ARC jet test in support of flexible thermal protection system evaluation and development the scope of this task order is to evaluate ftps layups and materials at comparable or harsher simulated…

NASA Langley Research Center issued a delivery order to The Boeing Company on June 19, 2017, with a ceiling value of $558,048, under the Basic and Applied Aerospace Research and Technology (BAART) parent vehicle, for arc jet testing of flexible thermal protection system (FTPS) layups and materials under simulated atmospheric reentry flight conditions.

The order calls for evaluation of FTPS materials across three test conditions: heat flux entry conditions of 50 W/cm² (17–50 W/cm² range, 1.7–10 kPa pressure); 50–75 W/cm² (50–75 W/cm² range, 3–6 kPa); and 75–130 W/cm² (75–130 W/cm² range, 3–10 kPa). Testing is to be conducted over up to 10 weeks total test time at the test facility in Hazelwood, Missouri. The order is priced on a cost-plus-fixed-fee basis with no set-aside. Ultimate completion date is October 31, 2020.

Service Contract Inventory data shows FY2021 invoicing of $8 thousand across 61 contractor hours at a derived government-paid rate of $135.93 per hour, with no subcontractors reported.

ARC jet test in support of flexible thermal protection system evaluation and development the scope of this task order is to evaluate ftps layups and materials at comparable or harsher simulated atmospheric reentry flight conditions. Ftps materials and systems will be tested utilizing the test facility for up to 10 weeks of total test time at three specific test conditions that simulate relevant test environments.the objectives for this task order are as follows: objective one: evaluation of ftps layups and materials at flight-like conditions simulating a heat flux entry condition (square pulse or mission profile in stagnation or shear) of 50 w/CM2 (heat flux between 17 and 50 w/CM2, pressure between 1.7 and 10KPA). Objective two: evaluation of ftps layups and materials at flight-like conditions simulating a heat flux entry condition (square pulse or mission profile in stagnation or shear) of 50-75 w/CM2 (heat flux between 50 and 75 w/CM2, pressure between 3 and 6KPA). Objective three: evaluation of ftps layups and materials at flight-like conditions simulating a heat flux entry condition (square pulse or mission profile in stagnation or shear) of 75-130 w/CM2 (heat flux between 75 and 130 w/CM2, pressure between 3 and 10 KPA).