Analytical impact time and angle guidance via time-varying sliding mode technique

Nonsingular PNG-Based Impact Time Control Guidance with Lower Dependence on Time-to-Go Estimate

“…always holds regardless of the sign of ξ T . Therefore, Equation (14) always has real number solutions during the guidance process. However, it should be noted that only the use of jξ T j cannot guarantee the effectiveness of the proposed ITCG in the case of ξ T < 0.…”

“…Moreover [1], a number of ITCG laws presented in the current research literature [2][3][4][5][6][7][8][9][10][11][12][13][14][15][16][17] are also dependent on the time-to-go estimation, although they may be designed based on different theories or techniques. For instance, the studies presented in [1][2][3][4][5][6][7][8][9][10] were performed in terms of the principle of PNG, among which several widely used formulas for estimating the time-to-go are also derived in the framework of PNG.…”

“…A sliding-mode-based ITCG law was derived in [11] with a simple time-to-go estimate that uses the range divided by the closing speed. Three specific ITCG laws based on sliding mode technique were proposed in [12][13][14], using the same time-to-go approximation proposed in [2]. The Lyapunov-based ITCG law as presented in [15] uses the time-to-go formula derived in [1].…”

A New Optimal Guidance Law with Impact Time and Angle Constraints Based on Sequential Convex Programming

“…Optimal control theory has been implemented to solve optimal guidance law under impact time and angle constraints [1][2][3]. Kim and Zhao have converted guidance law to a polynomial form with respect to the range-to-go, and three coefficients in the polynomial are designed to control the impact time, impact angle, and zero miss distance [4,5], respectively. Besides, the errors of impact time and angle also have been selected as sliding surface to constraint terminal impact time and angle by sliding-mode control, whereas not optimal [6][7][8].…”

Autopilot and guidance law design considering impact angle and time

“…In the problem of missile interception, it is desired to obtain a minimum miss distance, and also satisfy terminal constraints such as impact angle and impact time. The motivation for achieving particular terminal impact angles stems from the requirement of increasing the lethality of the warhead that the missile carries [1]; for example, the top attack is preferable in the anti‐tank application since tanks are vulnerable from the top [2]. The impact time constraint is very important for homing missiles in salvo attacks or cooperative attack missions, in which multiple missiles are commanded to simultaneously hit a target [2].…”