Separation device using pogo-pin for deployable structure of CubeSat

Abstract

A separation device for a deployable structure is configured to use the pogo-pin to supply power for severing a restraining wire. The separation device may enable the deployable structure to be elastically separated by means of an elastic force exerted thereon by a spring and may enable a deployed state of the structure to be ascertained immediately after deployment.

Claims

1. A separation device for a deployable structure of a CubeSat, the separation device being configured to enable the deployable structure to rotatably hinged at a lower end of a side surface of the CubeSat and to be folded against the side surface of the CubeSat for restraint or to be separated therefrom for deployment, the separation device comprising: a printed circuit board provided at upper edges of the CubeSat, the printed circuit board having a pogo-pin protruding outward; and a resistor board provided at an upper end of the deployable structure, the resistor board having an interface terminal coming into press contact with the pogo-pin when the deployable structure is folded against the side surface of the CubeSat and a resistor electrically connected with the interface terminal and generating heat when a current is supplied thereto from the pogo-pin, wherein the printed circuit board and the resistor board are configured such that a wire is wound thereon to cause the deployable structure to be restrained, and when the resistor supplies heat to the wire to sever the wire, the deployable structure is caused to spring back by an elastic force exerted thereon by the pogo-pin and thus to be unfolded and deployed from the side surface of the CubeSat.

2. The separation device of claim 1, wherein the deployable structure is a plurality of solar panels, and each solar panel is provided to be hinged to a corresponding lower end of each side surface of the CubeSat, the printed circuit board has a square ring shape and is attached to the upper edges of the CubeSat, and the pogo-pin is a plurality of pogo-pins, each provided at a central portion of each edge of the printed circuit board.

3. The separation device of claim 2, wherein a pair of pogo-pins are provided in parallel at each edge of the printed circuit board.

4. The separation device of claim 3, wherein the resistor board has a pair of interface terminals provided to come into contact with the pogo-pins, the respective interface terminals being electrically connected with the resistor.

5. The separation device of claim 2, wherein the printed circuit board has a first securing pin provided at each edge thereof and allowing the corresponding wire to be wound thereon.

6. The separation device of claim 5, wherein resistor board is secured to the upper end of the deployable structure by a bracket, the bracket having a second securing pin and a third securing pin that stand vertically to be distanced from each other and allow the wire to be wound thereon, and the wire is simultaneously wound on the first securing pin, the second securing pin, and the third securing pin, causing the deployable structure to be restrained.

7. The separation device of claim 6, wherein the printed circuit board has a first securing pin insertion notch and a second securing pin insertion notch formed at each corresponding edge thereof such that the second securing pin and the third securing pin are inserted into and seated in the notches, respectively.

8. The separation device of claim 2, wherein the printed circuit board has a single power supply connector provided to supply power to the respective pogo-pins from an external power source.

9. A CubeSat having the separation device of claim 1, wherein the printed circuit board is mounted at upper edges of the CubeSat, and the resistor board is mounted at an upper end of the deployable structure.

10. The CubeSat of claim 9, wherein the deployable structure is a solar panel, and the solar panel is provided to be hinged to a lower end of each side surface of the CubeSat, the printed circuit board has a square ring shape and is attached to the upper edges of the CubeSat, and each pogo-pin is provided at a central portion of each edge of the printed circuit board.

11. The CubeSat of claim 10, wherein a pair of pogo-pins are provided in parallel at each edge of the printed circuit board.

12. The CubeSat of claim 10, wherein the printed circuit board has a single power supply connector provided to supply power to the respective pogo-pins from an external power source.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) The above and other aspects, features and other advantages of the present invention will be more clearly understood from the following detailed description when taken in conjunction with the accompanying drawings, in which:

(2) FIG. 1 are views showing a typical CubeSat;

(3) FIG. 2 is a view showing a state where a separation device for a deployable structure according to an embodiment of the present invention restrains the deployable structure;

(4) FIG. 3 is a view showing a state where the separation device for the deployable structure according to the embodiment of the present invention separates and releases the deployable structure from restraint;

(5) FIG. 4 is an enlarged view showing the state where the separation device for the deployable structure according to the embodiment of the present invention restrains the deployable structure;

(6) FIG. 5 is an enlarged view showing the state where the separation device for the deployable structure according to the embodiment of the present invention releases the deployable structure from restraint; and

(7) FIG. 6 is a view showing results of a separation test for the separation device for the deployable structure according to the embodiment of the present invention.

DETAILED DESCRIPTION

(8) Although the terms used in the description of the present invention are selected from generally known and used terms, some of the terms mentioned in the description of the present invention have been selected by the applicant, the detailed meanings of which should be understood not simply by the actual terms used, but by the meaning of each term as desired in the detailed description of the invention and/or in consideration of the meanings used.

(9) Hereinafter, a detailed description will be given for the technical configuration of the present invention with reference to embodiments illustrated in the accompanying drawings.

(10) However, the present invention is not limited to such embodiments and may be achieved in other ways. The same reference numerals will be used throughout the drawings and the description to refer to the same or like elements or parts.

(11) Referring to FIGS. 2 to 4, a separation device 100 for a deployable structure according to an embodiment of the present invention is a device that enables a deployable structure 11 rotatably hinged to a lower end of a side surface of a CubeSat 10 to be folded against the side surface of the CubeSat 10 for restraint or to be separated therefrom for deployment.

(12) Furthermore, the deployable structure 11 may be a solar panel that supplies power to the CubeSat 10.

(13) The separation device 100 for the deployable structure includes a printed circuit board 110 and a resistor board 120.

(14) The printed circuit board 110 is a PCB substrate provided at upper edges of the CubeSat 10.

(15) Furthermore, the printed circuit board 110 is provided with a pogo-pin 111 protruding outward.

(16) The pogo-pin 111 is a connection terminal for performing electrical conduction between two circuit boards and is configured with a cylindrical housing, a piston-shaped connection terminal linearly movable into the housing, and a spring provided inside the housing to elastically support the connection terminal outward.

(17) Furthermore, the pogo-pin 111 is provided as a pair of pogo-pins 111 distanced from each other, one of which is used as a (+) terminal and the other is used as a (−) terminal.

(18) Furthermore, the pogo-pin 111 may be provided according to the number of deployable structures 11. If the CubeSat 10 has four sides surfaces each having the deployable structure 11, the CubeSat 10 has four upper edges each having the pogo-pin 111.

(19) In this case, the printed circuit board 110 is formed into a square ring shape and attached to the upper edges of the CubeSat 10, and each pair of pogo pins 111 protrude outward from a central portion of each edge of the printed circuit board 110.

(20) The resistor board 120 is provided at an upper end (upper end in a folded state) of the deployable structure 11 and includes an interface terminal 121 coming into contact with the pair of pogo-pins to be in electrical contact therewith and a resistor 122 electrically connected with the interface terminal 121 and generating heat when a current is applied thereto.

(21) Furthermore, the resistor board 120 may be secured to the upper end of the deployable structure 11 by a bracket 130.

(22) Meanwhile, the printed circuit board 110 and the resistor board 120 are restrained to each other by a wire 140 melted by heat and severed. The resistor 122 supplies heat to the wire 140 to sever the wire, causing the deployable structure 11 to spring back by means of a spring elastic force exerted thereon by the pogo pins 111 and thus to be unfolded and deployed from the side surface of the CubeSat 10.

(23) Furthermore, the printed circuit board 110 has a first securing pin 112 standing vertically and allowing the wire 140 to be wound thereon, while the bracket 130 has a second securing pin 131 and a third securing pin 132 that stand vertically to be distanced from each other with the resistor board 120 interposed therebetween and allow the wire 140 to be wound thereon.

(24) In other words, the wire 140 is simultaneously wound on the outer peripheries of the first securing pin 112, the second securing pin 131, and the third securing pin 132 to form a loop configuration, causing the deployable structure 11 to be restrained.

(25) Furthermore, the wire 140 is simultaneously wound on the first securing pin 112, the second securing pin 131, and the third securing pin 132 while being in contact with the resistor 122.

(26) Thus, the wire 140 causes the deployable structure 11 to be restrained in a direction of rotation of the deployable structure 11.

(27) Meanwhile, the deployable structure 11 may rotate in a lateral direction on the side surface of the CubeSat 10, in which case a lower hinge may be broken and thus separated from the CubeSat 10.

(28) Thus, the present invention provides a first securing pin insertion notch 113 and a second securing pin insertion notch 114 each formed at each edge of the printed circuit board 110 such that when the deployable structure 11 is folded, the second securing pin 131 and the third securing pin 132 are inserted into and seated in the notches, respectively. This makes it possible to prevent the deployable structure 11 from rotating in the lateral direction in a restrained state (rotating about the axis perpendicular to the side surface of the CubeSat).

(29) In other words, the separation device 100 for the deployable structure according to the embodiment of the present invention enables the deployable structure 11 to be restrained both in the direction of rotation and in the lateral direction, achieving a significant improvement of the stability of restraint.

(30) Furthermore, the printed circuit board 110 has a power supply connector 115 provided to supply power to the respective pogo-pins 111. The respective pogo-pins 111 are electrically connected to each other on the printed circuit board 110, so it is sufficient that the connector 115 is a single connector. Accordingly, this is advantageous in overcoming constraints of the space and weight of the CubeSat.

(31) Furthermore, the pogo-pins 111 are configured to have no current flowing therethrough when the deployable structure 11 is separated and thus also serves as switches for checking whether the deployable structure 11 is deployed. Accordingly, this is advantageous in that there is no need an additional system for checking whether deployment is performed.

(32) FIG. 6 is a view showing results of a separation test for the separation device for the deployable structure according to the embodiment of the present invention.

(33) Referring to FIG. 6, as a result of an operation function test when a voltage of 8 V is applied to the pogo-pins 111, a solar panel was first deployed in 0.8 seconds, and all the solar panels were deployed in 1.4 seconds.

(34) Although a preferred embodiment of the present invention has been described for illustrative purposes, those skilled in the art will appreciate that various modifications, additions and substitutions are possible, without departing from the scope and spirit of the invention as disclosed in the accompanying claims.