阅读说明：本技术 一种空间在轨可更换模块机电热一体化接口装置 (Electromechanical and thermal integrated interface device of space on-orbit replaceable module ) 是由 孔宁 庄原 任杰 韩润奇 马帅 刘育强 张�杰 刘希刚 张立元 王耀兵 于 2020-04-07 设计创作，主要内容包括：本发明提供一种空间在轨可更换模块机电热一体化接口装置,属于空间在轨可更换模块技术领域。该发明包括主动端与被动端两个模块,主动端包括圆壳、传动轴、锁紧卡爪、热交换输出面、电连接器插接口、导向锥杆、视觉摄像头预置槽、紧定螺钉、齿轮传动组及中心轴,被动端包括导向锥孔、热交换接收面、电连接器接收槽及中心锁紧杆。本发明可以实现在轨可更换模块在大容差下的可靠对接、轴向拉近锁紧,从而完成机械连接分离、能源通信传输、热量传导的机电热一体化协同对接,布局扁平、紧凑的锁紧机构一定程度上为模块提供了较大的可用内部空间,提高了模块的有效负载。(The invention provides an electromechanical and thermal integrated interface device of a space on-orbit replaceable module, and belongs to the technical field of space on-orbit replaceable modules. The device comprises an active end and a passive end, wherein the active end comprises a round shell, a transmission shaft, a locking claw, a heat exchange output surface, an electric connector jack, a guide taper rod, a visual camera preset groove, a set screw, a gear transmission group and a central shaft, and the passive end comprises a guide taper hole, a heat exchange receiving surface, an electric connector receiving groove and a central locking rod. The invention can realize reliable butt joint and axial drawing locking of the rail replaceable module under large tolerance, thereby completing mechanical-electrical-thermal integrated cooperative butt joint of mechanical connection separation, energy communication transmission and heat conduction, providing a larger available internal space for the module to a certain extent by a locking mechanism with flat and compact layout, and improving the effective load of the module.)

1. A space on-orbit replaceable module electromechanical and thermal integrated interface device is characterized in that: comprises an active end (1) and a passive end (2), wherein the active end (1) comprises a round shell (3), a transmission shaft (4), a locking claw (5), a heat exchange output surface (6), an electric connector interface (7), a guide taper rod (8), a vision camera preset groove (9), a set screw (10), a gear transmission set (11), a stud (12) and a central shaft (13), the passive end (2) comprises a guide taper hole (14), a heat exchange receiving surface (15), an electric connector receiving groove (16) and a central locking rod (17), the locking claw (5), the set screw (10), the gear transmission set (11), the stud (12) and the central shaft (13) are positioned in the round shell (3), a motor is connected with the transmission shaft (4), the locking claw (5) is positioned on the stud (12), the electric connector interface (7) and the vision camera preset groove (9) are respectively positioned at two sides of the heat exchange output surface (6), the guide taper rods (8) are distributed at four corners of the butt joint surface of the driving end (1), the guide taper holes (14) are distributed at four corners of the butt joint surface of the driven end (2), the electric connector receiving grooves (16) are positioned at two sides of the heat exchange receiving surface (15), and the central locking rod (17) is positioned at the center of the butt joint surface of the driven end (2).

2. The space-on-orbit replaceable module mechatronic-thermal integrated interface device of claim 1, wherein: the motor and the transmission shaft (4) transmit torque through a gear transmission set (11).

3. The space-on-orbit replaceable module mechatronic-thermal integrated interface device of claim 1, wherein: the gear transmission set (11) is positioned on the transmission shaft (4) and the stud (12) and meshed with each other, and a central large gear of the gear transmission set (11) is positioned on the central shaft (13).

4. The space-on-orbit replaceable module mechatronic-thermal integrated interface device of claim 1, wherein: the locking claw (5) is connected with the stud (12) through a thread pair.

5. The space-on-orbit replaceable module mechatronic-thermal integrated interface device of claim 1, wherein: the round shell (3) is connected with the end face of the driving end (1) through a set screw (10) and a stud (12).

6. The space-on-orbit replaceable module mechatronic-thermal integrated interface device of claim 1, wherein: the guide taper rod (8) and the driving end (1) are integrally formed, the body part of the guide taper rod (8) is cylindrical, the bottom of the guide taper rod is conical, the diameter of the bottom of the guide taper rod is larger than that of the body part, and the bottom of the guide taper rod (8) contains a sensor.

7. The space-on-orbit replaceable module mechatronic-thermal integrated interface device of claim 1, wherein: the guide taper hole (14) is connected with the butt joint surface of the driven end (2) through a screw.

8. The space-on-orbit replaceable module mechatronic-thermal integrated interface device of claim 1, wherein: the diameter of the head part of the central locking rod (17) is larger than that of the body part.

Technical Field

The invention relates to the technical field of space on-orbit replaceable modules, in particular to an electromechanical and thermal integrated interface device of a space on-orbit replaceable module.

Background

In recent years, autonomous on-orbit services have become a reality due to advances in technologies such as space robots and space rendezvous and docking. The autonomous on-orbit service technology can realize the on-orbit services such as the replacement and the upgrade of a target spacecraft receiving module, but also puts higher requirements on the serviceability of the target spacecraft.

An on-orbit service-oriented modular spacecraft is also gradually a research hotspot in the international aerospace field, and the modular spacecraft generally requires interfaces with unified standards, such as mechanical, energy, communication, thermal control and the like, between modules and the spacecraft and between modules and space robots, and the modules have the characteristics of being replaceable, easy to operate, plug and play and the like.

Before launching, the spacecraft needs to adopt a series of measures for improving the reliability, such as higher requirements on elements, adoption of a redundant design, selection of relatively mature parts, mature technology and the like, and the structure has redundant locking capacity, so that although the reliability is improved, the complexity of an interface is improved to a certain extent, the weight of a module is further increased, and the available space in the module is greatly reduced.

Disclosure of Invention

The invention provides a space on-orbit replaceable module electromechanical-thermal integrated interface device, aiming at solving the problems that the on-orbit replaceable module is axially pulled close and locked in a flat and narrow space so as to complete mechanical connection separation, energy communication transmission, electromechanical-thermal integrated cooperative docking of heat conduction and the like.

The device comprises an active end and a passive end, wherein the active end comprises a round shell, a transmission shaft, a locking claw, a heat exchange output surface, an electric connector interface, a guide taper rod, a visual camera preset groove and a set screw, the gear transmission set, the stud and the central shaft, the driven end comprises a guide taper hole, a heat exchange receiving surface, an electric connector receiving groove and a central locking rod, the locking clamping jaws, the set screw, the gear transmission set, the stud and the central shaft are positioned in the round shell, the motor is connected with the transmission shaft, the locking clamping jaws are positioned on the stud, an electric connector plug interface and a vision camera preset groove are respectively positioned on two sides of the heat exchange output surface, the guide taper rods are distributed on four corners of the active end butt joint surface, the guide taper holes are distributed on four corners of the driven end butt joint surface, the electric connector receiving groove is positioned on two sides of the heat exchange receiving surface, and the central locking rod is positioned in.

The motor and the transmission shaft transmit torque through the gear transmission set.

The gear transmission set is positioned on the transmission shaft and the stud and meshed with each other, and the central gearwheel of the gear transmission set is positioned on the central shaft.

The locking claw is connected with the stud through a thread pair.

The round shell is connected with the end face of the driving end through a set screw and a stud.

The guide taper rod and the driving end are integrally formed, the body part of the guide taper rod is cylindrical, the diameter is small, a coarse guide effect is achieved, the bottom of the guide taper rod is conical, the diameter is large, a fine guide effect is achieved, and the bottom of the guide taper rod is provided with a sensor.

The guide taper hole is connected with the passive end butting surface through a screw.

The diameter of the head part of the central locking rod is larger than that of the body part.

The technical scheme of the invention has the following beneficial effects:

the invention realizes accurate butt joint under the control of visual shooting by using the rough and fine guiding of the guiding taper rod, and has the advantages of small occupied space, high guiding precision, convenient detection control and the like.

Drawings

FIG. 1 is a schematic structural diagram of an electromechanical-thermal integrated interface device of a space on-track replaceable module according to the present invention;

FIG. 2 is an exploded view of the active end structure of the on-orbit replaceable module mechatronic interface device of the present invention;

fig. 3 is a schematic diagram of a passive end structure of the space on-track replaceable module mechatronic interface device according to the present invention.

Wherein: the method comprises the following steps of 1-driving end, 2-driven end, 3-round shell, 4-transmission shaft, 5-locking claw, 6-heat exchange output surface, 7-electric connector plug socket, 8-guide conical rod, 9-vision camera preset groove, 10-set screw, 11-gear transmission group, 12-stud, 13-central shaft, 14-guide conical hole, 15-heat exchange receiving surface, 16-electric connector receiving groove and 17-central locking rod.

Detailed Description

In order to make the technical problems, technical solutions and advantages of the present invention more apparent, the following detailed description is given with reference to the accompanying drawings and specific embodiments.

The invention provides an electromechanical and thermal integrated interface device of a space on-orbit replaceable module.

As shown in fig. 1, 2 and 3, the device comprises an active end 1 and a passive end 2, the active end 1 comprises a circular shell 3, a transmission shaft 4, a locking jaw 5, a heat exchange output surface 6, an electric connector interface 7, a guide taper rod 8, a vision camera preset groove 9, a set screw 10, a gear transmission set 11, a stud 12 and a central shaft 13, the passive end 2 comprises a guide taper hole 14, a heat exchange receiving surface 15, an electric connector receiving groove 16 and a central locking rod 17, the locking jaw 5, the set screw 10, the gear transmission set 11, the stud 12 and the central shaft 13 are positioned in the circular shell, a motor is connected with the transmission shaft 4, the locking jaw 5 is positioned on the stud 12, the electric connector interface 7 and the vision camera preset groove 9 are respectively positioned at two sides of the heat exchange output surface 6, the guide taper rods 8 are distributed at four corners of the active end 1 surface, the guide taper holes 14 are distributed at four corners of the passive end 2 interface, electrical connector receiving slots 16 are located on either side of the heat exchange receiving face 15 and a central locking bar 17 is located centrally of the mating face of the passive end 2.

In the driving end 1 module, a motor is connected with a transmission shaft 4, torque is transmitted through a gear transmission set 11 which is positioned on the transmission shaft 4 and studs 12 and is meshed with each other, wherein the gear transmission set 11 comprises 4 small gears and 1 large gear, the small gears are respectively fixed on the transmission shaft 4 and three studs 12, the large gears are positioned on a central shaft 13, a locking jaw 5 is positioned on the studs 12, the two are connected through a thread pair, so that the locking jaw 5 can realize two motions of rotation and translation, the locking jaw 5, a set screw 10, the gear transmission set 11, the studs 12 and the central shaft 13 are positioned in a round shell 3, the round shell 3 is connected with the end face of the driving end through the set screw 10 and the studs 12, a guide conical rod 8 and the driving end are integrally formed and distributed on four corners of a butt joint face, the body of the guide conical rod 8 is cylindrical, has a small diameter and plays a role of coarse guiding, the diameter is big, plays accurate guide effect for realize the satellite under wide-angle, radial tolerance mechanical connection part's accurate butt joint, and 8 bottoms on the guide taper pole contain the sensor for relative distance between the real-time supervision satellite, electric connector interface 7, vision camera preset tank 9 are located the both sides of heat exchange output face 6 respectively, and the planar arrangement of electric heat interface provides great space for the mechanism realizes energy communication transmission, heat energy conduction.

In the passive end 2, guiding taper holes 14 are distributed on four corners of a passive end abutting surface and are connected through screws, electric connector receiving grooves 16 are positioned on two sides of a heat exchange receiving surface 15, a central locking rod 17 is positioned in the center of the passive end abutting surface, the diameter of the head part of the central locking rod is larger than that of the body part of the central locking rod, and the central locking rod is used for bearing axial tension and realizing axial closing and locking.

The invention can realize three stages of taper rod guiding, pre-contact locking and axial drawing locking in the butt joint process, and the specific working principle is as follows:

1. a taper rod guiding stage: the mechanical arm clamps the on-orbit replaceable module provided with the driving end 1 under the auxiliary action of the preset groove 9 of the visual camera for butt joint, the locking claw 5 is in an open state integrally at the coarse guiding stage, waiting for the locking rod 17 at the center of the driven end 2 to be in place, and the mechanical arm pushes the driving end 1 to approach the guide taper hole 14 in the feeding mode so that the body part of the guide taper rod 8 enters the guide taper hole 14;

2. pre-contact locking stage: when a sensor at the bottom of the guide conical rod 8 is triggered, the guide stage is finished, the mechanical arm switches the working mode to the follow-up mode, the locking stage is started, the central locking rod 17 of the passive end 2 is in place, then the motor of the active end 1 is started to drive the three gears which synchronously rotate, the gears drive the studs 12 fixedly connected with the gears to rotate, and under the action of friction force, the studs 12 drive the three locking jaws 5 to rotate until the clamping grooves are contacted with the central locking rod 17;

3. and (3) axial pulling and locking: the motor continues to drive the gear transmission set 11, due to the rotation stopping effect of the central locking rod 17, under the effect of the threads of the stud 12, the three locking claws 5 synchronously move downwards to press the end face of the central locking rod 17, under the effect of the pressing force, the bottom of the guide conical rod 8 enters a fine guide stage, the plugging of the plugging port 7 of the electric connector is further realized, the heat exchange ring is tightly attached, and finally on the basis of the locking of the butting interface, the reliable connection of the energy source and the communication interface and the pressure contact of the heat exchange interface are completed, and the electromechanical and thermal integrated transmission of the on-orbit replaceable module is realized.

While the foregoing is directed to the preferred embodiment of the present invention, it will be understood by those skilled in the art that various changes and modifications may be made without departing from the spirit and scope of the invention as defined in the appended claims.