Radiation Environmental Modeling is crucial to proper predictive modeling and electronic response to the radiation environment. When compared to on-orbit data, CREME96 has been shown to be inaccurate in predicting the radiation environment. The NEDD bases much of its radiation environment data on CREME96 output. Close coordination and partnership with DoD radiation-hardened efforts will result in leveraged - not duplicated or independently developed - technology capabilities of: a) Radiation-hardened, reconfigurable FPGA-based electronics; and b) High Performance Processors (NOT duplication or independent development)

Adams, James H.

Cressler, John D.

Frazier, Donald O.

Johnson, Michael A.

Keys, Andrew S.

Kolawa, Elizabeth A.

Patrick, Marshall C.

Watson, Michael D.

NASA Technical Reports Server

https://ntrs.nasa.gov/search.jsp?R=20070037453 2019-08-30T02:04:32+00:00Z
• The Vision for Space
Exploration (VSE) directs
NASA to pursue a long-
term human and robotic
program to explore the
solar system.
• The VSE is based on the
following goals:
- Return the shuttle to flight
(following the Columbia
accident) and complete the
International Space Station
by 2010.
Develop a Crew Exploration
Vehicle, test by 2008, first
manned mission no later
than 2014.
- Return to the Moon as early
as 2015 and no later than
2020.
• Gain experience and
knowledge for human missions
to Mars.
• Increase the use of robotic
exploration to maximize our
understanding of the solar
system.
SPACE 2007 - 20 September 2007
• The Constellation Program consists of multiple projects,
jointly being developed to fulfill the goals of the VSE.
SPACE 2007 - 20 September 2007 3
Space Radiation
affects all spacecraft.
 0acecra eect °ncshave a long history of _ 1°1power resets, sating,
dueandto:Systemfailures I_ 1010[Trappe__dpr Oto_n_ ' r iT_a_npp_'_d_il:r_t__SnIs
• Long duration I05I° ______to __ Iex0 sures u,,r
.OooreOi  a ,e o,ar
proton activity, I
• Ambient galactic
cosmic ray 10 5
environment. 10" 4 10" 2 100 102 104
P:_rti_lm pn_rnv MP.V
SPACE 2007 - 20 September 2007 4
Multiple approaches may be employed (independently or in
combination) to protect electronic systems in the radiation
environment:
- Shielding,
- Mission Design (radiation avoidance),
- Radiation Hardening by Architecture,
• Commercial parts in redundant and duplicative configurations (Triple Module
Redundancy),
• Increases overhead in voting logic, power consumption, flight mass
• Multiple levels of redundancy implemented for tad-damage risk mitigation:
- Component level
- Board level
- Subsystem level
- Spacecraft level
- Radiation Hardening by Design,
• TMR strategies within the chip layout,
• designing dopant wells and isolation trenches into the chip layout,
• implementing error detecting and correction circuits, and
• device spacing and decoupling.
- Radiation Hardening by Process,
• Employ specific materials, processing techniques,
• Usually performed on dedicated rad-hard foundry fabrication lines.
SPACE 2007 - 20 September 2007 5
NASA spacecraft developers have defined a Radiation
Hardness Assurance (RHA) methodology process*,
In general, the process may be described by the following
steps:
- 1) define the radiation hazard,
- 2) evaluate the hazard,
- 3) define the requirements to be met by the spacecraft's electronics,
- 4) evaluate the electronics to be used,
- 5) engineer processes to mitigate hazard damage, and
- 6)iterate on the methodology, if and when necessary.
To promote the successful implementation of RHA for
Constellation (and other NASA) missions, the RHESE project
aims to deliver products that assist in mitigating the hazard
damage,
*LaBel, K. A., Johnson, A. H., Barth, J. L., Reed, R. A., and Barnes, C. E., "Emerging Radiation
Hardness Assurance(RHA) Issues: A NASA Approach for Space Flight Programs," IEEE Transactions
on Nuclear Science, Vol. 45, No. 6, Dec. 1998, pp. 2727-2736.
SPACE 2007 - 20 September 2007 6
The Radiat'on Hardened E ectron'cs for Space
Environments (RHESE) project ex3ands the curren
state-of-the-art in radiation-hardened electronics to develo
hic h oerformance devices robust enou; h to withstand the
demandng radiation and thermal conditions encountered
within the soace and lunar env=ronments.
The specific goals of the RHESE project are to foster technolog.y
development efforts in radiation-hardened electronics possessing
these associated capabilities:
- improved total ionization dose (TID) tolerance,
- reduced single event upset rates,
- increased threshold for single event latch-up,
- increased sustained processor performance,
- increased processor efficiency,
- increased speed of dynamic reconfigurability,
- reduced operating temperature range's lower bound,
- increased the available levels of redundancy and reconfigurability, and
- increased the reliability and accuracy of radiation effects modeling,
SPACE 2007 - 20 September 2007 7
• RHESE is a "requirements-pull" technology development effort.
RHESE is a "cross-cutting" technology, serving a broad base of multiple
project customers within Constellation.
- Every project requiring...
• operation inan extreme space environment,
• avionics, processors, automation, communications, etc.
... should include RHESE in its implementation trade space.
RHESE's products are developed in response to the needs and
requirements of multiple Constellation program elements, including:
- Ares V Crew LaunchVehicle,
- Orion Crew ExplorationVehicle's lunar capability,'
- Lunar Lander,
- Lunar Outpost,
- Surface Systems,
- Extra Vehicular Activity (EVA) elements,
- Future applicationsto Mars exploration architecture elements.
Constellation Program requirements for avionics and electronics continue
to evolve and become more defined.
RHESE will develop products per derived requirements based on the
Constellation Architecture's Level I and Level II requirements defined to
date.
SPACE 2007 - 20 September 2007 8
Specifically, the RHESE tasks are:
- Model of Radiation Effects on Electronics (MREE),
- Single Event Effects (SEE)Immune Reconfigurable Field
Programmable Gate Array (FPGA) (SIRF),
- Radiation Hardened High Performance Processors (HPP),
- Reconfigurable Computing (RC),
- Silicon-Germanium (SiGe) Integrated Electronics for Extreme
Environments.
SPACE 2007 - 20 September 2007 9
The Main Objective
- A computational tool to estimate radiation
effects in space in support of spacecraft design
• Total dose
• Single Event Effects
•" Secondary Objectives
- To provide a detailed description of the
radiation environment in support of radiation
health and instrument design
• In deep space
• Inside the magnetosphere
° Behind shielding
SPACE 2007 - 20 September 2007 10
f Devi.ce/Ctrcult/System_
CREME96
Integral over
path length
Distribution +
critical charge
MREE
GEO_I --g 2_SOLAHMIN_I O0/EILS.TFX
1 D -I
-_10 -I=
10-_
10 -le1o-..L ___'_._
1o -1 1o 0 to I 1o 8 1o a lO 4 lo 6
IQnetle En_ly (MeV/nuBl_n)
i0-_ _ ----_ ..........
_ 10.12 ] ....... _=., [
I
"15.t _
t0 -_ 10-_ 10_ 10_
Energy (MeV)
Multi-volume Calorimetry +
Charge-collection models +
Critical charge
SPACE 2007 - 20 September 2007 11
• Reconfigurable gate arrays form the basis of many adaptable,
scaleable, computing engines
- Add flexibility, capability and robustness to surface and flight systems
; L:J-~t .. 7 .•~
SPACE 2007 - 20 September 2007 12
• 5th generation Virtex™ device
- 90 nm process
- 11 metal layers
- Up to 8M gates
• Columnar Architecture enables
resource "dial-in" of
Logic
- Block RAM
- 110
- DSP Slices
- PowerPC Cores
Fabrication process and device architecture
yield a high speed, flexible component
SPACE 2007 - 20 September 2007 13
Existing reconfigurable FPGAs are very susceptible to radiation-
induced single event effects
- Significant FPGA resources are currently required to mitigate radiation-
induced single event effects
0
E
0
E
Rad_usceptible
User invoked TRM required
(requires FPGA resources)
€_
o
0
t'-
t-
O
(1)
LL
tY
c/)
BB - Logic function
SlRF Fabric
Mitigation implemented at device level
Objectives: Eliminate need for user-invoked TMR. Bring a state-of-the-art radiation
hardened reconfigurable FPGA to the space electronics market by ~2010.
SPACE 2007 - 20 September 2007 14
Problem: Exploration Systems Missions
Directorate objectives and strategies
can be constrained by computing
capabilities and power efficiencies
- Autonomous landing and hazard
avoidance systems
- Autonomous vehicle operations
- Autonomous rendezvous and docking
- Vision systems
P
SPACE 2007 - 20 September 2007 15
16
PDR Dates
2020
LSAM
Lander
; ,
i ~; ,
, I'..
: Lunar'. Lunar
; EVA '. Outposts
2010
CEV
Block II
2000
~.-- -10 yrs. ---+:
I .
1.. R6COO
.. Mongoose V
\.
i
r :
!
Year
1990
• 803880X
• 80286
1980
•
1970
• Commercial Processor
.. Radiation-hardened processor
Cole 2
1E4
0.1
2000 ----
1000
Radiation-hardened processors lag commercial devices by several technology generations
(approx. 10 years)
RHESE High performance Processor project full-success metric for general purpose processors
conservatively keeps pace with historical trend (-Moore's Law)
-:::Ja.
s:.
C)
:::J 100
e---s:.(/)
1-9:
~~0 .......
en
en 10CIlCJ
e
Q.
1.0
SPACE 2007 - 20 September 2007
• Subproject Objectives
• Provide reconfigurable computing capabilities as a preferred alternative to
conventional forms
- Processor Modularity
- Interface Modularity
• Reduction of Flight Spares
• Accommodation for Circuit Life Limitations
• Resources where needed, as needed
• Supplement other efforts to mitigate environmental impacts by providing the
capability to detect and work around malfunctioning circuitry
- Fault Tolerance
- Fault Detection, Isolation, and Mitigation
•
• Generally: capitalize on the unique capabilities of RC to adapt in target
systems for changing requirements, performance and environmental
parameters
SPACE 2007 - 20 September 2007 17
Flight-Qualified, Multi-String Redundant Hardware is Expensive
- Development, Integration, IV&V, and Flight Qualification
- Space and Weight
- Power Consumption and Cooling
Custom Design of Computing Resources for Every New Flight System
or Subsystem is Unnecessary and Wasteful
Requirements for Flexibility are Increasing and Make Sense
- Reconfigurable (Flexible) and Modular Capabilities
- For Dissimilar Spares, and Incremental Changeover to New Technology:
Capacity to use one system to back up any number of others
- General Reusability
Current Options for Harsh/Flight Environment Systems are Limited
- Custom Hardware, Firmware, and Software
- Dedicated and Inflexible
- Often Proprietary: Collaboration Inhibited
Modular Spares == Fewer Flight Spares
SPACE 2007 - 20 September 2007 18
The Moon: A Classic Extreme Environment!
Extreme Temperature Ranges:
• +120C to -180C (300C T swings!)
• 28 day cycles
• -230C in shadowed polar craters
Radiation:
• 100 krad over 10 years
• single event effects (SEE)
• solar events
Man'l Different Circuit Needs:
• digital building blocks
• analog building blocks
• data conversion (ADC/DAC)
• RF communications
• actuation and control
• sensors / sensor interfaces
-. !:li9hly Mixed-Signal Flavor
SPACE 2007 - 20 September 2007
Current Rovers I Robotics
Requires "Warm Box"
19
• SiGe HBT + CMOS + full suite of passives (Integration)
• 100% Si Manufacturing Compatibility (MOSIS Foundry)
• Wide-Temperature Capable + Radiation Tolerant
SPACE 2007 - 20 September 2007 20
REUin
connector
housing!
Digital
control die
Analog front
end die
Our Project End Game:
The SiGe ETDP Remote
Electronics Unit, circa 2009
Conceptual integrated REU
system-on-chip SiGe BiCMOS die
Our Goals
• 1.5" high by 1.5" wide by 0.5"
long = 1.1 cubic inches
• < 1 kg
• < 1-2 Watts
... -180°C to +125°C, rad tolerant!
The X-33 Remote Health
Monitoring Node,
circa 1998
(BAE)
~ecifications
• 5" wide by 3" high by 6.75"
long = 101 cubic inches
• 11 kg weight
• 17.2 Watts power dissipation
• -55°C to +125°C
SUQ.ports MANY Sensor Types:
Temperature, Strain, Pressure, Acceleration, Vibration, Heat Flux, Position, etc.
Use This REU as a Remote Vehicle Health Monitoring Node
SPACE 2007 - 20 September 2007 21
All RHESE tasks are "reqUirenlen,t~~~~~~11
pulled" by specific CARD
requirements, LAT technology
needs, and surface systems' def
environments.
An application-dependent trade spa:~~~,~t:"l";;
is definedby:'""'''' .~~~'
- Radiation Hardening by Architecture
using COTS processors, and
- Radiation Hardening By Design using
Rad-Hard processors. ;;;,;,;,
Considerations include performanc~:":
requirements, power efficiency, des,!gn
complexity, radiation '"
Radiation and low temperature
environments currently drive spacecraft
system architectures.
- Centralized systems to keep
electronics warm are costly, weighty
and use excessive cable lengths.
Mitigation can be achieved byactiv
SiGe electronics.
SPACE 2007 - 20 September 2007
SPACE 2007 - 20 September 2007 23
Radiation Environmental Modeling is
crucial to proper predictive modeling
and electronic response to the
radiation environment.
- When compared to on-orbit data,
CREME96 has been shown to be
inaccurate in predicting the radiation
environment.
The NEDD bases much of its radiation
environment data on CREME96 output.
Close coordination and partnership with
DoD radiation-hardened efforts will resu
in leveraged - not duplicated or
independently developed - technology
capabilities of:
- Radiation-hardened, reconfigurable FPGA-
based electronics,
- High Performance Processors (NOT
duplication or independent development). • -.J.,.~ ,
'-----------------------,:~


Radiation Hardened Electronics for Space Environments (RHESE)

Radiation Hardened Electronics for Space Environments (RHESE)

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