What question did this study set out to answer?

To establish a conceptual and computational framework for evaluating solid-propellant propulsion performance, maneuver durations, and mass requirements in small-satellite missions.

August 19, 2026Open Access

Conceptual Performance Analysis of Solid-Propellant Propulsion for Small Satellites

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To establish a conceptual and computational framework for evaluating solid-propellant propulsion performance, maneuver durations, and mass requirements in small-satellite missions.
Combined the rocket thrust equation, specific impulse, total impulse, and the ideal rocket equation into an analytical framework.
Conducted a parametric analysis using representative non-experimental propulsion parameters across variations in thrust, specific impulse, mass ratio, and required velocity change.
Increasing specific impulse directly reduces the ideal propellant mass needed to achieve a specified velocity change.
Increasing thrust decreases maneuver duration by delivering the required total impulse more rapidly.
Mission analysis identifies operational constraints unique to solid propulsion, including lack of restart capability, structural and thermal loads, and integration safety requirements.

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Implication

Parametric modeling demonstrates trade-offs between thrust, specific impulse, and mass in small satellites, highlighting design limits for solid-propellant propulsion.

Cite This Study

Olimbek Kubayev (2026) studied this question.

synapsesocial.com/papers/6a85642503308d306e2d7b6e https://doi.org/10.5281/zenodo.21983922

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Implication

Parametric modeling demonstrates trade-offs between thrust, specific impulse, and mass in small satellites, highlighting design limits for solid-propellant propulsion.

Conceptual Performance Analysis of Solid-Propellant Propulsion for Small Satellites

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Discussion

Implication

Cite This Study

Conceptual Performance Analysis of Solid-Propellant Propulsion for Small Satellites

Key Points

Discussion

Implication

Cite This Study

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