JPH02182599A - Docking mechanism - Google Patents

Abstract

PURPOSE:To reduce a contact impart in a translation direction by a method wherein, in a title mechanism loaded on an artificial satellite, an extension mechanism is mounted to a first space craft through a cushioning mechanism having a leaf spring and a damper and the degree of freedom of rotation and translation, and capture mechanisms coupled to the tip of the extension mechanism and a second space craft are provided. CONSTITUTION:When an external force is exerted on a moving plate 12, a leaf spring 5b is resiliently displaced, a damper 4 is expanded and contracted in a longitudinal direction, and rotational and translational movement of a cushioning mechanism 6 are provided. A plate 10 on the stationary side of the cushioning mechanism 6 is secured to a space craft 1, and a moving plate 12 is mounted to a relay plate 11 so that it is positioned in the vicinity of the center in a longitudinal direction of the extension mechanism 7. Rupture mechanisms 8 are formed to the tip of the extension mechanism 7 and a space craft 2. This constitution enables relaxation of an impact in a rotation direction and a translation direction.

Description

DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to a docking mechanism that is attached to a spacecraft such as an artificial satellite, a space station, or a space platform.

[Conventional technology]

FIG. 3 shows an example of the configuration of a conventional docking mechanism.

In the figure, (11 is the first spacecraft (hereinafter referred to as spacecraft a), 12+ is the second spacecraft (hereinafter referred to as spacecraft), (31 is the ball end, (4) is the damper,
(5a) is a spring, (6) is attached to the spacecraft (1), ball end (3), damper (4), spring (5)
a), and (7) is the buffer mechanism fR (
Extension mechanism attached to 61, (8) is spacecraft b 11
A pair of capture mechanisms are attached to the end faces of spacecraft a and the tip of the extension mechanism (7), and +91 is a set of coupling mechanisms attached to the end faces of spacecraft a and space ab.

A conventional docking mechanism is constructed as described above.

Spacecraft a fl) and spacecraft b (2) flying separately
After approaching, a pair of capture mechanisms (8) are brought into contact and connected by extending the extension mechanism (7), and by retracting the extension mechanism (7), the relative distance is further shortened, and a pair of coupling mechanisms (
After 9) operates, spacecraft a II) and b f2J enter the coupled state. When this capture mechanism (8) is connected and extended 4
11 When the +71 is pulled in and the coupling mechanism (9) is coupled, displacement occurs in the damper (4) and the spring (5a), and the shock absorber m (61) acts, causing the spacecraft a ill
, b (reducing the contact impact load of 21 and reducing the positional deviation between the two).

[Problem to be solved by the invention]

In the conventional docking mechanism configured as described above, the buffer a fit +e+ has only the degree of freedom of rotation around the ball end (3), so there is a problem that the contact impact load in the translational direction cannot be reduced. In addition, in order to support the extension mechanism (7) at the ball end (3) position, it is necessary to have a support point at a position away from the end face of the spacecraft 11), and the structure of the spacecraft 8(l) is There were problems in that it was complicated and increased in weight.Also, since the extension mechanism (7) was supported on one side in the longitudinal direction, it was difficult to ensure the rigidity necessary to withstand vibration loads. This invention was made to solve this problem.

A docking mechanism is realized in which the buffer mechanism supporting the extension agt has a translational degree of freedom in addition to a rotational degree of freedom, has a support point on the end face of the spacecraft a, and can support the vicinity of the longitudinal center of the extension mechanism. The purpose is to

[Means to solve the problem]

In the docking mechanism according to the present invention, the fixed side is fixed to the end face of the spacecraft 8 as a buffer mechanism, and the movable side is fixed to the extension mechanism, between the movable side and the fixed side.

It has a buffer mechanism composed of a plurality of leaf springs and a damper that connect the two.

[For production]

According to this invention 1, when an external force is applied to the extension mechanism.

Since a plurality of leaf springs fixed to the movable side and the fixed side of the buffer mechanism are elastically deformed, the buffer mechanism has a translational degree of freedom in addition to a rotational degree of freedom. Moreover, there is a holding point on the end face of the spacecraft a, and the vicinity of the longitudinal center of the extension mechanism can be supported.

〔Example〕

FIG. 1 is a diagram showing one embodiment of the present invention.

In the figure, (1) is spacecraft a, (21 is spacecraft I, +
41 is a damper, (sb) is a leaf spring, and (6) is composed of a plurality of leaf springs (5b) and a damper (4) whose fixed side is fixed to the end face of the spacecraft 811+, and which connects the movable side and the fixed side. (7) is an extension mechanism attached to the movable side of the buffer mechanism +6), and (8) is a set of captures attached to the end face of the spacecraft 8(l) and the tip of the extension mechanism (7). Machine 111. +91 is spacecraft 8 (1) and spacecraft b (2
) is a pair of coupling mechanisms attached to the end faces of the

FIG. 2 (al) is a diagram showing one configuration example of the buffer mechanism (6) according to the present invention.

In the figure, +41. ('b) + (7) is the same as in Fig. 1, α [is a fixed side play that has a hole in the center large enough for the extension mechanism (7) to pass through], (1ml has an extension mechanism (7) in the center). (7) has a hole large enough to pass through;
Two plates (5b) that intersect with the damper (4) in an X shape
a relay plate connected to fixed side plate αq by
The α-ri has a hole in the center large enough for the extension mechanism (7) to pass through, and two leaf springs (
5b) is the movable plate connected to the relay plate σ and ζ. Figure 2b shows the buffer mechanism (
6) Operation explanation diagram, +41. (5b),
Ql, ([1), +12 is the same as in Fig. 2 fa). In FIG. 2(b), when an external force is applied to the movable plate α2, the leaf spring (5b) is elastically displaced, and the damper (4)
expands and contracts in the longitudinal direction, so the buffer mechanism (6) has rotational degrees of freedom and translational degrees of freedom. In addition, the buffer mechanism (6
), the extension mechanism (7) can be passed through the central part of the extension mechanism (7), so the fixed side plate α [is fixed to the end face of the spacecraft 8(l), and the vicinity of the longitudinal center of the extension mechanism (7) is inserted into the movable plate. It is possible to fix it at a3.

〔Effect of the invention〕

According to the docking mechanism according to the present invention, the buffer mechanism supporting the extension mechanism has a translational degree of freedom in addition to a rotational degree of freedom, has a support point on the end face of the spacecraft, and has a support point at the longitudinal center of the extension mechanism. This has the effect of realizing a docking mechanism that can support nearby areas.

[Brief explanation of the drawing]

FIG. 1 is a diagram showing one embodiment of the docking mechanism according to the present invention, FIG. 2(a) is a diagram showing one configuration example of the buffer mechanism according to the present invention, and FIG. The operation explanatory diagram, Fig. 3, is a diagram showing one embodiment of the conventional docking mechanism.
3+ is the ball end, (4) is the damper, and (5a) is the spring. (5b) is a plate spring, (6) is a buffer mechanism, and (7) is an extension mechanism. (8) is the capture mechanism, (9) is the coupling mechanism, α1 is the fixed side plate, συ is the relay plate, and aa is the movable side plate. Note that the same reference numerals in Figure 1 indicate the same parts.

Claims (1)

[Claims] an extension mechanism provided on the first spacecraft and extending when the first spacecraft and the second spacecraft are docked; A pair of capture mechanisms that are connected in contact with each other are provided on opposing surfaces of the first and second spacecraft, and after the pair of capture mechanisms are coupled, the first and second spacecraft are coupled. In the docking mechanism, the fixed side is provided in the first spacecraft, the movable side is provided in the extension mechanism, and a plurality of leaf springs and dampers are provided to connect the fixed side and the movable side. What is claimed is: 1. A docking mechanism characterized by comprising a buffer mechanism having rotational degrees of freedom and translational degrees of freedom.