EFFECTIVITY
CONFIG 1
AIRPLANES WITH DELCO INS
798 Page 2
34-41-00
Apr 25/86
ALIGN
MODE SELECTOR UNIT
INS BATTERY XFR SWITCH
Inertial Navigation System Component Location
Figure 1 (Sheet 2)
EFFECTIVITY
AIRPLANES WITH DELCO INS
CONFIG 1798 Page 3
34-41-00
Apr 25/86
DH
DH
20 20 20 20
10 10 10 10
F 5 5 F 5 5
55
5 5
S
S
1010
1010
20 TEST
20 2020
T
ATTITUDE DIRECTOR INDICATOR ATTITUDE DIRECTOR INDICATOR
23
G
ATTITUDE INS NORM NORM INS
F/OON
ON 3
ATT/COMP STAB CAPT
33
2 CAPT 3 CAPT 3 F/O 2 F/O 2
CAPT 1 CAPT 1 F/O 2 F/O 2
CAPT 1 CAPT 1 F/O 3 F/O 3
INS AND ATTITUDE TRANSFER SWITCHES INS AND ATTITUDE TRANSFER SWITCHES
23
H
INS
NORM ON
ON 1
3
INS TRANSFER SWITCH
I3
Inertial Navigation System Component Location Figure 1 (Sheet 3)
EFFECTIVITY
AIRPLANES WITH DELCO INS CONFIG 1798 Page 4
34-41-00
Apr 25/86
(4) The three battery units are located on a separate shelf (E12) just forward of the main equipment center at body station 390 and buttock line 45R. Access to the battery units is through the main equipment center.
D. The INS continuously computes horizontal navigation data and senses airplane attitude displacements in pitch, roll, and yaw from a local-horizontal reference. Output signals from the INS are used to steer the airplane over a computed course to a preselected destination, to maintain the airplane and the weather radar display at a level attitude, to provide pitch data for the overrotation warning system, and to display navigation data and airplane attitude on navigation and flight instruments. Each INS furnishes a numerical display of its navigation data and operating status.
E. The INS navigation unit contains a gyro stabilized gimbal assembly which senses all changes in airplane attitude and acceleration. Attitude stabilization signals are produced for airplane movement about its pitch, roll, and yaw axes. Instruments in the gimbal assembly sense all vertical and horizontal accelerations (velocity changes). The velocity change signals, central air data computer signals, and manually inserted position data are used by a digital computer in the navigation unit. The digital computer uses the input signals to continuously solve navigation equations, to produce output signals for automatic steering along the desired track, and for display of the computed data.
F. The INS is characterized by the following features:
(1)
Automatic self-alignment and calibration are accomplished each time the INS is turned on.
(2)
Provides continuous cyclic ground alignment.
(3)
Uses (but does not require) inputs from external navigation aids.
(4)
Monitors its own performance and furnishes warning indications when output signals and displayed data are unreliable.
(5)
Insertion of present position, waypoint, and destination data is easily accomplished by using a keyboard.
(6)
Operates accurately within any latitude and longitude encountered in flight, including polar flights.
(7)
Indicating lights and displays can be replaced while INS is operating without hazard to equipment or personnel.
(8)
Can be used to produce only attitude (roll, pitch, and yaw) stabilization signals if navigation and/or steering signals become unreliable.
(9)
Provides continuous automatic three INS position mixing solution.
(10) On AF 116-150, 152-199; LH 011-030, 051-070, 082-099; AZ 221-299; XA MD 501-599; GN 601-699; AT 701-750; VM 751-799; less airplanes with XA PMS, see *[1], *[2], 34-41-00 page 1;
provides position update capability using radio navigation inputs.
(11)
Although barometric altitude and true airspeed from the central air data computer are inputs to the INS, loss of these inputs will not seriously affect INS operation.
(12)
INS performance can be improved during flight by making a position fix when an accurate present position reference is available.
(13)
On airplanes with PMS, PMS provides updated present position to the INS.
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