NBSIR 74-589R

Instruction and Technical Manual for

Prototype Landing Signal Officer's

Display System

Charles C. Gordon

Measurement Engineering Division

Institute for Applied Technology

National Bureau of Standards

Washington, D. C. 20234

November 1974

Interim Report

Sponsored by:

Commander

Naval Air System Command

Code 53722

Department of Navy

Washington, D. C. 20361
rI1
NBSIR 74-'589R

INSTRUCTION AND TECHNICAL MANUAL FOR

PROTOTYPE LANDING SIGNAL OFFICER'S

DISPLAY SYSTEM

Charles C. Gordon

Measurement Engineering Division

Institute for Applied Technology

National Bureau of Standards

Washington, D. C. 20234

November 1974

Interim Report

Sponsored by;

Commander

Naval Air System Command

Code 53722

Department of Navy

Washington, D. C. 20361

U. S. DEPARTMENT OF COMMERCE, Frederick B. Dent, Secretary

NATIONAL BUREAU OF STANDARDS. Richard W. Roberts. Director

Table of Contents

Page

1.0 Introduction 1

1.1 Specifications 6

1.1.1 Displays 6

1.1.2 Head-Up Displays ^> 1.1.3 Intercom Unit 7

1.1. ^ Power Required 7

2.0 Console Display and Controls 7

2.1 Console Mount and Controls 7

2.2 Displays and Controls 7

2.2.1 Intercom and PLAT 7

2.2.2 Pointer Displays 7

2.2.2a Airspeed 12

2.2.2b Rate of Descent 12

2.2.2c Range 12

2. 2. 2d Ramp Motion 12

2.2.3 Deck Open and Closed and LSO Wave-Off ... 12

2.2. n Aircraft Type 13

2.2.5 ACLS Status 13

2.2.6 V/ind Angle and Speed 13

2.2.7 MOVLAS 13

2.3 Head-Up Display 13

2.3.1 Airspeed 1^

2.3.2 Ramp Motion 1^

2.3.3 Aircraft Range 14

2.3.4 Glide-Slope Line Up 14

3.0 Console Operation 14

4.0 Console Storage , IH

Technical Details of the Equipment ...... 19

5.0 Main Pov/er Control and A.C. Wiring 19

5.1 Power Panel 19

5.2 Main Power Turn On 19

6.0 Head-Up (HUD) Display 20

6.1 Head-Up Display Optics 2 0

6.2 liead-Up Display Generator 20

6.2.1 CRT Beam Path 20

6.2.1a Timing 22

6.2.1b Signals 22

6.2.1c Blanking 22

6. 2. Id Detailed Description of CR'^ Beam Path 22

6.2.2 Waveform Generators, Board i^l/99 23

6.2.3 Display Synthesizer, Board #100/199 .... 24

i
6.3 CRT Deflection Amplifier and Yoke 2f)

6Jl CR'^ Pov;er and Interface Circuitry 3^

7.0 Console Display Scales-Introduction 31

7.1 Airspeed 31

7.1.1 Radar Airspeed 3') 7.2 Rate of Descent 3^^ 7.3 Range 35

7. ^ Ramp Motion 35

3.n Console Indicators ' 36

3.1 Deck Status 3^

8.1.1 Deck Open 3^

8.1.2 Deck Closed 3^

8.1.3 LSO Wave-Off (PLOLS Wave-Off) 37

• 8.2 ACLS Radar Status o 37

8.1.2 Radar Selection Switch 37

8.2.2 Airspeed Selection Switch 37

8.2.3 Lock-On and Fode 38

8.2.4 ACLS V/ave-Off 38

8.2.5 V/arninp; 39

8.3 rWLAS 3^

- 8.4 Aircraft Type Designator 39

8.5 Wind Speed 39

8.6 V/ind Direction 40

9.0 Plat and Intercommunication Units 41

10.0 Miscellaneous • 4l

10.1 LSO Console, Auxiliary Electronic Cabinet and

Ship's Source V/irinc 41

10.2 Junction Box Wiring Requirements 42

10.3 Console Plug Layout 42

10.4 Head-Up Scale, Console Scales Console Scale . Pointer Supplies 42

10.5 V/ind and Aircraft Type Pov/er Supplies 43

10.6 Card Cage Layout in Auxiliary Electronic Cabinet. 43

10.7 Synchro-to-DC Converter Layout 4 3

10.8 Miscellaneous Connections 4 3

11.0 Simulator 44

12.0 Appendix 44

12.1 Scale Removal .• 4 4

12.2 UUD Scale Lamp Replacement 4 5

12.3 Removal of Rear Access Panel 46

12.4 Removal and Installation of HUD CRT Assembly . . 46

12.5 IIUD Circuit Card Wiring Table 47

12.6 HUD Calibration Table 40

12.7 Physical Characteristics of Console, Panning Head

and Auxiliary Electronic Cabinet 49

12.8 Drawing List 40

ii

I
INSTRUCTION AND TECHNICAL MANUAL

FOR

PROTOTYPE LANDING SIGNAL OFFICER'S DISPLAY SYSTEM

1.0 Introduction

This manual describes the prototype Landing Signal Officer's (LSO) Display

System that Is Installed aboard the aircraft carrier USS Ranger CVA61. The

prototype LSO Console was designed and engineered to fulfill requirements proposed

in a study for an improved LSO work station^). The first four sections (1.0 thru

^.5) of this manual provide the information needed to operate the equipment, while

the remaining sections give a technical description of the equipment and will be

useful when service or modifications are required. The technical sections are

written to be used in conjunction with the electronic and mechanical drawings

furnished with the equipment.

The display system consists of two major parts: a Display Console, Figure 1,

located at the LSO station, and an Auxiliary Electronics Cabinet, Figure 2,

located one deck directly below the LSO platform. The information displayed by

the Console is obtained from the ship's radars and recovery-status sources.

The front panel of the Console contains scales and indicators that display

Airspeed, Range, Rate of Descent, Ramp ' (or deck) Motion, Aircraft Type, Wind

Direction and Speed, Deck Status, Pilot Landing Aid Television (PLAT), and

Automatic Carrier Landing System (ACLS) operating status. In addition, the

Console provides a Head-up Display (HUD), that shows Airspeed, Range, Ramp Motion,

and aircraft Glide-Slope position. The HUD information is optically focused to - appear at infinity and it can be superimposed on the sky by Console tilt and

rotation. This enables the LSO to see a distant aircraft and the HUD Display in

the same field of view; both are simultaneously in focus. Cross lines in the HUD

are glide-slope reference lin^s for showing the position of its electronically

generated Aircraft Symbol, but do not function as a "gunsight" reference to use

the HUD for visual aircraft tracking.

The Auxiliary Electronic Cabinet ,' Figure 2, contains the Interface and signal

processing electronics between the ship's signal sources and the Console displays.

This cabinet is located in the emergency escape room for the LSO which is directly

below the LSO platform. The cabinet is secured to the inside wall of this room

with its front facing the watertight door; . All the input and output signal cables

as well as the power cables come into the front of the cabinet. The cables

between the Auxiliary Electronic Cabinet and the LSO Console go through the

outside bulkhead of the room using watertight fittings. All the ship's source

signals come into a Signal J-box and a Synchro Signal J-box. These boxes are

mounted on the inside of the outer bulkhead of this room and are the distribution

points for the signals to the Auxiliary Electronic Cabinet.

The Auxiliary Electronic Cabinet is divided into an upper and a lower section

which are accessible by sliding either section forward. Figure 3 shows a top view

of the upper chassis. Significant components visible in this photograph are

labeled. The lower chassis is shown in Figure ^. The visible components are also

labeled for Ideptification. The Scale and Display card cage has been doubled In

size and extends nearly to the front of the panel for the final installation on

the Ranger. This was necessary in order to include Interface cards for the SPN44, wind, and aircraft type information. Not visible in this lower chassis are

power supplies for the CRT, cards, and lamps.

TT) Landing Signal Officer: Work Station Design, Technical Report 1707,

Dec. 1970 by Gail J. Borden, Human Factors Research, Inc.
2
3


1.1 Specifications

1.1.1 Displays

(1) Airspeed ; 80 to l80 knots, one knot resolution, approx. 38.5 cm

(15.15 In) scale, incandescent moving pointer indicator, adjacent

trend pointer.

(2) Range ; 0 to 3 nautical miles, 0.1 nautical mile resolution,

approx. 11.8 cm (4.65 in) scale. Incandescent moving pointer

indicator.

(3) Rate of Descent ; 0 to 2000 ft/min, 50 ft/min resolution, approx.

15.6 cm (6.15 in) scale, incandescent moving pointer indicator,

adjacent trend lamp.

(i|) Ramp Motion ; 0 to + 20 ft and -19 ft, with one foot resolution,

approx. 15.6 cm (6.15 in) center zero scale, incandescent moving

pointer indicator, trim lamp for ship's trim independent of Ramp

Motion.

(5) Deck Open ; Green lamp

(6) Deck Closed ; Red lamp

(7) LSO Wave-Off; Red flashing, 90/min

(8) True Airspeed ; White light, TAS, indicator

(9) Closing Airspeed ; White light, CLSG, indicator

(10) SPN-42 ; White light, il2, indicator

(11) SPN-12/44 ; White light, 12/44, Indicator

(12) Aircraft Type Designator ; Alpha-numeric incandescent characters

for A3, A4, A5, A6, A7, CI, C2, El, F4 and F8 aircraft.

(13) Automatic Carrier Landing System (ACLS) ; Incandescent characters

for Lock-On, Modes I, II, or III.

(14) ACLS Wave-Off ; Blue flashing,' l80/min

(15) VJind Angle ; Alpha character for port (P) or starboard (S) and

numeric characters of 0° through 50° for angle, incandescent.

(16) Wind Speed ; Incandescent characters for 0 to 99 knots.

(17) PLAT: Pilot landing aid television monitor

(18) MOVLAS: Incandescent repeater of the ship's Manually Operated

Visual Landing Aid System.

1.1.2 Head-Up Displays (HUD)

(1) Mirror ; 10-inch diameter, spherical concave of l8-inch focal

length.

(2) Combiner ; 30% reflectance, 70^ transmittance , 1/4 inch safety

glass, 10-1/2 inches by 13-1/2 inches.

(3) CRT : High intensity HUD type, 3 inch diameter, 70° deflectance, iWV anode, 6.3V filament.

(4) Airspeed display ; 80 to l80 knots of true airspeed.

(5) Ramp Motion ; +20 ft of ship's ramp motion or ship's trim

separately.

6
(6) Glide-Slope Path ; Aircraft symbol showing azimuth and altitude

relative to the touch-down-point with 30 ft or If) ft scale

factor selection. Azimuth of 240 ft left and right and

altitude of +240 ft up and -150 ft down are Indicated with the

30 ft scale factor. Azimuth of 80 ft left and right and altitude

of +80 ft and -50 ft are Indicated with the 10 ft scale factor.

(7) Range Circle ; Appears v;hen range of aircraft Is one mile or less

from the carrier and disappears as a function of Its distance

from the carrier as the aircraft approaches the deck 3/4 circle

equals 3/4 mile, 1/2 mile, 1/4 circle equals 1/4 mile, etc.-

1.1.3 Intercom Unit ; Two station 21MC (LS-458/SIC) unit for communication to

Primary Plight (Prl Fly) or Carrier Traffic Control Center (CATCC).

1.1.4 Power Required ; 115V, 60 Hz,- single phase, 15 ampere.

2.0 Console Displays and Controls

2.1 Console Mount and Controls

The console is located at the LSO platform and Is mounted on a hydraulic

platform. Figure 5. The hydraulic platform is built around a hydraulic

anchor damper (Mark VII, Mod. II) from the ship's arresting gear. The anchor

damper is mounted for vertical travel. When lowered, the LSO console Is

below the LSO platform and is stored in an aluminum box with a weatherproof

cover. Figure 6. With the platform raised to its highest position the center

of the HUD combiner glass is 73 Inches above the deck. The platform can be

stopped and locked in any lower position for a shorter LSO by the use of the

up and down hydraulic valve selector sv/ltch and the motor control switch. A

TV-type panning head is mounted between the hydraulic platform and the

console, thereby allowing the console to be rotated horizontally and tilted.

Viewing problems caused by the sun, glare, or other lighting conditions can

be minimized by utilizing the panning head.

2.2 Displays and Controls

No controls for the console displays are located on the front panel.

The controls for the Pilot Landing Aid Television monitor (TLA'^) are located

on the left side of "the Console, Figure 7, and all other console display

controls are on the right side of the Console, Figure 8.

2.2.1 Intercom and PLAT

A standard, two-station, intercomm.unicat ion station (LS-45B/SIC)

is mounted on the right side of the Console front panel. It

communicates with Primary Flight (Prl. Fly) and the Carrier Traffic

Control Center (CATCC). All of its controls are on the front and It

Is powered from the ship's Intercom system.

At the center of the left side of the front panel is the Pilot

Landing Air Television monitor (PLAT), which connects to the ship's

common centerllne television camera that views the aircraft

approaching for a recovery. The on-off switch, contrast, brightness,

horizontal hold and vertical hold controls for the PLAT^ are on the

left side panel. Figure 7. . 2.2.2 Pointer Displays

The PLAT is framed by four, pointer-type displays; Airspeed,

Range, Rate of Descent, and Ramp (or Deck) Motion. Each display

consists of a row of incandescent lamps adjacent to a calibrated scale

that is separately back-lighted. Each rovr of lamps serves the

function of a scale pointer, the pointer position being indicated by

turning on the appropriate lamp. The lamps are mounted in individual

compartments, and in order to provide redundancy two lamps are mounted

in each compartment. Each of the four pointers has its own intensity

control and its own on-off toggle switch, located on the right side

panel. Figure 8. Individual control of the backlighting for the four

7
RANGER JNSrAi
III"""

11
scales is not provided. Instead, a single toggle switch provides OMOFF control; and a momentary action double-throw, center OFF, toggle

switch controls intensity. Holding the switch UP will increase

intensity, and holding it DOWN will reduce intensity.

2.2.2a Airspeed

The Airspeed scale, located above the PLAT, covers the

range of 80 to l80 knots. Its pointer will stay at 80 knots

when the correct value is less than or equal to 80, and will \ read l80 knots whenever the correct value is equal to or greater than 180. A trend light is adjacent to the main

pointer. When the airspeed is increasing, the trend lamp is one knot less and with decreasing airspeed, the trend lamp is

one knot greater. Either true airspeed (TAS) or closing

airspeed (CLSG) may be chosen for presentation. The selection

is made by the TAS/CLSG toggle switch located near the middle

of the right side control panel. The choice thus made is shown

by the letters TAS or CLSG appearing at the right-hand end of

the Airspeed scale. In addition, either the ship's SPN-il2

radar or its SPN-12/^^ radar can be selected as the source of

the airspeed signal. The selection is made by the SPN-42 or

SPN-12/44 toggle switch, and the choice thus made is indicated

at the right-hand end of the Airspeed scale by the presence of

the number, 42 or the number, 44,

2.2.2b Rate of Descent

The Rate of Descent scale is the vertical scale to the

right of the PLAT, It indicates the rate of descent in

hundreds of feet per minute for, an approaching aircraft. The

scale covers a range of zero to a maximum of 1912 feet per

minute with a resolution of 50 feet per minute. If the rate of

descent is greater than 1912 feet per minute, it will continue

to read this value. A' trend lamp adjacent to the main pointer

and of lesser intensity is used to indicate the direction of

change for rate of descent. If the trend lamp is a higher

number, the rate of descent is decreasing; and if it is a lower

number, the rate is increasing.

2.2.2c Range

The console Range Scale is below the PLAT display. It

operates when the aircraft is 3 nautical miles or less from the

touchdown point. Its pointer will remain at 3 miles when the

range is 3 miles or greater. The scale has a resolution of 0.1

nautical mile.

2. 2. 2d Ramp Motion

The Ramp Motion Scale is the vertical scale to the left of

the Plat display. The input information source is the ship's

Harmonization Computer (SFHC) Instead of the SPM-42 radar. It

indicates ramp motion plus ship's trim in the normal operating

mode. A momentary toggle switch on the right side control

panel is used to select ship's trim as a separate display on the Ramp Scale. A Trim lamp below the scale comes on when

ship's trim Is being selected for display. The scale is a zero

center display with a range of +20 feet of high ramp to -19

feet of low ramp. The area between +10 feet and +20 feet is

covered by a red filter to produce a red pointer indication.

This is the danger area and warns the LSO of a possible ramp

strike. The ramp pointer remains at full scale when the ramp

motion exceeds the +20 or -19 feet extremes.

2,2.3 Deck Open and Closed and LSO V/ave-Off

Three deck status indicators are located on the left of the

Airspeed Scale, A green light indicates the deck Is open and ready to

12
land aircraft. An adjacent red light Indicates a closed deck and any

approaching aircraft must not land. With a closed deck, any aircraft

is given a wave-off. The LSO initiates a Presnel Optical Landing

System Wave-Off (FLOLS wave-off) with a "pickle-switch". The wave-off

is indicated by the red flashing lamps below the open and closed deck

lamps. The rate is approximately 90 flashes per minute.

2.2.ii Aircraft Type

The aircraft type that is being recovered on each landing is

indicated by one alpha and one numeric character. These characters

are displayed between the Rate of Descent scale and the Intercom

station just above the ACLS status indicators. This display is set up

by signals from Pri. Ply and is used for verification between the

• recovery set up and the aircraft in the glide-slope to be recovered.

Seven-segment, incandescent lamp indicators are used for the alphanumeric aircraft type characters.

2.2.5 ACLS Status

The operating status of the Automatic Carrier Landing System

(ACLS) is indicated Just below the aircraft type by backlighted

indicators. The ACLS system indicates a Lock-On and three modes of

operation. Mode I is a full ACLS landing. Mode II is an instrument

landing approach and Mode III is a "talk down" landing. The mode

indicators are below the Lock-On light. The ACLS system generates a wave-off when data obtained from the computer and radar system or aircraft response to the landing instructions are questionable. The

ACLS wave-off signal is displayed as a blue flashing light below the

Model lamps. The flash rate of this v/ave-off is approximately l80 per

minute

.

2.2.6 Wind Angle and Speed

The wind angle, either port (?) or starboard (S), and the

magnitude of the angle in degrees is indicated by three alpha-numeric

characters below the ACLS Status displays. The angle is relative to

the centerline of the angled landing deck which is 10 degrees to port

of the ship's centerline. Therefore, wind down the centerline of the

ship would be indicated on the Console as an S 10° wind. Sevensegment, incandescent indicators are also used for these alpha-numeric

characters. Approximately 50° can be displayed by the wind angle

• indicators in either the port or starboard direction. Normal landing

operations are conducted with the wind within 10° of the centerline

touch-down-point

.

The two numeric characters below the wind angle indicators

display the wind speed. These are capable of 0 to 99 knots

indication. The characters are the same type as in the wind angle

display. Normal operations are 30 knots of wind speed at the proper

angle down the recovery deck.

2.2.7 MOVLAS

The MOVLAS is a repeater which operates when the ship's Manually

Operated Visual Landing Aid System (MOVLAS) is used. The MOVLAS

repeater is located on the left side of the console. Figures 1 and

Figure 2. The repeater duplicates at the LSO Console the MOVLAS

display of datum bar and "meatball" lights that the pilot sees. The

MOVLAS repeater has a separate on-off switch and intensity control

which are located on the right side panel of the console. Figure 8.

2.3 Head-Up Display

Figure 6.2.1 shows the information displayed by the Head-Up Display

(HUD). Some of this can also be seen in the View Combiner in. Figure 1. The

eyes of the observer should be in front of, and at the same height as the display. Positioning the eyes too far to the side, or too high or low, will

cause part or all of the display to disappear from sight. A 'relative narrow

13
angle of view is a characteristic inherent in all HUD's. The HUD display

should be adjusted to approximately the same viewing- angle as the glide-slope

path of the approaching aircraft. This permits a horif^ontally shift of the

eyes to monitor the HUD information without lowering the head. Left and

right views of the HUD in position are shown in Figures 7 and 8 respectively.

Figure 9 shows the Console back with the lamp housing open. Figure 10 is a view of the top of the Console with the combiner glass removed.

2.3.1 Airspeed

The Airspeed scale covers the range of 80 to l80 knots and always

indicates true airspeed (TAS). Its pointer will disappear off- scale

if the speed is more than a few knots outside of this range.

2.3.2 Ramp Motion (or Deck Motion)

Ramp Motion is the vertical scale at the extreme left. This

scale displays Ramp Motion which includes the ship's trim. The

pointer will move off-scale if the scale limits are exceeded.

Otherwise it is identical to the Ramp Motion display that is on the

Console front panel. Ship's trim without ramp motion can be obtained

by using the trim only switch to display trim on the front panel ramp

scale.

2.3.3 Aircraft Range

Aircraft Range is displayed as a large, disappearing circle.

When the aircraft is more than one nautical mile away, the circle does

not appear. When the aircraft approaches to 0.99 miles, a nearly

complete circle suddenly appears on the display. At 0.5 miles, half a

. circle remains; at 0.25 miles a quarter of the circle remains visible;

and so on until at about 0.01 miles the circle disappears completely.

The circle, or portions thereof has a constant diameter at all times.

2.3.^ Glide-Slope Line Up

Glide-Slope Line Up information is presented by the location with

respect to reference cross lines, of an electronically generated

aircraft symbol. A choice of two scale factors is available, 30 feet

per division (ft/div) and 10 feet per division. To indicate to the

observer that the 30 ft/div is in use, the aircraft is represented as

a small circle. Wings and a tail are added when the 10 ft/div scale

factor is in use. The selection is made with a three position rotary

switch on the HUD illumination panel. The third position is an automatic (Auto) mode and is the preferred position for normal

operation. This mode produces a scale factor of 30 ft/div for the

aircraft symbol when the aircraft is more than one nautical mile away,

and a symbol scale factor of 10 ft/div and the range circle (Sec

2.3.3) when the aircraft is less than one mile away. For the 30

ft/div scale factor, the displacement of the aircraft symbol is

electronically limited so that the symbol ivill remain in view no matter how far the aircraft is from the desired glide slope. With the

10 ft/div scale factor, the symbol can be driven completely out of

view.

3.0 Console Operation

The following procedures for operation of the LSO Console apply to the unit

as installed on the LSO platform of the USS Ranger, CVA61.

3.1 Fold back the wooden floor over the console storage box. Figure 6.

3.2 Remove the storage box cover by releasing the four hold down screw

clamps. Figure 6.

3.3 Store the box cover in the vertical rack provided at deck level

just forward of the platform.-

1^
15
16
3.^ Place the hydraulic valve selector In the up position. This is

with the pointer up and handle down.

3.5 Make sure the LSO Console will not strike any of the box sides

when being raised.

3.6 Press and hold the motor switch to raise the unit to the desired

height for the operating LSO. Release the motor svritch. If it is

necessary to lower the console, change the hydraulic valve selector

switch to pointer down and operate the motor switch. The hydraulic

valve selector switch must either be placed in the neutral (horizontal)

position or returned to the up position to prevent the console from

creeping down.

3.7 Release the spherical concave mirror latch and raise the mirror into

place, firmly securing it with the large diameter knurled knob.

3.8 Flip the combiner protector cover to the right side. Magnetic strips

will hold it in place.

3.9 Hold the top edge of the combiner glass with the fingers of the left hand,

compress the two center knobs together at the center of the frame base,

lift the top edge with the left hand while sliding the bottom edge

forward until it stops with the glass at a 45° angle, release the

compressed knobs in the right hand making sure the pins snap into

the track holes to secure the glass in place. See Figure 5 for the

LSO Console in the operating position.

3.10 Uncover the MOVLAS on the left side by opening its door to a ^5°

angle. Figure 7.

3.11 On the left side. Figure 7, turn the pointers control knob completely

counterclockwise and the toggle switch to OFF on the HUD Illumination

Panel. This prevents the HUD CRT from being too bright when power is

applied.

3.12 The console is now ready for application of Main Power.

In the following steps use Figure 8 as a reference. This is a photograph of the right side control panel.

3.13 Turn the Main Power switch on. 3.14 Adjust the Deck Open or Closed, radar type SPM42 or SPN12/44 and

Closing (CLSG) or True (TAS) airspeed lamps to the desired intensity

with the Lamps Control in the Deck Status Section of this panel.

Note ; The alarm is not used on the Ranger so these controls do not

function.

3.15 Turn on the Ramp Motion, Airspeed, Range, Sink Rate (Rate of Descent),

ACLS and MOVLAS switches. These are adjacent and to the right of each

potentiometer control for each function. Turn on the panel intensity

control switch in the lower left corner of this panel if illumination

of the right and left control panels is required.

3.16 If the console is being used in daylight turn off the panel intensity

control switch since each panel is etched with white letters for daylight

use. For night or low light level use, adjust the panel intensity level

with the potentiometer control which controls both right and left panels.

3.17 Adjust each pointer of the four display scales to the desired intensity

for the existing ambient light.

3.18 Adjust all scale intensities with the single Scale Intensity control.

This is a center off switch which is momentary in both directions from

center. Holding this switch up increases the scale intensity, holding it

dovm lowers the intensity.

3.19 The ACLS control adjusts the Lock-On, Mode I, II or III Intensities of

the ACLS status display.

17
3.20 The Alrcraft-Wlnd Control adjusts the intensity of the Aircraft Type and

Wind displays.

3.21 Use the two toggle switches to select the proper type radar input; either,

SPN42 or SPN12/4^I and TAS or CLSG for the airspeed to be displayed. The

intensity for these displays was adjusted in 3.1^ of this section.

3.22 Adjust the MOVLAS intensity with its potentiometer control.

Use Figure 3 as the reference for the following adjustments. This is a photograph of the left side console control panel. Note: The HUD illumination ' Panel

has the Glide Slope Line Up Range Change switch replaced with a 3 position switch for

the Ranger console. The positions are (1) Auto, (2) 30 feet, (3) 10 feet, see Dwg.

27E.

3.23 Turn the HUD display on with its ON-OPP switch.

3.24 Use the Scale toggle switch to adjust the HUD scale intensity. This

is a momentary switch. Holding it u£, increases and holding it down,

decreases the HUD scale intensity.

3.25 Adjust the pointer intensity on the CRT HUD display with the Pointers control

potentiometer adjacent to the ON-OFP switch.

3.26 Set the Glide-Slope for aircraft symbol display as desired with the Auto,

30 feet or 10 feet switch as follows

(a) Auto: This is in general the most desirable position for

normal operations. When the aircraft has greater than a one mile range, the aircraft symbol is a round circle and

the crossline scale marks represent 30 feet each. When"

the aircraft comes v/ithin one mile, the range circle of one nautical mile appears (see Figure 5.2), and the aircraft'

symbol adds a tail and v;ings and each scale mark represents

10 feet from the touch-dovrn-point represented by the center

of the cross hairs. As the aircraft approaches the range

circle disappears in a counterclockwise direction. "^^he portion of the circle remaining displays the range; l/'»

circle means 1/4 nautical mile range, etc. The circle

disappears at touchdown of the aircraft.

(b) 30 feet: In this position the aircraft symbol will always

be a round circle and never have wings and tail. Each cross mark will represent 30 feet off the touch-down-point throughout

the recovery. The range circle will appear at one mile and

operate as in part (a).

(c) 10 feet: In this position the aircraft symbol will always

have wings and tail and each scale mark represents 10 feet

from the touch-down point. The range circle will appear at

1 mile and operate as in part (a).

3.27 Turn on the Plat at the panel switch.

3.28 Adjust the Plat with the Contrast, Brightness, Vertical and Horizontal Hold

controls provided below the OM-OFF switch for the best visibility for the

existing operating conditions.

3.29 The tilt and angular rotation of the console is adjusted for the best

operating conditions with the TV type panning head controls.

4 . 0 Console Storage

The folloiwng procedure should be used for storing the console after landing

operations are complete.

4.1 Blank the CRT pointers with the Pointer Control, Figure 7.

18
4.2 Turn off the HUD Illumination with the ON-OFF toggle switch. Figure 7.

4.3 Turn off Main Pov/er only after doing No. 1 and No. 2. This protects the

HUD CR'T'. It is not necessary to turn off the other displays on the console.

This procedure leaves the intensity controls set at the level of the last

operation and could require only minor adjustments when landing operations

are renewed.

4.4 If the external optics and console have become very dirty or wet due to

landing operations, clean and dry them. To remove dirt, JP-5 fuel, etc., use alcohol, mild detergent in water, and fresh water rinse in that order to

clean the combiner, the spherical concave mirror and the HUD protective

glass cover. Do not rub hard . Dry with a soft, clean cotton cloth or

cotton. Clean the circular-polarized panel using the same techniques.

Wipe the balance of the Console free of dirt or moisture with a soft

cloth.

4.5 Go to item No. 10 in the Console Operation section and reverse steps

No. 10 through No. 1 of this procedure to store the LSO Console below

the platform.

Technical Details of the Equipment

The material contained in this section describes the operation of the circuits

used in the console to generate the display. This material is to be used in

conjunction with a set of circuit and block diagrams supplied with the equipment. P. list of these drawings is included in the Appendix.

This information applies only to the console as installed aboard the USS Ranger

for testing and evaluation of this prototype. Analysis of these tests is expected to

result in a final design from this preliminary model. The material is divided into

sections 5.0-12.0.

5.0 Main Power Control and A.C. Wiring - Reference Drawing 6E3> and Block Diagram

6E3B.

5.1 Pov/er Panel

The LSO Console and the Auxiliary Electronic Cabinet require 115V AC 60

Hz single phase pov/er. A maximum of 15 amperes is required. The input power

line comes into the Auxiliary Electronic Cabinet on the upper section panel,

(Figure 2). This panel also contains a 15 ampere circuit breaker, an elapsed

time meter and a 115V AC outlet. The 115V AC outlet is to power an oscilloscope or soldering iron for equipment service.

As long as the main power sv:itch on the console is off, neither the

console nor the Auxiliary Electronic Cabinet functions when 115V AC is

applied to the input panel. The only active element is a 175-watt heater

located in the LSO console. This heater keeps the unit dry during storage

periods. Two 90° - 100° thermo svfitches in series prevent overheating. The

heater is turned off during landing operations when using the console.

5.2 Main Power Turn On

In order to turn main pov/er on , the 15 ampere circuit breaker must be

closed on the Auxiliary Electronic Cabinet panel and then the main power

switch must be closed on the LSO console. The following occurs v/lth this

operation: (1) the 115V AC circuits in the Auxiliary Electronic Cabinet and

the LSO console are activated when the relay Kl closes, (2) the elapsed time

meter starts, and (3) the console heater is turned off. The elapsed tine

meter indicates the hours the equipment is used.

A nineteen conductor cable (19A-19V) shown in drawing 6E3 connected from

the upper panel of the Auxiliary Electronic Cabinet to the LSO console

(Figure 2) is the main power control cable between the two units. The

additional functions of this cable, other than 115^/ AC control between the

two units, are covered in other sections.

19
The cables connected to the front of the lower panel (Figure 2) will be

discussed later as they relate to the equipment operation.

6.n Ilead-IJp Display : Reference Dwg. IM and M

6.1 Head-Up Display Optics :

The two drawings IM and 2M illustrate the optics and ray diagrams of the

system used in the LSO console. The basic requirements were to project, as if at infinity, a display of the most important aircraft status information

during the landing of aircraft. This display is then superimposed on the sky

by using the TV panning head to set the tilt and azimuth of the console. The

LSO operator can monitor this information without lowering his head (Head-Up)

from the approach path or refocuslng his eyes to the lower console. A 10-

inch diameter, l8-inch focal length, spherical concave mirror is used to

project the display as if at infinity. The display consists of true

airspeed, ramp motion, range, and aircraft glide-slope path relative to the

touch-down-point. By placing the information source at the focal point of

the spherical concave mirror, a virtual image is produced at infinity. A

nominal 30% reflectance and 70% transmittance combiner is inserted at k5°

between the source and the 10-lnch mirror. When the viewer looks through the

reflecting side at 90° to the source-to-mirror path, a display of source

information appears as if at infinity. For simplicity and cost reduction,

the display scale information is etched on an illuminated reticle and the

dynamic analog information for each scale is presented on a high intensity

cathode ray tube (CR'^). The two sources (Scale Display and Pointer Display)

are combined on a polyethyleneterephthalate film pellicle of 50%

transmittance and 50% reflectance to make the composite HUD information

source. Each source is located so that the optical path eouals the focal

length of the 10-lnch mirror. The reticle scale illumination is obtained by

passing the light from a 250-watt ,28-volt AC lamp through a heat deflector,

a heat absorber, a dlffuser and a green filter. This produces a green scale

display of approximately 520 nanometers. The pointer display is green; the

CRT phosphor is green. The two light sources in the green region are not of

the same wavelength so that the pointers and scale lines are not confused.

The intensity of the CRT pointer is controlled by the potentiometer, Gl.

This circuitry is fully described in Section 6.4. A two-direction momentary

switch v;ith a center off position is used to control the reticle scale

illumination. This switch controls a motor driven autotrans former to vary

the output of the 28V AC transformer for the HUD scale lamp. This circuitry

is shown In Drawings 6E and 6E3.

6 . 2 Head-Up Display Generator - Introduction

The Head-Up Display Generator produces the dynamic portion of the HeadUp Display (HUD). The circuitry of the display generator is contained on two

plug-in printed circuit cards located In the HUD chassis that Is itself

inside the Auxiliary Cabinet. One card is labeled CIRCUIT BOARD /'l/gp.

Waveform Generators; and the other is labeled CIRCUIT BOARD #100/199, Display

Synthesizer. Circuits that interface these two cards to the CRT are not

considered part of the Head-Up Display Generator and are not described in

Section 6.2. The interface circuits are a deflection amplifier, described in

Section 6.3, a blanking circuit, described in Section 6.4, and a protection

circuit described in Section 6.4.

6.2.1 CRT Beam Path

Figure 6.2.1 shows the visual display that is drawn by the CRT,

and also Indicates the time during which the various parts of the

display are dravzn. This figure is helpful in relating the visual

display to the circuits and waveforms that drive the CR''' beam.. In

order to relate this draviing to the circuits that generate the

display, an Introduction to the timing and signals that drive the CR"!^ must be provided.

20
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21
6.2.1a Timing - Reference Dwr. 31E1

The CRT display circuits are controlled by an internal 790

Hz clock oscillator. Twenty-four cycles of the clock are required to completely draw the display once. In order to

Identify the timing of events within the 2^-cycle sequence, we count clock cycles. Counting starts when the CRT beam finishes

the RANGE circle portion of the display (this zero-count

corresponds to the negative transition of the rectangular wave

at pin 5 of plug 1 or of socket 1). The clock runs continuously and a new 24-cycle sequence begins as soon as the

previous sequence ends.

6.2.1b Signals

The CRT is controlled by two types of signals; deflection

signals that produce deflection in the X and Y directions, and

a blanking signal that turns off the beam during intervals when

a visible trace is not desired.

6.2.1c Blanking

The CRT beam is blanked during the time that it is

traveling from one of the four major display areas to the next.

A total of at least 150ys needs to be allowed for the beam to

travel to, and settle down accurately into its new location.

In addition, the trace is blanked for approximately Bus near

the beginning of each clock cycle. This is done so that the

beam will not be visible as it Jumps from one part of a local

drawing to another part of the same item, as when Jumping from

the end of the tail of the AIRCRAFT SYMBOL to the beginning of

the wing portion of the AIRCRAFT SYMBOL. The 8 us pulse is

timed so that it begins about 3y s before a Jump starts. This

lead time compensates for delays that occur in the blanking

Interface circuit.

6. 2. Id Detailed Description of CRT Beam Path

The DECK Motion pointer is drawn during the first two

cycles of the 24-cycle sequence. The CRT beam is blanked

during the first half of the first cycle in order to allow time

for the currents in the X and Y-axis deflection coils to change

to the values required to drive the beam from the top of the

RANGE circle, over to the DECK MOTION pointer location. The

visible part of the pointer starts halfvmy through the first

clock cycle. The pointer is composed of three closely spaced

parallel lines, each drawn from left-to-right and each taking

one-half clock cycle to draw. The top line is drawn first,

followed by the bottom line and then the middle line. The beam

then Jumps to the AIRSPEED pointer, v/hich has the same

structure

.

The AIRSPEED pointer is drawn during the third and fourth

clock cycles, with the first half of the third cycle being

blanked, as before. The visible part of this pointer consists

of three closely-spaced vertical lines drawn from bottom-totop. The right-hand line is drawn first, then the left-hand

line, and finally the middle. The beam then immediately

travels to the AIRCRAFT SYMBOL.

The AIRCRAFT SYMBOL is drawn during the fifth thru the

eighth clock cycles. If the low sensitivity glide slope

deflection factor (i.e. 30 feet per division) is in use for

positioning the AIRCRAFT SYMBOL, then this is indicated to the

viewer by representing the aircraft simply as a small circle,

drawn during the seventh and eighth clock cycles. In order to

make the brightness of the circle about the same as that of the

pointers, the circle is drawn twice, once during the seventh

clock cycle and once during the eighth clock cycle. These

22
circles are drawn counter-clockwise from the 3-o' clock

position. Wings and a tall are added whenever the more

sensitive deflection factor (I.e. 10 feet per division) Is

used. In this situation the beam Is blanked only during the

first half of the fifth clock cycle, with the aircraft's tall

being drawn from bottom-to-top during the last half of this

cycle. The wings are then drawn during the sixth cycle and

consist of two left-to-right sweeps, with the second sweep

being used only to increase brightness.

The RANGP] CIRCLE is drawn once during each of the last l6

cycles of the 2^1-cycle sequence. The repetitions are needed in

order to build up adequate brightness. The first one-third,

approximately, of the first circle is blanked in order to allow

time for the CRT beam to fully reach the RANGE circle after

leaving the AIRCRAFT SYflBOL display. Each repetition starts at

the top of the circle and travels clockwise. When the aircraft

range is less than one nautical mile, a portion of the circle

will be blanked. The fraction of the circle that remains

visible is equal to the aircraft range in fractions of a nautical mile (e.g. when 3/^ of the circle is visible, the

aircraft is 3/H mile from the carrier). In order to prevent

the circle from being "burned" into the CRT phosphor, the

entire circle is blanked out when the aircraft is more than one mile from the carrier.

6.2.2 Waveform Generators - Description of Circuit Board #1/99

Reference Dwgs . 31E1 and 31E2

The primary functions of this circuit board are to

generate the control signals that are- needed by Circuit Board

#100/199 (Display Synthesizer) to generate the CRT display, and

to generate the CRT blanking signal.

The heart of Circuit Board #1/99 is a 790 Hz sine wave

oscillator.. The oscillator is composed of a feedback loop

around Ul, IJ2, and IJ3, while Ql and Q2 stabilize the sine wave

amplitude at approximately +B volts peak. Ul and U2 are in

networks that produce unity gain at all frequencies but whose

phase shift is a function of frequency. Since inverting

amplifier IJ3 produces close to lR0° phase shift at all

frequencies of interest, and since a 3^0° phase shift around

the loop is needed for oscillation, then close to 90° phase

shift must be provided by the netvrork of Ul and also of U2.

This 90° shift provides the quadrature signals that are needed

to drav? circles on the CRT. U'l is a light emitting diode

optically coupled to a cadmium sulfide photo-conductor and Is

used to adjust the gain of U3 and thus stabilize the sine wave

amplitude

.

Voltage comparator U5 is used to convert the sine wave

into a square wave (has slight dissymmetry) that is then used

to drive the digital circuits that follovr. The output of the

voltage comparator goes to +5 volts when the negative slope of

the sine wave reaches 0.00 volts, and goes lov/ when the

positive slope of the sine vrave reaches approximately +0.2

volts. This hysteresis insures that U5 will not produce

unwanted output transitions. The output of U5 drives several

circuits. When the output of U5 goes high, the output of U21-a

goes low for about 7uS. This pulse blanks the CRT". U21-b

Introduces a 3ijs delay between the output of U5 and the input

of binary divider U22. The delay ensures that the CRT is

blanked before counter U22 advances to the next segment of the

display picture. U27-a and U27-b form a circuit whose output

goes lov; for approximately 6ys on each transition (negative as well as positive) of the U5 output. These double-frequency

pulses are used to reset a linear ramp generator on Circuit

Board #100/199.

23
A binary divlde-by-eight divider (TT22) and a divide-bythree circuit (U23) produce the basic timing that steps the CRT" display thru its sequence of 24 clock cycles. The first eight

cycles are decoded by \]2H y whose outputs are low except for the

output line selected by the 3-bit input code. The decoded

outputs are used as required to provide the gating signals that

are needed by Circuit Board ^100/199. All outputs of U2'} are held low during the last l6 cycles of the seauence by holding

pin 11 of U2H (U24/11) high.

The circuit formed by U2f^-a, IJ21-d, and U21-c, produce

blanking pulses that are one-half clock cycle long; beginning

at the start of the first, third, and fifth clock cycles of the

sequence of 24, This circuit also produces another blanking

pulse about 30n u s long at the beginning of the ninth clock

cycle. These four blanking pulses allow a generous amount of

time for the current in the CRT deflection coils to make the

large change that is needed to produce a major position change

of the beam. The output of NAND gate, U30, is the blanking

signal and drives the CRT via an interface circuit. Pins 1 and

15 of U30, which are connected to wiring that is external to

the circuit board, are protected from voltage transients by

resistor-diode networks.

Blanking of the CRT during the RANGE circle display is

controlled by the signal from U143/9 (Circuit Board #100/199).

This signal is a steady-state +5V when the aircraft range is one or more nautical miles, but becomes a rectangular wave when

the range is between zero and one mile. When the range is more

than one mile, the +5V control signal allows C25 to charge, via

R30, to +5V. This forces the output of U29-d to stay low and

thereby blank the entire RANGE circle. Rut when the range is

less than one mile, the voltage across C25 cannot rise above

1,3V because it is periodically discharged by the low voltage

portion of the control signal from Ul43. Because the output of

U29-d is now held high, the output of NAND gate U29-C will

respond to the signal from Ul43, allowing the CRT beam to be

visible only during the time intervals that this signal is

high.

NAND gate U2R-d causes the tail and wings of the AIRCRAFT

SYMBOL to be blanked vfhenever the less sensitive glide slope

deflection factor (30 feet per division) is used.

Circuit Board #1/99 is powered by the +20V and -20V

supplies that are used for the interface deflection amplifier.

Integrated circuit voltage regulators are used to reduce these

incoming voltages to those required by the circuitry. Voltage

regulator U91 produces +l4.8o +.03 volts and -14.8 volts for

use by both circuit boards. The +14.80 volts must be

accurately set because it is used as a reference voltage for

several circuits on Circuit Board #100/199. The [3-volt output

provided by regulator U92 is needed only by Circuit Board

#1/99.

2.3 Display Synthesizer - Description of Circuit Board #100/199

Reference Dwgs . 31E3 thru 31E5

This circuit board uses analog data supplied by the SPN-42

radar system and the waveforms generated by Circuit Board #1/99

to produce the analog X and Y deflection signals for the CRT.

A deflection amplifier interfaces the circuit board to the CRT

deflection coils. The basic scheme of the circuit board is to use FET switches to select the input signals as required and

feed them to a summing amplifier.

24
P-channel Junction field-effect transistors are used

extensively on Circuit Board #100/199 as switches. The devices

used have a diode connected to the analog input terminal of the

transistor. Drawing 31E3 shows how these transistors are used

in a typical circuit. The output end of each PET (UlOl) drives

a low impedance load whose voltage is always within O.IV of

ground. When the control voltage (applied to the gate of the

PET) is low, then the drain-to-source resistance of the PET is

low (approximately 200 ohms) and signal current flows easily

thru the PET. But when the gate voltage is driven high, the

resistance from source-to-drain is very high and signal current

does not reach the output terminal. The PET cannot turn off

unless its gate voltage is at least 3V or so more positive than

both the analog input and output terminals. By grounding the

free end of the auxiliary diode, the analog input voltage at

the PET is prevented from going more than about 0.7V positive,

thus keeping it well below the +5V gate signal. Scaling

resistors, which are always needed between the signal sources

and the PET analog input, safely limit the current drawn when

the diode conducts. The timing waveforms that control the

various PET switches are always shown on the circuit

schematics. Por example, UlOl-a lets signal current reach Its

output terminal only during the first and second clock cycles,

and UlOl-b lets the signals thru only during the third and

fourth clock cycles. All control signals for all PET switches

are generated by Circuit Board #1/99.

The description of the circuits used on Circuit Board

#100/199 flows more smoothly if we start with the output stage

and work toward the input stages. Summing amplifiers Ul6l and

UI62 produce the X and Y deflection signals used by the C'R'v. The diode and resistor networks that appear at the output of

each sum.ming amplifier provide a first-order correction for

non-linearity that is inherent in the CRT itself. The networks

cause large output voltages to be attenuated more than are smaller voltages. This tends to correct for the greater

deflection sensitivity that the CRT provides at large

deflection angles. The summing amplifiers are designed so that

the signal delivered to the deflection amplifier can under no circumstance exceed the +1.5V maximum input signal rating of

the amplifier. The 1200 ohm resistors, R171 and RI78, are "^not on the circuit board, but are connected directly to the inputs

of the interface deflection amplifier. This is done because

the manufacturer requires that the deflection amplifier be

connected to a low source resistance whenever power is applied.

The trimming resistors, labeled X-Axls Zero and Y-Axis Zero, are used to position the CRT beam at the intersection of the X

and Y axis of the aircraft glide slope scale, not at the

geometric center of the CRT screen. The circuits that are used to synthesize the DECK MOTION

pointer and the AIRSPEED pointer are basically the same, so only the latter will be described here. The timing signal from

pin F of plug #100 (Dwg. 31E3) causes the two-channel PET

switch (UlOl-b) to conduct during the entire third and fourth

cycles of the 2il-cycle sequence. The signals that produce horizontal deflection are connected via scaling resistors to

pin 1^ of UlOl-b. These signals are: a) an analog signal that

contains the airspeed data; b) a stable dc offset signal; c)

two square-wave signals that when combined give the pointer its

width by slightly separating its three' vertical strokes.

Vertical deflection signals are connected via scaling resistors

to pin 11 of UlOl-b. These signals are: a) a sawtooth wave

that is twice the clock frequency, and thus draws four vertical

lines during the two clock cycles allotted to the AIRSPEED

pointer. One of these four vertical strokes, the first, is

blanked by circuits on Circuit Board #1/99, and the remaining

three strokes form the visible pointer.

25
The AIRCRAFT SYMBOL GENERATOR works in the same manner as the pointer circuits; but because it produces a more

complicated pattern, more FET switches are required. The

position of the center of the AIRCRAFT SYMBOL is determined by

the azimuth and elevation (X and Y-axis, respectively) analog

voltage from the SPN-'42 radar. These signals are applied to

the summing amplifiers via U121 during the entire four clock

cycles used to synthesize the AIRCRAFT SYMBOL. When the

deflection sensitivity is to be 30 feet per division only U121-

a is activated, but when the sensitivity is to be 10 feet per

division, then both U121-a and U121-b are turned on. The

AIRCRAFT SYMBOL itself is drawn with respect to this beam

location. The AIRCRAFT SYMBOL is drawn in three separate

stages. The tail is drawn first, then the wings, and finally

the circle. When the deflection sensitivity for the AIRCRAFT

SYMBOL position is 30 feet per division, then the wings and

tail are blanked in order to indicate that this deflection

factor is in use.

The RANGE GENERATOR produces a large circle on the CRT and

also develops a control signal that blanks the circle, or portions thereof, as required. The CR'^' beam will describe a large circle as long as Ul^l lets thru the two quadature sine

waves that are applied to its inputs. When the analog range

signal applied to U143/4 is more negative than -10.3V (i.e.

when the aircraft range is more than one nautical mile), then

the output of Ul43 stays high. This causes Circuit Board #1/99

to blank the entire circle. But when the range signal is more

positive than -10.3V, the negative-going linear ramp applied to

111^3/3 will keep the output of Ul4 3 low while the ramp is more

negative than the range signal. Thus vrhen the range is less

than one mile the output of the comparator is a rectangular

wave. This waveform will cause Circuit Board #1/99 to blank

only that part of the range circle that would be drawn while

the rectangular wave is low.

Buffer amplifiers are used to interface the five analog

data lines from the SPN-42 radar. A separate amplifier is used

for each of the five Inputs. The impedance seen by the input

signals is at least 300 kilohms, and the amplifier inputs are protected to beyond +200V dc or peak ac. The output voltage

from UI83 and Ul84 is limited so that AIRCRAFT SYMBOL cannot be

driven off the CRT screen when the lower sensitivity (i.e. 30

feet per division) glide slope deflection is in use. The gain

of each amplifier is tailored to meet the needs of the circuits

it drives. All five amplifiers also function as low-pass

filters, thereby reducing noise problems.

6. 3 CRT Deflection Amplifier and Yoke Assembly

Reference Dwg. 2E, 5E and «M

"

The HUD circuit cards, consisting of the Waveform Generator and Display

Synthesizer, generate input voltages to the deflection amplifier for the HUD

CRT.

/ The^- cathode ray tube is a three inch diameter, high intensity HUD type;

either 3M51P1M (Thomas) or KC3074P1M (Dumont). This tube has magnetic

deflection with electrostatic focusing. The required voltages are shown in

Dwg. 2E, The cabling from the deflection amplifier to the CRT yoke is shown

in Dwg. 5E. The CRT mounting and yoke layout is shown in Dwg. 8m. The

component parts of the CRT, yoke and reticle are shown in Figure 11. the

complete assembly is shown in Figure 12. Figure 13 shows the HUD CRT

assembly location.

The deflection amplifier for the CRT yoke is a Celco model DA-PP2B with

+1.5 ampere capacity (replacement is DA-PP2N +2 ampere). The yoke is a Celco

BY714S512. Power requirements are +20V DC and -20V DC and 115V AC.

26
27
28
29
Caution ; Do not turn on any power unless all terminals on the Amplifier

strip are properly connected. At no time should outputs be open circuited

while the unit is in operation because the yoke coil is part of the feedback

loop. Power supplies are to be turned on and' off simultaneously.

The Celco driver is a direct coupled amplifier which operates as a voltage-to-current converter. The amplifier attempts to convert any applied

input voltage waveform to an equivalent current waveform through the yoke

load. A +1 volt input will result in a +1 ampere output in the yoke. The

amplifier contains two identical units for horiztonal and vertical deflection

of the CRT. The input voltage should be restricted to +1.5 volts, therefore,

the output is +1.5 amperes. The output (yoke) current for each amplifier can

be monitored at the terminals marked 2 and 8. The optimum source impedance

for the amplifier is 1000 ohms. A 1200 ohm resistor is connected across each

input section of the amplifier at the amplifier terminal strip. These

resistors and the output impedance of the Display Synthesizer described in

Section 6.2.3 combine to produce a 1000 ohms impedance at the input of each

amplifier section.

CRT Power and Interface Circuitry : Reference Dwg. 2E,

4E, 5E, 5E1, 7E, lOE, Figure 2, and Block Diagram 2EB

The circuits shown in Dwg. 2E fulfill the voltage requirements for the

HUD CRT. The 6.3V AC winding on a Stancor ?AQ^21 power transformer is

dedicated to the CRT filament. The other winding is rectified with a onehalf rectifier, filtered, and regulated with zener diodes to produce -75V DC

for the CRT control grid (Gl). This -75V Gl source is gated on only when an output from the CRT is required for displaying information. This gating is

done with the circuitry of Ql and Q2. The gating is controlled by the HUD

card, 1/99 Waveform Generator, described in Section 6.2.2. A zero volt input

signal to Ql turns it on -bringing its collector close to ground from a negative -75V. The transistor Q2 is an emitter follower with the Gl control

as part of the emitter resistor. The emitter resistor .is such that the Gl

control will vary from -28V to -5 3V and have a rise time of approximately ten

microseconds to bring the CRT on when set for maximum brightness. The

emitter voltage is from the -75V source. The other grid control voltage (G2) and the focus voltage (G^l) are obtained from individual dividers and potentiometers from, a 600V DC power

supply (ARM 036, BMA). The G2 voltfege is set for approximately +480 volts by

the 500 kilohm control. The focus (G4) voltage can be varied between +300

and +550 volts v;lth the 250 kilohm control.

The above voltages are generated in the Auxiliary Electronic Cabinet.

Drawing 4e (Power Supplies and CRT Gl Gating Layout) shows the location of

the components for the CRT filament, Gl and G4 controls. The 500 kilohm

control, G2, has been removed from the location shown to the back of the

chassis for ease of adjustment and service. These voltages go to the HUD CF.^

In the LSO Console as part of a nlneteen-conductor cable shown on drawing

lOE. This cable comes from the lovjer panel, of the Auxiliary Electronic

Cabinet (Figure 3) to the LSO Console. Its location at the LSO Console is

shovm in drawing 5E1. The connectors and conductors are color coded.

The CRT anode voltage is supplied by a CPS Model 5OOIP unit that Is

variable from 13kV to 15kV. Output Is about 13.8kV for this application.

The anode voltage supply Is in the Auxiliary Electronic Cabinet and is

supplied to the CRT by an RG-8/U coaxial cable. This cable is combined with

the four deflection amplifier output cables to the CR"^ deflection yoke in a single sheath shown in Dwg. 5E. The connectors are color coded to prevent

misconnectlons . The location of the 13kV supply and the deflection amplifier

is shown in Dwg. 4e and Dwg. 3E respectively. The cable is connected between

the Auxiliary Electronic Cabinet and the LSO Console as shown in Figure 9 and

Dwg. 5E1 respectively.

The Monitor of Oscillator and -70V circuit in drav/lng 7E is necessary in

order to protect the HUD CRT from phosphor damage due to a high Intensity

spot occurring if (1) scanning voltages are lost or (2) the Gl control

30
voltage is lost. A two part detector circuit is used to monitor these

voltages. The CD4001AE detects the absence of the 6^ s pulses from the HIID waveform generators for a period equal to the R-C time constant determined by

the 8.2 megohm and 3300pF capacitor or the loss of the -70V (Gl) supply.

Failure of either of these produces a positive input to the CDitOOlAE. Its

output at #10 goes to ground, turning off Ql transistor, opening the 800 ohm

coil relay (HCr^llD), which in turn causes the KRP llA to open and interrupt

the 115V AC to the 13 kV CRT anode supply. This protects the HUD CRT until

repairs are made. The source of the 6ys pulses is the HUD Waveform

Generator, i«l/99, card for the scanning voltages. The -70V is the CRT

maximum negative value of the Gl control voltage. These circuits are on a separate card which is mounted in the card cage containing the two HUD

circuit cards, #1/99 and #100/199.

.0 Console Display Scales - Introduction ; Dwgs. 13E, l^E, 15E, 16E,

17E, 18E, 19E, 20E, 21E and Block Diagram 13EB-21EB

The LSO Console contains four scales of the illuminated pointer type for

display of Airspeed, Range, Rate of Descent, and Ramp Motion. The inputs for the

first three of these scales use analog signals from the ship's SPN-^2 radar ACLS

system or the SPN-12/44 radar. The ramp motion signal is from the ship's

harmonization computers.

Drawings 13EB-21ER show a general block diagram of each scale. The analog

signal from the input source goes to an analog to digital converter with binary

output. The binary output is decoded from 1 to n where n is the full scale number

of a particular scale. The decoder enables the appropriate lamp driver to turn on the lamp corresponding to the binary number. Each number is indicated by a pair

of lamps for increased brightness and redundancy. A clock pulse initiates the

conversion cycle of the analog to digital converter (A/D) during which time the

A/D sends out a "busy" signal on the strobe line to inhibit the decoder during a conversion cycle. At the end of a conversion cycle, the strobe line goes to a "logic low" which enables the decoder. The conversion time (about 200 s) is short

in relation to the clock period.

In the case of the Airspeed and Rate of Descent scale, a "trend" lamp was required that would indicate whether the function was increasing or decreasing.

This lamp is adjacent to the main pointer lamp and of lesser intensity. It

appears behind the main pointer lamp for an increasing function and ahead for a decreasing function. For these two scales the binary data output from the A/D is

continuously compared with the A/D output data periodically stored. The

comparator provides two outputs which indicate when data is less than or greater

than stored data. This provides a sense of direction for changing data. The

direction signal is stored in a flip-flop and the gated output provides a signal

for the addition or subtraction of one to the data by means of a full adder. The

duty factor of this addition or subtraction determines the relative brightness of

the trend indicator.

The illumination intensity of the four scales is adjusted by a momentary,

center-off, switch that controls a motor driven autotransform.er to vary the output

of a l^V transformer, Dwg. 6e and 6E3. Each scale has a separate on-off switch

and potentiometer control for pointer intensity which are located on the right

side of the console, Dwg. 6e,

Drawing l^E, Scale Display Input-Output Wiring, is a composite of the wiring

of the scales for indicating the input to the output layout. All analog to

digital conversion for the scales is performed by printed circuit cards located in

the Auxiliary Electronic Cabinet. The analog input signals are via the 100

conductor cable and the binary outputs go to the LSO Console through the 128

conductor cable to their respective display circuits. These Auxiliary Electronic

Cabinet circuits consist of the Airspeed Preamp and Ramp Motion Invert. Amp. Card,

Airspeed (J300), Ramp Motion (J200), Range (JlOO), and Rate of Descent (Sink Rate,

J400), cards.

7.1 Airspeed Scale - Reference Dwg. 13E, 15E, 16e and

Block Diagram 13EB-21EB

The Airspeed Scale indicates aircraft airspeed by a moving pointer light

over a range of from 80 to iBO knots (0 to 100 points). The scale

31
incorporates a trend light of lesser intensity adjacent to the main pointer

to Indicate either increasing or decreasing airspeed. Both the scale and the

pointer have individual intensity controls as well as separate power sources.

These are located on the right of the console with the scale on-off switch.

The input for the Airspeed Display is an analog voltage from the SPM-42

(or HH) ship's radar true airspeed (TAS) or closing airspeed (CLSO) sources.

The SPN-42 radar Automatic Carrier Landing System (ACLS) and the radar

both have TAS and CLSG airspeed outputs. The desired airspeed for display on the Airspeed Scale is selected by the TAS or CLSG and SPN-i|2 or SPN-il'4

switches on the right of the Console. These are fully described in Sections

8.2.1 and 8.2.2. The SPN-^('I is a synchro output at the LSO platform. A

synchro-to-dc converter is used to convert its output to analog voltage of

the same range as the SPN-42. This conversion is covered in Section 7.1.1.

The Airspeed cards, (J500 and J300), are located in the Auxiliary

Electronic Cabinet. The input ranges from 3.13V DC for 80 knots to 7.04V DC

for 180 knots. Dwg. 13E shows the Airspeed Preamp, U502, with an offset

voltage, R515 control, to compensate for this range of inputs. This circuit

is necessary since the following analog to digital converter (ADC 898B)

operates from 0 to lOV DC. The offset control, R515, and the gain control,

R51^, are used for calibration of the Airspeed Scale so that it starts at 80

knots for 3.13V DC and covers 100 knots (to I80 knots) when the voltage

swings through the range of 3.13V DC to 7.0AV DC. The output of the Airspeed

Preamp (U502) is applied to the analog to digital converter, card J300, Dwg.

15E (ADC-898B). The control, R300, on the card J300 is preset. The NE555

(U300) timer pulse of approx. 2-3 ms duration and 7 ms period triggers the

monostable rw (U301) producing a 1h s pulse to start the analog to digital

conversion. The conversion time is approximately 200vis. The timing chart.

Figure 7.1, is representative of the series of circuit events.

In Figure 7.1 the timing trace, (1), represents the output of the timer

U300 (NE555) at #11 of U302. This output triggers the one shot, U301

(SN7^121), to produce a l\i s positive pulse at #6 of U301 to start the A/D

conversion, trace (2). Number (3) trace shows the A/D conversion time of

approximately 200 ps during which time the pointer and trend lamps are inhibited at the airspeed display scale. Trace (^4) shows the levels at #10

and #12 of U307. During the low portion of this, #8 and #11 of U307 are at

logic 1. This adds 1 and subtracts 1 to U309 and U310 adders respectively.

The resultant is the display time of the pointer ("pointer on"). The high

time of trace (4) is the enable condition of U308 into U309 and U310 via

U307. This is the trend light "on time". Trace (5) is the level condition

of #6 of U302. The high level is the data transfer time from the A/D to the

latches (U303, U304). The low level time is the length of the latch U303,

U304. In the trace (6) the down level time of 2-3ms inhibits the outputs of

U305, U3O6 via U302, #8. The high level allows U308 to be set or reset

depending on the status of #12 or #13 of U306. If data A is greater than

latch B (U306, #13), then U308 Is set via #3 of U307. If data A is less than

B (U306 #13), then U308 is set to the opposite state. Therefore, these

circuits continuously compare (U305, U306) binary data output from the A/D

(898B) with the A/D output data periodically stored in the latches (TI305,

U3O6). The comparator provides 2 outputs at U306, numbers 12 and 13, which

indicate when data (A) is less than (A <B) or greater than (A > B) stored data

(B). This provides a sense of direction for changing data. The direction

signal is stored in the flip-flop U308 (nos. 10, 11) and the gated output

U307 (nos. 8 & 11) provides a signal for the addition or subtraction of 1 to

the data by means of the full adder U309 and U310. The duty factor of this

addition or subtraction determines the relative brightness of the trend

light. This can be changed to meet field requirements by adjusting R305 and

R304 of U300 (NE555).

The seven binary data lines and the strobe, Dwg. 15E, go to the LSn

Console via the 128 conductor cable for the Airspeed Scale of 100 Decoder and

Driver Circuitry, Dwg. I6E. A SN74155 2-line-to-4-llne Decoder/Demultiplexer

operating from the three most significant bits (16,32,64) of the seven binary

lines is used in the 3-line to 8-line decoder mode. The SN74155 sequentially

strobes six SN74154 units to decode the least significant bits (1,2,4 and 8)

into 16 line output for a total of 96 (6 x I6) discrete counts, (O-Q5).

32
Time

I 7ms • ,2-3ms

I

#11 of

U302

0 V I

I

I Start

I Conversion

Start

U301 #6

200y s conversion time

Inhibits lamps

at console

EOC

End of

Conversion

I

#10 & #12

of U307

#6 of

U302

.PojnterMakes 8 & 11 'o^

U307 logic 1 which

adds 1 and subtracts

1 to U309 & U310

adders, hence value

of pointer

/

I Data

I Transfer

I

I

\

Enables condition

of U308 into U309

& U310 via U307.

This is trend light

on time.

Data is latched

in U303, U30A

Inhibits

Outputs of

U305, U306

via U302 #8

Allows U308

to be set or reset

depending on status

of #12 or #13 of U306

Figure 7.1 Display Scale Timing
Another SN74155 with the 1 and 2 bit input is strobed by the number 7 line

output of the 8 line decoder to produce counts 9fi-9B. The circuits

consisting of the SNT^OO, SN7^32 and the SN7^155, used for the 96-98 count

along with the strobe #8, produce count 99 and prevent over ranging. The

outputs of the SN74l5i4 units drive UHP400 lamp drivers. Each UHP^OO contains

H individual drivers; therefore, a total of 25 UHPMOO units are required for

the airspeed scale. Each driver in the UHP400 is of the open collector type

and its load is two, type number 715, 5V, 115 mA lamps in parallel for both

brightness and redundancy. Voltages below and above the 3.13V DC to 7.04V DC

are indicated as 80 knots and I80 knots respectively.

7.1.1 SPN-^^ Radar Airspeed - Reference Dwg. 24E1, 24E3,

2'4E6 and Block Diagram 24EB

The SPM-4^1 radar is not part of the ACLS system. The SPN-44

radar has both true (TAS) and closing (CLSG) airspeeds available at

the LSO platform to drive synchro repeaters. The SPN-^4 airspeeds are

also displayed on the Airspeed Scale display. The synchro signals

must be converted to a DC output in order to drive the Airspeed cards

of Section 7.1. This is described in the following paragraphs.

A single printed circuit card contains the circuitry for the

conversion from synchro-to-dc output. Synchro-to-dc converters

(Astrosystems Mod. No. MIOOOS-906) are fed from the SI, S2, S3, and

reference high and low lines that are available from each synchro.

Each converter output is a linear DC signal of 0 to 10 volts for 0° to

360° of synchro rotation which represents 0 to 200 knots of airspeed.

The converter output goes to a non- inverting operational amplifier

with level-set and gain calibrate controls. The operational amplifier

output check points are 80 knots = 3.13V, (l44°) 130 knots = 5.09V

(23^°) and 180 knots = 7.0ilV (324°). The output of the operational

amplifier feeds the Airspeed Scale and the HUD by way of the radar

type and airspeed selector switches. Identical circuits for TAS and

CLSG Airspeed are used as shown in Dwg. 24E3. As in the use of SPM-42

only true airspeed (TAS) is shown on the HUD display from the SPN-^^^.

The console scale will display either TAS or CLSG data from the SPN-il4 as it does for the SPN-42. Therefore, proper operation of the

selector switches will give TAS on the HUD and CLSG on the console

scale from the SPN-^i^.

7.2 Rate of Descent Scale - Reference Dwgs . 21E, 18e and Block Diagram 13EB-21EB

The SPN-il2 radar ACLS system has an analog output of 0 to lOV DC for 0

to 1912 feet per minute representing the rate of descent (sink rate) of the

aircraft as it approaches along the glide slope path to its final touch-dov/npoint. The Rate of Descent card in the Auxiliary Electronics Cabinet and the

Scale of 40 Decoder and Lamp Drive in the console convert the analog signal

to the Rate of Descent console display. The SPN-42 output is converted from

a linear analog voltage to a digital output by the circuit shovm in Dwg. 21E.

This circuit operates the same as the airspeed circuit, Dwg. 15E, Including a trend lamp pointer to indicate an increasing or decreasing rate of descent.

The input varies from 0 to +10V DC which is the range required for the

analog to digital converter (ADC-898B), therefore no preamp is required as in

Dwg. 13E. Potentiometer R400 is a divider on the input permitting

calibration adjustment for the final output of U409 and U4lO of 7P counts

(six binary data lines). Refer to Section 7.1 and Figure 7.1 for the timing

and the detailed discussion of the Internal circuit functions.

The Rate of Descent console display required 40 discrete levels.

Therefore, the circuit, Dwg. #21, was designed for 2° bit output, but it

incorporates circuitry for only a range of 0 to 39 counts (40 discrete

levels). The six binary data lines and the end of conversion (EOC) strobe

feed the Scale of 40 Decoder and Lamp Driver in the console, Dwg. IBe,

through the 128 conductor cable. The input strobe activates or inhibits the

2Y0-2Y3 section of a 2N74155 unit. The 2 most significant bits of the 6

binary lines (I6 and 32 bits)- are used to operate the SM74155 in the 2-to-4

line decoder mode. The decoded output strobes two SN74154 4-line-to-l6 line

Decoders/Demultiplexers where the first four bits (1,2,4,8) are the input

34
bits from the binary source. These tv;o units produce outputs for counts from

0 to 31. Another SN7^155 and a SNT^OO (Quad 2-input Positive NAMD gate)

produce the counts of 32 through 39. The two SUlHl^h and the SM7'^155

decoders feed UHP400 Quad 2-lnput AND power drivers. The UHPilOO units turn

on console lamps to represent the number of feet per minute an approaching

aircraft is descending or ascending. The trend lamp is adjacent to the main

pointer but one number less for an increasing rate of descent. The trend

lamp is one number greater than the pointer for a decreasing rate of descent.

7.3 Range Scale - Reference Dwgs : 19E, 20E and Block Diagram 13EB-21EB

The console Range Scale operates when the aircraft is 3 nautical miles

or less from the touch-down-point. It has a resolution of 0.1 nautical mile

per scale division for the three mile scale. The SPM-il2 range buffer has an output of 0 to 30V DC for three miles. The Range card is located in the

Auxiliary Electronic Cabinet. Referring to Dwg. 19E, this input is applied

through the R109 gain control to UIO^I. The U104 circuit is a load isolation

amplifier. The signal is not inverted in UIO^^ and its output goes to the

analog to digital converter, A/D, (ADC-898B) via RlOO which is set to full

input to give a voltage swing of 0 to 10 volts when R109 has been correctly

set. Analog to digital conversion of the input signal is started by a short

pulse from the timer UlOO (NE555) applied via the SN7^00 unit to the A/D at

terminal number 3. The resultant A/D output is five binary output data

lines. The SN74L85 4-bit magnitude comparator and the SN7400 gates are used

to detect when the aircraft is less than 0.5 nautical miles from the carrier

touch-down-point. Originally, this was to be used in conjunction with the

deck becoming closed at 0.5 mile, or less, range to initiate a warning to the

LSO. Initial field tests indicated this feature was not necessary and it is

not operating on the Ranger installation.

The five binary output lines and the end of conversion (EOC) strobe go

to the LSO console through the 128 conductor cable. The Range Scale of 30

Decoder and Lamp driver circuitry in the LSO console is shown in Dwg. 20E.

As in the other scales, the end of conversion strobe inhibits the scale

pointer lamps during conversion time to prevent an erratic display as the

binary bits shift. Two SN7415 4-line-to-l6 line Decoders/Demultiplexers are used to decode the five binary data lines and drive the UHP400 lamp drivers.

Output 30 and 31 both drive the same pointer lamp. The input control, Dwg.

19E, RIO9, is adjusted for pointer action of 0 to 30 on the display scale for

0 to 3 nautical miles of range. When the range is greater than three miles,

the pointer remains at the maximum value on the scale.

7.4 Ramp Motion Scale : Reference Dv;g. 13E, 17E and Block Diagram

13EB-21EB

The source for the Ramp Motion signal is from the ship Harmonization

Computer (SFHC) and not from the SPN-42 radar, the source for the other

scales.

A momentary toggle sv;itch is located on the right control panel of the

console. In the normal position of this switch, this scale displays the sum

of the ramp displacement due to the sea and any fixed displacement due to the

ship's trim. In the momentary position of this switch, ship trim is

separately displayed on the scale. Ship's trim is defined as the deck

position relative to the true horizontal independent of sea action. If the

ship has bow-down trim, a resulting ramp above the horizontal exists and

there is a lesser dynamic travel of the ramp before it reaches +20 feet on the scale and a greater travel to reach - 20 feet. Care must be taken in the

adjustment of the offset (R206) and gain (R200) controls in order to give a true ramp plus trim or trim only display on the scale. The Ramp Motion

signal covers the range of +10V DC for +20 ft of ramp motion (including

trim). This signal is the input to the Ramp card in the Auxiliary Electronic

Cabinet, This signal is inverted with a unity gain operational amplifier,

Dwg. 13E, before the analog to digital converter. The inverted ramp motion

signal feeds the analog to digital converter, Dwg. 17E. The +10V DC change,

(Dwg. 13E), is digitized by the analog to digital converter, A/D, (ADC-898B),

to produce 6 binary bits. The gain control (R200) and offset control (P206) are used for calibration and operation of the A/D with a +10V DC input. The

process is started with the U200 (NE555) timer. The six binary data lines

35
and strobe signal go to the Scale of ^10 Decoder Lamp Driver located in the

LSO console for the Ramp Motion Scale, Dwg. 18E.

The operation of the Ramp Motion display circuitry is the same as for

the Rate of Descent Scale of 40 discussed in Section 5.3.3 except for the

following details. The Ramp Motion card incorporates an offset so that the

zero count of the decoded binary output represents the high ramp, +10V DC

signal, and is displayed as +20 feet on the top of the Ramp Scale. When

there is no ramp motion (zero volts), the count is number 20 and the scale

display is zero feet. A low ramp of -9.5V DC is -19 feet on the scale and

count number 39. Therefore, the scale is capable of a range of +20 feet to - 19 feet of ramp motion.

The most dangerous ramp position during landing operations is a high

ramp from +10 feet to +20 feet. This range is indicated by a red filter on

the scale. A high ramp is much more dangerous than a low ramp since the

latter means a hard landing and less danger to the pilot and aircraft, while

the former may mean a ramp strike.

8 . 0 Console Indicators

This section covers a group of console lamps other than the display scales.

The lamps indicate other information for aircraft landing operations. These

indicators are all located on the front of the console except the MOVLAS which is on the left side. Information is presented by lamps being on, off, flashing, or

by alpha-numeric disnlays.

8.1 Deck Status - Reference, Dg. 6E1 and Block Diagram 6E1B

This section covers three indications that are extremely important

during landing operations involving the condition of the deck and the waveoff signal transmitted to the aircraft by the LSO. Each indicator is covered

separately.

8.1.1 Deck Open - Reference, Dwg. 6E1

The "Deck Open" indicator means the deck has no obstructions on

it to prevent landing and all recovery systems are ready to recover

the aircraft in the glide-slope approach path. This condition is

indicated to the LSO by the "Deck Open" signal at the console.

The "Deck Open" signal is a 115V AC signal from the ship when all

conditions are correct. This signal goes to the V/ave-Off and Deck

Status Card in the Auxiliary Electronics Cabinet, Dwg. 6e1. The 115V

AC signal closes the relay, K6 , which activates the two 12V AC lamps

of the Deck Open indicator located in the upper left corner of the

console. A green filter is used in front of these lam.ps. Two lamps

are used for redundancy. The Deck Open signal will remain on as long

as 115V AC is applied to relay K6. A rheostat located on the right of

the console. Figure 2, labeled "Lamps" in the Deck Status section of

the front panel controls varies the intensity of the Deck Open

indicator. This control also sets the intensity level for the Deck

Closed signal covered in section 8.1.2. This intensity control will

control the brightness of these indicators for both day and night

operations.

8.1.2 Deck Closed - Reference, Dwg. 6E1

The aircraft recovery deck is closed when recovery equipment is

not ready to recover the aircraft in the glide slope approach path or when obstructions are present. This is indicated to the LSO with a "Deck Closed" lamp display in the left end of the Airspeed Scale

module. The Deck Closed (red) and Deck Open (green) indicators are adjacent to each other.

The "Deck Closed" signal is a 115V AC signal from the ship when

all conditions are not correct. This signal goes to the Wave-Off and

Deck Status card in the Auxiliary Electronics Cabinet, Dwg. 6E1. The

115V AC signal closes the relay, K5 , which activates the two 12V AC

36
lamps of the red Deck Closed indicator in the LSO console. The deckclosed lamp will remain on until the 115V AC signal is removed

indicating the deck is not closed. The intensity of this indicator is

controlled by the same rheostat as used for the Deck Open lamps.

8.1.3 LSO Wave-Off (FLOLS Wave-Off) - Reference Dwg. 6E1

The LSO uses a hand held "pickle switch" to initiate a Presnel

Optical Landing System (PLOLS) wave-off to signal the pilot on the

glide-slope landing approach not to land. The FLOLS wave-off flashes

red lights on the fresnel lens system which are visible to the pilot.

The LSO needs to know that the FLOLS wave-off has been triggered,

therefore, a LSO wave-off indicator is located Just below the Deck

Open and Deck Closed lamps in the Airspeed Scale module.

The LSO wave-off signal to the Auxiliary Electronics Cabinet is a 28V DC signal from the FLOLS wave-off. The 28V DC signal activates

the 24V relay, K3, Dwg. 6E1. This relay removes the ground connection

of the LSO Wave-Off Flash Timer located in the Airspeed module in the

console. The flasher consists of the Ul (NE555) timer of

approximately 3^0 counts per minute and the U2 (SN7''7^) flip-flop as a divide-by-four circuit for 90 flashes per minute. The output of the

flip-flop (U2) triggers three of the four sections of the UHP^OO lamp

drivers. Each section has a 12V lamp as its load and these

simultaneously flash at 90 flashes per minute to indicate the

initiation of the FLOLS wave-off signal.

ACLS Radar Status - Reference, Dwg. 6e1, 6E2, and Block Diagrams

6E1B and 6E2B.

The principal source of display signals for the LSO console is from the

Automatic Carrier Landing System (ACLS), SPN-42 radar. Certain operational

Indicators pertaining to the automatic landing of aircraft regarding the ACLS

performance are indicated at the console for the LSO's use. 8.2.1 Radar Selection Switch - Reference, Dwg. 6E2

The selection of either the SPN-42 or SPN-4^1 radar is indicated

on the LSO Console in the right end of the Airspeed Scale module by

two 12V lamps.

The SPN-42 and SPN-^4 ship's radar both supply airspeed

information for the LSO Console display. A Radar Selection Switch is

located on the right side of the console to select either the SPM-^2

or the SPN-i|4 radar by the action of the relay, Kl, in the Auxiliary

Electronic Cabinet. The airspeed input to the airspeed card is from

the SPN-42 source when the switch is in the SPN-42 position. The 12V

lamp in the upper right hand corner of the console indicates SPN-'42

selection. In the SPN-44 position the switch closes the relay, Kl,

and the SPN-44 airspeed source is used and indicated by the SPN-4i|

(12V) lamp above the SPN-42 lamp.

8.2.2 Airspeed Selection Switch : Reference Dwg. 6E2

The Airspeed Selection Switch is located on the right side of the

console. It is a two position switch for selecting either true (TAS) or closing (CLSG) airspeed. Both of the radars have two airspeeds

available as outputs. In the TAS position of this switch the relay,

K2, in the Auxiliary Electronic is open and the true airspeed from the

selected radar is displayed on the Airspeed Scale. The TAS lamp at

the right end of the Airspeed Scale comes on. In the CLSG position,

relay, K2, is closed and the closing airspeed goes to the Airspeed

Scale. The CLSG lamp comes on above the TAS lamp and the TAS lamp

goes off. Note that the wiring of relays, Kl and K2, is such that their

operation only changes the Airspeed Scale display to either TAS or

CLSG. True airspeed only, is shown on the HUD display.

37
8.2.3 Lock-On and Mode

The Automatic Carrier Landing System (ACLS) has a number of

discrete signals Indicated at Its console relating to Its operation.

Certain ones are displayed at the console for the use of the LSO

during landings. They operate as described In the following

discussion.

Lock-On ; Reference, Dwg. 6E2

The Lock-On Indicator conveys to the LSO operator that the ACLS

equipment Is coupled to the aircraft of Interest and the results of

the coupled data regarding the approach Is being used to attempt a fully automatic aircraft recovery.

The ACLS lock-on signal of 28V DC activates the relay, K3, (Dwg.

6E2) In the Auxiliary Electronic Cabinet. The relay, K3, turns on the

12V lamps of the console Lock-On Indicator.

Mode I - Reference, Dwg. 6E2

The Mode I operation using ACLS Is a completely "hands-off"

landing with the pilot acting as a monitor. The ACLS equipment is

"locked-on" and complete Instructions are transmitted to the aircraft

controls to automatically fly the plane from Lock-On to the touchdown-point and recovery.

A 28V DC signal from the SPN-42 closes relay, K^, (Dwg. 6E2) in

the Auxiliary Electronic Cabinet. When relay K4 Is closed, the 12V

lamp indicates Mode I operation on the console.

Mode II - Reference, Dwg. 6E2

The partial control of the aircraft by the ACLS system is defined

as Mode II. This is basically an instrument landing system operation.

The 28V DC Mode II signal from the SPN-^12 activates the relay,

K5, (Dwg. 6E2) which turns on the Mode II indicator at the LSO

console.

Mode III - Reference, Dwg. 6E2

The Mode III operation indicates a "talk-down" landing of the

aircraft. Even though a Lock-On is obtained with the aircraft, data

obtained for control or response to control is unreliable. Therefore,

the pilot is flying the plane to make a non-ACLS landing.

The SPN-'42 sends out a 28V DC Mode III signal to close the relay,

K6, (Dwg. 6E2). Relay K6 turns on the 12V lamp of the Mode III

console indicator.

8, 2 A ACLS Wave-Off : Reference, Dwg. 6e1

The ACLS equipment initiates a wave-off signal to the aircraft

making a landing approach when it determines from its Internal checks

and aircraft control that its data Is not reliable. An ACLS wave-off

is not necessarily a final wave-off.

The ACLS wave-off 28V DC signal from the SPN-^2 closes relay, K2,

Dwg. 6E1. Relay K2 removes the ground of the ACLS wave-off flash

timer. This circuitry is located in the ACLS display status module at

the console. The UlOO (NE555) timer operates at approximately 360

flashes per minute. A flip-flop, (UlOl), is used to divide by tv/o for

l80 flashes per minute. The flip-flop output triggers the three

sections of the UHP400 lamp driver to operate the three ACLS wave-off

lamps simultaneously. A blue filter is used for the ACLS wave-off

display.

o ,d

38
8.2.5 Warning: Reference, Dwg. 6E2

The radar system automatically generates an ACLS wave-off

when the system Information does not satisfy certain Internal checks.

Therefore the v/arnlng display, v/hlch was to be activated by any one of

these fall-to-check conditions, was considered superficial and Is not

used In this Installation aboard the Ranger.

8.3 MOVI.AS Indicator ; Reference Dwg. 25E

A MOVLAS repeater Is Incorporated on the left side of the LSO Console.

The Manual Operated Visual Landing Aid System (MOVLAS) Is used when the

Fresnel lens landing system Is Inoperative. The repeater Is driven from the

ship's MOVT^AS source and repeats what the pilot sees for the LSO station.

The datum bar Is supplied by 6V AC for the green Indicators. The "meatball"

Indicators are vertical amber lamps except for the three lov;er lamps, which

are red. Indicating danger. The ship's +5V DC is comjnon to one side of these

lamps and the proper amber or red lamps are turned on by the MO^TLAS

controller grounding the other lamp terminal. A dual control potentiometer

is used to adjust the datum bar and "meatball" intensity. The system has a separate on-off switch to turn it off when not in use. These controls are on the right side of the console.

8.4 Aircraft Type Designator - Reference, Dwg. 22E, 23E, and Block Diagram 22EB

Ten different types of aircraft may be recovered aboard the IJSS Ranger.

Each Aircraft is designated by one alpha and one numeric character in Prlm.ary

Flight. No second numeric character is required. This same display is shown

on the LSO Console.

The aircraft type is designated by a +2hY DC signal on a single

conductor with a common return for all signals. Each aircraft type signal

comes to the Aircraft Designator Card, (Dwg. 22E), in the Auxiliary

Electronic Cabinet and is converted to a 4-blt code. As an example: a 2'4 volt signal, from the "A 3" aircraft type, at f(l of Ul causes the gate to

conduct. Terminal #2 goes to ground to produce a logic "0". Diodes are coupled from the #2 output of Ul to the proper input of two 4-line

decoder/drivers (SCS Model 1005) for seven bit output. The required input to

the alpha (A) driver is logic 1010 and 0011 is the logic for the numeric (3)

driver. The resultant seven bit output is 0001000 for "A" and 0000110 for

"3" respectively. The two seven bit outputs turn on the proper segments of

two seven segment incandescent lamp displays to Indicate the A3 aircraft. A

complete truth table for input and output is contained on Dwg. 22E. Two

spare lines and gates have been provided for possible additional aircraft. A

new aircraft can be indicated by adding diodes to the proper output lines on the card using the truth table. The 4-line to 7-line decoder/driver and

alpha-numeric character display circuits are in the ACLS module of the

console

.

The presence of an aircraft, a +24V DC signal on one of the ten lines,

is detected using the "OR" circuit of Ul and U2 and relay, Kl, shown in Dwg.

23E. \^^^en any section of Ul or U2 conducts, relay, Kl, closes to switch +4V

DC power to the alpha-numeric aircraft type console indicators. Therefore,

if no aircraft is being recovered. Primary Plight does not activate a single

line to the Ul, U2 "OR" gate, Kl remains open, and no segment of the aircraft

display characters can be on regardless of the decoder/drivers output. This

prevents partial or erronous displays.

The source of power to the relay Kl, for the aircraft alpha-numeric

characters, is from the Q3 and Q4 circuits with a maximum of 4 volts and a minimum of 1.26 volts available. The display intensity control is a 500 ohm,

2V! rheostat located on the right side panel of the console and labeled

Alrcraft-V/ind Intensity.

8.5 Wind Speed Card : Reference, Dwg. 24e4 and Block Diagram 24EB

Wind speed across the carrier deck is important and critical for the

recovery of aircraft. Wind speed and direction are transmitted to the LSO

station in synchro form. These synchro voltages are used as the input for

the wind speed indicator and are fed into the synchro-to-dc converter (Mod.

39
no. MlOOOS-906) located in the Auxiliary Electronic Cabinet. The converter

card pro'^uces 0 to +10 volts DC output for the total range. A noninverting

operational amplifier (Ul) with level set (Rl) and calibrate (R4) controls

supplies the analog to digital converter (A/D) and display circuitry located

in the LSO console. The A/D (ADC-898D) converter is used in the analog input

to 2 digit BCD output mode. The conversion is started by the Ul (NE555) free

running timer of approximately 7 ms period having a 12u s pulse width. The U4

(1/4 of 7400) inverts this for the start pulse. The resultant A/D output is

2 digit BCD.

The 2 BCD outputs drive two Model 1005 decoder/drivers (U2 and U3), to

convert each 4 line BDC to 7 line output respectively. The output of the two

decoder/drivers, U2 and U3, turn on the respective tens and units wind speed

numeric displays. Each numeric character is seven incandescent lamps

arranged in a seven segment numeric character format. A maximum of 99 knots

can be indicated for the wind speed. The operating wind speed for aircraft

recovery is, usually, 30 knots.

The A/D converter, timer, decoders, and the two numeric indicators are located in the console ACLS box. A lamp intensity control, 500 ohms, 2W, is

used to control the light output to accommodate day and night operations.

This control is the same one used for the aircraft type designator and wind

angles display, Dwg. 23E. Its setting controls the output voltage supplied

for both the wind speed and angle from transistors Ql and Q2. The whole

display of ACLS, Wind Angle and Speed and Aircraft Type can be turned off by

the on-off switch (Dwg. 6e) adjacent to the ACLS intensity control on the

right side of the console.

6 Wind Direction : Reference Dwg. 24E5, 23E and Block Diagram 24EB

Wind angle magnitude, and either port (P) or starboard (S) direction,

are critical factors to be displayed at the console. The original SI, S2, S3

and reference synchro lines for wind angle feed a synchro-to-dc converter

(Mod. No. MlOOOS-906) for wind angle conversion to a DC output voltage. This

circuit is in the Auxiliary Electronic Cabinet. The MlOOOS-906 is used in

the +180° mode in order to reference the wind angle to the centerline of the

angled landing deck of the carrier. A reference adjustment control, (R12),

' sets the converter output for zero as referenced to the angled deck. The

angled deck of the Ranger is 10° to port of the center line of the carrier or

at 350°. Therefore, the converter is set at zero output for 350° synchro

rotation. An absolute value circuit (U2, U3) converts the +5V DC signal for

+ 180° to 0 to +5V DC in order to indicate the magnitude of the angle. An

analog to digital converter, (ADC-898D), timer (U5, NE555), decoder/drivers

(U6, U7: Mod. 1005) and two numeric display characters are located in the

ACLS console box. These circuits function the same as those for wind speed,

as described in section 8.5, to display tens and units of vrind angle

magnitude. The wind angle displays up to 50° maximum, either port or starboard, for a zero to five volt change in the absolute circuit. Related

to the angled deck as the required reference, this is + 50° of magnitude.

Landing operations are usually conducted within + 10° of the centerline of

the angled deck.

The direction of the wind, either port or starboard, is part of the wind

angle display. The output of the synchro-to-dc converter of Dwg. 24E5 feeds

a "zero level" detector (U3) shown on tne Dwg. 23E. The zero level detector

produces a plus output for a plus input and a ground (zero) output for a negative input. Therefore, it is used to. sense port or starboard output from

the + 180° converter. This circuitry and the following gating of U4 is used

to drive relays which turn on the respective P or S Indicators. A positive

input to U3 is a starboard signal and a negative input to U3 produces the

• port signal. The P/S alpha character is also a seven segment incandescent

type. Coding for P/S is done by the relays K2 and K3 since only two

characters have to be displayed and they have several segments in common in

their format.

The on-off and intensity controls of this display are covered in Section

8.5.

40
9. 0 PLAT and Intercominunlcatlon Units

Plat Monitor : Reference Dwg. IE and Block Diagram lEB

A Conrac ENA 9/N TV monitor was used In the LSO console for the Pilot Landing

Aid Television monitor (PLAT). This displays the Information from the TV camera

mounted In the deck that monitors the glide-slope approach of the landing

aircraft. The picture tube and circuit chassis were separated In order to

physically locate them In the available space of the console. Remote controls

were brought out to a PLAT control panel on the left side of the console. The

circuit changes for this are shown In Dwg. IE. A parallel power on-off switch was added with a two ivafer 6 pole-two position rotary switch to select either Internal

or remote operation. For remote operation, an external brightness, contrast,

vertical and horizontal hold controls were added. The two hold controls are screwdriver adjustments on the original chassis. They are Included on the left

side console panel in addition to the normal chassis controls of brightness and

contrast for the operator's use. The arrangement for remote operation permits the

monitor to be removed and switched back to normal Internal controls for testing

and servicing.

The composite television input for the PLAT comes into the LSO console by a RG-90/U coaxial cable on the bottom of the LSO console as shown in Dwg. 5E1.

Intercommunication Units

The LSO operator has two forms of communications available at the console.

An outlet for a radio phone handset is mounted to the right and below the TV

panning head which supports the console. The radio handset is used to communicate

V7lth the pilot in the aircraft glide-slope approach. The radio handset along with

the "pickle switch" hook to the front bar at the base of the console.

An Intercom, 21MC Unit (LS-453/SIC) , is mounted in the right side of the LSO

console. This is a standard two station unit with all connections brought out to

a plug on the bottom of the console so this unit can be connected to the ship's

Intercom system. This unit is wired so that the LSO can communicate with the

Primary Plight (Prl Fly) Center and the Carrier Traffic Control Center (CATCC).

The details for the wiring of this unit are covered in the MAVSHIPS 365-2822,

Technical Manual for Intercommunication Station LS-^5B/SIC, December 12, 1962.

10.0 Miscellaneous

10.1 LSO Console, Auxiliary Electronic Cabinet and Ship's Source Wiring : Reference Dwg. HE and Figure 2

The Dwg. HE shovrs a composite of cable connections from the ship's

input sources to both the Auxiliary Electronic Cabinet and any direct source

to the LSO Console. The Interconnect cables betv/een the Auxiliary Electronic

Cabinet and LSO Console are shown. The Auxiliary Electronic Cabinet is

located one level belovr the flight deck in a small room almost directly below

the LSO platform. The LSO escape passage hatch opens into the back of the

Auxiliary Electronic Cabinet room. Two J-boxes supply input signals to the Auxiliary Electronic Cabinet.

These are located on the outer bulkhead of the room. The distance from, the

signal J-boxes to the Auxiliary Electronic Cabinet is only a few feet.

The Signal J-box is the input terminal box for all of the ship's signals

to the Auxiliary Electronic Cabinet except the synchro signals which are in a separate J-box. These are the ACLS SPII-^2, Ramp Motion, VJave-Off, Deck OpenClosed and Aircraft Type Signals. A single, 100 conductor, cable conducts

these signals to the Auxiliary Electronic Cabinet.

The Auxiliary Electronic Cabinet contains the circuitry for converting

the input signals to the proper format to drive the displays of the LSO

Console. A 128 conductor cable transmits these signals between the auxiliary

electronics and LSO Console. - The 128 conductor, CRT Povrer Control, Console

Power Control and Power, CRT Defl. Amp. and 13 kV cable are about 30 ft in

length and couple the Auxiliary Electronic Cabinet to the LSO console on the

LSO deck platform. These cables are com.blned in a single flexible bundle

ill
with the following cables: (1) output cable from the Intercom 21MC unit

(LS-458/SIC) , (2)' composite Plat Input (RG90/U) , (3) MOVLAS Repeater Input,

(4) a dry nitrogen supply line (not used on the present Rnger installation),

(5) Ship's Radio System, and FLOT^ Wave-off and Cut Lights. This bundle of

cables is secured to the LSO Console mount and travels up and down as the

console is raised and lowered. All input-output cable plugs and sockets come

into the base of the LSO console. These plugs and sockets are color coded

and mechanically keyed to prevent improper assembly at both the Auxiliary

Electronic Cabinet and the LSO Console.

The radio handset and LSO "pickle switch" for LSO Wave-Off attach to

their respective plugs just below the LSO Console.

10.2 Junction Box Wiring Requirements ; Reference Dwg. 12E

The Signal J-box connections are indicated in this drawing. All input

and other cables as well as each terminal block is coded for ease of circuit

tracing and maintenance. For example, consider the Deck Open signal; it

comes in from the ship on RB38I and RBB and terminates on the terminal board

STB2 lug 15 (STB2-15) and STB2-19 respectively. The high signal, STB2-15,

goes to the Auxiliary Electronic Cabinet via the 100 conductor cable on Mo.

20 and STB2-19, which is the return, goes to 100-21. Likewise, the SPN-42

true airspeed (TAS) comes from rack l4 terminal board 31 terminal No. 9

(l^TB31-9) and is connected to the terminal block in the Signal J-box

designated by STBl-10. From STBl-10 the true airspeed goes to the Auxiliary

Electronic Cabinet by the #100-11 conductor. The ground return for this is

#100-6 to STBl-3 to TB31-8. Dwg. 12E does not show all of the detail

markings; these markings are in the Signal J-box on each lead and terminal

board.

The Synchro Signal J-box handles the synchro signal input lines from the

following synchros; wind speed, wind direction, and SPM-44 radar true and

closing airspeed lines, A single cable from this box conducts these input

signals to the synchro-to-dc converters in the Auxiliary Electronic Cabinet.

The Synchro J-box input leads, terminal blocks and output leads are all

coded similar to that used for the Signal J-box. The cross reference, Dwgs

.

24e, 2^IE4, and 24E5, shovis the synchro inputs to the auxiliary box via the

synchro-to-dc converter cable.

10.3 Console Plug Layout - Reference Dwg. 5E1

This drawing is useful for set-up and trouble shooting. The drawing is

a top view of the bottom of the LSO Console. It shows the location of all

the Input and output plugs or sockets. The two "pickle switches" for the LSO

wave-off and the radio handset locations are external for the Ranger

installation. They are mounted just below the console. It was considered

unnecessary for them to come into the box and go out since their use was not

related to the Internal workings of the console.

10. 4 Head-Up Scale, Console Scales & Console Scale Pointer Supplies

Reference Dwg, 6E, Block Diagram 5EB, Layout Dwgs. 4E and Figure 3.

Several different power sources, both AC and DC, are required for panel,

scale, scale pointer, and status display illumination. Dwg. 6E shows the

details of these. All of these supplies are located in the Auxiliary

Electronic Cabinet and have their controls on the LSO Console.

A 12 volt transformer is used to illuminate the ACLS lamps of Lock-on,

Mode I, II or III, and the deck status of either Open or Closed Deck. These

functions are shown in Dwg. 6E1 and 6E2 and discussed in Sections 8.1 and

8.2.

A 6.3 volt transformer is dedicated to Illuminate the three side panels

consisting of HUD, PLAT and Deck Status. This is also shown in Deg. 8E. A 2

ohm, 12.5 watt, rheostat in series with fixed resistors controls the

intensity of these panel control labels for night and low light levels. An

on-off switch is included to turn the illumination off during daylight

operations since the control functions are labeled in white on a black panel.
The HUD scale Illumination is controlled by a motor driven variable

autotrans former through a slip-clutch that functions when the autotransformer

is driven to either extreme. The autotransformer controls the output of a 28

volt transformer used for the HUD scale lamp. Also see Dwg. 6E3.

A similar motor driven autotransformer controls a 14 volt transformer to

Illuminate the four console display scales of Airspeed, Range, Rate of

Descent, and Ramp Motion. Also see Dwg. 6E3.

A 7V DC supply is used for pointer illumination of these scales (Lambda

Model LCS-B-01). This supply furnishes the voltage for both the trend and

the non-trend pointers as shown in the output circuit. The four scales have

individual pointer intensity controls and on-off switches. Certain

conditions may not require a scale display so each can be turned off

separately.

The ACLS SPN-42 information of Lock-On, Mode I, II and III has a separate on-off switch and a 50 ohm, 25V/, intensity control. The on-off

switch is a double pole type; the other side controls the Wind and Aircraft

Displays discussed in 10.4. These controls are detailed on drawing 6E1 and

6E2.

10.5 Wind and Aircraft Type Power Supplies - Reference, Dwg. 23E

The wind speed and magnitude synchro-to-dc converters and the SPN-^^

true and closing airspeed synchro-to-dc converters require +15V DC and -15V

DC. The circuits for obtaining these voltages are shown in Dwg. 23E. The

voltage regulators VR4, type 7815, and VR3, type 7915, are used to obtain the

+15V DC and -15V DC from the +20V DC and -20V DC supplies in the Auxiliary

Electronic Cabinet for the SPM-44 true and closing synchro-to-dc converters

described in Section 7.1.2, Dwg. 24E3.

Separate regulators, VR2 (type 7815) and VRl (type 7915), generate +15V

DC and -15V DC from the +20V DC and - 20 VDC for the wind speed and wind

angle synchro-to-dc converters covered in Section 8.5 and 8.6, Dwgs. 24e4 and

24E5. The +15V DC and -15V DC from VR2 and VRl are also required for the

analog-to-BCD converters, (ADC-898D), that drive the wind angle and speed

displays. These converters are located in the ACLS module with the

decoder/drivers for each alpha-numeric display.

The above described circuits along with the P/S detector, "any aircraft

detector" and +4V DC for aircraft and +4V DC for wind displays are all

contained on a single card located in the Auxiliary Electronic Cabinet.

10 . 6 Card Cage Layout in the Auxiliary Electronic Cabinet

Reference, Dg. 24E6

This is a reference layout showing the location in the Auxiliary

Electronic Cabinet of nine printed circuit cards for the four display scales,

the aircraft type indicator, and the vrind speed and viind angle indicators.

This information is useful when servicing or testing the equipment.

10.7 Synchro-to-DC Converter Layout : Reference, Dwg. 2HE1 and 24E2

These two drawings apply to the synchro-to-dc converter cards of SPN-44

true and closing airspeed and wind angle and speed for physical location of

parts and construction. They supplement the detailed circuit diagrams for

these functions in drawings 24E3, 24e4 and 24E5.

10.8 Miscellaneous Connections : Reference, Dwgs. 9E, 9E1, and 9E2

The drav/ing, 9E, is the layout of one of the several upper to lower

chassis connectors in the Auxiliary Electronic Cabinet. Also two terminal

boards are used for connecting input and output voltages or signals within

the chassis or to the LSO Console. The drawing 9E1 is a layout of these

terminal boards. Both of these layouts are useful for servicing of the

equipment.

its
Two terminal boards are located X'/ithln the LSn Console on the bottom.

These are used as distribution points of certain voltages. They are shovm in

drawing 9E2 with the voltage on each terminal. These are in addition to the

input plugs and sockets shovm in drawing 5E1.

n Simulator - Reference Dwg. 26e

The circuitry in drawing 26E has been built into a portable simulator test

box. The output signals incorporated in this simulator test box can be used to

test the LSO Console operation without the SPM-42 output or other outputs. The

controls and switches permit checking of the functions as indicated on the- box.

The simulator outputs go to the signal J-box in place of the normal input data.

Three adjustable power supplies are necessary as inputs to the box. They are as follows: +30V DC, +10V DC, -lOV DC supplies. A 115 AC line is necessary for the

open and closed deck tests. The indicated input levels to the box from the

supplies are the maximum levels to each circuit under test. The potentiometers on the box permit adjustment of the output to the circuit under test to cover the

full operating range.

A standard 115V 60 Hz test synchro is used to test the displays driven by the

ship's synchro output. The test synchro is a three line (SI, S2, and S3) unit

having 115V 60 Hz two line reference input with a 0° to 3^0° dial at its end to

adjust the output related to degree rotation. The SI, S2, S3 signals, and

reference signals are applied to the synchro signal J-box in place of the normal

ship's signals for the functions to be tested.

The author wishes to acknowledge the technical, design, and assembly

contributions made by R. 0. Stone, Owen B. Laug, David J. Brenner, F. L.

Greenough, Charles A. Douglas, Marvel R. Freund, Irvin Philmon, Leonard P. Leach,

William F. Lange and Patrick J. Tobin of NBS during the project. Also, the author

appreciates the excellent cooperation and contributions made by Donald H. Cooper

(Alameda) and Marvin L. Romack (San Diego) of the Carrier and Field Services

Offices of NAEC during the installation of the LSO system aboard the USS Ranger

for the test and evaluation period.

Mr. Dean V/. Houck, formerly of M & T Co., provided technical liaison betv;een

the Navy and NBS.

The Automatic Carrier Landing System Facility at the Patuxent Naval Air Station

provided excellent cooperation and technical assistance for testing of the

equipment before shipboard installation.

APPENDIX

12.1 Scale Removal

All the scales are removable from the front of the console. The

following three steps must be followed before any of the scales can be

removed. Handle polarized plastic faceplate with care to prevent scratching.

1. Console should be in an inside, dry and protected

area x^ith all electrical power turned off.

2. Remove the four screws in the corners of the

.LS-^58/SIC intercom and remove the intercom

by pulling straight out.

3. Remove all the screv/s in the bezel around the outer

edge of the plastic faceplate, then carefully remove

the bezel and the faceplate.

^1. Each scale is then removed as follows:

Ramp Motion

(a) Follow steps 1, 2 and 3 and then loosen the two

captive screws located on the tv;o ends of the scale.
(b) Remove scale part way and then disconnect the

connector on rear of the scale by reaching In

through the Intercom opening.

Airspeed

(a) Follow steps 1, 2, and 3 under Scale Removal and

then loosen the captive screws on the two ends of

the scale.

(b) Remove scale part way and then disconnect the connector

on rear of the scale by reaching In through

the Intercom opening.

ACLS

(a) Follow steps 1, 2 and 3 under Scale Removal and

then loosen the two captive screws on the top and

bottom of the scale.

(b) Remove scale part way and then disconnect connectors

on rear of scale by reaching In through the Intercom

opening.

Rate of Descent

(a) Follow steps 1, 2 and 3 and then either follow

the steps for removing the ACLS scale or for opening

the back of the console. Either one of these steps

will be necessary to allow access to disconnect the

connector from the rear of the Rate of Descent (or Sink Rate) scale.

(b) Disconnect connector.

(c) Remove scale by loosening the two captive screws

at the top and bottom of the scale.

Range Scale

(a) Follow steps 1, 2 and 3 and then loosen the two

captive screws from both ends of the scale.

(b) Remove scale by pulling straight out.

12,2 HUD Scale Lamp Replacement

The HUD Scale lamp should be visually Inspected frequently for signs of

blackening. In case of blackening or burn out, the lamp should be replaced

with an Identical lamp. (4596 Aircraft Landing Lamp. PAR-36, 28 volt, 250

wat t

)

1. Turn off the power to the console and. If time Is

available, allow lamp housing to cool a fev; minutes

to prevent burning fingers .

2. Lamp housing on rear of console Is unlocked and

hinged down by pulling outward on the two knurled

knobs on the ends of the housing.

3. Remove lamp by rotating lamp retaining clips clockv/lse.

4. Loosen screws on back of lamp and remove power leads.

5. Replace new lamp by following the removal steps In the

reverse order.

45
12 . 3 Removal of Rear Access Panel of Console

1. Turn off power to console.

2. Pull outward on the two knurled knobs at the ends of

the lamp housing and lower housing to an open position.

3. Loosen all captive screws around outer edge of panel,

including the three screws located inside the lamp

housing. Close the lamp housing. Lower panel on hinges.

H. Panel may be removed from console completely by

unplugging the two electrical plugs and moving panel

to the right to separate the hinge pins.

12A Removal and Installation of HUD CRT Assembly

I. Turn off all power to the unit .

2. Place the spherical concave mirror in the raised position

and secure it as for normal operation.

3. Raise the combiner until the guide pins in the track are

at the slots 1-1/2 inches from the fully raised position.

4. At all times carefully support the glass combiner .

5. Compress the two round knobs at the bottom edge of the

combiner toward the center to release pressure on the

track and lift the bottom edge out of the slots.

6. Remove the right edge of the combiner from its pivot

support by pushing on the arm at the glass edge and

moving the glass to the left. Store the combiner in a safe place until ready for installation.

7. Remove the eight (8) Allen head 10-32 stainless steel screws

on the top around the CRT protection glass or plastic cover.

8. Release the hinged back by releasing the l8 captive screv/s

including the ones covered by the lamp housing see section 12.3.

Remove the back completely by disconnecting the motor and lamp

plugs and sliding the back to the right off of its pin

hinges. The back may be left on by carefully letting it

hinge down against the rear carrying bar.

9. Remove the high voltage lead to the CRT at the plug.

10. Disconnect the two plugs directly in back and at the

bottom of the CRT shield.

11. Disconnect the grid control (Gl) lead (green wire) at the

small connector.

12. Remove the assembly ground lead (black) from the left

side and re-tighten the screw to clear the top cut out,

13. Clear all disconnected plugs from other wiring.

IH . Grasp the assembly by the CRT shield and lift up until the

unit can be handled from the outside.

15. Finally remove the assembly from above being very careful

not to touch, scratch or damage the spherical concave mirror

above.

16. Insert a replacement assembly HTID or the same unit after

service by reversing the above operations proceeding from

15 to 1.

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12.6 HUD Calibration Table

Ramp Motion: + lOV gives full-scale deflection

Airspeed: + 3.13V = 80 knots

3.91V = 100 " 5.09V = 130 " D.2oV = loO

7.0W = 180 "

+ 2.58V = 1/4 mile

5.16 = 1/2 " 7.74 = 3/4 " 10.32 = 1.0 "

Range :

Aircraft Symbol : Divisions 10 ft/div 30 ft/div X or Y

0 OV OV X

3 2.93V ~ " 5 14.88V — " 8 7.80V 23.4V Tt

0 OV OV Y

3 2.36V 7.05V It 5 3.92V 11.77V tf 8 6.28V 18.R2V tt

12.7 Physical Characteristics of LSO Console, Panning Head, and

Auxiliary Electronic Cabinet

Console (Approx. Size and Weight)

1. Weight: 54.43 kg (120 lbs)

2. Width with spherical concave mirror in stored (down)

position: 64.44 cm (25.375 in)

3. Height Including rubber feet: 44.68 cm (17.625 in)

4. Depth including HUD lamp box and front and back carrying

handles: 64 cm (25.25 in)

Panning Head (Approx. Size and Weight)

1. V/idth: 30.5 cm (1 ft)

2. Height: 17.8 cm (7 in)

3. Depth: 19 cm (7.5 in)

4. Weight: 7.26 kg (16 lbs)

Auxiliary Electronic Cabinet (Approx. Size and Weight)

1. Height: 124.5 cm (49 in)

2. Width: 66 cm (26 in)

3. Depth: 64 cm (25.25 in), with door handles

68.6 cm (27 in)

4. Weight: 104.33 kg (230 lbs)

12.8 Electronic Diagrams

Block

Diagram Drawing

Plat Monitor Changes lEB IE

CRT, Gl, G2, G4 and 15kV

Power Circuits 2EB 2E

CRT Power & Defl. Amp. Front View Layout 3E

49
Power Supplies & CRT Gating Layout

Cabling: High Voltage & Amplifier to CRT 5E

Console Plug Layout 5E1

Head-Up Scale, Console Scales & Console

Scale Pointer Supplies 6EB 6E

Wave-Off & Deck Status 6E1B 6E1

ACLS Radar Selection Status with ACLS

Lock-On, Modes & Warning 6E2B 6E2

Main Power Control R AC Wiring 6E3B 6E3

Monitor of Oscillator & -70V 7EB 7E

Function Panel Illumination 8E

6 Terminal Socket & Cable, Upper Chassis 9E

Terminal Board Connections 9E1

Console Terminal Board Connections 9E2

CRT Voltage and Power Cable lOE

LSO Console, Secondary Electronic Cabinet

to Ship's Source Wiring HE

Junction Box Wiring Requirements 12E

Airspeed Preamp and Ramp Motion Invert. Amp. 13EB-21EB 13E

Scale Display Input-Output Wiring 13EB-21EB 14E

Airspeed: Analog to Digital Converter 13EB-21EB 15E

Airspeed Scale of 100 Decoder & Driver 13EB-21EB 16E

Ramp Motion: Analog to Digital Converter 13EB-21EB 17E

Scale of ^0 Decoder Lamp Driver for

Ramp Motion and Rate of Descent 13EB-21EB 18e

Range: Analog to Digital Converter 13EB-21EB 19E

Range Scale of 30 Decoder & Lamp Driver 13EB-21EB 20E

Rate of Descent: Analog to Digital

Converter 13EB-21EB 21E

Aircraft Designator Card 22EB 22E

Power Card: +4V, +15V, -15V 23EB 23E

SPN-il4, V/ind Speed & Angle 2hEB 24E

Synchro-to-DC Cards for Airspeed & Wind Data, Layout 24E1

Synchro-to-DC Converter Drilling Layout 24E2

True & Closing Airspeed Cards for SPMi|4 2ilEB 2ilE3

Wind Speed Card 24EB 24e4

50
Wind Angle Card 2ilER 2'1E5

Card Cage Layout for Auxiliary Cabinet

SPMil2, SFU^iH & Wind 2^E6

MOVLAS Indicator 25E

Simulator: Box and Circuitry 26E

HUD Display Switches 27E

HUD Circuits, Technical Details 31E1-31E5

Mechanical Drawings

Head-Up Display Optics IM R 2M

HUD CRT Deflection Amplifier and Yoke BM

USCOMM-NBS-DC 51
NBS-IUA (REV. 7-7JI

U.S. DEPT. OF COMM. BIBLIOGRAPHIC DATA

SHEET

1. I'l MI K A 1 ION ()|( Kl roH r NO. NBSIR 74-589R2. (i(lV 'l Al < I s MUD

No.

3. K( ( ipH iii's Ai ti ssion Nil.

4. Ill l.i: AND MiM 11 ll.i INSTRUCTION AND TECHNICAL MANUAL

FOR

PROTOTYPE LANDING SIGNAL OFFICER'S DISPLAY SYSTEM

C 1)11 1 \ . 3. 1 u hi K a I ion 1 '.it c November 1974

6. I'lrfof niiiii; Organization ( odt- NBSIR 74-589R

7. AU rilOK(S)

Charles C. Gordon

8. Pirforming Organ. Report No.

9. Pi:Kt"ORMINCi OKC.AN'IZATION NAMi; AND ADDKKSS

NATIONAL BUREAU OF STANDARDS

DEPARTMENT OF mMUFRrF

WASHINGTON, D.C. 20234

10. Proie^t/Ta.sk 'Work L'nil No.

11. Contract , Grant No.

12. Sponsoring Organization Name and C ompleic Address (Street, City, State, ZIP)

Commander

Naval Air Systems Command - Code 53722

Dept. of Navy - Washington, D. C, 20361

1 J. 1 ypc or Kcport & Period Covered

Interim Report

14. Sponsoring Agency Code

15. SUPFLEMENTAKY NOTES

16. ABSTRACT (A 200-word or less (actual summary ol most sigpilicanj information. If document includes a significant

bibliography or literature survey, mention it here.)

This manual describes the prototype Landing Signal Officer's (LSO)

Display System that is installed aboard the USS Ranger CVA61 Aircraft

Carrier. The prototype LSO Console was designed and engineered to

fulfill requirements proposed in a study for an improved LSO work

station. The first four sections (1.0 thru 4.5) of this manual provide

the information needed to operate the equipment, while the remaining

sections give a technical description of the equipment and will be

useful when service or modifications are required. The technical

sections are written to be used in conjunction with the electronic and

mechanical drawings furnished with the equipment.

17. KEY U'ORUS (six to twelve entries; alphabetical order, capitalize only the first letter ol the first key \iord unless a proper name; separated by semicolons) Aircraft Carrier landings monitoring; Aircraft airspeed,

range, and rate of descent monitor; Carrier ramp motion repeater; Head-up

display (HUD); Landing signal officer's console; MOVLAS repeater.

18. AVAILABILITY Unlimited [X For Off icial Oistribution. Do Not Release to NTIS

Order From Sup. of Doc, U.S. Covcrnment Printing Office Washington, DX. 20I0:, SH C.ii. No. CM

Order l-rom National Technical Information Service (NT IS) Springfield, Virginia 22ISI

19. SECURITY CI.A.SS (THIS REPORT)

UNCLASSIFIED

21. NO. OH PAGES

55

20. SE( UKITY CLASS

(THIS PAGE)

UNCLASSIFIED

22, Price

USCOMM-OC 29042-P74

I

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