Model predictive control strategy with a decreasing horizon interval for a reusable launcher in a landing scenario
| dc.contributor.author | Zaragoza Prous, Guillermo | |
| dc.contributor.author | Felicetti, Leonard | |
| dc.contributor.author | Grustan Gutierrez, Enric | |
| dc.date.accessioned | 2024-11-25T09:43:10Z | |
| dc.date.available | 2024-11-25T09:43:10Z | |
| dc.date.freetoread | 2024-11-25 | |
| dc.date.issued | 2024-10-18 | |
| dc.date.pubOnline | 2024-10-18 | |
| dc.description.abstract | The descending and landing problem of an Reusable Launch Vehicle (RLV) concerns a wide variety of factors to overcome, such as the instability generated due to the aerodynamic forces during the descent phases and the strict requirements for accurate pinpoint landing to be met with limited control authority. In addition, the Guidance algorithm needs to be continuously and rapidly updated, in order to cope with the dynamically changing conditions that the RLV can experience during the re-entry and landing phase. One of the key technologies being studied to solve this problem is Model Predictive Control (MPC). MPC uses a linearized model of the problem to obtain a solution of the scenario, given a specific landing time in the future, called the prediction horizon (PH). In this paper, a new strategy to manage the PH of an MPC scheme is proposed for the landing scenario of an RLV. This strategy considers an offline predefined interval of PHs to obtain a valid solution instead of a single predefined PH. This strategy guarantees a wider set of feasible solutions to be searched with a Convex Optimization method, increasing the robustness of the algorithm at the guidance stage. A simulation setup is introduced for the landing scenario of an RLV, including full simulation of translational and rotational dynamics, along with the control laws to actuate each of the actuators of the vehicle. The results of the presented algorithm are then shown for the landing scenario of the first stage of a rocket. | |
| dc.description.conferencename | IAC2024 International Astronautical Congress | |
| dc.identifier.citation | Zaragoza Prous G, Felicetti L, Grustan Gutierrez E. (2024) Model predictive control strategy with a decreasing horizon interval for a reusable launcher in a landing scenario. IAC2024 International Astronautical Congress, 14-18 October 2024, Milan, Italy | |
| dc.identifier.elementsID | 559143 | |
| dc.identifier.uri | https://dl.iafastro.directory/event/IAC-2024/paper/84269/ | |
| dc.identifier.uri | https://dspace.lib.cranfield.ac.uk/handle/1826/23213 | |
| dc.language.iso | en | |
| dc.publisher | International Astronautical Federation (IAF) | |
| dc.publisher.uri | https://dl.iafastro.directory/event/IAC-2024/paper/84269/ | |
| dc.rights | Attribution 4.0 International | en |
| dc.rights.uri | http://creativecommons.org/licenses/by/4.0/ | |
| dc.subject | Model Predictive Control | |
| dc.subject | Guidance | |
| dc.subject | Convex Optimization | |
| dc.subject | Reusable Launch Vehicle | |
| dc.subject | Powered Descent Landing | |
| dc.subject | Prediction Horizon | |
| dc.title | Model predictive control strategy with a decreasing horizon interval for a reusable launcher in a landing scenario | |
| dc.type | Conference paper | |
| dcterms.coverage | Milan, Italy | |
| dcterms.dateAccepted | 2024-10-14 | |
| dcterms.temporal.endDate | 18 Oct 2024 | |
| dcterms.temporal.startDate | 14 Oct 2024 |