Traditional approaches for predicting the apogee of a sounding rocket rely on running numerous simulations using complex aerospace software. These simulations require significant computational resources, making the design process time-consuming and inefficient. Additionally, repeated testing increases redundancy, limiting the speed of optimisation for future rocket designs. To address this, we propose a Fuzzy Inference System (FIS)-based model, leveraging fuzzy sets to predict a sounding rocket’s apogee based on input parameters, such as mass, impulse, wind speed, and engine burn time. Integrating Fuzzy logic into the design process minimises computational and material redundancy while improving design efficiency. Fuzzy logic is employed to handle uncertainties in real-world launch conditions, improving prediction reliability. The Fuzzy rules are defined as per simulation data from OpenRocket, reducing the need for repeated computationally expensive simulations. Experimental validation of metrics like the desired apogee demonstrates that the approach achieves high accuracy, optimizing the design process while maintaining computational efficiency. This approach enhances early-stage rocket design by providing rapid and reliable apogee predictions, by also considering wind speed as a parameter, applicable to sounding rockets.


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    Titel :

    Fuzzy Logic-based Apogee Prediction for Sounding Rockets


    Beteiligte:
    Purohit, Eishani (Autor:in) / L, Agilandeeswari (Autor:in) / M, Prabukumar (Autor:in)


    Erscheinungsdatum :

    13.06.2025


    Format / Umfang :

    371752 byte




    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch





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