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Robust Reentry Guidance of a Reusable Launch Vehicle Using Model Predictive Static Programming

Halbe, Omkar and Raja, Ramsingh G and Padhi, Radhakant (2014) Robust Reentry Guidance of a Reusable Launch Vehicle Using Model Predictive Static Programming. In: JOURNAL OF GUIDANCE CONTROL AND DYNAMICS, 37 (1). pp. 134-148.

jl_gui_con_dyn_37-1_134_2014.pdf - Accepted Version

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Official URL: http://dx.doi.org/10.2514/1.61615


A robust suboptimal reentry guidance scheme is presented for a reusable launch vehicle using the recently developed, computationally efficient model predictive static programming. The formulation uses the nonlinear vehicle dynamics with a spherical and rotating Earth, hard constraints for desired terminal conditions, and an innovative cost function having several components with associated weighting factors that can account for path and control constraints in a soft constraint manner, thereby leading to smooth solutions of the guidance parameters. The proposed guidance essentially shapes the trajectory of the vehicle by computing the necessary angle of attack and bank angle that the vehicle should execute. The path constraints are the structural load constraint, thermal load constraint, bounds on the angle of attack, and bounds on the bank angle. In addition, the terminal constraints include the three-dimensional position and velocity vector components at the end of the reentry. Whereas the angle-of-attack command is generated directly, the bank angle command is generated by first generating the required heading angle history and then using it in a dynamic inversion loop considering the heading angle dynamics. Such a two-loop synthesis of bank angle leads to better management of the vehicle trajectory and avoids mathematical complexity as well. Moreover, all bank angle maneuvers have been confined to the middle of the trajectory and the vehicle ends the reentry segment with near-zero bank angle, which is quite desirable. It has also been demonstrated that the proposed guidance has sufficient robustness for state perturbations as well as parametric uncertainties in the model.

Item Type: Journal Article
Additional Information: copyright for this article belongs to AMER INST AERONAUTICS ASTRONAUTICS, 1801 ALEXANDER BELL DRIVE, STE 500, RESTON, VA 22091-4344 USA
Department/Centre: Division of Mechanical Sciences > Aerospace Engineering(Formerly Aeronautical Engineering)
Date Deposited: 27 May 2014 11:37
Last Modified: 28 May 2014 05:42
URI: http://eprints.iisc.ac.in/id/eprint/49054

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