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Development of a Solid Propellant Rocket in the Frame of the Cabo Tuna Mexican Program

Abstract

This work presents the experimental results of launching of Fénix I-2 “Alejandro Pedroza Meléndez” (F2APM), a Mexican manufacture single-stage solid propellant rocket motor from Cabo Tuna Range in Charcas, San Luis Potosí, México. The solid fuel sounding rocket motor was KN-Sorbitol propellant type. The rocket performed its flight at perfect weather and visibility conditions, reaching a maximum altitude of about 6 000 m. Engine and flight trajectory showed very good agreement with the theoretical data measurement obtained from captive-fired experiment. At burnt-out, locked-in resonance increased drag limiting the maximum vertical reach.

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Data Availability

The data used to support the findings of this study are available from the corresponding author upon request.

Abbreviations

Isp:

Specific impulse, N s/Kg

Vbo:

Burnout velocity, m/s

Mo:

Total weight, Kg

Mbo:

Rocket weight at burnout, Kg

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Correspondence to J. R. Martínez.

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Saucedo-Zárate, G., Arauz-Lara, J.L., de la Cruz-Mendoza, J.A. et al. Development of a Solid Propellant Rocket in the Frame of the Cabo Tuna Mexican Program. Aerotec. Missili Spaz. 101, 135–141 (2022). https://doi.org/10.1007/s42496-022-00115-8

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  • DOI: https://doi.org/10.1007/s42496-022-00115-8

Keywords

  • Rocket motor
  • Static-fired
  • Ballistic evaluation
  • Launched rocket
  • Qualitative evaluation