JP4071026B2 - Artificial satellite structure - Google Patents

Description

[0001]
BACKGROUND OF THE INVENTION
The present invention relates to an artificial satellite structure for efficiently storing electronic equipment.
[0002]
[Prior art]
FIG. 9 is a diagram showing a conventional artificial satellite structure. In the figure, 8 is an electronic device to be mounted, 21 is a cylindrical central cylinder located at the center of the structure, 22 is a web attached to the outside of the central cylinder 21 in the radial direction and parallel to the central axis of the central cylinder 21. Panels 23 are attached to the upper ends of the central cylinder 21 and the web panel 22 in the horizontal direction, and the ceiling panels constituting the ceiling of the box-type structure 24 are attached in the horizontal direction from the lower side of the central cylinder 21. A base panel 25 constituting the bottom plate is an outer surface panel which is attached to the web panel 22, the ceiling panel 23 and the base panel 24 and constitutes the outer surface of the box-type structure. The electronic device 8 to be mounted is arranged and supported on the outer surface panel 25.
[0003]
Since the central cylinder 21 has a cylindrical shape, it has very high rigidity and strength against both horizontal load and vertical load. Therefore, the central cylinder 21 bears the horizontal load and vertical load of the entire satellite.
[0004]
On the other hand, an artificial satellite that does not use a central cylinder is disclosed in JP-A-11-208596. In this case, a reinforcing panel is installed instead of the central cylinder, thereby satisfying rigidity and strength.
[0005]
[Problems to be solved by the invention]
Since the conventional satellite structure is configured as described above, the presence of a central cylinder in the center makes it impossible to secure sufficient space for mounting electronic equipment that increases in response to the increase in power consumption. was there.
[0006]
Further, when the central cylinder is not used, the rigidity and strength become insufficient, so that a reinforcing panel must be installed, and there is a problem that a sufficient space for mounting the electronic device cannot be secured.
[0007]
The present invention has been made to solve the above-described problems. In an artificial satellite structure in which the mounting space cannot be increased by simply increasing the size due to the launch vehicle, it is possible to increase the power. The purpose is to obtain an artificial satellite structure that can secure a sufficient mounting space for increasing electronic devices.
[0008]
Another object of the present invention is to provide an artificial satellite structure that is excellent in rigidity and strength even when a central cylinder is not used, and that can sufficiently secure a mounting space for electronic equipment.
[0009]
[Means for Solving the Problems]
An artificial satellite structure according to the present invention includes a payload structure portion formed in a box shape by an outer surface panel, a bus structure portion formed at a lower end of the payload structure portion, an electronic device housed in the payload structure portion, an electronic The electronic equipment mounting panel is disposed and supported and installed in the payload structure, and the electronic equipment mounting panel is installed in a direction parallel to the axis direction of the launch when the plane direction is launched. Two outer peripheral sides extending in a direction perpendicular to the machine axis direction are fixed to the outer surface panel of the payload structure portion in contact with each of them.
[0010]
The satellite structure according to the present invention can be pulled out and removed from the payload structure by sliding the electronic device mounting panel.
[0011]
In the artificial satellite structure according to the present invention, a panel for mounting an electronic device incorporates a heat pipe for releasing heat generated in the electronic device.
[0012]
In the artificial satellite structure according to the present invention, the electronic device mounting panel arranges and supports the electronic device on both surfaces thereof.
[0014]
In the artificial satellite structure according to the present invention, the electronic device mounting panel is installed in parallel to the north-south panel forming the payload structure.
[0015]
In the satellite structure according to the present invention, the electronic device mounting panel is installed in parallel to the east-west panel forming the payload structure.
[0017]
DETAILED DESCRIPTION OF THE INVENTION
Hereinafter, an embodiment of the present invention will be described.
Embodiment 1 FIG.
FIG. 1 is an exploded perspective view of a satellite structure according to Embodiment 1 of the present invention. In FIG. 1, 1 is a payload structure formed at the upper part of the satellite structure, 2 is a bus structure formed at the lower end of the payload structure 1, and 3 is an electronic device mounting panel on which electronic devices are arranged and supported. Show. Reference numeral 4 denotes a payload part east-west panel, 5 denotes a payload part north-south panel, 6 denotes a payload part ceiling panel, 7 denotes a bus part interface panel, and the payload structure part is formed by 4, 5, 6, and 7. Reference numeral 8 denotes an electronic device.
[0018]
The artificial satellite structure according to the present invention is mainly composed of a payload structure portion 1 on which mission-related electronic devices are mounted, and a bus structure portion 2 on which power supply system and propulsion system devices are mainly mounted. Inside the payload structure portion 1, an electronic device mounting panel 3 for mounting electronic devices is installed in the vertical direction and in a direction parallel to the payload portion north-south panel 5. This electronic device mounting panel 3 can be pulled out freely in the direction of the arrow in the figure by removing the payload part east-west panel 4. At the time of launching the rocket, the four outer peripheral sides of the electronic device mounting panel 3 are fixed and supported by the panels in contact therewith.
[0019]
FIG. 2 is a diagram showing a first natural vibration mode of a structural analysis result when the present embodiment is applied to a 6-ton class satellite structure. For comparison, FIG. 3 is a diagram illustrating a primary natural vibration mode of a structural analysis result of a conventional central cylinder type. The primary natural frequency is 23 Hz, and the secondary natural frequency is 25 Hz. It has almost the same rigidity as the central cylinder type (primary natural frequency: about 20 Hz) and is given on the rocket side. Satisfies the requirement of 15 Hz or higher.
[0020]
Moreover, the mountable area of the electronic device according to the present embodiment is about twice that of the central cylinder type.
[0021]
4 is a cross-sectional view of the electronic device mounting panel 3 in FIG. Reference numeral 9 denotes a cooling heat pipe, 9a denotes an auxiliary heat pipe for connecting the electronic device 8 and the heat pipe 9, and other reference numerals are the same as those in FIG. The electronic device 8 is arranged and supported on both surfaces of the electronic device mounting panel 3, and cooling heat pipes 9 are arranged in a lattice shape inside the electronic device mounting panel 3. In addition, an auxiliary heat pipe 9 a is disposed so as to connect the mounting surface of the electronic device 8 and the heat pipe 9. FIG. 5 is a view showing an arrangement example of the heat pipe 9.
[0022]
As described above, according to the first embodiment, it is possible to increase the space of the electronic device 8 that can be mounted by installing the electronic device mounting panel 3 in the payload structure portion 1 and increasing the number of the panels. An effect is obtained.
[0023]
Further, by removing the payload portion east-west panel 4, the electronic device mounting panel 3 can be pulled out and removed, and the electronic device can be easily attached and detached, so that the effect of facilitating repair or the like can be obtained.
[0024]
Further, by incorporating the heat pipe 9 in the electronic device mounting panel 3, the effect that heat generated from the electronic device 8 can be released through the heap pipe 9 can be obtained.
[0025]
Further, by arranging and supporting the electronic device 8 on both surfaces of the electronic device mounting panel 3, the mounting area is doubled compared to the case where the electronic device 8 is disposed only on one surface, and the space of the electronic device 8 that can be mounted is increased. The effect of being able to be obtained.
[0026]
In addition, by installing the electronic device mounting panel 3 in the payload structure portion 1 in the vertical direction, it is possible to obtain an effect that the electronic device mounting panel 3 can be supported in the panel surface direction against the load in the axis direction at the time of launch.
[0027]
Moreover, the effect that the electronic device 8 can be installed also in the payload part north-south panel 5 is acquired by installing the electronic equipment mounting panel 3 in parallel with the payload part north-south panel 5.
[0028]
In addition, by installing the electronic device mounting panel 3 in parallel with the north-south surface panel 5 of the payload portion, it becomes easy to connect the heat between the east surface panel and the west surface panel, and to easily release the generated heat. can get.
[0029]
In addition, by using the electronic device mounting panel 3 as a rigid member, rigidity and strength equivalent to those of a conventional central cylinder type satellite can be obtained without installing a reinforcing panel, and the electronic device is mounted. The effect that sufficient space can be secured is obtained.
[0030]
Embodiment 2. FIG.
FIG. 6 is an exploded perspective view of an artificial satellite structure according to Embodiment 2 of the present invention. In FIG. 6, the same reference numerals are used to indicate the same components as in FIG. 1, and detailed descriptions thereof are omitted.
[0031]
The configuration of the artificial satellite structure in the present embodiment is almost the same as that in the first embodiment. However, in this embodiment, the electronic device mounting panel 3 is placed in parallel with the payload section east-west panel 4 as shown in FIG. Deploy. In this case, the electronic device mounting panel 3 can be taken in and out by removing the payload part north-south panel 5.
[0032]
As described above, according to the second embodiment, the same effect as in the first embodiment can be obtained.
[0033]
Embodiment 3 FIG.
FIG. 7 is an exploded perspective view of an artificial satellite structure according to Embodiment 3 of the present invention. In FIG. 7, the same reference numerals are used to indicate the same components as those in FIG. 1, and detailed descriptions thereof are omitted.
[0034]
The configuration of the satellite structure in the present embodiment is almost the same as that of the first embodiment. However, in this embodiment, as shown in FIG. The panel 3 and the electronic device mounting panel 3 arranged in parallel with the payload part north-south panel 5 are mixed. In this case, the electronic device mounting panel 3 can be taken in and out by removing the payload part east-west panel 4 or the payload part north-south panel 5.
[0035]
As described above, according to the third embodiment, the same effect as in the first embodiment can be obtained.
[0036]
Reference example.
FIG. 8 is an exploded perspective view of the artificial satellite structure according to the reference example . In FIG. 8, the same reference numerals are used to indicate the same components as in FIG. 1, and detailed descriptions thereof are omitted.
[0037]
The configuration of the artificial satellite structure in the present reference example is almost the same as that of the first embodiment, but in this reference example , the electronic device mounting panel 3 is arranged in the horizontal direction as shown in FIG. In this case, the electronic device mounting panel 3 can be taken in and out by removing the payload part east-west panel 4 or the payload part north-south panel 5.
[0038]
As described above, according to this reference example , as in the first, second, and third embodiments, the effect that the space for mounting the electronic device 8 can be increased, the effect that the electronic device 8 can be easily attached and detached, and the electronic The effect which can escape the heat_generation | fever from the apparatus 8 and the effect which can connect the heat | fever between panels are acquired.
[0039]
In each of the above embodiments, the electronic device 8 is disposed on both surfaces of each electronic device mounting panel 3, but may be disposed only on one surface.
[0040]
【The invention's effect】
As described above, according to the present invention, the payload structure portion formed in a box shape by the outer surface panel, the bus structure portion formed at the lower end of the payload structure portion, and the electronic device housed in the payload structure portion, The electronic device mounting panel is arranged and supported and installed in the payload structure portion, so that the space for mounting the electronic device can be increased by increasing the number of electronic device mounting panels in the payload structure portion. There is an effect that can be increased.
[0041]
According to the present invention, the electronic device mounting panel is configured so that it can be pulled out and removed from the payload structure by sliding, so that the electronic device can be easily attached and detached, so that it is easy to repair and the like. There is an effect.
[0042]
According to the present invention, since the electronic device mounting panel is configured to incorporate the heat pipe for releasing the heat generated in the electronic device, there is an effect that the generated heat can be released through the heap pipe.
[0043]
According to the present invention, the electronic device mounting panel is configured so that the electronic device is disposed and supported on both surfaces thereof, so that the mountable area is doubled compared to the case where the electronic device is mounted on only one surface, and the electronic device can be mounted. There is an effect that can increase the space.
[0044]
According to the present invention, since the electronic device mounting panel is configured to be installed in the vertical direction in the payload structure portion, it can be supported in the panel surface direction against the load in the axial direction at the time of launch, It has the effect of obtaining the same rigidity and strength as a central cylinder type satellite.
[0045]
According to the present invention, since the electronic device mounting panel is configured to be installed in parallel with the north-south surface panel forming the payload structure portion, the electronic device can also be installed on the payload portion north-south surface panel. At the same time, the heat connection between the east panel and the west panel is facilitated, and the generated heat is easily released.
[0046]
According to this invention, since the electronic device mounting panel is configured to be installed in parallel with the east-west panel forming the payload structure portion, the electronic device can also be installed in the payload portion east-west panel. At the same time, the heat connection between the south panel and the north panel is facilitated, and the generated heat is easily released.
[Brief description of the drawings]
FIG. 1 is an exploded perspective view of an artificial satellite structure according to Embodiment 1 of the present invention.
FIG. 2 is a diagram showing a primary natural vibration mode of a structural analysis result according to Embodiment 1 of the present invention.
FIG. 3 is a diagram showing a primary natural vibration mode of a structural analysis result of a conventional central cylinder type.
4 is a cross-sectional view of the electronic device mounting panel in FIG. 1;
FIG. 5 is a diagram showing an arrangement example of heat pipes in FIG. 4;
FIG. 6 is an exploded perspective view of an artificial satellite structure according to Embodiment 2 of the present invention.
FIG. 7 is an exploded perspective view of an artificial satellite structure according to Embodiment 3 of the present invention.
FIG. 8 is an exploded perspective view of a satellite structure according to a reference example .
FIG. 9 is an exploded perspective view of a conventional artificial satellite structure.

Claims (6)

A payload structure formed in a box shape by an outer surface panel, a bus structure formed at the lower end of the payload structure, an electronic device housed in the payload structure, and the electronic device disposed and supported An electronic device mounting panel installed in the payload structure,
The electronic device mounting panel is installed in a direction parallel to the axis direction at the time of launch, and the outer peripheral two sides extending in a direction perpendicular to the axis direction at the time of launch are in contact with each other An artificial satellite structure characterized by being fixed to an outer surface panel of a payload structure portion .   2. The artificial satellite structure according to claim 1, wherein the electronic device mounting panel can be pulled out and removed from the payload structure by sliding.   2. The artificial satellite structure according to claim 1, wherein the electronic device mounting panel includes a heat pipe for releasing heat generated in the electronic device.   2. The artificial satellite structure according to claim 1, wherein the electronic device mounting panel arranges and supports the electronic devices on both surfaces thereof.   2. The artificial satellite structure according to claim 1, wherein the electronic device mounting panel is installed in parallel with the north-south panel forming the payload structure.   2. The artificial satellite structure according to claim 1, wherein the electronic device mounting panel is installed in parallel with the east-west panel forming the payload structure portion.

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