Fuel-optimal G-MPSP guidance for powered descent phase of soft lunar landing

Sachan, Kapil; Padhi, Radhakant

doi:10.1109/cca.2015.7320730

Cited by 13 publications

(4 citation statements)

References 6 publications

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“…Note that the weight matrix is alternatively chosen to adjust the magnitude of the control history at different time steps. For the constrained optimal problem defined in equations (20) and (22), static optimization theory is applied, which gives the augmented cost function…”

Section: Angle Constrained Mpsp Guidancementioning

confidence: 99%

“…Afterwards, the state constrained MPSP formulation was tested on an air-to-air engagement scenario. Considering the soft landing problem of a lunar craft during the powered descent phase, Sachan and Padhi [20] proposed a fuel optimal guidance law under the help of G-MPSP, where both terminal position and velocity were satisfied by adjusting the magnitude and angle of thrust. Bringing in sliding mode control, S. Li and X. Li [21] solved the divergence problem of the common MPSP algorithm caused by model inaccuracy; better robustness was proved when applied to maneuvering target interception.…”

Section: Introductionmentioning

confidence: 99%

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Suboptimal Midcourse Guidance with Terminal-Angle Constraint for Hypersonic Target Interception

Wan

Chang

et al. 2019

International Journal of Aerospace Engineering

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For the problem of hypersonic target interception, a novel midcourse guidance method with terminal-angle constraint is proposed. Referring to the air-breathing and the boost-gliding hypersonic targets, flight characteristics and difficulties of interception are analyzed, respectively. The requirements of midcourse guidance for interceptors are provided additionally. The kinematics model of adversaries is established concerning line-of-sight coupling in longitudinal and lateral planes. Suboptimal guidance law with terminal-angle constraint, specifically the final line-of-sight angle or impact angle, is presented by means of model predictive static programming. The trajectory is optimized and the load factor would finally converge after penalizing control sequence and output deviations. The realization of terminal angle is firstly verified with a constant speed target. A full interception scenario is further simulated focusing on a typical boost-gliding target, which flies along a skipping trajectory. Results show the success of providing handover conditions for intercepting hypersonic targets.

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Section: Angle Constrained Mpsp Guidancementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Suboptimal Midcourse Guidance with Terminal-Angle Constraint for Hypersonic Target Interception

Wan

Chang

et al. 2019

International Journal of Aerospace Engineering

View full text Add to dashboard Cite

show abstract

“…Since the thrust engine is usually fixed with the lunar lander's body, the vertical landing introduces a final attitude constraint, which can be represented by the final steering angle [8]. Consequently, there were some attempts to generate the optimal trajectory ending with a vertical landing [1], [2], [15]- [17]. For instance, in [1], the lunar landing trajectory was divided into two parts, with the final steering angle constraint augmented into the cost functional.…”

Section: Introductionmentioning

confidence: 99%

“…By integrating the equations of motion for altitude, velocity magnitude, and time analytically as a function of flight path angle, the thrust vector was used as a parameter to shape the trajectory. In [17], to handle the final steering angle constraint, a time-varying matrix was added to the cost functional, and the resulting optimal control problem was solved via model predictive static programming.…”

Section: Introductionmentioning

confidence: 99%