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Payload Control System (NASDAT, EIP)

Payload Control System (NASDAT, EIP). ER-2 and WB-57 Implementation NASA ASF, 9/14/2010 (PRELIMINARY 09/08/10). Contents. Introduction Requirements Implementation EIP NASDAT Network Control System Test Plan Schedule / Milestones Conclusions / Action Items Acronym List (Appendix).

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Payload Control System (NASDAT, EIP)

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  1. Payload Control System (NASDAT, EIP) ER-2 and WB-57 Implementation NASA ASF, 9/14/2010 (PRELIMINARY 09/08/10)

  2. Contents • Introduction • Requirements • Implementation • EIP • NASDAT • Network • Control System • Test Plan • Schedule / Milestones • Conclusions / Action Items • Acronym List (Appendix)

  3. Introduction • This review will… • Cover the preliminary requirements & design for the ER-2 and WB-57 EIP and NASDAT units. • Demonstrate the ASF is ready to proceed with detailed design. • This review will not… • Be a review of the Global Hawk system (it’s different!) • Cover, in any significant detail, payload communications or the InMar-SAT system. ASF – Airborne Sensor Facility @ NASA ARC EIP – Experimenter Interface Panel; an instrument electrical interface. NASDAT – NASAAirborne Science Data Acquisition and Transmission unit

  4. Key Requirements • Level 1 (NASA Airborne Science / HQ): Sensor Web – A distributed and coordinated network of sensors which collectively act as a single “macro- instrument.” (Delin, Sensors Magazine 4/1/2004)

  5. Key Requirements • Level 2/3 (ER-2 & WB-57 Systems):

  6. Requirements (25A x 2 ckts) (79A) (50A x 2 EIPs) (72Ax2 EIPs) (79A) (30A) (30A) DC CURRENT CAPABILITY: 100A per EIP (2.8kW)* AC CURRENT REQUIREMENT: 50A / Ф, per EIP* * - Ampacity analysis per SAE-50881D (Wiring Aerospace Vehicle)

  7. EIP Implementation EIP Functional Block Diagram:

  8. EIP Implementation • A modular, PCB-based design reduces wiring and simplifies assembly & maintenance w/rt to the Global Hawk version. SSPC Module (4) AC Distribution Module Legacy Module DC Distribution Module Ethernet Module (Monitor Module Not Shown)

  9. Support 5 experiments with 3 ‘Misison Critical’ and 1 (modified) ‘Air Data’ connector(s) Drop to 4 PWR connectors (5 command relays / EIP); EIP Implementation J6-J9 change to D38999/21-16 Provide analysis for 50A/circuit (same connector) Fuse internal circuit internally Replace J13 & J14 with Ethernet; leave aircraft wire in place & use as needed. Ship-side signals (DC, AC, Control input) connectors are unchanged.

  10. EIP Implementation EIP Front Panel: Mission Critical 2x50A DC Output Control & Data Input AC/DC Power AC/DC Power Mission Critical Mission Critical 3Ф AC Input AC/DC Power Legacy Output AC/DC Power 8x100 Mb Ethernet 4x1Gb Ethernet

  11. EIP Implementation • Legacy EIP Power (Mixed AC/DC) Connector Using 3 #16 DC circuits, 2 with SSPCs @ 17.5A trip, 1 fused @ 10A Tie shields at backshell (TBD) • - GLOPAC safety circuit used for command circuit – lose NC contact (except for legacy connector) • GPS splitter designed-in but not installed; GPS socket removed in PWR connector • IRIG-B moved to PWR connector (GLOPAC style)

  12. EIP Implementation

  13. L1/L2/Omnistar GPS (coax) (not provided for WB-57/ER-2) 3Ф, 400Hz AC Circuit #1 (10A/Ф) 3Ф, 400Hz AC Circuit #2 (10A/Ф) 28VDC Circuit #1 @ 17.25A 28VDC Circuit #2 @ 17.25A IRIG-B (coax) Command Relay (N.O. & COM) @ 10A EIP Implementation • Standard Instrument Power Connector (Amphenol D38999/20WG16SN) • 16 x AWG #16 contacts, same pinout as Global Hawk EIP

  14. EIP Implementation • DC In & Hi-Power Out connectors: same as prior design

  15. EIP Implementation • Modified Legacy Data Connector (page 1 of 2) NEW ASSIGNMENTS: ZJ: INTERLOCK #2 ZM: AIRCRAFT GROUND ZN: ALTITUDE SWITCH #2 N.O. ZP: ALTITUDE SWITCH #2 COM ZQ: LANDING GEAR #2 N.O. ZR: LANDING GEAR #2 COM ZS: FAIL LAMP DRIVE #2 ZT: SPARE

  16. EIP Implementation • Mission Critical / Aircraft Data Connector (page 2 of 2)

  17. EIP Implementation • Mission Critical Connector (Amphenol TVP06RW9-9S) • High-density D38999/III, 9x AWG #23 contacts • Will supply conversion adapters to legacy connector Redundant Interlocks Ground Landing Gear COM N.O. Redundant Fail Drive COM N.O. Altitude Switch

  18. EIP Implementation • Solid State Power Controllers (SSPCs): • DC relay, over-current and arc-fault breaker in 1.5in3 • Trip state, voltage & current monitor • Low power dissipation: • Ron = 6mΩ @ 20A (120mW), no relay coil • Command relay inputs are opto-isolated (<20mA/input) • Fails to ‘open’ state • -55ºC to 85ºC operation • Surge tolerant (48V @ 1s, 80V @ 100ms) • Units for power circuits will be permanently ‘CLOSED’ • Status: Rev- testing in process

  19. EIP Implementation • DC Monitor Module: • Revised form factor of Global Hawk design • UDP Status Packet Contents: • Voltage & Current for each 15A DC circuit (not for high-power) • Trip status for all SSPCs • Interlock & Fail line status for each payload • (1) External temperature (AD5626) • Humidity • EIP Internal Health Temperatures • Status: Schematic Design • Legacy Module: • Patches Control/Data input to Legacy Output and Mission Critical Connectors • Leverages PCB solder-tail connector technology • Status: Schematic Design Analog Devices AC2626 Temperature Probe

  20. EIP Implementation • AC Distribution PCB (Rev A): • Layer Stackup (0.125” Thick): • Top: Shield • Inner 1-2: Ckts. 1 & 2 ФA • Inner 3: Shield • Inner 4-5: Ckts. 1 & 2 ФB • Inner 6: Shield • Inner 7-8: Ckts. 1 & 2 ФC • Inner 9: Shield • Inner 10: Circuit 1 Neutral • Inner 11: Shield • Inner 12: Circuit 2 Neutral • Bottom: Shield • Layer Spacing: 4.15 mils (min) • Max Electric Field: 120.4 V/mil • FR4 DBV: 1100V/mil • Status: Ready for Fabrication DBV – Dielectric Breakdown Voltage

  21. EIP Implementation • Ethernet Module: Sixnet APSwitch • 8x 100Mbit ports, 4x Gigabit ports • 1x 100Mbit port internal to EIP (use for monitor) • Interconnects: MIL-DTL-38999/III Quadrax • Part #: 25-8 D38999/III (8 quadrax inserts) • Status: Functional & environmental evaluation.

  22. NASDAT Implementation • NASDAT = DC-8 REVEAL + … • Aircraft Data Isolation Card • Isolation for RS-232, ARINC-429, MIL-STD-1553, IRIG-B, RS-422 • Analog Input Isolation Card • L1/L2/OmniStar GPS Support • COTS Enclosure • SIE 714/716 Series in ¾ ATR Short • Improved Thermal Management SIE 714 & 716 ATR Enclosures

  23. NASDAT Implementation NASDAT Functional Block Diagram:

  24. NASDAT Implementation • NASDAT J1: Isolated Inputs • ARINC-429 (4 channels) • MIL-STD-1553 (1 dual-redundant channel) • RS-232 (2 channels) • RS-422 (2 channels) • Analog (8 channels) • GPS antenna (loop-through via internal splitter) • Power 28VDC

  25. NASDAT Implementation • NASDAT J2: Outputs; Configuration • 5 buffered outputs to 4 pair each, selected from: • (Isolated) Inputs: ARINC-429, RS-232, RS-422 • NASDAT-generated: ARINC-429, RS-232, • RS-422, IRIG-B, PPS • 2 full RS-232 for external payload support instruments • 1 full RS-422 for external payload support instruments • Configuration jumpers • KVM • Access to signals is useful for maintenance

  26. NASDAT Implementation NASDAT J3: Ethernet I/O – Quadrax NASDAT J4: USB Disk – attached or remote Amphenol Rugged USB Keys & Box Connectors (mated) Amphenol Rugged USB Keys & Box Connectors (de-mated)

  27. NASDAT Implementation • NASDAT Standard Data Products: • IWG1-formatted 1 Hz Nav/Housekeeping Data • UDP broadcast to aircraft LAN • UDP telemetry to ground • File recorded on-board • NTP, IRIG-B • Instrument status packet telemetry and monitoring • Instrument ad-hoc low-rate C3 UDP telemetry • “Kitchen Sink” file of most available data at 1 Hz • “Dynamics” file of attitude/accels/rates at 20 Hz

  28. NASDAT Implementation • NASDAT Optional Data Products: • Higher rate data • Other formats or parameters easily configurable • Can read or drive external instruments if needed • Can repeat or generate various signals if needed • NASDAT Legacy Data Products • ER-2 Nav Format • ER-2 Time Format • DC-8 ASCII Format • RS-232, ARINC-429, IRIG-B outputs

  29. NASDAT Implementation • NASDAT Internal Sensors: • Cabin Temp • Cabin RH • Cabin Pressure • Input Volts and Amps • Internal Temps • High-Precision GPS Clock • Miniature GPS/IMU • OmniStar-Capable GPS

  30. NASDAT Implementation NASDAT Internal Configuration Options: • SIM cards for the four Iridium modems • Miniature GPS/IMU installed: LandMark20, MIDG-II, None • Omnistar VBS service activated • Dataforth 5B S/C modules for A/D inputs • Software baseline load per aircraft VBS – Virtual Base Station

  31. NASDAT Implementation • NASDAT Front Panel Contents • J1: Inputs • J2: Outputs and per-aircraft configuration • J3: Ethernet • J4: USB • J5, J6, J7, J8: Iridium TNC Coax • Lamps: 5V “CPU” & 28V “Power” • RH probe • Pressure transducer port • Klixon 5A C/B - input power disable • Switch, guarded - Iridium Radio disable • J-hooks for ATR mounting

  32. NASDAT Implementation • NASDAT Back Panel Contents: • Mating bushings for ATR mounting pins • GoreTex vents for pressure EQ • NASDAT Mounting Tray: • Standard ARINC-404A “ATR ¾ Short” • No vibration isolation necessary • May want fan under tray in E-Bay

  33. NASDAT Implementation • Prototype NASDAT Custom Cards: DATAFORTH CARD (Rev A) INPUT/OUTPUT ISOLATION CARD (Rev -)

  34. Network Implementation • Managed mesh w/ RSTP configured as 1G ring has two levels of fault tolerance: • Ring topology has built in redundancy • 1G over Cu = 2 quadrax (break one, down to 100Mbit) Image from Sixnet Ethertrak Software Users Manual RSTP – Rapid Spanning Tree Protocol – allows redundant connections in a managed network

  35. Network Implementation • Network impacts on system: • 1G ring means 4 quadrax / EIP & bulkheads • Cable: Tensolite NF24Q100 • Bulkheads: Amphenol TBD (19-18 pattern) • Ring network requires infrastructure power • 2 sets of 28VDC @ ~0.5A / EIP • Fused internally in each EIP • Spare pins available on control input harness

  36. Network Implementation • Worst-Case 1000BASE-T Cabling: • 2 Ethernet Switches, 4 ER-2 Bulkheads, all Tensolite NF24Q100 + Quadrax • TIA/AIA-568b (CAT6) vs. ER-2 Quadrax: • Conclusion: ER-2 IL meets worst-case CAT6 IL specification IL: Insertion Loss (i.e. attenuation)

  37. Control Implementation • Barebones Implementation (Now) • Low risk: Uses existing switch panel and wiring • Optimized Implementation (Later) • Uses Ethernet for indication and/or control • Requires additional electronics box to translate switches & lamp drives to/from network packets • (WB-57 only) FAIL => FAIL/STATUS • Logic Low: FAIL (red lamp on) • Logic High: RUNNING (red & blue lamps off) • Switching @ TBD kHz: STATUS (blue light on)

  38. Control Implementation BAREBONES OPTIMIZED #1 OPTIMIZED #2

  39. Test Plan • All unique designs will be qualification tested for vibration & thermal / altitude • Test procedures for each major assembly • EIP Test Bench • Developed for GLOPAC EIPs • Automated I/R/C “buzz-out” • Automated monitor calibration • DC & AC generators & loads I/R/C: Isolation / Resistance / Continuity test – finds unintended short or open circuits prior to first power -on

  40. Test Plan Ethernet switch integrated into EIP for WB/ER-2 Will need larger AC load (20kW) Will use 100A in-house TRU, not Champion Unit Need larger AC source; may have to go 60Hz

  41. Test Plan • Vibration – • Qualification Test per DRB 367-1100-121 (TBD) • 7.17grms, 3-axis,1 hour per axis • Fixture modification needed (new bolt pattern) • Thermal Altitude • Worst-case thermal & altitude combinations for pressurized and unpressurized areas • -55C -> 0C @ 70kft • 0C -> 45C @ 30kft • 0C -> 60C (TBD) @ sea level

  42. Test Plan May need to request waiver for infrastructure power cold start (TBD) Considering changing profile & dwell times to match DO-160F approach

  43. Schedule / Milestones • May 2010 – Materials funding issued • September 2010 – PDR • December 2010 – NASDAT Pre-Production • February 2011 – EIP Pre-Production • April 2011 – EIP & NASDAT Production • American Recovery and Reinvestment Act (ARRA) funds expire in June 2011

  44. Conclusion / Actions • The NASDAT, EIP, and associated hardware are ready for detailed design. • Review and record any actions flagged during the presentation.

  45. Payload Control System (NASDAT, EIP) ER-2 and WB-57 Implementation NASA ASF, 9/14/2010 (PRELIMINARY 09/08/10)

  46. Acronym List • Ω - Ohms • Ф – Phase • 1G – Gigabit Ethernet • A - Amperes • AC – Alternating Current • AIA – Aerospace Industries Association • ASF – Airborne Sensor Facility • ATR – Air Transport Rack • C – Celsius / Centigrade • CAT6 – Category 6 • CPU – Central Processing Unit • DC – Direct Current • EIP – Experimenter Interface Panel • GLOPAC – Global Hawk Pacific • GRIP – Genesis and Rapid Intensification Processes • HQ - Headquarters • Hz – Hertz • IP – Internet Protocol • IRIG – Inter-range Instrumentation Group • IRIG-B – IRIG Code B • I/R/C – Isolation , Resistance, Continuity • k – Kilo (thousand) • kHz - Kilohertz • ms - Millisecond • NASDAT - NASA Airborne Science Data Acquisition and Transmission unit • PDR – Preliminary Design Review • RSTP – Rapid Scanning Tree Protocol • S/C – Signal Conditioning • SAE – Society of Automotive Engineers • SSPC – Solid State Power Controller • SSR – Solid State Relay • TBD – To Be Determined • TCP – Transmission Control Protocol • TIA – Telecommunications Industry Association • uC – Microcontroller • UDP – User Datagram Protocol • uP – Microprocessor • VAC – Volts, AC • VDC – Volts, DC • V – Volts • W - Watts

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