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Flight Systems SCU 9iS, Installation & Operation Manual

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Flight Systems SCU 9iS Installation & Operation Manual Download Page 17

 

Installation / Operation Manual 
System Control Unit 

 

16.03.2021 | V1.04 

-17-  

 

The START_PWR and STARTER relay outputs drive up to 500 mA of inductive load and are referenced 
to the internal ground (Pin 15). The SCU uses these outputs to drive external start power and starter 
relays to simplify or even automate the engine start procedure. Using the Start Power relay, the ECU 
is  automatically  connected  to  the  battery  power  during  engine  startup  as  opposed  to  the  pilot 

activating a spring loaded “Start Power” switch. The function is activated only after startup of the 

SCU 

until the engine reaches 1500 rpm for the first time. As soon as this condition is met, the ECU is supplied 

by one of the internal generators. A separate, mechanically locking “Battery Backup” toggle switch (as 

found on the  SCU Front Panel)  remains  necessary in order to  fulfil all safety requirements (e.g. for 
engine restart in flight). An extinguishing diode across the relay coil is not needed and a suitable relay 
is  available  as  an  accessory  (see  Chapter  5.7).  The  Starter  relay  is  intended  for  use  on  unmanned 
aircraft. Feel free to contact RS Flight Systems for different sensor and actuator configurations. 

 

5.3

 

External Connector 

The I/O connector offers filtered, but unregulated power output and further general I/O connections. 
The digital inputs are referenced to aircraft ground (Pin 3). 

The low-side outputs are referenced to the internal ground and the high-side outputs are referenced 
to the power output. 

Pin Number 

Signal Name 

Function 

1 

DIN9 

do not connect 

2 

DIN10 

do not connect 

3 

AC_GND 

do not connect 

4 

LS_OUT2 

do not connect 

5 

LS_OUT3 

do not connect 

6 

LS_OUT4 

do not connect 

7 

LS_OUT5 

do not connect 

8 

LS_OUT6 

do not connect 

9 

LS_OUT7 

do not connect 

10 

GND 

Internal Ground 

11 

GND 

Internal Ground 

12 

GND 

Internal Ground 

13 

GND 

Internal Ground 

14 

GND 

Internal Ground 

15 

LS_OUT0 

do not connect 

16 

HS_OUT2 

do not connect 

17 

HS_OUT3 

do not connect 

18 

HS_OUT4 

do not connect 

19 

HS_OUT5 

do not connect 

20 

HS_OUT6 

do not connect 

21 

HS_OUT7 

do not connect 

22 

PWR 

Power Output (9-32 V) 

23 

PWR 

Power Output (9-32 V) 

Summary of Contents for SCU 9iS

Page 1: ...Installation Operation Manual SCU 9iS System Control Unit Version 1 04 Copyright 2021 RS Flight Systems GmbH ...

Page 2: ... Panel 9 4 3 Drawings SCU Front Panel 11 5 Electrical Installation 13 5 1 Lane A Lane B Lane C Connector 14 5 2 Auxiliary Connector 15 5 3 External Connector 17 5 4 Front Panel out Connector 18 5 5 Electrical Installation Front Display Panel 18 5 6 Wiring Diagram SCU 20 5 7 Available Accessories 21 6 Operation 22 6 1 Startup Power Relay Function 22 6 2 Flight Data Recording 22 6 3 Software Update ...

Page 3: ...al actuator system Three optically isolated CANaerospace data bus interfaces for retained redundancy Engine Data transfer to CAN based third party avionics systems e g by Garmin or Dynon Continuous monitoring and health checking of both ECU display buses Seamless integration into the Rotax 912iS 915iS engine wiring harness Minimum installation effort single device 2 connectors and 6 wires for basi...

Page 4: ...without switches the following additional functions are offered Indication of the most important engine parameters engine status and ECU faults Simple and self explanatory operation via three push buttons All necessary indicator lights for Rotax iS engine operation All necessary switches for Rotax iS engine operation Front Panel only in combination with optional Start Power function Figure 2 3 SCU...

Page 5: ...3 A at 14 V 0 18 A at 28 V without external load CANaerospace Interfaces According to ISO 11898 2 optically isolated two input channels one output channel Analog I O 4 inputs 10 V Digital I O 5 low side inputs 5 high side inputs 14 outputs 7 low side 7 high side driving up to 2 4 A each Positioning Combined GPS Galileo Sensor Navilock NL 603P 4 Hz update rate Electronics Xilinx Spartan 3 FPGA with...

Page 6: ... Pattern width height 4 M4 screws 80 x 57 mm 3 15 x 2 24 in 4 M4 screws 142 x 58 mm 3 59 x 2 28 in Total Mass 0 12 kg 0 26 lbs 0 4 kg 0 88 lbs Housing Aluminum visible surfaces anodized to aerospace standard Supply Voltage 12 V and 3 3 V supplied by the SCU Main Unit Lane A B LEDs supplied by ECU HIC connector Power Consumption typ 0 5 W Display 2 1 inch monochrome OLED display 170 viewing angle 1...

Page 7: ...ons can be taken from Figure 4 1 If you are using fixed female threads in the mounting surface instead of nuts provide a minimum thread length of 4 mm Always secure your mounting joint The Front and Display Panels require a rounded rectangular cutout see Figure 4 6 and Figure 4 8 and are mounted on the aircraft instrument panel using four M4 Philips headed screws included in the package Three dime...

Page 8: ...16 03 2021 V1 04 8 Installation Operation Manual System Control Unit 4 1 Drawings SCU 9iS Main Unit Figure 4 1 SCU 9iS Main Unit front view Figure 4 2 SCU 9iS Main Unit side view ...

Page 9: ...ion Operation Manual System Control Unit 16 03 2021 V1 04 9 Figure 4 3 SCU9iS Main Unit isometric view 4 2 Drawings SCU Display Panel Figure 4 4 SCU Display Panel top view Figure 4 5 SCU Display Panel side view ...

Page 10: ...16 03 2021 V1 04 10 Installation Operation Manual System Control Unit Figure 4 6 SCU Display Panel front view Figure 4 7 SCU Display Panel isometric view ...

Page 11: ...allation Operation Manual System Control Unit 16 03 2021 V1 04 11 4 3 Drawings SCU Front Panel Figure 4 8 SCU Front Panel front view Figure 4 9 SCU Front Panel top view Figure 4 10 SCU Front Panel side view ...

Page 12: ...16 03 2021 V1 04 12 Installation Operation Manual System Control Unit Figure 4 11 SCU Front Panel isometric view ...

Page 13: ...the operation of the unit yet may impair recordings of position ground speed and UTC data Each of the extension units comes with two standard density D Sub connectors with 4 40 UNC threaded fastening on the rear of the display part In case of the Front Panel the ignition auxiliary fuel pump and battery backup power switches need to be connected using individual wires according to the Installation ...

Page 14: ...mpedance of 120 Ω Do not connect either of the CAN Ground Pins available on the two Harness Interface Connectors Since termination resistors are built into the ECU as well as the SCU no additional resistors are necessary Pin Number Signal Name Function 1 PWR_IN positive SCU power supply 2 CANL_A CAN Low connect to HIC A Pin 5 3 EXT_PWR_ACT do not connect 4 EXT_DIN2 do not connect 5 AC_GND negative...

Page 15: ...or The Auxiliary Connector is used for general I O purposes It offers regulated 12 V Pin 13 and 5 V Pin 11 reference voltages for sensors and can supply a maximum of 100 mA each Both supplies are referenced to a common ground Pins 5 and 12 isolated from the aircraft supply potentials The analog inputs also refer to the same potential The maximum analog input voltage is 10 V Note that higher voltag...

Page 16: ...contact RS Flight Systems for further details A prewired harness is available as an accessory see Chapter 5 7 Pin Number Pin Name Function 1 AIN0 Analog Input 0 Fuel Pressure 2 DIN6 do not connect 3 DIN7 do not connect 4 AIN3 Analog Input 3 Governor Limit 5 GND Analog Input Reference Ground 6 START_PWR Start Power Relay Output 7 MOTOR Propeller Governor H Bridge Driver Output High Side 8 MOTOR Pro...

Page 17: ...l is not needed and a suitable relay is available as an accessory see Chapter 5 7 The Starter relay is intended for use on unmanned aircraft Feel free to contact RS Flight Systems for different sensor and actuator configurations 5 3 External Connector The I O connector offers filtered but unregulated power output and further general I O connections The digital inputs are referenced to aircraft gro...

Page 18: ...panel out connector is listed in Table 5 8 Pin Number Signal Name Function 1 PWR_IN 12V positive Front Panel power supply 2 PWR_IN 3 3V positive display power supply 3 OLED_SCK Display control 4 OLED_MOSI Display control 5 OLED_CS Display control 6 TAST1 Button 1 7 TAST2 Button 2 8 TAST3 Button 3 9 GND Internal Ground Table 5 8 Front Panel Out Connector pinout 5 5 Electrical Installation Front Dis...

Page 19: ...nectors The Start Backup Power LED pin 5 can be connected in parallel to the Start Power Relay in order to show the pilot the status of Start Power Relay function For the connection of the generator LEDs please refer to the manual of the generator Pin Number Signal Name Function 1 LANE_A Warning Lamp Lane A 2 LANE_A_GND Warning Lamp Lane A ground 3 LANE_B Warning Lamp Lane B 4 LANE_B_GND Warning L...

Page 20: ... 7 8 6 15 ECU HIC A Main Bus Aircraft GND HIC B FPS C A B C A B Governor 5 6 3 4 5 6 3 4 390 Ω GNSS Antenna SPR 0 1 1 12 11 4 5 7 8 6 15 2 4 6 8 CAN Low A CAN High A 120 Ω Fusebox 2 3 2 3 X3 Signal Input Reference GND 5 V Reference Stop Signal Reference GND Motor Motor Start Power Aircraft GND GNSS EMS GND Aircraft GND 1 5 2 7 2 7 STP white black red white black red blue DNC Aircraft GND STP DNC A...

Page 21: ... 5 ft 10 806 Hollow Screw Adapter to mount the fuel pressure sensor on the fuel rail 10 085 Connector Kit Auxiliary EMU SCU Manufacturing kit for Auxiliary connector Includes shell connector housing and contacts Requires M22520 crimping tool 21008 716 SLPC Connection Harness Prewired shielded harness for governor control Open end on SCU side to allow for custom integration Length 3 m 10 ft 10 140 ...

Page 22: ...tart power using an external relay wired in parallel to the SPS This relay is activated as soon as the SCU is powered up below 1 sec and remains activated until the engine reaches 1500 rpm for the first time As soon as this happens the relay is deactivated and is never activated again until the SCU is turned off Using this function engine start can be commanded through a Start Key Switch whose STA...

Page 23: ...cal data rate is 30 kilobytes per second Using a 32 GB SDHC memory card this results in a maximum recording time of 300 hours A powerful Engine Management Debriefing Station EMDS software for the Microsoft Windows SuSE Linux and Apple MacOS X operating systems is delivered with the SCU This tool see Figure 6 3 to Figure 6 7 allows for visualization and post processing of the recorded data as well ...

Page 24: ...16 03 2021 V1 04 24 Installation Operation Manual System Control Unit Figure 6 4 EMDS Data Screen Figure 6 5 EMDS Fault Matrix Screen ...

Page 25: ...Installation Operation Manual System Control Unit 16 03 2021 V1 04 25 Figure 6 6 EMDS Limits Screen Figure 6 7 EMDS generated Google Earth View ...

Page 26: ...re detected the content is automatically programmed into flash memory and the device starts up using the new software An installation logfile INSTALL LOG is created and stored on the memory card and the update files are deleted The standard software versions are listed in Table 6 1 Feel free to contact RS Flight Systems for customized software versions with individual SLPC algorithms Software Vers...

Page 27: ...or GB Gigabyte GEN Generator GND Ground GNSS Global Navigation Satellite System e g GPS Galileo GLONASS HIC Harness Interface Connector ISO International Organization for Standardization I O Input Output LCD Liquid Crystal Display LED Light Emitting Diode MAN Manifold Pressure MCR Master Caution Reset RET Return RPM Revolutions per Minute Engine Speed RS 232 Recommended Standard 232 RX Reception S...

Page 28: ...RS Flight Systems GmbH Oberer Luessbach 29 31 82335 Berg Germany 49 8178 8681 300 contact rs flightsystems com www rs flightsystems com SCU 9iS Version 1 04 Copyright 2021 RS Flight Systems GmbH ...

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