Capability Analysis of Global Hypersonic Wind Tunnel Facilities for Aerothermodynamic Investigations

This paper contains two parts: numerical analyses and a control method. The numerical analyses of a hypersonic flying object’s aerodynamic heating environment are based on three different two-dimensional outflow fields via finite element calculations. Then, the reference temperature trajectories of a hypersonic flying object are obtained. The other one is an intelligent proportional-derivative (IPD) with a nonlinear global sliding mode control (NGSMC) based on a nonlinear extended state observer (NESO) for a real-time ground aerodynamic heating simulation of a hypersonic flying object, named a thermal-structural test with quartz lamp heaters. The composite controller is made of three sub-components: a model free frame that is independent of the system dynamic model along with an ultra-local model; a NESO for the lumped disturbances observation; and an integral sliding mode control with a nonlinear function for the observation errors compensation. The flight environment of the hypersonic flying object is from Mach number 0.6 to Mach number 5.0, with between flight altitude of 31,272 m and flight altitude of 13,577 m. The comparative results demonstrate some superiorities of the proposed composite controller in terms of tracking errors and robustness.

show abstract

Capability Analysis of Global Hypersonic Wind Tunnel Facilities for Aerothermodynamic Investigations

Cited by 4 publications

References 38 publications

Efficient diffuser design for plasma wind tunnels with a large blockage model

Efficient diffuser design for plasma wind tunnels with a large blockage model

Research on Ramjet Modeling for Control and Multivariable Control System Transform

Numerical Analyses and a Nonlinear Composite Controller for a Real-Time Ground Aerodynamic Heating Simulation of a Hypersonic Flying Object

Contact Info

Product

Resources

About