that all stray fields are balanced.To approximate these conditions, the compensationof MAD equipment is usually performed inflight, well at sea. In this way, the equipment iscompensated under operation conditions, whichclosely resemble those of actual ASW search flights.From the foregoing, it should be clear that theobjective of compensation is to gain a state of totalbalance of magnetic forces around the magnetometer.Thereafter, any sudden shift in one of the balancedforces (such as an anomaly in the earth’s field force)upsets the total balance. This imbalance is indicatedon the recorder. Unfortunately, a shift in ANY of thebalanced forces will be indicated. Shift in any of theforces other than the earth’s natural field are regardedas noise.MAJOR COMPONENTSFigure 4-25.-A. Arrangement of compensating colts.B. Compensating coil circuit.The MAD system consists of the AN/ASQ-81MAD set, AN/ASA-64 submarine anomaly detecting(SAD) group, AN/ASA-65 magnetic compensator4-20
group, AN/ASA-71 selector control group, and theRO-32/ASQ MAD recorder.AN/ASQ-81 MAD SetThe AN/ASQ-81 set consists of the DT-323magnetic detector, the AM-4535 amplifier-powersupply, and the C-6983 detecting set control box.DT-323 MAGNETIC DETECTOR.— Thedetection element includes six separate heliumabsorption cells and six IR detectors, arranged inpairs, with the pairs oriented at 90° to each other.This configuration ensures that one or more of thepairs is at least partially in line with the earth’s fieldregardless of aircraft attitude or direction of flight.The signals from all three detector pairs are combinedin a summing amplifier. The final output to theamplifier-power supply is not affected by aircraftmaneuvers because of the arrangement.AM-4535 AMPLIFIER-POWER SUPPLY.—The amplifier-power supply (fig. 4-26) serves twopurposes. The first purpose is the power supplyportion. This section provides the necessary power tothe MAD subsystem. The amplifier section containsthe necessary electronics to detect the anomaly signalfrom the detector output signal.There are three fail indicators on the amplifierpowersupply. The FAIL light comes on when there isa fault in the assembly being tested with the BITEswitch. The FAIL DETECTOR and the FAIL AMPPWR SUPPLY lights indicate failure of the magneticdetector or the amplifier-power supply. The ALTCOMP dial is used to vary the amplitude of thealtitude compensation signal. The BUILT IN TESTswitch provides a self-test of quick replaceableassemblies in the amplifier-power supply. The twocircuit breakers provide circuit protection for the dcpower to the magnetic detector and the 115-volt acpower to the amplifier-power supply.On the right side of the amplifier-power supply,there is a hinged door that covers a maintenancepanel. When this door is closed, the equipmentoperates in the normal mode. On the maintenancepanel there is a RES OSC ADJ switch that is used tomanually adjust the resonance oscillator frequencyduring maintenance procedures. There is also aMODE SELECT switch that selects various systemconfigurations necessary for proper maintenance andtroubleshooting.C-6983 CONTROL BOX.— The detecting setcontrol box (fig. 4-27) contains the operating switchesand indicators for the MAD system. Across the top ofthe faceplate are five indicators that indicate faults inthe other units. The indicator labeled 3 indicates amagnetic detector failure when lit. The indicatorlabeled 2 indicates amplifier failure. The next twoindicators indicate a control box fault. The SYSREADY indicator illuminates when the system isready for operation. This indicator will blink duringwarm-up.There are three toggle switches across the middleportion of the control box. The one on the right is thepower switch. This switch applies power to thesystem. The middle switch is labeled CAL. It selectsthe calibration signal for use. The switch on the left isFigure 4-26.-AM-4535 amplifier-power supply.Figure 4-27.-C-6893 detecting set control.4-21
Page 7 and 8:
PASS/FAIL ASSIGNMENT PROCEDURESIf y
Page 9:
Student CommentsCourse Title:Aviati
Page 12 and 13:
Table 1-1.-Radio-Frequency Spectrum
Page 14 and 15:
Figure 1-3.-LS-602/AI control panel
Page 16 and 17:
Figure 1-4.-Manchester encoding.thr
Page 18 and 19:
they can complete a full cycle. The
Page 20 and 21:
one-shot circuit output is directly
Page 22 and 23:
Figure 1-7.-VHF-AM control box.Figu
Page 24:
indicators in the following text. E
Page 27 and 28:
Figure 1-11.-C-9245/ARC-161 control
Page 29 and 30:
and the PWR/FILL switch is not in t
Page 31 and 32:
panel is in OFF. If the DTS control
Page 33 and 34:
the keyboard are sent directly. Rec
Page 35:
the signal data converter, where it
Page 38 and 39:
Navigation is both an art and a sci
Page 40 and 41:
this axis at right angles to it (fi
Page 42 and 43:
. Course is the intended horizontal
Page 44 and 45:
The standard atmosphere is theoreti
Page 46 and 47:
eadings are higher than actual. Thi
Page 48 and 49:
The barometric switch in the RAWS a
Page 50 and 51: Major ComponentsThe AN/ARN-84(V) TA
Page 52 and 53: the outputs is used for the automat
Page 54 and 55: DOPPLERIn the following text we wil
Page 57 and 58: CHAPTER 3RADARAs an avionics superv
Page 59 and 60: the antennas will stop at the posit
Page 61 and 62: AS-2146/APS-115 AntennaThe radar an
Page 63 and 64: completes the processing of radar a
Page 65 and 66: In the on-line mode, the sensor sta
Page 67 and 68: Mode SwitchThe mode switch is pract
Page 69 and 70: purpose of the horizon line is to i
Page 71 and 72: Maximum range for tracking is 40,00
Page 73 and 74: transmit a reply when RF interrogat
Page 75 and 76: airspeed-altitude computer. All fra
Page 77 and 78: SIF reply code is identical to the
Page 79: In mode 4, the reply video pulse is
Page 82 and 83: sound wave. The frequency (in hertz
Page 84 and 85: to affect the rate of travel of the
Page 86 and 87: DOPPLER EFFECTWhen there is relativ
Page 88 and 89: Figure 4-7.-Transducer installed on
Page 90 and 91: The Sonar Detecting-Range Set AN/AQ
Page 92 and 93: Figure 4-16.-RO-358/ASQ-13A.mechani
Page 94 and 95: applies 115 volts ac to the transmi
Page 96 and 97: are known as angles of dip (fig. 4-
Page 98 and 99: feet in length and represents the f
Page 102 and 103: labeled ALT COMP. This switch is us
Page 104 and 105: select which signal goes to which p
Page 106 and 107: the passive directional sonobuoy (f
Page 108 and 109: REVIEW QUESTIONSQ1. How was the wor
Page 110 and 111: TACAN signals. When localizer signa
Page 112 and 113: 1. The HEADING NO-GO indicator illu
Page 114 and 115: Figure 5-7.-New optical sight with
Page 116 and 117: computer’s program determines whi
Page 118 and 119: ias circuit, horizontal and vertica
Page 120 and 121: Figure 5-9.-Symbology—Continued.5
Page 122 and 123: Figure 5-14.-Sparrow mode.Figure 5-
Page 124 and 125: TACTICAL DISPLAY SYSTEM INTERFACEFi
Page 126 and 127: electrical signal, which varies in
Page 128 and 129: noise-free at that level. The impor
Page 130 and 131: Like the random interlace, this sys
Page 132 and 133: The polarity of the signal develope
Page 134 and 135: The SEC tube has applications in ex
Page 137 and 138: CHAPTER 6INFRAREDThe term infrared
Page 139 and 140: Table 6-1.-Characteristics of IR Ra
Page 141 and 142: potential difference across a PN ju
Page 143 and 144: system increases, and the reliabili
Page 145 and 146: used in the Navy, their principles
Page 147 and 148: signals from the control servomecha
Page 149 and 150: Figure 6-15.-FLIR positioning/stabi
Page 151 and 152:
Figure 6-17.-Video converter video
Page 153 and 154:
clamping signals from the sync gene
Page 155 and 156:
shared by both azimuth and elevatio
Page 157 and 158:
where they are converted into three
Page 159 and 160:
go to the azimuth/elevation heat si
Page 161 and 162:
TARGET TRACKING SIGHT CONTROLAs men
Page 163 and 164:
control is injected in this module.
Page 165 and 166:
CHAPTER 7WEAPONS SYSTEMSAs a result
Page 167 and 168:
Figure 7-5.-Master light control pa
Page 169 and 170:
Rocket firing systemWalleye systemA
Page 171 and 172:
The wing-form display is displayed
Page 173 and 174:
Figure 7-15.-Emergency jettison con
Page 175 and 176:
The A/A weapon select switch select
Page 177 and 178:
Part of the system consists of unpr
Page 179 and 180:
Figure 7-22.-SH-3 (series) search a
Page 181 and 182:
ottle and the ECU are mounted on to
Page 183 and 184:
Figure 7-25.-Pylon/rack assembly.ci
Page 185:
REVIEW QUESTIONSQ1. True or False.
Page 188 and 189:
COMPUTER APPLICATIONSTYPES OF COMPU
Page 190 and 191:
the most important. This data manip
Page 192 and 193:
and other data that are to be used
Page 194 and 195:
to represent the same data that was
Page 196 and 197:
compatibility permits the computer
Page 198 and 199:
most cases, the processing speed fa
Page 200 and 201:
4. Stores the results of manipulati
Page 202 and 203:
An overall check of a computer can
Page 205 and 206:
CHAPTER 9AUTOMATIC CARRIER LANDING
Page 207 and 208:
stabilized deck-coordinated system
Page 209 and 210:
Figure 9-3.-Mode I landing sequence
Page 211:
Figure 9-5.-Lateral automatic wave-
Page 214 and 215:
Precipitation StaticPrecipitation s
Page 216 and 217:
l Sliding-contact interference. Thi
Page 218 and 219:
the signal applied to it. These spu
Page 220 and 221:
the following methods: short circui
Page 222 and 223:
Figure 10-4.-Internal construction
Page 224 and 225:
Figure 10-9.-Methods for using RC f
Page 226 and 227:
Band-Rejection FiltersA band-reject
Page 228 and 229:
Causes of Static ElectricityGenerat
Page 230 and 231:
composed of carbon particles, impre
Page 233 and 234:
APPENDIX 1REFERENCES USED TODEVELOP
Page 235:
Chapter 7Airborne Weapons/Stores Lo
Page 238 and 239:
CHAPTER 3A1.A2.A3.A4.A5.A6.A7.A8.A9
Page 240 and 241:
A7. Linking two or more computers t
Page 242 and 243:
FORMULASAIII-2
Page 244 and 245:
AIII-4
Page 246 and 247:
Comparison of Units in Electric and
Page 248 and 249:
Antisubmarine warfare weapons syste
Page 250 and 251:
Electrostatic discharge, 10-15compo
Page 252 and 253:
Heads-up display (HUD), 5-5air-to-a
Page 254 and 255:
NNavigation basics, 2-1airborne nav
Page 256 and 257:
Teletype system, 1-22block diagram,
Page 259:
Assignment QuestionsInformation: Th
Page 262 and 263:
1-11. What will the Sillumination o
Page 264 and 265:
1-35.1-36.1-37.1-38.UHF-1 does NOT
Page 266 and 267:
1-59. What arethat thetactical1. Fr
Page 268 and 269:
ASSIGNMENT 2Textbook Assignment:
Page 270 and 271:
IN ANSWERING QUESTIONS 2-22 THROUGH
Page 272 and 273:
2-43. What method does the AN/APN-1
Page 274 and 275:
2-64. What distance is the maximum
Page 276 and 277:
3-12.3-13.The antenna position prog
Page 278 and 279:
3-32. The 128 nautical mile range i
Page 280 and 281:
IN ANSWERING QUESTION 3-53,FIGURE 3
Page 282 and 283:
3-74. What is the nominal peak powe
Page 284 and 285:
4-12. Sonar transmission losses can
Page 286 and 287:
4-31.4-32.4-33.When positive gradie
Page 288 and 289:
4-52. The function of the dual curs
Page 290 and 291:
4-71. The angle between a magnetic
Page 292 and 293:
IN ANSWERING QUESTIONS 5-9 THROUGH
Page 294 and 295:
5-29. What component contains theop
Page 296 and 297:
5-51. What type of RF output signal
Page 298 and 299:
Page 300 and 301:
6-20. On the HSI, when a tactical m
Page 302 and 303:
6-42. What control(s) the symbolbri
Page 304 and 305:
6-65. Which, if any, of the followi
Page 306 and 307:
7-11. If the temperature of a black
Page 308 and 309:
7-34.A scan mirror is indexed three
Page 310 and 311:
7-56. What is the primary differenc
Page 312 and 313:
Page 314 and 315:
8-21. With the landing gear handle
Page 316 and 317:
8-42. With the F/A-18 AIM-9 Sidewin
Page 318 and 319:
8-66. The jettison of wing stores I
Page 320 and 321:
9-13. What method is used to change
Page 322 and 323:
9-36. In magnetic core memories, a
Page 324 and 325:
9-57. What typeaccess toof instruct
Page 326 and 327:
10-12. To maintain the angle-of-att
Page 328 and 329:
10-35. A receiver tuned to 2.4 kHze
Page 330:
10-55. When rubbed against any of t
show all

Aviation Electronics Technician 1 - Historic Naval Ships Association

Create successful ePaper yourself

Delete template?

Save as template?