Guidance scheme for operating multiple ship defense missiles with dual seekers

Abstract

This paper proposes a guidance scheme to operate ship defense missiles using dual seekers—radio frequency and strapdown imaging infrared seekers—against the threat of antiship missiles. Key challenges associated with considered operational concept such as the multipath error of an radio frequency seeker, the narrow field of view of an strapdown imaging infrared seeker, and the interference between the target and defense missiles are identified. A guidance scheme that can address these challenges is proposed by combining an optimal guidance law for the midcourse phase and the proportional navigation guidance for the terminal phase. A relationship among interceptor/target velocity, minimum line-of-sight angle for the radio frequency seeker, and the field of view of the strapdown imaging infrared seeker for a successful intercept is analytically derived and graphically presented. Numerical simulations for the engagements between ship defense missiles and an antiship missile demonstrate the validity of the proposed guidance scheme.

Suboptimal mid-course guidance algorithm for accelerating missiles

“…The first algorithm for the comparison is the mid-course guidance algorithm in Jeon et al. 9 This algorithm is selected to show the results when the gravitational acceleration and velocity change are not considered in the guidance algorithm design. The lateral acceleration command, aCMD, of this algorithm is designed as where rbo, γMd, and σd are obtained from the terminal constraint update algorithm, proposed in this paper.…”

“…The lateral acceleration command, aCMD, of this algorithm is designed as where rbo, γMd, and σd are obtained from the terminal constraint update algorithm, proposed in this paper. The design parameter n is selected as follows which makes the objective function of Jeon et al., 9 minJ=12∫rP0 rboα2(rP-rbo)ndrP, to be identical to that of this paper given in equation (17). The missile system handled in this paper generates lateral acceleration by rotating the missile acceleration vector with respect to the velocity vector, and the rotation angle is symbolized as α.…”

“…From those two statements, the magnitude of M change after the early stage is expected to be small. This results in the assumption that the gravitational acceleration terms in equation (9) are constant shown as follows…”

“…The studies of Jeon et al. 9 and Lee and Jeon 10 also propose mid-course guidance laws based on optimal control theory to satisfy terminal engagement requirements. Application of these algorithms may be limited to the case of small velocity changes because of the constant-velocity assumption.…”

“…Neural-network algorithms studied in Song and Tahk 7,8 for mid-course guidance require offline training of the optimal solutions before on-board implementation. The studies of Jeon et al 9 and Lee and Jeon 10 also propose mid-course guidance laws based on optimal control theory to satisfy terminal engagement requirements. Application of these algorithms may be limited to the case of small velocity changes because of the constant-velocity assumption.…”