The invention relates to a non-cooperative target satellite-rocket docking ring capturing mechanism and a capture method thereof. The invention solves the problems of low integration, large volume, heavy weight and low tolerance, and long capture time of the existing non-cooperative target docking ring capturing mechanism. The non-cooperative target satellite-rocket docking ring capturing mechanism adopts a motor to directly drive the ball screw shaft to drive the screw nut fixed on the adapter to carry out linear motion. A low end of that adapter and the capture fin forms a swivel pair through the needle bearing assembly. An upper support housing needle roller bearing assembly is placed in the middle of the positioning groove of the capture finger. The upward and downward motion of the adapter makes the capturing finger to complete the opening and closing motion, and accomplish the capture of the non-cooperative target. The stroke switch and the stroke switch signal acquisition boardare used to control the opening and closing of the capture finger. The invention is applicable to the capture of the satellite-arrow butt joint ring, and has the advantages of small volume, large tolerance, high connection rigidity, short capture time and the like.

A non-cooperative target satellite-rocket docking ring capturing mechanism and a capture method thereof

A conic rod stretching expansion mechanism based on two-way spiral groove drive comprises a guide barrel (1), a stretching expansion mechanism (001) and a supporting seat (20). The front end of the stretching expansion mechanism (001) is installed in the guide barrel (1), the rear end is installed in the supporting seat (20), and the front end conducts stretching motion along the inner wall of theguide barrel (1) under the power drive effect. Two-way spiral groove drive design is adopted, drive is simple, and actions are accurate and reliable; conic rod stretching and expansion actions do notneed reverse drive, high-speed operation can be conducted, and a target is quickly captured; and the structure is compact, the locating accuracy is high, the conic rod stretching expansion mechanismis suitable for a capture mechanism of a tail end executive device, the conic rod stretching expansion mechanism is applied to a high-orbit satellite universal capture device, a target satellite engine throat pipe can be reliably captured multiple times, and the conic rod stretching expansion mechanism also can serve as a locking mechanism used after accurate alignment conducted by a space dockingmechanism accurate alignment device.

Conic rod stretching expansion mechanism based on two-way spiral groove drive

The invention relates to a mechanical-electric-heat integrated isomorphism interface facing modularized spacecraft multi-face docking. The speed of a motor is reduced and the torque of the motor is increased through a speed reducer, an output shaft is connected with an output shaft connecting sliding block through an output shaft key and a sliding block groove, and the output shaft connecting sliding block is fixed through a shaft end face baffle and a fixing screw; a mode that a hollow threaded rod is connected with internal threads is adopted for mechanical locking, conic chamfers are arranged on the end faces of the threaded rod and a threaded barrel for docking fault tolerance, and the thread count of spiral lines of the threads is equal to the number of docking angles. The isomorphisminterface has the beneficial effects that a threaded rod and threaded hole connecting mode is adopted by the isomorphism interface, effective locking and fixing are achieved, the threaded rod is controlled to stretch and retract according to task requirements, installation under a multi-face docking condition is achieved, meanwhile, various types of interfaces are distributed axially symmetrically, and docking at multiple installation angles is allowed; and the interface is simple in structure and can meet the requirements of medium-small modularized spacecrafts for high reliability, large fault tolerance, quick replacement and low cost of the docking interface.

Mechanical-electric-heat integrated isomorphism interface facing modularized spacecraft multi-face docking

The invention discloses a spatial non-cooperative target capturing mechanism and method. Existing capturing mechanisms cannot adapt to docking interfaces of different sizes, thereby being low in capturing success rate. A first motor drives a first-stage screw, a first nut and the first-stage screw form a spiral pair, a lifting platform is fixed to the first nut, a central bearing barrel is fixed on the base, a sliding barrel fixedly sleeves outside the lifting platform, the sliding barrel and the inner wall of the central bearing barrel form a sliding pair, a supporting platform is fixed to the lifting platform, and a second stepped sleeve is fixed on the supporting platform through a second fixed supporting seat; a second motor drives a second-stage screw, a second nut and the second-stage screw form a spiral pair, a top platform sleeves outside the second-stage screw and is fixed to a second stepped sleeve, the tail end of a first connection rod is hinged to the top platform, and themiddle of a second connection rod is hinged to the second nut while the tail end of the same is hinged to the middle of the first connection rod. The spatial non-cooperative target capturing mechanism can adapt to the docking interfaces different in size.

Spatial non-cooperative target capturing mechanism and method

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Spatial non-cooperative target capturing mechanism and method