Topology Optimization of Self-Actuating Mechanisms Containing Active Materials
By systematically combining active and passive materials within a single structure or mechanism, one can tailor the strain response of the system to achieve some target motion. Topology optimization provides a means with which to mathematically determine the optimal distribution and layout of the constituent materials in order to obtain the desired structural response. This design process contains many mathematical and scientific challenges that we seek to address through this research. At the CDI Lab, we are working to develop novel computional techniques for modeling active materials such as shape memory polymers and shape memory alloys, which we will then incorporate into out design optimization algorithms to automatically generate optimal material layouts for self-actuating mechanisms.
Design of a Bi-Stable Morphing Airfoil Via Topology Optimization
The objective of the project is harness the geometric nonlineary of structures to design a novel camber morphing mechanism for a bi-stable airfoil using topology optimization. Morphing can be defined as an external shape change of a structure which has the potential to dramatically alter its performance. Wing morphing can broadly be summarized as continuous shape change of the wing between different configurations whereby the whole structure moves as a single entity, thus eliminating the gaps between hinged members (flaps and slats) in conventional aircraft. Structural morphing confers significant performance benefits including reduced noise, vibrations, and parasitic drag.
Figure 1 shows the finite element mesh and boundary conditions for the optimization problem. By optimally distribution material within this region, we can tailor the non-linear force-displacement response to achieve a bi-stable structure. Once the structure is made bi-stable, it can be deployed to dynamically adapt to changing flight conditions, enabling optimal performance in multiple flight regimes.
Optimal Design of a Hyper-Elliptic Cambered Span Wing
Span-optimized configurations are achieved using a Langrange multiplier method coupled with a vortex lattice analysis code. The study intends to explore a diverse range of planform configurations such as rectangular, tapered and elliptic.
Preliminary analysis of rectangular planform cambered span configuration reveals net reduction of 16.75 % in drag at a design CL of 0.43. Comparisons are made from a baseline planar configuration with Elliptic spanload. Both designs have an equal projected span with the HECS configuration with a larger wetted surface area.
The objective of this research is to create an original computational design framework for the optimal design of multifunctional, heterogeneous material systems. New advances in additive manufacturing have made possible the rapid and inexpensive fabrication of complex designs containing multiple classes of materials, including metals, ceramics, and polymers, all within a single print job. This capability allows manufacturers to produce heterogeneous, multi-component designs, without the need for assembly, thereby eliminating the cost and design limitations that assembly entails. In addition to parameterizing the design problem to allow for multiple materials, we must implement coupled, multi-physics finite element analysis models that can simulate multiple material response phenomena (i.e. plasticity, brittle damage, hyperelasticity), within a single system. Within this research thrust, we are exploring several application domains, including
- Thermomechanical design
- Adaptive morphing using electroactive polymers
- Design for additive manufacturing
Figure 5 shows an example of multi-material topology optimization for maximum elastic stiffness subject to temperature constraints. The structure must functions as a bridge, withstanding a three-point bending load, and it must also function as a heat sink. In response to an applied thermal load at the bottom surface, the design must effectively dissipate heat energy the prevent excess heating along the top surface. The thermal response is modeled using a linear steady-state thermal conductivity model.