Lyapunov-Based Guidance Law for Impact Time Control and Simultaneous Arrival

Saleem, Abdul; Ratnoo, Ashwini

doi:10.2514/1.g001349

Cited by 130 publications

(53 citation statements)

References 15 publications

Supporting

Mentioning

Contrasting

Unclassified

Order By: Relevance

“…Remark 10. It is noted that in all literature on both cooperative and individual guidance [1][2][3][4][5][6][7]10], only the engagement geometry (4) was involved to generate the missile acceleration, and the missile dynamics (1) was not considered, causing it to have no autopilot. However, in this paper, based on the IGC scheme, the engagement geometry (4) and the missile dynamics (1) are integrated to design directly the commanded (reference) value of the elevator deflection (which is a more realistic control input), exploiting fully the coupling between guidance and autopilot.…”

Section: Proof Of Theorem Definementioning

confidence: 99%

“…Hence in cooperative homing the missiles are required to be equipped with a communication device, which increases the cost and complexity of the scheme [8,9]. The second approach is individual homing [1,2,10], in which a common impact time is commanded (pre-specified) to all missiles in advance, and thereafter each missile tries to hit the target at the pre-specified time. This is a more promising way for multiple low-cost missiles attacking a single target simultaneously from various directions.…”

Section: Introductionmentioning

confidence: 99%

“…This approach combines the engagement geometry with the missile dynamics and directly yields the elevator deflection (which is a realistic control input) to change the velocity direction in the missile control systems. In the current literature [1][2][3][4][5][6][7]10], only the engagement geometry was studied, using the missile normal acceleration as the control input; and the missile dynamics were not considered (which hence ignores the coupling between the engagement geometry and missile dynamics), resulting in no autopilot. 2.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Impact time and angle constrained integrated guidance and control with application to salvo attack

Wang

Tan

Cheng

2019

Asian Journal of Control

View full text Add to dashboard Cite

In this paper, a novel method is proposed to estimate the impact time (time taken to hit the target) for missiles guided by integrated guidance and control (IGC).Firstly, the elevator deflection command is directly designed in the frame of IGC to make the line-of-sight (LOS) angle converge to the desired value in finite time; thereafter, the missiles will fly along the desired LOS until they hit the target.Then a method to estimate the impact time is provided; this can help the user systematically choose the missile parameters in order to achieve a certain impact time, and thus this result can be applied to the case of salvo attack of multiple missiles without online data links. Finally, simulation studies are performed to verify the effectiveness of the proposed scheme.

show abstract

Section: Proof Of Theorem Definementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Impact time and angle constrained integrated guidance and control with application to salvo attack

Wang

Tan

Cheng

2019

Asian Journal of Control

View full text Add to dashboard Cite

show abstract

“…Each missile can utilize the guidance law (17) to achieve the desired impact time at each time step. Inspired by the salvo attack strategy introduced in [24], the detailed algorithm is given in Algorithm 1.…”

Section: Salvo Attackmentioning

confidence: 99%

Impact-Time-Control Guidance Law for Missile with Time-Varying Velocity

Zhou

Wang

Zhao

2016

Mathematical Problems in Engineering

View full text Add to dashboard Cite

The problem of impact-time-control guidance (ITCG) for the homing missile with time-varying velocity is addressed. First, a novel ITCG law is proposed based on the integral sliding mode control (ISMC) method. Then, a salvo attack algorithm is designed based on the proposed guidance law. The performances of the conventional ITCG laws strongly depend on the accuracy of the estimated time-to-go (TTG). However, the accurate estimated TTG can be obtained only if the missile velocity is constant. The conventional ITCG laws were designed under the assumption that the missile velocity is constant. The most attractive feature of this work is that the newly proposed ITCG law relaxes the constant velocity assumption, which only needs the variation range of the missile velocity. Finally, the numerical simulation demonstrates the effectiveness of the proposed method.

show abstract

“…To avoid considerable effort to time-to-go, the ITCG law without using time-to-go has been developed in recent studies [18][19][20][21][22][23][24][25][26][27][28][29][30][31]. Tekin et al [18][19][20][21][22] proposed a series of notable guidance laws under various conditions using polynomial shaping of the look angle and range and the feedback linearization technique.…”

Section: Introductionmentioning

confidence: 99%

Nonsingular PNG-Based Impact Time Control Guidance with Lower Dependence on Time-to-Go Estimate

Chang

Chen

2019

International Journal of Aerospace Engineering

View full text Add to dashboard Cite

In a bid to take advantage of natural characteristics of the proportional navigation guidance (PNG) in practical engineering, the PNG-based impact time control guidance (ITCG) continues to be a popular alternative for achieving the desired impact time of a missile. For most such ITCG, the performance is dependent on the accuracy of the time-to-go estimation. Along the lines of the development of PNG-based ITCG in earlier studies, a nonsingular ITCG is proposed on the basis of nonlinear formulations. It is demonstrated that, by theoretical analysis and numerical simulation, this proposed ITCG is shown to be advantageous in certain circumstances. By deriving a novel additional acceleration command, the proposed law is of lower dependence on time-to-go estimate and is capable of eliminating some singularities, leading to wider adjustable range of the desired impact time and better adaptability to more conditions. This research is expected to be supplementary to those presented in the current research literature.

show abstract

Lyapunov-Based Guidance Law for Impact Time Control and Simultaneous Arrival

Cited by 130 publications

References 15 publications

Impact time and angle constrained integrated guidance and control with application to salvo attack

Impact time and angle constrained integrated guidance and control with application to salvo attack

Impact-Time-Control Guidance Law for Missile with Time-Varying Velocity

Nonsingular PNG-Based Impact Time Control Guidance with Lower Dependence on Time-to-Go Estimate

Contact Info

Product

Resources

About