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Data Acquisition Units (DAU) and Sensor Interface Units (SIU)

Moritz Data Acquisition and Sensor Interface units are multi - processor based products, used to interface with a wide variety of aircraft sensors to precisely measure, process, and report aircraft engine, electrical, and fuel parameters. Automated built in calibration eliminates the need for field calibration while maintaining system accuracy and reliability over time.

 

These units have two serial outputs that can meet the requirements for RS232, RS422, RS485, ARINC429, BYTE FLIGHT, or CAN type interfaces. The output of these units is used to interface with the existing aircraft MFD and PFD, providing all electrical, engine, and fuel information.

 

 

Features:

  • Dual power inputs
  • Dual serial data outputs
  • Multiple Resistive type inputs for CHT(6 channel), OAT, OT, FT, FQ sensor interface and measurements
  • Multiple Thermocouple type inputs with cold junction compensation for EGT / TIT (6 channels) sensor interface and measurements
  • Multiple Frequency type inputs for RPM, %RPM, and FF sensor interface and measurements
  • Multiple Voltage and mVolt inputs for VAC, MAP, OP, and VDC sensor interface and measurements
  • Multiple Discrete type inputs for aircraft identification, and Squat switch interface
  • Multiple Discrete outputs for interface with aircraft Annunciator / master Caution / Advisory panel
  • Multiple sensor excitation (voltage) outputs
  • Multiple Shunt interface circuitry for aircraft Battery and Alternators current monitoring and measurements

Specification:

  • Operating Voltage: 10 to 32 VDC
  • Weight: 2.0 LBS Max.
  • Operating Temperature: - 40° C to +70 ° C
  • Storage Temperature: - 55 ° C to + 85 ° C
  • Accuracy: +/- 1% of full-scale value at room temperature, +/- 2% of full-scale value over extreme temperature ranges.
  • Dimensions (DAU): 2.73(H) x 5.12(W) x 6.4(L)
  • Dimensions (SIU): 1.80(H) x 5.40(W) x 6.15(L)
  • Software testing and certification: RTCA – DO – 178B level ”C”
  • Environmental testing and certification: RTCA – DO – 160D, see table-1 for details
  • Certification: FAA TSO

 

DO – 160D Enviornmental Qualification Test
Enviornmental Section Conducted Test Category
Temperature and Altitude    
Low Temperature 4.5.1 B1
High Temperature 4.5.2 & 4.5.3 B1
In-Flight Loss of Cooling 4.5.4 X
Altitude 4.6.1 C1
Decompression 4.6.2 4.6.3
Overpressure 4.6.3 A1
Temperature Variation 5 B
Humidity 6 A
Operational Shocks and Crash Safety 7 B
Vibration 8 S, Curve M
Explosive Proofness 9 X
Water Proofness 10 X
Fluids Susceptibility 11 X
Sand and Dust 12 X
Fungus Resistance 13 X
Salt Spray 14 X
Magnetic Effects 15 Class A
Power Input 16 B
Voltage Spike 17 B
Audio Frequency Conducted Susceptibility 18 B
Induced Signal Susceptibility 19 A
Radio Frequency Susceptibility 20 W
Emission of Radio Frequency Energy 21 M
Lightning Induced Transient Susceptibility 22 A3E3
Lightning Direct Effects 23 X
Icing 24 X
Electro Static Discharge 25 A
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