Initial virtual flight test for a dynamically similar aircraft model with control augmentation system |
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Authors: | Guo Linliang Zhu Minghong Nie Bowen Kong Peng Zhong Chengwen |
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Institution: | 1. School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China;2. Low Speed Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China |
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Abstract: | To satisfy the validation requirements of flight control law for advanced aircraft, a wind tunnel based virtual flight testing has been implemented in a low speed wind tunnel. A 3-degree-of-freedom gimbal, ventrally installed in the model, was used in conjunction with an actively con-trolled dynamically similar model of aircraft, which was equipped with the inertial measurement unit, attitude and heading reference system, embedded computer and servo-actuators. The model, which could be rotated around its center of gravity freely by the aerodynamic moments, together with the flow field, operator and real time control system made up the closed-loop testing circuit. The model is statically unstable in longitudinal direction, and it can fly stably in wind tunnel with the function of control augmentation of the flight control laws. The experimental results indicate that the model responds well to the operator's instructions. The response of the model in the tests shows reasonable agreement with the simulation results. The difference of response of angle of attack is less than 0.5°. The effect of stability augmentation and attitude control law was validated in the test, meanwhile the feasibility of virtual flight test technique treated as preliminary evaluation tool for advanced flight vehicle configuration research was also verified. |
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Keywords: | 3-degree-of-freedom gimbal Dynamic test Flight dynamics simulation Flight control system Real time Wind tunnel |
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