| Project/Area Number |
09450370
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| Research Category |
Grant-in-Aid for Scientific Research (B)
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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 | Kyushu University |
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Principal Investigator |
SAKURAI Akira Kyushu University, Dept. Aeronautics and Astronautics, Professor, 工学研究科, 教授 (80037952)
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| Co-Investigator(Kenkyū-buntansha) |
HIGASHINO Shin'ichiro Kyushu University, Dept. Aeronautics and Astronautics, Assisstant Professor, 工学研究科, 講師 (40243901)
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| Project Period (FY) |
1997 – 1999
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| Project Status |
Completed (Fiscal Year 1999)
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| Budget Amount *help |
¥13,400,000 (Direct Cost: ¥13,400,000)
Fiscal Year 1999: ¥2,100,000 (Direct Cost: ¥2,100,000)
Fiscal Year 1998: ¥1,800,000 (Direct Cost: ¥1,800,000)
Fiscal Year 1997: ¥9,500,000 (Direct Cost: ¥9,500,000)
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| Keywords | Flight Testing / Remotely-Piloted Research Vehicle / Aerodynamic Characteristics / Maneuver Design / 無人飛行機 / マヌ-バ設計 |
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| Research Abstract |
It is known that the aerodynamic characteristics estimated from flight data degrade when the parameters, which contribute to the aerodynamic forces and moments, have strong correlations with each other. Physical reasons of this problem were made clear and letting the vehicle maneuver without using original control surfaces was shown to be effective by simulation. A new method to estimate the aerodynamic characteristics using a device named a "flying sting balance", which is a combination of additional control surfaces installed at the end of a boom connected to the tail of a vehicle and load cells at the root of the boom, was proposed, and the usefulness of this device was shown by simulation and flight experiments using an Remotely-Piloted Research Vehicle (RPRV) for longitudinal aerodynamic characteristics.
The flight experiment system had been developed by the authors, and the on-board computer system was expanded in order to control the vehicle for the specific maneuvers and the flights using the flying sting balance. The computer system is composed of off-the-shelf very small and light computer boards on the standard called PC/104. In order to check system malfunction and software bugs on ground, hardware-in-the-loop real time flight simulation was developed as well as the real time software system constructed on the concept of object-oriented programming.
An alternative to the heavy and bulky attitude sensors, a method to estimate the pitch and bank angles for attitude control was developed using accelerometers and low-cost angular rate sensors having drifts. The angles are estimated by filtering out the significant frequency bands of the two combining them.
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