JP3833671B2 - Space environment test equipment - Google Patents

Description

  The present invention relates to a space environment test apparatus, and more particularly, a space environment test apparatus that forms a high vacuum and extremely low temperature environment substantially equivalent to the space environment and tests various devices used in space such as artificial satellites. About.

  As shown in FIG. 6, the space environment test apparatus has a vacuum vessel 1 that has been evacuated to a high vacuum, in order to simulate the cold and darkness of the universe, the inner surface is painted black and liquid nitrogen that is a low-temperature liquefied gas, A heat absorbing wall called a shroud (hereinafter referred to as a shroud) 2 is provided which is cooled to 100K or less with the above refrigerant.

  In order to test various devices (device under test) 3 such as artificial satellites with this space environment test apparatus, a gantry 4 for fixing the device under test 3 and adjustment, wiring, piping, etc. of the device under test 3 It is necessary to install a fixed or detachable work scaffold 5 for preparing the test.

  However, since the mount 4 and the work scaffold 5 are provided so as to protrude inside the shroud 2, not only a dead space is created in the test environment space and the effective space is narrowed, but also in the case of a fixed work scaffold In the test environment space, a normal temperature surface that causes a test error is created. On the other hand, in the case of a detachable work scaffold, installation and removal work is complicated, and it is difficult to take a structure that can receive a large load, so it is difficult to load the test subject with a load on the work scaffold. It is.

  Therefore, the present invention effectively utilizes the space in the vacuum vessel, prevents a normal temperature surface that causes a test error in the test environment space, and further loads the work scaffold without complicated work. An object of the present invention is to provide a space environment test apparatus that can carry a device under test.

In order to achieve the above-described object, the space environment test apparatus of the present invention includes a heat absorption wall for holding the inside of the vacuum vessel at a cryogenic temperature and an object for fixing the test piece for holding the sample to be tested. In the space environment test apparatus comprising the gantry, a substantially horizontal working scaffold floor that is cooled in the same manner as the heat absorbing wall is provided in the vacuum vessel, and covers the gantry for fixing the device under test. A cover is detachably provided on the floor for the working scaffold .

  In a space environment test apparatus equipped with a base for fixing a DUT that holds the DUT, the cover is cooled by heat conduction from the floor by covering the base with a removable cover. The gantry is covered with a cover at the same temperature as the heat absorption wall, and it is possible to prevent a normal temperature surface from occurring in the test environment.

  Hereinafter, the present invention will be described in more detail based on embodiments shown in the drawings. FIG. 1 is a cross-sectional view of a vacuum vessel of a space environment test apparatus showing a first embodiment of the present invention. Inside a vacuum container 11 constituting the space environment test apparatus, a shroud 12 along an upper inner peripheral wall, and a lower part Are provided with a floor 13 installed substantially horizontally and a pedestal 15 for holding a device under test 14.

  The floor portion 13 is supported by a column 16 erected on the bottom of the vacuum vessel 11, is formed in a highly rigid structure that can sufficiently withstand the load of the device under test 14 and the worker, and the floor portion 13. In addition, the vacuum vessel wall, which is a room temperature surface, is not seen from the test environment space 17 surrounded by the shroud 12. Further, the member constituting the floor portion 13 is provided with a flow path 18 through which a refrigerant such as liquid nitrogen flows, and is cooled to substantially the same temperature as the shroud 12 by the refrigerant supplied to the flow path 18.

  The floor portion 13 is used as a scaffold for attaching the device under test 14 to the gantry 15 and for preparing for the test of the device under test 14 such as adjustment, wiring, piping, etc. And acts as the same heat absorbing wall as the shroud 12.

  As a result, it is not necessary to install a working scaffold when installing or removing the DUT 14, and at the same time, it is possible to prevent a normal temperature surface that causes a test error from occurring in the test environment space 17 and to perform an accurate test. It can be performed. It should be noted that the gantry 15 may also be provided with a coolant channel, and the gantry 15 may be cooled to substantially the same temperature as the shroud 12.

  Between each floor part 13, the cover 41 which covers the test environment space 17 side of the base 15 for fixing to-be-tested object is provided. The cover 41 is made of aluminum, stainless steel or the like, and is detachably attached so as to be spanned between the floor portions 13 located on both sides of the gantry 15.

  FIG. 2 shows a second embodiment of the present invention, and shows an embodiment in which the floor portion 13 is constituted by a plurality of finned tubes 21. The finned tube 21 is formed by integrally forming fins 23 on the outer periphery of a tube body 22 serving as a refrigerant flow path, and reinforcing flanges 24 are formed at both end portions of the fins 23. The floor portion 13 is formed by placing a plurality of the finned tubes 21 in parallel on a frame 25 provided at the bottom of the vacuum vessel 11.

  Also in the present embodiment, the floor portion 13 is used as a scaffold and can be cooled to the same temperature as the shroud 12 by flowing a coolant through the tube of the finned tube 21, and installation, adjustment, etc. of the DUT 14 can be easily performed. It is possible to perform an accurate test.

  FIG. 3 shows a third embodiment of the present invention, and shows an example in which a cooling panel of the floor portion 13 is configured by fixing a pipe 32 serving as a refrigerant flow path to the back surface of the flat plate 31 by welding. The flat plate 31 is provided on a frame 33 provided at the bottom of the vacuum vessel 11 via an appropriate spacer 34 and is used for fixing a working scaffold and the DUT 14 as described above. , Acting as the same heat absorbing wall as the shroud 12.

  In the second and third embodiments of FIGS. 2 and 3, the cover 41 covering the test environment space 17 side of the gantry 15 can be detachably mounted between the floor portions 13 located on both sides of the gantry 15. Attached to. The cover 41 is also formed of aluminum, stainless steel or the like, like the finned tube 21 and the flat plate 31.

  As shown in the first, second, and third embodiments, by attaching the cover 41 to the floor portion 13, the cover 41 is cooled by heat conduction due to contact with the floor portion 13, thereby cooling the pedestal 15 that is a normal temperature portion. It is possible to cover with the cover 41 in a state of being applied. Therefore, it is possible to prevent a room temperature surface from being generated in the test environment space 17 by attaching the cover 41 to the pedestal 15 exposed in the test environment space 17 according to the size of the device under test.

  4 shows, for example, as shown in the first embodiment, the floor portion 13 is divided into three rows on the central portion and both sides in the axial direction of the vacuum vessel 11, and the refrigerant flow path is also provided on the gantry 15. An example of the refrigerant supply system when provided is shown.

  In this refrigerant supply system, the refrigerant supply main pipe 51 is branched into five refrigerant supply pipes 52 and 52 corresponding to the floor portions 13 and the gantry 15, and control valves 53 and 53 are provided respectively. Thereby, the refrigerant | coolant supply amount to each floor part 13 and the mount frame 15 can be controlled by adjusting the opening degree of each control valve 53, 53, and each part can be cooled to the temperature as needed.

  FIG. 5 shows another embodiment of the refrigerant supply system. This refrigerant supply system includes five supply pipes 61 and 61 corresponding to the floor portions 13 and the gantry 15, and branches from the supply pipes 61 and 61, respectively, to supply a heating fluid such as a refrigerant supply main pipe 62 and nitrogen gas. Branch pipes 64 and 65 connected to the heat medium supply main pipe 63 to be supplied, control valves 66 and 66 provided in the supply pipe 61, and switching valves 67 and 68 provided in the branch pipes 64 and 65, respectively. It is comprised by.

  When the refrigerant supply system is configured in this way, the switching valves 67 and 68 are switched and opened and the control valves 66 and 66 are opened and closed as necessary, thereby cooling and heating the floor portions 13 and the gantry 15. Can be done individually.

It is sectional drawing of the vacuum vessel which shows 1st Example of the space environment test apparatus of this invention. It is sectional drawing of the principal part of the vacuum vessel which shows 2nd Example similarly. It is sectional drawing of the principal part of the vacuum vessel which shows a 3rd Example similarly. It is a systematic diagram which shows one Example of the refrigerant | coolant supply system of the space environment test apparatus of this invention. It is a systematic diagram which shows the other Example of a refrigerant | coolant supply system. It is sectional drawing of the vacuum vessel which shows an example of the conventional space environment test apparatus.

Explanation of symbols

  DESCRIPTION OF SYMBOLS 11 ... Vacuum container, 12 ... Shroud, 13 ... Floor part, 14 ... Test object, 15 ... Mount, 16 ... Column, 17 ... Test environment space, 18 ... Flow path, 21 ... Finned tube, 31 ... Flat plate, 32 ... pipe, 41 ... cover, 51, 62 ... refrigerant supply main pipe, 53, 66 ... control valve, 63 ... heat medium supply main pipe, 67, 68 ... switching valve

Claims (1)

In a space environment test apparatus provided with a heat absorption wall for holding the inside of the vacuum vessel at a cryogenic temperature and a base for fixing a device under test for holding the device under test on the inner periphery of the vacuum vessel, In addition, a substantially horizontal working scaffold floor that is cooled in the same manner as the heat absorbing wall is provided, and a cover that covers the test object fixing base is detachably provided on the working scaffold floor. Space environment test equipment.

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