Optimization of Conceptual Aircraft Design for Stability/Control and Performance
Abstract
The goal of this research was to develop a design optimization capability for the conceptual design of airplanes, where static and dynamic stability and control requirements are addressed simultaneously together with mission and performance requirements. Typically, these requirements are not even considered until after initial aircraft sizing is completed. A design program was created to size the airplane, determine dimensions and locations of tail surfaces (horizontal and vertical tails), control surfaces (elevator, rudder, ailerons), and landing gear, and distribute systems and components all in one step in an optimal manner. Analysis methods used in the calculation of applied aerodynamics, weight and balance, mission analysis, performance, and static 1 dynamic stability and control are all computationally fast, leading to an analysis module that is extremely efficient for optimization or parametric studies. Integration of the optimization modules with the analysis module is done in a way that makes it possible to easily change selections of design variables, constraints, and objective function for different design optimization studies. Results of the analysis program were compared with data from existing aircraft to verify accuracy. These results and those from a number of optimization test cases are included in this thesis. In its present form the new capability is a valuable addition to the computer design tools available for conceptual design of general aviation airplanes. It will be very useful for educational purposes especially in undergraduate and graduate airplane design courses.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 2000
- Accession Number
- ADA387211
Entities
People
- John D. Galloway Jr
Organizations
- University of Washington