Load relief control of launch vehicle using aerodynamic angle estimation

A nonlinear closed-loop load relief scheme is proposed to reduce the aerodynamic load during the ascent phase of a launch vehicle. The proposed controller is designed based on a back-stepping and sliding-mode control scheme with aerodynamic angle feedback. A hybrid load-relief strategy using the loa...

Full description

Saved in:
Bibliographic Details
Published in:Proceedings of the Institution of Mechanical Engineers. Part G, Journal of aerospace engineering Journal of aerospace engineering, 2018-06, Vol.232 (8), p.1598-1605
Main Authors: Oh, Gyeongtaek, Park, Jongho, Park, Jeongha, Lee, Hongju, Kim, Youdan, Shin, Sang-Joon, Ahn, Jaemyung, Cho, Sangbum
Format: Article
Language:English
Subjects:
Aerodynamic loads
Aerodynamics
Aerospace industry
Ascent
Computer simulation
Control
Control systems design
Dynamic pressure
Feedback
Kalman filters
Launch vehicles
Load
Sliding mode control
Vehicles
Citations: Items that this one cites
Items that cite this one
Online Access:Get full text
Tags: Add Tag
No Tags, Be the first to tag this record!
Description
Summary:A nonlinear closed-loop load relief scheme is proposed to reduce the aerodynamic load during the ascent phase of a launch vehicle. The proposed controller is designed based on a back-stepping and sliding-mode control scheme with aerodynamic angle feedback. A hybrid load-relief strategy using the load relief scheme around the period of the maximum dynamic pressure and the traditional minimum-drift scheme during the other period is proposed. An aerodynamic angle estimator is also developed using a Kalman filter for the feedback of the load relief control. Numerical simulation is conducted to demonstrate the performance of the proposed strategy as well as the potential benefits.
ISSN:0954-4100
2041-3025
DOI:10.1177/0954410017699435