عنوان مقاله [English]
نویسندگان [English]چکیده [English]
In this Paper, The online optimal integrated guidance and control algorithm design has been provided for two-stages Launch Vehicle .The flight equations are nonlinear and has been derived in flight plane. In order to solve it based on numerical solution and shooting method logic by the combination between ODE - start to end solver algorithm by considering initial conditions for integrated states and co-states - and optimization fmincon SQP algorithm has been acted. In order to verify designing method the results of this algorithm solutions has been compared with the results of a valid separated guidance and control algorithm for launch vehicle. The result function involves minimum control effort, terminal terms and minimizing burning time. The results indicate the satisfaction of three mentioned identities achieving high accurate orbital insertion and more coordination between the operation of guidance and control algorithms in integrated logic comparing with separated ones.