Energy Based Suboptimal Reentry Guidance of a Reusable                                                         Launch Vehicle Using Model Predictive Static Programming

Halbe, Omkar; Mathavaraj, S.; Padhi, Radhakant

doi:10.2514/6.2010-8311

Cited by 5 publications

(4 citation statements)

References 8 publications

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“…(Luo et al, 2007a) and the application of model predictive static programming (MPSP). The approach by (Luo et al, 2007a) centers around posing an SQP problem as a linear complimentarity problem, while the principle behind MPSP is to combine MPC and approximate dynamic programming though a parametric optimization formulation (Halbe et al, 2014(Halbe et al, , 2010Chawla et al, 2010). (van Soest et al, 2006;Recasens et al, 2005) corroborate the effectiveness of MPCbased approaches by comparing the performance of constrained MPC with that of PID control applied to feedback-linearized reentry flight.…”

Section: Atmospheric Entrymentioning

confidence: 92%

Advances in Trajectory Optimization for Space Vehicle Control

Malyuta¹,

Yu²,

Elango³

et al. 2021

Preprint

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Space mission design places a premium on cost and operational efficiency. The search for new science and life beyond Earth calls for spacecraft that can deliver scientific payloads to geologically rich yet hazardous landing sites. At the same time, the last four decades of optimization research have put a suite of powerful optimization tools at the fingertips of the controls engineer. As we enter the new decade, optimization theory, algorithms, and software tooling have reached a critical mass to start seeing serious application in space vehicle guidance and control systems. This survey paper provides a detailed overview of recent advances, successes, and promising directions for optimization-based space vehicle control. The considered applications include planetary landing, rendezvous and proximity operations, small body landing, constrained attitude reorientation, endo-atmospheric flight including ascent and reentry, and orbit transfer and injection. The primary focus is on the last ten years of progress, which have seen a veritable rise in the number of applications using three core technologies: lossless convexification, sequential convex programming, and model predictive control. The reader will come away with a well-rounded understanding of the state-of-the-art in each space vehicle control application, and will be well positioned to tackle important current open problems using convex optimization as a core technology.

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Section: Atmospheric Entrymentioning

confidence: 92%

Advances in Trajectory Optimization for Space Vehicle Control

Malyuta¹,

Yu²,

Elango³

et al. 2021

Preprint

View full text Add to dashboard Cite

show abstract

“…In the energy management problem for the hypersonic vehicle with SRB in the ascent phase, we assume that the height curve is a Bézier curve. Now we can use the starting and ending states to calculate the control point ( 9), (10). Assuming the starting point of the Bézier curve is the current state, and the ending point is the desired terminal state, we can get…”

Section: Bézier Spline Guidance Methodsmentioning

confidence: 99%

“…The subscript '0' represents the initial moment in the current guidance cycle. Taking the first derivative of the height into consideration, and letting it equal to the derivative of the Bézier curve in (10), we can get…”

Section: Bézier Spline Guidance Methodsmentioning

confidence: 99%

“…Therefore, the MPSP is easy to implement with the vehicle-borne computational device, manifesting high accuracy and sufficient online computation efficiency. It is thus widely used in guidance law design for different missions, such as reentry guidance law design, 10,11 and moon soft landing guidance. 12,13 Maity et al 14,15 used the MPSP method to design guidance law for solid rocket vehicles launching into the high orbit.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Ascent adaptive energy management method for solid rocket‐powered hypersonic vehicle under uncertainties

Liu

Wang

et al. 2023

Adaptive Control & Signal

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Summary The solid rocket booster is widely used in the launch mission for hypersonic vehicles nowadays, whose ascent energy management is still a challenging problem due to the inherent dynamic nonlinearity. This paper casts the problem into an equivalent ascent guidance one and proposes a model predictive static programming (MPSP) based solution. The MPSP‐based method is a computationally efficient solver that adapts to different energy demands while guaranteeing the satisfaction of terminal constraints. To further improve the performance of MPSP in this problem, a Bézier spline guidance method is proposed to generate high‐quality reference trajectories such that the MPSP can converge with high accuracy while satisfying the real‐time requirement. Additionally, an online parameter estimation based on the extended Kalman filter is employed to avoid large terminal state deviations incurred by parametric uncertainties during the Bézier curve computation and linearization in MPSP. Numerical simulations with different hard terminal constraints and uncertainties are conducted to demonstrate the effectiveness and robustness of the proposed algorithm. The simulation results show that our proposed algorithm can guide the hypersonic vehicle to a given terminal state under uncertainties and outperforms several existing ascent energy management methods.

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Designing a closed-loop guidance system to increase the accuracy of satellite-carrier boosters' landing point

Tavakoli

Novinzadeh

2018

Aerospace Science and Technology

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Energy Based Suboptimal Reentry Guidance of a Reusable Launch Vehicle Using Model Predictive Static Programming

Cited by 5 publications

References 8 publications

Advances in Trajectory Optimization for Space Vehicle Control

Advances in Trajectory Optimization for Space Vehicle Control

Ascent adaptive energy management method for solid rocket‐powered hypersonic vehicle under uncertainties

Designing a closed-loop guidance system to increase the accuracy of satellite-carrier boosters' landing point

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