Control-relevant modeling of hypersonic vehicles

Abstract

Scramjet powered hypersonic vehicles represent the next critical step toward achieving NASA's vision for Highly Reliable Reusable Launch Systems (HRRLS), affordable space access, planetary re-entry systems, and global reach vehicles. The design of such vehicles is a very interdisciplinary and highly complex problem. As such, the development of varying fidelity mathematical models for assessing overall stability and performance during the design process is very important. In particular, developing "low-order" models with "sufficient fidelity" to capture control-centric phenomena becomes vital in early stages of vehicle design. Historically, the early stage vehicle design process never incorporated control related considerations. The design obtained by such practice is not optimal and can often lead to poor design from a stability and performance view point. This paper presents control-relevant modeling efforts which will facilitate quick iterative control analysis and design during early stages of vehicle design. The paper is intended to be of an introductory nature and presents the high level modeling framework and associated challenges. An example linear 6 DOF model with some representative analysis is also given to demonstrate the applicability of the tool suite.

A real-time infrared radiation imaging simulation method of aircraft skin with aerodynamic heating effect

“…He also proved that the new CFD tool can improve the accuracy of meshing and remeshing [15]. Vogel et al brought about an integrated control model of hypersonic vehicle by using panel element method [16]. In 2011, Ma et al realized that the process of material panel element generation is very time-consuming and error prone, and proposed an automatic mesh generator, called as AUTOMESH [17].…”

3-D Simulation of Flexible Hypersonic Vehicles

“…This specific OML geometry was provided by VSI a and is described in Ref. 4. The OML consists of a fuselage, scramjet cowl, and two stabilizers with elevator flaps.…”

Partitioned Time-Domain Substructure Coupling Methodology for Efficient Hypersonic Vehicle Simulation

“…6. This specific geometry was provided by Vibroacoustics Solutions, Inc. ‡ and is described in [24]. The OML includes both the fuselage as well as the scramjet cowl.…”