The complexity of bi-propellant rocket engines is well documented as it forms an inherent problemto the design of a rocket. Modern simulation tools such as Computational Fluid Dynamics (CFD)have allowed for the verification of the theoretical functionality of a design, as well as optimisationof the performance of the engine assembly. These methods are however not sufficient to fully verifythe functionality of an engine, nor are they sufficient to research the real-world behaviour thereof foracademic purposes. The use of a rocket test stand therefore proves to be crucial, in order to ensurethe functionality of an engine and to characterise its performance.

The conceptual design of a rocket test stand was undertaken, as an initial step towards the fullrealisation of the intended construction thereof. This ’development rig’ consists of two test cells,intended to support test articles rated for a maximum thrust of 35 kN each, being supplied by a jointpropellant supply. Four adjacent diagnostic rooms will additionally be housed in order to meet therequirements of the stakeholders and allow for high fidelity measurements of flow behaviour withincombustion. For this endeavour the conceptual design of the test site was laid out, with a focus on thefluid supply system. The baseline design will operate using propalox mixtures driven by a nitrogensystem, with an extended design being discussed for alternative fuel mixtures and supporting gasses infuture. Subsequently, the operational capability was discussed to give insight into the potential testswhich can be performed at this facility once it has undergone commissioning.