JP3030468B2 - Space environment test equipment - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION [Industrial Application Field] The present invention forms a high-vacuum and cryogenic environment which is almost equivalent to the space environment, and is used for testing various devices used in space such as artificial satellites. Related to space environment test equipment.

[Background Art] A space environment test apparatus (space chamber) generally includes a heat absorbing wall called a shroud or a shield inside a vacuum vessel to simulate the darkness and darkness of the universe, and a vacuum pump inside the vacuum vessel. It simulates the high vacuum of the universe by evacuating. That is, shroud 100K
It is common to simulate the darkness and darkness of the universe by cooling below, and liquid nitrogen has been mainly used as the cold source. Furthermore, in order to accommodate a specimen with a large amount of released gas in the vacuum container and to evacuate it to a high vacuum, it is necessary to evacuate using a very large pump. It was necessary to incorporate a cryogenic exhaust surface, that is, a cryopanel inside the shroud, to cool the cryopanel to 20K or less, and to function as a cryopump for condensing and exhausting gas such as nitrogen. Helium supplied from a helium refrigerator is conventionally used as a cooling source for the cryopanel.

In addition, when the inside of the vacuum vessel is heated to room temperature after the test is completed, it is generally performed by introducing nitrogen gas into the shroud.

[Problems to be solved by the invention]

In such a space environment test apparatus, the piping for supplying liquid nitrogen to the shroud is constructed by supplying liquid nitrogen to a target shroud through a vacuum vessel wall near the shroud for supplying liquid nitrogen. The method is such that a liquid nitrogen pipe penetrating the vacuum vessel is once penetrated into the inside of the shroud, and then piped inside the shroud to supply liquid nitrogen to a target shroud.

However, if the space environment test equipment is small,
Although there is no problem with the above method, if the size is increased and a large number of liquid nitrogen supply pipes are required, the number of penetrations of the vacuum vessel increases and the external pipes also become long, which may cause leakage of the vacuum vessel or a vacuum vessel. There are drawbacks such as requiring a large space for piping outside. In addition, the above-described method has a drawback that the space for installing the test body inside the shroud is limited.

In view of the above, an object of the present invention is to provide a space environment test apparatus capable of efficiently installing pipes and reducing a space for piping work inside and outside a vacuum vessel, particularly in a space environment test apparatus requiring a large number of pipes.

[Means for solving the problem]

In order to achieve the above object, a space environment test apparatus according to the first invention is a space environment test apparatus in which a frame is fixed to an inner peripheral wall of a vacuum vessel and a heat absorbing wall is supported by the frame. The heat absorbing wall is fixed to the inner periphery of the frame via a connecting member, and a pipe for supplying liquid nitrogen to the heat absorbing wall is provided between the heat absorbing wall and the frame. The second invention is characterized in that a shield plate is provided on the outer periphery of the frame of the first invention.

〔Example〕

Hereinafter, the present invention will be described in more detail based on embodiments shown in the drawings.

First, as shown in FIG. 3, a space environment test apparatus 1 according to the present embodiment has a shroud 3 divided and formed into a plurality of blocks in a vacuum vessel 2, and each shroud 3 Each has an inlet manifold 4 and an outlet manifold 5 for introducing liquid nitrogen, and the inlet manifold 4 is arranged below the shroud 3 so that the outlet manifold 5 on the upper side is located.

As shown in FIGS. 1 and 2, the shroud 3 forms a fin tube 6 having a wing side integrally provided on both sides of a tube in an arc shape having a predetermined curvature. Along the inner peripheral wall without any gaps,
Both ends are connected to the inlet manifold 4 or the outlet manifold 5 via a vent pipe 7 and a coupling 8, respectively.

This shroud 3 is usually formed as a unit by integrally forming the frame 10 with the shroud 3, the inlet manifold 4, the outlet manifold 5, the fin tube 6, a pipe for liquid nitrogen described later, etc. It is installed in. That is, the inlet manifold 4 and the outlet manifold 5 are fixed to both ends of a frame 10 in which a channel-shaped mold is formed with the same curvature as the inner periphery of the container, respectively, with U bolts 11, and the fin tube 6 is connected via a connecting member 12. And the fin tube 6 is connected between the manifolds 4, 5 and the fin tube 6 via a vent tube 7 and a coupling 8, respectively.

At this time, since the vent pipe 7 rises in the direction of the container center from both the manifolds 4 and 5 and bends substantially 90 degrees and is connected to the fin pipe 6, a space is provided between the fin pipe 6 and the frame 10. S is formed. The connection structure between the manifolds 4 and 5 and the fin tube 6 as described above is inevitably generated in order to make the area of the shroud 3 covering the inner peripheral wall of the vacuum vessel 2 as large as possible and without any gap. That is,
Since the portion of the shroud 3 acting as a heat absorbing wall is substantially the portion of the fin tube 6 and the wing side, it is necessary to make the adjacent shrouds 3 as close as possible. When the pipe 7 is protruded from both manifolds 4 and 5 and the fin pipe 6 is connected in the tangential direction of the container, a certain interval is required for joining the respective parts. The space where the fin tube 6 does not exist is widened, and the internal space where the test specimen is installed is directly exposed to the container wall, which causes a disadvantage that heat loss increases. With the above structure, the gap between the adjacent manifolds 4 and 5 can be minimized, so that such an inconvenience can be avoided.

Further, as described above, by connecting the both manifolds 4 and 5 and the fin tube 6 via the bent vent tube 7, the shrinkage of the fin tube 6 when cooled to extremely low temperature is absorbed by the vent tube 7. be able to.

Therefore, in the present invention, the space S between the fin tube 6 and the frame 10 which is inevitably generated as described above is used as a piping space, and the space S is used as a liquid nitrogen pipe, and the liquid nitrogen is supplied to the shroud 3. Liquid nitrogen supply pipe 13 and liquid nitrogen return pipe for returning liquid nitrogen from shroud 3
14 are arranged, these pipes are fixed to the frame 10 with U-bolts 15 in the same manner as the above-mentioned manifold, and these pipes and the manifold are connected by a crossover pipe 16.

The shroud unit thus formed is fixed to female screw blocks 17 provided at predetermined intervals on the inner peripheral wall of the vacuum vessel 2 with bolts 18 and nuts 19 so as to sandwich the frame 10.

Further, a shield plate 20 for blocking heat radiation between the shroud 3 and the vacuum vessel 2 is provided on the outer periphery of the frame 10 as necessary. By providing the shield plate 20 in this way and performing piping on the inner peripheral side of the shield plate 20, heat radiation between various pipes and the container wall can also be reduced, and the amount of liquid nitrogen used can be significantly reduced. .

The structure of the details such as the shroud can be appropriately selected according to the size of the vacuum vessel, the number of divisions of the shroud, and the like, and the order of fixing to the vessel is not limited to the above embodiment.

〔The invention's effect〕

As described above, the space environment test apparatus of the present invention
Since the space formed in the outer peripheral portion of the heat absorbing wall is used as a piping space, the number of penetrations of the vacuum vessel can be reduced, and the number of penetrations causing leakage of the vacuum vessel can be minimized. In addition, it is not necessary to provide a wide piping space outside the vacuum vessel, and a test object installation space inside the shroud can be widened.

Therefore, the diameter of the vacuum container can be reduced, the installation of external auxiliary equipment and the like can be facilitated, and the space for installation can be reduced.

[Brief description of the drawings]

FIG. 1 shows an embodiment of the present invention. FIG. 1 is a longitudinal sectional view of a main part, FIG. 2 is an enlarged sectional view of part A in FIG. 1, and FIG. 3 is a schematic view showing an installation state of a shroud. It is. DESCRIPTION OF SYMBOLS 1 ... Space environment test apparatus, 2 ... Vacuum container, 3 ... Shroud, 4 ... Inlet manifold, 5 ... Outlet manifold, 6 ... Fin tube, 7 ... Vent tube, 8 ... Coupling, 10 ... frame, 12 ... connecting member, 13 ... liquid nitrogen supply pipe, 14 ... liquid nitrogen return pipe, S ... space

──────────────────────────────────────────────────続 き Continuation of the front page (56) References JP-A-61-182281 (JP, A) US Patent 3,455,561 (US, A) (58) Fields investigated (Int. Cl. ⁷ , DB name) B64G 7 / 00 G01M 19/00

Claims (2)

(57) [Claims] In a space environment test apparatus in which a frame is fixed to an inner peripheral wall of a vacuum vessel and a heat absorbing wall is supported by the frame, the heat absorbing wall is fixed to an inner periphery of the frame via a connecting member. A space environment test apparatus, wherein a pipe for supplying liquid nitrogen to the heat absorbing wall is provided between the heat absorbing wall and the frame. 2. The space environment test apparatus according to claim 1, wherein a shield plate is provided on an outer periphery of said frame.