The invention discloses a rotary servo thruster and an attitude control system, and belongs to the technical field of aircraft propulsion, the rotary servo thruster comprises a first connecting piece, a first accommodating ring and a second accommodating ring are arranged on the first connecting piece side by side, a steering assembly is arranged in the first accommodating ring, and a driving assembly is arranged in the second accommodating ring; the steering assembly comprises a driving mechanism arranged in the first direction, and an output shaft of the driving mechanism is connected with a driving gear. The driving assembly comprises a first shell, a fuel gas inlet is formed in the first shell in the first direction, a fuel gas outlet is formed in the first shell in the second direction, the first shell is sleeved with an outer gear ring, and the driving gear is rotationally meshed with the outer gear ring. According to the rotary servo thruster, attitude control of the aircraft is achieved by correspondingly adjusting the thrust direction and the thrust magnitude of the rotary servo thruster, the overall mass of an existing aircraft attitude control system is greatly reduced, the number of arranged thrusters is reduced, and the reliability of attitude control is improved.
本发明公开了一种旋转伺服推力器及姿态控制系统,属于飞行器推进技术领域,包括第一连接件,第一连接件上并排开设第一容置环和第二容置环,第一容置环内设有转向组件,第二容置环内设有驱动组件,转向组件包括沿第一方向布置的驱动机构,驱动机构的输出轴连接驱动齿轮;驱动组件包括第一壳体,第一壳体沿第一方向设有燃料进气口,沿第二方向设有燃料出气口,第一壳体外部套设外齿圈,驱动齿轮与外齿圈转动啮合。本申请中的旋转伺服推力器,其通过对应调整旋转伺服推力器的推力方向和推力大小,实现飞行器的姿态控制,极大降低了现有飞行器姿态控制系统的整体质量,减少推力器布置数量,提高姿态控制的可靠性。
Rotary servo thruster and attitude control system
一种旋转伺服推力器及姿态控制系统
2024-03-08
Patent
Electronic Resource
Chinese
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