Look-Angle-Shaping Guidance Law for Impact Angle and Time Control With Field-of-View Constraint

Kim, Hyeong-Geun; Lee, Jun-Yong; Kim, Hyoun Jin; Kwon, Hye Won; Park, Jang-Seong

doi:10.1109/taes.2019.2924175

Cited by 60 publications

(16 citation statements)

References 26 publications

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“…Diğer gruptaki yöntemler ise göreceli olarak yeni gelişmekte olup kestirim bilgisine ihtiyaç duymazlar ve farklı bir tasarım yaklaşımı kullanırlar. Bunlara örnek olarak [10,11] verilebilir.…”

Section: çOklu Füze Sistemleri Için Güdüm Algoritması Tasarımı Guidance Algorithm Design For Multi-missile Systemsunclassified

Çoklu Füze Sistemleri için Güdüm Algoritması Tasarımı

Tekin¹,

Erer²

2021

Deu Muhendislik Fakultesi Fen Ve Muhendislik

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ÖzBu çalışmada, çoklu otonom sistemler için güdüm algoritma tasarımları sunulmuştur. Otonom sistem olarak jenerik bir füze ele alınmıştır. İlk olarak, eş zamanlı varış kontrolü için menzilin zamana bağlı genel bir polinom olarak şekillendirildiği bir güdüm tasarımı sunulmuştur. Sonrasında bir lider ve takipçilerden oluşan bir sistem için füze güdümü kullanılarak bir takip algoritması tasarımı önerilmiştir. Bunun için varış açısının kontrolünü sağlayan bir yöntem, lidere göre sabit olarak konumlandırılan bir sanal lideri kuyruk takibi modunda izlemek için kullanılmıştır. Her iki ortak saldırı yaklaşımında, otonom sisteme yeni üyeler, görev tanımları merkezi kontrol birimi ya da lider tarafından tanımlanarak dahil olabilirler. Önerilen yaklaşımlar füzeler için örneklenmiş olup, insansız hava araçlarında ve robotik alanında da kullanılabilir.

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Section: çOklu Füze Sistemleri Için Güdüm Algoritması Tasarımı Guidance Algorithm Design For Multi-missile Systemsunclassified

Çoklu Füze Sistemleri için Güdüm Algoritması Tasarımı

Tekin¹,

Erer²

2021

Deu Muhendislik Fakultesi Fen Ve Muhendislik

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“…The FOV constraint is guaranteed by the varying-gain approach. Different from [14], an ITACG law with FOV constraint is derived based on the look angle shaping technique in [15]. In [16], the authors consider the three-dimensional impact time control problem.…”

Section: Introductionmentioning

confidence: 99%

“…Through optimal control theory, an ITCG law with FOV constraint in three-dimensional space is obtained. Although [12][13][14][15][16] consider the FOV constraint, they require a small angle assumption and time-to-go estimation, which is not what we want. In [17], a PNG law with time-varying navigation gain is presented.…”

Section: Introductionmentioning

confidence: 99%

“…Due to the open-loop structure of the proposed guidance law and the insufficient utilization of the maximum detection capability of the seeker, the guidance law is modified to a closed-loop structure, and the maximum detection capability of the seeker is more utilized. The main advantages of the proposed ITCG law with FOV constraint are summarized as follows: First, compared with [12][13][14][15][16], the proposed method does not require the small angle assumption and time-to-go estimation, which avoids the degradation of guidance law performance caused by estimation error. Second, compared with [17][18][19][20], the proposed method can make more use of the seeker's maximum detection capability when the initial lead angle is far less than the maximum look angle of the seeker.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Field-of-View Constrained Impact Time Control Guidance via Time-Varying Sliding Mode Control

Ma¹,

Wang²,

Wang³

2021

Aerospace

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The problem of impact time control guidance with field-of-view constraint is addressed based on time-varying sliding mode control. The kinematic conditions that satisfy the impact time control with field-of-view constraint are defined, and then a novel time-varying sliding surface is constructed to achieve the defined conditions. The sliding surface contains two unknown coefficients: one is tuned to achieve the global sliding surface to satisfy the impact time constraint and zero miss distance, and the other is tuned to guarantee the field-of-view constraint. The guidance law is designed to ensure the realization of the global sliding mode. On this basis, the guidance law is modified to a closed-loop structure, and the maximum detection capability of the seeker is utilized to a greater extent. Under the proposed guidance law, neither the small angle assumption nor time-to-go estimation is needed. The guidance command is continuous and converges to 0 at the desired impact time. Simulation results demonstrate the effectiveness and superiority of the proposed guidance law.

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“…For years, various guidance laws have been utilized with different control concepts. Currently, most popular terminal guidance laws defined by Locke involve line-of-sight (LOS) guidance [6], [7], LOS rate guidance [8], [9], commandto-line-of-sight (CLOS) guidance [10], [11], and other advanced guidances such as proportional navigation guidance (PNG) [12]- [14], command to optimal interception point (COIP) guidance [15], augmented proportional navigation guidance (APNG) [16], optimal guidance law [17]- [19], linear quadratic Gaussian (LQG) theory [20], [21], sliding mode theory [22], H ∞ robust theory, impact angle control [23]- [25] and fuzzy logic control theory [26]- [28], etc. For the above conventional guidance strategy designs, it assumed the information of target and missile can be obtained perfectly by the seeker of missile for guidance control design, namely it neglect the effect of measurement noise in seeker.…”

Section: Introdutctionmentioning

confidence: 99%

Robust Stochastic Observer-Based Attack-Tolerant Missile Guidance Control Design Under Malicious Actuator and Sensor Attacks

2021

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In this study, the robust H ∞ stochastic observer-based attack-tolerant guidance control strategy is designed for the nonlinear stochastic missile guidance control system under the external disturbance and measurement noise as well as actuator attack signal and sensor attack signal. To simplify the attack signal estimation, a novel nonsingular smoothed dynamic model is introduced to efficiently describe the actuator and sensor attack signals. Consequently, the state/attack signal estimation can be easily achieved by using conventional Luenberger observer. Next, to attenuate the effect of external disturbance, measurement noise and approximation errors of attack signal on the missile guidance control system, the robust H ∞ attack-tolerant guidance control performance is considered and the design condition is derived in terms of nonlinear Hamilton-Jacobi inequality (HJI) constrained problem. Since HJI can not be easily solved analytically or numerically, the Takagi-Sugeno (T-S) fuzzy modelling method is utilized to facilitate the robust H ∞ attack-tolerant guidance control strategy design. Thereafter, the H ∞ observer-based attacktolerant control design problem is transformed into linear matrix inequalities problem (LMIP) which can be solved very efficiently by using the convex optimization techniques. Simulation example, with the comparison between the proposed method and conventional robust missile guidance strategy, is given to illustrate the design procedures and validate the performance of the proposed method.

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Look-Angle-Shaping Guidance Law for Impact Angle and Time Control With Field-of-View Constraint

Cited by 60 publications

References 26 publications

Çoklu Füze Sistemleri için Güdüm Algoritması Tasarımı

Çoklu Füze Sistemleri için Güdüm Algoritması Tasarımı

Field-of-View Constrained Impact Time Control Guidance via Time-Varying Sliding Mode Control

Robust Stochastic Observer-Based Attack-Tolerant Missile Guidance Control Design Under Malicious Actuator and Sensor Attacks

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