nication. According to this, it can be seen as a low
level interface to the legacy embedded systems.
The physical interface controller includes a sub-
set of common ready-to-use interfaces as: ETH, SPI,
I2C, etc.
3.1.2 Coordination Module
The coordination module is composed by a proces-
sor running some balancing algorithms and safety al-
gorithms and by several specific processing blocks,
e.g. cryptography. Albeit, it is possible to execute the
same process on a softcore processor, the current so-
lution relies on a dual core microprocessor. The pro-
cessor will be in charge to manage the node resources
allocation and to balance services with the aim to en-
sure the system reliability with a dynamic load distri-
bution.
3.1.3 Security Module
The component identified as DRM (Dynamic Recon-
figuration Module) is in charge of managing the re-
configuration of the processing blocks and software
modules based on the system context and status. The
purpose of this functional block is to increase security
and dependability aspects of the node allowing the de-
vice to switch between different operational modes.
Furthermore this module allows to run multiple ap-
plications on the same device enhancing the depend-
ability and redundancy.
nS-ESD-GW architecture includes a Data In-
tegrity controller to process data by implementing
cyclic redundancy check. In conjunction with a En-
crypt/Decrypt controller it will be possible to ensure a
long term storage of sensitive data improving security
aspects of the node. Cryptographic algorithms impose
tremendous processing power demands that can be a
bottleneck in high speed and real time networks. To
follow the variety and the rapid changes in algorithms
and standards, a cryptographic implementation must
also support different algorithms and should be up-
gradeable in field. For all these reasons, a reconfig-
urable/upgradable FPGA based HW accelerator will
provide software-like flexibility with hardware-like
performances. The Fault Detection module will en-
compass the nSHIELD and application domain spe-
cific fault detection algorithms.
3.2 Application Scenario
To verify the validness of the framework and its com-
ponents, an avionic demonstrator has been employed.
Due to framework complexity and to its large amount
of features, this demonstrator is not enough to ver-
ify all of its features. Therefore the demonstrator is
focused on some of them and more in detail on veri-
fying the following concepts:
• Dynamic composability;
• Fault detection and recovery;
• SPD Interoperability and Integration of heteroge-
neous system.
An avionic system is a critical or even life-critical
one, for these reasons keeping it in fully operational
status is of vital importance. To mitigate effects, such
as loss of services or loss of lives, caused by failure of
system components, the system redundancy is com-
monplace in the avionic field. In this way, in the oc-
currence of a fault, spare parts can substitute damaged
ones. In such a context we employ system supervisor
based on nSHIELD methodologies, that is capable to
identify and recover a fault by means of composabil-
ity. At the heart of the chosen avionic application sce-
nario there is the Unmanned Aerial Vehicle (UAV),
a system composed by an aircraft controlled by a pi-
lot located on the ground, through a remote control
unit. Our target is to keep constant the level of safety
of the overall mission through the cooperation of het-
erogeneous tools and related technologies, in order to
protect staff and aircrafts from accidental and/or ma-
licious harm, crime and any other possible threat. In
order to achieve our goal, we can identify some criti-
cal issues:
• difficulties to coordinate heterogeneous systems
to achieve an appropriate level of security;
• difficulties to reassemble the system and to react
to a non-predictable and known events;
• difficulties to react promptly to threats based on
context changing.
The avionic scenario refers to an UAV flock
flight mission. The main actors of the scenario are:
two UAVs (scaled down to the Integrated Modular
Avionic (IMA) systems), the nS-ESD-GW gateway,
a Software Defined Radio (SDR), a GPS sensor board
and a Remote Control Unit (RCU). In the course of
an UAV flock flight mission, where the adequate level
of security is kept due to the coordination between the
RCU and the UAV, two events of failure will be tack-
led: a fault solved at UAV’s system level, and a fault
settled at system of systems level.
With the aim to demonstrate the fault detection
and the system dynamic reconfigurability, an initial
configuration of the scenario is made up of a single
UAV and its RCU. During a normal operational sta-
tus, the first fault occurs: suddenly the GPS position-
ing module experiences a failure. When this event
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