Preliminary Test PDF Stampa E-mail

Immagine1Immagine5The first test, designed to validate the choice of material identified for the "nose " of the capsule, which is the most thermally stressed section of the structure, were carried out in the hypersonic tunnel SPES Department of Aerospace Engineering, University Federico II of Naples (DIAS).
The two subsequent tests, both successfully conducted on January 20, 2011, which reproduced the environmental conditions encountered in the capsule during re-entry into the layers of the upper atmosphere and are made with the tunnel parameters listed below, have provided extremely positive and encouraging results the continuation of activities.
The test on the demonstrator IRENE capsule in hypersonic tunnel SCIROCCO PWT (Plasma Wind Tunnel) CIRA, is expected to close the program, between April and May of 2011.

 

 

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Test 1

System parameters:
• total mass flow rate: 0.5 g / s
• total specific enthalpy (nozzle exit): 8.5 MJ / kg
• Mach Number: 6
• Test duration: 270 sec
Operating conditions:
• Heat flow: 380 kW/m2
• Maximum temperature: 1350 ° C

Sample tested
• Material from the nose behind a hardener
ceramic material and a layer of thermal insulation


Test 2

  System parameters:
• total mass flow rate: 0.5 g / s
• total specific enthalpy (nozzle exit): 9.2 MJ / kg
• Mach Number of votes: 6
• Test duration: 270 sec
Operating conditions:
• Heat flow: 410 kW/m2
• Maximum temperature: 1370 ° C

Sample tested
• Material from the nose without protection

 

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Test 1 Results

No mechanical effect observed on the material;

Test 2 Results

Found a slight uneven wear and less than two tenths of a millimeter in the central part of the exposed surface heat flow.

Conclusions

These results bode well for the technological and functional tests on the model.
E 'significantly confirmed the design decision taken by the Consortium ALI seeking solutions focused on the use of low-cost materials "off the shelf", easy availability and workability.