Rib structure of deployable mesh antenna for satellites

Abstract

The present invention relates to a rib structure of a deployable satellite mesh antenna that utilizes self-elastic restoring force as a deployment power source to deploy ribs, thereby minimizing damage to the mesh during the process of folding the ribs of the multi-stage structure, improving the reflection gain and efficiency of the antenna, and ensuring reliability and mechanical life during deployment. The deployable satellite mesh antenna according to the present invention comprises: a rib that is folded or deployed around a hinge axis, including a first rib, a second rib, and a third rib; and a mesh supported across one surface of the first rib, the second rib, and the third rib. The invention is characterized by having inclined surfaces formed on the first rib, the second rib, and the third rib to prevent the mesh from being squeezed between the ribs during the process of the third rib being folded to the second rib and the process of the second rib being folded to the first rib.

Description

Technology Field

[0001] The present invention relates to a rib structure for a deployable satellite mesh antenna, and more specifically, to a rib structure for a deployable satellite mesh antenna that utilizes self-elastic restoring force as a deployment power source to deploy ribs, thereby minimizing damage to the mesh during the process of folding the ribs of the multi-stage structure, improving the reflection gain and efficiency of the antenna, and ensuring reliability and mechanical life during deployment. Background Technology

[0003] As space missions have recently become more advanced, the demand for deep space communication, high-resolution Earth observation, and large-capacity data transmission is surging. To meet these demands, large antennas equipped with high gain and excellent resolution are essential.

[0004] To transport large antennas into orbit, a space launch vehicle must be used. However, the internal space of a launch vehicle's payload fairing is limited in volume and shape. Therefore, it is physically impossible to mount a single, fixed antenna of the required size for orbit directly onto the launch vehicle from the ground.

[0005] The deployable mesh antenna was designed to overcome the spatial limitations of such projectiles.

[0006] The aforementioned deployable mesh antenna is configured to be stored in a folded state to fit within the internal space of the fairing when launched from the ground, and to be ejected from the payload and deployed into a large structure after entering the target orbit in space.

[0007] As a developed deployable mesh antenna, a space-use mesh antenna and a method for assembling the same are disclosed in Registered Patent Publication No. 10-2584706.

[0008] The above technology comprises a space net-type antenna including a main reflector that performs the role of a main reflector when deployed, a rib unit that is coupled to the main reflector and induces and guides the deployment of the main reflector through the unfolding of a rib-type rib unit that was folded, and an antenna rim in which the radially inner end of the rib unit is hinge-coupled so as to arrange a plurality of the rib units radially, wherein the antenna comprises an assembly means for coupling the main reflector and the rib unit, and the assembly means comprises a coupling member for bolting, screwing, or riveting the main reflector to the rib unit; a coupling hole formed in the rib unit to allow the coupling member to be bolted, screwed, or riveted; and a through hole formed in the main reflector to allow the coupling member to pass through, and the antenna further comprises a deformation prevention member provided between the coupling member and the through hole, provided in a certain area radially outward of the through hole.

[0009] Additionally, U.S. Patent No. 10,847,893 discloses an articulated folding rib reflector for concentrating radiation.

[0010] The above technology describes a reflector assembly comprising a central hub, a series of ribs coupled to the central hub, and a flexible reflective material attached to the ribs. Each rib comprises a root rib, an intermediate rib, and a tip rib, wherein the root rib is configured to rotate in a first direction around a first axis extending away from the coaxial axis of the central hub, the intermediate rib is configured to rotate in a first direction around a second axis substantially parallel to the first axis, and the tip rib is configured to rotate in a first direction around a third axis substantially parallel to the second axis as the reflector assembly moves into an unfolded configuration. The flexible reflective material and the ribs are configured to form a reflective surface having a substantially parabolic surface profile configured to concentrate electromagnetic energy together.

[0012] However, conventional antennas for space structures have a problem in which the mesh gets stuck between the ribs during the rib folding process, and the mesh is damaged by the ribs due to the mesh coming into direct contact with the ribs. Prior art literature

[0014] Korean Patent Publication No. 10-2584706 (September 26, 2023) U.S. Patent No. 10,847,893 (November 24, 2020) The problem to be solved

[0015] The present invention was devised to solve the above problems, and the problem to be solved by the present invention is to provide a rib structure for a deployable satellite mesh antenna that can minimize damage to the mesh by preventing contact between the rib at the hinge portion and the mesh during the process of folding the rib to house the deployable satellite mesh antenna in a payload. means of solving the problem

[0017] The rib structure of a deployable satellite mesh antenna according to the present invention for solving the above problem comprises: a rib that folds or unfolds around a hinge axis, including a first rib, a second rib, and a third rib; and a mesh supported across one surface of the first rib, the second rib, and the third rib; wherein inclined surfaces are formed on the first rib, the second rib, and the third rib to prevent the mesh from getting stuck between the ribs during the process of the third rib being folded to the second rib and the process of the second rib being folded to the first rib.

[0018] Here, the inclined surface is formed adjacent to the part joined through the hinge.

[0019] In addition, the inclined surface is formed to slope downward toward the hinge side from the surface where the mesh is supported.

[0020] In addition, the above-mentioned inclined surface may be composed of a surface having curvature.

[0021] Additionally, a support member that supports the mesh is configured on the inclined surface, and the support member may include a seating groove formed inside the rib, a support plate installed in the seating groove, and an elastic body installed between the seating groove and the support plate to elastically support the support plate.

[0022] In addition, an elastic band may be formed between the inclined surface and the inclined surface facing it. Effects of the invention

[0024] According to the present invention, mechanical damage and plastic deformation of the mesh can be prevented by structurally blocking physical contact between the rib and the mesh during the storage process, thereby maintaining the precision of the antenna reflective surface after deployment and improving deployment reliability. Brief explanation of the drawing

[0026] FIG. 1 is a perspective view of a deployable satellite mesh antenna according to the present invention in a deployed state. FIG. 2 is an exploded perspective view of a deployable satellite mesh antenna according to the present invention. FIG. 3 is a perspective view of a rib in a folded state applied to a rib structure of a deployable satellite mesh antenna according to the present invention. FIG. 4 is a perspective view of a first rib in an unfolded state applied to the rib structure of a deployable satellite mesh antenna according to the present invention. FIG. 5 is a perspective view of a second rib applied to the rib structure of a deployable satellite mesh antenna according to the present invention in an unfolded state. FIG. 6 is a perspective view of a third rib in an unfolded state applied to the rib structure of a deployable satellite mesh antenna according to the present invention. FIG. 7 is a side view of the folded state of a rib applied to the rib structure of a deployable satellite mesh antenna according to the present invention. FIG. 8 is a left perspective view applied to the rib structure of a deployable satellite mesh antenna according to the present invention. FIG. 9 is a right perspective view applied to the rib structure of a deployable satellite mesh antenna according to the present invention. FIG. 10 is an exploded perspective view of a first deployment module portion applied to the rib structure of a deployable satellite mesh antenna according to the present invention. FIG. 11 is an exploded perspective view of a second deployment module portion applied to the rib structure of a deployable satellite mesh antenna according to the present invention. FIG. 12 is an exploded perspective view of a third deployment module portion applied to the rib structure of a deployable satellite mesh antenna according to the present invention. FIG. 12a is an operational state diagram of the second and third deployment modules applied to the rib structure of a deployable satellite mesh antenna according to the present invention. FIG. 13 is a side view of the folded state of a rib applied to the rib structure of a deployable satellite mesh antenna according to the present invention. FIG. 14 is a drawing showing an inclined surface according to another embodiment of the rib structure of a deployable satellite mesh antenna according to the present invention. FIG. 15 is a drawing in which a support member is configured on an inclined surface in the rib structure of a deployable satellite mesh antenna according to the present invention. FIG. 16 is a drawing showing an elastic band formed on an inclined surface in the rib structure of a deployable satellite mesh antenna according to the present invention. FIG. 17 is an exploded side view of a portion of the rib structure of a deployable satellite mesh antenna according to the present invention in a deployed state. FIG. 18 is a side view of a combined state of a portion of the rib structure of a deployable satellite mesh antenna according to the present invention in an unfolded state. FIG. 19 is a side view of a portion of the rib structure of a deployable satellite mesh antenna according to the present invention in a folded state. Specific details for implementing the invention

[0027] Next, a preferred embodiment of the rib structure of a deployable satellite mesh antenna according to the present invention will be described in detail with reference to the drawings.

[0028] In the following, the same reference numerals are used for technical elements that perform the same function, and repeated detailed descriptions are omitted to avoid redundant explanations.

[0029] Furthermore, the embodiments described below are provided as examples to effectively demonstrate preferred embodiments of the present invention and should not be interpreted to limit the scope of the present invention.

[0031] The present invention relates to a rib structure of a deployable satellite mesh antenna that utilizes self-elastic restoring force as a deployment power source to deploy ribs, thereby minimizing damage to the mesh during the process of folding the ribs of the multi-stage structure, improving the reflection gain and efficiency of the antenna, and ensuring reliability and mechanical life during deployment.

[0033] FIG. 1 is a perspective view of a deployable satellite mesh antenna according to the present invention in a deployed state, and FIG. 2 is an exploded perspective view of a deployable satellite mesh antenna according to the present invention.

[0034] Referring to the attached FIG. 1 and FIG. 2, the deployable satellite mesh antenna (1) according to the present invention comprises a hub (100), a rib (200), a net (300), a mesh (400), and a receiver (not shown in the drawing).

[0035] The hub (100) is the central part of the deployable mesh antenna and is coupled to the main body of the satellite (not shown in the drawing).

[0036] The above hub (100) is composed of a disc with an open center, and a plurality of ribs (200) are installed along the circumference of the outer part.

[0037] A plurality of ribs (200) are installed along the circumference of the hub (100).

[0038] In the present invention, the ribs (200) are shown as 36, but can be increased or decreased depending on design conditions.

[0039] In addition, in the present invention, one rib (200) may be composed of a multi-stage joint.

[0040] The rib (200) according to the present invention shown in the drawing is depicted as having three joints consisting of a first rib (210), a second rib (220), and a third rib (230), but it may be changed to two joints or four joints, etc., depending on the design conditions.

[0041] The net (300) is installed on the upper surface of the rib (200) and may be composed of fibers of a flexible material.

[0042] The above net (300) may be excluded depending on the design conditions.

[0043] The mesh (400) is installed on the upper surface of the rib (200) and performs the function of reflecting radio waves. In this case, if a net (300) is included, the net (300) is configured between the rib (200) and the mesh (400).

[0044] Here, when the net (300) is configured, the net (300) serves as an intermediate for combining the rib (200) and the mesh (400), and the net (300) is combined with the rib (200) using a combining method such as a hook, and the mesh (400) can be combined with the net (300) using a combining method such as a binder or sewing.

[0045] The above mesh (400) refers to a thin metal mesh that acts as a reflector surface that reflects radio waves to gather focus.

[0046] Since the satellite antenna must be accommodated in a narrow space inside the launch vehicle, its size and weight are limited. Accordingly, the mesh (400) is made of a special alloy that has low deformation and good conductivity even in the extreme environment of space.

[0047] For example, it may be made of tungsten or molybdenum, which are very strong and heat-resistant, or gold may be plated on the surface to maximize reflection efficiency and prevent oxidation.

[0048] A receiver (not shown in the drawing) is installed vertically at the center of the hub (100) and receives radio waves reflected from the mesh (400).

[0049] At this time, the receiver may be composed of a second reflector. That is, the receiver may be configured to reflect the radio waves reflected from the mesh (400) back to an opening formed in the center of the hub (100).

[0051] FIG. 3 is a perspective view of a rib structure applied to a mesh antenna for a deployable satellite according to the present invention in a folded state, FIG. 4 is a perspective view of a first rib in an unfolded state, FIG. 5 is a perspective view of a second rib in an unfolded state, and FIG. 6 is a perspective view of a third rib in an unfolded state.

[0052] Referring to the attached FIGS. 3 to 6, the rib (200) is composed of a first rib (210) positioned close to the hub (100), a second rib (220) positioned at the leading end (free end) of the first rib (210), and a third rib (230) positioned at the leading end (free end) of the second rib (220).

[0053] At this time, each of the above ribs (first rib, second rib, and third rib) is configured to be folded inward.

[0054] That is, the third rib (230) is folded to the second rib (220), and while the third rib (230) is folded to the second rib (220), the second rib (220) is folded to the first rib (210), and while the second rib (220) is folded to the first rib (210), the first rib (210) is folded to the central axis of the hub (100).

[0055] Unfolding is done in the reverse order of the folding.

[0056] That is, the unfolding process involves the first rib (210) being unfolded, followed by the second rib (220) being unfolded, and then the third rib (230) being unfolded.

[0058] FIG. 7 is a side view of the folded state of the ribs applied to the rib structure of a deployable satellite mesh antenna according to the present invention.

[0059] Referring to the attached FIG. 7, a unfolding section (600) is configured between the ribs to unfold the ribs in a folded state.

[0060] In detail, the unfolding unit (600) is composed of a first unfolding module (610) installed between the hub (100) and the first rib (210), a second unfolding module (620) installed between the first rib (210) and the second rib (220), and a third unfolding module (630) installed between the second rib (220) and the third rib (230), and performs the function of causing the first rib (210), the second rib (220), and the third rib (230) to be unfolded by hinge rotation in a folded state.

[0062] The above-mentioned unfolding unit (600) is configured such that the first rib (210), the second rib (220), and the third rib (230) are rotated and unfolded by the restoring force of the elastic body that is rolled in opposite directions around the hinge.

[0063] The above-mentioned unfolding unit (600) is subjected to a restoring force that causes each rib (first rib, second rib, and third rib) to unfold from a folded state.

[0064] At this time, the deployment operation of the deployment unit (600) must be performed after the satellite mesh antenna of the present invention is positioned in space at a set location and ejected from the payload. That is, the deployment operation of the deployment unit (600) must be performed when necessary, and the release unit (700) is configured to restrict the operation of the deployment unit (600) and allow the deployment operation to be performed only when necessary.

[0065] The above release unit (700) performs the function of restricting the hinge drive of the unfolding unit (600) when the rib (200) is in a folded state, and releasing the restricted hinge drive of the unfolding unit (600) so that the rib (200) can unfold.

[0066] In addition, in the present invention, the unfolding unit (600) is composed of three unfolding modules consisting of a first unfolding module (610), a second unfolding module (620), and a third unfolding module (63), and each unfolding module (610, 620, 630) must be operated sequentially to prevent damage to the mesh (400) caused by the ribs (210, 220, 230) during the unfolding process.

[0067] Accordingly, in order for three deployment modules to be deployed sequentially as the first deployment module (610), the second deployment module (620), and the third deployment module (630), the release unit (700) according to the present invention comprises a first release module (710) for releasing the release of

[0068] That is, when the first release module (710) is operated, the release of the first unfolding module (210) causes the first rib (210) to unfold, and when the second release module (720) is operated, the release of the second unfolding module (220) causes the second rib (220) to unfold, and when the third unfolding module (230) is operated, the release of the third rib (230) causes it to unfold.

[0070] Accordingly, each of the three deployment modules (610, 620, 630) and the three release modules (710, 720, 730) will be described.

[0072] FIG. 8 shows a left perspective view of a rib applied to a deployable satellite mesh antenna according to the present invention, FIG. 9 shows a right perspective view of a rib, and FIG. 10 shows an exploded perspective view of a first deployment module part.

[0073] Referring to the attached FIGS. 8 to 10, the first deployment module (610) according to the present invention includes a hub bracket (611), a first-1 rib bracket (612), a spool (613), and an elastic plate spring (614).

[0074] The hub bracket (611) is fixed to the hub (100, see FIG. 7) and is configured with a hinge shaft (611a) that is formed to protrude horizontally.

[0075] The first rib bracket (612) is coupled to the lower part of the first rib (210) (direction indicated in the drawing), and a hinge hole (612a) is formed on one side to be fitted into the hinge shaft (611a) and hinged, and a fixing piece (612b) is formed protrudingly on the other side.

[0076] The spool (613) is installed on the hinge axis (611a) and is positioned parallel to the axis of the fixing piece (612b).

[0077] The elastic plate spring (614) is composed of a plate-shaped spring rolled in one direction, with one side part rolled and installed on the spool (613) and the other side part rolled and installed on the outer surface of the fixing piece (612b).

[0078] At this time, the elastic plate spring (614) is installed by being rolled up on the spool (613) in a direction opposite to the direction in which it is installed by being rolled up on the outer surface of the fixing piece (612b), and is installed in an "S" shape.

[0079] Accordingly, with the installation of the elastic plate spring (614), the first rib (210) generates an elastic restoring force in the direction of expansion.

[0080] Accordingly, the first rib (210) is rotated and unfolded by the restoring force of the elastic body (elastic plate spring) that is rolled in opposite directions around the hinge axis (611a).

[0081] In the above configuration, the elastic plate spring (614) can be replaced with another spring having elastic restoring force.

[0082] For example, it can be replaced with an elastic body such as a coil spring, a torsion spring, etc., which is applied between the spool (613) and the fixed piece (612b) and increases the elastic restoring force by folding the first rib (210), or a shape memory alloy.

[0084] Referring to FIG. 8, the first release module (710) of the release unit (700) includes a through hole (711) formed on the upper outer side of the first rib (210) and a string (712) passing through the through hole (711).

[0085] That is, the string (712) passes through the through hole (711) formed in each first rib (210) and weaves the upper side of the first rib (210), and is configured to maintain the folded state of the first rib (210) by the length of the string (712).

[0086] When unfolding, if at least one point of the string (712) is cut with a cutting tool or broken by electric heat, the interlaced state of the string (712) is released, the folded state of the first rib (210) is released, and the first rib (210) is unfolded by the first unfolding module (610).

[0087] Accordingly, the string (712) is made of a material that has a predetermined tensile strength but can be easily cut by a cutter or electric heat.

[0089] FIG. 11 shows an exploded perspective view of a second deployment module portion applied to the rib structure of a deployable satellite mesh antenna according to the present invention.

[0090] In the attached FIG. 11, configurations identical to those in FIG. 10 are described using the same terminology but with different reference numerals.

[0091] Referring to the attached FIG. 11, the second deployment module (620) includes a first-2 rib bracket (621), a second-1 rib bracket (622), a spool (623), and an elastic plate spring (624).

[0092] The first-second rib bracket (621) is installed at the tip of the first rib (210) and is configured with a hinge shaft (621a) that is formed to protrude horizontally.

[0093] The second-1 rib bracket (622) is coupled to the second rib (220), and a hinge hole (622a) is formed on one side to be fitted into the hinge shaft (621a) and hinged, and a fixing piece (622b) is formed protrudingly on the other side.

[0094] The spool (623) is installed on the hinge axis (621a) and is positioned parallel to the axis of the fixing piece (622b).

[0095] The elastic plate spring (624) is composed of a plate-shaped spring rolled in one direction, with one side part rolled and installed on the spool (623) and the other side part rolled and installed on the outer surface of the fixing piece (622b).

[0096] At this time, the elastic plate spring (624) is installed by being rolled up on the spool (623) in a direction opposite to the direction in which it is installed by being rolled up on the outer surface of the fixing piece (622b), and is installed in an "S" shape.

[0097] Accordingly, with the installation of the elastic plate spring (624), the second rib (220) generates an elastic restoring force in the direction of expansion.

[0098] Accordingly, the second rib (220) is rotated and unfolded by the restoring force of the elastic body (elastic plate spring) that is rolled in opposite directions around the hinge axis (621a).

[0100] The second release module (720) of the release unit (700) includes a shaft (721) that is inserted into and protrudes from the outside of the first-second rib bracket (621), a latch (722) coupled to the outside of the shaft (721), and a sheave (723) coupled to the inside of the shaft (721).

[0101] The hook formed at the tip of the latch (722) above is configured to engage with the catch projection (622c) formed on the outer circumference of the hinge hole (622a) of the second-1 rib bracket (622).

[0102] Although not shown in the drawing, the end of the first wire (not shown in the drawing) connected from the hub (100, see FIG. 7) is connected to the sheave (723).

[0103] With the above configuration, when the second rib (220) is folded toward the first rib (210), the hook of the latch (722) engages with the catch projection (622c), thereby restraining the second rib (220) to the first rib (210).

[0104] Accordingly, the release of the second restraint release module (720) is achieved by winding the end of the first wire connected to the hub side, causing the sheave (723) connected to the end of the first wire to rotate, and the shaft (721) rotates due to the rotation of the sheave (723), and the latch (722) rotates due to the rotation of the shaft (721), and the hook of the latch (722) is disengaged from the locking projection (622c) due to the rotation of the latch (722).

[0105] When the hook of the above latch (722) is disengaged from the locking projection (622c), the second rib (220) is extended from the first rib (210) by the elastic restoring force of the elastic plate spring (624).

[0107] FIG. 12 is an exploded perspective view of a third deployment module portion applied to the rib structure of a deployable satellite mesh antenna according to the present invention.

[0108] In the attached FIG. 12, configurations identical to those in FIG. 11 are described using the same terminology but with different reference numerals.

[0109] Referring to the attached FIG. 12, the third deployment module (630) includes a second-2 rib bracket (631), a third-1 rib bracket (632), a spool (633), and an elastic plate spring (634).

[0110] The second-2 rib bracket (631) is installed at the tip of the second rib (220) and is configured with a hinge shaft (631a) that is formed to protrude horizontally.

[0111] The third-1 rib bracket (632) is coupled to the third rib (230), and a hinge hole (632a) is formed on one side to be fitted into the hinge shaft (631a) and hinged, and a fixing piece (632b) is formed protrudingly on the other side.

[0112] Here, the hinge hole (632a) may be configured with a bearing (635) that smoothly induces hinge movement, and a snap ring (636) that prevents the shaft from coming off may be installed.

[0113] The spool (633) is installed on the hinge axis (631a) and is positioned parallel to the axis of the fixing piece (632b).

[0114] The elastic plate spring (634) is composed of a plate-shaped spring rolled in one direction, with one side part rolled and installed on the spool (633) and the other side part rolled and installed on the outer surface of the fixing piece (632b).

[0115] At this time, the elastic plate spring (634) is installed by being rolled onto the spool (633) in a direction opposite to the direction in which it is installed by being rolled onto the outer surface of the fixing piece (632b), and is installed in an "S" shape.

[0116] Accordingly, with the installation of the elastic plate spring (634), the third rib (230) generates an elastic restoring force in the direction of development.

[0117] Accordingly, the third rib (230) is rotated and unfolded by the restoring force of the elastic body (elastic plate spring) that is rolled in opposite directions around the hinge axis (631a).

[0119] The third release module (730) of the release unit (700) includes a shaft (731) that is inserted into and protrudes from the outside of the second-2 rib bracket (631), a latch (732) coupled to the outside of the shaft (731), and a sheave (733) coupled to the inside of the shaft (731).

[0120] The hook formed at the tip of the latch (732) above is configured to engage with the catch projection (632c) formed on the outer circumference of the hinge hole (632a) of the third-1 rib bracket (632).

[0121] Although not shown in the drawing, the sheave (723) of the second release module (720) and the sheave (733) of the third release module (730) are connected by a second wire (not shown in the drawing).

[0122] With the above configuration, when the third rib (230) is folded toward the second rib (220), the hook of the latch (732) engages with the catch projection (632c), thereby restraining the third rib (230) to the second rib (220).

[0123] Accordingly, the release of the third release module (730) is achieved by winding the end of the first wire connected to the hub side, which causes the sheave (723) of the second release module (720) to rotate, and the second wire connected to the sheave (723) is wound onto the sheave (723) by the rotation of the sheave (723), and as the second wire is wound, the sheave (733) rotates.

[0124] The shaft (731) is rotated by the rotation of the sheave (733), and the latch (732) is rotated by the rotation of the shaft (731), and the hook of the latch (732) is disengaged from the locking projection (632c) by the rotation of the latch (732).

[0125] When the hook of the above latch (732) is disengaged from the locking projection (632c), the third rib (230) is extended from the third rib (230) by the elastic restoring force of the elastic plate spring (634).

[0126] During this process, one end of the second wire is wound onto the sheave (723) of the second release module (720), thereby rotating the sheave (733) of the third release module (730).

[0127] The unfolding must be done in the order of the first rib (210), the second rib (220), and the third rib (230).

[0128] Accordingly, the sheave (723) of the second release module (720) and the sheave (733) of the third release module (730) can be rotated simultaneously according to the winding of the first wire.

[0129] In order to prevent the sheave (723) of the second release module (720) and the sheave (733) of the third release module (730) from rotating simultaneously, the sheave (723) of the second release module (720) and the latch (722) are configured such that the latch (722) can rotate immediately by winding the first wire, and the sheave (733) of the third release module (730) is configured to rotate when the degree of winding of the first wire exceeds a certain range.

[0130] This can be achieved by adjusting the length of the second wire, adjusting the engagement angle of the sheave and latch, or adjusting the circumference of the wire wound onto the sheave.

[0132] The sheave rotates by the winding of the y, and the second release module (720) and the third release module (730) are explained through an embodiment.

[0133] FIG. 12a shows the operation state diagram of the second and third deployment modules applied to the rib structure of a deployable satellite mesh antenna according to the present invention.

[0134] FIG. 12a shows an embodiment in which the second release module (720) and the third release module (730) are sequentially unfolded according to the winding of the wire. Referring to (a) of FIG. 12a, the initial state of the second release module (720) and the third release module (730) is such that the latch (722, 732) is restrained by the locking projection (622c, 632c).

[0135] One end of the first wire (W1) is connected to the hub (100), and the other end is connected to the sheave (723) of the second release module (720).

[0136] One end of the second wire (W2) is connected to the sheave (723) of the second release module (720), and the other end is connected to the sheave (733) of the third release module (730).

[0137] In the above, the rotational projection (722a) formed on the latch (722) of the second release module (720) and the rotational projection (723a) formed on the sheave (723) are configured to interlock with each other.

[0138] Additionally, the rotational projection (732a) formed on the latch (732) of the third release module (730) and the rotational projection (733a) formed on the sheave (733) are configured to be spaced apart from each other at a predetermined angle.

[0140] Figure 12a (b) shows the state in which the first wire (W1) is operated by winding using a motor or the like at the hub side.

[0141] Since the rotational projection (722a) formed on the latch (722) of the second release module (720) and the rotational projection (723a) formed on the sheave (723) are engaged with each other, when the first wire (W1) is wound from the hub side, the sheave (723) of the second release module (720) rotates, and the latch (722) rotates and is released from the locking projection (622c). Accordingly, the release of the first rib (210) and the second rib (220) is achieved.

[0142] In addition, a portion of the second wire (W2) is wound onto the sheave (723) of the second release module (720) by winding the first wire (W1).

[0143] However, since the rotational projection (732a) formed on the latch (732) of the third release module (730) and the rotational projection (733a) formed on the sheave (733) are spaced apart from each other at a predetermined angle, the latch (732) of the third release module (730) cannot rotate until the rotational projection (732a) formed on the latch (732) of the third release module (730) and the rotational projection (733a) formed on the sheave (733) reach a rotation angle at which they interlock, and the latch (732) of the third release module (730) remains in a state of being constrained by the locking projection (632c). That is, the second rib (220) and the third rib (230) remain in a constrained state.

[0145] Figure 12a (c) shows the operating state as the first wire (W1) is further wound.

[0146] Since the rotational projection (722a) formed on the latch (722) of the second release module (720) and the rotational projection (723a) formed on the sheave (723) are still engaged with each other, when the first wire (W1) is wound from the hub side, the sheave (723) of the second release module (720) rotates, and the latch (722) rotates further.

[0147] In addition, a portion of the second wire (W2) is wound onto the sheave (723) of the second release module (720) by the winding of the first wire (W1), and the sheave (733) of the third release module (730) is rotated.

[0148] At this time, since the rotational projection (732a) formed on the latch (732) of the third release module (730) and the rotational projection (733a) formed on the sheave (733) are still engaged with each other, as the sheave (733) of the third release module (730) rotates, the latch (732) of the third release module (730) rotates, and thus the latch (732) rotates and disengages from the locking projection (632c). Accordingly, the release of the second rib (220) and the third rib (230) is achieved.

[0150] In addition, the latch (722) of the second release module (720) and the latch (732) of the third release module (730) may be configured with a torsion spring, etc., to prevent artificial rotation caused by vibration or external pressure, or to prevent jamming caused by a restoring force applied during the rotation of the sheave.

[0152] According to the present invention, by utilizing the self-elastic restoring force of the elastic plate spring as a power source for deployment, it deploys smoothly and naturally without mechanical friction, thereby minimizing deployment shock applied to the structure upon completion of deployment, preventing attitude disturbance of the satellite body, and fundamentally eliminating the risk of deployment failure due to component seizure even in harsh space environments of high vacuum and cryogenic temperatures, thus ensuring reliability in deployment.

[0154] Meanwhile, in satellite mesh antennas, mesh jamming occurs between ribs during the rib folding process, and direct contact between the ribs can lead to damage to the mesh caused by the ribs.

[0155] Accordingly, the rib structure of the present invention for a deployable satellite mesh antenna is configured to prevent contact between the rib and the mesh at the hinge portion during the process of folding the rib to house it in the payload.

[0157] FIG. 13 is a side view of the folded state of the ribs applied to the rib structure of a deployable satellite mesh antenna according to the present invention.

[0158] Referring to the attached FIG. 13, the configuration of a unfolding part (600) having a hinge between the ribs to fold or unfold the ribs is schematically shown, and the configuration for unfolding the ribs in a folded state is omitted and schematically shown.

[0159] Here, the unfolding unit (600) is composed of a first unfolding unit (510) installed between the hub (100) and the first rib (210), a second unfolding unit (620) installed between the first rib (210) and the second rib (220), and a third unfolding unit (630) installed between the second rib (220) and the third rib (230).

[0161] Although the first unfolding module (610) also has a hinge configured for folding and unfolding between the hub and the first rib (210), the mesh is not folded or contacted during the folding process of the first unfolding module (610), so a description of this is omitted.

[0162] The second unfolding module (620) and the third unfolding module (630) each have a hinge (H1, H2) configured therein, and are folded or unfolded around the hinge (H1, H2) as an axis.

[0163] To explain the sequence of the folding process, the third rib (230) is folded into the second rib (220), and while the third rib (230) is folded into the second rib (220), the second rib (220) is folded into the first rib (210).

[0164] At this time, a mesh is installed that is supported across one surface of the first rib (210), the second rib (220), and the third rib (230), and an inclined surface is formed on the surface where the ribs face each other.

[0165] Specifically, in order to prevent the mesh from getting stuck between the ribs during the process in which the third rib (230) is folded to the second rib (220) and the process in which the second rib (220) is folded to the first rib (210), an inclined surface (211) is formed on the first rib (210), inclined surfaces (221, 222) are formed on the second rib (220), and an inclined surface (231) is formed on the third rib (230).

[0166] Here, as the second rib (220) folds with the first rib (210) and the third rib (230) also folds, inclined surfaces (221, 222) are formed on both sides.

[0167] That is, the inclined surfaces (211, 221, 222, 231) are formed adjacent to the portion joined through the hinge (H1, H2).

[0168] In addition, the inclined surfaces (211, 221, 222, 231) are formed to slope downward toward the hinge (H1, H2) side from the surface where the mesh is supported.

[0169] Due to the configuration of these inclined surfaces, the ribs do not come into contact with each other when the ribs are folded, and a predetermined space is formed between the ribs and the rib surfaces facing each other as the ribs are folded. A mesh is accommodated in this space, thereby preventing the mesh from being rolled into or jammed in the gaps between the ribs.

[0170] In addition, since the problem of the mesh getting caught on the ribs during unfolding is resolved, damage to the mesh caused by unfolding failure can be prevented.

[0172] The above inclined surfaces (211, 221, 222, 231) may consist of inclined planes as well as planes having gentle curvature.

[0174] FIG. 14 is a drawing showing an inclined surface according to another embodiment of the rib structure of a deployable satellite mesh antenna according to the present invention.

[0175] The inclined surface shown in FIG. 14 represents an inclined surface (211) applied to the first rib (210), and can also be applied to other inclined surfaces (221, 222, 231).

[0176] Referring to the attached FIG. 14, the inclined surface (211) forms a gentle curved surface to have curvature.

[0177] When such an inclined surface (211) is formed as a gentle curved surface having curvature, there is an advantage in that the space in which the mesh can be accommodated is relatively increased.

[0179] The space secured by the configuration of the slope cannot be used to join the mesh to the rib.

[0180] Accordingly, when the rib is in a folded state, the mesh is accommodated with a gentle curvature, but vibration or external pressure may be applied to the rib during the process of launching the satellite or during the process of the rib unfolding after settling into orbit.

[0181] Therefore, a configuration that holds the mesh accommodated in the space secured by the slope may be further included.

[0183] FIG. 15 shows a drawing in which a support member is formed on an inclined surface in the rib structure of a deployable satellite mesh antenna according to the present invention.

[0184] The inclined surface (211) shown in FIG. 15 is depicted as being formed on the first rib (210), but it can also be applied to other inclined surfaces (221, 222, 231).

[0185] Referring to (a) and (b) of the attached FIG. 15, the support member (800) is installed on an inclined surface (211) and performs the function of supporting the mesh, and includes a seating groove (810) formed inside the rib (210), a support plate (820) installed so as to be rotatable in the seating groove (810), and an elastic body (830) installed between the seating groove (810) and the support plate (820) to elastically support the support plate (820).

[0186] In the above, the support plate (820) can be made of a flexible material, and it is sufficient if the material does not damage the mesh upon contact with the mesh.

[0187] According to the above configuration, the support plate (820) is supported by an elastic body (830) and protrudes from the inclined surface (211), thereby supporting and holding the mesh during the process of the rib folding.

[0188] In addition, it stably guides the mesh even during the rib unfolding process to prevent the mesh from getting stuck in the unfolding section.

[0190] (c) of the attached FIG. 15 shows another embodiment of the support member (800), and the support member (800) of the other embodiment includes a seating groove (810) formed inside the rib, a support plate (820) installed in the seating groove (810), and an elastic body (830) installed between the seating groove (810) and the support plate (820) to elastically support the support plate.

[0191] Here, the shape is configured such that the thickness becomes relatively larger in the hinge direction along the inclined surface (211) of the support plate (820).

[0193] Thus, the lower surface of the mesh (400) disposed on the upper surface is supported by the configuration of the support member (800) so that the mesh (400) maintains a predetermined curved surface.

[0195] In addition, as the unfolding part formed between the ribs folds or unfolds around the hinge axis, the mesh may come into contact with the rotation of the hinge and be damaged.

[0197] FIG. 16 is a drawing showing an elastic band formed on an inclined surface in the rib structure of a deployable satellite mesh antenna according to the present invention.

[0198] FIG. 16 illustrates an inclined surface between the first rib (210) and the second rib (220), and the elastic band can also be applied between the second rib and the third rib.

[0199] Referring to the attached FIG. 16, an elastic band (850) is formed between the inclined surface (211) formed on the first rib (210) and the inclined surface (222) formed on the second rib (220) facing the inclined surface (211).

[0200] That is, the elastic band (850) may be made of a rubber band or the like that is elastic and has a predetermined width.

[0201] One side of the elastic band (850) is attached to an inclined surface (211) formed on the first rib (210), and the other side is attached to an inclined surface (222) formed on the second rib (220).

[0202] These elastic bands separate the mesh and the second deployment module (620).

[0203] According to the above elastic band, the phenomenon of the mesh getting stuck in the unfolding part (600) when the rib is folded or unfolded can be fundamentally prevented, and after the rib is unfolded, the mesh is supported, thereby improving the reflection efficiency of the mesh.

[0205] According to the present invention, mechanical damage and plastic deformation of the mesh can be prevented by structurally blocking physical contact between the rib and the mesh during the storage process, thereby maintaining the precision of the antenna reflective surface after deployment and improving deployment reliability.

[0207] Meanwhile, there is a need to protect the mesh from the hinge movement of the unfolding part by preventing contact between the mesh and the unfolding part during the folding process by folding the rib.

[0208] It includes a configuration that minimizes damage to the mesh by preventing the mesh from coming into contact with the deployment section during the process of folding the ribs to house the rib structure of a deployable satellite mesh antenna into the payload.

[0210] FIG. 17 shows an exploded side view of a portion of the rib structure of a deployable satellite mesh antenna according to the present invention in an unfolded state, and FIG. 18 shows a side view of the combined state.

[0211] Referring to the attached FIGS. 17 and 18, a unfolding section (500) having a hinge between the ribs is configured to fold or unfold the ribs.

[0212] The configuration unfolded in the above-mentioned unfolding section (600) is omitted from the description.

[0213] In detail, the expansion section (600) is installed between the hub (100) and the first rib (210), between the first rib (210) and the second rib (220), and between the second rib (220) and the third rib (230).

[0214] To explain the sequence of the folding process, the third rib (230) is folded into the second rib (220), and while the third rib (230) is folded into the second rib (220), the second rib (220) is folded into the first rib (210).

[0215] A protective pad (900) is configured on the first rib (210) to prevent the mesh from getting caught between the unfolding parts during the process in which the third rib (230) is folded into the second rib (220) and the process in which the second rib (220) is folded into the first rib (210).

[0216] The above protective pad (900) is installed on one of the ribs that face each other when the third rib (230) is folded to the second rib (22) and when the second rib (220) is folded to the first rib (210), and performs the function of preventing the mesh from contacting the unfolding part (600).

[0217] Here, the protective pad (900) is installed on one of the selected ribs facing each other when the third rib (230) is folded to the second rib (220) and when the second rib (220) is folded to the first rib (210).

[0218] That is, one side of the protective pad (900) is connected to the rib, and the other side is formed as a free end.

[0219] For example, when a portion of the protective pad (900) is attached to the first rib (210) centered on the second deployment module (520), the end of the protective pad (900) rolled toward the second rib (220) is formed as a free end. Additionally, when a portion of the protective pad (900) is attached to the third rib (230) centered on the third deployment module (630), the end of the protective pad (900) rolled toward the second rib (220) is formed as a free end.

[0220] Accordingly, the above protective pad (900) is made of a flexible material, and a mesh (400) is received in a rolled state on the inner side thereof.

[0221] The flexible material of the above protective pad (900) may be made of one material selected from polyimide (PI), TPU (thermoplastic polyurethane), rubber, and silicone.

[0223] Meanwhile, as the above protective pad (900) is installed, the gap between the ribs facing each other in the folded state can be narrowed due to the thickness of the above protective pad (900).

[0224] If the gap between the ribs narrows, the mesh folded between the protective pads may be folded by the pads, causing a fold line to form.

[0225] Accordingly, a seating groove (910) may be formed on the surface where the above protective pad (900) is attached or installed, or on the rounded surface that contacts the opposing rib.

[0226] By securing a gap between ribs facing each other while the ribs are folded by the above-mentioned seating groove (910), the mesh (400) can be folded to prevent the occurrence of wrinkles.

[0228] FIG. 19 is a side view of a portion of the rib structure of a deployable satellite mesh antenna according to the present invention in a folded state.

[0229] According to the attached FIG. 19, the protective pad (900) accommodates the mesh (400) that is rolled up near the unfolding part (600) during the process of the ribs (210, 220) being folded inside it.

[0230] In addition, when the ribs (210, 220) are in a folded state, the protective pad (900) partitions the space between the unfolded section (600) and the mesh (400).

[0231] Although not shown in the drawing, the same effect occurs even when the second rib (220) and the third rib (230) are in a folded state.

[0232] That is, the protective pad (900) fundamentally prevents the mesh (400) from coming into contact with the unfolded part (600) when the rib (200) is in a folded or unfolded state, thereby protecting the mesh (400).

[0234] According to the present invention, mechanical damage and plastic deformation of the mesh can be prevented by structurally blocking physical contact between the rib and the mesh during the storage process, thereby maintaining the precision of the antenna reflective surface after deployment and improving deployment reliability.

[0236] Although a preferred embodiment of the rib structure of a deployable satellite mesh antenna according to the present invention has been described above, the present invention is not limited thereto, and various modifications are possible within the scope of the claims, the description of the invention, and the attached drawings, and such modifications also fall within the scope of the present invention. Explanation of the symbols

[0238] 1: Deployable mesh antenna for satellites 100: Hub 200: Rib 210: 1st Lib 220: 2nd Lib 230: 3rd Rib 300: Net 400: Mesh 600: Deployment 610: 1st Deployment Module 620: 2nd Deployment Module 630: 3rd Deployment Module 700: Release from Detention Department 710: 1st Release Module 720: 2nd Release Module 730: 3rd Release Module 800: Support part 810: Settling home 820: Support plate 830: Elastic body 850: Elastic band 900: Protective pad 910: Seating groove

Claims

Claim 1 A rib structure of a deployable satellite mesh antenna comprising: a rib that folds or unfolds around a hinge axis, including a first rib, a second rib, and a third rib; and a mesh supported across one surface of the first rib, the second rib, and the third rib, wherein inclined surfaces are formed on the first rib, the second rib, and the third rib to prevent the mesh from being jammed between the ribs during the process of the third rib being folded to the second rib and the process of the second rib being folded to the first rib. Claim 2 A rib structure of a deployable satellite mesh antenna according to claim 1, characterized in that the inclined surface is formed adjacent to the portion joined through the hinge. Claim 3 A rib structure of a deployable satellite mesh antenna according to claim 1, characterized in that the inclined surface is formed to be inclined downward toward the hinge side from the surface where the mesh is supported. Claim 4 A rib structure of a mesh antenna for a deployable satellite according to claim 1, wherein the inclined surface has curvature. Claim 5 A rib structure of a deployable satellite mesh antenna according to claim 1, characterized in that a support member supporting the mesh is formed on the inclined surface. Claim 6 A rib structure of a deployable satellite mesh antenna according to claim 5, wherein the support member comprises: a seating groove formed on the inner side of each of the first rib, the second rib, and the third rib; a support plate installed in the seating groove; and an elastic body installed between the seating groove and the support plate to elastically support the support plate. Claim 7 A rib structure of a deployable satellite mesh antenna according to claim 1, characterized in that an elastic band is formed between the inclined surface and the inclined surface facing it.

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