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 |
|