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IntroductionThe preliminary design data for the Juno rocket motor is presented in this web page. This motor, powered by the KN-Dextrose propellant, has a predicted total impulse of 885 N-sec, which categorizes it as a mid "J" class motor. This intended purpose of this rocket motor is to serve as a "booster", or first stage motor, of the two stage Cirrus Two rocket, which is currently in the design phase. This rocket has an apogee target of 20,000 feet (6 km), and will utilize an "L" class Lambda rocket motor as the second stage sustainer.
As a booster, the Juno rocket motor is designed to have a short burn, high thrust operation, which will provide the rocket vehicle with a rapid climb off the launch pad, and achieve ample velocity to ensure a stable vertical attitude for second stage firing. To deliver the desired thrust profile, the motor utilizes a single hollow cylindrical grain of approximately 650 grams (1.4 lbs) mass, with unrestricted burning. As such, the burning surfaces consist of the core, outer grain surface, and both ends, resulting in a slightly regressive theoretical thrust profile. |
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The following images are excerpts from the SRM_beta Excel spreadsheet that was utilized in the design of the motor: ![]()
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