Space on-orbit refueling self-locking type butt-joint interface device

Abstract

The invention provides a space on-orbit refueling self-locking type butt-joint interface device, and belongs to the technical field of space operation. The device comprises a to-be-injected interfaceand a refueling interface, wherein the refueling interface is located in the center position of a refueling platform at the tail end of a refueling mechanical arm, and the to-be-injected interface islocated on a refueling platform of the outer wall of a to-be-injected spacecraft liquid storage tank. The to-be-injected interface and the refueling interface have self-sealing functions in the processes of pre-refueling introduction, refueling and post-refueling separation, no liquid leakage exists in the whole action process, in addition, a self-locking special structure formed among a steel ball, a refueling interface outer shell and an inner taper sleeve can guarantee reliable locking and smooth separation in the refueling process, the device can achieve double-self-sealing under-pressingrefueling, no liquid leakage and sealing are achieved in the whole process, self-locking is reliable, separation is rapid and safe, the phenomenon of being stuck is avoided, and a large reference value is provided for solving the core problem of interface design in the on-orbit refueling field.

Description

technical field [0001] The invention relates to a docking interface device used in aerospace, belonging to the technical field of space operations. Background technique [0002] On-orbit refueling refers to the on-orbit operation of using the service spacecraft to supply propellant to the target spacecraft in space orbit, that is, to supply gas and liquid for spacecraft such as satellites and space stations. Its function is similar to that of an aerial refueling machine. This is one of the important components of the space on-orbit service operation technology system. After the traditional spacecraft is launched into orbit, the propellant and its component modules are solidified, which will cause some problems: First, after the initial propellant is exhausted, even if other systems can still work normally, The service life of the spacecraft is coming to an end; second, in order to save propellant and prolong the service life in orbit, the maneuverability of the spacecraft i...

AI Technical Summary

Problems solved by technology

After the traditional spacecraft is launched into orbit, the propellant and its component modules are solidified, which will cause some problems: First, after the initial propellant is exhausted, even if other systems can still work normally, The service life of the spacecraft is coming to an end; second, in order to save propellant and prolong the service life in orbit, the maneuverability of the spacecraft is often limited, so it must be used vigorously; third, as a large system, a key component of the spacecraft After the failure, the whole star will not work, which is embarrassing

[0009] Application Publication No. CN104058109A Chinese patent "a kind of liquid transmission interface for satellite in-orbit autonomous filling" design scheme has the following problems: the structure is complex, and due to the use of The solution is to squeeze the steel ball into the groove and lock it through an approximately flat retaining ring, and remove the retaining ring to unlock and release it. If it is separated under the action of force, it will be stuck, that is to say, the driving plane type The translational movement of the retaining ring to realize the unlocking force cannot overcome the force of the retaining ring being stuck

This design mechanism is cumbersome, bulky, and the transmission efficiency is not high, and it has high requirements for the machining accuracy of the screw.

[0016](3) There is a reverse stroke gap in the screw drive, and every time it is reversed and unlocked, it will contact the thread and key that match the same screw and nut with the keyway The same place causes repeated impacts and is prone to fatigue cracks

[0017](4) only considers the sealing problem at the moment of filling after the connection is established, and does not consider the filling introduction process, filling separation process, and liquid sealing after filling separation Therefore, there is a phenomenon of liquid splash leakage in the pipeline

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