DLR-Logo -> http://www.dlr.de
DLR Portal Home | Imprint | Privacy Policy | Contact | Deutsch
Fontsize: [-] Text [+]

Vector Field-based Guidance Development for Launch Vehicle Re-entry via Actuated Parafoil

Fari, Stefano and Grande, Davide (2021) Vector Field-based Guidance Development for Launch Vehicle Re-entry via Actuated Parafoil. In: Proceedings of the International Astronautical Congress, IAC. 72th International Astronautical Congress, 25-29 Oct 2021, Dubai, United Arab Emirates. ISSN 0074-1795.

[img] PDF

Official URL: https://iafastro.directory/iac/paper/id/66968/summary/


In this paper, a launch vehicles re-entry strategy using an actuated parafoil is analyzed. In recent years, this concept is gaining new momentum: it offers a lightweight and cost-effective control solution for autonomous landing of reusable rockets to specific ground or sea coordinates, as well as for mid-air capturing. This landing maneuver requires appropriate modeling together with suitable guidance and control strategies. This work expands upon the following aspects: (1) the development of suitable models for control synthesis and verification; (2) the design of heading control system; (3) the application of a path-following guidance law capable of steering the payload (i.e. the launch vehicle) to the prescribed end-of-mission point. Three models of increasing complexity are proposed based on different assumptions and the dynamics are compared in an ad-hoc simulation environment. MATLAB-Simulink is employed to design two versions of a 6 Degrees Of Freedom (DOF) model accounting for distinct aerodynamic effects. On the other hand, the multi-physics object-oriented language Modelica is used to develop a higher-fidelity 9DOF dynamic model of the system. The latter is then compiled and embedded within MATLAB-Simulink. The same environment allows the implementation of the designed Guidance and Control (G&C) algorithms. The G&C architecture comprises both low-level control loops, regulating course andyaw angles by means of differential steering commands onto the canopy strings, and a guidance layer where the VF path-following is employed. VF methods have already shown remarkable results for fixed-wing unmanned vehicles due to the lower steady-state errors as compared to other approaches, while retaining the potential for real-time implementation. With this work, the method is extended to the application of a launcher recovery. The results of the simulations are investigated, highlighting overall satisfactory performance even in presence of wind disturbances.

Item URL in elib:https://elib.dlr.de/145123/
Document Type:Conference or Workshop Item (Speech)
Title:Vector Field-based Guidance Development for Launch Vehicle Re-entry via Actuated Parafoil
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Fari, StefanoUNSPECIFIEDhttps://orcid.org/0000-0001-5595-6905UNSPECIFIED
Grande, DavideUNSPECIFIEDhttps://orcid.org/0000-0002-4936-6797UNSPECIFIED
Date:25 October 2021
Journal or Publication Title:Proceedings of the International Astronautical Congress, IAC
Refereed publication:No
Open Access:Yes
Gold Open Access:No
In ISI Web of Science:No
Keywords:Launch vehicle re-entry, Parafoil, Vector Field path-following, Modelica, Multi-body modeling
Event Title:72th International Astronautical Congress
Event Location:Dubai, United Arab Emirates
Event Type:international Conference
Event Dates:25-29 Oct 2021
Organizer:International Astronautical Federation
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Space
HGF - Program Themes:Space Transportation
DLR - Research area:Raumfahrt
DLR - Program:R RP - Space Transportation
DLR - Research theme (Project):R - Reusable Space Systems and Propulsion Technology
Location: Bremen
Institutes and Institutions:Institute of Space Systems > Navigation and Control Systems
Deposited By: Fari, Stefano
Deposited On:03 Nov 2021 09:25
Last Modified:29 Nov 2021 09:03

Repository Staff Only: item control page

Help & Contact
electronic library is running on EPrints 3.3.12
Website and database design: Copyright © German Aerospace Center (DLR). All rights reserved.