The design of hypersonic vehicles is influenced by tightly coupled interactions between aerodynamics, propulsion, and structures. Therefore, in the conceptual design phases, the identification and mitigation of potential problem areas and disciplinary interrelations are critical. Although the multidisciplinary character of hypersonic designs is well known, research in hypersonics is primarily f...

A new nonlinear fault-tolerant controller is designed to solve the part of actuator failure problem, the hypersonic aircraft nonlinear observer and controller are designed synthetically. We develop the research model based on a SISO output feedback nonlinear unobservered minimum phase system under the condition of single channel actuator failure of the hypersonic aircraft, adopt Kfilter to reco...

This paper focuses on developing a linear parameter varying (LPV) controller for an airbreathing hypersonic vehicle using a velocity-based approach. The design of flight control systems for airbreathing hypersonic vehicles is a highly challenging task due to the unique characteristics of the vehicle dynamics. Motivated by recent results on a velocity-based linearization approach and LPV control...

The hypersonic rarefied wind tunnel has lately been developed at JAXA. The characteristics of hypersonic rarefied flows have been investigated experimentally and numerically in this work. Using a sphere pendulous model, the test flow has been probed by measuring its displacement due to the aerodynamic force. In addition, a spatial variation of total pressure of the test flow has also been measu...

Wind tunnels are being used to study the aerodynamic properties of race cars, fighter planes etc. It allows us to make a reusable prototype and test it in the tunnel. Hypersonic wind tunnels operate at hypersonic speeds ie, with a mach number greater than 6. For doing experiments, it is necessary to maintain a constant pressure in the settling chamber of the tunnel so that we get the desired Ma...

This paper describes the development and implementation of a partitioned-based, multiphysics, multi-fidelity simulation framework for flexible hypersonic vehicles. This simulation framework will enable the study of the dominant physics needed for the generation of control-oriented models and will provide a reference model for flight control evaluation. A partitioned-based solution is employed t...

The interaction of free-stream disturbances and the bow shock wave in hypersonic ow past a blunt leading edge is an important part of hypersonic boundary layer receptivity to free-stream disturbances. It has been shown that, for a perfect gas, the back and forth interaction and reeection of acoustic waves behind the shock greatly amplify the magnitudes of the disturbance waves. The interaction ...

in this paper, an approximate axisymmetric method is developed which can reliably calculate fully viscous hypersonic flow over blunt-nosed bodies. in this method, a maslen’s second-order pressure expression is used instead of the normal momentum equation. the combination of maslen’s second-order pressure expression and viscous shock layer equations is developed to accurately and efficiently com...

in the present work, an engineering method is developed to predict laminar and turbulent heating-rate solutions for blunt reentry spacecraft at hypersonic conditions. the calculation of aerodynamic heating around blunt bodies requires alternative solution of inviscid flow field around the hypersonic bodies. in this paper, the procedure is of an inverse nature, that is, a shock wave is assumed a...