Stability analysis of a hypersonic vehicle controlled by the characteristic model based adaptive controller

Abstract

Stability analysis of a hypersonic vehicle controlled by the characteristic model based adaptive controller SCIENTIA SINICA Informationis 42, 379 (2012); Characteristic model based adaptive controller design and analysis for a class of SISO systems SCIENCE CHINA Information Sciences 59, 052202 (2016); Stability analysis of golden-section adaptive control systems based on the characteristic model SCIENCE CHINA Information Sciences 60, 092205 (2017); Fuzzy dynamic characteristic model based attitude control of hypersonic vehicle in gliding phase SCIENCE CHINA Information Sciences 54, 448 (2011); ${\mathcal{L}}_{1}$ adaptive control of a generic hypersonic vehicle model with a blended pneumatic and thrust vectoring control strategy SCIENCE CHINA Information Sciences 60, 032203 (2017);. RESEARCH PAPER. SCIENCE CHINA Information Sciences

Characteristic Model-Based Robust Model Predictive Control for Hypersonic Vehicles with Constraints

“…Using linear aerodynamics hypothesis and neglecting the influences of control surface deflections on aerodynamic forces, the rigid body attitude dynamic equations are as follows (Zhang and Hu, 2012):…”

“…The characteristic model for the plant (Eqs 3-5) as given in Eqs 1 and 2 possesses the following properties: the coefficients f i1 , f i2 (i = α, β, ϕ) and g 1 , g 2 , g 3 are slowly time-varying, the ranges of these parameters can be decided a priori, in response to the same input, the output of the original model (Eqs 1 and 2) is identical to the output of the characteristic model (Eqs 3-5) at each sampling time. Sum of all the coefficients of (Eqs 3-5) equals 1 (Zhang and Hu, 2012) as follows:…”

“…Let δ α ≈ δ e , then the control constraints can be transformed into ∥δ α (k)∥ 2 ≤ δ e max [the readers can see Zhang and Hu (2012) for detail], the output constraints are ∥α(k)∥ 2 ≤ α max and · α 2 ≈ ∥ω y ∥ 2 ≤ ω y max .…”

“…According to a certain flight state of a plane-symmetry near space hypersonic vehicle, such as (α, β, ϕ) = (10 • , 0 • , 0 • ), obtain the corresponding characteristic model parameters range (Zhang and Hu, 2012). Let the flight height is 40 km, speed is 10 Ma, and the range of aerodynamic coefficient (Liu and Chen, 2010) ∈ [4.5363 4.1338].…”

“…Thus, it is difficult to adapt the large envelope and multitasking flight movement using the traditional PID control, as the selection of the operating points and the design of the scheduling algorithm remains a time-consuming procedure for engineers. Therefore, domestic and foreign researchers study the advanced controller design to make the vehicles have stable flight characteristics and strong robustness (Zhang and Hu, 2012). Since there exist thermal and mechanical constraints in safety boundaries of reentry flight corridors, the hypersonic reentry control system must satisfy strict input and state constraints (Lu, 1999;Shen and Lu, 2003), including the constraints on aerodynamic angles, angular velocities, and control moments.…”