Design optimization of micro air launch vehicle using differential evolution

Abstract

In this paper, we have used the differential evolution to optimize the design of a Micro Air Launch Vehicle and its launch trajectory. Since trajectory design of a launch vehicle requires prior knowledge of the masses and propulsion performance parameters of the Micro Air Launch Vehicle, whereas the vehicle design requires prior knowledge of the required velocity V to insert the required payload into the target orbit, a two step optimization cycle was adopted. A Micro Air Launch Vehicle was designed to launch a 20 kg payload into a 00 km circular polar orbit. The preliminary design of the Micro Air Launch Vehicle was conducted given the required V, which was obtained from trajectory optimization, and then applied in mission analysis to obtain the initial masses. These initial masses were used in the vehicle design to get the performance and geometry parameters. The objective function of the Micro Air Launch Vehicle design optimization is to minimize the initial mass under speci ed constraints on the insertion orbit. The objective of trajectory optimization is to maximize the payload mass under constraints on orbit speci cations and design variables. For the 20 kg payload mass, the optimal initial mass is 1267.8 kg and optimal payload is 20.6 kg, which slightly exceeds the mission requirements.

Effect of Varying Design Options on the Transient Behavior of a Hybrid Rocket Motor

“…Th e sizing of the overall propulsion system needs the initial mass and total ΔV. For the mission selected here, the mission analysis of the micro air launch vehicle gives a total initial mass of 1,287.34 kg and ΔV of 2,624 m/s (Aldheeb et al, 2012). Th ese values are used to calculate the fi nal mass, propellant mass, fuel mass and fuel mass fl ux of the hybrid rocket stage using the following relations: 5where m fi nal is the fi nal mass (kg) and m initial is the initial mass (kg).…”

Multi-Disciplinary System Design Optimization of a Launch Vehicle Upper-Stage

“…The need to design with a systematic approach in addition to design implementation based on physics of an aerospace product attracts some researchers to optimized systematic design. Aldheeb et al (2012) tried to create an optimized design for a Micro Air Launch Vehicle.…”