JP6495200B2 - Support leg structure for space environment test equipment - Google Patents

Description

  The present invention relates to a support leg structure for a space environment test apparatus having a large vacuum chamber that can simulate a space environment.

  Space environment test equipment installs a heat absorption wall called shroud inside the vacuum chamber, cools the shroud with liquefied nitrogen, and evacuates the inside of the vacuum chamber with a vacuum pump. It is a device that simulates high vacuum and tests specimens such as artificial satellites. A large vacuum chamber capable of performing advanced tests associated with an increase in size and performance of an artificial satellite or the like needs to have a vibration isolation mechanism that minimizes vibrations transmitted from the outside.

As for the vibration-proof structure of a large vacuum chamber, it is generally known to use a bellows mechanism that can expand and contract in the axial direction. The bellows mechanism refers to pipes and joints that are provided with functions such as stretchability and bendability. The bellows mechanism used in space environment test equipment is a vacuum chamber that absorbs vibrations transmitted from the outside. It is applied as an anti-vibration measure.
For example, Patent Document 1 discloses a bellows mechanism that absorbs vibration transmission to a vacuum chamber by a bellows provided in a vacuum chamber (see FIG. 1 in Patent Document 1).

JP 2012-149676 A

  In the bellows mechanism 10 shown in FIG. 1 of Patent Document 1, the through portion 114 and the thin portion 115 disposed in the flange portion 102 that connects the vacuum chamber and the bellows 10 absorb vibration. However, such a structure has a problem that the strength of the flange 102 itself is not sufficient, and vibration and eccentricity cannot be sufficiently absorbed. Furthermore, in the flange part 102 having the through part 114 and the thin part 115, the structure is complicated, and it is difficult to remove the bellows 10. As a result, there is a problem that the maintainability is deteriorated.

  The present invention has been made to solve the above-described problem, and can achieve vibration absorption while dealing with eccentricity. Furthermore, the space environment has a simple structure and easy maintenance such as removal. An object of the present invention is to provide a support leg structure for a test apparatus.

(1) The support leg structure of the space environment test apparatus according to the present invention is installed in a vacuum chamber and supports an internal frame on which a specimen is placed.
A support leg that is erected on an installation surface and that supports the internal frame by penetrating a through part formed in a peripheral wall part of the vacuum chamber;
A cylindrical bellows through which the support leg is inserted and whose upper end is attached to the peripheral part of the penetrating part, and is extendable and contractible in the axial direction of the support leg;
A loose flange that is formed of an annular member, is attached to the lower end of the bellows, and forms an inward flange at the lower end of the bellows;
A fixing plate attached to the support leg so that a lower surface part abuts on an upper surface part of the loose flange;
A bellows receiving flange that is detachably attached to the lower surface side of the fixing plate and supports the bellows by sandwiching the loose flange in cooperation with the fixing plate. .

(2) Further, in the above (1), the bellows receiving flange is composed of a plurality of members divided in the circumferential direction, and the support leg portion is an intermediate leg that is detachable below the fixed plate. And a space in which the bellows can be extracted from the support leg by removing the intermediate leg.

  In the support leg structure of the space environment test apparatus according to the present invention, the lower end of the bellows is not fixed by a bolt or the like, but is fixed by being clamped by a fixing plate and a bellows receiving flange. Even when the portion and the bellows are eccentric, the bellows can be attached without being deformed forcefully, and strict alignment is not required when the bellows is attached.

It is explanatory drawing explaining the support leg structure of the space environment test apparatus which concerns on embodiment of this invention. It is a figure showing the whole space environment test device concerning the present invention. In the support leg structure which concerns on this Embodiment, it is a figure explaining the eccentricity of a support leg part and a bellows. It is explanatory drawing of the bellows receiving flange used for the support leg structure which concerns on this Embodiment. FIG. 6 is a diagram for explaining a bellows removal procedure in the support leg structure of the space environment test apparatus according to the present invention (part 1); (2) explaining the bellows removal procedure in the support leg structure of the space environment test apparatus according to the present invention. (3) for demonstrating the removal procedure of a bellows in the support leg structure of the space environment test apparatus which concerns on this invention. FIG. 10 is a diagram for explaining a procedure for removing the bellows in the support leg structure of the space environment test apparatus according to the present invention (part 4);

  A support leg structure 1 (hereinafter simply referred to as “support leg structure 1”) of a space environment test apparatus according to an embodiment of the present invention is installed in a vacuum chamber 30 of the space environment test apparatus 100, and a specimen 110 is mounted thereon. As shown in FIG. 1 and FIG. 2, the supporting leg 10, the bellows 41, the loose flange 43, and the fixing plate 45 that stand on the installation surface 201 are supported. And a bellows receiving flange 47.

  Hereafter, each component of the space environment test apparatus 100 and the support leg structure 1 which concerns on this Embodiment is demonstrated in detail based on FIGS.

<Space environment test equipment>
As shown in FIG. 2, the space environment test apparatus 100 includes a vacuum chamber 30 and an internal gantry 20 that is accommodated in the vacuum chamber 30 and on which a specimen 110 is placed. In order to perform advanced tests accompanying performance enhancement, the inside of the vacuum chamber 30 is evacuated to a high vacuum and cooled to a very low temperature in order to simulate the darkness of the universe. Is done.

  When an optical system test or the like is performed in the space environment test apparatus 100, vibrations generated by the operation of the vacuum pump and vibrations caused by the flow of the refrigerant used for cooling do not affect the optical system test or the like. Thus, anti-vibration measures are taken.

<Vacuum chamber>
The vacuum chamber 30 includes a chamber portion 31 that houses the internal gantry 20 and a nozzle portion 33 that is provided on a peripheral wall portion of the chamber portion 31.
As shown in FIG. 2, a stainless steel vacuum vessel having a cylindrical cross section can be used for the chamber portion 31.

  The nozzle part 33 is provided in the peripheral wall part of the chamber part 31 in order to form the penetration part in which the support leg part 10 is inserted. The nozzle portion 33 extends in the axial direction of the support leg portion 10 from the opening provided in the peripheral wall portion toward the installation surface 201.

<Support leg>
The support leg 10 is erected on the installation surface 201 and has a divided structure including an upper leg 11, an intermediate leg 13, and a lower leg 15.

The upper leg portion 11 supports the inner mount 20 from its lower surface, and a fixed plate 45 is attached to the upper leg portion 11.
The intermediate leg 13 is disposed between the upper leg 11 and the lower leg 15, the upper end is connected to the lower end of the upper leg 11 by a bolt b1, and the lower end of the lower leg 15 by the bolt b2. It is detachable by being connected to the upper end.

A space where the bellows 41 can be extracted from the support leg 10 can be formed by removing the intermediate leg 13. As will be described later, when the bellows 41 is extracted from the support leg 10, it is preferable that the height of the intermediate leg 13 is set higher than the height of the bellows 41 in order to extract the bellows 41 by moving in the horizontal direction. . However, when the bellows 41 is extracted, for example, when the posture is changed obliquely, the height of the intermediate leg 13 does not necessarily need to be higher than the height of the bellows 41.
The lower leg portion 15 has a lower end portion fixed to the installation surface 201 by a bolt b3.

As shown in FIG. 2, the support leg 10 is erected on an installation surface 201 provided on the vibration isolation surface plate 200, and vibration from the ground surface 202 is prevented from propagating to the internal frame 20. ing.
The support leg 10 may be erected on an installation surface provided on an independent foundation that is insulated from vibration generated from a device or the like that evacuates the vacuum chamber 30.

  The support legs 10 according to the present embodiment support a plurality of the internal gantry 20 and the vacuum chamber 30, and the number is appropriately selected according to the dimensions of the space environment test apparatus 100 (for example, a diameter of 9 m X 4 x 2 rows for a length of 12 m, 3 x 2 rows for a diameter of 6 m x length of 8 m), but the number is not particularly limited.

<Bellows>
The bellows 41 is formed of a cylindrical body that can expand and contract in the axial direction of the support leg 10, and is provided between the vacuum chamber 30 and the support leg 10 to absorb the vibration of the vacuum chamber and vibrate the upper leg 11. It is something that should not be given.
As shown in FIG. 1, the bellows 41 is flange-connected at its upper end side by a nozzle 33 and a bolt b3. Note that an O-ring 41 a is disposed between the bellows 41 and the nozzle portion 33 in order to maintain airtightness.
As a material of the bellows 41, for example, a stainless steel material such as SUS304 can be used.

<Loose flange>
The loose flange 43 is made of an annular member having an opening at the center, and is detachably attached to the lower end of the bellows 41 with a bolt b4 with the support leg 11 inserted through the opening. An inward flange portion is formed on the surface. Note that an O-ring 41 b is disposed between the loose flange 43 and the bellows 41 in order to maintain airtightness.

The opening of the loose flange 43 is set to have a diameter smaller than the inner diameter of the bellows 41 and larger than an outer diameter of a mounting projection 47a (described later) of the bellows receiving flange 47.
Since the size of the opening is smaller than the inner diameter of the bellows 41, the inner peripheral edge of the loose flange 43 extends toward the support leg 10 from the inner peripheral surface of the bellows 41 in the attached state.
Further, since the size of the opening is larger than the outer diameter of the mounting convex portion 47 a of the bellows receiving flange 47, there is a gap between the mounting convex portion 47 a and the inner peripheral edge of the loose flange 43 in the mounted state. S is formed (see FIG. 1).

<Fixed plate>
The fixed plate 45 is formed of an annular plate and is fixed in a state of being airtight with the support leg 10 in a state where the support leg portion 10 is inserted, and in the fixed state, the lower surface portion is the upper surface portion of the loose flange 43. Abut.
An O-ring 45a is disposed between the fixed plate 45 and the loose flange 43 in order to maintain airtightness.

<Bellows receiving flange>
The bellows receiving flange 47 supports the lower surface portion of the loose flange 43 and is detachably attached to the fixing plate 45 with bolts b6, and supports the bellows 41 by sandwiching the loose flange 43 in cooperation with the fixing plate 45. To do.

  As shown in FIG. 4, the bellows receiving flange 47 is formed by arranging, for example, three fan-shaped members divided into three in the circumferential direction of the support leg portion 10 in the circumferential direction, and has an annular shape as a whole. Each fan-shaped member has an attachment convex portion 47a having a height about the thickness of the loose flange 43 at the inner peripheral edge. A bolt hole is formed in the mounting convex portion 47a, and the bellows receiving flange 47 is attached to the fixed plate 45 by inserting a bolt b6 into the bolt hole. That is, the bellows receiving flange 47 and the fixing plate 45 sandwich the loose flange 43 attached to the bellows 41 so that the lower portion of the bellows 41 is fixed.

When the loose flange 43 is sandwiched between the bellows receiving flange 47 and the fixing plate 45, a gap S is formed between the mounting convex portion 47a and the inner peripheral edge of the loose flange 43 as described above. By forming the gap S, for example, even when the support leg 10 and the bellows 41 are eccentric, the deviation due to the eccentricity can be absorbed and the bellows 41 can be easily attached. . In other words, exact alignment is not necessary when the bellows 41 is attached.
This point will be described in more detail with reference to FIG.

  As shown in FIG. 3, in the support leg structure 1, the gap 33 is formed between the opening of the loose flange 43 and the mounting projection 47 a of the bellows receiving flange 47. The support leg 10 is connected in an airtight manner.

  FIG. 3A shows a state in which the center axis A1 of the support leg 10 and the center axis A2 of the nozzle portion 33 coincide with each other and are not eccentric. At this time, the loose flange 43 and the bellows receiving flange 47 The left and right clearances S between the mounting protrusions 47a are equal.

  FIG. 3B shows a state where the center axis A1 of the support leg 10 and the center axis A2 of the nozzle portion 33 do not coincide with each other and are eccentric, and at this time, the loose flange 43 and the bellows receiving flange 47 are shown. There is a difference in the left and right clearance S between the mounting projection 47a. Specifically, the center axis A2 of the nozzle portion 33 is shifted to the left side in the figure with respect to the center axis A1 of the support leg part 10, so that the gap S on the left side in the figure is large and the gap S on the right side in the figure is It is getting smaller. This means that the nozzle part 33 and the support leg part 10 can be connected in a state where the deviation of the center axis A2 of the nozzle part 33 with respect to the center axis A1 of the support leg part 10 is allowed, in other words, the support leg. The displacement of the central axis A2 of the nozzle portion 33 with respect to the central axis A1 of the portion 10 can be absorbed by adopting a method in which the loose flange 43 is fixed by being sandwiched between the fixing plate 45 and the bellows receiving flange 47.

Thereby, when attaching the bellows 41, even if the center axis A1 of the support leg 10 and the center axis of the bellows 41 are eccentric, the attachment can be performed without applying excessive deformation in the radial direction of the bellows 41. Become.
Since the bellows 41 is not deformed excessively, the bellows 41 can expand and contract in the axial direction of the support leg 10, and the vibration generated in the vacuum chamber 30 is absorbed by the bellows 41, and the vibration passes through the upper leg 11. Thus, it is possible to prevent propagation to the internal mount 20.

In the above description, the bellows receiving flange 47 is composed of a plurality of members divided into three parts in the circumferential direction of the support leg 10, but the divided members are connected and integrated with each other. The number of each divided member is not particularly limited.
In addition, the bellows receiving flange 47 sandwiches the loose flange 43 in cooperation with the fixed plate 45, but a predetermined pressing force capable of airtight between the loose flange 43 and the fixed plate 45 is applied to the loose flange 43. It may be provided, and may not exist over the entire circumference (360 °) of the support leg 10.

  In the above description, each member is flanged by bolts b1 to b5. However, the support leg structure according to the present invention is not limited to this, and each member is connected in an airtight manner. Anything is fine.

  Next, in the support leg structure 1 according to the present embodiment, a procedure for removing and replacing the bellows 41 will be described below with reference to FIGS.

  First, as shown in FIG. 5, the bolt b6 connecting the bellows receiving flange 47 and the fixing plate 45 is removed, and the bellows receiving flange 47 is removed. At this time, the bellows receiving flange 47 is not an annular member but has a divided structure, so that it can be removed even if the support leg 10 is present.

Next, as shown in FIG. 6, bolts b <b> 1 connecting the upper leg 11 and the intermediate leg 13 in the support leg 10, and the intermediate leg 13 and the lower leg 15 are connected. Remove the bolt b2 and slide the intermediate leg 13 sideways to remove it.
As described above, since the vacuum chamber 30 is supported by the plurality of support leg structures 1, even if the intermediate leg 13 is removed from one support leg 10, the vacuum chamber 30 has another support leg structure. As shown in FIG. 7, the upper leg portion 11 floats in the air, and the loose flange 43 that is an annular member and the bellows 41 that is a tubular member are removed from the support portion 10. A space to be extracted is formed.

Next, as shown in FIG. 7, the bolt b <b> 5 connecting the loose flange 43 and the bellows 41 is removed, and the loose flange 43 is removed from the bellows 41.
Finally, as shown in FIG. 8, the bolt b4 connecting the bellows 41 and the nozzle portion 33 is removed, and the bellows 41 is lowered to the position where the intermediate leg portion 13 is attached and then laterally moved, so that the bellows 41 Is removed from the support leg 10.

  When the removed bellows 41 is newly replaced and attached to the support leg 10 again, the above procedure may be reversed.

  As described above, the support leg structure 1 according to the present embodiment supports the bellows 41 by sandwiching the loose flange 43 attached to the lower part of the bellows 41 between the fixing plate 45 attached to the support leg 10 and the bellows receiving flange 47. Since it was attached to the leg part 10, even if the support leg part 10 and the bellows 41 are eccentric, it can be attached to the support leg part 10 without forcibly deforming the bellows 41.

  Furthermore, the support leg structure 1 according to the present embodiment has a simple structure including the intermediate leg portion 13 of the support leg portion 10 and the bellows receiving flange 47 having a split structure, so that the bellows 41 can be removed and replaced. In addition to facilitating maintenance, the bellows 41 can be increased in diameter.

DESCRIPTION OF SYMBOLS 1 Support leg structure 10 Support leg part 11 Upper leg part 13 Intermediate leg part 15 Lower leg part 20 Inner mount 30 Vacuum chamber 31 Chamber part 33 Nozzle part 41 Bellows 43 Loose flange 45 Fixed plate 47 Bellows receiving flange 47a Mounting convex part 100 Space Environmental test apparatus 110 Specimen 200 Anti-vibration surface plate 201 Installation surface 202 Ground surface b1 to b6 Bolts A1 and A2 Central axis S Gap

Claims (2)

A support leg structure of a space environment test apparatus that is installed in a vacuum chamber and supports an internal frame on which a specimen is placed,
A support leg that is erected on an installation surface and that supports the internal frame by penetrating a through part formed in a peripheral wall part of the vacuum chamber;
A cylindrical bellows through which the support leg is inserted and whose upper end is attached to the peripheral part of the penetrating part, and is extendable and contractible in the axial direction of the support leg;
A loose flange that is formed of an annular member, is attached to the lower end of the bellows, and forms an inward flange at the lower end of the bellows;
A fixing plate attached to the support leg so that a lower surface part abuts on an upper surface part of the loose flange;
A space environment test comprising: a bellows receiving flange that is detachably attached to the lower surface side of the fixed plate and supports the bellows by sandwiching the loose flange in cooperation with the fixed plate. Support leg structure of the device. The bellows receiving flange is composed of a plurality of members divided in the circumferential direction,
The support leg has a removable intermediate leg under the fixed plate, and a space in which the bellows can be extracted from the support leg can be formed by removing the intermediate leg. The support leg structure of the space environment test apparatus according to claim 1.