Space Core
Menu

ENES, Cambiar a español

Space Core

Lammar-HR-L3

High performance · Space applications

Radiation-hardened LEON3-FT single-board computer for mission management, navigation and payload processing on LEO, MEO and GEO satellites.

Download PDF

Applications

  • Mission management computer for LEO and MEO
  • Navigation computer for LEO and MEO
  • Payload computer for LEO, MEO and GEO

Compliant with

  • NASA standards
  • ECSS standards, including Q-ST and E-ST
  • MIL-STD-810
  • MIL-STD-4161E

Highlights

  • Ready to fly and customizable for the mission configuration.
  • Engineering model (EM) for software development and flight model (FM) for qualification.
Connector face of the Lammar-HR-L3 onboard computer.

Overview

  • Single +5V external input voltage.
  • High-performance rad-hard components.
  • Board size 150 × 155 × 15 mm.
  • Three micro-DB9 and three high-density D-subminiature connectors for the external interfaces.
Lammar-HR-L3 processor, memory and supervision features.

Main features

  • One dual-core LEON3-FT SPARC V8 compliant 32-bit processor.
  • One 32K × 8-bit PROM memory.
  • Two 8M × 8-bit flash memories.
  • One 4M × 39-bit SRAM memory (32 data bits plus 7 bits for EDAC).
  • One 64M × 48-bit SDRAM memory (32 data bits plus 16 bits for Reed-Solomon EDAC).
  • Power supervisory circuit to monitor the supply voltages and protect the CPU.
  • Watchdog that resets the computer automatically if the software fails.
  • Triple hardware rescue if the software fails.
External interfaces of the Lammar-HR-L3 onboard computer.

Interfaces

  • Four RS-422 full-duplex ports.
  • Two SpaceWire ports.
  • Two CAN 2.0 buses.
  • SPI / I2C.
  • Eight general-purpose inputs and eight general-purpose outputs.
  • One telemetry / telecommand (TM/TC) RS-422 port.
  • Pulse-per-second: two input and two output RS-422 ports.
  • One JTAG interface for programming and debugging.
Lammar-HR-L3 flight enclosure.

Environment and construction

Figures below are taken from the product brochure and describe the interface components and the mechanical design. They do not replace a mission-specific radiation analysis.

  • RS-422 components: total dose 300 krad(Si) maximum, SEU LET 100 MeV/mg/cm², single-event latch-up immune.
  • SpaceWire: compatible with IEEE 1596.3 SCI LVDS and ANSI/TIA/EIA-644. TID greater than 100 krad(Si). SEL greater than 80 MeV·cm²/mg.
  • CAN 2.0: SEE immune to LET 86 MeV·cm²/mg. High and low dose rate 100 krad(Si).
  • Temperature range −55 °C to +125 °C.
  • Enclosure in aluminum 6061-T6, hardware per ECSS-Q-ST-70. Screws, bolts and washers in titanium. Gears and shafts in stainless steel AISI 304, bronze and PEEK. Surface finish shielded to mitigate radiation effects on the electronics.