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acoustic, electromagnetic, etc.)
Acoustic Emission
Acellent Technologies
Desirable SHM Attributes
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 Physics-based material properties measurements to
 determine material state throughout life cycle – allow design
conservativeness to be minimized
 Intelligent structures (self-diagnostic, self-healing, health
monitoring & diagnostics, manufacturability w/sensors, etc.)
Leading to design optimization, weight saving, less fuel
consumption & environmental impact
SHM Outcomes
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 Develop and demonstrate SHM technologies that can be
used to monitor structural integrity in service conditions
with high reliability & durability.
 As in conventional NDT, a single technology will not be
suited for the entire range of applications, based on
different materials, component geometries and damage
scenarios.
 Diagnosis must have high reliability over the aircraft
lifetime, since un-justified maintenance actions are quite
costly to the operator and spurious warnings degrades
confidence in the system.
 Accuracy and reliability may even be more stringent, since
further optimization of structural design will rely on SHM
with better knowledge of actual flight loads & condition.
Challenges to SHM
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 Components shall qualified, as part of aircraft certification, meaning they
shall perform the specified function while withstanding the specified
environmental conditions.
 Include large variations of temperature, vibrations, impacts, Electro-
Magnetic Hazards, chemical fluids, etc… as per RTCA DO 160 and aircraft
integrator directives.
 Components qualification shall demonstrate that the system performs
reliably in the specified environmental conditions, in all the aircraft
operational conditions over it’s lifetime.
 Specific issues need to be considered particularly:
 Easy installation and application on surfaces
 Accuracy and reliability when used on painted surfaces
 No corrosive damage to surfaces where applied
 No delaminating between sensor and monitored structure
 Suitable for metal, composite, sandwich structures
 Suitable for various damage: cracks, corrosion, delamination, de-bonding…
 Clearly different requirements will apply onto the system components:
sensors, processors, computers, wiring, power supply, … depending on the
technologies, architecture and installation location retained.
 Micro-Nano-Technologies have the potential for supporting qualification
requirements and the SHM business case.
System Qualification
H. Speckmann, Materials & Processes - Testing Technology, Airbus
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Implementing SHM
 SHM is not a new concept - it is already implemented on military aircraft,
with a different rationale but some converging features.
 Still the constraints of airworthiness certification and the existing
cost/benefit have limited its introduction in commercial aviation
 There is currently no specific FAA or EASA policy on CBM for civil aircraft. However,
some guidance is provided in FAR-29 (FAA, 2003) on achieving maintenance or
airworthiness credits with HUMS that could be developed.
 US DoD stated the requirement to transition to a CBM program by the end of 2015.
 Confidence needs to be built that SHM will bring the expected benefits, while
maintaining or improving the safety and efficiency of modern aircraft – by
progressive introduction and proving the reliability & benefits.
 1st generation of SHM shall target maintenance cost reduction and
increased aircraft availability - technology will allow saving cost and time in
regulatory inspections.
 2nd and 3rd generations of SHM shall integrate a new certifiable design
philosophy and will permit weight reduction.
 Sensors and their local processors would be more integrated with microelectronics
allowing more decentralized architecture where local processors perform & record
the first level of SHM processing until transmission to the upper level processor.
H. Speckmann, Materials & Processes - Testing Technology, Airbus
23
 LAHMP Health Monitoring System F-15 Flight Tests
 In 2003, the Army awarded an SBIR Phase II contract to TRI/Austin to develop a
diagnostic/prognostic system that could monitor aircraft and rotorcraft structural
components in flight.
 focused on ruggedizing the system, optimizing performance, reducing power draw,
　
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