Indirect Impact-Angle-Control Against Stationary Targets Using Biased Pure Proportional Navigation

Erer, Koray S.; Merttopçuoglu, Osman

doi:10.2514/1.52105

Cited by 231 publications

(118 citation statements)

References 3 publications

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“…The differentiation of (17) k times with respect to the normalized flight time s becomes (19) hence the following identity is obtained by inserting (19) into (16). …”

Section: Solution To the Tasgl Design Problemmentioning

confidence: 99%

“…The biased term can be easily determined using the closed-form BPN solution derived under the assumption that the missile dynamic lags are negligible [14][15][16]. The BPN based method could be a viable solution for field engineers because it is easy to implement for its simple structure and, moreover, does not require acceleration feedbacks.…”

Section: Introductionmentioning

confidence: 99%

“…On the other hand, the BPN based method incorporates an intentional bias term with the PN guidance command to meet the impact angle requirement [11][12][13][14][15][16].…”

Section: Introductionmentioning

confidence: 99%

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Terminal acceleration stabilizing guidance law for impact angle constrained interception of a non-maneuvering target

Moon

Jung

2015

Int. J. Control Autom. Syst.

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A practical homing guidance scheme is newly proposed in order to meet the impact angle and terminal acceleration constraints, simultaneously. Provided that the homing guidance loop is modeled as a linear time-varying differential equation by approximating the missile dynamics as a firstorder system, its closed-form solution is expressed as a linear combination of hypergeometric functions. It implies that the instability of the homing guidance loop is mainly due to the missile dynamic lags and, furthermore, the non-diverging homing trajectory could be obtained by introducing the additional biased acceleration command as a rational function of time-to-go. These inspirational observations motivate us to formulate an impact angle control problem as designing an appropriate biased term which generates a non-diverging time-to-go polynomial homing trajectory for given terminal constraints. The resultant guidance command has a similar form used in conventional guidance laws but its feedback gains vary with time-to-go. This similarity means that, during the flight, the proposed guidance law adaptively embraces existing guidance laws derived by intentionally ignoring the effect of missile dynamic lags. Through the numerical simulations, the performance of the proposed guidance scheme is evaluated.

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“…The differentiation of (17) k times with respect to the normalized flight time s becomes (19) hence the following identity is obtained by inserting (19) into (16). …”

Section: Solution To the Tasgl Design Problemmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Terminal acceleration stabilizing guidance law for impact angle constrained interception of a non-maneuvering target

Moon

Jung

2015

Int. J. Control Autom. Syst.

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“…참고문헌 [7][8]에서는 비례항법 특성을 이용하여 정지된 표적 또는 기 동이 없고 일정한 속도로 움직이는 표적에 대하 여 지대지(ground-to-ground) 교전 시나리오에서 0°에서 -180°까지의 충돌각을 만족하도록 하기 위한 복합 유도법칙을 제안하였다. 참고문헌 [9] 에서는 가속도 명령을 두 단계로 나누어 초기 유 도에서는 비례항법에 고정된 편향항을 포함한 유 도법칙을 적용하고, 편향항의 …”

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Composite Guidance Law for Impact Angle Control of Passive Homing Missiles

Park¹,

Tahk²,

Kim³

2014

Journal of the Korean Society for Aeronautical & Space Scie

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In this paper, based on the characteristics of proportional navigation, a composite guidance law is proposed for impact angle control of passive homing missiles maintaining the lock-on condition of the seeker. The proposed law is composed of two guidance commands: the first command is to keep the look angle constant after converging to the specific look angle of the seeker, and the second is to impact the target with terminal angle constraint and is implemented after satisfying the specific line of sight(LOS) angle. Because the proposed law considers the seeker's filed-of-view(FOV) and acceleration limits simultaneously and requires neither time-to-go estimation nor relative range information, it can be easily applied to passive homing missiles. The performance and characteristics of the proposed law are investigated through nonlinear simulations with various engagement conditions.

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“…APN guidance laws can achieve the desired impact angle with only information of line-of-sight (LOS) angle or LOS angular rate by adjusting the proportional navigation coefficient [1] or adding a bias term [2,3]. However, it is always assumed in APN approaches that the target is stationary or the target's maneuvering path is known.…”

Section: Introductionmentioning

confidence: 99%

Two-Phase Optimal Guidance Law considering Impact Angle Constraint with Bearings-Only Measurements

Wang

Tang

Guo

et al. 2017

International Journal of Aerospace Engineering

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The implementation of advanced guidance laws with bearings-only measurements requires estimation of the range information. To improve estimation accuracy and satisfy the impact angle constraint, this paper proposes a two-phase optimal guidance law consisting of an observing phase and an attacking phase. In the observing phase, the determinant of Fisher information matrix is maximized to achieve the optimal observability and a suboptimal solution expressed by leading angle is derived analytically. Then, a terminal sliding-mode guidance law is designed to track the desired leading angle. In the followed attacking phase, an optimal guidance law is integrated with a switching term to satisfy both the impact angle constraint and the field-of-view constraint. Finally, comparison studies of the proposed guidance law and a traditional optimal guidance law are conducted on stationary targets and maneuvering targets cases. Simulation results demonstrate that the proposed guidance law is able to improve the range observability and achieve better terminal performances including impact angle accuracy and miss distance.

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Indirect Impact-Angle-Control Against Stationary Targets Using Biased Pure Proportional Navigation

Cited by 231 publications

References 3 publications

Terminal acceleration stabilizing guidance law for impact angle constrained interception of a non-maneuvering target

Terminal acceleration stabilizing guidance law for impact angle constrained interception of a non-maneuvering target

Composite Guidance Law for Impact Angle Control of Passive Homing Missiles

Two-Phase Optimal Guidance Law considering Impact Angle Constraint with Bearings-Only Measurements

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