CN111541093A - Electromechanical and thermal integrated interface device of space on-orbit replaceable module - Google Patents

Abstract

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.

Description

A space on-orbit replaceable module electromechanical and thermal integrated interface device

technical field

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

Background technique

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

Modular spacecraft for on-orbit services has gradually become a hot research topic in the international aerospace field. Such modular spacecraft usually requires standard and unified machinery, energy, and equipment between modules and spacecraft, and between modules and space robots. Communication, thermal control and other interfaces, and its modules are replaceable, easy to operate, and plug and play.

Before the launch of the spacecraft, a series of measures to improve reliability should be taken, such as higher requirements for components, redundant design, selection of relatively mature components and mature technologies, etc. The redundant locking capability of the structure may improve reliability. , but to a certain extent, the complexity of the interface is increased, which in turn increases the weight of the module and greatly reduces the available space inside the module.

SUMMARY OF THE INVENTION

In order to solve the problem of realizing the axially pulling and locking form of the on-rail replaceable module in a flat and narrow space, so as to complete the mechanical connection and separation, energy communication transmission, and heat conduction, the electromechanical and thermal integration coordinated docking and the like are provided. Space on-orbit replaceable module electromechanical thermal integration interface device.

The device includes an active end and a passive end. The active end includes a round shell, a transmission shaft, a locking claw, a heat exchange output surface, an electrical connector socket, a guide taper rod, a vision camera preset slot, a set screw, and a gear drive. Set, stud and central shaft, the passive end includes guide taper hole, heat exchange receiving surface, electrical connector receiving groove and central locking rod, locking claw, set screw, gear transmission group, stud and central shaft are located in In the round shell, the motor is connected with the transmission shaft, the locking claw is located on the stud, the electrical connector socket and the visual camera preset slot are respectively located on both sides of the heat exchange output surface, and the guide taper rods are distributed on the active end docking surface. On the four corners, the guide cone holes are distributed on the four corners of the passive end butting surface, the electrical connector receiving grooves are located on both sides of the heat exchange receiving surface, and the central locking rod is located in the center of the passive end butting surface.

The electric motor and the drive shaft transmit torque through the gear transmission group.

The gear transmission group is located on the transmission shaft and meshes with the stud, and the central large gear of the gear transmission group is located on the central shaft.

There is a threaded pair connection between the locking claw and the stud.

The round shell and the end face of the active end are connected by set screws and studs.

The guide cone rod and the active end are integrally formed. The guide cone rod body is cylindrical with a small diameter and plays a role of rough guidance. The bottom is tapered with a large diameter and plays a role of fine guidance. The bottom of the guide cone rod contains a sensor.

The guide taper hole is connected with the abutment surface of the passive end by means of screws.

The diameter of the head of the center locking rod is larger than the diameter of the body.

The beneficial effects of the above-mentioned technical solutions of the present invention are as follows:

The invention utilizes the rough and fine guidance of the guide cone rod to realize the precise docking under the control of visual camera, and has the advantages of small occupied space, high guidance precision, convenient detection and control, and the like.

Description of drawings

1 is a schematic structural diagram of an electromechanical-thermal integrated interface device for a space-on-orbit replaceable module of the present invention;

2 is a schematic exploded view of the active end structure of the space-on-orbit replaceable module electromechanical-thermal integrated interface device of the present invention;

FIG. 3 is a schematic structural diagram of the passive end of the electromechanical-thermal integrated interface device of the space-on-orbit replaceable module of the present invention.

Among them: 1-active end, 2-passive end, 3-round shell, 4-drive shaft, 5-locking claw, 6-heat exchange output surface, 7-electric connector socket, 8-guide taper rod, 9- visual camera preset slot, 10- set screw, 11- gear transmission group, 12- stud, 13- center shaft, 14- guide taper hole, 15- heat exchange receiving surface, 16- electrical connector receiving groove , 17-center locking lever.

Detailed ways

In order to make the technical problems, technical solutions and advantages to be solved by the present invention more clear, the following will be described in detail with reference to the accompanying drawings and specific embodiments.

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

As shown in Figure 1, Figure 2 and Figure 3, the device includes an active end 1 and a passive end 2. The active end 1 includes a round shell 3, a transmission shaft 4, a locking claw 5, a heat exchange output surface 6, and an electrical connector Insertion port 7, guide taper rod 8, visual camera preset slot 9, set screw 10, gear transmission group 11, stud 12 and central shaft 13, passive end 2 includes guide taper hole 14, heat exchange receiving surface 15, electrical The connector receiving slot 16 and the central locking rod 17, the locking claw 5, the set screw 10, the gear transmission group 11, the stud 12 and the central shaft 13 are located in the round shell, the motor is connected with the transmission shaft 4, the locking card The claw 5 is located on the stud 12, the electrical connector socket 7 and the visual camera preset slot 9 are respectively located on both sides of the heat exchange output surface 6, and the guide taper rods 8 are distributed on the four corners of the butting surface of the active end 1, and the guide taper holes 14 are distributed on the four corners of the butt surface of the passive end 2 , the electrical connector receiving grooves 16 are located on both sides of the heat exchange receiving surface 15 , and the central locking rod 17 is located in the center of the butt surface of the passive end 2 .

In the active end 1 module, the motor is connected with the transmission shaft 4, and the torque is transmitted through the gear transmission group 11 which is located on the transmission shaft 4 and the stud 12, and the gear transmission group 11 contains 4 pinions and 1 large gear. The pinion gear is respectively fixed on the transmission shaft 4 and the three studs 12, the large gear is on the central shaft 13, the locking claw 5 is located on the stud 12, and the two are connected by a threaded pair, so that the locking claw 5 can be Two movements of rotation and translation are realized. The locking jaw 5, the set screw 10, the gear transmission group 11, the stud 12, and the central shaft 13 are located in the circular shell 3, and the circular shell 3 and the driving end face pass through the set screw 10. , The studs 12 are connected, the guide taper rod 8 is integrally formed with the active end, and is distributed on the four corners of the butting surface. The guide taper rod 8 is cylindrical with a small diameter and plays a rough guiding role. The bottom is tapered and has a large diameter. , plays the role of precise guidance, and is used to realize the precise docking of the mechanical connection parts of the satellites under large angles and radial tolerances. The bottom of the guide cone 8 contains sensors for real-time monitoring of the relative distance between satellites. The electrical connector plugs The interface 7 and the visual camera preset slot 9 are respectively located on both sides of the heat exchange output surface 6, and the plane arrangement of the electric heating interface provides a large space for the mechanism to realize energy communication transmission and heat energy conduction.

In the passive end 2, the guide taper holes 14 are distributed on the four corners of the passive end butting surface, and are connected by screws, the electrical connector receiving grooves 16 are located on both sides of the heat exchange receiving surface 15, and the central locking rod 17 is located on the passive end butting surface. The diameter of the head of the central locking rod is larger than the diameter of the body, which is used to bear the axial tension and realize the axial pulling and locking.

The invention can realize three stages of taper rod guidance, pre-contact locking, and axial pulling and locking during the docking process, and the specific working principle is as follows:

1. Cone-rod guiding stage: The robotic arm clamps the on-track replaceable module equipped with the active end 1 under the assistance of the vision camera preset slot 9 for docking. In the rough guiding stage, the locking claw 5 is "open" ” state, waiting for the central locking rod 17 of the passive end 2 to be in place, the robotic arm pushes the active end 1 to approach the guide taper hole 14 in the feeding mode, so that the guide taper rod 8 enters the guide taper hole 14;

2. Pre-contact locking stage: When the sensor at the bottom of the guide cone 8 is triggered, the guide stage ends, the manipulator switches from the working mode to the follow-up mode, and enters the locking stage. At this time, the central locking rod 17 of the passive end 2 is closed. After that, the motor of the active end 1 starts to drive three gears that rotate synchronously, and the gears drive the stud 12 fixedly connected to it to rotate. Under the action of friction, the stud 12 drives the three locking claws 5 to rotate until The card slot is in contact with the central locking rod 17;

3. Axial pulling and locking stage: The motor continues to drive the gear transmission group 11. Due to the anti-rotation effect of the central locking rod 17, under the action of the thread of the stud 12, the three locking claws 5 are synchronously downward. Move, press the end face of the central locking rod 17, under the action of the pressing force, the bottom of the guide taper rod 8 enters the fine guiding stage, further realizing the plugging of the electrical connector socket 7 and the tightness of the heat exchange ring, Finally, based on the locking of the docking interface, the reliable connection of the energy and communication interfaces and the pressure contact of the heat exchange interface are completed, realizing the integrated electromechanical and thermal transmission of the on-orbit replaceable module.

The above are the preferred embodiments of the present invention. It should be pointed out that for those skilled in the art, without departing from the principles of the present invention, several improvements and modifications can be made. These improvements and modifications It should also be regarded as the protection scope of the present invention.

Claims (8)

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.

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