Impact Time and Angle Guidance With Sliding Mode Control

Integrated guidance and control law for cooperative attack of multiple missiles

“…Many cooperative guidance laws are deduced on the basis of fixed missile velocity [3,10,[13][14][15][16][19][20][21], which is difficult to realize in practice. In this paper, no assumption of fixed missile velocity is made and the velocity is calculated by dynamic equation of missile.…”

“…During the engagement, missiles communicate through online data link to get the timeto-go of other missiles, and then they adjust their flight to achieve the accordance of the impact time. In [3,10,13], guidance laws controlling both impact time and impact angle were proposed. The guidance law in [13] is an extension of ITCG, in which the missile jerk was used as a control input to control impact angle and an extra term about the impact time error was included in the control input to control impact time.…”

“…In [10], a biased proportional navigation guidance was designed using backstepping control method. [3], where a combination of a line-of-sight rate shaping technique and a second-order sliding mode approach has been adopted to satisfy the constraints of impact time and impact angle. In all of above researches, the estimation of time-to-go is necessary, so the precision of time-to-go estimation has great effect on the precision of guidance law.…”

“…In [14], a game theoretic approach was employed for the design of an integrated linear autopilot-guidance controller that minimizes the interception miss and control energy of the interceptor, under the worst case of target maneuver and worst case of measurement disturbances. In recent years, such nonlinear control theory as sliding mode control (SMC) [7,11,18], backstepping control [6] and dynamic surface control (DSC) [4,5] was employed to design the robust integrated guidance-control controller. In this paper, to consider the guidance requirement and missile's dynamic characteristics simultaneously, the concept of IGC is adopted.…”

Sliding mode control based guidance law with impact time constraints

“…In the past few years, sliding mode control (SMC) algorithm, [1], has been used to develop terminal constrained guidance laws [11]- [16]. In the papers, [11]- [15], guidance laws are designed to achieve a desired impact angle at interception for various kinds of targets, while [16] presents a guidance law for stationary targets with terminal angle and time constraints.…”