Nonlinear Model Predictive Control based Missile Guidance for Target Interception

Integrated Guidance and Control Using Model Predictive Control with Flight Path Angle Prediction against Pull-Up Maneuvering Target

“…for all k ∈ {0, • • • , N − 1}, where Q k and R k are weighting matrices of x k and u k , respectively. In Equation (10), subscript 0 indicates the current time and N is the number of samples. Therefore, the length of the time horizon in MPC, t c , can be computed as follows:…”

“…For the MPC problem in Equation (10), a nonzero number is assigned to the fifth diagonal element in Q k so that a small z m is to be achieved for intercepting the target, as shown in Table 1. The other diagonal elements in Q k are left at zero because they are not required to be regulated.…”

“…It is shown that the computation time depends on N (= t c /∆t c ), which is the number of samples. Note that computational complexity for the proposed algorithm mainly comes from solving the convex optimization in Equation (10), of which the problem size grows linearly with N. Also, note that Equation (10) constitutes a sparse quadratic programming problem, and the computational complexity for solving sparse quadratic programming via the interior point methods with sparse matrix factorization is proportional to the number of nonzero elements in the associated KKT matrix, which is proportional to the problem size [36,37]. This matches very well with the results observed in Table 2.…”

“…Research on missile guidance and control fields is being actively conducted nowadays, as it has always been [1][2][3][4][5][6][7][8][9][10]. Traditionally, the guidance system and control system of an interceptor missile are separately designed.…”

“…All of the aforementioned guidance studies [1][2][3][4][5][6][7][8][9][10], as well as advanced guidance research such as Impact Angle Control Guidance (IACG) [11][12][13], Impact Time and Angle Control Guidance (ITACG) [14], or circular navigation guidance [15] only consider some form of guidance problems. As they are combined with the control loops, most of them suffer from terminal instability issues in the vicinity of the impact.…”