VTOL Aircraft Conceptual Design Optimization

Overview

The goal of this project is to implement a Python-based library for the VTOL conceptual design optimization . We aim to enable rapid design space exploration for various VTOL vehicles:

• VTOL configurations: Multirotor, tailsitter, lift+cruise, and tilt-rotor
• Propulsion architectures: series and parallele hybrid, turboelectric, and all-electric.
• Vehicle size: from lightweight UAV to larger crewed vehicles

Implementation

We use OpenMDAO as an underlying framework. OpenMDAO enables fast and accurate derivative computations, which is important for successful gradient-based optimization. Various optimizers, including SLSQP, SNOPT, and IPOPT (via pyOptSparse) can be used for optimization.

We also use the following packages:

• OpenAeroStruct: vortex lattice method
• CCBlade: blade element momentum theory for rotor analysis
• OpenConcept: flight mission analysis

Examples

NOTE: the numbers on the figure axes are intentionally removed.

Example 1: trends of the takeoff weight and vehicle geometry (wing and rotor disk size) as a function of the 1g hover disk loading.

Example 2: sensitivity of the takeoff weight with respect to the cruise L/D under various frame weight assumptions.