Load relief control of launch vehicle using aerodynamic angle estimation. (June 2018)

• Record Type: Journal Article
• Authors: Oh, Gyeongtaek; Park, Jongho; Park, Jeongha; Lee, Hongju; Kim, Youdan; Shin, Sang-Joon; Ahn, Jaemyung; Cho, Sangbum
• Is Part Of: Proceedings of the Institution of Mechanical Engineers. Volume 232:Number 8(2018)
• Page Start: 1598
• Page End: 1605
• Publication Date: 2018-06
• Subjects: Launch vehicle -- hybrid load relief control -- angle of attack estimation; Aeronautics -- Periodicals; Astronautics -- Periodicals; Airplanes -- Design and construction -- Periodicals; Aerospace industries -- Periodicals; 629.1
• DOI: 10.1177/0954410017699435
• Languages: English
• ISSNs: 0954-4100

Abstract

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.