A rotary separation spring actuating device

Abstract

The invention discloses a rotating separation spring actuating device, which relates to the field of launch vehicle fairing separation, and comprises a sleeve and an operating part, the lower end of the sleeve is open, an upper hinge is arranged above the sleeve, and the The upper end of the sleeve is movably connected with the upper hinge, and the lower hinge is provided below the sleeve; the action part includes a separation spring, a slider and a push rod located inside the sleeve, and the separation spring The upper end is abutted against the inner top surface of the sleeve, the lower end is abutted against the upper end surface of the slider to drive the slider to move along the axial direction of the sleeve, and the upper end of the push rod is abutted against the slider. The lower end face protrudes outward from the sleeve through the opening at the lower end of the sleeve, and the lower end of the protruding part is flexibly connected with the lower hinge. The present invention has simple overall structure, large actuating distance, can be arranged in groups in the circumferential direction of the fairing, and has reliable actuation and little disturbance of posture.

Description

technical field [0001] The invention relates to the field of separation of launch vehicle fairings, in particular to a rotating separation spring actuating device. Background technique [0002] As a simple structure and reliable separation power device, the spring actuated device is widely used in aerospace vehicles. At the same time, since the action direction of the spring is a straight line, it is specifically used in axial separation, such as the separation of satellites and rockets, the axial separation of fairings, and the like. [0003] When the fairing is rotated and separated, the spring actuating device is often installed on the top of the fairing, and the spring compressed between the two half-covers is used to push the two half-covers to rotate and separate. Due to the small space on the top of the fairing, the number of actuating devices that can be arranged is limited, resulting in a large spring force of a single spring, which brings difficulties to the half-...

AI Technical Summary

Problems solved by technology

Due to the small space on the top of the fairing, the number of actuating devices that can be arranged is limited, resulting in a large spring force of a single spring, which brings difficulties to the half-cover docking; at the same time, when the actuating device is installed on the top, the spring actuating distance is also relatively long Small, in the case of overload separation, it is not conducive to the smooth rotation of the half cover through a fixed angle, and may even cause the opened half cover to close again, and this arrangement, the position of the actuator acting on the fairing will also As the fairing rotates and changes continuously, the size of the rotating arm of the two half-covers is different, resulting in inconsistent separation speeds of the two half-covers, causing certain disturbances to the attitude of the rocket body

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