JP2011093339A - Holding bracket of development structure - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a holding bracket of a development structure which surely reduces an impact level transmitted to a body of a spacecraft when the holding state of the development structure is released. <P>SOLUTION: The holding bracket 1 holds the development structure including a solar cell paddle and a communication antenna in a folded state at the body 5 of the spacecraft and separates the development structure by actuating an explosive device that becomes an impact generation source 3 after reaching the space. The holding bracket 1 includes: front side members 12 of a flat plate shape on which the development structure is fixed and held; back side members 13 of the flat plate shape that are mounted in the body 5 of the spacecraft; and side surface side members 11 of the flat plate shape that connect the front side members 12 to the back side members 13. By arranging the front side members 12 and the back side members 13 alternately in parallel and by connecting the end surfaces of front side members 12 and the back side members 13 by the side face side members 11 arranged perpendicularly to the front side members 12, a structure of a lattice shape is obtained that forms a front side cavities 14 and back side cavities 15 having openings of a rectangular shape at the front and back sides alternately. <P>COPYRIGHT: (C)2011,JPO&INPIT

Description

  The present invention relates to a deployment structure holding bracket, and in particular, holds a deployment structure such as a solar array paddle (SAP) or a communication antenna mounted on a spacecraft such as an artificial satellite in a folded state, The present invention relates to a deployment structure holding bracket capable of reducing an impact generated when the deployment structure is deployed.

  In recent years, spacecraft such as artificial satellites have a large area, such as solar array paddles (SAP) and communication antennas, in order to achieve high performance and reliability in space. A structure that occupies a volume has come to be mounted. In order to withstand the severe rocket launch environment, such a large area and volume structure is fixed and held in a folded state on the spacecraft body side, and after reaching the outer space, the fixed part is released. , Has a structure that expands so as to obtain a large area and volume. For this reason, it is necessary for the fixing portion to include a holding / releasing mechanism that has both a mechanism for firmly fixing the deployment structure and a mechanism for reliably releasing when the space reaches the outer space.

  Such a deployment structure holding and releasing mechanism is provided with a deployment structure holding bracket for fixing and holding the deployment structure body at the spacecraft body side in the folded position of the deployment structure, for example, fastening bolts and nuts, etc. The fixed structure is used to position and fix the unfolded structure in a folded state, and when reaching space, the explosives are explode by remote drive control and operated by pyrotechnics such as bolt cutters and separation nuts. By releasing the fixing function of the fixing member, the unfolded structure held by the unfolded structure holding bracket is released from the folded state and is deployed in outer space.

  Here, the impact force generated when the expanded structure is released from the folded state due to the explosion of the explosive reaches the attachment site of the expanded structure holding bracket via the expanded structure holding bracket, and further It propagates to the equipment such as electronic equipment housed in the navigation body. For this reason, it affects the performance of the mounted device such as an electronic device, and in the worst case, when an impact exceeding the guaranteed level of the mounted device is applied, a result of causing damage to the mounted device is caused.

  For this reason, for example, Japanese Patent Application Laid-Open No. 2001-171600 “Holding and Release Bracket for Expanded Structure” and Japanese Patent Application Laid-Open No. Various proposals have been made in the past, such as “Deployment holding mechanism of deployment structure in spacecraft”, Japanese Patent Publication No. 59299/1990.

  FIG. 6 is a schematic view showing an example of a deployment structure holding bracket for a current spacecraft as described in Patent Document 1, and a deployment structure for fixing and holding the deployment structure in a folded state. The structure of a body holding bracket (hereinafter sometimes abbreviated as “holding bracket”) is shown. FIG. 6A shows a plan view of the holding bracket, and FIG. 6B shows a side view of the holding bracket.

  In FIG. 6, the holding bracket 1 </ b> E has a rectangular parallelepiped box-shaped structure and is made of a metal material having a predetermined thickness D. The holding bracket 1E has a mechanism for holding the expanded structure in a folded state on a rectangular-shaped holding / separating plate 10E, and for separating the expanded structure from the holding / separating plate 10E during expansion. Here, at each end of the holding / separating plate 10E, the legs 2 bent at right angles are connected. A mounting plate 4 is bent and extended at the ends of the left and right leg portions 2 of each leg portion 2 so as to be fixed to the spacecraft body 5, and four mounting portions 4 a are provided on the mounting plate 4. , 4b, 4c, and 4d, and are integrated with the spacecraft body 5 by bolts, nuts, and adhesives at the attachment portions 4a, 4b, 4c, and 4d, respectively.

  Further, when the spacecraft is launched, the expanded structure in a folded state is held and fixed on the separation surface 40 side of the holding separation plate 10E of the holding bracket 1E shown in the side view of FIG. For this reason, although not shown, a mechanism (for example, a fastening member such as a fastening bolt / nut for holding and fixing the expanded structure in a folded state) can be attached to the substantially central portion of the holding bracket 1E (for example, , A fastening bolt insertion hole).

  Further, as shown in the impact generation source 3 of FIG. 6, the holding side 30 (that is, the spacecraft body 5 side) of the holding separation plate 10E of the holding bracket 1E has a fastening bolt The gunpowder etc. for canceling the fixing function of fixing members, such as a nut, are equipped. Exploding explosives attached to the holding side 30 in the substantially central part of the holding separation plate 10E of the holding bracket 1E and operating pyrotechnics such as a bolt cutter and a separation nut by remote control when reaching space. Thus, the unfolded structure fixedly held on the separation surface 40 of the holding bracket 1E is released from the folded state in the direction indicated by the release side 20, and is deployed in outer space.

  When the unfolded structure is released from the separation surface 40 of the holding bracket 1E, the impact from the impact generating source 3 is a flat metal having a uniform thickness D, as indicated by impact propagation paths 50a, 50b, 50c, and 50d. It propagates in the holding bracket 1E made of a plate, reaches the attachment parts 4a, 4b, 4c, and 4d where the holding bracket 1E is attached to the spacecraft body 5 and propagates to the spacecraft body 5 side.

  In a limited space of a spacecraft that requires weight reduction, the impact level that propagates to the spacecraft body 5 side is not sufficiently reduced, and the electronic equipment mounted on the spacecraft body 5 There is a case that the shock resistance value of the mounted equipment is deviated. For this reason, in order to increase the mass of the holding bracket 1E that forms the impact propagation paths 50a, 50b, 50c, 50d, the thickness of the holding bracket 1E is increased as much as possible, or the size of the holding bracket 1E is increased as much as possible. There have been proposals to change the material of the holding bracket 1E or to form the holding bracket 1E using an impact buffering material. For example, in Patent Document 1, the structure of the leg 2 up to the attachment parts 4a, 4b, 4c, 4d for attaching the holding bracket 1E to the spacecraft body 5 is described as an elastic part having a flexible elastic force. The proposal which reduces the impact from the impact generation source 3 is made | formed by forming by.

  Alternatively, using an adhesive made of a material (resin, synthetic rubber, etc.) having a higher impact attenuation rate than a metal material, for example, Japanese Patent Application Laid-Open No. 2008-95071 “Adhesive material for multi-stage or single-stage curing” There has also been a proposal to join the holding bracket 1E to the spacecraft body 5 at the attachment sites 4a, 4b, 4c, and 4d by using an adhesive containing an epoxy material and a curing agent, as in “and its method of use”. .

JP 2001-171600 A (page 3-4) JP-A-10-59299 (page 2-3) JP 2008-95071 A (page 3-5)

  However, in order to reduce the impact level below the guaranteed shock resistance value of the mounted equipment such as electronic equipment mounted in the spacecraft body by the current technology as described above, the mass of the holding bracket is increased. In addition, the thickness of the holding bracket is increased, the size of the holding bracket is increased, the material of the holding bracket is changed, the size of the holding bracket is increased, the shock-absorbing material is used, Alternatively, it is necessary to change the placement of electronic equipment and other devices to keep them away from the impact source, which ultimately increases the mass of the spacecraft and increases costs due to additional construction. The problem of being invited occurs.

  In addition, when checking the impact environment level after mounting the onboard equipment on the spacecraft, an abnormality that deviates from the shock resistance guaranteed value of the onboard equipment is detected, and replacement / addition of component parts, readjustment, etc. There is a need, and in the later stages of development, problems such as increased costs due to change design and additional construction, or increased mass of the spacecraft may occur.

  The present invention has been made in view of such circumstances, and by adopting a structure that reliably obtains an impact reduction effect in a limited space such as a spacecraft, in designing a deployment structure holding bracket, It is possible to effectively prevent the impact environment level from deviating after the on-board equipment such as electronic equipment is installed, and to more reliably suppress the increase in the mass of the space navigation body and the cost increase due to the additional work in the late stage of spacecraft development. It is an object to provide a simple deployment structure holding bracket.

  That is, the present invention, for example, after the launch of the spacecraft, when holding and releasing the deployment structure such as the solar cell paddle and the communication antenna, the pyrotechnics operations such as the separation nut, the bolt cutter, the wire cutter, etc. An object of the present invention is to provide a deployment structure holding bracket having a structure capable of reliably reducing the level of impact propagating to the navigation body main body.

  In order to solve the above-described problems, the deployment structure holding bracket according to the present invention employs the following characteristic configuration.

  (1) After the unfolded structure used in the unfolded state is fixed and held in a state where the unfolded body is folded to the spacecraft body side, the unfolded structure in the folded state is obtained by operating a pyrotechnic as an impact generation source. A deployment structure holding bracket that separates for deployment, a flat plate-shaped surface side member that fixes and holds the deployment structure, a flat plate-shaped back surface side member that is attached to the spacecraft body side, and the surface side A flat plate-shaped side surface member that connects the member and the back surface side member, the front surface side member and the back surface side member are alternately arranged in parallel, and are perpendicular to the front surface side member and the back surface side member. By connecting the end surfaces of the front surface side member and the back surface side member by the side surface member arranged in the grid, a rectangular box having rectangular openings alternately formed on the front surface side and the back surface side is formed. Construction Deployment structure retention bracket to.

  According to the deployment structure holding bracket of the present invention, the following effects can be obtained.

  That is, the effect of the deployment structure holding bracket of the present invention is that the impact environment level at the time of deployment of the deployment structure after the installation of the installation device such as the electronic device on the spacecraft body is the shock resistance guaranteed value of the installation device. It is possible to more reliably prevent the deviation from the above, and at the later stage of development of the spacecraft, it is possible to suppress the increase in the mass of the spacecraft and the cost increase due to additional construction by pulling the deployment structure holding bracket. That is.

  The reason for this is that by forming a lattice-like bent structure with cavities alternately on the front and back as a deployment structure holding bracket, even in a limited space such as a spacecraft such as an artificial satellite, the deployment structure It is possible to ensure a sufficiently long impact propagation distance until the impact due to pyrotechnic operation during body deployment reaches the attachment site where the deployment structure holding bracket is attached to the spacecraft body, This is because it is possible to increase the mass on the impact propagation path, and therefore, it is possible to obtain a sufficient impact level reduction effect at the site where the deployment structure holding bracket is attached to the spacecraft body.

It is a schematic diagram which shows an example of the expansion structure holding | maintenance bracket of the spacecraft concerning this invention. It is a schematic diagram which shows the other example of the expansion structure holding | maintenance bracket of the spacecraft which concerns on this invention. It is a schematic diagram which shows the further different example of the expansion structure holding | maintenance bracket of the spacecraft which concerns on this invention. It is a schematic diagram which shows the further different example of the expansion structure holding | maintenance bracket of the spacecraft which concerns on this invention. It is a schematic diagram which shows the further different example of the expansion structure holding | maintenance bracket of the spacecraft which concerns on this invention. It is a schematic diagram which shows an example of the expansion structure holding | maintenance bracket of the present spacecraft.

  Hereinafter, a preferred embodiment of a deployment structure holding bracket according to the present invention will be described with reference to the accompanying drawings. In the following description, as the deployment structure holding bracket according to the present invention, the folded deployment structure is fixedly held, and the shape of the holding separation plate for separating the deployment structure when reaching the outer space is the background. As in the case of FIG. 6 described in the art, the case of a rectangular shape will be described. However, the present invention is not limited to such a rectangular shape, and the development structure can be fixedly held and separated. As long as it has a shape, it may be an arbitrary shape such as a circular shape or a triangular shape.

(Features of the present invention)
Prior to the description of the embodiments of the present invention, an outline of the features of the present invention will be described first. The present invention can be developed even in a limited space such as a spacecraft such as an artificial satellite by forming a lattice-like bent structure having cavities alternately on the front and back as a deployment structure holding bracket. It is possible to ensure a sufficiently long impact propagation distance until the impact due to pyrotechnic operation during the deployment of the structure reaches the mounting site where the deployment structure holding bracket is attached to the spacecraft body. The main feature is that a sufficient impact reduction effect can be obtained at the attachment part of the body holding bracket.

  Thus, after mounting onboard equipment such as electronic equipment, it effectively prevents the impact environment level at the time of deployment from deviating from the impact resistance guaranteed value of the onboard equipment, in the late stage of spacecraft development, By pulling the deployment structure holding bracket, it is possible to more reliably suppress the increase in the mass of the spacecraft and the increase in cost due to additional construction compared to the current technology.

(First embodiment)
Next, 1st Embodiment of the expansion | deployment structure holding | maintenance bracket based on this invention is described using FIG. FIG. 1 is a schematic diagram showing an example of a deployment structure holding bracket for a spacecraft according to the present invention, showing an example of a structure of a deployment structure holding bracket for fixing the deployment structure in a folded state. Yes. 1A shows a plan view of the deployment structure holding bracket, FIG. 1B shows a side view of the deployment structure holding bracket, and FIG. 1C shows FIG. 1A. The cross-section of the unfolded structure holding bracket of FIG.

  In FIG. 1, a developed structure holding bracket 1 (hereinafter abbreviated as holding bracket 1) has a rectangular parallelepiped box-like structure as in FIG. 6, and has a predetermined thickness d. It is made up of. For example, an aluminum alloy is used as the metal plate. The holding bracket 1 has a mechanism for holding the expanded structure in a folded state on a rectangular-shaped holding / separating plate 10 and separating the expanded structure from the holding / separating plate 10 at the time of expansion. Here, at each end of the holding / separating plate 10, as in the case of FIG. 6, the legs 2 bent at right angles are connected. A mounting plate 4 is bent and extended at the ends of the left and right legs 2 in FIG. 1 of each leg 2 in order to be fixed to the spacecraft body 5. Attachment parts 4a, 4b, 4c, and 4d are provided, and each of the attachment parts 4a, 4b, 4c, and 4d is integrated with the spacecraft body 5 by bolts, nuts, and adhesives.

  Here, as shown in the cross-sectional view of FIG. 1C, the holding bracket 1 shown in FIG. 1 is different from the holding bracket 1E shown in FIG. Instead, it has a lattice-like bent structure. That is, a thick metal plate having a thickness greater than the required thickness d is prepared as the holding separation plate 10, and the thickness is held alternately by a rectangular opening having a predetermined diameter from the front and back of the metal plate. The separation plate 10 is drilled to a position that reaches a predetermined thickness d, and rectangular cavities (grooves) are alternately formed on the front and back of the metal plate, thereby realizing the holding separation plate 10 having a lattice-like bent structure. is doing.

  In other words, as shown in the cross-sectional view of FIG. 1C, the holding bracket 1 has a flat plate-shaped front surface side member 12 and a rear surface side member 13 that are alternately positioned in parallel with each other on the front surface side. The end surfaces of the front surface side member 12 and the back surface side member 13 are connected to each other through a flat plate side surface side member 11 arranged in a direction perpendicular to the member 12 and the back surface side member 13. By adopting such a shape, the holding bracket 1 forms a rectangular box having a rectangular opening as the front surface side cavity portion 14 and the back surface side cavity portion 15, and the opening side and bottom surface side of the formed rectangular box are formed. A bent-shaped structure alternately arranged on the front and back of the holding separation plate 10, that is, a lattice-like bent structure having openings alternately on the front and back of the holding bracket 1.

  It is necessary as the holding separation plate 10 instead of forming the holding separation plate 10 having a lattice-like bent structure by punching a thick metal plate having a thickness larger than the thickness d required as the holding separation plate 10. The holding separation plate 10 having a lattice-like bending structure may be formed by alternately bending a single flat plate-like metal plate having a thickness d as shown in FIG. C), the side member 11, the front member 12, and the rear member 13 are prepared as separate members, and the end surfaces of the front member 12 and the rear member 13 arranged alternately in parallel are the front member 12 and the rear member. By forming a shape joined to the upper and lower end faces of the side member 11 arranged at right angles to the side member 13, a front and back alternately, a lattice shape having a rectangular hole-shaped front side cavity 14 and back side cavity 15 Holding part of the bending structure It is also possible to form the plate 10.

  When the spacecraft is launched, the unfolded expanded structure is held and fixed on the holding separation plate 10 of the holding bracket 1 shown in the side view of FIG. . For this reason, although not shown, a mechanism (for example, a fastening member such as a fastening bolt / nut for holding and fixing the expanded structure in a folded state) can be attached to the substantially central portion of the holding bracket 1 (for example, , A fastening bolt insertion hole).

  Further, as shown in the impact generation source 3 in FIG. 1, in the same manner as in FIG. 6, the outer space is located just below the center of the holding separation plate 10 of the holding bracket 1 (that is, on the spacecraft body 5 side). It is equipped with gunpowder etc. for releasing the fixing function of fixing members such as fastening bolts and nuts when it arrives. When reaching space, by exploding explosives mounted almost directly below the central part of the holding separation plate 10 of the holding bracket 1 by remote control and operating pyrotechnics such as bolt cutters and separation nuts, The unfolded structure fixed and held on the holding separation plate 10 of the holding bracket 1 is released from the folded state toward the outer space in FIG.

  As shown in the impact propagation paths 50a, 50b, 50c, and 50d in FIG. 1A, the impact from the impact generating source 3 when the unfolded structure is released from the retaining / separating plate 10 of the retaining bracket 1 is as follows. The holding bracket 1 reaches the attachment parts 4a, 4b, 4c and 4d where the holding bracket 1 is attached to the spacecraft body 5 and propagates to the spacecraft body 5 side.

  Here, as shown in FIG. 1C, the holding separation plate 10 of the holding bracket 1 has a lattice-like structure in which the front surface side members 12 and the back surface side members 13 are alternately joined by the side surface side members 11. Therefore, as shown in FIG. 1 (C), the impact from the impact generating source 3 is caused by the side surface member 11, the back surface side member 13, the side surface side member 11, the surface from the vicinity of the substantially central portion of the holding / separating plate 10. The side members 12, the side members 11,... Move in a staggered manner to the attachment sites 4a, 4b, 4c, 4d while being bent at right angles. Therefore, the length of the impact propagation paths 50a, 50b, 50c, and 50d can be secured sufficiently longer than in the case of FIG. 6, and the impact environment level at the attachment sites 4a, 4b, 4c, and 4d is greater than in the case of FIG. Can also be greatly reduced. Further, since the mass on the impact propagation paths 50a, 50b, 50c, and 50d can be increased as compared with the case of FIG. 6, the impact environment level at the attachment sites 4a, 4b, 4c, and 4d can be more reliably reduced. be able to.

(Second Embodiment)
Next, 2nd Embodiment of the expansion | deployment structure holding | maintenance bracket based on this invention is described using FIG. FIG. 2 is a schematic view showing another example of the deployment structure holding bracket of the spacecraft according to the present invention, and FIG. 1 shows the deployment structure holding bracket for fixing the deployment structure in a folded state. Different structural examples are shown. 2A shows a plan view of the deployment structure holding bracket, FIG. 2B shows a side view of the deployment structure holding bracket, and FIG. 2C shows FIG. 2A. The cross-section of the unfolded structure holding bracket of FIG.

  In FIG. 2, the unfolded structure holding bracket 1A (hereinafter abbreviated as holding bracket 1A) has a rectangular parallelepiped box-like structure as in FIGS. 1 and 6, and has a predetermined thickness d. It is made of a metal material having The holding bracket 1A holds the expanded structure in a folded state, and at each end of the rectangular holding separation plate 10 for separating the expanded structure when expanded, is the same as in the case of FIGS. The leg 2 bent at a right angle is formed. A mounting plate 4 is bent and extended at the ends of the left and right leg portions 2 of each leg portion 2 so as to be fixed to the spacecraft body 5, and four mounting portions 4 a are provided on the mounting plate 4. , 4b, 4c, and 4d, and are integrated with the spacecraft body 5 by bolts, nuts, and adhesives at the attachment portions 4a, 4b, 4c, and 4d, respectively.

  Here, the holding bracket 1A shown in FIG. 2 is different from the holding bracket 1E shown in FIG. 6 as shown in the sectional view of FIG. It is not a flat plate with a uniform thickness, but a lattice-like bent structure. However, unlike the rectangular cavity in the case of FIG. 1, the holding separation plate 10A has a lattice-like bent structure having a circular cavity. That is, a thick metal plate having a thickness larger than the required thickness d is prepared as the holding separation plate 10A, and the thickness is held alternately by circular openings with a predetermined diameter from the front and back of the metal plate. The separation plate 10A is drilled to a position that reaches a predetermined thickness d, and circular cavities (grooves) are alternately formed on the front and back of the metal plate, thereby realizing a holding separation plate 10A having a lattice-like bent structure. is doing.

  That is, as shown in the sectional view of FIG. 2C, the holding bracket 1 </ b> A has a flat plate-shaped front surface side member 12 and a rear surface side member 13 that are alternately disposed in parallel with each other on the front surface side. The end surfaces of the front surface side member 12 and the back surface side member 13 are connected to each other through a cylindrical side surface side member 11A disposed in a direction perpendicular to the member 12 and the back surface side member 13. With this shape, the holding bracket 1A forms a round box having a circular opening as the front side cavity 14A and the back side cavity 15A, and the opening side and bottom side of the formed round box are formed. A bent-shaped structure alternately arranged on the front and back of the holding separation plate 10A, that is, a lattice-shaped bent structure having openings alternately on the front and back of the holding bracket 1 is provided.

  Thus, the holding bracket shown in FIG. 1 as the first embodiment is realized by realizing a holding bracket 1A having a bent structure in which round boxes having circular openings are alternately arranged as a lattice-like structure. Compared to 1, the side-side member 11A is slightly increased in thickness, but the processing for drilling the front-side cavity 14A and the back-side cavity 15A is simplified, so the cost is reduced. Can be achieved.

  Instead of forming the holding separation plate 10A having a lattice-like bent structure by perforating a thick metal plate having a thickness larger than the thickness d required for the holding separation plate 10A, both surfaces are semicylindrical. The side surface member 11A, the plate-shaped surface side member 12 of the wall thickness d, and the back surface side member 13 are prepared as separate members, and the end surfaces of the front surface side member 12 and the back surface side member 13 alternately arranged in parallel are By joining the upper and lower end faces of the side member 11 arranged at right angles to the front side member 12 and the back side member 13 and forming a shape in which the semi-cylindrical side members 11A are joined together, the front and back sides are alternated. In addition, it is possible to form a holding separation plate 10A having a lattice-like bent structure having a circular hole-shaped front surface side cavity portion 14A and a back surface side cavity portion 15A.

(Other embodiments)
Next, other embodiments of the unfolded structure holding bracket according to the present invention will be described with reference to FIGS. First, another embodiment shown in FIG. 3 will be described. FIG. 3 is a schematic view showing still another example of the deployment structure holding bracket of the spacecraft according to the present invention, and is a cross-sectional view of FIGS. 1C and 2C in the first and second embodiments. As in the case of the figure, the cross-sectional structure of the holding separation plate 10B is shown. 3 shows a modified example of the holding bracket 1 having the rectangular opening in FIG. 1 for the sake of simplicity of explanation, the holding bracket 1A having the circular opening in FIG. It goes without saying that the same applies to cases.

  As shown in FIG. 3, a holding separation plate 10B forming a holding bracket having a lattice-like bending structure is different from the holding separation plate 10 in the case of FIG. The structure is not inclined at right angles to the member 13 but inclined at a predetermined inclination angle α as an inclination angle at which a strength capable of fixing and holding the developed structure is obtained. Along with this, the cavity portion also forms an inclined cavity portion with the front surface side cavity portion 14B and the back surface side cavity portion 15B.

  In the holding / separating plate 10B shown in FIG. 3, all the side members 11B are inclined in the same direction at an inclination angle α, but the adjacent side members 11B are alternately inclined. The structure may be configured so as to be inclined obliquely in the opposite direction at an angle α so that the opening areas of the opening portions of the front surface side cavity portion 14B and the back surface side cavity portion 15B are narrowed.

  As described above, by making the side surface member 11B obliquely inclined, the length of the side surface member 11B can be compared with that of the side surface member 11 in FIG. 1 even in a limited space such as a spacecraft. Thus, the length of the impact propagation path 50a, 50b, 50c, 50d from the impact generation source 3 to the attachment site 4a, 4b, 4c, 4d can be secured longer. Thus, the impact environment level at the attachment portions 4a, 4b, 4c, 4d can be further reduced as compared with the case of FIG. In addition, the side surface members 11B adjacent to each other are inclined in opposite directions to narrow the opening area of the opening of each cavity, thereby ensuring a longer impact propagation path and holding and separating plate 10B. It is also possible to improve the mechanical strength.

  Next, another embodiment shown in FIG. 4 will be described. FIG. 4 is a schematic diagram showing still another example of the spacecraft deployment structure holding bracket according to the present invention, and shows the cross-sectional structure of the holding separation plate 10C as in the case of FIG. 4 shows a modified example of the holding bracket 1 having the rectangular opening in FIG. 1 as in the case of FIG. 3, for the sake of simplicity, the circular opening in FIG. Needless to say, the same holds for the holding bracket 1A having a portion. Further, the present invention can be similarly applied to a holding bracket having a tilted structure as shown in FIG.

  In the holding / separating plate 10 </ b> C shown in FIG. 4, the side surface member 11 </ b> C forming the holding / separating plate 10 </ b> C is configured to have a buffer member 16 that reduces the propagation of impact force. Here, the buffer member 16 is made of, for example, one or both of a rubber cushion and an elastic body such as a leaf spring. In some cases, the side member 11 </ b> C may be formed of only the buffer member 16.

  As described above, the side surface member 11C has a structure having the buffer member 16, so that it reaches the attachment sites 4a, 4b, 4c, and 4d from the impact generating source 3 as compared with the structure of the holding bracket 1 of FIG. It is possible to further reduce the impact force at the time of performing, and it is possible to further reduce the impact environment level at the attachment portions 4a, 4b, 4c, and 4d.

  Next, another embodiment shown in FIG. 5 will be described. FIG. 5 is a schematic view showing still another example of the spacecraft expansion structure holding bracket according to the present invention, and shows a cross-sectional structure of the holding separation plate 10D as in the case of FIG. 5 shows a modified example of the holding bracket 1 having the rectangular opening in FIG. 1 as in the case of FIGS. 3 and 4 for the sake of simplicity. It goes without saying that the same holds true for the holding bracket 1A having a shaped opening. Moreover, even in the case of the structure of the holding bracket as shown in FIGS.

  In the holding / separating plate 10D shown in FIG. 5, the surface-side cavity is further formed from the respective end surfaces of the surface-side member 12 and the back-side member 13 that form the holding / separating plate 10D with respect to the holding / separating plate 10 shown in FIG. 14. In a state of extending to the opening side of the back side cavity 15, the front side flange 12 a as the front side reinforcing plate and the back side flange 13 a as the back side reinforcing plate are provided. The opening area of each opening of the back side cavity 15 is made smaller than the cross-sectional area of the inside cavity.

  As described above, the mechanical strength in the vicinity of the opening is greatly increased by adopting the structure including the front surface side cavity portion 14, the front surface flange portion 12 a extending to the opening side of the back surface side cavity portion 15, and the back surface flange portion 13 a. Can be enhanced.

The configuration of the preferred embodiment of the present invention has been described above. However, it should be noted that such examples are merely illustrative of the invention and do not limit the invention in any way. Those skilled in the art will readily understand that various modifications and changes can be made according to a specific application without departing from the gist of the present invention. For example, the embodiment of the present invention can be expressed as the following configuration in addition to the configuration (1) in the means for solving the problems.
(2) After the unfolded structure used in the unfolded state is fixed and held in a state where it is folded to the spacecraft body side, the unfolded structure in the folded state is obtained by operating a pyrotechnic that becomes an impact generation source. A deployment structure holding bracket that separates for deployment, a flat plate-shaped surface side member that fixes and holds the deployment structure, a flat plate-shaped back surface side member that is attached to the spacecraft body side, and the surface side A cylindrical side surface member that connects the member and the back surface side member, the front surface side member and the back surface side member are alternately arranged in parallel, and are perpendicular to the front surface side member and the back surface side member. By connecting the end surfaces of the front surface side member and the back surface side member by the side surface side member arranged in a grid shape, a circular box having circular openings alternately formed on the front surface side and the back surface side is formed. Construction Deployment structure retention bracket to.
(3) Instead of arranging the side surface member at right angles to the front surface side member and the back surface side member, the side surface member is arranged in a state inclined at a predetermined inclination angle, and the surface side member is formed by the side surface member. And (1) or (2), the unfolded structure holding bracket connecting the end surfaces of the rear surface side member and the rear surface side member.
(4) The side structure member arranged in an inclined state is inclined in the same direction, or the side surface members adjacent to each other are alternately inclined in the opposite direction. bracket.
(5) The expanded structure holding bracket according to any one of (1) to (4), wherein a part or all of the side surface side member is formed as a structure having a buffer member that reduces a propagating impact force.
(6) The unfolded structure holding bracket according to (5), wherein the buffer member is formed of one or both of a cushion and a leaf spring.
(7) The above-mentioned (1) to (6), wherein a front flange portion and a rear flange portion are provided to extend from the end surfaces of the front surface side member and the back surface side member toward the respective openings. One of the expanded structure retention brackets.
(8) Any of the above (1) to (7), wherein the impact generation source is disposed on the back surface side of the deployment structure holding bracket and in the center of the deployment structure holding bracket. Expanded structure retention bracket.

1 Holding bracket (deployment structure holding bracket)
1A Holding bracket (deployment structure holding bracket)
1E Holding bracket (deployment structure holding bracket)
2 Leg 3 Shock source 4 Mounting plate 5 Spacecraft body 4a Mounting site 4b Mounting site 4c Mounting site 4d Mounting site 10 Holding separation plate 10A Holding separation plate 10B Holding separation plate 10C Holding separation plate 10D Holding separation plate 10E Holding separation Plate 11 Side member 11A Side member 12 Front member 12a Front flange 13 Back member 13a Back flange 14 Front side cavity 14A Front side cavity 14B Front side cavity 15 Back side cavity 15A Back side cavity 15B Back side cavity 16 Buffer member 20 Release side 30 Holding side 40 Separation surface 50a Impact propagation path 50b Impact propagation path 50c Impact propagation path 50d Shock propagation path

Claims (8)

  To deploy the unfolded structure in a folded state by operating a pyrotechnic that is a source of impact after the unfolded structure used in the unfolded state is fixed and held in the state of the spacecraft body. A development structure holding bracket that is separated into a flat plate-shaped surface side member for fixing and holding the development structure, a flat plate-shaped rear surface side member for attachment to the spacecraft body side, the front surface side member, and the A flat plate-shaped side surface member connecting the back surface side member, the front surface side member and the back surface side member are alternately arranged in parallel, and are disposed at right angles to the front surface side member and the back surface side member. By connecting the end surfaces of the front surface side member and the back surface side member by the side surface side member, a lattice-like structure is formed in which square boxes having rectangular openings alternately on the front surface side and the back surface side are formed. Expand structure holding bracket, wherein the door.   To deploy the unfolded structure in a folded state by operating a pyrotechnic that is a source of impact after the unfolded structure used in the unfolded state is fixed and held in the state of the spacecraft body. A development structure holding bracket that is separated into a flat plate-shaped surface side member for fixing and holding the development structure, a flat plate-shaped rear surface side member for attachment to the spacecraft body side, the front surface side member, and the A cylindrical side surface member connected to the back surface side member, the front surface side member and the back surface side member are alternately arranged in parallel, and are disposed at right angles to the front surface side member and the back surface side member. By connecting the end surfaces of the front surface side member and the back surface side member by the side surface side member, a lattice-like structure is formed in which round boxes having circular openings alternately on the front surface side and the back surface side are formed. Expand structure holding bracket, wherein the door.   Instead of arranging the side member at a right angle to the front member and the rear member, the side member is arranged obliquely by a predetermined inclination angle, and the front member and the rear member are inclined by the side member. The deployment structure holding bracket according to claim 1, wherein an end surface of the side member is connected to the side structure.   4. The development according to claim 3, wherein the side surface members arranged in an inclined state are inclined in the same direction, or the side surface members adjacent to each other are alternately inclined in opposite directions. Structure retention bracket.   The deployment structure holding bracket according to any one of claims 1 to 4, wherein a part or all of the side surface side member is formed as a structure having a buffer member that reduces a propagating impact force.   6. The unfolded structure holding bracket according to claim 5, wherein the buffer member is composed of one or both of a cushion and a leaf spring.   7. The front flange portion and the rear flange portion are provided so as to extend from the end faces of the front surface side member and the rear surface side member toward the respective opening portions, respectively. The expansion structure holding bracket according to any one of the above.   The said impact generation source is the said back surface side member side of the said expansion | deployment structure holding bracket, Comprising: It arrange | positions in the center of the said expansion | deployment structure holding bracket. Expanded structure holding bracket.

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