A Conceptual Design Workflow for Producing a Controllable 6DOF Simulation of a High-Speed Vehicle

Document Type

Article

Publication Date

1-1-2024

Identifier/URL

41474922 (Pure)

Abstract

Quantifying subsystem power requirements for a high-speed vehicle is a major hurdle in the conceptual design stage. As space and weight are at a premium, there is little room for overdesign when sizing power generation and thermal management systems. Improving the predictive capability of the power requirement would allow for the size and weight of the power generation subsystem to be included in the conceptual design optimization process. The difficulty in obtaining these power requirements for high-speed systems is that many of them require six degree-of-freedom (6DOF) simulations and control schemes for them to accurately characterize power profiles, such as the actuation subsystem. While high speed simulation and control has been considered in the literature before, this is typically done much later in the design process. This research aims to propose a workflow using low-fidelity methods to quickly produce a controllable 6DOF simulation from a high-speed vehicle geometry. This workflow uses the Configuration-Based Aerodynamics (CBAERO) software to generate an aerodynamic database, and control surface increments are obtained using flat-plate modified Newtonian approximations. The plant model is then compiled in SIMULINK, where a Linear-Quadratic-Integrator (LQI) controller is used to control the longitudinal and lateral dynamics, and a PI controller is used to control the speed, with control tuning specifications based on MIL-STD-1797A. This workflow was performed on a notional high-speed vehicle, and a controllable 6DOF simulation was produced and used to simulate a maneuvering trajectory. The bank angle was observed to track alternating steps within one degree with a settling time less than 5.5 seconds, while regulating the flight path angle to zero with a root-mean square error of 0.167 degrees and maintaining flight speed with a root mean square error of 0.0203 Mach over a 540 second simulation.

Comments

Publisher Copyright: © 2024, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

DOI

10.2514/6.2024-4301

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