TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
Online ISSN : 2189-4205
Print ISSN : 0549-3811
ISSN-L : 0549-3811
Dynamic Inversion Controller Design for Balloon-Launched Supersonic Aircraft
Tetsujiro NINOMIYAHirokazu SUZUKIJun’ichiro KAWAGUCHI
Author information
JOURNALS FREE ACCESS

2018 Volume 61 Issue 6 Pages 248-257

Details
Abstract

While balloon launch is one of the most cost-efficient ways to realize a supersonic flight experiment, it presents some issues for the controller. D-SEND#2 is one flight experiment of this kind which was carried out in 2015. An unpowered test vehicle was lifted to an altitude of 30 km by a balloon and then released. After separation, the vehicle's onboard flight control computer selected a target Boom Measurement System (BMS) according to the separation point. The vehicle then autonomously flew to the BMS selected and established the prescribed sonic boom measurement flight conditions. The design of the guidance, navigation, and control system for the D-SEND#2 flight test was exceptionally challenging, and it was solved by a combination of a sophisticated guidance law and a control law based on dynamic inversion and time scale separation. This paper describes a controller design method for a balloon-launch flight experiment and applied it to a D-SEND#2 control system design. Flight results are presented to show the effectiveness of the controller design method.

Information related to the author
© 2018 The Japan Society for Aeronautical and Space Sciences
Previous article Next article
feedback
Top