Design of Guidance and Control System for Manned Spaceplane Accommodating Variation in Dynamic Characteristics and Failure
| Project/Area Number |
20560740
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| Research Category |
Grant-in-Aid for Scientific Research (C)
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| Allocation Type | Single-year Grants |
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| Section | 一般 |
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| Research Field |
Aerospace engineering
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| Research Institution | Nihon University |
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Principal Investigator |
SHIMADA Yuzo Nihon University, 理工学部, 教授 (90060235)
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| Co-Investigator(Renkei-kenkyūsha) |
ABE Akio 日本大学, 理工学部, 助教 (60434114)
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| Project Period (FY) |
2008 – 2010
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| Project Status |
Completed (Fiscal Year 2010)
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| Budget Amount *help |
¥4,030,000 (Direct Cost: ¥3,100,000、Indirect Cost: ¥930,000)
Fiscal Year 2010: ¥650,000 (Direct Cost: ¥500,000、Indirect Cost: ¥150,000)
Fiscal Year 2009: ¥650,000 (Direct Cost: ¥500,000、Indirect Cost: ¥150,000)
Fiscal Year 2008: ¥2,730,000 (Direct Cost: ¥2,100,000、Indirect Cost: ¥630,000)
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| Keywords | 宇宙往還機 / 有人宇宙輸送システム / 回収技術 / 飛行制御 / 適応制御 / 耐故障制御 / 外乱オブザーバ / フィードバック線形化 / パラメトリックな適応制御 / 非パラメトリックな適応制御 / ブィードバック線形化 / ロバスト制御 / 突風外乱 / 外乱適応オブザーバ / 線形化 |
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| Research Abstract |
Two types of adaptive control law were studied with the aim of improving the reliability of manned space transportation. One is a novel nonparametric approach and the other is a conventional parametric approach. On the basis of the first approach, a flight control system was designed by combining disturbance observers and a feedback linearization technique. A numerically simulated automatic landing on a runway was successfully carried out using the data of a space shuttle orbiter. In the second method, lateral directional motion was adapted to design a minimum phase system, and its effectiveness was confirmed by numerical simulation with a disturbance observer. A fault-tolerant control law was also developed so that a flight performance can be maintained, even if one or two actuators among the five control surfaces break down.
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Report
(4 results)
Research Products
(26 results)
