This paper describes an effort to optimize the design of an entire space launch vehicle to low Earth (circular) orbit, consisting of multiple stages using a genetic algorithm with the goal of minimizing vehicle weight and ultimately vehicle cost. The entire launch vehicle system is analyzed using various multistage configurations to reach low Earth orbit. Specifically, three-and four-stage solid propellant vehicles have been analyzed. The vehicle performance modeling requires that analysis from four separate disciplines be integrated into the design optimization process. The disciplines of propulsion characteristics, aerodynamics, mass properties, and flight dynamics have been integrated to produce a high-fidelity system model of the entire vehicle. In addition, the system model has been validated using the existing launch vehicle data. The cost model is mass based and uses extensive historical data to produce a cost estimating relationship for a solid propellant vehicle. For the design optimization, the goal is for the genetic algorithm to minimize the differences between the desired and actual orbital parameters. This ensures that the payload achieves the desired orbit. One final goal is to minimize the overall vehicle mass, thus minimizing the system cost per launch. This paper will represent the first effort of its kind to minimize the solid propellant launch vehicle cost at the preliminary design level using a genetic algorithm.

This paper describes an effort to optimize the design of an entire space launch vehicle to low-Earth (circular) orbit, consisting of multiple stages using a genetic algorithm (GA) with the goal of minimizing vehicle weight and ultimately vehicle cost. The entire launch vehicle system is analyzed using various multistage configurations to reach low-Earth orbit. Specifically, three and four-stage solid propellant vehicles have been analyzed. The vehicle performance modeling requires that analysis from four separate disciplines be integrated into the design optimization process. The disciplines of propulsion characteristics, aerodynamics, mass properties and flight dynamics have been integrated to produce a high fidelity system model of the entire vehicle. In addition, the system model has been validated using existing launch vehicle data. The cost model is mass-based and uses extensive historical data to produce a cost estimating relationship for a solid propellant vehicle. For the design optimization, the goals of the problem are for the GA to minimize the differences between the desired and actual orbital parameters. This ensures the payload achieves the desired orbit. One final goal is to minimize the overall vehicle mass thus minimizing the system cost per launch. The paper will represent the first effort of its kind to minimize solid propellant launch vehicle cost at the preliminary design level using a GA.

This paper describes an effort to optimize liquid-fueled space launch vehicles for minimum cost. The entire launch vehicle is modeled to achieve a low-Earth (circular) orbit using multiple stages. The optimization scheme employs a genetic algorithm (GA) with the goals of minimizing both vehicle weight and vehicle cost per launch. Two and three-stage liquid propellant launch vehicles have been analyzed. In addition, results from an air-launched, two-stage liquid propellant launch vehicle are presented. The vehicle performance modeling requires that analysis from four separate disciplines be integrated into the design optimization process. Modeling of propulsion systems, aerodynamics, mass properties and flight dynamics have been integrated to produce a high fidelity system model of the entire vehicle. An existing, two-stage liquid propellant launch vehicle has been used to validate the two-stage liquid propellant system model. The cost model is mass-based and uses extensive historical data to produce a cost estimating relationship for a liquid propellant vehicle. For the design optimization, the primary goal is for the GA to minimize the differences between the desired and actual orbital parameters. This ensures the payload achieves the desired orbit. The third goal is to minimize total launch vehicle mass and system cost per launch.

The paper describes overall experience and lessons learned from the USAF Academy's small satellite research program-"FalconSAT"-and the challenges faced by undertaking serious space mission development in a highly-constrained undergraduate environment. The goal of the program is to give students the opportunity to "learn space by doing space." Background on the program is first presented including successes and failures since the program's inception. Discussion begins by focusing on specific curriculum changes made within the Academy Department of Astronautics over the last several years to enable students to have even 5 hours per week to devote to space mission development. The culmination of this curriculum is a capstone small satellite design course sequence. The processes within these courses will be described along with how the courses are organized to get the maximum amount of learning and effort out of the students given the limited class time available. Various aspects of the courses will be discussed such as the Design Review Process and how cooperation with other departments and organizations help to provide expertise and extra funding. Challenges associated with these courses and the associated project that the students are expected to complete are also discussed. How are student learning objectives and real world deadlines balanced? How is the problem of high student turnaround handled? The paper will discuss various solutions the Academy has evolved to address these challenges. The paper concludes with current program status and recent feedback from students involved in the project.

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