Application of embedded bondline sensor technology to a nozzleless rocket motor
other
Stress and temperature at the bondline of a nozzleless solid rocket motor were measured during manufacturing and thermal cycling using bondline stress and temperature sensors embedded in the thermal insulation/liner layer. Results were cross checked with the prediction delivered by a Finite Element Model of the motor, using both a linear viscoelastic and a non-linear viscoelastic (Swanson et al.) constitutive model for the propellant and a hyperelastic formulation (Ogden) for the thermal insulation layer. The physical and mechanical properties of the materials constituting the grain, including the propellant, were characterised by performing an extensive test
programme. The conventional failure properties were also characterised.
At the end of the thermal cycling programme, a defined crack was applied, and the structural response of the cracked grain during thermal cycling was recorded. An algorithm to detect the presence of a crack was developed using sensors’ data. The structural response of the flawed motor was compared with predictions delivered by the FE model of the motor.
programme. The conventional failure properties were also characterised.
At the end of the thermal cycling programme, a defined crack was applied, and the structural response of the cracked grain during thermal cycling was recorded. An algorithm to detect the presence of a crack was developed using sensors’ data. The structural response of the flawed motor was compared with predictions delivered by the FE model of the motor.
TNO Identifier
183528
Source title
37th International Annual Conference of ICT, Karlsruhe, Germany, 27-30 June 2006
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