Rapid Optimal Multiburn Ascent Planning and Guidance

Lu, Ping; Griffin, Brian J.; Dukeman, Gregory A.; Chavez, Frank R.

doi:10.2514/1.36084

Cited by 81 publications

(27 citation statements)

References 10 publications

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“…For guidance inside the atmosphere, numerous methods have been developed and studied. Further details can found in the references [6][7][8][9][10]. However, for exo-atmospheric guidance, the PEG approach still remains as the basis for modification and improvement.…”

Section: Review Of Exo-atmospheric Guidance Methodsmentioning

confidence: 99%

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Pseudospectral Model Predictive Control for Exo-atmospheric Guidance

Rahman¹,

Zhang²,

Yang³

et al. 2015

International Journal of Aeronautical and Space Sciences

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This paper suggests applying pseudospectral model predictive method for exo-atmospheric guidance. The method is a fusion of pseudospectral law and model predictive control, in which a two point boundary value problem is formulated using model predictive approach and solved by applying pseudospectral law. In this work, the method is applied to exo-atmospheric guidance with specific target requirement. The existing exo-atmospheric guidance methods suffice general requirements for guidance, but cannot ensure specific target constraints; whereas, the presented method is able to do so. The proposed guidance law is assessed through simulation of perturbed cases, and the tests suggest that the method is able to operate semiautonomously under control and thrust vector perturbations.

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Section: Review Of Exo-atmospheric Guidance Methodsmentioning

confidence: 99%

“…Substituting the control relation in the state equation, the TPBVP can be stated as 6 The optimal control is then…”

Section: (11)mentioning

confidence: 99%

Pseudospectral Model Predictive Control for Exo-atmospheric Guidance

Rahman¹,

Zhang²,

Yang³

et al. 2015

International Journal of Aeronautical and Space Sciences

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“…In Ref. 12, both heads-up ascent case and heads-down ascent case are discussed independently. In this paper, the two cases are combined in the same formulation by introducing a sign function…”

Section: Iiia2 Treat α and Bank Angle σ As Control Variablesmentioning

confidence: 99%

“…12, this problem would require a total of 58 user-supplied initial guesses, covering the state and costate at the beginning of each burn or coast arc (except for the initial state at lift off), and the times for burn and coast arcs of the second stage. With the current automated generation of initial guesses, only a guessed total flight time is the sole user-provided initial guess.…”

Section: Numerical Demonstrationmentioning

confidence: 99%

Improvements to Optimal Launch Ascent Guidance

Pan

2010

AIAA Guidance, Navigation, and Control Conference

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This paper presents enhancements for optimal endo-and exo-atmospheric ascent guidance. For 3-dimensional endo-atmospheric ascent, based on analysis of the necessary conditions for the optimal solution, the costate equations are formulated differently as compared to previous work. This change considerably simplifies the vector costate equations, and more importantly, helps avoid a potential numerical difficulty the previous formulation can encounter when the angle of attack is zero. For optimal exo-atmospheric ascent problems with multi-burn and -coast arcs, multiple-shooting methods have proven to be effective. But a main difficulty has been the generation of initial guesses for the burn times, coast times and the state and costate at the beginnings and ends of all the burn and coast arcs. In this paper an algorithm is developed to automate the solution process for such a problem with arbitrary given number of multi-burn and coast arcs, without the need for user-supplied initial guesses. These developments are demonstrated with numerical experiments.

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“…This approximation enables simple analytical solution to the costate equation and has proven to be very useful in closed-loop guidance applications where the solution is repeatedly computed based on current state and any effect due to inaccurate gravity model is greatly reduced. 5,7 Note that the linear gravity model in Eq. (5) is only used in developing the guidance solution in this paper, not for simulating the trajectory.…”

Section: Optimal Ascent Problemmentioning

confidence: 99%

A Versatile Powered Guidance Algorithm

Forbes

Baldwin

2012

AIAA Guidance, Navigation, and Control Conference

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A versatile and flexible optimal guidance algorithm for upper stages of launch vehicles is presented in this paper. Closed-form solution for the optimal state trajectory is obtained for 3-dimensional powered flight over a spherical Earth under a linear gravity simplification. The algorithm is applicable to any missions with terminal conditions expressible as equality constraints on the final position and velocity vectors. Furthermore, a coast arc can be inserted between any two powered stages for improving the performance in terms of the injected mass (or reduction of propellant consumption), and the optimal duration of the coast will be determined reliably by the algorithm. Compared to the representative existing exo-atmospheric powered guidance software, the applicability of this algorithm is much broader, and no restrictive approximations or empirical conditions are used.

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Rapid Optimal Multiburn Ascent Planning and Guidance

Cited by 81 publications

References 10 publications

Pseudospectral Model Predictive Control for Exo-atmospheric Guidance

Pseudospectral Model Predictive Control for Exo-atmospheric Guidance

Improvements to Optimal Launch Ascent Guidance

A Versatile Powered Guidance Algorithm

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