<inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML"><mrow><msup><mrow><mi>STAJe</mi></mrow><mrow><mo>−</mo></mrow></msup></mrow></math></inline-formula>: A Supersonic Flight Program <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML"><mrow><msup><mi>STAJe</mi><mo>−</mo></msup></mrow></math></inline-formula> 1 Payload Design and System Study

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${STAJe}^{-}$ : A Supersonic Flight Program ${STAJe}^{-}$ 1 Payload Design and System Study

Kunze, Jens / Vijay Shelar, Sampada / Paull, Allan

The ${STAJe}^{-}$ flight program is the latest implementation of a university-based supersonic and hypersonic flight-test program. In the first flight, which is the subject of this study, the focus is on evaluating the suitability of commercial off-the-shelf electronic hardware, additively manufactured internal payload structures, and a long-range communications technique in the challenging environment presented by flight at high supersonic Mach numbers. These items can significantly reduce the cost of a flight experiment, and thus lower the threshold for flight experimentation. The scientific objectives of this flight are to collect pressure and temperature data on the whole trajectory to compare to numerical models, to optically measure the temperature of composite fins mounted on the payload, and to eject the flight module from the rocket assembly and track its location for subsequent recovery. Design calculations for the tracking system are presented alongside experimental results from ground tests demonstrating the suitability of the system. Furthermore, a one-dimensional calculation of the external wall temperatures over the trajectory is presented, which shows that internal systems are sufficiently protected from the harsh environment. Although the materials are shown to be appropriate for the flight, a layer of cork will be added to parts of the payload to further reduce the chance of structural failure. In addition, it is shown that a pneumatic ejection system is suited to overcoming the drag forces on the front of the rocket to initiate separation.