JPH04252800A - Separating device for space navigating body - Google Patents

Abstract

(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.

Description

[Detailed description of the invention]

0001

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to spacecraft such as rockets and artificial satellites, and more particularly to a device for separating a plurality of spacecraft that are coupled together in outer space.

0002

2. Description of the Related Art A conventional spacecraft separation device of this type will be described with reference to the drawings. 3 is a longitudinal cross-sectional view of a conventional separation device, FIG. 4 is a cross-sectional view taken along the line B1-B2 in FIG. 3, and FIG. 5 is a cross-sectional view taken along the line C1-C2 in FIG. 4 showing a first conventional example. Moreover, FIG. 6 is a sectional view taken along the line C1-C2 in FIG. 4, showing a second conventional example.

The spacecraft 1 and the spacecraft 2 to be separated are connected by a plurality of V-shaped clamp shoes 4 attached to a pair of bands 3. The pair of bands 3 together with the clamp shoes 4 are tightened around the spacecrafts 1 and 2 at the joint/separation planes, and these are further tightened by separation bolts 8. Space vehicle 2
After separating the separation bolt 8 and releasing the band 3 in order to separate the spacecraft 1 from the spacecraft 1, the band 3 needs to be prevented from impacting the separated spacecraft 1.

Conventionally, as shown in FIG. 5, as a method for preventing this collision, a coil spring-type push-out pin 9 provided on the spacecraft 2 is used to simultaneously separate the separation bolt 8. There is a method of pressing the band 3 and the clamp shoe 4 attached thereto onto the receiving metal fitting 7 that has been placed.

As another method, FIG. 6 shows a method in which the band 3 and the clamp shoe 4 attached thereto are attracted to and held by a coil spring 10 fixed to the receiving fitting 7. ing.

[0006]

[Problems to be Solved by the Invention] The above-described conventional spacecraft separation device disposes a coil spring inside or outside of the separation surface in order to press or attract the band to the receiving metal fitting after separation of the spacecraft. Therefore, there was an implementation constraint that an area had to be secured for this purpose. Furthermore, after the spacecraft was connected, adjustment work was required to set the strength of the coil springs evenly.

[0007]

[Means for Solving the Problems] The spacecraft separation device of the present invention tightens the periphery of a first spacecraft and the periphery of a second spacecraft to be separated at their coupling/separation surfaces. a pair of bands; a plurality of clamp shoes attached to the bands and performing the tightening action;
A separating device for a spacecraft, which includes a separation bolt that connects and separates the first and second spacecraft by tightening and separating the pair of bands; an electromagnet having polarity in the radial direction; a receiving metal fitting provided on the first spacecraft and having a permanent magnet attached thereto at a position facing the clamp shoe with a constant spacing from the band; and the separation bolt. The band includes means for reversing the current direction of the electromagnet at the time of separation to attract the band to the receiving metal fitting.

[0008]

DESCRIPTION OF THE PREFERRED EMBODIMENTS Next, the present invention will be explained with reference to the drawings.

FIG. 1 is a longitudinal sectional view of one embodiment of the present invention. Further, FIG. 2 is a cross-sectional view taken along line A1-A2.

When the spacecraft 1 and the spacecraft 2 to be separated are in a coupled state, the V-shaped groove of the clamp shoe 4 attached to the inside of the band 3 is inserted between the spacecraft 1 and the spacecraft 2. The band 3 is tightened by a separation bolt 8 in accordance with the joint portion of the navigation object 2. The clamp shoe 4 has a built-in electromagnet 5 having a polarity in the radial direction of the separation plane between the spacecraft 1 and the spacecraft 2 (radial direction from the center of the spacecraft 2 indicated by a circle in FIG. 2). has been done. Further, the spacecraft 2 is provided with a receiving metal fitting 7 on a surface facing the band 3, in which permanent magnets 6 are arranged at a constant interval. When the spacecraft 1 and the spacecraft 2 are in a coupled state, the electromagnet 5 is energized in the direction in which it has a repulsive force with the permanent magnet 6, so that the tightening force of the band 3 is not hindered.

[0011] At the same time as separating the separation bolt 8 to separate the spacecraft 1 and the spacecraft 2, the direction of the current applied to the electromagnet 5 is reversed, and the electromagnet 5 has a magnetic force in the direction of attracting the permanent magnet 6. to occur. Due to this magnetic force, the clamp shoe 4 and the band 3 to which it is attached are attracted to the receiving metal fitting 7, and the band 3 is attached to the separated spacecraft 1.
Collision with is avoided.

0012

[Effects of the Invention] As explained above, the spacecraft separation device of the present invention combines an electromagnet built into the clamp shoe of the band that connects the spacecraft and a permanent magnet attached to the receiving bracket of the spacecraft. After the spacecraft is separated, the band and clamp shoe are attracted to the receiving fitting by the magnetic force acting between them. As a result, it is possible to realize a separation device that has a simple structure, eliminates the need to secure an area for arranging the coil spring near the separation surface, and does not require adjustment of the coil spring after setting the band.

[Brief explanation of the drawing]

FIG. 1 is a longitudinal sectional view of an embodiment of a separation device for a spacecraft according to the present invention.

FIG. 2 is a sectional view taken along the line A1-A2 in FIG. 1;

FIG. 3 is a longitudinal cross-sectional view of a conventional spacecraft separation device.

FIG. 4 is a sectional view taken along the line B1-B2 in FIG. 3;

FIG. 5 is a sectional view taken along the line C1-C2 in FIG. 4, showing a first conventional example.

FIG. 6 is a sectional view taken along the line C1-C2 in FIG. 4, showing a second conventional example.

[Explanation of symbols]

1, 2 Spacecraft 3 Band 4 Clamp shoe 5 Electromagnet 6 Permanent magnet 7 Receiving metal fittings 8 Separation bolt 9 Push-out pin 10 Coil spring

Claims (2)

[Claims] 1. A pair of bands for tightening the circumference of a first spacecraft and the circumference of a second spacecraft to be separated at their coupling/separation surfaces, and a pair of bands attached to the bands to exert the tightening action. In the spacecraft separation device, the spacecraft separation device includes a plurality of clamp shoes, and a separation bolt that connects and separates the first and second spacecraft by tightening and separating the pair of bands. and an electromagnet having a polarity in the radial direction of the coupling/separation surface, and a receiver provided on the first spacecraft and having a permanent magnet attached thereto at a position facing the clamp shoe at a constant distance from the band. A separation device for an spacecraft, comprising a metal fitting and means for reversing the direction of energization of the electromagnet to attract the band to the receiving metal fitting when separating the separation bolt. 2. A spacecraft comprising the separation device.