Co-Authors:
Dagan, O., Faculty of Aerospace Engineering, Technion - Israel Institute of Technology, Haifa, Israel
Geva, A., Faculty of Aerospace Engineering, Technion - Israel Institute of Technology, Haifa, Israel
Lavi, L., Faculty of Aerospace Engineering, Technion - Israel Institute of Technology, Haifa, Israel
Raviv, M., Faculty of Aerospace Engineering, Technion - Israel Institute of Technology, Haifa, Israel
Shaki, J., Faculty of Aerospace Engineering, Technion - Israel Institute of Technology, Haifa, Israel
Spector, I., Faculty of Aerospace Engineering, Technion - Israel Institute of Technology, Haifa, Israel
Fridman, T., Faculty of Aerospace Engineering, Technion - Israel Institute of Technology, Haifa, Israel
Perelshtain, Y., Faculty of Aerospace Engineering, Technion - Israel Institute of Technology, Haifa, Israel
Abstract:
This article details the design, testing, and manufacturing processes conducted by the BATMOBILE team within the framework of the Technion Aerospace Engineering faculty design project. The project is subjected to limitations dictated by the AIAA/Cessna/RMS Student Design/Build/Fly Competition. The primary objective is to maximize the total flight score, which is comprised of three missions to be completed in succession: a ferry flight and two payload flights (softballs and bats). For the aircraft design process we took drag, weight, manufacturability and reparability, stability and control, box restrictions and cost as our main evaluation parameters. This process yielded a modular configuration with a tractor propulsion system, conventional wing, dual boom bronco tail and a tricycle landing gear. Flight and landing scenarios were simulated by concentrated forces on the landing gear hard points and on the wing joints. Load distribution was analyzed by using the theory of elasticity, identifying areas of concentration. The aircraft was finally put through two series of successful test flights, which showed its airworthiness and capability of performing the missions it was designed to. The project's design process was made up of 3 stages: conceptual design, preliminary design and detailed design. Conceptual design: analysis focused on selecting the configuration that would both abide the competition rules, and maximize the competition score. The rules were carefully analyzed in order to identify the mission requirements as well as getting an initial idea for the optimal aircraft for the various missions. In this stage, a team brainstorming procedure was conducted, and the basic design of the aircraft was chosen with the use of the FOM (Figure Of Merit) method as well as using past experience and knowledge. Preliminary design analysis focused on examination of critical design variables in the various aerospace disciplines. These included: aerodynamics, structure, propulsion, weight and balance, stability and control and performance. In this stage, the aircraft took shape and, after the various analyses (both theoretical and experimental) were made in each field, the main components and materials were chosen in order to satisfy the requirements. Detailed design focused on selecting the final components and avionics systems, as well as releasing of drawings for manufacturing purposes. Once the design of the aircraft was complete, the manufacturing process began. This process included selecting building methods and techniques based on cost, available equipment, qualities and skills required, and finally, building of the aircraft.
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