Practical Aspects of Optimal Midcourse Guidance For Air-to-air Engagement

Majumder, S.B.; Basha, S. Mahaboob; Tiwari, P.K.; Prasad, D.B.N.; Sarkar, A. K.

doi:10.1016/j.ifacol.2016.03.119

Cited by 6 publications

(5 citation statements)

References 2 publications

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“…A function which represents the transition from Oxz coordinate to x 0 x 1 z 1 coordinate is given in (2).…”

Section: Equation Of Motionmentioning

confidence: 99%

“…Optimal control and estimation theory have been commonly used in the design of advanced guidance systems from the late 1960s [2][3][4][5][6][7][13][14][15][16]. Such approaches have been used to develop tracking algorithms that extract the maximum amount of information about a target trajectory.…”

Section: Introductionmentioning

confidence: 99%

“…In reference [1], by considering the desired impact angle without violating the field-of-view limit, the authors studied a two-stage pure proportional navigation guidance law. Majumder et al investigated a near-optimal solution in real-time for air-to-air engagement [2]. This solution is used to solve the midcourse guidance problem in real-time for air-to-air engagement.…”

Section: Introductionmentioning

confidence: 99%

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An Optimal Algorithm for Midcourse Guidance Law Under Wind Disturbance

Nguyen¹,

Nguyen²

2020

AJAE

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The guidance laws are commonly designed to yield as small a miss distance as possible, harmonious with the missile's acceleration capability. In recent decades, the concept of optimized guidance law is well understood in applications where information concerning the target range and line-of-sight angle is available. Researchers' efforts have been continually made to apply modern control theory to conventional and adaptive autopilot designs, even though the classical theory is still applicable to autopilots. It can be noted that it is desirable to perform a detailed computer-aided feasibility study within the context of a realistic missile-target engagement model. Development and evaluation of guidance and control laws for simplified missile-target engagement scenarios are extended and adapted to the air-to-air missile situation and implemented in a complete three-dimensional engagement model. Thus, this study proposed a computational method for constructing an optimal midcourse guidance law, which is based on the optimal control theory and initial boundary conditions. This proposed guidance law is derived from an optimal control theory with the boundary conditions such as allowed relative distance between missile and target at the final time, low line-of-sight rate. A numerical simulation verifies the performance of this guidance law with the impact of harmonic wind. The simulation results demonstrate that the quality of effectiveness as well as the applicability of this proposed algorithm.

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“…A function which represents the transition from Oxz coordinate to x 0 x 1 z 1 coordinate is given in (2).…”

Section: Equation Of Motionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

An Optimal Algorithm for Midcourse Guidance Law Under Wind Disturbance

Nguyen¹,

Nguyen²

2020

AJAE

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“…The issues arising from the trajectory prediction error implicit in the basic proportional navigation guidance law (PNG) were addressed. Singular perturbation control approach was applied to the midcourse guidance problem in [9]- [11]. The analytical design of kappa guidance laws based on simplifying approximations and the linear optimal control theory was presented in [12], [13].…”

Section: Introductionmentioning

confidence: 99%

Three-Dimensional Guidance Method With Course Modification for Altitude Shaping in Endoatmospheric Interception

Cho

2023

IEEE Trans. Aerosp. Electron. Syst.

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“…[6][7][8] An optimal control problem is always converted to a two-point boundary value problem (TPBVP). 9 Gauss pseudospectral method (GPM) is well-known to deal with the TPBVP by transforming the problem into solving a set of linear algebraic equations. Indirect Legendre pseudospectral method (ILPM), which obviates the need for solving the time-intensive backward integration of the matrix Riccati differential equation, was firstly proposed by Fahroo and Ross.…”

Section: Introductionmentioning

confidence: 99%

Cooperative near-space interceptor mid-course guidance law with terminal handover constraints

Zhang

Tang

Guo

2018

Proceedings of the Institution of Mechanical Engineers, Part G:

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A cooperative problem in mid-course guidance phase is addressed in this paper. For providing suitable initial conditions of successful terminal salvo attack, a novel finite-time cooperative mid-course guidance law with terminal handover constraints is proposed. Firstly, a three-dimensional guidance model of mid-course is decoupled in a planar line-of-sight frame as a two-point boundary value problem. The terminal handover constraints which can guarantee an ideal zero effort terminal engagement are proposed and analyzed. Secondly, the design of the cooperative mid-course guidance law is separated into two stages. The acceleration commands along the line-of-sight direction are developed based on the finite-time average-consensus protocol and super-twisting algorithm in the first stage. In the second stage, the model predictive static programming method is adopted to solve the two-point boundary value problem in line-of-sight frame with a known final time from first stage. Furthermore, sliding mode control theory is used in combination with model predictive static programming method to satisfy terminal handover constraints with bounded perturbation. Finally, numerical simulations of two four-interceptor cooperative scenario are carried out to verify the validity of the proposed cooperative guidance law. The simulation results reflect that all the four interceptors can reach their own predictive interception points with specific approach angles simultaneously.

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Practical Aspects of Optimal Midcourse Guidance For Air-to-air Engagement

Cited by 6 publications

References 2 publications

An Optimal Algorithm for Midcourse Guidance Law Under Wind Disturbance

An Optimal Algorithm for Midcourse Guidance Law Under Wind Disturbance

Three-Dimensional Guidance Method With Course Modification for Altitude Shaping in Endoatmospheric Interception

Cooperative near-space interceptor mid-course guidance law with terminal handover constraints

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