Hypersonic flight control system design using fixed order robust controllers

Abstract

Control system design for hypersonic vehicles will be complicated by coupling e ects between aerodynamics, propulsion, and structure. Using H 1 and-synthesis techniques, these features can be modeled as uncertainties and incorporated into the design procedure of a ight c o n trol system. However, modern control theory techniques generally lead to high order controllers. A technique to constrain controller dimension a priori in the design process is used to design xed order controllers which are robust to mixed real/complex uncertainties. Typical hypersonic e ects like propulsion system perturbations and aeroelastic fuselage bending are modeled as uncertainties in a robust control design framework.

Speed control of high speed aircraft with fixed attack angle and constant elastic shape states

“…In accordance with the research principle of from simple to complex, we extract the simple model of hypersonic engine, attack angle is constant elastic form in constant case. The relationship between the vehicle speed and engine oil supply factor is researched [9][10][11][12] . Through speed control research of a simple model, on the one hand we can preliminary verify the rationality of the engine, on the other hand we can preliminary understand the dynamic characteristics of engine, and the coupling relationship between attack angle and elastic form.…”

Integral Sliding Mode Control of Airship Pitch Channel simplified model

“…It is mainly due to the strong nonlinearity [1][2][3][4] , fast time-varying characteristics and the three channel coupling problems brings great challenge to the control theory. At present, the traditional methods such as traditional PID, state feedback and state space method [5][6][7][8] have been adopted by scholars at home and abroad, also variable structure, adaptive control and other modern control methods are tried in hypersonic vehicle control, even neural network, genetic algorithm, fuzzy control and other intelligent method are studied and applied.…”

Simulation of open loop response of a kind of high speed aircraft with virtual flying conditions

“…The purpose is to study height change on the influence of the attitude stability of hypersonic flight vehicle [1][2][3][4] . At the same time, the relationship between engine thrust and the oil supply factor is researched under the constant form condition of constant attack angle.…”