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专利的详细说明本专利是有关控制飞行器的飞行姿态或者飞行轨迹的飞行器液压舵机装置。如图1所示,以前上述液压舵机装置的主要部件蓄压器1及作动器(操舵机构)2在飞行器里由于火箭发动机3所处的位置的关系,一般地是将其分别设置在火箭发动机3的前后,上述的主要部件1和2之间是用导管4来连接的。把火箭发动机3前面蓄压器1的高压油输送到在火箭发动机3后面的操舵机构2里。
Detailed Description of the Patents The present patent relates to an aircraft hydraulic steering gear device for controlling the flight attitude or flight path of an aircraft. As shown in FIG. 1, the pressure accumulator 1 and the actuator (steering mechanism) 2, which are the main components of the above-described hydraulic steering gear system, have been conventionally provided in the aircraft on the basis of the position of the rocket motor 3 Before and after the rocket motor 3, the main components 1 and 2 described above are connected by a duct 4. High pressure oil in front of the rocket motor 3, accumulator 1, is delivered to the steering gear 2 behind the rocket motor 3.