CN108945531A - Small-sized satellite in orbit captures docking mechanism - Google Patents

Abstract

The invention relates to a small-sized in-orbit satellite capture and docking mechanism, which consists of an internal gear, a pinion, a stepping motor, a rotating conical frame, a needle bearing, a conical frame, a block, a roller, a guide rail, a damping spring, Ring support frame, electromagnet and other components. A stepper motor powers the parent star capture mechanism through an internal meshing internal gear connected with a pinion. The baffle is installed on the rotating conical frame connected with the needle roller bearing and the parent star conical frame, so that the functions of locking and opening can be realized. The link-type spring buffer device is composed of rollers, guide rails and shock-absorbing springs, and is connected to the ring-shaped support frame welded on the inner surface of the sub-star tapered frame. When the link-type spring buffer device is compressed into the groove, the ring-shaped The supporting frame can play a supporting role against the elastic force of the shock absorbing spring. By switching on and off the three pairs of electromagnets evenly distributed on the inner and outer surfaces of the conical frame of the parent star and the conical frame of the child star, the functions of close fitting and open separation of the parent star and the child star can be realized.

Description

Small in-orbit satellite capture and docking mechanism

technical field

The invention relates to a small on-orbit satellite capturing and docking mechanism.

Background technique

With the development of aerospace technology, the autonomous in-orbit service of small satellites has gradually become a hot spot in the development of aerospace in the world, so the space capture and docking mechanism plays a vital role. At present, there are mainly three types of docking mechanisms on spacecraft: the cone-rod docking mechanism, which pulls the two satellites closer and locks them through a series of transmission and expansion devices; the isomorphic peripheral docking mechanism, which uses the same mechanical structure to complete Satellite capture and docking tasks; the trident docking mechanism, with the help of three grabbing hooks and three wedge-shaped openings, achieves a strong capture and docking function. Although the above-mentioned docking mechanisms can well complete the function of space capture and docking, these docking mechanisms mainly serve large spacecraft and satellites, and have complex structures, large volume and mass, and high manufacturing costs, so they are not suitable for on-orbit service of small satellites.

Contents of the invention

The purpose of the present invention is to provide a small in-orbit satellite capture and docking mechanism.

The basic technical scheme is: the small-sized on-orbit satellite capture and docking mechanism consists of internal gear, pinion, stepper motor, rotating conical frame, needle roller bearing, parent star conical frame, baffle, roller, guide rail, shock absorbing spring , sub-star tapered frame, ring support frame, electromagnet. The internal gear and the pinion are meshed with each other to form a pair of internal gears, which provide power for the parent star capture mechanism through a stepping motor. The rotating conical frame is connected with the mother star conical frame through the needle bearing, and the rotating conical frame is supported by the needle bearing. The baffle is installed at the end of the circle of the rotating tapered frame, and the baffle can be rotated to achieve the functions of locking and opening. Rollers, guide rails and damping springs together constitute a link-type spring buffer device, which is connected to a ring-shaped support frame welded on the inner surface of the sub-star tapered frame. When the link-type spring buffer device is compressed into When in the groove, the annular support frame can play a supporting role against the elastic force of the shock absorbing spring. Three pairs of electromagnets are evenly distributed on the inner and outer surfaces of the conical frame of the parent star and the conical frame of the child star. By switching on and off the power of the electromagnet, the functions of close fitting and open separation of the parent star and the child star can be realized.

The advantages of the present invention are:

1. The structure of this mechanism is simple, the layout is compact and the installation is convenient. At the same time, the mass and volume of the satellite are greatly reduced. It is very suitable for the capture and docking of small satellites in orbit.

2. The capture mechanism has a certain ability to restore the alignment, and can complete the capture task without a high-precision control system to control the docking attitude.

3. The docking mechanism has a certain buffering and shock-absorbing effect, which can reduce the vibration and impact generated when the satellite docks and collides, thereby improving the reliability and safety of satellite docking.

Description of drawings

Below in conjunction with accompanying drawing this mechanism is further described.

Attached Figure 1: Schematic Diagram of Capture Mechanism

Attached Figure 2: Schematic Diagram of Capture Docking Mechanism

Figure 3: Sectional view of the internal gear

Attached Figure 4: Sectional view of the baffle rotation

Attached Figure 5: Sectional view of the connecting rod spring buffer device

In the figure: 1 internal gear, 2 pinion gear, 3 stepping motor, 4 rotating conical frame, 5 needle roller bearing, 6 parent star conical frame, 7 stopper, 8 roller, 9 guide rail, 10 shock absorbing spring , 11 sub-star tapered racks, 12 ring support frames, 13 electromagnets.

Detailed ways

The specific structure and implementation mode of the present invention will be further described below in conjunction with the accompanying drawings.

The structural composition of the present invention is as shown in Fig. 1, Fig. 2, Fig. 3, Fig. 4 and Fig. 5 . The small on-orbit satellite capture and docking mechanism consists of an internal gear (1), a pinion (2), a stepping motor (3), a rotating conical frame (4), a needle roller bearing (5), and a mother star conical frame (6 ), retaining plate (7), roller (8), guide rail (9), damping spring (10), sub-star tapered frame (11), annular support frame (12), and electromagnet (13). The internal gear (1) and the pinion (2) mesh with each other to form a pair of internal gears, which transmit power to the parent star capture mechanism through the stepping motor (3). The rotating conical frame (4) is connected with the parent star conical frame (6) through the needle bearing (5), and supports the rotating conical frame (4) by means of the needle bearing (5). The baffle (7) is installed at the end of the circle of the rotating conical frame (4), and the baffle (7) can be rotated to achieve the functions of locking and opening. Rollers (8), guide rails (9) and damping springs (10) together constitute a link-type spring buffer device, and the link-type spring buffer device and the ring support frame welded on the inner surface of the sub-star cone frame (11) (12) are connected, when the connecting rod type spring buffer device is compressed into the groove, the annular support frame (12) can play a supporting role against the elastic force of the shock absorbing spring. Three pairs of electromagnets (13) are evenly distributed on the inner and outer surfaces of the parent star conical frame (6) and the sub star conical frame (11). Star's tight fit with open separation features.

Working process of the present invention is as follows:

When the mother star is docked with the child star, first the child star cone frame (11) enters the inside of the mother star cone frame (6), and the three pairs of link springs distributed on the circumference of the child star cone frame The buffer device gradually contacts with the inner wall of the parent tapered frame (6), and the rollers (8), guide rails (9) and damping springs (10) are slowly compressed into the slot. Then when the parent star and the child star reach a certain distance, the three pairs of electromagnets (13) installed on the two stars are energized to make the mother star and the child star closely fit together; at this time, the stepping motor (3) works, The power is transmitted to the block (7) through the internal gear (1), pinion (2) and rotating conical frame (4), the block (7) turns from the open state to the closed state, and the electromagnet (13) is powered off , Complete the two-star locking work. Finally, when the mother star and the child star are about to be separated, the electromagnet (13) is energized, and the mother star and the child star are closely attached; the stepping motor (3) rotates in the opposite direction, through the internal gear (1), the pinion gear (2) And rotate the tapered frame (4) to transmit power to the catch (7), and the catch (7) turns to the open state from the closed state; at this moment, the electromagnet (13) is powered off, and the work of the two stars breaking away is completed.

Claims (1)

1. a kind of small-sized satellite in orbit captures docking mechanism, by internal gear, pinion gear, stepper motor, rotation conic frame, needle roller Bearing, female star taper rack, baffle, roller, guide rail, damping spring, component taper rack, ring holder, electromagnet composition, It is characterized by: internal gear and pinion gear are intermeshed, a pair of of inside engaged gear is constituted, is female star catching machine by stepper motor Structure provides power；Rotation conic frame is connected by needle bearing with female star taper rack, by needle bearing, to rotation conic Frame plays a supportive role；Baffle is mounted on rotation conic frame circumferential end, and baffle can be realized locking and be opened with rotational angle Function；Roller, guide rail and damping spring collectively form link-type spring bumper, link-type spring bumper and welding In component, the ring holder of taper rack inner surface is connected, when link-type spring bumper is compressed into slot, annular Support frame can play resist damping spring elastic force supporting role, while a series of spring-damp system can prevent docking when Excessively violent vibration is generated, ensure that the stability in docking operation；Three pairs of electromagnet are respectively uniformly distributed in female star taper Fitting closely for female star and component may be implemented by the power on/off of electromagnet in the surfaces externally and internally of rack and component taper rack The function isolated with opening, female star and component all use the surfaces externally and internally of taper, ensure that the reliability of two stars docking range.