JPH03231100A - Joining device - Google Patents

Abstract

PURPOSE:To improve the joint fuculty by installing a plurality of electromagnets on the peripheral part of the joint part of one space navigation body and installing a plurality of permanent magnets on the peripheral part of the other space navigation body, in a joint device for joining at least two space navigation bodies. CONSTITUTION:A plurality of electric magnets 1 and a plurality of opposed electric power sources 6 are installed on one space navigation body 10 to be joined, and the supplied electric current to the electromagnet 1 can be controlled by a control circuit 5. Further, the other space navigation body 11 is equipped with a plurality of permanent magnet bodies 2 at the position opposed to the positions of a plurality of the electromagnets 1. Further, probes 3 and 4 which are meshed each other are installed at the center parts of the space navigation bodies 10 and 11. Both the space navigation bodies 10 and 11 are attracted by the magnetic forces of the electromagnet 1 and the permanent magnet body 2 by the introduction by the probes 3 and 4, and both the navigation bodies 10 and 11 are joined. In this case, the connection speed and the joint force can be adjusted by controlling the electric conduction to the electromagnet 1, and the generation of shock is prevented.

Description

DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to a coupling device for a spacecraft, and more particularly to a coupling device using magnetic force.

[Conventional technology]

A conventional coupling device connects a probe 23 (P
robe), Drogue 2 to the other spacecraft 22
4 (Drogue), and a method of mechanically coupling the spacecraft 21 and the spacecraft 22 by the force of the attitude control system and propulsion system, or a non-impact type coupling shown in the perspective view of Fig. 3. There is a method, such as a method in which the boom 25 (Room) of the spacecraft 21A captures the other spacecraft (not shown) using the clara pull mechanism 26, and then the boom 25 is retracted and coupled.

[Problem to be solved by the invention]

In the conventional coupling device described above, in the case of the impact type coupling device shown in FIG. 2, a large force is required for latching, and it is essential that the impact force be absorbed by the damper 27, and the mechanical parts are It has the disadvantage of being complicated. In addition, in the case of the non-impact type coupling device shown in Figure 3, the impact force can be ignored, so there is no need for a damper, but a boom and a mechanism for extending the boom, a clara-pull mechanism, are required, and similarly mechanical parts are required. It has the disadvantage of being complicated.

[Means to solve the problem]

The coupling device of the present invention is a coupling device for coupling at least two spacecraft, in which a plurality of electromagnets are provided around the coupling portion of one spacecraft, and a plurality of electromagnets are provided around the coupling portion of the other spacecraft. A plurality of permanent magnetic bodies are provided at positions opposite to the positions of the plurality of electromagnets.

〔Example〕

Next, the present invention will be explained with reference to the drawings. FIG. 1 is a block diagram of one embodiment of the present invention. A plurality of electromagnets 1 and a plurality of corresponding power supplies 6 are attached to the spacecraft 10, and a control circuit 5 controls the current supplied to the electromagnets. On the other hand, a permanent magnetic body 2 is attached to the spacecraft 11. This coupling operation is performed by the spacecraft 10.
While adjusting the alignment of the spacecraft 10.11, a probe 3 and a drogue 4 are provided at the center of the spacecraft 10.11, respectively, so that the electromagnet 1 and the permanent magnetic body 2 are coupled together. A plurality of them are arranged on the outside of the circumference of No. 11. Spacecraft 10.11 approaches by attitude propulsion to a distance where magnetic force becomes effective, electromagnet 1 and permanent magnetic body 2
They are attracted and connected by their mutual magnetic force. Here, the coupling speed and coupling force can be freely changed by the control circuit 5 to achieve coupling with a gentle impact.

〔Effect of the invention〕

As explained above, the present invention can easily change the coupling force by attaching a simple electromagnet, a control circuit for controlling magnetic force, and a permanent magnetic body to a spacecraft.Furthermore, since a plurality of electromagnets are attached, alignment Can be adjusted,
The binding rate can also be changed freely. This has the effect that the impact force at the time of coupling is small and stable coupling of spacecrafts is possible.

[Brief explanation of drawings]

FIG. 1 is a block diagram of one embodiment of the present invention, FIG. 2 and FIG.
The figure is a perspective view of a conventional coupling device. DESCRIPTION OF SYMBOLS 1... Electromagnet, 2... Permanent magnetic material, 3... Probe, 4... Drogue, 5... Control circuit, 6... Power supply, 1011... Spacecraft.

Claims (1)

[Claims] 1. In a coupling device for coupling at least two spacecraft, a plurality of electromagnets are provided around the coupling portion of one spacecraft, and the coupling portion of the other spacecraft is provided with a plurality of electromagnets. A coupling device characterized in that a plurality of permanent magnetic bodies are provided at positions facing the plurality of electromagnets around the periphery of the coupling device. 2. The electromagnet of the one spacecraft is magnetized by the output current of the power supply circuit controlled by the control circuit, and is coupled to the permanent magnetic body of the other spacecraft with arbitrary coupling speed and force. 2. The coupling device according to claim 1.