Lead Angle Constrained Optimal Midcourse Guidance

Dwivedi, P.N.; Kumar, Prem; Bhattacharya, Abhijit; Padhi, Radhakant

doi:10.2514/6.2013-4786

Cited by 5 publications

(3 citation statements)

References 20 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…t n go ) and included in the denominator of the cost function. Several improvements to the basic idea have been reported in the recent literature, such as incorporating the target movement information [8] and optimally selecting the desired angles [9].…”

Section: Introductionmentioning

confidence: 99%

Selection of optimal time-to-go in generalized vector explicit guidance

Mondal

Padhi

2015

2015 IEEE Conference on Control Applications (CCA)

Self Cite

View full text Add to dashboard Cite

A new method of selection of time-to-go (tgo) for Generalized Vector Explicit Guidance (GENEX) law have been proposed in this paper. tgo is known to be an important parameter in the control and cost function of GENEX guidance law. In this paper the formulation has been done to find an optimal value of tgo that minimizes the performance cost. Mechanization of GENEX with this optimal tgo reduces the lateral acceleration demand and consequently increases the range of the interceptor. This new formulation of computing tgo comes in closed form and thus it can be implemented onboard. This new formulation is applied in the terminal phase of an surface-to-air interceptor for an angle constrained engagement. Results generated by simulation justify the use of optimal tgo.

show abstract

Section: Introductionmentioning

confidence: 99%

Selection of optimal time-to-go in generalized vector explicit guidance

Mondal

Padhi

2015

2015 IEEE Conference on Control Applications (CCA)

Self Cite

View full text Add to dashboard Cite

show abstract

“…Due to the lower speed of aircraft compared to hypersonic targets, it is difficult to guarantee the accuracy of intersection by using traditional guidance law [1][2][3] . Dwivedi et al [4] addressed this issue by designing an optimal mid-guidance law with front angle constraints to enable the seeker on the aircraft to detect and monitor the target effectively. Chen et al [5] designed a medium guidance law based on the T-S fuzzy method and sliding mode control.…”

Section: Introductionmentioning

confidence: 99%

Trajectory prediction-based guidance law

Li,

Guo,

Jiang

2024

J. Phys.: Conf. Ser.

View full text Add to dashboard Cite

This paper proposes a guidance law based on trajectory prediction, aiming to address the difficulty of traditional guidance laws in meeting high-speed and highly maneuverable vehicles. The unscented Kalman filtering (UKF) technique is employed to estimate the target’s motion and predict the virtual impact point using the Singer model and measuring model. The midcourse guidance law is applied to the virtual target, taking into account the constraint of the intersection angle, while the terminal guidance utilizes modified proportional guidance. To mitigate the overload chattering in the transition sections of both midcourse and terminal guidance, the distance is used to modify the transition section of the terminal guidance. Simulation results demonstrate that the proposed guidance law effectively reduces both the encounter angle and the required maneuvering. Furthermore, to minimize midcourse guidance errors, the prediction results of the virtual target are continually updated during the trace process. This method can also be applied to trail other highly maneuverable targets.

show abstract

“…To tackle this threat, massive work on the defense system has been done [4 -8]. Dwivedi et al [9] developed a lead angle constraint optimal midcourse guidance which can generate the desired optimal terminal condition. Sahu et al [10] developed an optimal terminal impact angle constrained midcourse guidance law with near-zero lateral acceleration in the terminal phase.…”

Section: Introductionmentioning

confidence: 99%

Aero-thermal heating constrained midcourse guidance using state-constrained model predictive static programming method

Fu¹,

Guo²,

Chen³

et al. 2018

Journal of Systems Engineering and Electronics

View full text Add to dashboard Cite

This paper proposes a multiple-constraints-guaranteed midcourse guidance law for the interception of the hypersonic targets. In traditional midcourse law design, the constraints of the aero-thermal heating are rarely taken into consideration. The performance of the infrared detection system may be degraded and the instability of the flight control system may be induced. To address this problem, a state-constrained model predictive static programming method is introduced such that both terminal constraints (position and angle) and optimal energy consumption can be ensured. As a result, a sub-optimal midcourse guidance, guaranteeing the aforementioned multiple-constraints to be never violated, is synthesized. Simulation results demonstrate the effectiveness of the proposed method.

show abstract

Lead Angle Constrained Optimal Midcourse Guidance

Cited by 5 publications

References 20 publications

Selection of optimal time-to-go in generalized vector explicit guidance

Selection of optimal time-to-go in generalized vector explicit guidance

Trajectory prediction-based guidance law

Aero-thermal heating constrained midcourse guidance using state-constrained model predictive static programming method

Contact Info

Product

Resources

About