JP2003081199A - Honeycomb sandwiched panel for satellite mounted optical equipment - Google Patents

Abstract

PROBLEM TO BE SOLVED: To solve the problem that troublesome labor is required for fabrication, there is a limit in the point of reduction weight, and the maximum thermal deformation of 5 μm causes the deformation of a reflecting mirror to possibly put a telescope into an unfocused condition and preclude the mounting of optical equipment having high resolution. SOLUTION: This honeycomb sandwiched panel for satellite mounted optical equipment comprises a honeycomb core and a skin for covering both-side surfaces of the honeycomb core, the honeycomb core and the skin being formed of CFRP. It also has an outside honeycomb core arranged on a portion to which a heavier load is applied than to other portions and an inside honeycomb core lighter than the outside honeycomb core, which is arranged on a portion excluding the outside honeycomb core.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a honeycomb sandwich panel used as an optical mount for an optical device such as a reflector mounted on a satellite.

[0002]

2. Description of the Related Art In recent years, as an optical mount for satellite-mounted optical equipment, CFRP (Car
Bon Fiber Reinforced Plas
Honeycomb sandwich panels using (tic: carbon fiber reinforced plastic) have been adopted. The honeycomb sandwich panel is a sandwich-shaped panel composed of a honeycomb core and a skin covering the honeycomb core. CFR
It is known that P has a high strength, is lighter in weight, and has less thermal strain than metals such as Invar alloy.

FIG. 7 shows a document: Proceedings European Con.
conference on Spacecraft Structures, Materials and Me
chanical Testing, Braunschweig, Germany, 4-6 Novem
FIG. 8 is a schematic perspective view showing an example of an optical mount of a satellite-mounted optical device using a conventional honeycomb sandwich panel shown in ber1998 (ESA SP-428, February 1999). This is the X-ray observation telescope XMM (X-ray Multi).
It is an optical mount of a reflecting mirror mounted on a mirror. In the figure, 31 is an optical mount. Reference numeral 32 denotes a main mirror (reflecting mirror) support frame, which is composed of a honeycomb sandwich panel using a skin made of CFRP. Three
Reference numeral 3 denotes a web, which is a member having a honeycomb sandwich structure made of aluminum. The web 33 is provided as a reinforcing member for the main mirror support pedestal 32, which is the main body, for the purpose of increasing rigidity so as to withstand the load at the time of launching the artificial satellite. Reference numeral 34 is a support hole for the primary mirror, and three holes are formed to support the primary mirror. The main mirror is fitted into each of the support holes 34 of the main mirror so that the main mirror is supported by the entire optical mount 31.

[0004]

As described above, the conventional optical mount using the honeycomb sandwich panel is the main mirror support mount 32 of the main body which is the honeycomb sandwich panel.
In addition to this, since the web 33 of the reinforcing member is provided, there is a problem that the production is complicated. Also,
Since many members are required, there is a problem in that there is a limit in weight reduction. Further, in the direction horizontal to the surface of the main mirror support base 32, thermal deformation of up to 5 μm occurs, so that there is a possibility that the reflecting mirror may be deformed and the telescope may become out of focus. There was a problem that the equipment could not be installed.

The present invention has been made to solve the above problems and is easy to manufacture, lightweight, high in strength, and less likely to be deformed by heat. The purpose is to get a panel.

[0006]

A honeycomb sandwich panel for an optical device mounted on a satellite according to the present invention comprises a honeycomb core and a skin covering both side surfaces of the honeycomb core. The honeycomb core and the skin are made of CFRP. It was made to become.

The honeycomb sandwich panel for satellite mounted optical equipment according to the present invention has a coefficient of thermal expansion within ± 0.5 ppm / K in all directions horizontal to the surface.

In the honeycomb sandwich panel for an optical device mounted on a satellite according to the present invention, the honeycomb core is provided with an outer honeycomb core arranged at a portion of the entire honeycomb core where a load is stronger than the other portions. The inner honeycomb core is arranged in a portion excluding the outer honeycomb core, and the outer honeycomb core has higher strength than the inner honeycomb core.

In the honeycomb sandwich panel for satellite-mounted optical equipment according to the present invention, the inner honeycomb core is made lighter than the outer honeycomb core.

In the honeycomb sandwich panel for an optical device mounted on a satellite according to the present invention, the honeycomb core has a direction in which a load is applied more strongly than other directions in the honeycomb core, and a shear force is generated in the honeycomb core. The honeycomb core is divided into a plurality of parts so as to be aligned with the receiving direction.

[0011]

BEST MODE FOR CARRYING OUT THE INVENTION An embodiment of the present invention will be described below. Embodiment 1. 1 is an exploded perspective view showing the structure of an optical mount 1 according to Embodiment 1 of the present invention. The optical mount 1 is a mount for a reflecting mirror of a telescope mounted on a satellite.

In the figure, reference numeral 1 is an optical mount (honeycomb sandwich panel for satellite-mounted optical equipment). 2 is CF
RP (Carbon Fiber Reinforce)
It is a skin (hereinafter referred to as a CFRP skin) made of dPlastic, and is provided so as to cover both surfaces of the honeycomb core. One surface of the CFRP skin 2 serves as the upper surface of the optical mount 1, and a reflecting mirror is attached to this upper surface. CF
As the material of the RP skin 2, for example, high-strength carbon fiber M60J (manufactured by Toray) is used as the carbon fiber, and cyanate resin EX1515 (manufactured by Bryte) is used as the resin.

Reference numeral a is a through hole for reflected light, which is provided at the center of the CFRP skin 2. The passage hole a is formed to allow the reflected light from the reflecting mirror to pass therethrough and reach the analysis device (not shown) installed below the optical mount. Reference numeral b is a support hole for supporting a truss (not shown) which constitutes a telescope on which a reflecting mirror is mounted.
The FRP skin 2 is provided at three locations at equal intervals on the peripheral edge thereof.

Reference numeral 3 denotes a honeycomb core made of CFRP (hereinafter referred to as CFRP honeycomb core), which is a central material of the honeycomb sandwich panel. As the CFRP honeycomb core 3, for example, UCF-83-1 / 4-3.0
(Made by YLA) is used. UCF-83-1 / 4-3.0
Has a density of 0.056 g / cm ³ , an L-direction shear strength of 1000 kPa, and a W-direction shear strength of 483 kPa.
The thermal expansion coefficient is about 1 ppm / K.

The honeycomb core has a honeycomb-like structure in which a large number of hexagonal cells are gathered. Due to this structure, the honeycomb core has different shear strength depending on the direction. Details will be described in the third embodiment.

Reference numeral A denotes a passage hole for reflected light, which is formed in the central portion of the CFRP honeycomb core 3 like the passage hole a in the skin 2. The passing holes a and A of the CFRP skin 2 and the CFRP honeycomb core 3 are provided at positions where they overlap. B is a support hole for the truss, which is provided at three locations on the peripheral edge of the CFRP honeycomb core 3. When the CFRP skin 2 and the CFRP honeycomb core 3 are overlapped with each other, the support hole B is provided at a position overlapping the support hole b.

Next, an example of a method of forming the optical mount 1 will be described. First, a sheet (referred to as a prepreg) in which the high strength carbon fiber M60J is impregnated with the cyanate resin EX1515 is prepared. Volume ratio of carbon fiber to total volume of prepreg (fiber volume content)
Is adjusted to be 50 to 60%. Next, 6 to 8 sheets of this prepreg are stacked. 120 on stacked prepreg
It is cured by applying heat of about ℃ and pressure of about 3 atm. The cured prepreg is cut into a required size and shape to form a passage hole a and a support hole b, and a CFR
P skin 2 is formed.

Next, one UCF-83-1 / 4-3.0 is cut into a required size and shape to form a CFRP honeycomb core 3. Next, a thermosetting sheet adhesive is spread on the surface of the CFRP skin 2. CFR on it
P Honeycomb core 3 is placed. A CFRP skin 2 on which a sheet-like adhesive is spread is covered from above and bonded by applying heat and pressure to form an original shape of a honeycomb sandwich panel.

Alternatively, when the resin used as the material of the CFRP skin 2 is a resin that functions as an adhesive, C
After stacking the FRP skin 2, the CFRP honeycomb core 3, and the CFRP skin 2 in this order, heat and pressure are applied to bond them to form the original shape of the honeycomb sandwich panel.

Next, the original shape of the honeycomb sandwich panel is cut into a required size and shape, and the passage hole a and the support hole b are formed to form the optical mount 1.

As described above, the optical mount 1 according to the first embodiment
According to this, since it is composed of the CFRP skin 2 and the CFRP honeycomb core 3, the strength is high, the risk of distortion due to heat is small, and since no reinforcing member or the like is required, it is easy to manufacture and lightweight. The effect is obtained.

Next, a modification of the first embodiment will be described. In the formation of the CFRP skin 2, at the stage of stacking the prepregs, the prepregs are sequentially stacked so as to have a certain angle with respect to the prepreg placed (stacked) in front. This is because CFRP contains carbon fibers and has directionality, so that the CFRP skin 2 can have equal properties in all directions (hereinafter, also referred to as isotropic).

For example, this is set to 0 ° with reference to the direction in which the first piece of the prepreg is placed, and 0 °, 60 °, -6
Stack 6 sheets in the order of 0 °, -60 °, 60 °, 0 °. Alternatively, 0 °, 45 °, -45 °, 90
Eight sheets may be stacked in the order of °, 90 °, -45 °, 45 °, 0 °. In addition, any stacking method may be used as long as the CFRP skin 2 is isotropic.

In the CFRP skin 2 thus formed, the coefficient of thermal expansion in all directions horizontal to the surface could be set to a low value of -0.3 ppm / K. By combining the CFRP skin 2 having such properties with the honeycomb core 3 of the first embodiment, it has been conventionally used as a material for satellite-mounted optical equipment in all directions horizontal to the surface. It is possible to obtain a honeycomb sandwich panel having a low thermal expansion coefficient of Invar alloy, which is lower than 0.5 ppm / K. Therefore, high resolution (for example, 0.2 to 0.3 ")
The effect that it can be applied to an optical mount of an optical device having a degree) is obtained.

Since the other parts are the same as the contents described above, detailed description thereof will be omitted.

Embodiment 2. 2 and 3 are explanatory views of an optical mount 11 according to Embodiment 2 of the present invention. FIG. 2 is an exploded perspective view of the structure of the optical mount 11.
FIG. 3 is a side view of the optical pedestal 11, and is a view when the outer core is viewed as a center.

In FIGS. 2 and 3, reference numeral 11 is an optical mount (honeycomb sandwich panel for satellite-mounted optical equipment). Reference numeral 12 is a CFRP skin, which is provided so as to cover both surfaces of the honeycomb core. Reference numeral a denotes a through hole for reflected light, which is provided at the center of the CFRP skin 12. Reference numeral “b” is a support hole, and in order to support a truss (not shown) that constitutes a telescope equipped with a reflecting mirror, three holes are provided at equal intervals of 120 ° around the central portion on the peripheral edge of the CFRP skin 12. There is. As the material of the CFRP skin 12, for example, high-strength carbon fiber M60J (manufactured by Toray) is used as the carbon fiber, and cyanate resin EX1515 (Bryt) is used as the resin.
e) is used.

Reference numeral 13 is a CFRP honeycomb core. Thirteen
a is a lightweight core (inner honeycomb core), and 13b is a high-strength core (outer honeycomb core). A is a through hole for reflected light, which is formed at the center of the lightweight core 13a. CF
When the RP skin 12 and the CFRP honeycomb core 13 are overlapped with each other, the through holes a for reflected light and A are provided at a position where they overlap. B are truss support holes, which are provided at three locations on the peripheral edge of the CFRP honeycomb core 13 and on each of the high-strength cores (outer honeycomb cores) 13b. C
When the FRP skin 12 and the CFRP honeycomb core 13 are overlapped with each other, the support hole B is provided at a position overlapping the support hole b. The CFRP honeycomb cores 13 are these lightweight cores 13.
a and a high-strength core 13b. this house,
The high-strength core 13b is arranged in a portion of the entire CFRP honeycomb core 13 to which a load is stronger than other portions. The details will be described below.

In the entire honeycomb core 13, the portion to which the load is stronger than the other portions is, first, the portion supporting the truss structure of the telescope mounting the optical mount, that is, the vicinity of the supporting hole B. . This is because it is considered that the weight of the telescope structure will be concentrated on the portion supporting the truss when the satellite equipped with the telescope is launched. The second point is the junction point between the reflecting mirror and the optical mount 11.
In the case of the optical pedestal 11, the reflecting mirror is joined to the inside of each part supporting the truss at three positions by two-legged metal fittings provided on the reflecting mirror. The joint between the optical mount 11 and the metal fittings is also
Similarly, it is considered that the weight of the reflector is concentrated when the satellite is launched.

Therefore, the high-strength cores 13b are arranged at three positions of the support hole B and the peripheral portion of the CFRP honeycomb core 13 including the joining point of the reflecting mirror inside thereof. Each of the high-strength cores 13b is a CFRP honeycomb core 13
It is formed in a shape symmetrical with 120 ° about the center of the axis. By doing so, the CFRP honeycomb core 1
It is possible to make the portions of No. 3 that receive a heavy load equally high in strength.

As the high strength core 13b, for example, UCF is used.
-159-1 / 4-11 (made by YLA) is used. UCF
-159-1 / 4-11 has a density of 0.16 g / c
m ³ , the shear strength in the L direction is 2700 kPa or more, and the shear strength in the W direction is 3170 kPa or more. Lightweight core 1
3a is arranged in a portion of the CFRP honeycomb core 13 excluding the high-strength core 13b. As the lightweight core 13a, for example, UCF-83-1-4-3.0 (YLA
Manufactured) is used.

Next, an example of a method of forming the optical mount 11 will be described. First, the high strength carbon fiber M60J is impregnated with the cyanate resin EX1515 to prepare a prepreg. At the time of production, the fiber volume content is adjusted to be 50 to 60%. 6-8 sheets of this prepreg are piled up. The stacked prepregs are cured by applying heat of about 120 ° C. and pressure of about 3 atm. The cured prepreg is cut into a required size and shape to form a passage hole a and a support hole b and form a CFRP skin 12.

Next, a piece of UCF-83-1 / 4-3.0 is cut into a required size and shape to form a lightweight core 13.
a is formed. Similarly, UCF-159-1 / 4
11 is cut into a required size and shape to form a high-strength core 13b. Then, the lightweight core 13a and the three high-strength cores 13b are bonded together to form the CFRP honeycomb core 13.

Next, a thermosetting sheet adhesive is spread on the surface of the CFRP skin 12. The CFRP honeycomb core 13 is placed on it. A sheet of adhesive is applied to this C
The FRP skin 12 is covered from above and bonded by applying heat and pressure to form a honeycomb sandwich panel original form.

Alternatively, when the material of the CFRP skin 12 is a resin that functions as an adhesive, the CFRP skin 12,
After stacking the CFRP honeycomb core 13 and the CFRP skin 12 in this order, heat and pressure are applied to bond them together to form the original shape of the honeycomb sandwich panel.

Next, the original shape of the honeycomb sandwich panel is cut into a required size and shape, and the passage hole a and the support hole b are formed to form the optical mount 11.

As described above, the optical mount 1 according to the second embodiment
According to the first aspect, since the CFRP skin 12 and the CFRP honeycomb core 13 are used, the same effect as in the first embodiment can be obtained. Further, since the CFRP honeycomb core 13 is composed of the lightweight core 13a and the high-strength core 13b, the strength of the optical mount can be improved while maintaining the lightness.

Embodiment 3. 4 to 6 are explanatory views of the optical mount 21 according to the third embodiment of the present invention. Figure 4
FIG. 3 is a perspective view showing an exploded configuration of the optical mount 21. FIG. 5 is an enlarged view of the honeycomb structure for explaining the coordinate direction in the honeycomb core of the optical mount 21. FIG. 6 is a divisional layout view of the CFRP honeycomb core of the optical pedestal 21 when viewed from above, which is shown in contrast to the coordinate direction of the honeycomb core.

In FIG. 4, reference numeral 21 is an optical mount (honeycomb sandwich panel for satellite mounted optical equipment). 22
Is a CFRP skin, and is provided so as to cover both surfaces of the honeycomb core. a is a through hole for reflected light, and CFRP
It is provided at the center of the skin 22. Reference numeral b is a support hole, and in order to support a truss (not shown) that constitutes a telescope equipped with a reflecting mirror, it is provided at three locations at equal intervals of 120 ° around the central portion on the peripheral portion of the CFRP skin 22. There is. As the material of the CFRP skin 22, for example, high-strength carbon fiber M60J (manufactured by Toray) is used as the carbon fiber, and cyanate resin EX1515 (manufactured by Bryte) is used as the resin.

Reference numeral 23 is a CFRP honeycomb core. CF
As the RP honeycomb core 23, for example, UCF-83-
1 / 4-3.0 (made by YLA) is used. The CFRP honeycomb core 23 is composed of six split cores 23p arranged so that the direction in which the honeycomb core has a high shear strength and the direction in which the load applied to the optical mount 21 is strong coincide with each other.

Next, the difference in shear strength depending on the direction of the honeycomb core will be described with reference to FIG. As shown in FIG. 5, the honeycomb core has a honeycomb-like structure in which a large number of hexagonal cells are gathered. When the direction in which the hexagonal shape of this cell is visible is viewed as the front, the horizontal direction including a pair of parallel two sides of the cell is the L direction in FIG.
The direction perpendicular to the direction is defined as the W direction.

Further, the front side of the cell is z of the spatial coordinate xyz.
And the L direction is the x direction. And L and x
The direction of spatial coordinates that is perpendicular to the direction and is also perpendicular to the z direction is defined as the y direction. At this time, the shear stress generated in the L direction of the honeycomb core is xz shear stress in coordinates, and the shear stress generated in the W direction is yz shear stress.

The shear stress in the L direction of the honeycomb core is x
Although it is possible to receive a shear load on the z-plane, as for the shear stress in the W direction, as is clear from FIG. 5, there is no surface itself that receives the shear load. Therefore, in the honeycomb core, the shear stress in the L direction is higher than that in the W direction.

Therefore, by matching the L direction of the honeycomb core with the direction in which the shear load is strongly generated in the honeycomb core, it is possible to obtain an optical pedestal that is strong against shear stress, that is, has high strength.

As shown in FIG. 6, in the entire CFRP honeycomb core 23, a strong shear load is applied toward the center of the support hole B at three locations. Also, other parts are
A strong shear load is applied in the 90 ° direction with respect to the center direction. Therefore, the CFRP honeycomb core 23 was configured by arranging the six split cores 23p in which the direction in which the CFRP honeycomb core 23 receives a strong shear load and the L direction of the honeycomb core structure were aligned. Of the six CFRP honeycomb cores 23 divided and arranged, the three divided cores 23p at the peripheral portion including the vicinity of the support hole B are the CFRs.
The shape is set so that the center of the P core 23 serves as an axis of 120 °. As a result, the CFRP honeycomb core 23
It is possible to make the strength of the optical pedestal 21 including the same uniform in any part. Other parts are the same as those in the first and second embodiments, and thus detailed description thereof will be omitted.

Next, an example of a method of forming the optical mount 21 will be described. First, the high strength carbon fiber M60J is impregnated with the cyanate resin EX1515 to prepare a prepreg. At the time of production, the fiber volume content is adjusted to be 50 to 60%. 6-8 sheets of this prepreg are piled up. The stacked prepregs are cured by applying heat of about 120 ° C. and pressure of about 3 atm. The cured prepreg is cut into a required size and shape to form the passage hole a and the support hole b, and the CFRP skin 22 is formed.

Next, one UCF-83-1 / 4-3.0 is prepared, and the six split cores 23p are taken into consideration in consideration of the direction of the honeycomb core and the direction of the shear strength received by the honeycomb core.
To form. After that, the split cores 23p are pasted together,
The CFRP honeycomb core 23 is formed.

Next, a thermosetting sheet adhesive is spread on the surface of the CFRP skin 22. The CFRP honeycomb core 23 is placed on it. A sheet of adhesive is applied to this C
The FRP skin 22 is covered from above and heat and pressure are applied to bond the FRP skin 22 to form the original shape of the honeycomb sandwich panel.

Alternatively, when the material of the CFRP skin 22 is a resin that functions as an adhesive, the CFRP skin 22,
After stacking the CFRP honeycomb core 23 and the CFRP skin 22 in this order, heat and pressure are applied to bond them together to form a honeycomb sandwich panel original form.

Next, the original shape of the honeycomb sandwich panel is cut into a required size and shape, and the passage hole a and the support hole b are formed to form the optical mount 21.

As described above, the optical mount 2 of the third embodiment
According to the first aspect, since the CFRP skin 22 and the CFRP honeycomb core 23 are used, the same effect as in the first embodiment can be obtained. In addition, the CFRP honeycomb core 23 is divided into a plurality of pieces so that the direction in which the load is stronger than the other directions in the honeycomb core and the direction in which the honeycomb core receives the shearing force on the surface coincide with each other. Since it is configured as described above, there is an effect that the strength can be improved while keeping the lightness of the optical mount as it is.

[0052]

As described above, according to the present invention, since the honeycomb core and the skins covering both side surfaces of the honeycomb core are made of CFRP, the honeycomb sandwich panel for satellite mounted optical equipment is constructed. Since the strength of the optical mount is low, the possibility of distortion due to heat is small, and since no reinforcing member or the like is required, an optical mount that is easy to manufacture and lightweight can be obtained.

According to the present invention, since the honeycomb sandwich panel for satellite-mounted optical equipment is constructed so that the coefficient of thermal expansion is within ± 0.5 ppm / K in all directions horizontal to the surface, Since it is possible to obtain a honeycomb sandwich panel that is less likely to be distorted due to, there is an effect that it can be applied to an optical mount of an optical device having high resolution.

According to the present invention, the honeycomb core is arranged in the portion of the entire honeycomb core where the load is applied more strongly than in the other portions, and in the portion excluding this outer honeycomb core. The honeycomb sandwich panel for satellite mounted optical equipment is configured so that the outer honeycomb core and the inner honeycomb core have higher strength than the inner honeycomb core, so that an optical mount that can improve the strength can be obtained. There is an effect that is.

According to the present invention, the inner honeycomb core is
Since the honeycomb sandwich panel for an optical device mounted on a satellite is configured to be lightweight with respect to the outer honeycomb core, there is an effect that an optical pedestal that keeps lightness can be obtained.

According to the present invention, the direction in which the load is applied more strongly than the other directions in the entire honeycomb core and the direction in which the honeycomb core has the surface that receives the shearing force coincide with each other. In addition, because the honeycomb sandwich panel for satellite mounted optical equipment is configured to be configured by dividing the honeycomb core into a plurality of parts, it is possible to obtain an optical mount that can improve the strength while keeping the lightness as it is. effective.

[Brief description of drawings]

FIG. 1 is an exploded perspective view showing a configuration of an optical mount (honeycomb sandwich panel for an optical device mounted on a satellite) according to Embodiment 1 of the present invention.

FIG. 2 is an exploded perspective view showing a configuration of an optical mount according to Embodiment 2 of the present invention.

FIG. 3 is a side view of the optical mount according to the second embodiment when viewed from the center of a high-strength core.

FIG. 4 is an exploded perspective view showing a configuration of an optical mount according to Embodiment 3 of the present invention.

[Fig. 5] Fig. 5 is an enlarged view of the honeycomb structure for explaining the coordinate directions in the honeycomb core of the optical mount according to the third embodiment of the present invention.

FIG. 6 is a view of C of the optical mount according to the third embodiment of the present invention
It is a division | segmentation arrangement | positioning view when a FRP honeycomb core is seen from the top, and is a figure shown in contrast with the coordinate direction of the honeycomb core.

FIG. 7 is a perspective view of an optical mount of a satellite-mounted optical device using a conventional honeycomb sandwich panel.

[Explanation of symbols]

1,11,21 Optical mount (honeycomb sandwich panel for satellite mounted optical equipment), 2,12,22 CFRP skin, 3,13,23 CFRP honeycomb core, 13a
Light weight core (inner honeycomb core), 13b high strength core (outer honeycomb core), 23p split core, a, A passage hole, b, B support hole.

Claims (5)

[Claims] 1. A honeycomb sandwich panel for a satellite-mounted optical device, comprising a honeycomb core and skins covering both side surfaces of the honeycomb core, wherein the honeycomb core and the skin are made of CFRP. Honeycomb sandwich panel for onboard optical equipment. 2. A honeycomb sandwich panel for satellite-mounted optical equipment according to claim 1, wherein the coefficient of thermal expansion is within ± 0.5 ppm / K in all directions horizontal to the surface. 3. The honeycomb core includes an outer honeycomb core arranged in a portion of the whole honeycomb core where a load is applied more strongly than other portions, and an inner honeycomb arranged in a portion excluding the outer honeycomb core. The honeycomb sandwich panel for an optical device mounted on a satellite according to claim 1, wherein the honeycomb sandwich panel comprises a core, and the outer honeycomb core has a higher strength than the inner honeycomb core. 4. A honeycomb sandwich panel for satellite-mounted optical equipment according to claim 3, wherein the inner honeycomb core is lighter than the outer honeycomb core. 5. The honeycomb core is such that the direction in which the load is applied more strongly than the other directions in the entire honeycomb core and the direction in which the honeycomb core receives a shearing force on the surface are aligned. 2. The honeycomb sandwich panel for satellite-mounted optical equipment according to claim 1, wherein the honeycomb core is configured by being divided into a plurality of pieces.