Near optimal re-entry guidance law using inverse problem approach

On-Board Near Optimal Flight Trajectory Generation using Deferential Flatness

“…In this paper, the author extends the previous works done on maximizing terminal velocity [19][20][21]. An explicit guidance law is developed by flatness approach for guiding a hypersonic unthrusted reentry vehicle (RV) to a fixed point on the ground (Eisler's problem [2]).…”

Neural-Based Compensation of Nonlinearities in an Airplane Longitudinal Model with Dynamic-Inversion Control

“…While the elevator deflection ( δ e ) and throttle setting ( η c ) are selected as control inputs ( U ), the airplane model with the state variables X = [ V , γ , q , α , h ] is given as follows [10]:$\begin{array}{c}T17\dot{V}=\frac{T\cos \alpha -D}{m}-g\sin \gamma ,\\ \\ \dot{\gamma }=\frac{L+T\sin \alpha }{mV}-\frac{g\cos \gamma }{V},\\ \\ \dot{q}=\frac{M_y}{I_y},\\ \\ \dot{\alpha }=q-\dot{\gamma },\\ \\ \dot{h}=V\sin \gamma ,\\ \end{array}$where m and I y denote the mass and moment of inertia of the airplane, respectively. Besides that, the lift L , the drag D , the thrust T , and the pitching moment M y are determined by $\begin{array}{c}T17L=\frac{\mathrm{1}}{\mathrm{2}}\rho V^{\mathrm{2}}{S}_w{C}_L,\\ \\ D=\frac{\mathrm{1}}{\mathrm{2}}\rho V^{\mathrm{2}}{S}_w{C}_D,\\ \\ M_y=\frac{\mathrm{1}}{\mathrm{2}}\rho V^{\mathrm{2}}{S}_w\stackrel{-}{c}{C}_M,\\ \\ T\end{array}$…”