The invention relates to an aircraft three-axis attitude control system and method. The system comprises a continuous jet device, a circulation control device and a synthetic jet device, the continuous jet device is arranged at the nose position of the aircraft; the continuous jet device is used for providing yaw attitude control; the circular rector control devices are arranged on the inner side and the outer side of the rear edge of a wing of the aircraft; the circular rector control device is used for providing lift augmentation and pitching attitude control and providing rolling attitude control; the synthetic jet devices are arranged at the front edges of wings on the two sides of the aircraft; and the synthetic jet device is used for providing lift augmentation and pitching attitude control through symmetric excitation, and is also used for providing rolling attitude control through asymmetric excitation. The attitude control of the aircraft can be realized, and the stability of the aircraft is improved.
本发明涉及一种飞行器三轴姿态控制系统及方法。该系统包括连续射流装置、环量控制装置和合成射流装置;所述连续射流装置设置在飞行器的机头位置;所述连续射流装置用于提供偏航姿态控制;所述环量控制装置设置在飞行器的机翼后缘内侧和外侧;所述环量控制装置用于提供增升及俯仰姿态控制和提供滚转姿态控制;所述合成射流装置设置在飞行器的两侧机翼前缘;所述合成射流装置用于通过对称激励提供增升及俯仰姿态控制,还用于通过非对称激励提供滚转姿态控制。本发明能够实现飞行器的姿态控制,并且提高飞行器的稳定性。
Aircraft three-axis attitude control system and method
一种飞行器三轴姿态控制系统及方法
2022-04-08
Patent
Elektronische Ressource
Chinesisch
IPC: | B64C AEROPLANES , Flugzeuge |
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