In the last few decades, significant advancements have been made in determining the variation in the thrust acting on spacecraft by rocket engines during flight tests. The immediate estimation of thrust for aircraft and spacecraft in flight is commonly not considered feasible. The outcome of a thrust stand is to limit the test article while estimating a satisfactory number of forces to characterize the thrust vector. From the various force measurement methods, the axial force measurement technique is described. An axial force measurement is made with a single component measurement system. The magnitude and direction are estimated and the location is thought to be on the rocket motors centerline. This paper described the thrust stand design configuration factors which meet specific requirements for instance accuracy, ease of assembly, safety, and low-cost sensors. An overview of types of hardware systems, electronic systems, basic literature review, and practical consideration of axial thrust measurement technique is analyzed. This paper also comprises the comparison of a 2 thrust stand design for the solid and hybrid rocket motors based on structural stability and reducing vibrational effects.


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    Titel :

    Preliminary Design Approach for Sub-Scale Rocket Motor Thrust Stand


    Weitere Titelangaben:

    Lect.Notes Mechanical Engineering


    Beteiligte:
    Narendranth, S. (Herausgeber:in) / Mukunda, P. G. (Herausgeber:in) / Saha, U. K. (Herausgeber:in) / Shukla, Harshit (Autor:in) / Jain, Umang (Autor:in) / Kumar, Deepak (Autor:in)


    Erscheinungsdatum :

    25.05.2022


    Format / Umfang :

    17 pages





    Medientyp :

    Aufsatz/Kapitel (Buch)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




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