Closed-form solution for a class of guidance laws

Yang, Ciann-Dong; Yeh, Fang-Bo

doi:10.2514/3.20234

Cited by 24 publications

(7 citation statements)

References 4 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The LOS angle rate a given in (13) and 14is obtained also by imposing the constraint Ni > 3 which is shown to be necessary for effective interception in Theorem 2. Substituting (13) and (14) into (7) and using RdR = d (R 2 /2), the solution of (7) and (8) can be written as (10) and (11).…”

Section: Manoeuvring Target Engagementmentioning

confidence: 99%

“…PROOF. TO guarantee effective capture, the missile should intercept the target with a finite acceleration and within a finite time [10]. From (13) and (14), A 7 !…”

Section: Remarksmentioning

confidence: 99%

“…Substituting a into (8) with (13), a can be written as Equation (19) shows that N t > 3 can prevent the LOS angular acceleration a from approaching infinity, as R -> 0. The final closing speed Rf can be derived from (10) and 11as…”

Section: Remarksmentioning

confidence: 99%

See 2 more Smart Citations

Observability-enhanced proportional navigation guidance with bearings-only measurements

Lim

1999

J. Aust. Math. Soc. Series B, Appl. Math

View full text Add to dashboard Cite

We analyse the performance of the additive observable proportional navigation guidance system, which is well-suited for low-cost homing missiles with bearings-only measurements. Closed-form solutions are derived for both manoeuvring and non-manoeuvring targets. Guidelines on how to select the navigation constants of the control law are presented. We show that the additive observable proportional navigation guidance system can cover a larger capture area than can a conventional proportional navigation system.

show abstract

Section: Manoeuvring Target Engagementmentioning

confidence: 99%

“…PROOF. TO guarantee effective capture, the missile should intercept the target with a finite acceleration and within a finite time [10]. From (13) and (14), A 7 !…”

Section: Remarksmentioning

confidence: 99%

See 1 more Smart Citation

Observability-enhanced proportional navigation guidance with bearings-only measurements

Lim

1999

J. Aust. Math. Soc. Series B, Appl. Math

View full text Add to dashboard Cite

show abstract

“…The study of absolute and relative motion of vehicles based on differential geometric curve principle is a new and popular research method in the field of missile interception. Anderson and Yang et al [23][24][25][26][27][28][29][30][31][32] obtained a more simplified relative motion equation through studying the rotation law of LOS by curvature and torsion. Taking the orbit of chaser and target as a curve in three-dimensional space, the theory of differential geometry curve can be extended to the control problem of approaching and forced fly-around against the tumbling target in space.…”

Section: Introductionmentioning

confidence: 99%

Control strategy design for forced fly-around against the tumbling target based on differential geometric principle

Liu

Liang

et al. 2020

View full text Add to dashboard Cite

Forced fly-around of spacecraft is the basis for tracking and capturing space tumbling target in active debris removal mission. In this paper, the relative kinematic equation between chaser and target is first obtained with the help of classical differential geometry principle. Then, taking the attitude dynamic model of tumbling target into consideration, the finite time convergence sliding model control (FTCSMC) is designed to enable the forced fly-around in the line of sight rotation coordinate system. Finally, the effectiveness and robustness of the control strategy are verified in two typical cases by numerical simulation.

show abstract

“…Two well known extensions from PN are pure proportional navigation (PPN) and true proportional navigation (TPN). Guelman was the first to derive the close-form solution of TPN [2], and Yang developed the general form of the solution of TPN [3,4]. A comparison between PPN and TPN was then made by Shukla and Mahapatra [5].…”

Section: Introductionmentioning

confidence: 99%

Integrated Game Based Guidance with Nonlinear Autopilot Design for Maneuvering Target Interception

Hsueh¹,

Wang²,

Fu³

2013

Asian Journal of Control

View full text Add to dashboard Cite

The integrated game theory based guidance law with nonlinear autopilot (GGNA) system is presented in this paper. The guidance law is designed based on linear differential game theory while considering the motion of the target in 3-D space such that the distance between the missile and the target is minimized faster than before. The autopilot system based on quaternion representation is developed using sliding mode control method to generate the attitude command. The stability of the integrated guidance and nonlinear autopilot system is analyzed with Lyapunov stability theory. In addition, this research assumes wingless missiles in our context in order to reduce the nonlinear effect from the aerodynamics. Furthermore, in order to extend the operation range of missiles from endo-atmosphere to exo-atmosphere, the missiles are equipped with Thrust Vector Control (TVC) mechanisms and Divert Control System (DCS). Finally, extensive simulations incorporating aerodynamic models are demonstrated to verify the validity of the proposed integrated guidance/autopilot systems. Moreover, the simulation results reveal that the mission of intercepting a maneuvering target is successfully accomplished.

show abstract

Closed-form solution for a class of guidance laws

Cited by 24 publications

References 4 publications

Observability-enhanced proportional navigation guidance with bearings-only measurements

Observability-enhanced proportional navigation guidance with bearings-only measurements

Control strategy design for forced fly-around against the tumbling target based on differential geometric principle

Integrated Game Based Guidance with Nonlinear Autopilot Design for Maneuvering Target Interception

Contact Info

Product

Resources

About