scholarly journals Effect of Control Surface-Fuselage Inertial Coupling on Hypersonic Vehicle Flight Dynamics

2011 ◽  
Author(s):  
Nathan Falkiewicz ◽  
Scott Frendreis ◽  
Carlos Cesnik
Keyword(s):  
Flight Dynamics ◽  
Hypersonic Vehicle ◽  
Control Surface ◽  
Inertial Coupling

Adaptive nonlinear generalized predictive control for hypersonic vehicle with unknown parameters and control constraints

2017 ◽  
Vol 233 (2) ◽  
pp. 510-532 ◽  
Author(s):  
Tingting Tang ◽  
Ruiyun Qi ◽  
Bin Jiang
Keyword(s):  
Predictive Control ◽  
Estimation Method ◽  
Hypersonic Vehicle ◽  
Control Surface ◽  
Generalized Predictive Control ◽  
Parameter Uncertainties ◽  
Unknown Parameters ◽  
Adaptive Parameter ◽  
Boundedness Problem ◽  
And Control

In this article, an adaptive nonlinear generalized predictive controller is developed for the hypersonic vehicle with unknown parameter uncertainties and control surface constraints. A nominal controller based on generalized predictive control is first developed for the nominal longitudinal model. Considering the complicated practical flying environment and outer unknown disturbances, a parametric longitudinal dynamics model of the hypersonic vehicle is constructed. Then, an adaptive parameter estimation method is proposed to update the unknown controller parameters and parameter projection is applied to solve the control singularity and the parameter boundedness problem. Control surface is restricted to deflect in a range. To satisfy the above constraint, the predictive time should be selected appropriately. Through a large number of simulation experiments, the suitable ranges of the predictive time under different commands are given. All closed-loop signals are guaranteed to be bounded. And simulation results verify the effectiveness of the proposed controller.

Impact of aeroelastic-propulsive interactions on flight dynamics of a hypersonic vehicle

1995 ◽  
Vol 32 (2) ◽  
pp. 355-362 ◽  
Author(s):  
David L. Raney ◽  
John D. Mcminn ◽  
Anthony S. Pototzky
Keyword(s):  
Flight Dynamics ◽  
Hypersonic Vehicle

scholarly journals Adaptive Command Filtered Integrated Guidance and Control for Hypersonic Vehicle with Magnitude, Rate and Bandwidth Constraints

2018 ◽  
Vol 151 ◽  
pp. 05004
Author(s):  
Liang Wang ◽  
Weihua Zhang ◽  
Ke Peng ◽  
Donghui Wang
Keyword(s):  
Sliding Mode ◽  
Integrated Design ◽  
Hypersonic Vehicle ◽  
Convergence Time ◽  
Control Surface ◽  
Control Input ◽  
Guidance And Control ◽  
Surface Deflection ◽  
Integrated Guidance And Control ◽  
And Control

This paper proposes a novel integrated guidance and control (IGC) method for hypersonic vehicle in terminal phase. Firstly, the system model is developed with a second order actuator dynamics. Then the back-stepping controller is designed hierarchically with command filters, where the first order command filters are implemented to construct the virtual control input with ideal states predicted by an adaptive estimator, and the nonlinear command filter is designed to produce magnitude, rate and bandwidth limited control surface deflection finally tracked by a terminal sliding mode controller with finite convergence time. Through a series of 6-DOF numerical simulations, it’s indicated that the proposed method successfully cancels out the large aerodynamics coefficient uncertainties and disturbances in hypersonic flight under limited control surface deflection. The contribution of this paper lies in the application and determination of nonlinear integrated design of guidance and control system for hypersonic vehicle.

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