Conceptual Design Solid Rocket Motor For Mars Ascent Vehicle Based On Volume & Mass Reduction

This paper has discussed a conceptual design of a solid rocket motor for use in a Mars ascent vehicle. In the modern technologies of solid rocket motor manufacturing, composite materials are used to reduce the rocket motor mass. So has built the motor case from composite fibers. In the design process, average thrust, average chamber pressure, burning time, nozzle expansion rate, and specific impulse; were used as input parameters. The design will be based on the Star۱۷ engine used in the second stage of the MAV. According to the specifications Star ۱۷ motor, restrictions; The maximum motor diameter, motor length, motor total mass, and the ratio of dry mass to total mass are considered in the design process to reduce the mass and volume of the motor. Based on input parameters and using equations, mass and dimensional specifications of motor, like components; The dimensions and mass of the nozzle, insulation mass, propellant mass, ignition mass, etc. will be obtained. In the following, by comparing the designed motor and the Star ۱۷ motor, the results of the new motor design will be obtained and the number of changes will be examined.

کلیدواژه ها:

Ascent vehicle ، Composite ، Mars ، Solid propellant ، Solid rocket motor