TERRAIN AVOIDANCE RADAR

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP89B00709R000400890017-0
• Release Decision: RIFPUB
• Original Classification: S
• Document Page Count: 26
• Document Creation Date: December 27, 2016
• Document Release Date: December 6, 2011
• Sequence Number: 17
• Publication Date: January 1, 1958
• Content Type: REPORT

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CRE1 core OF,
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TERRAIN AVOIDANCE RADAR
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WESTINGHOUSE ELECTRIC CORPORATION
Air Arm Division
Baltimore, Maryland
NOTICE: This document contains information of.
fecting the national defense of the United States
within the meaning of the Espionage Laws, Title
18, U.S.C., Sections 793-794. The transmission or
the revelation of its contents in any manner to an
unauthorized person is prohibited by law.
SECRET
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CONFIDENTIAL
I&
This brochure contains information of a patent or proprietary nature; therefore,
all recipients are liable for the unauthorized use or disclosure of any part thereof
without the express written permission of Westinghouse Electric Corporation.
2 CONFIDENTIAL SECRET
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OUTLINE OF BROCHURE
TERRAIN AVOIDANCE RADAR
1.
Introduction ....................................................
5
2.
Low Altitude Missions .............................................
6
3.
Radar Indication .................................................
8
X-Scope Indicator .............................................
10
E-Scope Indicator .............................................
12
4.
Equipment ....................................................
14
Antenna and R-T Unit ... .... ......................................
16
Size and Weight ..................................................
20
7.
Summary of System Characteristics . . . . . .
23
ILLUSTRATIONS
Figure
Page
1.
Low Altitude Missions ............................................
Scanning Method ..... . ......................................... .
7
3.
Transverse Profile Indication (X-Scope) . .
11
4.
Longitudinal Profile Indication (E-Scope) .
13
5.
X-Scope and E-Scope .............................................. 15
6.
Antenna and Receiver-Transmitter ....................................
17
7.
Power Supply, Control, Modulator ............... .. ....................
19
8.
Size and Weight ............................. .. .................. 20
9.
System Configurations ............................ . ............... 21
SUHEU
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CONFIDENTIAL
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This brochure presents a brief introduction to Westinghouse Terrain Avoid-
ance Radar Systems. Since 1952, Westinghouse Air Arm Division ,has developed
and flight-tested several systems designed for aircraft with a mission require-
ment of low-altitude flight in either darkness or adverse weather.
Flight tests have proven the feasibility of a three-dimensional system of
presentation. At present, development is progressing on an advanced version-of
the Terrain Avoidance Radar Featuring greatly increased capabilities and sig
nificant reduction in size and weight over early flight test models. It is con-
templated that the flight test of this model will be conducted at Air Arm Division
in the near future.
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LOW ALTITUDE MISSIONS
With the rapid growth of ground-based, long-range radar and IR in-
stallations, , low-altitude approaches and penetrations have become in-
creasingly important as a means of avoiding detection over enemy territory.
The probability of survival'increases as altitude decreases, with an
increasingly more than proportionate benefit as the flight path drops below
500 feet. Maximum security can be achieved by following valleys or flight
paths behind. concealing ridges. This also minimizes the effectiveness
of-electronic countermeasures. by the enemy.
Low-level. approach to enemy territory from the sea can be made
with greater security from detection if a terrain avoidance system is uti-
'lized to give the pilot.a good landfall presentation in azimuth as well as
in elevation. With this three-dimensional information, a flight path near
wave-top level is possible right up to the shore line. Subsequent recon-
naissance can then be carried out at low altitude, taking advantage. of
protective topography where available.
Toss Bombing
The advantages of 'utilizing toss-bombing technique' s can be ef-
fectively supplemented by low-level approaches prior to the toss maneuver.
An effective terrain avoidance system can provide greater probability of
Support
and obscured from enemy radar by concealing ridges.
Missions which require the delivery of manpower and' supplies
near front line areas may be made with greater safety in the dark of night
Eu
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Low Altitude Reconnaissance
 LOW ALTITUDE
`'
RECONNAISSANCE
I I II 1 1II I l_ III 1 J -
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GP-6/64
-'CONFIDENTIAL
SUPPORT'
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TOSS BOMBING
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RADAR INDICATION
The method of presentation used in the Westinghouse Terrain Avoid-
ance Radar was selected as a result of an extensive study of the prob-
lem, plus numerous discussions with military personnel and pilots who,
had first-hand knowledge of the operational requirements. The objective
is to provide information requiring the minimum amount of pilot interpreta-
tion in order to reduce response time and the chance for error. Pilot
procedures for mission accomplishment are generally the same as those
followed under visual daylight conditions. The indicator simulates the
view which the pilot would normally see through his windshield; i.e.,
elevation angles vs azimuth angle related to the aircraft as the point of
viewing.
Scanning Method
The radar scans a sector ahead of the plane. This sector is 30
degrees wide and 10 degrees thick, vertically. A 2-degree pencil beam
scans this sector with a horizontal scan rate of 23 lines per second. Ver-
tical scanning is at a rate of approximately 2 frames per second.
The third dimension is presented by color-gating the signal re-
turns into three color segments - red for near, yellow for intermediate, and
green for distant targets, out to maximum range.
A "white" storage-type cathode ray tube is used in conjunction
with a red and green filter system to produce color images on a ground
glass viewing screen. Two scanning rasters on the cathode ray tube pro-
vide images of red and green while an appropriate amount of time-sharing
provides the yellow image where the red and green overlap.
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X-Scope Indicator
By superimposing the scan sector on a section of terrain, the
corresponding indicator presentation is illustrated. The color contours
correspond to the terrain contours within the various color segments.
The "wings" at the center indicate the aircraft heading in re-
lation to the radar picture. The radar presentation is natural, requiring
no mental transposition by the pilot. This ensures maximum speed of re-
cognition with minimum chance of error in interpretation.
The illustration shows in "static" form the presentation available
to the pilot, but in actual operation the pilot also perceives "rate" infor-
mation as the target contours progressively pass through the color se-
quence. Any lateral drift of the plane due to crosswind is similarly ap-
parent as a gradual drift of the radar picture, analagous to the drift ob-
served optically through the windshield under visual flight conditions.
The red and yellow segment limits are arbitrarily illustrated as
1% and 3 miles. These limits can be preset to other values to suit the
speed and maneuverability characteristics of a particular aircraft.
A pattern of lines across the indicator is tied in to a vertical
reference and thus serves to indicate aircraft roll attitude. These will re-
main parallel to the horizon and keep track of roll altitude even in severe
nose-up maneuvers where no ground return shows on the indicator.
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Figure 3. Transverse Profile Indication (X-Scope)
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E_Scope Indicator
The E-scope is an auxiliary indicator which presents a longi-
tudinal profile of terrain ahead of the aircraft. All radar signal informa-
tion required by this indicator is contained within the signals processed
by the X-scope system. By electronically selecting the signal return
along a narrow vertical section, a profile of the terrain intersected by that
section can be provided. Furthermore, the terrain profile displayed can
be chosen at will, anywhere within the 30-degree scan sector of the an-
tenna system.
This provides the advantages of detail range and elevation in-
formation normally presented by profilometer systems with the additional
feature of providing a choice of profile over a 30-degree angle without
changing aircraft heading. The position of the selected profile section is
indicated by a thin vertical trace on the X-scope transverse profile pre-
sentation.
Across the top of the E-scope a luminous line indicates altitude
of the plane above ground. This is calibrated to 1000 feet and derives its
signal from a portion of the radar signal directed at the ground below.
U
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Figure 4. Longitudinal Profile Indication (E_Scope)
A/C HEADING
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CONFIDENTIAL
EQUIPMENT
The X-Scope, which presents a transverse profile, is the principal
indicator for the pilot during low-altitude maneuvers.
The E-Scope, which presents a longitudinal profile, is an auxiliary
indicator to provide additional useful information and is particularly recom-
mended where a navigator is employed.
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Fiqure S. X_Scope and E_Scope
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The antenna installation with the receiver-transmitter and the modu-
lator can be mounted in any position affording a forward view and a space
of 23 inches in diameter and 36 inches long; however, the mounting must
be in a position which is not subject to undue angular distortion.
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COM,F14?I~I,T;LAL. r
MOUNTED IN
LOWER SECTION
REFLECTOR
SCANNING FEED
HORN
RECEIVER-TRANSMITTER
WING FUEL POD
INSTALLATION
WING SEARCHLIGHT
POD INSTALLATION
GP-6161
Figure 6. Antenna and Receiver_Transmitter
17 .,
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Figure 7. Power Supply, Control, Modulator
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Size and Weight
SINGLE INDICATOR (PILOT)
EQUIPMENT
DIMENSIONS
W-H-D (INCHES)
VOLUME
CU. FT.
WEIGHT
LBS
I
ANTENNA
16 x 16 x 12
1.78
42
2
RECEIVER-TRANSMITTER
II-I/8x9x11
.64
30
3
MODULATOR
9 x 6 x 7
.22
12
4
POWER SUPPLY
15 x II-I/4 x 15-I/2
1.52
20
5
SYNCHRONIZER
I2x 3-5/8 x 18
.45
10
6
CONTROL
8 x 10-7/8 x 8
.41
10
7
X-SCOPE (TRANSVERSE PROFILE)
OPTICAL HEAD
10 x 8 x 19-1/2
6 x 6 x 8
1.03
25
TOTAL SYSTEM
6.05 CU. FT.
149 LBS
MULTIPLE INDICATOR (PILOT AND NAVIGATOR)
EQUIPMENT
DIMENSIONS
W-H-D (INCHES)
VOLUME
CU. FT.
WEIGHT
LBS
I
ANTENNA
16 x 16 x 12
1.78
42
2
RECEIVER - TRANSMITTER
II-1/8x9 x 11
.64
30
3
MODULATOR
9 x 6 x 7
.22
12
4
POWER SUPPLY
15 x I I-I/4 x 15-1/2
1.52
20
5
SYNCHRONIZER
12x 3-5/8 x 18
.45
10
6
CONTROL
8 x 10-7/8 x 8
.41
10
7
X-SCOPE (TRANSVERSE PROFILE)
OPTICAL HEAD
10 x 8 x 19-1/2
6 x 6 x 8
1.03
25
8
AUXILIARY X-SCOPE (FOR NAVIGATOR)
OPTICAL HEAD
10 x 8 x 19-1/2
6 x 6 x 8
1.03
25
9
E-SCOPE (FOR NAVIGATOR)
12 x 8-1/2 x 18
1.06
20
TOTAL SYSTEM
8.14 CU. FT.
194 LBS
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1`%~\n. ..,+ 1A ; 144' `fRsY1 /JxbIA'C Y T I A
ANTENNA
R-T UNIT -
11'
SINGLE INDICATOR ARRANGEMENT (PILOT)
TOTAL SYSTEM VOLUME 6.05 CU. FT.
TOTAL SYSTEM WEIGHT 149 LBS.
ANTENNA
R-T UNIT
AUXILIARY X-SCOPE
E-SCOPE AND SYNCHRONIZER
CONTROL
DUAL INDICATOR ARRANGEMENT (PILOT AND NAVIGATOR)
]l
ll.
TOTAL SYSTEM VOLUME
8.14 CU. FT.
TOTAL SYSTEM WEIGHT
194 LBS.
Figure 8. System Configurations
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CON-FIDENr4A'L
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SUMMARY OF SYSTEM CHARACTERISTICS` 0
Pencil Beam 2 degrees
Scan Sector
Vertical 10 degrees
Horizontal 30 degrees
Scan Rate
Horizontal Lines 23 per second
Frames 2 per second
Attack Angle Adjustment
it
5 degrees Manually Adjustable at Control 'Unit'il
II,
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CONFIDENTIAL G.
7& 7q)
Transmitter
Magnetron Type
Frequency
Power
Pulse Length
Receiver
System noise figure
Receiver gain
IF frequency
Bandwidth
Local Oscillator
Tuning
MA 207
34,900 ? 350 Mc
60 Kw peak
0.25 microseconds
1365 pulses per second
12-56
91. db'
45. Mc
4.2 Mc
VA-97 Klystron
AFC or Manual
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Indicator - Transverse Profile (X_Scope)
Presentation Azimuth vs elevation, 10 x 3Q degrees.
Three range segments in red, orange, and
green.
CRT RCA C73703B storage tube with selective
erase gun.
Marks Vertical trace to indicate position of longi-
tudinal profile displayed on E-Scope.
Lines to indicate aircraft attitude.
Indicator - Longitudinal Profile (E_Scope)
Presentation Range vs. elevation
Scale 10-mile and 20-mile
CRT 5UP7
Marks 1-mile marks on 10-mile range
2-mile marks on 20-mile range
1[
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..CC?KFI~PENTIAL
System
Power Consumption
28 V DC
400 cycle 3
Total 1580 watts
CONFIDENTIAL
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