KR-20260065211-A - Satellite connector with center alignment capability

KR20260065211AKR 20260065211 AKR20260065211 AKR 20260065211AKR-20260065211-A

Abstract

The present invention discloses a satellite connecting device capable of center alignment, which interconnects a floating satellite and a target object, comprising: a first connecting module protruding from the satellite and having a connecting pin formed that extends outward with a relatively small circumference from the protruding end; and a second connecting module positioned on the target object toward the satellite, having an internal receiving space and one side open so that a part of the first connecting module is inserted and fixed, and a part of the second connecting module holds the connecting pin and inserts and fixes one side of the first connecting module inward along the longitudinal direction of the receiving space, wherein the center of the first connecting module is positioned on the same centerline as the second connecting module, and the connecting pin is inserted and fixed inside the second connecting module while positioned on the centerline to receive fuel.

Inventors

최동운
원대희
소병록

Assignees

한국생산기술연구원

Dates

Publication Date: 20260508
Application Date: 20241101

Claims (9)

As a satellite connecting device that interconnects a floating satellite and an object, A first connection module protruding from the above satellite, wherein a connecting pin is formed that extends outward from the protruding end portion with a relatively small circumference; and A second connecting module positioned toward the satellite from the object above, having an internal receiving space and one side open so that a part of the first connecting module is inserted and fixed, and a part holds the connecting pin to insert and fix one side of the first connecting module inward along the longitudinal direction of the receiving space; comprising An artificial satellite connection device capable of center alignment, characterized in that the center of the first connection module is positioned on the same centerline as the second connection module, and the connection pin is inserted and fixed inside the second connection module while positioned on the centerline to receive fuel.
In paragraph 1, The above second connection module is, A housing having an external shape and an internal receiving space having a certain length; A coupling unit provided inside the housing and selectively coupled with the connecting pin; A fixing unit having an opening on one side of the housing and passing a part of the first connecting module through it to be connected to the first connecting module; and A moving unit that selectively connects to the connecting pin and moves along the longitudinal direction of the receiving space between the fixed unit and the coupling unit to pull the connecting pin and combine with the coupling unit; A satellite connection device capable of center alignment including
In paragraph 2, The first connection module includes a separate protrusion protruding forward at a position adjacent to the connection pin on one side of the satellite, and The above-mentioned second connecting module is a satellite connecting device capable of center alignment, characterized in that the opening is formed to correspond to the shape of the protrusion, and when connected, the protrusion is inserted into the opening.
In paragraph 3, The above protrusion is, A satellite connection device capable of center alignment, composed of multiple units arranged radially around the connecting pin.
In paragraph 3, The above protrusion is, A satellite connection device capable of center alignment, characterized by being formed in a curved shape along a protruding perimeter from the center toward the edge.
In paragraph 3, The above fixed unit is, A satellite connection device capable of center alignment formed to wrap around the circumference of the above-mentioned protrusion, with a portion optionally protruding toward the above-mentioned protrusion for fixation.
In paragraph 6, The above fixed unit is, A fastening part formed in a ring shape with the opening formed in the center; and A plurality of fixing parts are provided along the inner diameter on the above-mentioned fastening part and are optionally protruded to be coupled with the protrusions; A satellite connection device capable of center alignment including
In paragraph 2, The above-mentioned coupling unit is, A support member having a certain area and arranged in a fixed state within the above-mentioned receiving space; and A nozzle part formed to protrude a certain length forward from the support part and positioned on the centerline, coupled to the end of the connecting pin to enable fuel flow; A satellite connection device capable of center alignment including
In paragraph 2, The above-mentioned moving unit is, A satellite connection device capable of center alignment, characterized by multiple wires each moving independently and moving while adjusted to wrap around the circumference of the connecting pin and positioned on the centerline.

Description

Satellite connector with center alignment capability The present invention relates to a satellite connection device capable of center alignment, and more specifically, to a satellite connection device capable of center alignment that can stably connect a first connection module provided on a satellite and a second connection module provided on an object by aligning their centerlines when combining them. By using other satellites or space stations to perform close-range observation, refueling, repairs, orbit changes, and parts replacements on a satellite launched into space and in orbit, the satellite's fuel is primarily used for orbit insertion, orbit maintenance and maneuvering, and attitude control, which can determine the satellite's lifespan. Accordingly, a service satellite is required to refuel client satellites that require refueling, and such a service satellite carries fuel to perform refueling, and after rendezvousing with the client satellite that is low on fuel, supplies the satellite's fuel to extend its lifespan. However, the rendezvous process between the client satellite and the service satellite for such refueling is complex and time-consuming, so refueling via rendezvous is not yet being properly attempted. In particular, since there is no air resistance in a zero-gravity environment, a cautious approach is required because inertia can cause unintended interference during movement or damage due to impact. Therefore, there is a need to develop a connecting device for a service satellite that can perform a stable and rapid rendezvous between the service satellite and the client satellite for refueling. FIG. 1 is a diagram showing an artificial satellite and an object being connected by a connecting device according to an embodiment of the present invention; FIG. 2 is a drawing showing the state in which the first connection module and the second connection module are arranged in the connection device of FIG. 1; FIG. 3 is a drawing showing the process of connecting the first connection module and the second connection module in the connection device of FIG. 1; FIG. 4 is a drawing showing the state in which a connecting pin and a moving unit are connected in the connecting device of FIG. 3; FIG. 5 is a drawing showing the shape of the protrusion and the opening in the connecting device of FIG. 3; FIG. 6 is a drawing showing the state in which a protrusion is seated in correspondence with the shape of an opening when the moving unit moves in the connecting device of FIG. 5; FIG. 7 is a drawing showing the state in which the protrusion in FIG. 5 is fixed by a fixing unit while seated in the opening; FIG. 8 is a drawing showing the operating state of the fixed unit of FIG. 5. Preferred embodiments of the present invention, in which the objectives of the present invention can be specifically realized, will be described below with reference to the attached drawings. In describing these embodiments, the same names and reference numerals are used for identical components, and additional explanations thereof will be omitted. In addition, in describing the embodiments of the present invention, it is stated in advance that while the same names and symbols are used for components having the same function, they are not substantially identical to the prior art. Furthermore, the terms used in the embodiments of the present invention are used merely to describe specific embodiments and are not intended to limit the invention. The singular expression includes the plural expression unless the context clearly indicates otherwise. Furthermore, in the embodiments of the present invention, terms such as "comprising" or "having" are intended to specify the existence of the features, numbers, steps, actions, components, parts, or combinations thereof described in the specification, and should be understood as not excluding in advance the existence or addition of one or more other features, numbers, steps, actions, components, parts, or combinations thereof. First, with reference to FIGS. 1 to 3, we will examine the configuration of a satellite connection device capable of center alignment according to the first embodiment of the present invention. FIG. 1 is a drawing showing an artificial satellite and an object being connected by a connecting device according to an embodiment of the present invention, FIG. 2 is a drawing showing the state in which a first connecting module and a second connecting module are arranged in the connecting device of FIG. 1, and FIG. 3 is a drawing showing the process of connecting the first connecting module and the second connecting module in the connecting device of FIG. 1. And Fig. 4 is a drawing showing the state in which the connecting pin and the moving unit are connected in the connecting device of Fig. 3, and Fig. 5 is a drawing showing the shape of the protrusion and the opening in the connecting device of Fig. 3. The present invention relates to a connecting device for intercon