JAXA Repository / AIREX 未来へ続く、宙(そら)への英知
titleD-SEND#2の制御系設計
Other TitleController design for D-SEND#2
DOIinfo:doi/10.20637/JAXA-RR-17-011/0001
Author(jpn)二宮, 哲次郎; 鈴木, 広一; 川口, 純一郎
Author(eng)Ninomiya, Tetsujiro; Suzuki, Hirokazu; Kawaguchi, Junichiro
Author Affiliation(jpn)宇宙航空研究開発機構航空技術部門飛行技術研究ユニット(JAXA); 宇宙航空研究開発機構研究開発部門第一研究ユニット(JAXA); 宇宙航空研究開発機構航空技術部門飛行技術研究ユニット(JAXA)
Author Affiliation(eng)Flight Research Unit, Aeronautical Technology Directorate, Japan Aerospace Exploration Agency (JAXA); Research Unit I, Research and Development Directorate, Japan Aerospace Exploration Agency (JAXA); Flight Research Unit, Aeronautical Technology Directorate, Japan Aerospace Exploration Agency (JAXA)
Issue Date2017-02-22
Publisher宇宙航空研究開発機構(JAXA)
Japan Aerospace Exploration Agency (JAXA)
Publication title宇宙航空研究開発機構研究開発報告
JAXA Research and Development Report
VolumeJAXA-RR-17-011
Start page1
End page50
Publication date2017-02-22
Languagejpn
eng
AbstractD-SENDプロジェクトは, ソニックブームの低減をするための空力設計技術を飛行実証するための飛行実験である. #2では, 有翼機体を高層気球を用いて高度約30kmから分離し, 地上に設置したソニックブーム計測システム(BMS)にてソニックブームを計測することを目的にしている. 気球より落下させるため、不確定な分離位置からBMSを目指して飛行し, 計測するタイミングに合わせて各種飛行条件を設定条件に合致させることが要求される. 本稿では, このような要求を満足するための制御系設計について報告する.
D-SEND is a project to demonstrate a low sonic boom aerodynamic design concept. In the #2 part of this project, an unpowered test vehicle is lifted to an altitude of 30km by a balloon from which it then separates. After separation, the vehicle's on-board flight control computer selects a target Boom Measurement System (BMS) according to the separation point. The vehicle then autonomously flies to the selected BMS and establishes prescribed sonic boom measurement flight conditions. The design of the GNC system for D-SEND#2 project is exceptionally challenging since 1) there is no nominal trajectory, 2) there is only limited control available to meet the requirements, 3) the required test conditions are difficult to achieve, and 4) the flight envelope is quite wide. The dynamic inversion method and time-scale separation technique are applied to deal with these problems. This paper describes the D-SEND#2 control system design in detail which solves these problems.
Description形態: カラー図版あり
Physical characteristics: Original contains color illustrations
KeywordsFlight test; Guidance and Control; Dynamic Inversion
Document TypeTechnical Report
JAXA Category研究開発報告
NASA Subject CategoryAircraft Communications and Navigation
ISSN(online)2433-2216
SHI-NOAA1730020000
Report NoJAXA-RR-17-011
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/872393


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