Pneumatic shearing unlocking mechanism and application thereof
A technology of an unlocking mechanism and a shear, which is applied in the aerospace field and can solve the problems of long response time, poor reliability, and difficulty in meeting the requirements of the separation task of a launch vehicle for non-pyrotechnical unlocking devices.
Pending Publication Date: 2021-12-10
TAIYUAN UNIVERSITY OF SCIENCE AND TECHNOLOGY +1
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Problems solved by technology
[0004] At this stage, the response time of non-pyrotechnic unlocking devices with sufficient carrying capacity is too long, and it is difficult to meet the requirements of the launch vehicle separation task; the assembly process of the above-mentioned devices is generally complicated and the reliability is poor. The overall structure and layout of the equipment have been greatly adjusted
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[0045] The technical solutions of the present invention will be clearly and completely described below in conjunction with the accompanying drawings and embodiments. Apparently, the described embodiments are only part of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.
[0046] A pneumatic shear unlocking mechanism, which can be applied to the tape separation device at the connection between the spacecraft and the ground launching device, it includes an upper docking ring 1 and a lower docking ring 2, and the upper end surface of the upper docking ring 1 is fixedly installed on the satellite A At the bottom, the lower end surface of the lower docking ring 2 is fixedly arranged on the ground or on the launch base, wherein: as Figure 1~Figure 3 As shown, the up...
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The invention discloses a pneumatic shearing unlocking mechanism and application thereof, and belongs to the technical field of spaceflight; an upper docking ring is arranged above a lower docking ring, the upper end face of the upper docking ring is fixedly installed at the bottom of a satellite A, and the lower end face of the lower docking ring is fixedly arranged on the ground or a launching base; the lower portion of the outer wall of the upper butt-joint ring and the upper portion of the outer wall of the lower butt-joint ring are connected through a belting locking mechanism, a tension spring assembly is arranged between the bottom of the lower butt-joint ring and the belting locking mechanism, and a spring separation assembly is arranged on the upper portion of the inner wall of the lower butt-joint ring. By using the shearing mechanism for replacing an initiating explosive device, a separation task is executed without touch and impact, it is ensured that the effective load enters an orbit independently without interference and executes the task, the locking device has the advantages of being large in locking force and small in unlocking impact, and meanwhile the shearing device can be used for separation of satellites and can also be used for separation of other spacecrafts.
Description
technical field [0001] The invention belongs to the field of aerospace technology, and relates to a non-pyrotechnic unlocking device for a carrier rocket, in particular to a pneumatic shearing unlocking mechanism and its application. Background technique [0002] Tape separation device is the most widely used payload separation mechanism so far. It has the advantages of good connection rigidity, high reliability, and strong bearing capacity. It is mainly composed of tapes, separation elements, V-shaped blocks and tethering devices. When locking, a plurality of straps that are used to connect the separation element and have blocks installed on the inside surround the outer edge of the docking surface between the launch vehicle and the payload, tighten the straps and then lock the nut of the separation element; when unlocking, The separation element works to disconnect or dissociate the connection between the straps, release the docking energy, impact the V-shaped block and th...
Claims
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IPC IPC(8): B64G1/64
CPCB64G1/645
Inventor 同阳张东陈慧琴张登宇张志峰吴会强王婧超郭雷杨楠赵志光王荣军胡季帆田继红
Owner TAIYUAN UNIVERSITY OF SCIENCE AND TECHNOLOGY