JPH04254299A - Coupling device for space equipment - Google Patents

Abstract

PURPOSE:To open/close a protective cover with simple and compact constitution by turning the protective cover, which covers possible to open/close an interface part, through a cam mechanism by pressing a protrusive part when a plurality of space equipments approach so as to be connected. CONSTITUTION:At normal time, that is, before a space equipment main unit 2 is connected to a pay load 1, an interface part 9 provided in a coupling surface 7 of the space equipment main unit 2, is covered with a protective cover 11 energized by a spring 8. Here, a protrusive part of the protective cover 11 is engaged with a hole part of the coupling surface 7 where the interface part 9 appears. When the space equipment main unit 2 approaches so as to be connected with the pay load 1, a damper 15 provided in a coupling surface 5 of the pay load 1, is brought into contact with the coupling surface 7 of the space equipment main unit 2 to press the protective cover 11. Then by successively moving a cam pin 22 in a cam groove 21, each interface part 9, 10 of the space equipment main unit 2 and the pay load 1 is connected to each other.

Description

[Detailed description of the invention]

0001

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a coupling device for space equipment, and more particularly to a coupling device for space equipment equipped with a protective cover covering an interface section.

0002

2. Description of the Related Art Space equipment docked in outer space is provided with interface parts (connectors, couplers, etc.) that are connected to each other during docking. This interface section must be exposed to space in order to connect during docking, and is susceptible to deterioration due to the effects of cosmic dust and cosmic rays. Additionally, there is a problem in that heat within the space device escapes to the low-temperature outer space via this interface section.

[0003] As a countermeasure to this problem, a technique can be considered in which the interface section is normally covered with a protective cover (having a protective/heat retaining function), and the protective cover is opened by a motor only when docking.

0004

[Problems to be Solved by the Invention] However, in order to open and close the protective cover using a motor in this way, a motor for opening and closing the protective cover, which is used only during docking, must be mounted on the space device, which increases the weight of the device. Power consumption will increase. This is a fatal drawback when considering launching this device into space.

An object of the present invention, which was created in consideration of the above circumstances, is to provide a coupling device for space equipment in which a protective cover is automatically opened during docking without using a motor.

[0006]

[Means for Solving the Problems] In order to achieve the above object, the present invention provides a coupling device for coupling interface parts of space instruments in outer space, in which a coupling surface of one space instrument is connected to a coupling surface of the other space instrument. A protrusion is provided to press the coupling surface of the other space device, and a protective cover is provided on the other space device to cover the interface part by rotation, and a cam mechanism is provided that rotates the protective cover by the pressure of the protrusion. It is characterized by the fact that it has been established.

[0007]

[Operation] According to the above structure, when space devices approach each other for docking, the convex portion provided on the coupling surface of one space device presses the coupling surface of the other space device. Then, due to this pressure, the cam mechanism provided on the other space device rotates the protective cover covering the interface section of the other space device, and opens the interface section. Thereafter, as the space devices come closer together, the interface section of one space device is connected to the opened interface section of the other space device.

[0008]

DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of the present invention will be described with reference to the accompanying drawings.

FIG. 5 shows a schematic perspective view of a payload 1 as one space device and a space device main body 2 as the other space device. As shown in the figure, the device main body 2 is provided with three latching arms 3, and the payload 1 is formed with a V guide 4 with which these latching arms 3 engage. Further, a cone-shaped guide pin 6 is provided on the coupling surface 5 of the payload 1, and a guide hole 8 with which the guide pin 6 engages is provided on the coupling surface 7 of the device body 2. These guide pins 6 and guide holes 8 are
When the interface section 9 of the device main body 2 and the interface section 10 of the payload 1 are coupled (docked), it functions to guide the coupling and correct angular deviation.

[0010] A protective cover 11 is provided on the coupling surface 7 of the device main body 2 and covers the interface portion 9 so as to be openable and closable by rotation. This protective cover is formed into a disk shape and has a long hole 12 shaped to expose the interface portion 9 of the device body 2. Therefore, when the protective cover 11 is rotated and the elongated hole 12 is aligned with the interface part 9, it is "open", and when it is not aligned, it is "closed".

On the other hand, the coupling surface 5 of the payload 1 is provided with a rod-shaped convex portion 13 that presses the coupling surface 7 of the device body 2. As shown in FIG. 1, the convex portion 13 is composed of a cylindrical damper 15 that is biased in the direction of extension by a spring 14 and can be freely expanded and contracted, and a push rod 16 arranged and fixed inside the damper 15. ing. The length of this push rod 16 is shorter than the length of the damper 15. According to this configuration, when the coupling surface 5 of the payload 1 approaches the coupling surface 7 of the device body 2, the tip of the damper 15 first contacts the coupling surface 7 of the device body 2, causing the spring 14 to contract (see FIG. ), then a further approach will result in said push rod 16 contacting the coupling surface 7 of the device body 2 (as shown in FIG. 4).

[0012] Such a damper 15 and push rod 1
By pressing the convex portion 13 consisting of 6, the protective cover 1
A cam mechanism 17 for rotating the device body 2 is provided in the device body 2. This cam mechanism 17 will be described below.

As shown in FIG. 1, the coupling surface 7 of the device body 2
The protective cover 11 provided at It is supposed to be covered. A portion 19a of this cam body 19 is exposed to the coupling surface 7, and the push rod 1 is attached thereto.
6 are in contact with each other.

The cam body 19 is provided within a cylindrical cam cover 20 fixed within the main body 2 so as to be freely movable in the axial direction. A cam groove 21 is formed in this cam cover 20 as shown in FIG. This cam groove 21 has a linear cover pushing part 21a and a spiral cover opening part 21.
The groove portions of the interface connection portion 21c and the linear interface connection portion 21c are continuous. Such a cam groove 21
A cam pin 22 attached to the cam body 19 is engaged with the cam pin 22 .

On the other hand, the protective cover 11 is provided with a cylinder 23 concentrically at its center. This cylinder 23
The cam cover 20 is placed inside. The cylindrical body 23 is pivotally supported by the cam cover 20, and the protective cover 11 is configured to rotate. Further, as shown in FIG. 2, a linear groove 24 is formed in this cylindrical body 23. The cam pin 22 that was engaged with the cam groove 21 is engaged with this groove 24 at the same time.

Note that 25 in FIG. 1 is a ball screw,
The ball screw 25 is rotated via a gear 26 by a motor (not shown) or the like, and the nut member 2 is screwed onto the screw 25.
By moving the latching arm 7 back and forth, the latching arm 3 is opened, closed, and pulled through a link mechanism (not shown).

The operation of this embodiment having the above configuration will be described.

In normal times, that is, before the space device main body 2 and the payload 1 are coupled (docked), the interface section 9 provided on the coupling surface 7 of the space device main body 2 is connected to the spring 18 as shown in FIG. It is covered by a protective cover 11 which is biased by the. At this time, a protective cover 1 is placed in the hole 28 (shown in FIG. 3) of the coupling surface 7 through which the interface section 9 looks.
The first convex portion 29 (shown in FIG. 3) is in an engaged state. Therefore, the coupling surface 7 has a flat shape with no unevenness, and even if some protrusion of the payload 1 comes into contact with the coupling surface 7, problems such as getting caught will not occur.

[0019] Space equipment main body 2 and payload 1 are combined (
When approaching for docking, first, as shown in FIG. 3, the damper 15 provided on the coupling surface 5 of the payload 1 contacts the coupling surface 7 of the device main body 2 and presses the protective cover 11. At this time, the spring 14 that biases the damper 15 contracts. This contraction of the spring 14 cushions the impact during docking. When the protective cover 11 is pressed in this manner, the cam pin 22 shown in FIG. 2 linearly moves the cover pressing portion 21a of the cam groove 21. As a result, the bonding surface 7
The protrusion 29 of the protective cover 11 is removed from the hole 28.

Thereafter, as the space equipment main body 2 and the payload 1 come closer together, the push rod 16 presses a portion 19a of the cam body 19 exposed on the coupling surface 7 of the equipment main body 2, as shown in FIG. do. Then, the cam pin 22 shown in FIG. 2 moves spirally through the cover opening 21b of the cam groove 21. As a result, the protective cover 11 rotates, and the elongated hole 12 of the protective cover 11 aligns with the interface part 9. That is, the protective cover 11 is in the "open" state.

When the space equipment main body 2 and the payload 1 come closer together, the cam pin 22 shown in FIG. is coupled to the interface section 9 of the space equipment main body 2.

Furthermore, when this connection is separated, the cam body 1
9 is biased in the extension direction by the spring 18, the cam pin 22 moves in the cam groove 21 in the order of the interface connecting part 21c, the cover opening part 21b, and the cover pushing part 21a, contrary to the above. , a state in which the protective cover 11 rotates and covers the interface part 9 of the space equipment main body 2,
That is, the protective cover 11 is in the "closed" state.

[0023] In this way, the protective cover 11 is automatically "opened" due to the proximity of the space equipment main body 2 and the payload 1.
At the same time, the protective cover 11 is automatically "closed" by these detachments. Since the opening/closing mechanism of the protective cover 11 does not use a motor and is composed of a simple cam mechanism 17, the device can be made smaller, lighter, and consume less power. Furthermore, since no electrical means is used, the reliability of opening/closing operation is high.

[0024]

[Effects of the Invention] As explained above, according to the present invention, the following excellent effects can be exhibited.

(1) Since a simple cam mechanism is used for the opening/closing mechanism of the protective cover without using a motor,
It is possible to promote smaller, lighter weight, and lower power consumption of devices.

(2) The opening/closing mechanism of the protective cover does not use electrical means, so it is highly reliable.

[Brief explanation of the drawing]

FIG. 1 is a side sectional view of a coupling device for space equipment showing an embodiment of the present invention.

FIG. 2 is an explanatory diagram showing the cam mechanism in FIG. 1;

FIG. 3 is an explanatory diagram showing the operation of the coupling device.

FIG. 4 is an explanatory diagram showing the operation of the coupling device.

FIG. 5 is a perspective view showing the space equipment main body and payload in FIG. 1;

[Explanation of symbols]

1 Payload 2 as one space device Space device body 5 as the other space device Coupling surface 7 Coupling surface 9 Interface section 10 Interface section 11 Protective cover 13 Convex section 17 Cam mechanism

Claims (1)

[Claims] Claim 1: In a coupling mechanism for coupling interface parts of space devices in space, a coupling surface of one space device is provided with a convex portion that presses the coupling surface of the other space device, In addition to providing a protective cover that covers the interface part so that it can be opened and closed freely by rotation,
A coupling device for space equipment, characterized in that a cam mechanism is provided for rotating the protective cover by pressing the convex portion.