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Curtiss-Wright DTS1+ CSfC - Page 24

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User Guide DDOC0199-000-A9
1-Slot Data Transport System (CSfC) 3 - 7 Overview
© 2024 Curtiss-Wright Defense Solutions Revision 2.0
User control, status, & maintenance interface
Command Line Interface (CLI) via:
Secure shell (SSH)
Serial RS-232
Ethernet
SNMP via Ethernet
Rear panel connections
J1: Power input
Remote Power Disable
MIL-STD-704E compliant +28VDC
20 Watts maximum power dissipation
1.3 Amps peak inrush current
J2: Ethernet interface, RS-232, Reset, and Zeroization
10/100/1000 copper
IEEE 802.3, 802.u, and 802.ab
RS-232 serial communications
Zeroize discrete
Reset (reboot) discrete
J3: Ethernet interface
10/100/1000 copper
IEEE 802.3, 802.u, and 802.ab
Front panel controls and indicators
POWER LED (green)
FAULT LED (red)
KEY LOADED LED (yellow)
DRIVE CAPACITY LEDs
KEY CLEAR Button
Built In Test (BIT) capability
Provides overall health and status and out-of limits detection and notification
Start-up BIT (SBIT) (displayed upon start up)
Periodic BIT (PBIT)
Initiated BIT (IBIT)
Maintenance BIT (MBIT)
Test control via CLI, health status query via CLI and SNMP
Environmental
Temperature
Operating: -45 to +55°C (+71°C for 30 minutes)
Storage: -45 to +85°C
Operational Random Vibration
1 hour per axis: 0.02 g2/Hz from 5 Hz to 2 kHz
Operational Shock
Each axis: 20 impact shocks of 20 g’s, 10 msec, 2 kHz frequency range
MIL-STD-810 Half Sine
MIL-STD-810 Terminal Peak Sawtooth
MIL-STD-810 Initial Peak Sawtooth
Total of 60 impacts per unit
Non-operational Crash Safety
Each axis: 20 impact shocks of 40 g’s, 8 msec, 2 kHz frequency range
In accordance with MIL-STD-810, Method 516.4, Procedure C
In accordance with MIL-STD-810, Method 516.4, Procedure V
Total of 60 impacts per unit
Designed to meet the following environments:
Operational Sine over Random Vibration
MIL-STD-810E for AH-1/UH-1 Helicopter in Instrument Panel location
Altitude: sea level to 40,000 feet
Humidity: 0 to 95%, 20 to 55°C
Salt Fog
Sand and dust
Fungus