KR102134620B1 - Satellite projectile having vibration reducing function and launching method using the same - Google Patents

Abstract

The present invention relates to a satellite projectile having a vibration reducing function, to provide a satellite projectile having a vibration reducing function provided with a fixing means on the top of the projectile so that the cube satellite accommodated in the projectile does not shake in the projectile when the projectile is launched into space The purpose. The satellite projectile having the vibration reducing function of the present invention is installed on the top of the projectile, and is provided with a fixing means movable in the vertical direction so as to fix the cube satellite accommodated inside the projectile. The cube satellite can be fixed by adjusting, and since the cube satellite is not shaken inside the projectile by the fixing means, when the projectile that does not need the projectile is launched into space, the cube satellite can move in a certain orbit without shaking within the projectile.

Description

Satellite projectile having vibration reducing function and launching method using the same}

The present invention relates to a satellite projectile having a vibration reduction function and a launching method using the same, and more specifically, the cube satellite is fixed to the projectile for accommodating the cube satellite therein and injecting the cube satellite in a certain orbit so as not to be shaken inside the projectile. The present invention relates to a satellite projectile having a configuration and a launching method using the same.

Cube satellite or Cubesat refers to an ultra-small satellite having a volume of 1L (10cmㅧ10cmㅧ10cm) and a mass of about 1.3kg, which has been developed for educational purposes but has been commercialized due to its excellent price/performance ratio.

Because of its small size, it is one-thousandth of the cost of a large satellite from development to launch, so it is less burdensome even if it breaks down. Existing large satellites require a one-to-one counterpart, but Cube Satellite has a fixed projectile itself. Therefore, it is economical because a single projectile can be used because it can be accommodated inside the projectile, lifted up to a certain orbit, and injected into the outer space of the cube satellite with the compression force of the spring inside the projectile.

The cube satellite is accommodated inside the projectile, launched into a certain orbit, and the spring installed in the projectile expands to launch the cube satellite into outer space. At this time, a rail for guiding the cube satellite is installed inside the projectile. The rail and the cube satellite are spaced apart at a predetermined distance so that the cube satellite can be easily moved.

At this time, when the projectile is launched in a certain orbit, the cube satellite and the cube satellite accommodated inside the projectile are shaken because the space between the cube satellite and the rail is spaced apart, and an unnecessary collision occurs.

Due to such collisions, the structural destructiveness of the cube satellites increases and the probability of causing unpredictable electrical or mechanical failures increases, and thus there is a need for a projectile that accommodates the cube satellites without shaking.

The present invention has been devised to solve the above problems, and an object of the present invention is to provide a vibration reducing function provided with a fixing means on the top of the projectile so that the cube satellite accommodated in the projectile does not shake within the projectile when the projectile is launched into space. It is to provide a satellite projectile.

A satellite projectile having a vibration reducing function of the present invention is a satellite projectile formed in a housing shape that receives a cube satellite therein and is launched into outer space, and is formed in front, rear, and four sides facing each other, the satellite projectile A rail installed in the longitudinal direction of the satellite projectile to guide movement of the cube satellite; An elastic part installed on a rear surface of the satellite projectile and supplying a force to cause the cube satellite to be injected into outer space; A door formed to be opened and closed on the front of the satellite projectile and opened when the cube satellite is ejected into outer space; And fixing means installed on at least one of the side surfaces of the satellite projectile to be movable to the side or opposite side, and preventing vibration of the cube satellite when the satellite projectile is launched into outer space. It is characterized by.

In addition, the satellite projectile is characterized in that the side where the fixing means is installed is formed as an opening and closing part that can be opened and closed.

In addition, the rail is formed of a rail structure separated into a plurality of pieces in the longitudinal direction, characterized in that the rail structure is installed spaced apart a predetermined distance, the fixing means is characterized in that disposed between the rail structure .

In addition, the fixing means is characterized in that installed on the opening and closing portion spaced apart from the rail a predetermined distance.

In addition, the satellite projectile is installed on the side where the fixing means is installed, a lever that is installed to be rotatable on the side or opposite side of the fixing means is installed; It is formed to protrude from the middle of the lever, and further includes a pressing portion for pressing the side on which the fixing means is installed. Further, at least a part of the side on which the fixing means is installed is formed as a contact portion pressed by the pressing portion, Depending on whether or not the pressing portion is pressed, it is characterized in that it is movable to the side or opposite side of the fixing means.

In addition, the contact portion is characterized in that it is formed of an elastic body, the fixing means is attached to the end of the contact portion, the fixing means is characterized in that moving together along the movement direction of the contact portion.

In addition, the door and the opening and closing portion, it characterized in that the hinge and the satellite projectile.

In addition, the door and the lever, it characterized in that the hinge and the satellite projectile.

In addition, the fixing means is characterized in that the protection portion is formed on the surface in contact with the cube satellite.

In addition, the fixing means is characterized in that the distance from the side where the fixing means is installed is adjustable according to the size of the cube satellite.

In addition, the satellite projectile is characterized in that when the satellite projectile reaches a predetermined orbit, the door and the opening and closing part are opened and the cube satellite is injected out of the satellite projectile by the elasticity of the elastic part.

In addition, the satellite projectile, when the satellite projectile reaches a predetermined orbit, the lever is separated from the satellite projectile, the door is opened, and the cube satellite is ejected out of the satellite projectile by elasticity of the elastic part Satellite projectile, characterized in that.

A satellite launching method using a satellite launching object of the present invention, the satellite launching step of launching the satellite launching body containing the cube satellite into outer space; An orbit entry determination step of determining whether the satellite projectile has entered a predetermined orbit; An opening/closing opening step in which the opening/closing section is opened when it is determined that the satellite launch vehicle has entered a predetermined orbit in the orbit determination step; A door opening step in which the door is opened; And receiving the force from the elastic part, and the cube satellite is ejected from the satellite projectile and launched into the outer space.

In addition, a satellite projectile launching step of launching the satellite projectile in which the cube satellite is accommodated into outer space; An orbit entry determination step of determining whether the satellite projectile has entered a predetermined orbit; A lever separation step in which the lever is separated when it is determined that the satellite launch vehicle has entered a predetermined orbit in the orbit entry determination step; A door opening step in which the door is opened; And receiving the force from the elastic part, and the cube satellite is ejected from the satellite projectile and launched into the outer space.

The satellite projectile having the vibration reduction function of the present invention according to the above-described configuration is installed on the top of the projectile, and is provided with a fixing means movable in the vertical direction to fix the cube satellite accommodated inside the projectile. Regardless, the cube satellite can be fixed by adjusting the fixing means.

In addition, since the cube satellite is not shaken inside the projectile by the fixing means, when the projectile that does not need the projectile is launched into space, the cube satellite can move in a certain orbit without shaking within the projectile.

1 is a side sectional view of a conventional satellite projectile
2 to 4 are side views of a satellite projectile according to a first embodiment of the present invention
Figure 5 is a perspective view of the opening and closing of the satellite projectile according to the first embodiment of the present invention
6 is a front view of a satellite projectile according to a first embodiment of the present invention
7 is a side view of the opening and closing portion of the satellite projectile according to the first embodiment of the present invention
8 to 10 are side views of a satellite projectile according to a second embodiment of the present invention
11 is a perspective view of an opening and closing portion of a satellite projectile according to a second embodiment of the present invention
12 is a front view of a satellite projectile according to a second embodiment of the present invention
13 is a side view of an opening and closing part of a satellite projectile according to a second embodiment of the present invention
14 to 16 are side views of a satellite projectile according to a third embodiment of the present invention
17 is a top perspective view of a satellite projectile according to a third embodiment of the present invention
18 is a front view of a satellite projectile according to a third embodiment of the present invention
19 is a top side view of a satellite projectile according to a third embodiment of the present invention

Hereinafter, an embodiment of the present invention will be described in detail with reference to the drawings.

1 shows a side sectional view of a conventional satellite projectile. As shown in FIG. 1, the cube satellite 10 is accommodated inside the satellite projectile 20, and the satellite projectile 20 is launched into outer space while receiving the cube satellite 10.

The satellite projectile 20 is composed of four sides that surround the front and rear faces and the front and rear faces in the form of a rectangular parallelepiped enclosure. An elastic portion 25 is installed at the rear of the satellite projectile 20 to provide a force for injecting the cube satellite 10 from the satellite projectile 20 into outer space, and the front of the satellite projectile 20 is an openable door (23).

When the satellite projectile 20 reaches a predetermined orbit, the door 23 is opened, and the cube satellite 10 receives force from the elastic portion 25 and the cube satellite 10 is launched into outer space.

At this time, a rail for guiding the movement of the cube satellite 10 is installed inside the projectile 20. For ease of description, the rail is divided into a lower rail 21 and an upper rail 22 to be described.

The cube satellite 10 is accommodated at a predetermined distance from the rail to be ejected from the satellite projectile 20 into outer space. At this time, when the satellite projectile 20 is launched into outer space, the cube satellite 10 accommodated inside the satellite projectile 20 collides with the lower rail 21 and the upper rail 22, thereby damaging the cube satellite 10 There is a concern that it can be.

The satellite projectile of the present invention was devised to solve the above-described problem, and will be described in more detail with reference to FIGS. 2 to 19.

<First Example>

2 to 4 are side sectional views of a satellite projectile according to a first embodiment of the present invention. As shown in FIG. 2, the cube satellite 100 is accommodated inside the satellite projectile 200.

The rear surface of the satellite projectile 200 is provided with an elastic part 240 that provides a force to move the cube satellite 100 to be injected into outer space. The front surface of the satellite projectile 200 is formed of a door 230 that is installed to be opened and closed, and the door 230 is hinged to the satellite projectile 200 by a door hinge 231.

In addition, a rail including a lower rail 210 and an upper rail 220 that guides the movement of the cube satellite 100 when the cube satellite 100 is injected into outer space is installed inside the satellite projectile 200. .

At least one of the four sides of the satellite projectile 200 is formed of an opening and closing part 250 that can be opened and closed, and a fixing means 260 for preventing vibration of the cube satellite 100 is installed in the opening and closing part 250.

In addition, a locking device 252 is further installed at the end of the opening/closing part 250, and the door 230 and the opening/closing part 250 are not opened until the cube satellite 100 is injected into outer space in combination with the door 230. Do not.

In order to describe one embodiment of the present invention, it is assumed that the upper surface of the side surfaces of the satellite projectile 200 is formed by the opening/closing part 250, and this is not intended to limit the side formed by the opening/closing part 250.

The upper rail 220 of the satellite projectile 200 according to the first embodiment of the present invention is installed as being separated into a plurality of structures, as shown in Figure 2, is installed spaced a predetermined distance. The fixing means 260 is preferably formed in a size corresponding to the gap between the upper rails 220 and is preferably installed in a shape inserted between the upper rails 220.

Fixing means 260 is installed is attached to the opening and closing portion 240, is installed to be movable in the longitudinal direction by the height adjustment unit 261. Therefore, since the fixing means 260 is installed to be movable up and down by the height adjusting unit 261, the height adjusting unit 261 is adjusted so that the fixing means 260 contacts the cube satellite 100, and the cube satellite (100) is fixed so as not to move inside the satellite projectile 200 by the pressure received from the fixing means (260).

Since the cube satellite 100 is fixed by the fixing means 260 so as not to move, the cube satellite 100 does not generate unnecessary collisions inside the satellite projectile 200 while the satellite projectile 200 is launched into outer space. There is an effect that the cube satellite 100 can be stably moved.

3 is a side sectional view showing a state in which the satellite 230 of the present invention enters a predetermined orbit and the door 230 and the opening and closing part 250 are opened, and FIG. 4 is the door 230 and the opening and closing part of the satellite projectile of the present invention. 250 is a side cross-sectional view showing a process in which the cube satellite 100 is ejected into the outer space by receiving the force from the elastic portion 240.

3 and 4, the locking device 252 is released to open and close the opening 250, and at the same time, the door 230 is also opened.

At this time, the door 230 is hinged by the satellite projectile 200 and the door hinge 231, and the opening and closing portion 250 is also hinged to the satellite projectile 200 by the opening and closing portion hinge 251.

When the opening/closing part 250 is opened, since the fixing means 260 also moves along the opening/closing part 250, the cube satellite 100 fixed by the fixing means 260 is free to move, and the lower rail 210 and It may be injected into the outer space along the upper rail 220.

The elastic part 240 in the compressed state expands and transmits compressive force to the cube satellite 100, and the cube satellite 100 receives the lower rail 210 and the upper rail 220 by the force transmitted from the elastic part 240. ) To be ejected into outer space.

5 is a perspective view showing an opening and closing part of a satellite projectile according to a first embodiment of the present invention. As shown in FIG. 5, at least one height adjusting unit 261 is attached to the lower portion of the plate-shaped opening and closing unit 250, and a fixing means 260 is attached to the lower end of the height adjusting unit 261.

At this time, the lower portion of the fixing means 260 may be further formed of a protective material of an elastic material for preventing slip.

6 is a front view of a satellite projectile according to a first embodiment of the present invention. 6, the upper rail 220 and the lower rail 210 are fixedly installed inside the satellite projectile 200, and the fixing means 260 is fixedly installed on the opening/closing part 250, but the height adjustment part ( 261) is installed to be movable to the side of the opening and closing portion 250 or the opposite side of the opening and closing portion 250.

The upper rail 220 is installed at a predetermined distance from the cube satellite 100, and the fixing means 260 is in contact with the cube satellite 100 so that the cube satellite 100 does not shake inside the satellite projectile 200.

When the satellite projectile 200 reaches a predetermined orbit, the opening/closing part 250 is opened, and the fixing means 260 also moves along the opening/closing part 250, so that the cube satellite 100 is unfixed and the upper rail 220 ) And the lower rail 210 to be ejected into outer space.

7 shows a side view of an opening and closing part of a satellite projectile according to a first embodiment of the present invention. As shown in FIG. 7, one end of the height adjustment unit 261 is coupled to the opening/closing unit 250, and the other end is coupled to the fixing means 260. The opening and closing portion 250 is preferably formed with a screw hole so as to be combined with the height adjusting portion 261, and the height adjusting portion 261 is formed to be movable up and down by tightening or loosening the screw.

Therefore, the height adjustment unit 261 can move the fixing means 260 coupled to the other end of the height adjustment unit 261 by the operation of tightening or loosening the screw to the opening/closing part 250 side or the opposite side of the opening/closing part 250. have.

In general, the size of the cube satellite 100 accommodated inside the satellite projectile 200 is standardized, but in the present invention, the height is adjusted so that the cube satellite 100 can be fixed regardless of the size of the cube satellite 100. The fixing means 260 may be moved by adjusting the portion 261.

At this time, in order to adjust the position of the fixing means 260 according to the size of the cube satellite 100, an elastic body such as a spring is installed as well as a height adjusting part 261 between the opening and closing part 250 and the fixing means 260. The position of the fixing means 260 may be automatically adjusted according to the size of the cube satellite 100 without additional adjustment.

<Second Example>

8 to 10 are sectional side views of a satellite projectile according to a second embodiment of the present invention. Since the configuration except for the opening/closing part 250 and the upper rail 270 is the same as the first embodiment described above, description thereof will be omitted.

In the satellite projectile 200 according to the second embodiment of the present invention, the lower rail 210 and the upper rail 270 are installed at a date without being spaced apart from the unit structure as in the first embodiment, and are opened and closed. Fixing means 280 installed on the 250 is also formed with a length similar to the lower rail 210 and the upper rail 270, using the height adjustment unit 281, the fixing means 280 to the opening and closing portion 250 side or opening and closing portion (250) can be moved to the opposite side, the opening and closing portion 250 is moved to the opposite side to fix the cube satellite 100 so as not to vibrate within the satellite projectile 200.

9 and 10, the locking device 252 is released to open and close the opening 250, and at the same time, the door 230 is also opened.

At this time, the door 230 is hinged by the satellite projectile 200 and the door hinge 231, and the opening and closing portion 250 is also hinged to the satellite projectile 200 by the opening and closing portion hinge 251.

When the opening/closing part 250 is opened, since the fixing means 280 also moves along the opening/closing part 250, the cube satellite 100 fixed by the fixing means 280 is free to move, and the lower rail 210 and It can be injected into the outer space along the upper rail 270.

The elastic part 240 in the compressed state expands and transmits compressive force to the cube satellite 100, and the cube satellite 100 receives the lower rail 210 and the upper rail 270 by the force transmitted from the elastic part 240. ) To be ejected into outer space.

11 is a perspective view showing an opening and closing part of a satellite projectile according to a second embodiment of the present invention. As shown in FIG. 11, at least one height adjustment unit 281 is attached to the center of the plate-shaped opening/closing unit 250, and fixing means 280 is provided at the lower end of the height adjustment unit 281 to the satellite projectile 200 ) Along the longitudinal direction.

At this time, the lower portion of the fixing means 280 may be further formed of a protective material of an elastic material for preventing slip.

12 is a front view of a satellite projectile according to a second embodiment of the present invention. As shown in FIG. 12, the cube satellite 100 is accommodated inside the satellite projectile 200, and the lower rail 210 and the upper rail 270 are installed inside the satellite projectile 200. The opening/closing part 250 is installed to be opened and closed, and a fixing means 280 is installed on the opening/closing part 250.

The fixing means 280 is preferably installed in the center of the opening/closing part 250, but is not intended to be limited thereto, and the width of the fixing means 280 and the upper rail 270 so that the opening/closing part 250 can be opened and closed smoothly. It is preferably formed so as not to contact.

When installed as in the second embodiment of the present invention, since the upper rail 270 and the lower rail 210 are installed without separation in the longitudinal direction of the satellite projectile 200, it is easy to guide the movement of the cube satellite 100 Since the fixing means 280 presses the center of the cube satellite 100, there is an effect that the pressure received by the cube satellite 100 is not concentrated on the side surface.

13 shows a side view of an opening and closing part of a satellite projectile according to a second embodiment of the present invention. As shown in Figure 13, one end of the height adjustment unit 281 is coupled to the opening and closing portion 250, the other end is coupled to the fixing means 280. The opening and closing portion 250 is preferably formed with a screw hole to be combined with the height adjusting portion 281, and the height adjusting portion 281 is formed to be movable up and down by tightening or loosening the screw.

Therefore, the height adjustment unit 281 can move the fixing means 280 coupled to the other end of the height adjustment unit 281 to the opening/closing part 250 side or the opposite side of the opening/closing part 250 by tightening or loosening the screw. have.

In general, the size of the cube satellite 100 accommodated inside the satellite projectile 200 is standardized, but in the case of the present invention, the height adjustment unit can fix the cube satellite 100 regardless of the size of the cube satellite 100 The fixing means 280 may be moved by adjusting the 281.

At this time, in order to adjust the position of the fixing means 280 according to the size of the cube satellite 100, an elastic body such as a spring is installed as well as a height adjusting part 281 between the opening and closing part 250 and the fixing means 280. The position of the fixing means 280 may be automatically adjusted according to the size of the cube satellite 100 without additional adjustment.

<Example 3>

14 to 16 are side sectional views of a satellite projectile according to a third embodiment of the present invention. The configuration except for the lever 300, the upper rail 290, and the opening/closing part 250 is the same as the first and second embodiments described above, and thus descriptions thereof will be omitted.

The satellite projectile 200 according to the third embodiment of the present invention is characterized in that the fixing means is not formed separately, and the upper rail 290 or the lower rail 210 simultaneously serves as a rail and the fixing means.

In order to describe the embodiment of the present invention, it is assumed that the upper rail 290 serves as a fixing means, and when the side where the lower rail 210 is installed, the side where the upper rail 290 is installed is referred to as an upper surface.

Unlike the first embodiment or the second embodiment, the third embodiment is characterized in that the side surface is not opened and closed when the cube satellite 100 is ejected from the satellite projectile 200, and the upper rail 290 is pressed by pressing the upper surface. The cube satellite 100 is fixed by moving it downward to fix the cube satellite 100 from moving, and when the cube satellite 100 is injected, the pressure applied to the upper surface is released so that the upper rail 290 moves upwards. It is desirable to be able to move along the rail.

In more detail, as shown in FIG. 14, a lever 300 is formed on the upper surface, one end of the lever 300 is hinged by a lever hinge 301, and the other end of the lever 301 is a locking device. 302 is formed and coupled with the door 230.

In the middle of the lever 300, a pressing part 310 is formed, the pressing part 310 presses the upper surface of the satellite projectile 200, the upper rail 290 moves downward, and the pressing part 310 is When separated from the upper surface of the satellite projectile 200, the upper rail 290 moves upward.

To this end, it is preferable that at least a part of the upper surface of the satellite projectile 200 is formed with a contact portion A in contact with the pressing portion 310, and the contact portion A is formed of an elastic body and does not contact the pressing portion 310. It is desirable to be installed so that it can be automatically raised when not in use.

In addition, since the contact portion (A) is attached and installed with the upper rail 290, the position of the upper rail 290 can be adjusted, and when the pressing portion 310 presses the contact portion (A), the upper rail 290 is lowered. By moving to and fixing the cube satellite 100, when the pressing portion 310 and the contact portion (A) are separated, the upper rail 290 may move upward to move the cube satellite 100 freely.

15 and 16, the locking device 302 is released so that the lever 300 rotates counterclockwise by the lever hinge 301, and at the same time, the door 230 is also opened.

When the crowbar 300 falls from the upper surface of the satellite projectile 200, the pressing portion 310, which was pressing the contact portion A, is separated from the contact portion A, and the contact portion A is formed of an elastic body so that the original position The upper rail 290, which is in contact with the cube satellite 100, moves away from the cube satellite 100 due to the restoring force to return to.

The cube satellite 100 fixed by the upper rail 290 is free to move, and may be injected into outer space along the lower rail 210 and the upper rail 290.

The elastic part 240 in the compressed state expands and transmits compressive force to the cube satellite 100, and the cube satellite 100 receives the lower rail 210 and the upper rail 290 by the force transmitted from the elastic part 240. ) To be ejected into outer space.

17 is a top perspective view of a satellite projectile 200 according to a third embodiment of the present invention. As shown in FIG. 17, a lever 300 is hinged and coupled by a lever hinge 301 on the upper surface of the satellite projectile 200, and a pressing part 310 is formed at the middle of the lever 300. .

Part of the upper surface is in contact with the pressing portion 310, the contact portion (A) is installed to be movable in the height direction by the pressing portion 310 is formed, the contact portion (A) is pressed when the pressing portion 310 It is preferable to move down and move upward when the pressing part 310 is separated.

At this time, the pressing part 310 is formed by being attached to the upper rail 290, the upper rail 290 is characterized in that it moves down and moves up according to the movement of the contact portion (A).

18 is a front view of a satellite projectile according to a third embodiment of the present invention. As shown in FIG. 18, the lever 300 is shown to be fixed so that the cube satellite 100 does not move in contact with the upper surface of the satellite projectile 200, and the pressing part 310 attached to the lever 300 ) Presses the contact portion (A), and as the contact portion (A) moves downward, the top rail (290) also moves down, and the cube satellite (100) and the top rail (290) contact to move the cube satellite (100). ) Is to prevent the satellite projectile 200 from shaking inside.

19 is a side view of an opening and closing portion of a satellite projectile according to a third embodiment of the present invention. (a) is to fix the cube satellite 100, (b) is to allow the cube satellite 100 to move.

As shown in (a) of Figure 19, the lever 300 and the upper surface of the satellite projectile 200 is in contact with the pressing portion 310 formed protruding in the middle of the lever 300 is formed on the upper surface of the satellite projectile 200 The contact portion (A) is pressed, and the contact portion (A) moves downward by the pressure received from the pressing portion (310).

The upper rail 290 attached to the lower end of the contact portion (A) moves down along the contact portion (A) to contact the cube satellite (100) and secures the cube satellite (100) from moving.

When the satellite projectile 200 reaches a predetermined orbit, the locking device 302 formed at one end of the lever 300 is released as shown in FIG. 19(b), and the lever hinge installed at the end of the lever 300 ( The lever 300 moves in the counterclockwise direction by 301, and the contact portion A moves upward because the pressing portion 310 that pressurized the contact portion A is also separated from the contact portion A.

As the contact portion A moves upward, the upper rail 290 also moves upward, and a predetermined distance is spaced between the cube satellite 100 and the upper rail 290. Accordingly, the cube satellite 100 is free to move, and the cube satellite 100 receives the compressive force from the elastic part 240 and moves along the upper rail 290 and the lower rail 210 to move the satellite projectile 200. Is injected out.

The common features of the first to third embodiments are the height adjusters 261, 281, and 291, which are installed so as to be movable to the side or the side opposite to at least one side of the satellite projectile 200, Cube means by applying pressure to the cube satellite 100 by moving the fixing means 260, 280 or the upper rail 290 formed at the ends of the height adjusters 261, 281, 291 to make contact with the cube satellite 100. It is to prevent (100) from moving.

In addition, when the cube satellite 100 is injected to the outside, in the first and second embodiments, the pressure applied to the cube satellite 100 disappears as the opening/closing part 250 is opened, and the movement of the cube satellite 100 is prevented. In the third embodiment, the pressure applied to the cube satellite 100 disappears as the lever 300 that pressurizes the contact portion A is separated from the contact portion A, and the movement of the cube satellite 100 is free. It is becoming.

It should not be interpreted that the technical spirit is limited to the above-described embodiments of the present invention. Of course, the scope of application is various, and various modifications can be implemented at the level of those skilled in the art without departing from the gist of the present invention as claimed in the claims. Accordingly, such improvements and modifications fall within the protection scope of the present invention as long as it is apparent to those skilled in the art.

10, 100 cube satellite
20, 200 satellite projectiles
21, 210 bottom rail
22, 220, 270, 290 top rail
23, 230 door
24, 231 door hinge
25, 240 elastic part
250 switchgear
251 hinge hinge
252, 302 lock
260, 280 fixing means
261, 281, 291 height adjustment
300 lever
301 lever hinge
310 pressing part
A contact

Claims (14)

In the satellite launch vehicle in the form of a housing formed by accommodating the cube satellite inside, launched into outer space, facing each other, the front, back and four sides,
A rail installed inside the satellite projectile in the longitudinal direction of the satellite projectile and guiding the movement of the cube satellite;
An elastic part installed on a rear surface of the satellite projectile and supplying a force to cause the cube satellite to be injected into outer space;
A door formed to be opened and closed on the front of the satellite projectile and opened when the cube satellite is ejected into outer space; And
A fixing means installed on at least one of the side surfaces of the satellite projectile to be movable to a side or opposite side, and preventing vibration by pressing the cube satellite when the satellite projectile is launched into outer space;
It includes,
A satellite projectile characterized in that the side on which the fixing means is installed is formed by an opening and closing part that can be opened and closed.
delete The method of claim 1, wherein the rail,
It is formed of a rail structure separated into a plurality in the longitudinal direction, characterized in that the rail structure is installed spaced a predetermined distance,
The fixing means,
Satellite projectile, characterized in that disposed between the rail structure.
According to claim 1, The fixing means,
A satellite projectile, characterized in that spaced apart from the rail by a predetermined distance on the opening and closing portion.
In the satellite launch vehicle in the form of a housing formed by accommodating the cube satellite inside, launched into outer space, facing each other, the front, back and four sides,
A rail installed inside the satellite projectile in the longitudinal direction of the satellite projectile and guiding the movement of the cube satellite;
An elastic part installed on a rear surface of the satellite projectile and supplying a force to cause the cube satellite to be injected into outer space;
A door formed to be opened and closed on the front of the satellite projectile and opened when the cube satellite is ejected into outer space;
A fixing means installed on at least one of the side surfaces of the satellite projectile to be movable to a side or opposite side, and preventing vibration by pressing the cube satellite when the satellite projectile is launched into outer space;
A lever that is installed on a side where the fixing means is installed, and is rotatably installed on a side or opposite side of the fixing means; And
It is formed to protrude from the middle of the lever, and pressurizing portion for pressing the side where the fixing means is installed.
A satellite projectile, characterized in that at least a part of the side where the fixing means is installed is formed as a contact portion that is pressed by the pressing portion, and is movable to a side or opposite side of the fixing means installed depending on whether the pressing portion is pressed.
The method of claim 5, wherein the contact portion,
It characterized in that it is formed of an elastic body, the fixing means is attached to the end of the contact portion, the fixing means is a satellite projectile, characterized in that moving together along the movement direction of the contact portion.
According to claim 1, The door and the opening and closing portion,
The satellite projectile, characterized in that hinged to the satellite projectile.
According to claim 5, The door and the lever,
The satellite projectile, characterized in that hinged to the satellite projectile.
The fixing means according to claim 1 or 5,
A satellite projectile, characterized in that a protective part is formed on a surface in contact with the cube satellite.
The fixing means according to claim 1 or 5,
The satellite projectile, characterized in that the distance from the side where the fixing means is installed is adjustable according to the size of the cube satellite.
The method according to claim 3 or 4, wherein the satellite projectile,
When the satellite projectile reaches a predetermined orbit, the door and the opening and closing portion is opened, the satellite projectile, characterized in that the elastic satellite to eject the cube satellite out of the satellite projectile.
The method of claim 6, wherein the satellite projectile,
When the satellite projectile reaches a predetermined orbit, the lever is separated from the satellite projectile, the door is opened, and the satellite projectile characterized by injecting the cube satellite out of the satellite projectile by elasticity of the elastic part .
In the satellite launch method using the satellite projectile of claim 3 or 4,
A satellite projectile launching step of launching the satellite projectile containing the cube satellite into outer space;
An orbit entry determination step of determining whether the satellite projectile has entered a predetermined orbit;
An opening/closing opening step in which the opening/closing section is opened when it is determined that the satellite launch vehicle has entered a predetermined orbit in the orbit determination step;
A door opening step in which the door is opened;
A cube satellite injection step in which the cube satellite is ejected from the satellite projectile and is launched into outer space by receiving a force from the elastic part;
Satellite launch method using a satellite projectile comprising a.
In the satellite launch method using the satellite launch vehicle of claim 6,
A satellite projectile launching step of launching the satellite projectile containing the cube satellite into outer space;
An orbit entry determination step of determining whether the satellite projectile has entered a predetermined orbit;
A lever separation step in which the lever is separated when it is determined that the satellite launch vehicle has entered a predetermined orbit in the orbit entry determination step;
A door opening step in which the door is opened;
A cube satellite injection step in which the cube satellite is ejected from the satellite projectile and is launched into outer space by receiving a force from the elastic part;
Satellite launch method using a satellite projectile comprising a.

Images