KR20100020228A - Hinge apparatus and satellite having the same - Google Patents

Abstract

PURPOSE: A hinge apparatus and a satellite having the same are provided to ensure development reliability in a simple structure wherein hinge brackets supporting the satellite body and a solar panel are connected with elastic members. CONSTITUTION: A first hinge bracket(40) is installed in a first unit. A second hinge bracket(50) is installed in a second unit. A connector(60) interlinks the first and second hinge brackets. The connector creates a restoring force in a folded state where the first and second units are faced each other. A coil spring is provided in the connector to gradually reduce the restoring force in the same direction as the second unit is opened with respect to the first unit.

Description

HINGE APPARATUS AND SATELLITE HAVING THE SAME}

The present invention relates to a satellite, and more particularly, to a hinge device and a satellite including the same to deploy a solar panel deployed from the satellite to the satellite to perform a predetermined mission in the mission orbit.

In general, solar panels used in satellites are power sources that produce power for satellites to perform their missions. The solar panel is folded into the satellite when launched from the earth, but when the satellite reaches the mission orbit, the solar panel is deployed from the satellite to produce power. The solar panel is connected to the satellite by a hinge device, which is folded about the satellite and then deployed.

On the other hand, when the satellite is launched out of the atmosphere from the earth at room temperature, the satellite comes into contact with the cryogenic or cryogenic environment. Therefore, the hinge device is thermally contracted or thermally expanded in a cryogenic or cryogenic environment, thereby lowering deployment reliability of the solar panel. The development failure of such a solar panel directly affects the power generation of the satellites, causing the performance degradation of the satellites. There may be a kinematic compensation as a countermeasure for preventing the performance degradation due to the temperature change of the hinge device, but this causes another problem that the structure of the hinge device becomes very complicated.

Therefore, research / development is needed for a hinge device that is simple in structure and can stably deploy solar panels from satellites in response to various temperature environments.

The present invention has been made in view of the above problems, and an object thereof is to provide a hinge device and a satellite including the same, which can secure deployment reliability with a simple structure.

Another object of the present invention is to provide a thermally excellent hinge device and a satellite including the same.

The hinge device according to the present invention for achieving the above object of the present invention, connecting the first and second hinge brackets and the first and second hinge brackets respectively installed in the first and second units, And connecting means for generating a restoring force when the first and second units face each other in a folded state.

According to an embodiment of the present invention, the connecting means may include a coil spring in which the restoring force is gradually decreased in a direction in which the second unit is deployed with respect to the first unit, and thus may be generated in a cryogenic or cryogenic environment. It can cope with thermal deformation.

In detail, the first hinge bracket includes a first support end supporting the first unit and a first connection end bent from the first support end to be connected to the connection means. Similarly, the second hinge bracket includes a second support end supporting the second unit and a second connection end bent from the second support end and connected to the connection means. Here, the first and second hinge brackets are formed to protrude so as to be in contact with each other at substantially central portions of the first and second connection ends, respectively, to guide the movement of the first and second hinge brackets. It may further include a guide stage.

On the other hand, the connecting means, the elastic body for generating the restoring force and the fixing portion including the first and second fixing members and fixing plates to fix both ends of the elastic body to the first and second connection ends, respectively.

Here, the first fixing member, the first insertion end is inserted into the first and second connection holes formed through the first and second connection end, respectively, and protrudes with an outer diameter larger than the outer diameter of the first insertion end. And a first protruding end for supporting the inner circumferential surface of the elastic body. The second fixing member is inserted between the first and second connecting end and the first fixing member and is bent from the second insertion end and the second insertion end to form an insertion hole communicating with the first and second connection holes. It includes a second protruding end for supporting the outer peripheral surface of the elastic body. The fixing plate may face the first and second fixing members with the first and second connecting ends interposed therebetween, and connect the first and second fixing members supporting the elastic body to the first and second connecting members. A fastening hole for fixing to the end is formed. These fixing parts are provided in pairs corresponding to both ends of the elastic body.

For reference, the first unit includes a satellite body, and the second unit includes a solar panel that is a power source of the satellite body. In addition, the second unit may further include a regulating unit for regulating the development range of the second unit.

Satellite for achieving the object of the present invention, the solar panel is connected to the satellite body, the satellite body, receiving the sunlight to generate power of the satellite body, and the hinge device for connecting the satellite body and the solar panel The hinge device includes: a first hinge bracket installed on the satellite body, a second hinge bracket installed on the solar panel, and connecting the first and second hinge brackets to the satellite body and the sun. It includes a connecting means for generating a restoring force in the folded state in which the panels face each other.

The hinge device and the satellite including the same according to the present invention as described above, by connecting the hinge brackets supporting the satellite body and the solar panel with an elastic body to generate a restoring force in the deployment direction, to ensure the deployment reliability of the solar panel with a simple structure can do.

In addition, the present invention is very excellent in terms of thermal by including a coil spring that can maintain the restoring force in a variety of temperature environment, such as cryogenic or cryogenic.

Hereinafter, exemplary embodiments of the present invention will be described in detail with reference to the accompanying drawings.

Referring to FIG. 1, the satellite 1 according to an embodiment of the present invention includes a satellite body 10, a solar panel 20, a hinge device 30, and the like.

The satellite body 10 is a body of the satellite 1 which is artificially shot from the earth and orbits around the earth, such as the moon, and performs a predetermined task such as scientific experiment, reconnaissance and / or communication. The satellite body 10 is launched from the earth by a projectile (not shown), and when it reaches the mission orbit, it is separated from the projectile (not shown) to drive the mission track by inertia. Since the operation technology configuration of the satellite body 10 can be understood from a known technology, detailed description and illustration are omitted.

The solar panel 20 is a power source that generates electrical energy for the satellite main body 10 reaching the mission orbit to perform a predetermined task. That is, the solar panel 20 is to generate power for the mission rather than the driving force of the satellite body 10.

The solar panel 20 includes a plurality of solar cells (not shown) to convert sunlight into electrical energy. Electrical energy converted by the solar panel 20 is supplied to the satellite body 10 by a connection between the solar panel 20 and the satellite body 10. Since the technical configuration of the solar panel 20 as described above can be understood from a known technology, detailed description and illustration are omitted.

The hinge device 30 interconnects the satellite body 10 and the solar panel 20 so that the solar panel 20 is movable with respect to the satellite body 10. Specifically, the hinge device 30 has a folding position in which the satellite body 10 and the solar panel 20 face each other, and a deployment position in which the solar panel 20 is deployed with respect to the satellite body 10. The satellite body 10 and the solar panel 20 are connected to each other so that the solar panel 20 can move. The hinge device 30 includes the first and second hinge brackets 40 and 50 and the connecting means 60 as shown in FIGS. 3 to 7.

The first hinge bracket 40 is installed on the satellite body 10 and includes a first support end 41 and a first connection end 43. The first support end 41 supports the satellite body 10, and the first connection end 43 is bent from the first support end 41 and connected to the connection means 60.

5 and 6, a fastening means S such as a screw or a bolt is inserted into the first support end 41 to fix the first support end 41 to the satellite body 10. A plurality of first fastening holes 42 are formed therethrough. In addition, a first connection hole 44 is formed through the first connection end 43 for connection with the connection means 60 described later.

The second hinge bracket 50 is installed on the solar panel 20 and is bent from the second support end 51 and the second connection end supporting the solar panel 20 and connected to the connection means 60. And a second connecting end 53. 5 and 6, a plurality of second fastening holes 52 are formed in the second support end 51 to be fastened with the solar panel 20, and the second connection end ( The second connection hole 54 for connection with the connecting means 60 is formed through 53. That is, the first and second hinge brackets 40 and 50 are different from each other and have the same configuration.

In addition, the first and second hinge brackets 40 and 50 may include first and second guide ends 45 and 55 which may be in contact with each other at substantially central portions of the first and second connection ends 43 and 53. ) Are projected respectively. The first and second guide ends 45 and 55 are provided with first and second guide surfaces 46 and 56 in contact with each other, so that the first and second hinge brackets 40 and 50 can be Guide movement in the deployment direction. In this case, the first and second guide surfaces 46 and 56 are formed as a curved surface, thereby smoothly guiding the first and second hinge brackets 40 and 50.

For reference, the first and second connection holes 44 and 54 formed in the first and second connection ends 43 and 53 are disposed between the first and second guide ends 45 and 55. Leave on and are formed in pairs.

The connecting means 60 connects the first and second hinge brackets 40 and 50 and generates a restoring force when the satellite body 10 and the solar panel 20 are in a folded state facing each other. That is, the connecting means 60 is to press the solar panel 20 in the direction in which the satellite body 10 is deployed. The connecting means 60 includes an elastic body 70 and the fixing portion 80. For reference, the connecting means 60 is provided in pairs corresponding to the pair of first and second connecting holes 44 and 54, so that the first and second hinge brackets 40 and 50 are provided. Connect more firmly.

The elastic body 70 generates a restoring force for pressing the solar panel 20 to a deployed position. That is, as shown in FIG. 7, the elastic body 70 is an initial state in which the solar panel 20 is unfolded in a deployed position. In the present embodiment, the elastic body 70 includes a spiral coil spring that can maintain the restoring force even in thermal deformation in various temperature environments.

For reference, when the solar panel 20 is launched from the earth, the solar panel 20 is folded to the satellite body 10 side by a pressing means (not shown). In this case, the elastic body 70 is also folded together so that a restoring force, that is, torque (Torque) ). When the pressing means (not shown) pressurizing the solar panel 20 is released, the solar panel 20 is developed from the satellite body 10 by the restoring force of the elastic body 70. Therefore, the torque of the elastic body 70 in the expanded state of the solar panel 20 is 0, the elastic body 70 is in the unfolded state.

The fixing part 80 fixes both ends 71 and 72 of the elastic body 70 to the first and second connection ends 43 and 53, respectively. As shown in FIGS. 3 to 7, the fixing part 80 includes a first fixing member 81, a second fixing member 86, and a fixing plate 90, such that one end of the elastic body 70 is formed. 71 and the other end 72 are fixed to the first and second connection ends 43 and 53, respectively.

As shown in FIGS. 5 and 7, the first fixing member 81 is disposed in the first and second connection holes 44 and 54 formed in the first and second connection ends 43 and 53. It includes a first insertion end 82 to be inserted, and a first projection end 83 protruding with an outer diameter larger than the outer diameter of the first insertion end 82 to support the inner circumferential surface 73 of the elastic body 70. Here, a seating groove 84 corresponding to the shape of the elastic body 70 which is the coil spring is formed on the outer circumferential surface of the first protruding end 83. In addition, a third fastening hole 85 is formed in the first insertion end 82 and the first protruding end 83 to communicate with the first and second connection holes 44 and 54.

As shown in FIGS. 5 and 7, the second fixing member 86 is inserted between the first and second connecting ends 53 and the first fixing member 81 and the first and second connecting holes. A second insertion end 87 formed with an insertion hole 88 communicating with (44) and 54; and a second bending end supported by the second insertion end 87 to support the outer circumferential surface 74 of the elastic body 70; And a protruding end 89. At this time, the first fixing member 81 is inserted and seated in the second insertion end 87. For reference, the diameter of the insertion hole 88 of the second insertion end 87 is a diameter that can communicate with the first and second connection hole 54.

The fixing plate 90 is disposed to face the first and second fixing members 81 and 86 with the first and second connection ends 43 and 53 interposed therebetween. In addition, the fixing plate 90 has first and second fixing members 81 and 86 for supporting both ends 71 and 72 of the elastic body 70 at the first and second connection ends 53. A fourth fastening hole 91 for fixing by the fastening means S is formed.

Looking at the process in which both ends 71 and 72 of the elastic body 70 are fixed to the first and second hinge brackets 40 and 50 by the fixing part 80, respectively, with reference to FIGS. 5 and 7. , As follows.

First, the second fixing member 86 such that the first connecting hole 44 formed in the first connecting end 43 of the first hinge bracket 40 and the insertion hole 88 of the second fixing member 86 communicate with each other. ). Thereafter, the first insertion end 82 of the first fixing member 81 is connected to the second insertion hole 82 so that the third coupling hole 85 formed in the first fixing member 81 communicates with the first connecting hole 44. It enters the insertion end 87. At this time, one end 71 of the elastic body 70 is supported by the inner circumferential surface 73 by the seating groove 84 of the first protruding end 83 and the outer circumferential surface 74 by the second protruding end 89. As a result, it is fixed between the first and second protruding ends 83 and 89. Here, the seating groove 84 has a shape corresponding to that of the elastic body 70 and supports the inner circumferential surface 73 of the elastic body 70, whereby the flow of one end 71 of the elastic body 70 is suppressed.

When the first and second fixing members 86 support the one end 71 of the elastic body 70, the first connecting hole, the third and fourth fastening holes 85 and 91 are arranged to communicate with each other. , The fastening means S enters through the fourth fastening hole 91 of the fixing plate 90 to fix the first and second fixing members 86 to the first connection end 43. In this case, the fixing plate 90 faces the first and second fixing members 81 and 86 with the first connection end 43 therebetween. As a result, the connection between the first hinge bracket 40 and the elastic body 70 is completed.

The connection operation of the first hinge bracket 40 and the elastic body 70 as described above is applied to the second hinge bracket 50 as it is, so that the first and second hinge brackets 40 and 50 are elastic bodies 70. Interconnected by

On the other hand, between the satellite body 10 and the solar panel 20 is a restricting unit 100 for regulating the development range of the solar panel 20 deployed by the hinge device 30 as shown in Figs. Is installed. The regulation unit 100 is in a folded state when the solar panel 20 is in a folded state with respect to the satellite body 10, and is in an unfolded state when the solar panel 20 is in a deployed state with respect to the satellite body 10. By varying, the development range between the satellite body 10 and the solar panel 20 is regulated. For reference, the regulation unit 100 may be guided so that the solar panel 20 can be smoothly deployed from the satellite body 10.

The operation of the satellite 1 according to the present invention having the above configuration will be described with reference to FIGS. 1 to 7.

As shown in FIG. 1, by the pressurizing means (not shown) until the satellite 1 is reached from the earth after the satellite 1 is launched from the earth while the solar panel 20 is folded on the satellite body 10. The solar panel 20 maintains the folded state. 3 and 6, the first and second hinge brackets 40 and 50 supporting the satellite body 10 and the solar panel 20 are vertically connected to each other. Connected by. In addition, the elastic body 70 interposed between the first and second hinge brackets 40 and 50 generates a restoring force in a direction in which the solar panel 20 is deployed with respect to the satellite body 10 by torque generation. .

When the satellite body 10 reaches the mission orbit, the pressing force of the pressing means (not shown) is released, so that the second hinge bracket 50 that supports the solar panel 20 as shown in FIGS. 4 and 7 is shown. The elastic body 70 is deployed in the deployment direction by the restoring force. Here, the second hinge bracket 50 is deployed to the point where the torque of the elastic body 70 becomes zero, whereby the first and second hinge brackets 40 and 50 are located in a state in which they are unfolded with each other. . Therefore, as shown in FIG. 2, the solar panel 20 generates power by facing the sun in a state in which the solar panel 20 is deployed with respect to the satellite body 10.

As described above, although described with reference to the preferred embodiment of the present invention, those skilled in the art various modifications and variations of the present invention without departing from the spirit and scope of the invention described in the claims below I can understand that you can.

1 is a perspective view schematically showing a satellite according to an embodiment of the present invention,

2 is a perspective view schematically showing a state in which a solar panel is deployed from a satellite body;

Figure 3 is a perspective view schematically showing the hinge device in a folded state as shown in Figure 1,

4 is a perspective view schematically showing a hinge device in a deployed state as shown in FIG. 2;

5 is an exploded perspective view of the hinge device;

6 is a side view of the main part of FIG. 1, and

7 is a cross-sectional view illustrating main parts of FIG. 2.

<Description of the symbols for the main parts of the drawings>

1: satellite 10: satellite body

20: solar panel 30: hinge device

40: first hinge bracket 50: second hinge bracket

60: connecting means 70: elastic body

80: fixed part

Claims (18)

A first hinge bracket installed on the first unit; A second hinge bracket installed on the second unit; And Connecting means for connecting the first and second hinge brackets and generating a restoring force when the first and second units are in a folded state facing each other; Hinge device comprising a. The method of claim 1, And the connecting means comprises a coil spring in which the restoring force is gradually reduced in a direction in which the second unit is deployed relative to the first unit. The method of claim 1, The first hinge bracket, A first support end supporting the first unit; And A first connection end bent from the first support end and connected to the connection means; Hinge device comprising a. The method of claim 3, wherein The second hinge bracket, A second support end for supporting the second unit; And A second connection end bent from the second support end and connected to the connection means; Hinge device comprising a. The method of claim 4, wherein The first and second hinge brackets, A hinge further comprising first and second guide ends protruding from each other at substantially central portions of the first and second connection ends to guide movement of the first and second hinge brackets; Device. The method of claim 4, wherein The connecting means, An elastic body for generating the restoring force; And Fixing parts fixing both ends of the elastic body to the first and second connection ends, respectively; Hinge device comprising a. The method of claim 6, And the elastic body is a coil spring. The method of claim 7, wherein The fixing part, A first insertion end inserted into the first and second connection holes penetrating through the first and second connection ends, respectively, and an outer diameter larger than the outer diameter of the first insertion end to protrude to support the inner circumferential surface of the elastic body; A first fixing member including a first protruding end; A second insertion end inserted between the first and second connection ends and the first fixing member and having an insertion hole communicating with the first and second connection holes, and bent from the second insertion end to support an outer circumferential surface of the elastic body; A second fixing member including a second protruding end; And Fastening for fixing the first and second fixing members supporting the elastic body to the first and second connecting ends facing the first and second fixing members with the first and second connecting ends interposed therebetween. Fixed plate is formed ball; Hinge device comprising a. The method according to any one of claims 1 to 8, And the first unit includes a satellite body, and the second unit includes a solar panel that is a power source of the satellite body. The method according to any one of claims 1 to 8, A regulating unit for regulating the development range by the second unit with respect to the first unit; Hinge device further comprising. A satellite body; A solar panel connected to the satellite body and receiving sunlight to generate power of the satellite body; And A hinge device connecting the satellite body and the solar panel; Including; The hinge device, A first hinge bracket installed on the satellite body; A second hinge bracket installed on the solar panel; And Connecting means for connecting the first and second hinge brackets and generating a restoring force in a folded state in which the satellite body and the solar panel face each other; Satellite comprising a. The method of claim 11, The connecting means is a satellite, characterized in that it comprises a coil spring in which the restoring force is gradually reduced in the direction in which the solar panel is deployed relative to the satellite body. The method of claim 11, The first hinge bracket, A first support end for supporting the satellite body; And A first connection end bent from the first support end and connected to the connection means; Satellite comprising a. The method of claim 13, The second hinge bracket, A second support end supporting the solar panel; And A second connection end bent from the second support end and connected to the connection means; Satellite comprising a. The method of claim 14, The first and second hinge brackets, Satellites further comprising first and second guide ends protruding from each other at substantially central portions of the first and second connection ends to guide movement of the first and second hinge brackets. . The method of claim 14, The connecting means, An elastic body for generating the restoring force; And Fixing parts fixing both ends of the elastic body to the first and second connection ends, respectively; Satellite comprising a. The method of claim 16, The fixing part, A first insertion end inserted into the first and second connection holes penetrating through the first and second connection ends, respectively, and an outer diameter larger than the outer diameter of the first insertion end to protrude to support the inner circumferential surface of the elastic body; A first fixing member including a first protruding end; A second insertion end inserted between the first and second connection ends and the first fixing member and having an insertion hole corresponding to the first and second connection holes, and bent from the second insertion end to form an outer peripheral surface of the elastic body. A second fixing member including a second protruding end for supporting the second fixing member; And Fastening for fixing the first and second fixing members supporting the elastic body to the first and second connecting ends facing the first and second fixing members with the first and second connecting ends interposed therebetween. Fixed plate is formed ball; Satellite comprising a. The method according to any one of claims 11 to 17, A regulating unit regulating the development range of the deployment state in which the solar panel is deployed from the satellite body and the restoring force is zero; Satellite containing more.

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