Trajectory Optimization for Launchers and Re-entry Vehicles

Cremaschi, Francesco

doi:10.1007/978-1-4614-4469-5_7

Cited by 2 publications

(2 citation statements)

References 17 publications

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“…14 It is used, as well, with light modifications, in many ascent trajectory optimization problems. [15][16][17][18] This program consists of a series of specific guidance laws, each to be performed in a determined leg of the trajectory; so, it can also be seen as a way to split the ascent trajectory into phases or arcs. The following guidance laws make up the selected guidance scheme for Vega Light LV.…”

Section: Flight Strategymentioning

confidence: 99%

Integrated Optimization of Ascent Trajectory and SRM Design of Multistage Launch Vehicles

Federici,

Zavoli,

Colasurdo

et al. 2019

Preprint

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This paper presents a methodology for the concurrent first-stage preliminary design and ascent trajectory optimization, with application to a Vega-derived Light Launch Vehicle. The reuse as first stage of an existing upper-stage (Zefiro 40) requires a propellant grain geometry redesign, in order to account for the mutated operating conditions. An optimization code based on the parallel running of several Differential Evolution algorithms is used to find the optimal internal pressure law during Z40 operation, together with the optimal thrust direction and other relevant flight parameters of the entire ascent trajectory. Payload injected into a target orbit is maximized, while respecting multiple design constraints, either involving the alone solid rocket motor or dependent on the actual flight trajectory. Numerical results for SSO injection are presented.

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Section: Flight Strategymentioning

confidence: 99%

Integrated Optimization of Ascent Trajectory and SRM Design of Multistage Launch Vehicles

Federici,

Zavoli,

Colasurdo

et al. 2019

Preprint

View full text Add to dashboard Cite

show abstract

“…The heat flux . q = 1 2 ρv 3 must not exceed the limit of 1135 W/m 2 [5,37] after the fairing jettisoning. An additional restriction, aimed to address the heating damage on the structure, is also included, with a limit of 40 MW/m 2 [35].…”

mentioning

confidence: 98%

Optimization of the Conceptual Design of a Multistage Rocket Launcher

et al. 2022

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The design of a vehicle launch comprises many factors, including the optimization of the climb path and the distribution of the mass in stages. The optimization process has been addressed historically from different points of view, using proprietary software solutions to obtain an ideal mass distribution among stages. In this research, we propose software for the separate optimization of the trajectory of a launch rocket, maximizing the payload weight and the global design, while varying the power plant selection. The launch is mathematically modeled considering its propulsive, gravitational, and aerodynamical aspects. The ascent trajectory is optimized by discretizing the trajectory using structural and physical constraints, and the design accounts for the mass and power plant of each stage. The optimization algorithm is checked against various real rockets and other modeling algorithms, obtaining differences of up to 9%.

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Trajectory Optimization for Launchers and Re-entry Vehicles

Cited by 2 publications

References 17 publications

Integrated Optimization of Ascent Trajectory and SRM Design of Multistage Launch Vehicles

Integrated Optimization of Ascent Trajectory and SRM Design of Multistage Launch Vehicles

Optimization of the Conceptual Design of a Multistage Rocket Launcher

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