PSI - Issue 53

Stefania Franchitti et al. / Procedia Structural Integrity 53 (2024) 397–406 Author name / Structural Integrity Procedia 00 (2019) 000 – 000

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Several tests have been performed to simulate the re-entry flight thermo-mechanical conditions and also to assess the reusability of the body flap support in sustaining more than one re-entry flight. The load envelope used within the test campaign is pictured in Fig. 9. Each test has been conducted applying the mechanical load and the thermal load together; in each load phase the force is kept constant while the thermal time-history follows the target one. K type thermocouple sensors have been used to measure the temperature at control point, on the metallic bearing, on the CMC breadboard and on the metallic outer attachment ring. Load cell installed at the actuator of the MTS System has been used for force measurements.

Fig. 9. Single Test Load Spectrum and temperature.

The Fig. 10 shows the sensors measurement of a one test performed, highlighting how the temperature of control point, on the bearing, has been always over the temperature target.

b

a

Fig. 10. Sensors measurement during the test (a) and picture of the prototype during the test (b).

At the end of the test campaign the prototype has successfully demonstrate to be able to withstand thermal and mechanical loads foreseen during a single re-entry flight highlighting moreover its capability to carry the loads derived from more than one re-entry flight without failure.