Click here to make tpub.com your Home Page

Page Title: Control, Navigation Latitude Data Interface
Back | Up | Next

Click here for thousands of PDF manuals

Google


Web
www.tpub.com

Home

   
Information Categories
.... Administration
Advancement
Aerographer
Automotive
Aviation
Construction
Diving
Draftsman
Engineering
Electronics
Food and Cooking
Logistics
Math
Medical
Music
Nuclear Fundamentals
Photography
Religion
   
   

 




img
MIL-N-81497A(AS)
Electrical Connectors - Electrical connectors.
3.5.1.7
shall be:
Function
Type
Designation
Aircraft
Cable to:
MS3114-H-22-55PZ
6J1
Edge Lightinq - Edge lighting shall be supplied
3.5.1.8
to the Control, Navigation from external sources. Edge lighting
shall be 5 to 28V, variable, 400 Hz, single phase.
Advisory Lamp Excitation -  All advisory lamps
3.5.1.9
shall be energized by a +28V DC or +9V DC aircraft power source.
Lamp Check Function -  The Control, Navigation shall
3.5.1.10
contain diode isolated circuitry to check all advisory lamps, when
the equipment is operating, upon application of an external +28V DC
test signal.
Color - The Control, Navigation including shell,
3.5.1.11
front panel, and controls, shall be lusterless black No. 37038 of
FED-STD-595.
Control, Navigation Mounting - The Control,
3.5.1.12
Navigation, shall be a console mounted unit in accordance with the
requirements of MIL-C-6781.
3.5.1.13
Control, Navigation Latitude Data Interface -
Upon receipt of a 10 KHz serial clock signal from the Computer,
Navigation, the Control, Navigation shall transfer a 13 bit serial
binary data word dependent upon the setting of the back-up latitude
thumbwheel switch positions. Each data word shall consist of three
4 bit characters and one 1 bit character. Bit position 13 shall
identify North or South (N or S) position. A logic 1 in bit position
13 shall indicate a South setting. The data word shall present least
significant bit first with the three 4 bit characters representing
10 arc MIN, DEG and 10 DEG intervals respectively in binary form.
Control, Gyroscope Assembly C7560\ASN-84 -  The
3.5.2
Control, Gyroscope Assembly unit shall meet the following requirements.
Function -  The Control, Gyroscope Assembly shall
3.5.2.1
contain the indicators necessary to inform the operator at all times
of mode of operation, alignment status, ilure status and indication.
The Control, Gyroscope Assembly shall also contain the Self Test Sub-
mode initiate control and the Submode control (for the Inertial Mode).
The Control, Gyroscope Assembly shall be the INS heading computer
providing analog signals of true heading, compensated magnetic heading,
slewed grid heading, magnetic variation, and clutched heading. Built-
in test circuitry (BITE) shall be incorporated into the Control, Gyro-
scope Assembly for the determination of unit malfunction. Manual
insertion of magnetic variation for the generation of coarse true
heading shall be provided.
29

Privacy Statement - Press Release - Copyright Information. - Contact Us

Integrated Publishing, Inc. - A (SDVOSB) Service Disabled Veteran Owned Small Business