Guidance Law for an Air-Breathing Launch Vehicle Using Predictive Control Concept

Brinda, V.; Dasgupta, S.

doi:10.2514/1.23221

Cited by 9 publications

(4 citation statements)

References 5 publications

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“…The optimization is performed in a non-linear method by Vincent and Grantham (1997) and Brinda and Dasgupta (2005). Control optimization is carried out by Lu et al (2003) and Brinda and Punnoose (2007) and the trajectory design dynamic optimization has been carried out by Betts (1998), Betts and Huffman (1993) and Ross et al (2003). In this paper, according to Maani et al (2013;, the orbital trajectory optimization has been carried out with three major differences; that are the solution method, reality of orbital mission and integration with the system design.…”

Section: Introductionmentioning

confidence: 99%

A Multi-Step Sequential System Optimization Design Method for Upper Stages

Bohlouri

Zakeri

Nosratollahi

2023

J. Aerosp. Technol. Manag.

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This paper proposes a new approach in multi-step sequential system optimization (MSSO) to implement a conceptual design for satellite upper stage with a maneuver in the conditions close to reality. In this method of design, there are two main cycles; trajectory optimization cycle and optimal design cycle, each one is correlated to each other in another cycle called configuration. In the trajectory optimization, the optimization objective is to place the upper stage in the destination orbit, using the minimum amount of fuel consumption. In this cycle, a new approach has been introduced for a three-dimensional trajectory using two genetic algorithms inside each other. In addition, selecting the suitable engine is carried out in this cycle. Convergence of design and exclusion of design are carried out in the configuration cycle. Convergence and optimization of subsystems design are carried out in the optimal design cycle. The innovations of this paper are implementation of the design according to multi-step sequential system design in which optimization is performed step by step, and orbital optimization is introduced according to a new approach. Choosing a desirable criterion for optimization process and proper coefficient for convergence in design, are among considerable characteristics of this paper. Validation has been performed using one of the upper stages in the world.

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Section: Introductionmentioning

confidence: 99%

A Multi-Step Sequential System Optimization Design Method for Upper Stages

Bohlouri

Zakeri

Nosratollahi

2023

J. Aerosp. Technol. Manag.

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“…Proportional navigation (PN) and its variants build the basis of guidance laws used in modern tactical and strategic missiles [2]. When the dynamic models of missile and target are available, the predictive guidance law can relax the requirements for interceptor acceleration when intercepting manoeuvering targets [3]. However, the target acceleration is hard to be estimated precisely in practical applications.…”

Section: Introductionmentioning

confidence: 99%

Finite time sliding sector guidance law with acceleration saturation constraint

Zhou

2016

IET Control Theory & Applications

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“…Up to now, several reentry control based on MPC for hypersonic vehicles has been designed. 10–12 In van Soest et al., 10 feedback linearization and constrained model predictive control were combined to design control for a hypersonic vehicle. In Christopher et al., 11 the control system consists of an outer-loop guidance layer and an inner-loop flight control layer and, for the outer loop, a model predictive control approach is pursued to prescribe the desired bank angle and flight path angle commands.…”

Section: Introductionmentioning

confidence: 99%

“…However, system constraints of hypersonic vehicles were never considered in Brinda and Dasgupta. 12 Though system constraints were considered in van Soest et al. 10 and Christopher et al., 11 weak robustness and calculation complexity limits their application in reality.…”

Section: Introductionmentioning

confidence: 99%

Disturbance observer-based sliding manifold predictive control for reentry hypersonic vehicles with multi-constraint

Jun

Sun

2015

Proceedings of the Institution of Mechanical Engineers, Part G:

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The presence of system strong constraints and large uncertainties in reentry hypersonic vehicles deteriorate the system performance. This paper considers disturbance observer-based sliding manifold predictive control design for a reentry hypersonic vehicle. In the outer loop, a new sliding manifold-based predictive control is proposed to realize reference command tracking. In the inner loop, a nonlinear disturbance observer is adopted to estimate lumped disturbances and a sliding manifold-based predictive control is designed to track the expected signal obtained from the outer loop. The use of sliding manifolds and disturbance observer enhance the control system’s robustness to uncertainties. The mode predictive control approach guarantees the satisfaction of the system constraints. The effectiveness of the proposed algorithm is verified by theoretical analysis and simulations.

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Guidance Law for an Air-Breathing Launch Vehicle Using Predictive Control Concept

Cited by 9 publications

References 5 publications

A Multi-Step Sequential System Optimization Design Method for Upper Stages

A Multi-Step Sequential System Optimization Design Method for Upper Stages

Finite time sliding sector guidance law with acceleration saturation constraint

Disturbance observer-based sliding manifold predictive control for reentry hypersonic vehicles with multi-constraint

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