JP2019189090A - Damping support structure - Google Patents

Abstract

To provide a damping support structure which can secure stable damping performance even if a panel, on which devices are mounted, is connected to a structure having a cryogenic temperature.SOLUTION: A damping support structure 1 includes: a panel 10 on which devices are mounted; a first mesh spring 14A provided at a device mounting side 10a of the panel 10; a second mesh spring 14B which is provided at an installation surface 12a side opposite to the device mounting side 10a of the panel 10 and sandwiches the panel 10 with the first mesh spring 14A; a heat insulation member 16 provided between the first mesh spring 14A and the panel 10; a pressed member 20 provided at a side of the first mesh spring 14A which is opposite to a heat insulation member 16 side; and a pressing member 22a which presses the pressed member 20 to an installation surface 12a side to press the first mesh spring 14A, the second mesh spring 14B, the panel 10, and the heat insulation member 16 to the installation surface 12a side.SELECTED DRAWING: Figure 5

Description

  The present invention relates to a damping support structure.

  Electronic devices used for rocket control and the like are mounted on the rocket while being mounted on a device mounting panel connected to the rocket structure.

  For electronic devices mounted on the panel, vibrations generated during fuel injection may propagate from the structure through the panel. For this reason, it is necessary to suppress the vibration of the panel to such an extent that the electronic device does not break down.

  As an invention related to vibration control of equipment mounted on a rocket, for example, there is an invention disclosed in Patent Document 1. According to the present invention, a panel on which a device is mounted is obtained by adhering a vibration damping device including a vibration detection unit that detects vibration and a vibration unit that cancels vibration to the surface of the panel on which vibration is generated. It is possible to cancel the vibration generated in

JP 2002-321700 A

  However, in the invention disclosed in Patent Document 1, if the controller that controls the vibration means fails, the desired vibration damping function is lost, and the failure of the mounted equipment is prevented. It may not be possible.

  In addition, as another example of vibration control of equipment mounted on the rocket, the panel on which the equipment is mounted is connected to the structure via vibration-proof rubber, rather than canceling out vibrations propagating from the outside by vibration control means. By doing so, there is also a method of suppressing vibrations propagating from the structure to the panel.

  However, in the method using the anti-vibration rubber, the damping performance may vary greatly due to individual differences caused by the production lot of the anti-vibration rubber used, and it is difficult to manage the rigidity of the anti-vibration rubber. In addition, when the structure is in a very low temperature state, the anti-vibration rubber may be cured by the cold heat conducted from the structure, and the desired damping performance may not be exhibited.

  The present invention has been made in view of such circumstances, and provides a damping support structure capable of ensuring stable damping performance even when a panel for mounting a device is connected to a cryogenic structure. For the purpose.

In order to solve the above problems, the damping support structure of the present invention employs the following means.
That is, the damping support structure according to one aspect of the present invention includes a panel on which a device is mounted, a first mesh spring provided on the device mounting side of the panel, and an installation on the opposite side of the panel from the device mounting side. A second mesh spring provided on the surface side and sandwiching the panel together with the first mesh spring; a heat insulating member provided between the first mesh spring and the panel; and the heat insulating member of the first mesh spring. A pressed member provided on the side opposite to the side, and pressing the pressed member toward the installation surface, thereby allowing the first mesh spring, the second mesh spring, the panel, and the heat insulating member to be A pressing member that presses toward the installation surface.

The pressing member of the damping support structure according to this aspect presses the pressed member toward the installation surface, thereby pressing the first mesh spring, the second mesh spring, and the panel toward the installation surface. Thereby, the panel clamped by a 1st mesh spring and a 2nd mesh spring can be elastically supported by giving the displacement of a compression direction to the 1st mesh spring and 2nd mesh spring which clamp a panel. At this time, for example, even when the installation surface connected to the structure of the rocket becomes extremely low temperature and the cold heat is transmitted to the mesh spring, the panel can be elastically supported while maintaining stable damping performance. . This is due to the characteristic of the mesh spring that can exhibit stable rigidity even in a cryogenic state. Accordingly, for example, when the electronic device is mounted on the panel, the electronic device can be protected from vibration. If anti-vibration rubber is used instead of the mesh spring, the desired damping performance may not be exhibited in an extremely low temperature state.
In addition, since a heat insulating member is provided between the first mesh spring and the panel, the conduction of cold heat to the panel can be suppressed even if the first mesh spring itself becomes a low temperature. Accordingly, for example, even when an electronic device is mounted on the panel, it is possible to suppress cold heat from being transmitted to the electronic device through the panel, so that the performance of the electronic device is not impaired by the cold heat. In addition, since the mesh spring has a large number of cavities inside, the heat insulation performance can be ensured to some extent as compared with, for example, a case where a vibration-proof rubber is used instead of the mesh spring. As the heat insulating member, for example, a resin such as GFRP is used.
Furthermore, for example, when vibration-proof rubber is used in place of the mesh spring and the damping support structure is used in a vacuum environment (for example, outer space), the surrounding structure is contaminated by outgas generated from the vibration-proof rubber. There is a possibility that. However, outgassing can be prevented by using a mesh spring.

  In the damping support structure according to an aspect of the present invention, the pressing member is a bolt, and one end of the bolt is the pressed member, the first mesh spring, the heat insulating member, the panel, and the first A 2 mesh spring is passed through and fastened to the installation surface side.

  According to the damping support structure according to this aspect, the pressing member is a bolt. The pressed member, the first mesh spring, the heat insulating member, the panel, and the second mesh spring can be integrated with the installation surface by the bolt. At this time, the head of the bolt can be a pressing member that presses the pressed member toward the installation surface.

  The damping support structure according to an aspect of the present invention includes a bush that regulates a distance between the pressed member and the installation surface.

  According to the damping support structure according to this aspect, the amount by which the pressed member is pushed into the installation surface side, that is, the compression amount of the first mesh spring and the second mesh spring pushed by the pressed member is regulated by the height of the bush. it can. The first mesh spring and the second mesh spring elastically support the panel by sandwiching the panel in a compressed state, but by controlling the amount of compression by the height of the bush, easy assembly is achieved. realizable. This is due to the characteristics of the mesh spring with little individual difference in damping performance. For example, when vibration-proof rubber with individual differences in damping performance is used instead of mesh springs, in order to obtain the desired damping performance, data on damping performance is obtained for each vibration-proof rubber to be used, and accordingly Since it is necessary to determine the amount of compression, it is difficult to manage the rigidity with the same size bush.

  In the damping support structure according to one aspect of the present invention, the panel is not in contact with the bush.

  According to the damping support structure according to this aspect, since the panel and the bush are not in contact with each other, for example, even when the installation surface connected to the structure of the rocket becomes extremely low temperature and the cold heat is conducted to the bush, The conduction of cold heat from the bush to the panel can be prevented. For example, when the bush is provided so as to penetrate the panel, the inner dimension of the through hole for the bush formed in the panel may be designed to be larger than the outer dimension of the bush.

  In the damping support structure according to one aspect of the present invention, the pressed member is a heat insulating material.

  According to the damping support structure according to this aspect, since the pressed member is a heat insulating material, for example, even when the installation surface connected to the structure of the rocket becomes extremely low temperature and the cold heat is conducted to the pressing member, The conduction of cold heat from the pressing member through the pressed member can be prevented. For example, a resin such as GFRP is used as the heat insulating material.

  In the damping support structure according to one aspect of the present invention, another heat insulating member is provided between the second mesh spring and the panel.

  According to the damping support structure according to this aspect, since the heat insulating member is provided between the second mesh spring and the panel, conduction of cold heat to the panel is suppressed even when the second mesh spring itself becomes low temperature. it can. Accordingly, for example, even when an electronic device is mounted on the panel, it is possible to suppress cold heat from being transmitted to the electronic device through the panel. For example, a resin such as GFRP is used as the heat insulating material.

  In the damping support structure according to one aspect of the present invention, the installation surface is connected to a rocket structure.

  According to the damping support structure of the present invention, stable damping performance can be ensured even when a panel on which equipment is mounted is connected to a cryogenic structure.

1 is a perspective view of a thrust cone to which a damping support structure according to an embodiment of the present invention is applied. It is the figure which showed the rocket provided with the thrust cone of FIG. It is a top view of the panel with which the attenuation | damping support structure which concerns on one Embodiment of invention is provided. It is a longitudinal cross-sectional view in the cutting line II of FIG. It is a longitudinal cross-sectional view of the attenuation | damping support structure which concerns on one Embodiment of this invention. It is a longitudinal cross-sectional view of the state which is not pressed of the attenuation | damping support structure which concerns on one Embodiment of this invention. It is the figure which showed the relationship between the displacement of a mesh spring, and a load. It is the figure which showed the relationship between the displacement of a vibration-proof rubber, and a load. It is a longitudinal cross-sectional view of the modification of the attenuation | damping support structure which concerns on one Embodiment of this invention. It is a longitudinal cross-sectional view of the other modification of the attenuation | damping support structure which concerns on one Embodiment of this invention.

  The damping support structure according to one embodiment of the present invention will be described below.

  As shown in FIG. 1, when the damping support structure 1 connects the panel 10 on which the electronic device 58 is mounted to the outer surface of an umbrella-like structure 56 (hereinafter referred to as “thrust cone 56”). It is a mechanism used for.

  As shown in FIG. 2, the thrust cone 56 is one of the elements constituting the rocket 50, and is connected to an oxidant tank 54 that stores an oxidant used in the second stage engine 52. In FIG. 2, an oxidant tank 54, a thrust cone 56, and a second stage engine 52 are arranged in order from the top.

  The thrust cone 56 is arranged so that an umbrella-shaped tip is located below the tip shown in FIG. 2, and the portion opposite to the tip (inner surface side) is the bottom of the oxidant tank 54 shown in FIG. 2. It is connected to the convex part on the side. As the oxidant stored in the oxidant tank 54, for example, liquid oxygen is used. Since the temperature of the liquid oxygen is an extremely low temperature of about 90K, the oxidant tank 54 and the thrust cone 56 connected to the oxidant tank 54 are also an extremely low temperature. The electronic device 58 provided on the outer surface side of the thrust cone 56 shown in FIG. 1 is covered with a heat insulating material (not shown) (for example, a sheet-like multilayer heat insulating material), and the second stage engine shown in FIG. It is insulated from the space on the 52 side.

  The thrust cone 56 is the same as the thrust cone 56 of FIG. 2 with the tip positioned upward in FIG. 1 but the tip positioned downward.

  As shown in FIG. 3, the panel 10 on which the electronic device 58 shown in FIG. 1 is mounted is a plate-like member that becomes a trapezoid when viewed in plan. The material of the panel 10 is, for example, an aluminum metal.

  As shown in FIG. 4, the panel 10 is connected to the thrust cone 56 via, for example, a stringer 12 whose cross section is Z-shaped and the damping support structure 1. The material of the stringer 12 is, for example, an aluminum-based metal, and is a long member extending in the direction perpendicular to the paper surface of FIG. On the device mounting side 10a (the upper side shown in FIG. 4) of the panel 10, an electronic device 58 used for controlling the rocket 50 is mounted.

Hereinafter, details of the damping support structure 1 will be described.
FIG. 5 shows an enlarged view of the vicinity of the damping support structure 1. The device mounting side 10a of the panel 10 has counterbore portions 11 which are round holes having a certain depth (for example, a depth of half or more of the thickness of the panel 10) at the four corners (see FIG. 3). Is formed. In the spot facing portion 11, a cylindrical first mesh spring 14 </ b> A having an axial direction in the vertical direction shown in FIG. 5 is provided. At this time, an annular heat insulating member 16 is provided between the bottom surface of the spot facing portion 11 and the first mesh spring 14A. The heat insulating member 16 is a washer formed of a resin such as GFRP (Glass Fiber Reinforced Plastics). It should be noted that dimples and gaps may be formed on the surface of the heat insulating member 16 in order to reduce the contact area.

  A second mesh spring 14B is provided on the opposite side of the spot facing portion 11 formed on the panel 10 so as to sandwich the panel 10 together with the first mesh spring 14A. Similarly to the first mesh spring 14A, the second mesh spring 14B has a cylindrical shape with the vertical direction shown in FIG. 5 as the axial direction. The second mesh spring 14 </ b> B is located on the installation surface 12 a formed on the Z-shaped stringer 12 connected to the thrust cone 56 on the side opposite to the device mounting side 10 a of the panel 10.

  The first mesh spring 14A and the second mesh spring 14B are formed, for example, into a cylindrical shape after knitting a stainless steel wire into a mesh shape. The first mesh spring 14A and the second mesh spring 14B have elasticity and do not depend on the temperature state of the use environment or individual differences. Demonstrate stable rigidity and damping performance.

  The damping support structure 1 is provided with a cylindrical bush 18 that penetrates the first mesh spring 14A, the heat insulating member 16, the counterbore 11 formed on the panel 10 and the second mesh spring 14B in the axial direction. Yes. The lower end of the bush 18 shown in FIG. 5 is in contact with the installation surface 12 a formed on the stringer 12. Further, a space 19 is formed in the radial direction between the bush 18 and the panel 10 so that the bush 18 and the panel 10 are not in contact with each other. That is, the outer diameter of the bush 18 is designed to be smaller than the inner diameter of the hole formed in the panel 10 through which the bush 18 passes. The material of the bush 18 is, for example, an aluminum metal.

  An annular pressed member 20 is provided on the opposite side of the first mesh spring 14 </ b> A from the heat insulating member 16. The first mesh spring 14 </ b> A and the upper end surface of the bush 18 are in contact with the lower surface of the pressed member 20. The pressed member 20 may be formed of, for example, a resin such as GFRP having heat insulation.

  The damping support structure 1 is provided with a bolt 22 penetrating in the axial direction with respect to the pressed member 20, the cylindrical bush 18, and the installation surface 12a. That is, the shaft portion 22b of the bolt 22 penetrates the pressed member 20, the bush 18, and the installation surface 12a, and the end 22c is located below the installation surface 12a. The bolt 22 includes a head portion 22a in addition to the shaft portion 22b. The head (pressing member) 22a included in the bolt 22 presses the pressed member 20 toward the installation surface 12a on its lower surface.

  The pressed member 20 pressed to the installation surface 12a side by the head (pressing member) 22a presses the first mesh spring 14A, the heat insulating member 16, the panel 10, and the second mesh spring 14B to the installation surface 12a side. Yes. At this time, the distance between the pressed member 20 and the installation surface 12a is regulated by the height of the bush 18 (the length in the axial direction). The end 22c of the bolt 22 penetrates the installation surface 12a, protrudes below the installation surface 12a shown in FIG. In addition, it is good also as a structure integrated so that the head (pressing member) 22a may serve as the function of the pressed member 20. The material of the bolt 22 and the nut 24 is, for example, an iron-based metal.

  In FIG. 5, the components provided in the damping support structure are united by a bolt 22 having a head portion 22a formed on the upper side and a lower nut 24, but the head portion 22a is formed on the lower side by inverting the top and bottom. Each component may be integrated with the bolt 22 and the upper nut 24, or each component may be integrated with the nut 24 and the shaft portion 22 b provided above and below, and the installation surface 12 a also functions as the nut 24. It is good also as a composition.

  As shown in FIG. 6, the first mesh spring 14A and the second mesh spring 14B are dimensioned in the axial direction when the first mesh spring 14A and the second mesh spring 14B are not pressed by the pressed member 20. It becomes a state larger than the dimension of the axial direction of the spring 14A and the 2nd mesh spring 14B. However, as described above, since the first mesh spring 14A and the second mesh spring 14B have elasticity, the first mesh spring 14A and the second mesh spring 14B are pressed and compressed by the head (pressing member) 22a toward the installation surface 12a. The

  The panel 10 sandwiched between the first mesh spring 14A and the second mesh spring 14B is elastically supported by the compressed first mesh spring 14A and second mesh spring 14B.

The present embodiment has the following effects.
By pressing the pressed member 20 toward the installation surface 12a, the first mesh spring 14A, the second mesh spring 14B, and the panel 10 are pushed into the installation surface 12a. Accordingly, the first mesh spring 14A and the second mesh spring 14B that sandwich the panel 10 are given displacement in the compression direction, so that the panel 10 sandwiched between the first mesh spring 14A and the second mesh spring 14B is elastically elastic. Can be supported. At this time, even when the installation surface 12a of the stringer 12 connected to the cryogenic thrust cone 56 becomes extremely cold and the cold heat is conducted to the first mesh spring 14A and the second mesh spring 14B, stable damping performance is maintained. In this state, the panel 10 can be elastically supported. This is due to the characteristics of the mesh spring that exhibits stable rigidity regardless of the temperature state of the use environment. Thus, the electronic device 58 mounted on the panel 10 can be protected from vibration even in a cryogenic state. If anti-vibration rubber is used instead of the first mesh spring 14A and the second mesh spring 14B, the desired damping performance may not be exhibited in an extremely low temperature state. This is due to the fact that the anti-vibration rubber is cured by being exposed to a cryogenic state, and the desired damping performance may not be obtained.

  In addition, since the heat insulating member 16 is provided between the first mesh spring 14A and the panel 10, the conduction of cold heat to the panel 10 can be suppressed even if the first mesh spring 14A itself becomes low temperature. Accordingly, it is possible to suppress conduction of cold heat to the electronic device 58 through the panel 10, so that the performance of the electronic device 58 is not impaired by the cold heat. Since the first mesh spring 14A and the second mesh spring 14B have a large number of cavities therein, for example, as compared with the case where vibration-proof rubber is used instead of the first mesh spring 14A and the second mesh spring 14B. Thus, the heat insulation performance can be secured to some extent.

  Further, for example, when vibration-proof rubber is used instead of the first mesh spring 14A and the second mesh spring 14B, outgas generated from the vibration-proof rubber in the vacuum environment (for example, outer space) It may adhere to the surface of the covering sheet-like multilayer heat insulating material and change the thermo-optical characteristics. However, outgassing can be prevented by using the first mesh spring 14A and the second mesh spring 14B.

  Further, the amount by which the pressed member 20 is pushed toward the installation surface 12 a, that is, the compression amount of the first mesh spring 14 </ b> A and the second mesh spring 14 </ b> B pushed by the pressed member 20 can be regulated by the height of the bush 18. By managing the compression amount of the first mesh spring 14A and the second mesh spring 14B according to the height of the bush 18, easy assembly can be realized. This is due to the characteristics of the first mesh spring 14A and the second mesh spring 14B with little individual difference in damping performance. FIG. 7A shows a change in load with respect to the displacement of the mesh spring. The three curves shown in the figure mean different displacement-load curves of mesh springs. As can be seen from the figure, the variation in the load due to the individual difference at the predetermined displacement X1 is ΔP1. On the other hand, as shown in FIG. 7B, the variation in the load due to the individual difference of the anti-vibration rubber is ΔP2, which is larger than ΔP1. Therefore, when vibration-proof rubber having individual differences in damping performance is used in place of the first mesh spring 14A and the second mesh spring 14B, the damping performance for each vibration-proof rubber to be used in order to obtain a desired damping performance. Therefore, it is difficult to manage the rigidity by the bush 18 having the same size.

  In addition, since the bush 18 and the panel 10 are configured to be in non-contact by the space 19 formed between the bush 18 and the panel 10, even when cold heat is conducted to the bush 18, The conduction of cold heat to the panel 10 can be prevented.

  Further, when the pressed member 20 is a heat insulating material, even if cold heat is conducted to the head portion 22a through the nut 24 and the shaft portion 22b, conduction of cold heat from the head portion 22a through the pressed member 20 is prevented. be able to.

  As a modification of the present embodiment, a second heat insulating member 17 may be provided between the second mesh spring 14B and the panel 10 as shown in FIG. The second heat insulating member 17 is an annular member like the heat insulating member 16, and is a washer formed of a resin such as GFRP, for example. Even if the second mesh spring 14 </ b> B itself becomes a low temperature by the second heat insulating member 17, the conduction of cold heat to the panel 10 can be suppressed.

  In the present embodiment, the stringer 12 having a cross section of Z shape (see FIG. 4) has been described. However, the cross section of the stringer is not limited to the Z shape. Instead, for example, as shown in FIG. 9, a stringer 12 ′ having a hat-like cross section may be adopted. Further, the shape of the nut 24 is not limited to that of the present embodiment, and any shape that can fix the bolt 22 may be used. For example, a plate nut 24 ′ may be used instead of the nut 24. good.

  The configurations of the above-described embodiments can be combined as much as possible. For example, a stringer 12 ′ having a hat-shaped cross section and a nut 24 may be combined, or a stringer 12 and a plate nut having a Z-shaped cross section. 24 'may be combined. Moreover, you may provide the 2nd heat insulation member 17 with respect to each combination.

DESCRIPTION OF SYMBOLS 1 Damping support structure 10 Panel 10a Equipment mounting surface 11 Counterbore part 12,12 'Stringer 12a Installation surface 14A 1st mesh spring 14B 2nd mesh spring 16 Heat insulation member 17 2nd heat insulation member 18 Bush 19 Space 20 Pressed member 22 Bolt 22a Head (pressing member)
22b Shaft portion 22c End portion 24 Nut 50 Rocket 52 Second stage engine 54 Oxidant tank 56 Thrust cone (structure)
58 Electronic equipment

Claims (7)

A panel on which the device is mounted;
A first mesh spring provided on the device mounting side of the panel;
A second mesh spring provided on the installation surface side of the panel opposite to the device mounting side and sandwiching the panel together with the first mesh spring;
A heat insulating member provided between the first mesh spring and the panel;
A pressed member provided on the side opposite to the heat insulating member side of the first mesh spring;
A pressing member that presses the first mesh spring, the second mesh spring, the panel, and the heat insulating member toward the installation surface by pressing the pressed member toward the installation surface;
A damping support structure comprising: The pressing member is a bolt,
2. The damping support according to claim 1, wherein one end of the bolt penetrates the pressed member, the first mesh spring, the heat insulating member, the panel, and the second mesh spring and is fastened to the installation surface side. Construction.   The attenuation | damping support structure of Claim 1 or 2 provided with the bush which regulates the distance between the said to-be-pressed member and the said installation surface.   The damping support structure according to claim 3, wherein the panel is not in contact with the bush.   The damping support structure according to claim 1, wherein the pressed member is a heat insulating material.   The damping support structure according to any one of claims 1 to 5, wherein another heat insulating member is provided between the second mesh spring and the panel.   The damping support structure according to any one of claims 1 to 6, wherein the installation surface is connected to a structure of a rocket.

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