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of a sensor. The working is based on the differential pressures contained in the air and vacuum galleries. The complete set-up is
placed over the body structure where the crack is likely to occur.
Picture 1 – System diagram of CVMTM sensor
Source: company
The galleries and sensors are designed in a way that when the aircraft body structure is intact, there is no differential pressure
air flow between the air galleries and vacuum galleries. Thus, no signal is sent through the pressure flow meter to the sensor
validating proper working of the component, while the SHM process enhances operational efficiency.
© Khandaker Partners. All rights reserved. The information and data contained herein is not warranted or represented to be accurate and complete.
This report is intended for U.S. residents and for information purposes only and should not be considered as advice or solicitation to buy or sell any
Security.
Picture 2 – CVMTM system installed on an intact component
Source: company
If a crack develops on the surface of an aircraft, the differential pressure between the galleries leads to the air flow from air
galleries to vacuum galleries through the crack. The transducer monitoring the sensor detects the air flow and in-turn provides
feedback to the software management system, which reports the development of a crack. The rate of air flow provides an
indication of the size of the crack (as demonstrated in the figure below).
© Khandaker Partners. All rights reserved. The information and data contained herein is not warranted or represented to be accurate and complete.
This report is intended for U.S. residents and for information purposes only and should not be considered as advice or solicitation to buy or sell any
Security.
Picture 3 – CVMTM system installed on a damaged component
Source: company
CVMTM Technology Applications
Commercial and military aerospace operations offer a vast arena for the company’s CVMTM technology-based SHM products.
SMS has successfully developed monitoring devices providing continuous and periodic monitoring applications for an aircraft
through the use of sensors and software systems. These applications enable scheduled maintenance tasks to be conducted and
check the crack formation on the body surface due to over fatigue.
SMS has conducted widespread research to support the technology base and developed a diverse category of sensors and
associated testing systems. A typical CVMTM based SHM system consists of the following four main components:
A sensor applied to the area requiring testing or inspection,
A vacuum source to control and apply partial vacuum to the sensor,
A differential pressure flow meter device with output options that interface with the control systems; and
A software management system that processes the data.
The traditional aircraft inspection methods that were used to check functionality and safety of the aircraft were time consuming
and expensive. As a result, aircraft were idle and this reduced operational efficiency. The customary inspection tools and
processes were not effective in terms of improving the turnaround time and returning the aircraft to service. SMS has developed
a monitoring system that can be built into the airframe at the time of manufacturing. The system is expected to be efficient and
offer attractive benefits.
Structural Monitoring
Continuous monitoring of probable fatigue critical areas on the surface of an aircraft is done through a simple self contained
CVMTM switch monitoring pack. Low power consumption enables supply of solar panels and an integral transmitter transmits
signals from the remote areas to a control centre if and when a crack occurs. This assists in reducing downtime, and thereby,
increases the safety and maintenance activities. Self-adhesive CVMTM sensors are attached to the area with high probability of
crack formation and are monitored during fatigue testing via CVMTM Switches. An alarm is triggered immediately when a
crack breaches the sensor. In addition, a built-in relay can stop the test if desired. Multiple sensors can be monitored through
multiple switches or cracks can be monitored through multi-channel sensors.
© Khandaker Partners. All rights reserved. The information and data contained herein is not warranted or represented to be accurate and complete.
This report is intended for U.S. residents and for information purposes only and should not be considered as advice or solicitation to buy or sell any
Security.
Picture 4 – The PM200 and CVMTM Switch Monitoring Products
Source: company
Periodic monitoring also requires permanent installation of the CVMTM sensors on an aircraft structure. This provides an
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