Data acquisition unit for suborbital rocket vibration measurement

Abstract Suborbital rockets and space launch vehicles experience high levels of vibration. They are caused by various factors, such as aerodynamic effects on the external surfaces engine combustion instability. The second factor is especially pronounced in hybrid rocket engines, main ILR-33 AMBER 2K rocket. In order to ensure correct operation all equipment payload board, vibration testing devices necessary part pre-flight qualification. For tests be truly indicative in-flight performance, environment vehicle must analysed. A conceptual measurement method was proposed, along with a prototype system. system adapted integrated into modular on-board computer or work independently separate module. device measures three axes several key points onboard rocket, possibility connecting multiple units daisy-chain configuration. This paper presents design module, including aspects integrating it avionics package. means acquiring storing data presented. validating system’s acquisition capabilities described detail. Qualification results identified issues discussed. Possible future improvements proposed.