KR102664656B1 - Insert-type Bay comprising Detachable member for System for Loading Multiple Payload for Space Launch Vehicle - Google Patents

Abstract

The present invention relates to an insertable bay for a satellite multiple loading system for a space launch vehicle including a detachable member. More specifically, the present invention relates to an insertable bay for a satellite multiple loading system for a space launch vehicle, and more specifically, to detach the plate on which the deployer is fixed to attach the deployer and the payload placed inside the deployer. The present invention relates to an insertion bay for a satellite multiple payload system for a space launch vehicle that includes a detachable member that can more easily perform rod maintenance.

Description

{Insert-type Bay comprising Detachable member for System for Loading Multiple Payload for Space Launch Vehicle}

The present invention relates to an insertable bay for a satellite multiple loading system for a space launch vehicle including a detachable member. More specifically, the present invention relates to an insertable bay for a satellite multiple loading system for a space launch vehicle, and more specifically, to detach the plate on which the deployer is fixed to attach the deployer and the payload placed inside the deployer. The present invention relates to an insertion bay for a satellite multiple payload system for a space launch vehicle that includes a detachable member that can more easily perform rod maintenance.

As micro-satellites are expanded worldwide, the market size of micro-satellites and their share of the overall satellite market are gradually increasing. Cubesat is a representative micro-satellite, and has various standardized sizes, with the 3U-sized (10cm

In general, a cube satellite is mounted inside a deployer, a separation device, and is fixed to the inside of the fairing of a space launch vehicle. When the space launch vehicle enters space orbit, it can be separated from the deployer and deployed into space. The deployed CubeSat performs missions such as earth observation and space data collection, and is mainly used by universities, government agencies, and companies for research and commercial purposes.

In addition, research is being conducted on technology for mass loading micro-satellites into fairings. The space inside the fairing is relatively narrow, so there is a problem that the size, type, and number of micro-satellites or small satellites that can be loaded inside are very limited. It is necessary to load multiple satellites of unlimited size, type, and number inside the fairing of a space launch vehicle.

The present invention is a satellite multi-loading device for a space launch vehicle including a detachable member that can more easily perform maintenance of the deployer and the payload placed inside the deployer by detaching the plate on which the deployer is fixed. The purpose is to provide an insertable bay for the system.

In order to solve the above problems, the present invention includes: a first upper deck having a plate shape and having a plurality of first coupling holes formed at preset intervals in the edge direction; A first side wall disposed on the lower side of the first upper deck and having a plurality of penetrating portions formed in a portion thereof; A first platform deck disposed below the first side wall, having a plate shape, and having a plurality of second coupling holes formed at preset intervals in the edge direction; And an adapter plate disposed in the internal space formed by the first upper deck, the first side wall, and the first platform deck, and one or more first deployers are arranged and fixed on the upper side, The adapter plate is detachable from the first platform deck, and the one or more first deployers provide an insertable bay, a portion of which is exposed to the outside through the penetration portion.

In some embodiments of the present invention, the adapter plate may be moved to the outside through the penetration part of the first side wall in a state in which the coupling with the first platform deck is released, and the one or more first deployers may be connected to the first deployer. It can be moved to the outside by moving the adapter plate.

In some embodiments of the present invention, the adapter plate includes a plurality of adapter plate coupling holes corresponding to the plurality of second coupling holes formed in the first platform deck, and the adapter plate is connected to the first upper deck. , In a state disposed in the internal space formed by the first side wall and the first platform deck, it is fastened by a fastening element through the plurality of second coupling holes and the plurality of adapter plate coupling holes to Can be combined into 1 platform deck.

In some embodiments of the present invention, the horizontal length of the penetrating portion formed in the first side wall may be greater than the sum of the horizontal lengths of each of the one or more first deployers disposed inside the first side wall.

In some embodiments of the present invention, the insertion bay may form a flange-type structure by the first upper deck and the first platform deck each having a plate shape on the upper and lower sides of the first side wall.

According to one embodiment of the present invention, by applying a satellite multi-loading system in which a plurality of bays with different shapes are stacked inside the fairing of a space launch vehicle, payloads of various sizes can be loaded at once, making it possible to load It can have the effect of further expanding restrictions on the types of payloads that can be deployed through space launch vehicles.

According to one embodiment of the present invention, the first bay and the second bay form a flange-type structure, which has the effect of more easily forming a satellite multi-mount system for a space launch vehicle including a plurality of combinations. .

According to one embodiment of the present invention, the effect of being able to more flexibly load various quantities of cube satellites, microsatellites, and small satellites can be achieved by using a satellite multi-loading system for space launch vehicles consisting of a plurality of combinations. .

According to an embodiment of the present invention, the first bay is relatively light in weight by omitting unnecessary reinforcing components, and can be optimized for arranging a small deployer.

According to one embodiment of the present invention, as the adapter plate is detachably placed in the first bay, when charging or checking the status of the deployer and payload due to launch delay, another satellite already loaded on the first bay or another It provides the ability to separate the deployer and payload without dismantling other bays from the space launch vehicle, which has the effect of improving engineers' workability.

According to one embodiment of the present invention, by additionally arranging satellites or deployers in the accommodation space formed inside the second bay, the number of payloads that can be loaded on the space launch vehicle is increased, and the payloads are more diverse. It can have the effect of being deployed into orbit.

According to an embodiment of the present invention, the second side wall of the second bay is formed by being joined by a lonzo run, so that the load of the deployer coupled to the second side wall is transferred to the lonjo run, making the lonjo run relatively large in size or heavy. It can be effective in stably deploying relatively heavy deployers or payloads.

Figure 1 schematically shows the internal configuration of a space launch vehicle to which a satellite multiple loading system for a space launch vehicle is applied according to an embodiment of the present invention.
Figure 2 schematically shows a perspective view of the first bay according to an embodiment of the present invention.
Figure 3 schematically shows the internal configuration of the first bay according to an embodiment of the present invention.
Figure 4 schematically shows a side view of the first bay according to an embodiment of the present invention.
Figure 5 schematically shows a perspective view of the second bay according to an embodiment of the present invention.
Figure 6 schematically shows the internal configuration of the second bay according to an embodiment of the present invention.
Figure 7 schematically shows a perspective view of a first deployer according to an embodiment of the present invention.
Figure 8 schematically shows an embodiment of a satellite multiple loading system for a space launch vehicle according to an embodiment of the present invention.
Figure 9 schematically shows an embodiment of a satellite multiple loading system for a space launch vehicle according to an embodiment of the present invention.
Figure 10 schematically shows an example of a fastening element according to an embodiment of the present invention.
Figure 11 schematically shows an embodiment of a satellite multiple loading system for a space launch vehicle according to an embodiment of the present invention.
Figure 12 schematically shows an embodiment of a satellite multiple loading system for a space launch vehicle according to an embodiment of the present invention.

BRIEF DESCRIPTION OF THE DRAWINGS Various embodiments and/or aspects are now disclosed with reference to the drawings. In the following description, for purposes of explanation, numerous specific details are set forth to facilitate a general understanding of one or more aspects. However, it will also be appreciated by those skilled in the art that this aspect(s) may be practiced without these specific details. The following description and accompanying drawings set forth in detail certain example aspects of one or more aspects. However, these aspects are illustrative and some of the various methods in the principles of the various aspects may be utilized, and the written description is intended to encompass all such aspects and their equivalents.

As used herein, “embodiments,” “examples,” “aspects,” “examples,” etc. may not be construed to mean that any aspect or design described is better or advantageous over other aspects or designs. .

Additionally, the term “or” is intended to mean an inclusive “or” and not an exclusive “or.” That is, unless otherwise specified or clear from context, “X utilizes A or B” is intended to mean one of the natural implicit substitutions. That is, either X uses A; X uses B; Or, if X uses both A and B, “X uses A or B” can apply to either of these cases. Additionally, the term “and/or” as used herein should be understood to refer to and include all possible combinations of one or more of the related listed items.

Additionally, the terms "comprise" and/or "comprising" mean that the feature and/or element is present, but exclude the presence or addition of one or more other features, elements and/or groups thereof. It should be understood as not doing so.

Additionally, terms including ordinal numbers, such as first, second, etc., may be used to describe various components, but the components are not limited by the terms. The above terms are used only for the purpose of distinguishing one component from another. For example, a first component may be named a second component without departing from the scope of the present invention, and similarly, the second component may also be named a first component. The term and/or includes any of a plurality of related stated items or a combination of a plurality of related stated items.

In addition, in the embodiments of the present invention, unless otherwise defined, all terms used herein, including technical or scientific terms, are generally understood by those skilled in the art to which the present invention pertains. It has the same meaning as Terms defined in commonly used dictionaries should be interpreted as having a meaning consistent with the meaning in the context of the related technology, and unless clearly defined in the embodiments of the present invention, have an ideal or excessively formal meaning. It is not interpreted as

Figure 1 schematically shows the internal configuration of a space launch vehicle (2) to which the satellite multiple loading system (1) for space launch vehicle according to an embodiment of the present invention is applied.

The space launch vehicle 2, which includes an upper structure 2100 including a three-stage engine and a fairing 2200, is a rocket used to transport a payload from the Earth's surface to outer space, and the payload includes satellites, probes, and a payload 3 including a payload. The space launch vehicle 2 loads the payload 3 inside the fairing 2200, and when it is launched from the launch pad and enters space orbit, the payload 3 can be deployed into the mission orbit.

However, the internal space of the fairing 2200 has a limited size, so there is a problem in that the size, type, and number of the payload 3 mounted inside are limited.

To solve this problem, in the present invention, the satellite multiple loading system for space launch vehicle (1) was applied to the interior of the fairing (2200). The satellite multi-loading system for a space launch vehicle (1) includes a plurality of bays with different shapes and can load various payloads inside the bays, so that the space launch vehicle can be loaded inside the fairing (2200). Restrictions on payload can be further relaxed.

Preferably, the satellite multiple loading system for space launch vehicles according to an embodiment of the present invention (1) includes one or more first bays (1100); and one or more second bays 1200 disposed above or below the first bay 1100 and coupled thereto.

As shown in FIG. 1, the satellite multiple loading system for space launch vehicle 1 prepares the first bay 1100, and arranges the second bay 1200 above the first bay 1100. And, the payload 3 can be placed on the upper side of the second bay 1200 to form a combination, and the space launch vehicle satellite multiple loading system 1 forming the combination is the adapter ( After being fixed to the upper side of the upper structure 1300, the adapter 1300 can be placed inside the fairing 2200 by placing it on the upper side of the upper structure 2100. Each of the first bay 1100 and the second bay 1200 can place a plurality of payloads 3, and the first bay 1100 or the second bay 1200 can also accommodate a payload 3 on the upper side. (3) can be placed.

In one embodiment of the present invention, the payload 3 includes one or more first payloads 31 mounted inside the first deployer, and one or more payloads 31 mounted inside or outside the second deployer. It may include a second payload 32, and one or more third payloads 33 mounted on the first bay 1100 or the second bay 1200. In one embodiment of the present invention, the first payload 31 and the second payload 32 may include a cube satellite, and the third payload 33 is relatively large in size compared to the cube satellite. It can include large small satellites. The third payload 33 according to an embodiment of the present invention has a plate shape, and a coupling flange (not shown) in which a plurality of payload coupling holes (not shown) are formed at preset intervals can be placed on the lower side. there is. That is, the third payload 33 can form a flange-type structure by the coupling flange (not shown).

Meanwhile, the satellite multiple loading system for space launch vehicle (1) may include a plurality of combinations that can be formed using one or more of the one or more first bays (1100) and the one or more second bays (1200). there is. Preferably, the satellite multiple loading system for space launch vehicle (1) uses one or more of the one or more first bays (1100), the one or more second bays (1200), and the one or more payloads (3). It may include a plurality of combinations that can be formed. That is, the satellite multiple loading system for space launch vehicle (1) according to an embodiment of the present invention is configured in what order the first bay (1100), the second bay (1200), and the one or more payloads (3) are Any number of them can be combined with each other.

For example, the space launch vehicle multi-payload system 1 may include, depending on the embodiment, a combination of one or more first bays 1100 and one or more third payloads 33, and a first bay 1100 - a third payload. Combination of 1st bay (1100) - payload (3), combination of 1 or more first bays (1100) - 1st bay (1100) - 1st bay (1100) - 1st bay (1100), 1 or more first bays (1100) A combination of bays 1100 - 1 or more second bays 1200 - 1 or more third payloads 33 (combination shown in FIG. 1), one or more second bays 1200 - 1 or more first bays 1100 ) - a combination of 1 or more third payloads 33, a combination of 1 or more second bays 1200 - 1 or more third payloads 33, and a combination of 1 or more second bays 1200. You can.

That is, in one embodiment of the present invention, by applying the satellite multi-loading system 1 in which a plurality of bays with different shapes are stacked inside the fairing 2200 of the space launch vehicle 2, payloads having various sizes (3) can be loaded at once, which has the effect of further expanding the limit on the type of payload (3) that can be deployed through one space launch vehicle (2).

Hereinafter, the first bay 1100 and the second bay 1200, which constitute the satellite multiple loading system 1 for a space launch vehicle according to an embodiment of the present invention, will be described in more detail.

Figure 2 schematically shows a perspective view of the first bay 1100 according to an embodiment of the present invention.

According to an embodiment of the present invention, the first bay 1100 includes a first upper deck 1110 that has a plate shape and has a plurality of first coupling holes 1111 formed at preset intervals in the edge direction; A first side wall 1130 disposed on the lower side of the first upper deck 1110 and having a plurality of penetrating portions formed in a portion thereof; And a first platform deck 1120 disposed on the lower side of the first side wall 1130, has a plate shape, and has a plurality of second coupling holes 1121 formed at preset intervals in the edge direction. . At this time, the first bay 1100 may correspond to an insertion type bay.

The first upper deck 1110 may have a plate shape in one embodiment of the present invention. The first upper deck 1110 is a circular plate to easily combine with the first bay 1100, the second bay 1200, or one or more payloads 3 adjacent to the first bay 1100. It is desirable to have a shape, and the payload 3 is preferably the third payload 3. However, according to an embodiment of the present invention, the first upper deck 1110 may be composed of a polygonal plate depending on the shape of the payload 3.

In one embodiment of the present invention, the first upper deck 1110 may correspond to the upper flange of the first bay 1100. Additionally, the first upper deck 1110 may be a circular or polygonal plate member with a plurality of grids formed on a portion thereof. The plurality of grids may have a honeycomb shape. As shown in FIG. 2, the plurality of grids may be formed in a circular area and a ring-shaped area at the center of the first upper deck 1110. However, the plurality of grids are not formed only in the above area, and can be variably applied within the limit of having a design safety factor corresponding to preset design requirements.

In addition, in one embodiment of the present invention, the first upper deck 1110 may have a plurality of first coupling holes 1111 formed at preset intervals in the edge direction.

As described above, the satellite multiple loading system for space launch vehicle (1) includes one or more of the one or more first bays (1100), the one or more second bays (1200), and the one or more payloads (3). It may include a plurality of combinations that can be formed using. That is, the first bay 1100 may have one of the first bay 1100, the second bay 1200, and the payload 3 disposed on the upper side, and the first bay 1100 The first bay 1100, the second bay 1200, and It can be firmly combined with one of the payloads (3). At this time, the payload 3 preferably corresponds to the third payload 33.

In one embodiment of the present invention, the first side wall 1130 is disposed on the lower side of the first upper deck 1110, and a plurality of penetrating portions may be formed in a portion of the first side wall 1130.

As shown in FIG. 2, the first side wall 1130 includes a ring-shaped cylindrical structure with an empty center, and may correspond to the side wall of the first bay 1100. A plurality of penetrating portions formed in a portion of the first side wall 1130 may have a rectangular shape based on a front view. Preferably, the first side wall 1130 may include a plurality of penetrating portions each formed in a rectangular shape in two walls facing each other.

In one embodiment of the present invention, the first platform deck 1120 is disposed below the first side wall 1130 and may have a plate shape. The first platform deck 1120 has a circular plate shape in order to easily combine the first bay 1100 with the adjacent first bay 1100, second bay 1200, or payload 3. It is desirable to have it, and the payload 3 is preferably the third payload 33.

In one embodiment of the present invention, the first platform deck 1120 may correspond to the lower flange of the first bay 1100. As described above, the first upper deck 1110 may correspond to the upper flange of the first bay 1100. That is, the first bay 1100 according to an embodiment of the present invention includes the first upper deck 1110 and the first platform deck each having a plate shape on the upper and lower sides of the first side wall 1130. 1120), a flange-type structure can be formed.

Due to this flange-type structure, when one of the one or more first bays 1100 and the other one of the one or more first bays 1100 are coupled to each other, the upper flange of the first bay 1100 and The lower flanges are in contact with each other and can be joined more easily. That is, as the first bay 1100 forms a flange-type structure by the upper and lower members, the first bay 1100 is connected to the one or more first bays 1100 or the one or more first bays 1100. ) can be combined with each other in any combination with one or more second bays 1200 or one or more third payloads 33 having a different shape.

Additionally, the first platform deck 1120 may be a circular or polygonal plate member corresponding to the first upper deck 1110. The diameter of the first platform deck 1120 preferably corresponds to the diameter of the first upper deck 1110, and the diameter of the first side wall 1130 is the first platform deck 1120 and the first It is preferable that it is smaller than the diameter of the upper deck (1110).

In addition, in one embodiment of the present invention, the first platform deck 1120 may have a plurality of second coupling holes 1121 formed at preset intervals in the edge direction.

As described above, the satellite multiple loading system for space launch vehicle (1) includes one or more of the one or more first bays (1100), the one or more second bays (1200), and the one or more payloads (3). It may include a plurality of combinations that can be formed using. At this time, one of the first bay 1100, the second bay 1200, and the adapter 1300 may be disposed on the lower side of the first bay 1100, and the first bay 1100 may be disposed on the lower side of the first bay 1100. The first bay 1100, the second bay 1200, and the adapter ( 1300) can be firmly combined with 1 of 1.

Due to the above structure, the first bay 1100 can have a relatively light weight. From the perspective of improving the fuel efficiency of the space launch vehicle 2, it is important to reduce the weight of the load loaded inside the fairing 2200 of the space launch vehicle 2. According to the present invention, unnecessary weight can be effectively removed by forming the first bay 1100 into a lightweight structure. In particular, the first bay 1100 may be suitable for placing a small deployer that does not require separate reinforcement components. Preferably, the first bay 1100 is relatively light in weight by omitting unnecessary reinforcing components, and can be optimized for placing a small deployer. In addition, the first bay 1100 can place not only the small deployer, but also a medium-sized or large-sized deployer when necessary.

Due to the above structure, the first bay 1100 according to an embodiment of the present invention forms a space inside and includes a first deployer 1150 capable of mounting one or more payloads 3. It is acceptable. Preferably, the first bay 1100 may have one or more first deployers 1150 capable of mounting one or more first payloads 31 in a space formed therein.

In one embodiment of the present invention, the one or more first deployers 1150 are formed by the first upper deck 1110, the first side wall 1130, and the first platform deck 1120. It can be accommodated in a space, and a portion of the one or more first deployers 1150 can be exposed to the outside through the penetration part.

The first deployer 1150 uses the applicant's patented technology (Patent Registration No. 10-2002306; Cube Satellite Space Separation Device, and Registered Patent Publication No. 10-2192978; Cube Satellite for firmly fixing the Cube Satellite. It may correspond to the cube satellite separation device disclosed in (Space Separation Device).

In one embodiment of the present invention, the one or more first deployers 1150 may include one or more of a 3U size deployer and a 6U size deployer. However, in addition to this, depending on the design environment, the size of the first deployer 1150 may be selected variably. Depending on the size of the first deployer 1150, the number of first deployers 1150 that can be placed in the first bay 1100 may vary. For example, when a plurality of 3U-sized first deployers 1150 are placed in the first bay 1100, four can be placed, and 3U-sized and 6U-sized deployers can be placed in the first bay 1100. When placing the first deployer (1150), two 3U size and one 6U size can be placed, and a plurality of 6U size first deployers (1150) can be placed in the first bay (1100). When placing, you can place two.

Additionally, the first bay 1100 can mount one or more payloads 3 inside the first deployer 1150. The payload 3 is preferably the first payload 31. In one embodiment of the present invention, the first payload 31 may include a cube satellite having one or more sizes among 1U size, 2U size, 3U size, and 6U size. However, the first payload 31 may also include a satellite having a size other than the size described above depending on the design environment. At this time, the size and number of the first payload 31 that can be mounted inside the first deployer 1150 can be variably selected depending on the size of the first deployer 1150. . For example, the first deployer 1150 of 3U size can deploy one 1U-sized cube satellite and one 2U-sized cube satellite, or three 1U-sized cube satellites. At this time, the one or more first deployers 1150 may deploy the one or more first payloads 31 accommodated therein in the horizontal direction.

Additionally, the first bay 1100 can mount the third payload 33 on the upper side of the first upper deck 1110.

Meanwhile, the first bay 1100 according to an embodiment of the present invention may further include a first sequencer 1160 mounted inside or outside.

In an embodiment of the present invention, the first sequencer 1160 may control the operation of the one or more first deployers 1150. Alternatively, the first sequencer 1160 controls operations including the opening and closing operations of the opening and closing portions 1152 of each of the one or more first deployers 1150, and the satellite multiple loading system for the space launch vehicle ( When the space launch vehicle (2) to which 1) is applied enters space orbit, the operation of the opening and closing portion (1152) of each of the one or more first deployers (1150) is controlled to control the operation of the one or more first deployers (1150). 1150) The one or more payloads 3 mounted inside each can be deployed into space orbit.

Preferably, under the control of the first sequencer 1160, the one or more first deployers 1150 can horizontally deploy the one or more payloads 3 stored therein. At this time, the payload 3 is preferably the first payload 31.

In addition, preferably, the payload 3 disposed on the upper side of the first upper deck 1110 of the first bay 1100 is deployed in the longitudinal direction under the control of the first sequencer 1160. , the payload 3 disposed on the upper side of the second upper deck 1220 of the second bay 1200 can be deployed in the longitudinal direction. At this time, the payload 3 is preferably the third payload 33.

For example, the first bay 1100 according to an embodiment of the present invention is controlled by the first sequencer 1160 to store the one or more devices accommodated inside the one or more first deployers 1150. The first payload 31 can be deployed in the horizontal direction, and the one or more third payloads 33 disposed on the upper side of the first bay 1100 can be deployed in the longitudinal direction.

In this way, the satellite multiple loading system for space launch vehicles (1) uses a satellite multiple loading system for space launch vehicles (1) composed of a plurality of combinations to more flexibly accommodate various quantities of cube satellites, microsatellites, and small satellites. It can have a stackable effect.

Figure 3 schematically shows the internal configuration of the first bay 1100 according to an embodiment of the present invention.

The first bay 1100 according to an embodiment of the present invention is an internal space formed by the first upper deck 1110, the first side wall 1130, and the first platform deck 1120. It may further include an adapter plate 1140 on which the one or more first deployers 1150 are disposed and fixed.

If the launch of the space launch vehicle 2 is delayed due to weather problems, etc., the condition of the payload 3 loaded inside the fairing 2200 of the space launch vehicle 2 may deteriorate, and the payload ( In order to check the condition of 3), there is a problem in that the payload 3 loaded on the upper side of the bay must be completely separated from the first bay 1100 and the space launch vehicle 2.

In order to solve this problem, the adapter plate 1140 is applied to the first bay 1100 in the present invention.

Preferably, the adapter plate 1140 is detachable from the first platform deck 1120 of the first bay 1100, and is connected to the first platform deck 1120 of the first bay 1100. In the disconnected state, it can be moved to the outside through the penetration part of the first side wall 1130, and the one or more first deployers 1150 can be moved to the outside by moving the adapter plate 1140. there is.

More specifically, the adapter plate 1140 has an adapter plate coupling hole 1141 formed on a corner side, and the adapter plate 1140 is coupled to the adapter plate 1140 while in contact with the first platform deck 1120. The hole 1141 and the second coupling hole 1121 of the first platform deck 1120 are fastened by a fastening element 1400 so that the adapter plate 1140 is attached to the upper side of the first platform deck 1120. It can be coupled to the first platform deck 1120 in the deployed state. When the fastening element 1400 is removed, the adapter plate 1140 may be separated from the first platform deck 1120 and may be detachable from the first platform deck 1120. When the adapter plate 1140 is separated from the first platform deck 1120 by releasing the coupling with the first platform deck 1120, the adapter plate 1140 is attached to the first side wall 1130. It can move to the outside through the penetration part. At this time, the adapter plate 1140 can be completely separated from the first bay 1100. By this movement of the adapter plate 1140, the one or more first deployers 1150 arranged and fixed on the upper side of the adapter plate 1140 may also move outward. At this time, the one or more first deployers 1150 may be completely separated from the first bay 1100.

With this structure, when additional charging is required or the condition of the first bay 1100 is required to be checked due to launch delay, the fastening element 1400 fastened to the adapter plate coupling hole 1141 is removed and , by moving the adapter plate 1140 to the outside to easily expose the one or more first deployers 1150 disposed on the upper side of the adapter plate 1140 to the outside, so that the first bay 1100 It is possible to more easily inspect the one or more first deployers 1150 arranged and the one or more payloads 3 loaded inside the first deployers 1150.

Preferably, the adapter plate 1140 is detachably disposed in the first bay 1100, so that when charging or checking the status of the deployer and payload 3 due to launch delay, the first bay 1100 ) It provides the ability to separate the deployer and payload without dismantling another satellite or another bay already loaded on top of the space launch vehicle, which has the effect of improving the engineer's workability.

Figure 4 schematically shows a side view of the first bay 1100 according to an embodiment of the present invention.

As described above, the first bay 1100 has one or more internal spaces formed by the first upper deck 1110, the first side wall 1130, and the first platform deck 1120. The first deployer 1150 can be accommodated. At this time, as shown in FIG. 4, the horizontal length of the penetrating portion formed in the first side wall 1130 is the horizontal length of each of the plurality of first deployers 1150 disposed inside the first side wall 1130. It is preferable that it is greater than the sum of the lengths.

If the sum of the horizontal lengths of each of the plurality of first deployers 1150 is greater than the horizontal length of the penetration part, both ends of the plurality of first deployers 1150 are connected to the first side wall 1130. ) may not be exposed to the outside, which may be an obstacle to the deployment of the one or more first payloads 31 loaded inside the plurality of first deployers 1150. In the present invention, in order to preemptively remove such obstructive elements, the horizontal length of the through portion of the first side wall 1130 was designed to be relatively large, and as a result, a portion of the plurality of first deployers 1150 were designed to be relatively large. The first side wall 1130 was exposed to the outside so that the one or more first payloads 31 could be deployed.

Figure 5 schematically shows a perspective view of the second bay 1200 according to an embodiment of the present invention.

The second bay 1200 according to an embodiment of the present invention has an upper frame 1210 that has a plate shape with a through portion formed in the center, and a plurality of third coupling holes 1211 are formed at preset intervals in the edge direction. ; a second side wall 1250 disposed below the upper frame 1210; And a platform frame 1230 disposed on the lower side of the second side wall 1250, has a plate shape with a penetrating portion formed in the center, and has a plurality of fourth coupling holes 1231 formed at preset intervals in the edge direction. can do. At this time, the second bay 1200 may correspond to a column-shaped bay.

In one embodiment of the present invention, the upper frame 1210 may have a plate shape with a penetrating portion formed in the center. The upper frame 1210 has a circular plate shape in order to easily combine the second bay 1200 with the adjacent first bay 1100, second bay 1200, or payload 3. desirable.

In one embodiment of the present invention, the upper frame 1210 may correspond to the upper flange of the second bay 1200. The penetrating portion may include a polygonal penetrating portion. Additionally, the upper frame 1210 may be a circular or polygonal plate member with a penetrating portion formed at the center.

Additionally, in one embodiment of the present invention, the upper frame 1210 may have a plurality of third coupling holes 1211 formed at preset intervals in the edge direction.

As described above, the satellite multiple loading system for space launch vehicle (1) includes one or more of the one or more first bays (1100), the one or more second bays (1200), and the one or more payloads (3). It may include a plurality of combinations that can be formed using. At this time, the second bay 1200 may have one of the first bay 1100, the second bay 1200, and the payload 3 disposed on the upper side, and the second bay 1200 The first bay 1100, the second bay 1200, and the payload are connected using a fastening element 1400, which will be described later, through the plurality of third coupling holes 1211 formed in the upper frame 1210. It can be firmly combined with 1 of the rods (3). At this time, the payload 3 preferably corresponds to the third payload 33.

In addition, although not shown in FIG. 5, in one embodiment of the present invention, one or more payloads 3 may be disposed on the upper side of the upper frame 1210. At this time, the payload 3 is preferably the third payload 33.

When the payload 3 is disposed on the upper side of the upper frame 1210, the upper frame 1210 is in contact with the coupling flange (not shown) of the payload 3 ( The third coupling hole 1211 of 1210) and the payload coupling hole (not shown) of the coupling flange (not shown) of the payload 3 are fastened by a fastening element to form the second bay 1200. and the payload 3 can be combined with each other.

In one embodiment of the present invention, the second side wall 1250 may be disposed below the upper frame 1210.

As shown in FIG. 5, the second side wall 1250 may be formed in a polygonal shape using a plurality of side panels 1252 or in a single circular shape. One side of each of the plurality of side panels 1252 may be disposed on the same axis as one of the plurality of sides forming the through portion formed in the upper frame 1210, and each of the plurality of side panels 1252 It may be arranged in a direction perpendicular to the through portion of the upper frame 1210. Due to this structure, the second side wall 1250 may include a polygonal pillar having a shape corresponding to the shape of the penetrating portion formed in the upper frame 1210. For example, when the penetrating portion has an octagonal shape, the second side wall 1250 may include a pillar having an octagonal shape.

In one embodiment of the present invention, the platform frame 1230 is disposed on the lower side of the second side wall 1250 and may have a plate shape with a penetrating portion formed in the center. The platform frame 1230 has a circular plate shape in order to easily combine the second bay 1200 with the adjacent first bay 1100, second bay 1200, or payload 3. desirable.

In one embodiment of the present invention, the platform frame 1230 may correspond to the lower flange of the second bay 1200. As described above, the upper frame 1210 may correspond to the upper flange of the second bay 1200. That is, the second bay 1200 according to an embodiment of the present invention is formed by the upper frame 1210 and the platform frame 1230, each of which has a plate shape, on the upper and lower sides of the second side wall 1250. A flange-type structure can be formed.

Due to this flange-type structure, when one of the one or more second bays 1200 and the other one of the one or more second bays 1200 are coupled to each other, the upper flange and the lower flange contact each other more easily. can be combined easily. That is, as the second bay 1200 forms a flange-type structure by the upper and lower members, the second bay 1200 has a shape different from the second bay 1200 or the second bay 1200. They can be combined with each other in any combination with the first bay 1100 or the payload 3. At this time, the payload 3 preferably corresponds to the third payload 33.

In addition, as described above, the first bay 1100 is connected to the first upper deck 1110 and the first platform deck 1120, which have a plate shape, respectively, on the upper and lower sides of the first side wall 1130. A flange-type structure can be formed by, and the third payload 33 can form a flange-type structure by the coupling flange (not shown).

That is, in one embodiment of the present invention, the first bay 1100, the second bay 1200, and the payload 3 are formed in a flange-type structure, so that the one or more first bays 1100 , When forming the space launch vehicle satellite multiple loading system (1) having one or more combinations of the one or more second bays (1200) and the one or more payloads (3), each flange is brought into contact with each other to make it easier. It can be implemented.

Additionally, the platform frame 1230 may be a circular or polygonal plate member corresponding to the upper frame 1210. The diameter of the platform frame 1230 preferably corresponds to the diameter of the upper frame 1210, and the diameter of the second side wall 1250 is larger than the diameters of the platform frame 1230 and the upper frame 1210. Small is preferable.

In one embodiment of the present invention, the platform frame 1230 may have a plurality of fourth coupling holes 1231 formed at preset intervals in the edge direction.

As described above, the satellite multiple loading system for space launch vehicle (1) includes one or more of the one or more first bays (1100), the one or more second bays (1200), and the one or more payloads (3). It may include a plurality of combinations that can be formed using. In one embodiment of the present invention, one of the first bay 1100, the second bay 1200, and the adapter 1300 may be disposed on the lower side of the second bay 1200, and the second bay 1200 The bay 1200 is connected to the first bay 1100 and the second bay 1200 using a fastening element 1400 to be described later through the plurality of fourth coupling holes 1231 formed in the platform frame 1230. , and can be firmly combined with one of the adapters 1300.

By the above structure, the second bay 1200 according to an embodiment of the present invention can place one or more second deployers 1260 capable of mounting one or more payloads 3. . Preferably, the second bay 1200 has one or more second deployers 1260 capable of mounting one or more second payloads 32 in a space outside the second side wall 1250. can do.

In one embodiment of the present invention, the one or more second deployers 1260 may be disposed on a portion of the second side wall 1250. The plurality of second deployers 1260 are preferably arranged in a direction perpendicular to the second side wall 1250. However, according to an embodiment of the present invention, the plurality of second deployers 1260 are arranged tilted at a preset angle to prevent collision with the space launch vehicle 2 or the surrounding payload 3. It could be.

The second deployer 1260 corresponds to the plurality of first deployers 1150 and corresponds to the applicant's patented technology (Registered Patent Publication No. 10-2002306; Cube Satellite Space Separation Device, and Registered Patent Publication No. It may correspond to the cube satellite separation device disclosed in No. 10-2192978; Cube Satellite Space Separation Device for Firmly Fixing Cube Satellites.

In one embodiment of the present invention, the one or more second deployers 1260 may include a 12U-sized deployer. However, in addition to this, depending on the design environment, the size of the second deployer 1260 may be selected variably. Preferably, the second deployer 1260 may have a cross-sectional area larger than that of the first deployer 1150. At this time, the cross-sectional area preferably corresponds to the area of a plane cut by a plane parallel to the longitudinal direction of the first deployer 1150 and the second deployer 1260. Alternatively, the second deployer 1260 may load a relatively larger amount of payload 3 therein than the first deployer 1150.

Additionally, in one embodiment of the present invention, the second payload 32 may include a cube satellite having one or more sizes among 1U size, 2U size, 3U size, 6U size, and 12U size. However, in addition to this, depending on the design environment, the size of the second payload 32 may be selected variably. At this time, the one or more second deployers 1260 may deploy the one or more payloads 3 accommodated therein in the horizontal direction.

Meanwhile, the second bay 1200 according to an embodiment of the present invention includes a second upper deck 1220 that is detachable from the penetrating portion formed at the center of the upper frame 1210; And it may further include a second platform deck 1240 that is detachable from the penetrating portion formed at the center of the platform frame 1230.

In one embodiment of the present invention, the second upper deck 1220 may be detachable from the penetrating portion formed at the center of the upper frame 1210. In one embodiment of the present invention, the second upper deck 1220 may be disposed in the through portion of the upper frame 1210 and be detachable.

As shown in FIG. 5, the second upper deck 1220 may have a shape corresponding to the through portion of the upper frame 1210, and serves as a kind of stopper to block the through portion of the upper frame 1210. can do. That is, the second upper deck 1220 may have a shape corresponding to the through portion of the upper frame 1210, so that when coupled to the upper frame 1210, it forms one plate with the upper frame 1210. can do. For example, when the penetrating portion of the upper frame 1210 has an octagonal shape, the second upper deck 1220 preferably has an octagonal shape corresponding to the shape of the penetrating portion.

In one embodiment of the present invention, one or more payloads 3 may be placed on the upper side of the second upper deck 1220. At this time, the payload 3 is preferably the third payload 33.

In one embodiment of the present invention, the second platform deck 1240 may be detachable from the penetrating portion formed at the center of the platform frame 1230. In one embodiment of the present invention, the second platform deck 1240 may be disposed in the through portion of the platform frame 1230 and detachable.

As shown in FIG. 5, the second platform deck 1240 may have a shape corresponding to the through portion of the platform frame 1230, and serves as a kind of stopper to block the through portion of the platform frame 1230. can do. That is, the second platform deck 1240 may have a shape corresponding to the through portion of the platform frame 1230, so that when coupled to the platform frame 1230, it forms one plate with the platform frame 1230. can do.

That is, for example, when the penetrating portion of the platform frame 1230 has an octagonal shape, the second platform deck 1240 preferably has an octagonal shape corresponding to the shape of the penetrating portion.

By the above structure, the second bay 1200 according to an embodiment of the present invention forms a space inside to accommodate a third deployer (not shown) capable of mounting the payload 3. can do. Or, the second bay 1200 has an internal space, accommodates a payload 3 or a third deployer (not shown) in the internal space, and is perpendicular to the outer peripheral surface of the second bay 1200, That is, the payload 3 can be additionally deployed in the longitudinal direction.

Preferably, the second bay 1200 according to an embodiment of the present invention includes the upper frame 1210, the second upper deck 1220, the second side wall 1250, and the platform frame 1230. ), and one or more third deployers (not shown) or one or more payloads 3 can be accommodated in the internal space formed by the second platform deck 1240. At this time, the payload 3 is preferably one or more of the first payload 31 and the second payload 32.

In addition, the second bay 1200 can mount one or more third payloads 33 on the upper side of the second upper deck 1220.

The third deployer (not shown) is the applicant's patented technology (Patent Registration No. 10-2002306; Cube) corresponding to the first deployer 1150 and the second deployer 1260. It may correspond to the cube satellite separation device disclosed in (Satellite Space Separation Device, and Cube Satellite Space Separation Device for Firmly Fixing Cube Satellites).

The second bay 1200 can mount one or more payloads 3 inside the third deployer (not shown). The payload 3 is preferably one or more of the first payload 31 and the second payload 32. At this time, the one or more third deployers (not shown) deploy the one or more payloads 3 accommodated therein in the longitudinal direction after the second upper deck 1220 is separated from the upper frame 1210. can do.

Meanwhile, in one embodiment of the present invention, the second bay 1200 may further include a second sequencer (not shown) mounted inside or outside.

The second sequencer (not shown) is connected to the upper frame 1210, the second upper deck 1220, the second side wall 1250, the platform frame 1230, and the second platform deck 1240. It can be placed in the internal space formed by, and can control the operations of the one or more third deployers (not shown), the payload 3, and the second upper deck 1220.

For example, the second sequencer (not shown) controls operations including the opening and closing operations of the opening and closing portions 1152 of each of the one or more second deployers 1260, thereby controlling multiple satellites for the space launch vehicle. When the space launch vehicle (2) to which the mounting system (1) is applied enters space orbit, the operation of the opening and closing portion (1152) of each of the one or more second deployers (1260) is controlled, and the one or more second deployers (1260) are operated. The one or more payloads 3 mounted inside each of the lowerers 1260 can be deployed in the horizontal direction. At this time, the payload 3 may include one or more of the first payload 31 and the second payload 32.

In addition, for example, the second sequencer (not shown) controls operations including the opening and closing operations of the opening and closing portions 1152 of each of the one or more third deployers (not shown) to control the space launch vehicle. When the space launch vehicle (2) to which the satellite multiple loading system (1) is applied enters space orbit, the operation of the opening and closing unit (1152) of each of the one or more third deployers (not shown) is controlled, and the first The one or more payloads 3 mounted inside each of the above third deployers (not shown) can be deployed in the longitudinal direction. At this time, the payload 3 may include one or more of the first payload 31 and the second payload 32.

Preferably, under the control of the second sequencer (not shown), the one or more second deployers 1260 horizontally deploy the one or more payloads 3 stored therein, or the one or more second deployers 1260 3 Deployer (not shown) deploys one or more payloads 3 accommodated therein in the longitudinal direction after the second upper deck 1220 is separated from the upper frame 1210, or (3) may be deployed in the longitudinal direction after the second upper deck 1220 is separated from the upper frame 1210. At this time, the payload 3 is preferably the second payload 32.

In addition, preferably, the payload 3 disposed on the upper side of the first upper deck 1110 of the first bay 1100 is deployed in the longitudinal direction under the control of the second sequencer (not shown). Alternatively, the payload 3 disposed on the upper side of the second upper deck 1220 of the second bay 1200 can be deployed in the longitudinal direction. At this time, the payload 3 is preferably the third payload 33.

In this way, the satellite multiple loading system for space launch vehicles (1) uses a satellite multiple loading system for space launch vehicles (1) composed of a plurality of combinations to more flexibly accommodate various quantities of cube satellites, microsatellites, and small satellites. It can have a stackable effect.

Figure 6 schematically shows the internal configuration of the second bay 1200 according to an embodiment of the present invention.

The second side wall 1250 according to an embodiment of the present invention is disposed in a vertical direction to the upper frame 1210 and has a shape bent at a preset angle, and has a plurality of fifth coupling holes 1251.1 in length. Ronzo Run (1251) formed at preset intervals in the direction; and a plurality of side panels 1252 in which a plurality of sixth coupling holes 1252.1 are formed at predetermined intervals in the edge direction.

In one embodiment of the present invention, the ronzo run 1251 is disposed perpendicular to the upper frame 1210 and has a shape bent at a preset angle, and has a plurality of fifth coupling holes 1251.1 in the longitudinal direction. It can be formed at preset intervals.

As shown in FIG. 6, the lonzo run 1251 may be disposed inside each corner of the second side wall 1250. At this time, the outer surface of the Lonzo Run 1251 may be in contact with the inner surface of the side panel 1252 of the second side wall 1250.

In one embodiment of the present invention, the plurality of side panels 1252 may have a plurality of sixth coupling holes 1252.1 formed at predetermined intervals in the edge direction.

As shown in FIG. 6, the sixth coupling hole (1252.1) formed in the plurality of side panels 1252 can be arranged coaxially with the fifth coupling hole (1251.1) formed in the lonzo run 1251. there is. Each of the plurality of side panels 1252 may be combined with the lonzo run 1251. Preferably, the fifth coupling hole 1251.1 of the lonzo run 1251 and the side panel 1252 are in contact with the inner surface of the side panel 1252 when the outer surface of the lonjo run 1251 is in contact with the inner surface of the side panel 1252. The sixth coupling hole 1252.1 is fastened by the fastening element 1400, so that the Lonzo Run 1251 and the side panel 1252 are coupled to each other to form the second side wall 1250, and the side panel The second deployer 1260 may be placed and fixed on the outer surface of 1252.

By this structure, the second deployer 1260 is coupled to the outer surface of the side panel 1252 forming the second side wall 1250 and transfers the load to the side panel 1252, and the side The panel 1252 is coupled to the outer surface of the Lonzo Run 1251 to support the load transferred from the second deployer 1260 or transfer it to the Lonzo Run 1251. In this case, the load of the second payload 32 mounted inside the second deployer 1260 can be effectively distributed, so that the relatively large or heavy payload 3 is placed in the second bay 1200. ) Or it may be suitable for deploying a deployer. Alternatively, the second bay 1200 disposes the Lonzo Run 1251, which is a reinforcing member, on the inside of the second side wall 1250, and the one or more second deployers 1260 or payload 3 The side panels 1252 surround each outer peripheral surface and support the load, so it is preferable that they are optimized for placing a large deployer or the satellite itself.

That is, the second side wall 1250 of the second bay 1200 is formed by being joined by the lonzo run 1251, so that the load of the deployer coupled to the second side wall 1250 is transmitted to the lonso run 1251. This can have the effect of stably placing a deployer or payload (3) that is relatively large in size or heavy in weight. In addition, the second bay 1200 can stably place not only the heavy deployer or payload 3, but also a relatively light small deployer or satellite when necessary.

Meanwhile, although not shown in FIG. 6, according to an embodiment of the present invention, in a state where the inner surface of the Lonzo Run 1251 is in contact with the outer surface of the side panel 1252, the first part of the Lonzo Run 1251 The 5th coupling hole 1251.1 and the 6th coupling hole 1252.1 of the side panel 1252 are fastened by the fastening element 1400, so that the ronzo run 1251 and the side panel 1252 are coupled to each other. A second side wall 1250 may be formed, and the second deployer 1260 may be placed and fixed on the outer surface of the side panel 1252.

Meanwhile, according to an embodiment of the present invention, the second deployer 1260 may not be disposed on one surface of the second side wall 1250 as shown in FIG. 6. In this case, the second sequencer may be disposed on the outer surface of a panel on which the second deployer 1260 is not disposed among the plurality of panels forming the second side wall 1250.

Meanwhile, according to an embodiment of the present invention, the second side wall 1250 may not include the lonzo run 1251 and the plurality of side panels 1252. In this case, the second side wall 1250 may have a cylindrical shape. Preferably, the second side wall 1250 according to an embodiment of the present invention includes a hollow cylindrical shape with a through hole formed in the center, the upper part contacts a part of the upper frame 1210, and the lower part may contact a portion of the platform frame 1230.

Figure 7 schematically shows a perspective view of the first deployer 1150 according to an embodiment of the present invention.

The first deployer 1150 according to an embodiment of the present invention includes a container unit 1151 capable of storing and protecting the one or more first payloads 31 therein; An opening and closing unit 1152 located in the front of the container unit 1151 to open and close an exit through which the one or more first payloads 31 can enter and exit; And it may include an opening/closing actuating unit (1153).

As shown in FIG. 7, the container unit 1151 allows the first payload 31 to be fixed and stored inside in accordance with the specifications of the first payload 31. Figure 7 shows the container unit 1151 in which a 3U-sized cube satellite can be accommodated.

Additionally, the first payload 31 can be inserted and extracted in the longitudinal direction of the container unit 1151. To this end, one longitudinal end of the container part 1151 forms an outlet, and the opening and closing part 1152 can open and close the outlet.

Additionally, the opening/closing actuator 1153 controls the opening/closing of the opening/closing unit 1152. As shown in FIG. 7, the opening/closing driving unit 1153 is provided with an opening/closing fixing pin on the opposite side where the opening/closing unit 1152 is connected to the container unit 1151 by a hinge, and when the opening/closing unit 1152 is in a closed state, By fixing the opening/closing fixing pin, the opening/closing portion 1152 can be closed, fixed, or released. As described above, the first sequencer 1160 can control the operation of the plurality of first deployers 1150. That is, the opening/closing actuator 1153 can control the opening/closing of the opening/closing unit 1152 under the control of the first sequencer 1160.

In addition, the first deployer 1150 according to an embodiment of the present invention applies force to the one or more first payloads 31 to push them out when the one or more first payloads 31 are separated. It may further include a spring portion.

Although the spring unit is not shown in FIG. 7, it includes a satellite connection unit that contacts the first payload 31 and transmits force to the first payload 31 when the first payload 31 is separated; a main spring unit that supplies force to the satellite connection unit when the first payload 31 is separated; And a satellite connection that is coupled to the satellite connection unit and can adjust the relative positions of the satellite connection unit and the container unit 1151 when the first payload 31 is stored inside the first deployer 1150. It may include an obituary part.

Due to the structure described above, the first deployer 1150 prevents the one or more first payloads 31 disposed inside from deviating from the designated position inside, thereby preventing vibration generated when the projectile is launched. Damage of the first payload 31 can be prevented.

As such, FIG. 7 shows a perspective view of the first deployer 1150, but excluding the overall size of the deployer, the second deployer 1260 disposed in the second bay 1200 , and the third deployer (not shown) may also include features and effects corresponding to the first deployer 1150.

That is, the second deployer 1260 according to an embodiment of the present invention includes a container unit 1151 capable of storing and protecting the second payload 32 therein; An opening and closing unit 1152 located in the front of the container unit 1151 to open and close an exit through which the second payload 32 can enter and exit; Opening and closing section (1153); and a spring unit that applies force to the second payload 32 to push it out when the second payload 32 is separated, and the second deployer 1260 is disposed inside. By preventing the second payload 32 from deviating from its internal designated position, it is possible to prevent the second payload 32 from being damaged due to vibration that occurs when a projectile is launched.

In addition, the third deployer (not shown) according to an embodiment of the present invention is capable of storing and protecting at least one of the first payload 31 and the second payload 32 inside. Container unit 1151; An opening and closing unit 1152 located in the front of the container unit 1151 to open and close an exit through which one or more of the first satellite and the second payload 32 can enter and exit; Opening and closing section (1153); And when one or more of the first payload 31 and the second payload 32 are separated, force is applied to one or more of the first payload 31 and the second payload 32 to push. The inner part may include a spring part; and the third deployer (not shown) is configured to place at least one of the first payload 31 and the second payload 32 disposed inside at a designated location inside the third deployer (not shown). It is possible to prevent one or more of the first payload 31 and the second payload 32 from being damaged due to vibration generated when the projectile is launched.

Figure 8 schematically shows an embodiment of a satellite multiple loading system 1 for a space launch vehicle according to an embodiment of the present invention.

As shown in Figure 8, in one embodiment of the present invention, the first upper deck 1110 of the first bay 1100 is in contact with the platform frame 1230 of the second bay 1200. In this state, the first coupling hole of the first upper deck 1110 of the first bay 1100 and the fourth coupling hole 1231 of the platform frame 1230 of the second bay 1200 are By being fastened by the fastening element 1400, the first bay 1100 and the second bay 1200 can be coupled to each other. In this way, the satellite multiple loading system for space launch vehicle 1 may include a combination of the first bay 1100 and the second bay 1200.

However, the satellite multiple loading system 1 for a space launch vehicle according to an embodiment of the present invention is not limited to this, and as described above, the one or more first bays 1100 and the one or more second bays 1200 ), and a plurality of combinations that can be formed using one or more of the one or more payloads 3. For example, the first bay 1100 may be mounted on the second bay 1200.

Figure 9 schematically shows an embodiment of a satellite multiple loading system 1 for a space launch vehicle according to an embodiment of the present invention.

As shown in Figure 9, in one embodiment of the present invention, the first upper deck 1110 of the first bay 1100 is in contact with the platform frame 1230 of the second bay 1200. In this state, the first coupling hole of the first upper deck 1110 of the first bay 1100 and the fourth coupling hole 1231 of the platform frame 1230 of the second bay 1200 are By being fastened by the fastening element 1400, the first bay 1100 and the second bay 1200 can be coupled to each other. At the same time, while the upper frame 1210 of the second bay 1200 is in contact with the coupling flange (not shown) of the payload 3, the upper frame 1210 of the second bay 1200 The third coupling hole 1211 of the payload 3 and the payload coupling hole (not shown) of the coupling flange (not shown) of the payload 3 are fastened by a fastening element 1400, and the second bay 1200 ) and the payload 3 can be combined with each other. At this time, the payload 3 is preferably the third payload 33.

However, the satellite multiple loading system 1 for a space launch vehicle according to an embodiment of the present invention is not limited to this, and as described above, the one or more first bays 1100 and the one or more second bays 1200 ), and a plurality of combinations that can be formed using one or more of the one or more payloads 3. For example, the first bay 1100 may be mounted on the second bay 1200, and the payload 3 may be mounted on the first bay 1100 at the same time.

As such, the satellite multiple loading system for space launch vehicle 1 may include a combination of the first bay 1100, the second bay 1200, and the payload 3.

Figure 10 schematically shows an embodiment of a fastening element 1400 according to an embodiment of the present invention.

The satellite multiple loading system for a space launch vehicle according to an embodiment of the present invention (1) is composed of one or more first bays (1100), one or more second bays (1200), and one or more payloads (3). It may further include a fastening element 1400 that fastens one or more pairs to each other. The fastening element 1400 is preferably a separable or controllable fastening element 1400, and the one or more payloads 3 are preferably a third payload 33.

As shown in FIG. 10(a), the fastening element 1400 may include a bolt and a coupling member 1410 including a nut coupled to one side of the bolt. The fastening element 1400 can be used to form a combination of the one or more first bays 1100, the one or more second bays 1200, and the one or more payloads 3. .

In one embodiment of the present invention, the coupling member 1410 is simultaneously inserted into the first coupling hole 1111 and the second coupling hole 1121 to couple the one or more first bays 1100 to each other. (shown in FIG. 10(a)), the one or more second bays 1200 are coupled to each other in a similar manner, or are simultaneously inserted into the first coupling hole 1111 and the fourth coupling hole 1231. The first bay 1100 and the second bay 1200 may be coupled to each other, the first bay 1100 may be coupled to the second bay 1200 in a similar manner, or the first bay 1100 may be coupled to the first bay 1100 ( 1111) and the second coupling hole 1121, and are simultaneously inserted into the first coupling hole 1111 and the fourth coupling hole 1231 to form the one or more first bays 1100 and the second bay. (1200) can be combined with each other.

Alternatively, the fastening element 1400 may include a fixing member 1420 including a fixing pin having a U shape, as shown in FIG. 10(b).

In one embodiment of the present invention, the fixing member 1420 fixes the lower end of the first upper deck 1110 and the upper end of the first platform deck 1120 to secure the one or more first bays 1100. ) are fixed to each other (shown in FIG. 10(b)), or the one or more second bays 1200 are fixed to each other in a similar manner, or the lower end of the first upper deck 1110 and the platform frame ( 1230) to fix the first bay 1100 and the second bay 1200 to each other, or to fix the first bay 1100 on the second bay 1200 in a similar manner. Alternatively, the lower end of the first upper deck 1110 and the upper end of the first platform deck 1120 are fixed and the lower end of the first upper deck 1110 and the upper end of the platform frame 1230 are fixed. By fixing, the one or more first bays 1100 and the second bays 1200 can be fixed to each other.

In addition, in one embodiment of the present invention, when using the fixing member 1420 to form the satellite multiple loading system 1 for a space launch vehicle as shown in FIG. 10(b), the first upper The first coupling hole 1111 of the deck 1110, the second coupling hole 1121 of the first platform deck 1120, the third coupling hole of the upper frame 1210, and the platform frame ( The fourth coupling hole 1231 of 1230) may not be formed, and a fastening element corresponding to the fixing member 1420 including the fixing pin may be formed.

In this way, by coupling or fixing the one or more first bays 1100 and the one or more second bays 1200 by the fastening element 1400, the satellite multiple loading system for space launch vehicle (1) It may include a plurality of combinations that can be formed by one or more first bays 1100 and one or more second bays 1200.

However, according to an embodiment of the present invention, the fastening element 1400 is not limited to the above-described pair, but includes the one or more first bays 1100, the one or more second bays 1200, and the one or more payloads. One or more pairs that can be combined in (3) can be connected to each other.

Figure 11 schematically shows an embodiment of a satellite multiple loading system 1 for a space launch vehicle according to an embodiment of the present invention.

As described above, the satellite multiple loading system for space launch vehicle (1) includes one or more of the one or more first bays (1100), the one or more second bays (1200), and the one or more payloads (3). It may include a plurality of combinations that can be formed using.

Figure 11(a) shows the satellite multiple loading system for space launch vehicle (1) including a combination of the first bay (1100) and the payload (3) disposed on the upper side of the first bay (1100). An example is schematically shown.

As shown in FIG. 11(a), when the first upper deck 1110 of the first bay 1100 is in contact with the coupling flange (not shown) of the payload 3, the first The first coupling hole 1111 of the first upper deck 1110 of the bay 1100 and the payload coupling hole (not shown) of the coupling flange (not shown) of the payload 3 are connected to the fastening element 1400. ), so that the first bay 1100 and the payload 3 can be coupled to each other. At this time, the payload 3 is preferably the third payload 33.

Figure 11(b) shows the first bay 1100, the first bay 1100 disposed on the upper side of the first bay 1100, and the payload disposed on the upper side of the first bay 1100. An embodiment of the above-mentioned satellite multiple loading system for space launch vehicle (1) including a combination of (3) is schematically shown.

As shown in Figure 11 (b), the first upper deck 1110 of one of the one or more first bays 1100 is the first platform deck of another one of the one or more first bays 1100 In a state of contact with (1120), the first coupling hole of the first upper deck 1110 of the one or more first bays 1100 and the first coupling hole of the other one of the one or more first bays 1100 The second coupling hole of the first platform deck 1120 is fastened by the fastening element 1400, so that one of the one or more first bays 1100 and the other one of the one or more first bays 1100 are connected to each other. Can be combined. Additionally, at the same time, while the first upper deck 1110 of the first bay 1100 is in contact with the coupling flange (not shown) of the payload 3, the first upper deck 1110 of the first bay 1100 is in contact with the coupling flange (not shown) of the payload 3. 1 The first coupling hole 1111 of the upper deck 1110 and the payload coupling hole (not shown) of the coupling flange (not shown) of the payload 3 are fastened by a fastening element 1400, The first bay 1100 and the payload 3 may be combined with each other. At this time, the payload 3 is preferably the third payload 33.

FIG. 11(c) schematically shows an embodiment of the satellite multiple loading system 1 for a space launch vehicle including a combination of four first bays 1100 sequentially stacked.

As shown in Figure 11 (c), the first upper deck 1110 of one of the one or more first bays 1100 is the first platform deck of another one of the one or more first bays 1100 In a state of contact with (1120), the first coupling hole 1111 of the first upper deck 1110 of one of the one or more first bays 1100 and the other of the one or more first bays 1100 The second coupling hole of one of the first platform decks 1120 is fastened by a fastening element 1400, so that one of the one or more first bays 1100 and the other of the one or more first bays 1100 One can be combined with another. Additionally, this combination may be performed repeatedly one or more times.

Figure 12 schematically shows an embodiment of a satellite multiple loading system 1 for a space launch vehicle according to an embodiment of the present invention.

As described above, the satellite multiple loading system for space launch vehicle (1) includes one or more of the one or more first bays (1100), the one or more second bays (1200), and the one or more payloads (3). It may include a plurality of combinations that can be formed using.

Figure 12(a) shows the satellite multiple loading system for space launch vehicle (1) including a combination of the second bay (1200) and the payload (3) disposed on the upper side of the second bay (1200). An example is schematically shown.

As shown in FIG. 12(a), when the first upper deck 1110 of the first bay 1100 is in contact with the platform frame 1230 of the second bay 1200, the first The first coupling hole of the first upper deck 1110 of the first bay 1100 and the fourth coupling hole 1231 of the platform frame 1230 of the second bay 1200 are fastening elements 1400. By fastening, the first bay 1100 and the second bay 1200 can be coupled to each other. In addition, at the same time, while the upper frame 1210 of the second bay 1200 is in contact with the coupling flange (not shown) of the payload 3, the upper frame of the second bay 1200 ( The third coupling hole 1211 of 1210) and the payload coupling hole (not shown) of the coupling flange (not shown) of the payload 3 are fastened by a fastening element 1400, and the second bay (1200) and the payload (3) may be combined with each other. At this time, the payload 3 is preferably the third payload 33.

FIG. 12(b) schematically shows an embodiment of the satellite multiple loading system 1 for a space launch vehicle including only the second bay 1200.

As shown in FIG. 12(b), when the first upper deck 1110 of the first bay 1100 is in contact with the platform frame 1230 of the second bay 1200, the first The first coupling hole of the first upper deck 1110 of the first bay 1100 and the fourth coupling hole 1231 of the platform frame 1230 of the second bay 1200 are fastening elements 1400. By fastening, the first bay 1100 and the second bay 1200 can be coupled to each other. In addition, at the same time, while the upper frame 1210 of the second bay 1200 is in contact with the coupling flange (not shown) of the payload 3, the upper frame of the second bay 1200 ( The third coupling hole 1211 of 1210) and the payload coupling hole (not shown) of the coupling flange (not shown) of the payload 3 are fastened by a fastening element 1400, and the second bay (1200) and the payload (3) may be combined with each other. At this time, the payload 3 is preferably the third payload 33. Additionally, at the same time, one or more first deployers 1150 may be additionally placed on the upper side of the adapter 1300.

Figure 12(c) shows the first bay 1100, the second bay 1200 disposed above the first bay 1100, and the payload disposed above the second bay 1200. An embodiment of the above-mentioned satellite multiple loading system for space launch vehicle (1) including a combination of (3) is schematically shown.

As shown in FIG. 12(c), in a state where the upper frame 1210 of the second bay 1200 is in contact with the coupling flange (not shown) of the payload 3, the second bay ( The third coupling hole 1211 of the upper frame 1210 of 1200) and the payload coupling hole (not shown) of the coupling flange (not shown) of the payload 3 are fastened by the fastening element 1400. Thus, the second bay 1200 and the payload 3 can be coupled to each other. At this time, the payload 3 is preferably the third payload 33.

Figure 12(d) shows the first bay 1100, the second bay 1200 disposed above the first bay 1100, and the payload disposed above the second bay 1200. An embodiment of the above-mentioned satellite multiple loading system for space launch vehicle (1) including a combination of (3) is schematically shown. FIG. 12(d) corresponds to an embodiment in which one or more first deployers 1160 are disposed on the upper side of the adapter 1300 in FIG. 12(c) described above.

That is, as shown in FIG. 12(d), the space launch vehicle satellite multiple loading system 1 has one or more first deployers 1160 added to the upper side of the adapter 1300, depending on the embodiment. It can be placed as .

In addition, although not shown in the drawing, in one embodiment of the present invention, the upper frame 1210 of one of the one or more second bays 1200 is connected to the upper frame 1210 of the other one of the one or more second bays 1200. In a state in contact with the platform frame 1230, the third coupling hole 1211 of the upper frame 1210 of one of the one or more second bays 1200 and the other one of the one or more second bays 1200 The fourth coupling hole 1231 of the platform frame 1230 is fastened by the fastening element 1400, so that one of the one or more second bays 1200 and the other of the one or more second bays 1200 One can be combined with another. In this case, the two second bays 1200 may be combined with each other.

In this way, the satellite multiple loading system for space launch vehicle (1) includes a plurality of devices that can be formed by one or more of the first bay (1100), the second bay (1200), and the payload (3). May include combinations.

According to one embodiment of the present invention, by applying a satellite multi-loading system in which a plurality of bays with different shapes are stacked inside the fairing of a space launch vehicle, payloads of various sizes can be loaded at once, making it possible to load It can have the effect of further expanding restrictions on the types of payloads that can be deployed through space launch vehicles.

According to one embodiment of the present invention, the first bay and the second bay form a flange-type structure, which has the effect of more easily forming a satellite multi-mount system for a space launch vehicle including a plurality of combinations. .

According to one embodiment of the present invention, the effect of being able to more flexibly load various quantities of cube satellites, microsatellites, and small satellites can be achieved by using a satellite multi-loading system for space launch vehicles consisting of a plurality of combinations. .

According to an embodiment of the present invention, the first bay is relatively light in weight by omitting unnecessary reinforcing components, and can be optimized for arranging a small deployer.

According to one embodiment of the present invention, as the adapter plate is detachably placed in the first bay, when charging or checking the status of the deployer and payload due to launch delay, another satellite already loaded on the first bay or another It provides the ability to separate the deployer and payload without dismantling other bays from the space launch vehicle, which has the effect of improving engineers' workability.

According to one embodiment of the present invention, by additionally arranging satellites or deployers in the accommodation space formed inside the second bay, the number of payloads that can be loaded on the space launch vehicle is increased, and the payloads are more diverse. It can have the effect of being deployed into orbit.

According to an embodiment of the present invention, the second side wall of the second bay is formed by being joined by a lonzo run, so that the load of the deployer coupled to the second side wall is transferred to the lonjo run, making the lonjo run relatively large in size or heavy. It can be effective in stably deploying relatively heavy deployers or payloads.

As described above, although the embodiments have been described with limited examples and drawings, various modifications and variations can be made by those skilled in the art from the above description. For example, the described techniques are performed in a different order than the described method, and/or components of the described system, structure, device, circuit, etc. are combined or combined in a different form than the described method, or other components are used. Alternatively, appropriate results may be achieved even if substituted or substituted by an equivalent. Therefore, other implementations, other embodiments, and equivalents of the claims also fall within the scope of the claims described below.

1: Satellite multiple loading system for space launch vehicle
1100: Bay 1
1110: first upper deck 1111: first coupling hole
1120: First platform deck 1121: Second coupling hole
1130: first side wall
1140: Adapter plate 1141: Adapter plate coupling hole
1150: 1st Deployer 1151: Container Department
1152: Opening/closing unit 1153: Opening/closing drive unit
1160: 1st sequencer
1200: 2nd bay
1210: Upper frame 1211: Third coupling hole
1220: 2nd upper deck
1230: Platform frame 1231: Fourth coupling hole
1240: 2nd platform deck
1250: Second side wall 1251: Lonzo Run
1251.1: Fifth coupling hole 1252: Side panel
1252.1: 6th coupling hole
1260: Second Deployer
1300: Adapter 1400: Fastening element
1410: Coupling member 1420: Fixing member
2: Space launch vehicle
2100: Upper structure 2200: Pairing
3: Payload
31: first payload 32: second payload
33: Third payload

Claims (5)

A first upper deck having a plate shape and having a plurality of first coupling holes formed at preset intervals in the edge direction;
a first side wall disposed on the lower side of the first upper deck and having a plurality of penetrating portions formed in a portion thereof;
a first platform deck disposed below the first side wall, having a plate shape, and having a plurality of second coupling holes formed at preset intervals in the edge direction; and
An adapter plate disposed in an internal space formed by the first upper deck, the first side wall, and the first platform deck, and on which one or more first deployers are disposed and fixed on the upper side,
The adapter plate is detachable from the first platform deck,
A portion of the one or more first deployers is exposed to the outside through the penetration portion,
The adapter plate can be moved outward through the penetration part of the first side wall in a state in which the coupling with the first platform deck is released,
The one or more first deployers can be moved to the outside by moving the adapter plate,
As the adapter plate is arranged to be detachable, the deployer and payload can be separated without dismantling another satellite or another bay already loaded from the space launch vehicle when charging or checking the condition of the deployer and payload. Insertable bay that provides functionality.
delete In claim 1,
The adapter plate includes a plurality of adapter plate coupling holes corresponding to the plurality of second coupling holes formed in the first platform deck,
With the adapter plate disposed in an internal space formed by the first upper deck, the first side wall, and the first platform deck, the plurality of second coupling holes and the plurality of adapter plate coupling holes An insertable bay that can be fastened by a fastening element and coupled to the first platform deck.
In claim 1,
An insertable bay wherein the horizontal length of the penetrating portion formed on the first side wall is greater than the sum of the horizontal lengths of each of the one or more first deployers disposed inside the first side wall.
In claim 1,
The insertion type bay forms a flange-type structure by the first upper deck and the first platform deck each having a plate shape on the upper and lower sides of the first side wall.

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