JP2022018294A - Optical device and space vehicle using the same - Google Patents

Abstract

To provide an optical device capable of freely changing the direction in which radiation pressure of light acts.SOLUTION: An optical device 1 extends along a reference surface, and comprises a plurality of inclined surfaces and a light control part. The plurality of inclined surfaces are inclined with respect to the reference surface in different directions from each other. The light control part is configured to be able to individually and electrically change the magnitude of actions applied onto the plurality of inclined surfaces by light entering the optical device 1. In the optical device 1, the plurality of inclined surfaces have respectively different directions in which the incoming light applies the radiation pressure. Thus, the optical device 1 can freely change the direction of a driving force which is applied as the total of radiation pressures of light acting on the plurality of inclined surfaces by the light control part individually controlling the amplitude of actions applied onto each inclined surface.SELECTED DRAWING: Figure 2

Description

The present invention relates to an optical device and a spacecraft using the same.

Non-Patent Document 1 describes a solar sail "IKAROS" which is a spacecraft capable of navigating in outer space. A solar sail is a space sailing vessel with a sail that receives sunlight. In other words, the solar sail can navigate in outer space using the radiation pressure that the sail receives from sunlight as a driving force.

Further, the solar sail described in Non-Patent Document 1 can perform attitude control by utilizing the radiation pressure that the sail receives from sunlight. In this sail, a plurality of optical devices for attitude control are arranged along the outer edge of the light receiving surface. Each optical device can electrically change the magnitude of the radiation pressure applied from sunlight.

Therefore, in the solar sail described in Non-Patent Document 1, by making the magnitude of the radiation pressure received from the sunlight different for each optical device, the solar sail is rotated about an arbitrary axis along the light receiving surface of the sail. Can be done. As a result, in this solar sail, the orientation of the light receiving surface of the sail can be arbitrarily changed.

However, in the solar sail described in Non-Patent Document 1, since the radiation pressure of sunlight incident on the optical device acts only in the direction orthogonal to the light receiving surface of the sail, it may receive a force in the direction parallel to the light receiving surface. Have difficulty. Therefore, in this optical device, it is difficult to control the attitude and the position by using the force in the direction parallel to the light receiving surface.

On the other hand, Patent Document 1 discloses an optical device capable of applying the radiation pressure of sunlight in a direction parallel to the light receiving surface. In this optical device, by injecting sunlight into a prism surface inclined with respect to the light receiving surface, it is possible to give a component parallel to the light receiving surface to the force applied by the action of the radiation pressure of the sunlight.

Japanese Unexamined Patent Publication No. 2018-205483

Osamu Mori, Junichiro Kawaguchi (11 others) "IKAROS Development and Mission Overview" Journal of the Japan Society for Aeronautics and Astronautics Vol. 60, No. 8, pp. 283-289 (August 2012)

In the technique described in Patent Document 1, the component parallel to the light receiving surface on which the radiation pressure of sunlight can be applied by one optical device is limited to one direction. Therefore, in order to enable efficient attitude control and position control using forces in various directions parallel to the light receiving surface in this technology, it is necessary to configure a combination of a plurality of optical devices.

In view of the above circumstances, an object of the present invention is to provide an optical device capable of variously changing the direction in which the radiation pressure of light acts, and a spacecraft using the optical device.

In order to achieve the above object, the optical device according to one embodiment of the present invention extends along a reference plane and includes a plurality of inclined planes and an optical control unit.
The plurality of inclined surfaces are inclined in different directions with respect to the reference surface.
The optical control unit is configured to be individually electrically switchable in the magnitude of the action applied to the plurality of inclined surfaces by the light incident on the optical device.

In this optical device, the direction in which the radiation pressure of the incident light acts is different for each of the plurality of inclined surfaces. Therefore, in this optical device, the magnitude of the action applied to each inclined surface is individually controlled by the optical control unit, so that the direction of the driving force applied as the total radiation pressure of the light acting on the plurality of inclined surfaces can be varied. Can be changed to.

The optical device may have at least three inclined surfaces.
In this configuration, it becomes easy to control the direction in which the radiation pressure of light acts.

The plurality of inclined surfaces may have light reflectivity.
The plurality of inclined surfaces may have photorefractive properties.
The plurality of inclined surfaces may include an inclined surface having light reflectivity and an inclined surface having light refraction.

The optical control unit may be provided on each of the plurality of inclined surfaces and may have a plurality of liquid crystal layers formed of the polymer-dispersed liquid crystal.
The optical control unit may have a plurality of chromic devices having surfaces whose light reflectivity can be individually electrically switched, and the surface of the plurality of chromic devices may be configured as the plurality of inclined surfaces.
With this configuration, the function of the optical control unit can be realized.

A spacecraft according to an embodiment of the present invention includes a light receiving surface and the optical device extending along the light receiving surface.
By using the above optical device in a spacecraft, efficient attitude control and position control in the spacecraft become possible.

An object of the present invention is to provide an optical device capable of variously changing the direction in which the radiation pressure of light acts, and a spacecraft using the optical device.

It is a perspective view of the optical device which concerns on one Embodiment of this invention. FIG. 3 is a partial plan view showing an enlarged region R of FIG. 1 of the optical device. It is a partial cross-sectional view along the AA'line of FIG. 2 of the said optical device. It is a partial cross-sectional view along the BB'line of FIG. 2 of the said optical device. It is a partial cross-sectional view which shows the fine structure of the liquid crystal layer in the OFF state of the said optical device. It is a partial cross-sectional view which shows the fine structure of the liquid crystal layer in the ON state of the said optical device. It is a partial cross-sectional view which shows an example of the operation of the said optical device. It is a partial cross-sectional view which shows an example of the operation of the said optical device. It is a partial cross-sectional view which shows an example of the operation of the said optical device. It is a partial cross-sectional view which shows an example of the operation of the said optical device. It is a partial plan view which shows the other structural example of the said optical device. It is a partial plan view which shows the modification of the said optical device. It is a partial cross-sectional view along the CC'line of FIG. 12 which shows an example of the operation of the modification of the said optical device. It is a partial cross-sectional view which shows an example of the operation of the modification of the said optical device. It is a partial plan view which shows the other structural example of the modification of the said optical device. It is a perspective view of the spacecraft provided with the said optical device. It is a perspective view which shows an example of the control of a spacecraft using the said optical device. It is a perspective view which shows an example of the control of a spacecraft using the said optical device. It is a perspective view which shows an example of the control of a spacecraft using the said optical device. It is a perspective view which shows an example of the control of a spacecraft using the said optical device. It is a perspective view which shows an example of the control of a spacecraft using the said optical device. It is a perspective view which shows the structural example of the artificial satellite using the said optical device. It is a perspective view which shows the structural example of the solar sail using the said optical device. It is a perspective view which shows the structural example of the telescope system using the said optical device. It is a perspective view which shows the structural example of the interferometer system using the said optical device. It is a perspective view which shows the structural example of the interferometer system using the said optical device.

Hereinafter, embodiments of the present invention will be described with reference to the drawings. However, the present invention is not limited to the following embodiments. In the following description, expressions indicating directions such as up, down, left, and right shall indicate directions along the paper surface of the drawing unless otherwise specified.

[Optical device 1]
An optical device 1 according to an embodiment of the present invention will be described with reference to FIGS. 1 to 11. In addition, each drawing shows an X-axis, a Y-axis, and a Z-axis which are coordinate axes orthogonal to each other as appropriate. The X-axis, Y-axis, and Z-axis define a fixed coordinate system fixed to the optical device 1 and are common to all drawings.

FIG. 1 is a perspective view of an optical device 1 according to an embodiment of the present invention. The optical device 1 has a sheet-like outline extending along the XY plane which is a reference plane. The optical device 1 according to the present embodiment is configured so that the direction in which the radiation pressure of the incident light acting from the upper side to the lower side in the Z-axis direction acts can be changed in various ways.

FIG. 2 is a partial plan view showing an enlarged region R of FIG. 1 on the upper surface of the optical device 1. The optical device 1 includes a plurality of first optical elements Ep represented by a high-density dot pattern, a plurality of second optical elements Eq represented by a low-density dot pattern, and a plurality of third optical elements represented by a solid color. It has an optical element Er.

The optical elements Ep, Eq, and Er are arranged in pixels along the XY plane. Each of the optical elements Ep, Eq, and Er is formed in a flat plate shape and is inclined in different directions with respect to the XY plane. Each optical element Ep, Eq, Er is configured as a reflecting element capable of independently reflecting light incident from above.

Each optical element Ep, Eq, Er has a size several times larger than the wavelength in the infrared region in order to effectively receive the action of light in the visible and infrared regions where the action of radiation pressure is the strongest. Is enough. Therefore, in the optical device 1, by making each optical element Ep, Eq, Er into a compact structure, it is possible to form a thin and lightweight film in the Z-axis direction.

3 and 4 are partial cross-sectional views along a plane parallel to the Z axis of the optical device 1, FIG. 3 shows a cross section along the AA'line of FIG. 2, and FIG. 4B- The cross section along the B'line is shown. That is, FIG. 3 shows a vertical cross section of the first and second optical elements Ep and Eq, and FIG. 4 shows a vertical cross section of the first and third optical elements Ep and Er.

Each optical element Ep, Eq, Er has a common layered structure including an inner electrode layer 10, an outer electrode layer 20, and a liquid crystal layer 30, respectively. In each optical element Ep, Eq, Er, the inner electrode layer 10 is located on the lower side, the outer electrode layer 20 is located on the upper side, and the liquid crystal layer 30 is located between the inner electrode layer 10 and the outer electrode layer 20. ..

The inner electrode layer 10 of each optical element Ep, Eq, Er has an inclined surface Dp, Dq, Dr adjacent to the liquid crystal layer 30. The inclined surfaces Dp, Dq, Dr of each optical element Ep, Eq, Er are inclined in different directions with respect to the XY plane, and the unit normal vectors are inclined in different directions with respect to the Z axis shown in FIG. It has p, q, and r.

The unit normal vectors p, q, and r of the inclined surfaces Dp, Dq, and Dr each have components parallel to the XY plane. Specifically, the unit normal vector p has a negative component in the X-axis direction and a negative component in the Y-axis direction, and the unit normal vector q has a positive component in the X-axis direction and a negative component in the Y-axis direction. r has a positive component in the Y-axis direction.

Each of the inclined surfaces Dp, Dq, Dr of the inner electrode layer 10 of each optical element Ep, Eq, Er has light reflectivity and mirror-reflects incident light. As a result, each optical element Ep, Eq, Er reflects light incident on the inclined surfaces Dp, Dq, Dr of the inner electrode layer 10 in the direction corresponding to the direction of the unit normal vector p, q, r, respectively. Functions as a mirror.

In the optical device 1, the inner electrode layers 10 of the optical elements Ep, Eq, and Er that reflect light on each inclined surface Dp, Dq, and Dr cooperate with each other to form an acting portion that is affected by the radiation pressure of light. Will be done. In each optical element Ep, Eq, Er, the radiation pressure of the light reflected on the inclined surfaces Dp, Dq, Dr acts in the direction of the inverse vector of the unit normal vector p, q, r.

In each of the optical elements Ep, Eq, and Er, the outer electrode layer 20 has light transmission, and the light incident from above passes through the outer electrode layer 20 and is incident on the liquid crystal layer 30. The optical device 1 has an optical control unit capable of controlling the magnitude of the action applied to the inclined surfaces Dp, Dq, Dr of the inner electrode layer 10 through the liquid crystal layer 30 for each optical element Ep, Eq, Er. Have.

More specifically, the optical control unit of the optical device 1 is configured to be able to electrically and individually switch the light transmission of the liquid crystal layer 30 in each optical element Ep, Eq, Er. .. In each optical element Ep, Eq, Er, the inner electrode layer 10 and the outer electrode layer 20 form a pair of electrodes of the optical control unit, and are configured so that a voltage can be applied to the liquid crystal layer 30.

The inner electrode layer 10 of each optical element Ep, Eq, Er has a configuration in which light reflectivity on the inclined surfaces Dp, Dq, Dr and conductivity for obtaining an electrical connection to the liquid crystal layer 30 can be satisfactorily obtained. All you need is. As an example, the inner electrode layer 10 can be formed of, for example, a metallic material such as aluminum having a metallic luster and high conductivity.

Further, the inner electrode layer 10 may be configured by using an insulating film member such as a resin film. In this case, by forming a metal film in the region including the inclined surfaces Dp, Dq, Dr in the film member by a thin-film deposition method or the like, the region in which the metal film is formed can be imparted with light reflectivity and conductivity.

The outer electrode layer 20 of each optical element Ep, Eq, Er can be configured by using a transparent film member such as a polyimide film. In this case, by forming a transparent conductive film such as ITO (Indium Tin Oxide) on the film member, an electrical connection to the liquid crystal layer 30 can be obtained.

The optical device 1 has a common power supply PS in which a plurality of optical elements Ep, Eq, and Er are connected in parallel, and a plurality of switches SW provided for each of the plurality of optical elements Ep, Eq, and Er. The power supply PS is connected to the inner electrode layer 10 and the outer electrode layer 20 of each optical element Ep, Eq, Er via a switch SW.

In the optical device 1, the energization state by the power supply PS can be changed by the switch SW for each optical element Ep, Eq, Er. Therefore, in the optical device 1, whether or not a voltage is applied to the liquid crystal layer 30 sandwiched between the inner electrode layer 10 and the outer electrode layer 20 can be electrically switched for each optical element Ep, Eq, Er.

That is, in the optical device 1, the OFF state in which the voltage is not applied to the liquid crystal layer 30 and the ON state in which the voltage is applied to the liquid crystal layer 30 can be individually switched for each optical element Ep, Eq, Er. Is. 5 and 6 are partial cross-sectional views schematically showing the liquid crystal layer 30, FIG. 5 shows an OFF state, and FIG. 6 shows an ON state.

The liquid crystal layer 30 is formed of a polymer dispersed liquid crystal (PDLC: Polymer Dispersed Liquid Crystal). That is, the liquid crystal layer 30 has a structure in which the liquid crystal droplets 32 are dispersed in the polymer material 31. The liquid crystal molecules constituting the droplet 32 have anisotropy.

In the liquid crystal layer 30 of the optical elements Ep, Eq, and Er in the OFF state shown in FIG. 5, since the liquid crystal molecules in the droplet 32 are oriented in random directions, the light incident on the droplet 32 is diffusely reflected by the liquid crystal molecules. Be done. Therefore, in the optical elements Ep, Eq, and Er in the OFF state, the light transmittance of the liquid crystal layer 30 is low.

Therefore, in the optical elements Ep, Eq, and Er in the OFF state, the amount of light incident on the inclined surface Dp, Dq, Dr of the inner electrode layer 10 is small because the light is blocked by the diffuse reflection by the liquid crystal layer 30. Become. Therefore, in the optical elements Ep, Eq, Er in the OFF state, the action of the radiation pressure of light is not effectively applied to the inclined surfaces Dp, Dq, Dr of the inner electrode layer 10.

On the other hand, in the liquid crystal layer 30 of the optical elements Ep, Eq, Er in the ON state shown in FIG. 6, the liquid crystal molecules in the droplet 32 are oriented along the direction in which the voltage is applied, so that the liquid crystal molecules are oriented in the orientation direction. Light is easily transmitted through the droplet 32 along the line. Therefore, in the optical elements Ep, Eq, and Er in the ON state, the light transmittance of the liquid crystal layer 30 is high.

Therefore, in the optical elements Ep, Eq, and Er in the ON state, the amount of light transmitted through the liquid crystal layer 30 and incident on the inclined surfaces Dp, Dq, and Dr of the inner electrode layer 10 increases. Therefore, in the optical elements Ep, Eq, Er in the ON state, the action of the radiation pressure of light is effectively applied to the inclined surfaces Dp, Dq, Dr of the inner electrode layer 10.

The basic operation of the optical device 1 will be described with reference to FIGS. 7 to 10. In the following description, attention will be paid only to the partial cross sections of the optical elements Ep and Eq shown in the drawings along the XZ plane. However, in the optical device 1, any other partial cross section parallel to the Z axis of the optical elements Ep, Eq, Er can be understood in the same manner as described below.

In the state shown in FIG. 7, the optical element Ep is in the ON state and the optical element Eq is in the OFF state. Therefore, in the optical element Ep in the ON state, the light transmitted through the liquid crystal layer 30 is incident on the inclined surface Dp of the inner electrode layer 10. On the other hand, in the optical element Eq in the OFF state, light is blocked by the liquid crystal layer 30.

Therefore, in the portion of the optical device 1 shown in FIG. 7, the radiation pressure of light acts effectively on the optical element Ep. Therefore, in this optical device 1, the unit normal vector p has a positive component in the X-axis direction due to the action of radiation pressure of light reflected by the inclined surface Dp having a negative component in the X-axis direction in the portion. The driving force F is applied.

In the state shown in FIG. 8, the optical element Ep is in the OFF state and the optical element Eq is in the ON state. Therefore, in the optical element Ep in the OFF state, light is blocked by the liquid crystal layer 30. On the other hand, in the optical element Eq in the ON state, the light transmitted through the liquid crystal layer 30 is incident on the inclined surface Dq of the inner electrode layer 10.

Therefore, in the portion of the optical device 1 shown in FIG. 8, the radiation pressure of light acts effectively on the optical element Eq. Therefore, in this optical device 1, the unit normal vector q has a negative component in the X-axis direction due to the action of the radiation pressure of the light reflected by the inclined surface Dq having the positive component in the X-axis direction in the portion. The driving force F is applied.

As described above, in the optical device 1, the optical elements Ep and Eq that effectively act on the radiation pressure of light can be changed by switching between the ON state and the OFF state in the optical elements Ep and Eq. As a result, in the optical device 1, the driving force F can have both positive and negative components in the X-axis direction.

The direction of the driving force F applied to an arbitrary portion in the optical device 1 is determined by the sum of the inverse vectors of the unit normal vectors p, q, r of the optical elements Ep, Eq, Er in the ON state in the portion. Therefore, the optical device 1 can receive the driving force F according to the combination of the optical elements Ep, Eq, and Er in the ON state at any part.

As described above, in the optical device 1, the unit normal vectors p, q, and r include all four components of plus and minus in the X-axis direction and plus and minus in the Y-axis direction. As a result, the optical device 1 can receive a driving force F having an arbitrary component parallel to the XY plane at an arbitrary portion.

Next, in the states shown in FIGS. 9 and 10, the ON state and the OFF state of the optical elements Ep and Eq are switched between the left region and the right region divided into two in the X-axis direction. In the portion of the optical device 1 shown in FIGS. 9 and 10, the optical elements Ep and Eq are in a common energized state in each region on the left side and the right side.

Specifically, in the state shown in FIG. 9, the optical elements Ep and Eq on the left side are both in the ON state, and the optical elements Ep and Eq on the right side are both in the OFF state. Therefore, in the portion of the optical device 1 shown in FIG. 9, the radiation pressure of light acts effectively on the inclined surfaces Dp and Dq of the optical elements Ep and Eq on the left side.

In the optical elements Ep and Eq on the left side of the portion of the optical device 1 shown in FIG. 9, the radiation pressures of the light acting on the inclined surfaces Dp and Dq cancel each other out in the X-axis direction and act downward in the Z-axis direction. Therefore, in this portion, a downward driving force F is applied only to the region on the left side, so that a counterclockwise moment around the Y axis is generated.

In the state shown in FIG. 10, the optical elements Ep and Eq on the left side are both in the OFF state, and the optical elements Ep and Eq on the right side are both in the ON state. Therefore, in the portion of the optical device 1 shown in FIG. 10, the radiation pressure of light acts effectively on the inclined surfaces Dp and Dq of the optical elements Ep and Eq on the right side.

In the optical elements Ep and Eq on the right side of the portion of the optical device 1 shown in FIG. 10, the radiation pressures of light acting on the inclined surfaces Dp and Dq cancel each other out in the X-axis direction and act downward in the Z-axis direction. Therefore, in this portion, a downward driving force F is applied only to the region on the right side, so that a clockwise moment around the Y axis is generated.

As described above, in the optical device 1, the region in which the radiation pressure of light is effectively applied can be biased along the X-axis direction by switching the energized states of the optical elements Ep and Eq. As a result, the optical device 1 can generate moments in both directions about the Y axis.

Similarly, in the optical device 1, the region in which the radiation pressure of light is effectively applied can be biased in any direction along the XY plane by switching the energized state of the optical elements Ep, Eq, and Er. As a result, the optical device 1 can generate a moment centered on an arbitrary axis parallel to the XY plane.

In the optical device 1, the driving force F is large by increasing or decreasing the number of the optical elements Ep, Eq, Er in the ON state so that the direction of the driving force F applied as the total action of the radiation pressure of the light does not change. Only the optics can be changed. As a result, the optical device 1 can receive driving forces F of various sizes in various directions at any portion.

Further, in the optical device 1, the arrangement of the optical elements Ep, Eq, and Er can be changed in various ways, and each optical element Ep, Eq, and Er can be arranged irregularly. Further, in the optical device 1, for each optical element Ep, Eq, Er, for example, the configuration such as the unit normal vector p, q, r, the shape, and the size can be variously changed.

In addition, the number of optical elements in the optical device 1 in which the directions of the unit normal vectors are different from each other may be two or more, and can be appropriately determined depending on the application and the like. For example, the optical device 1 may have a configuration in which four optical elements Ep, Eq, Er, and Es are arranged as shown in FIG.

However, in the optical device 1, in order to obtain a driving force F having an arbitrary component parallel to the XY plane, it is preferable that there are three or more optical elements having different directions of unit normal vectors, and further, the unit method. It is more preferable that the line vector includes all four components of plus and minus in the X-axis direction and plus and minus in the Y-axis direction.

Further, the inclined surface of the optical device 1 does not have to be a reflecting surface as long as it is configured to be able to effectively receive the action of the radiation pressure of light. That is, the inclined surface of the optical device 1 may be a refracting surface having light refractive property or an absorbing surface having light absorbing property. As an example, the optical device 1A according to a modified example in which the inclined surface is a refracting surface will be described.

FIG. 12 is a partial plan view of the optical device 1A. 13 and 14 are partial cross-sectional views taken along the line CC'of FIG. 12 of the optical device 1A. In each of the optical elements Ep, Eq, and Er of the optical device 1A, a laminate of the inner electrode layer 10, the outer electrode layer 20, and the liquid crystal layer 30 is arranged along the XY plane. The inner electrode layer 10 has light transmission like the outer electrode layer 20.

That is, in the optical device 1A, a plurality of liquid crystal layers 30 provided on the optical elements Ep, Eq, and Er are arranged on the same plane parallel to the XY plane. Therefore, in the optical device 1A, the manufacturing cost can be reduced by using a series of liquid crystal panels including a plurality of liquid crystal layers 30 in the optical elements Ep, Eq, and Er.

Further, each optical element Ep, Eq, Er further has a transmission member 40 provided adjacent to the outer electrode layer 20 in the Z-axis direction. The transmission member 40 has light transmission and includes inclined surfaces Dp, Dq, and Dr facing downward in the Z-axis direction. In the optical device 1A, a plurality of transmissive members 40 are configured as acting portions that are affected by the radiation pressure of light on the inclined surfaces Dp, Dq, and Dr.

The plurality of transmissive members 40 provided on the optical elements Ep, Eq, and Er can be configured as, for example, a series of multi-faceted transmissive films subjected to multi-face processing. The multi-faceted transmissive film constituting the plurality of transmissive members 40 can be manufactured by using techniques such as press working and etching processing.

In the state shown in FIG. 13, the optical element Ep is in the ON state and the optical element Eq is in the OFF state. Therefore, in the optical element Ep in the ON state, the light transmitted through the liquid crystal layer 30 and further dropped by the transmitting member 40 is refracted by the inclined surface Dp. As a result, the driving force F is applied to the optical element Ep by the action of the radiation pressure of the light applied to the inclined surface Dp.

In the state shown in FIG. 14, the optical element Ep is in the OFF state and the optical element Eq is in the ON state. Therefore, in the optical element Eq in the ON state, the light transmitted through the liquid crystal layer 30 and further dropped by the transmitting member 40 is refracted by the inclined surface Dq. As a result, the driving force F is applied to the optical element Eq by the action of the radiation pressure of the light applied to the inclined surface Dq.

The optical device 1A preferably has a light-shielding portion B that blocks light between the optical elements Ep, Eq, and Er. This makes it possible to prevent the intrusion of light incident on the adjacent optical elements Ep, Eq, Er. For example, in the state shown in FIG. 13, it is possible to prevent the light incident on the optical element Ep from entering the optical element Eq.

The number of optical elements can be appropriately determined in the optical device 1A as well. For example, as shown in FIG. 15, four optical elements Ep, Eq, Er, and Es may be arranged. In the configuration shown in FIG. 15, since the conventional liquid crystal panel manufacturing technique can be used as it is, the manufacturing cost of the optical device 1A can be reduced.

[Control of Spacecraft 100 Using Optical Device 1]
The control of the spacecraft 100 using the optical device 1 according to the present embodiment will be described with reference to FIGS. 16 to 21. FIG. 16 is a perspective view of the spacecraft 100 provided with the optical device 1 according to the present embodiment. The spacecraft 100 is a cubic model assuming an arbitrary device that can operate in a region where sunlight is incident in outer space.

The optical device 1 can semi-permanently control the spacecraft 100 without consuming any resources such as propellants by using the radiation pressure of sunlight. Further, since the thrust generated by the radiant pressure of sunlight is as small as several nanonewtons, it is possible to control the spacecraft 100 with ultra-high accuracy, which is impossible with the optical device 1 in the past.

The optical device 1 is particularly advantageous for controlling the spacecraft 100 in a region where disturbance due to the radiation pressure of sunlight in outer space is dominant. As an example, the optical device 1 becomes a orbit dominated by Lagrange point orbits such as L1, L2, L3, L4, and L5, and orbital disturbances due to solar radiation pressure such as geostationary orbits, elliptical orbits, and interplanetary flight orbits. It is very useful for controlling the spacecraft 100 on which it rides.

In the spacecraft 100, the outer surface extending along the XY plane is configured as the light receiving surface 110 that receives the incident sunlight. The optical device 1 is provided along the light receiving surface 110 of the spacecraft 100. As shown in FIG. 16, the optical device 1 is divided into 16 segments S including a plurality of optical elements Ep, Eq, and Er along the X-axis and the Y-axis.

In the optical device 1, the direction in which the radiation pressure of sunlight acts is set for each segment S, and the energized state of each optical element Ep, Eq, Er so that the radiation pressure of sunlight acts in the set direction. Is controlled. As a result, in the optical device 1, the driving force F in various directions can be obtained as the total of the radiation pressure of the sunlight applied to all the segments S.

In the optical device 1, the number of segments S to be divided is not limited to 16, and can be arbitrarily determined. Further, in the optical device 1, it is not essential to divide the segment S into segments S including a plurality of optical elements Ep, Eq, Er. For example, the direction in which the radiation pressure of sunlight is applied is set for each optical element Ep, Eq, Er. It may be set in detail.

In the optical device 1 shown in FIG. 17, all the segments S are set so that the radiation pressure of light acts to the right along the X axis. Therefore, in the optical device 1 in this state, the driving force F is applied to the spacecraft 100 to the right by the action of the radiation pressure of sunlight, so that the spacecraft 100 can be moved to the right.

Similarly, in the optical device 1, all segments S are set so that the radiation pressure of sunlight acts to the left along the X axis, and the driving force F applied by the radiation pressure of sunlight acts on the space. The machine 100 can be moved to the left. In this way, the optical device 1 can move the spacecraft 100 in both directions along the X axis.

Further, in the optical device 1 shown in FIG. 18, all the segments S are set so that the radiation pressure of sunlight acts upward along the Y axis. Therefore, in the optical device 1 in this state, the driving force F is applied upward to the spacecraft 100 by the action of the radiation pressure of sunlight, so that the spacecraft 100 can be moved upward.

Similarly, in the optical device 1, all segments S are set so that the radiation pressure of sunlight acts downward along the Y axis, and the driving force F applied by the action of the radiation pressure of sunlight causes the space. The machine 100 can be moved downward. In this way, the optical device 1 can move the spacecraft 100 in both directions along the Y axis.

Further, in the optical device 1, all the segments S can be set so that the radiation pressure of sunlight acts inward along the Z axis. As a result, in the optical device 1, the driving force F is applied inwardly to the spacecraft 100 by the action of the radiation pressure of sunlight, so that the spacecraft 100 can be moved inward.

Here, assuming a plurality of spacecraft 100, by applying a driving force F toward the back along the Z axis to only some spacecraft 100, the part spacecraft 100 and other spacecraft are applied. The 100 and 100 can be moved relative to each other along the Z axis. That is, the optical device 1 can move the plurality of spacecraft 100 relative to each other along the Z axis.

As described above, the optical device 1 can apply the driving force F to the spacecraft 100 in any direction along the X-axis, the Y-axis, and the Z-axis. As a result, in the optical device 1, the spacecraft 100 can be moved in any direction in the XYZ space, that is, efficient position control with three translational degrees of freedom with respect to the spacecraft 100 becomes possible.

Next, in the optical device 1 shown in FIG. 19, each segment S is set so that the radiation pressure of sunlight acts in a direction in which the radiation pressure orbits clockwise. Therefore, in the optical device 1 in this state, the spacecraft 100 can be rotated clockwise by a moment about an axis parallel to the Z axis generated by the driving force F due to the action of the radiation pressure of sunlight.

Similarly, in the optical device 1, the spacecraft 100 can be rotated counterclockwise by setting each segment S so that the radiation pressure of sunlight orbits counterclockwise. In this way, the optical device 1 can rotate the spacecraft 100 in both directions about an axis parallel to the Z axis.

Further, in the optical device 1 shown in FIG. 20, the radiation pressure of sunlight is set to act inward with respect to the segment S in the left half region. Therefore, in the optical device 1 in this state, the spacecraft 100 is rotated in the direction shown in FIG. 20 by a moment centered on an axis parallel to the Y axis generated by the driving force F due to the action of the radiation pressure of sunlight. Can be done.

Similarly, in the optical device 1, the spacecraft 100 is rotated in the opposite direction to the above by setting the radiation pressure of sunlight to act inwardly with respect to the segment S in the right half region. Can be done. In this way, the optical device 1 can rotate the spacecraft 100 in both directions about an axis parallel to the Y axis.

Further, in the optical device 1 shown in FIG. 21, the radiation pressure of sunlight is set to act inwardly with respect to the segment S in the upper half region. Therefore, in the optical device 1 in this state, the spacecraft 100 is rotated in the direction shown in FIG. 21 by a moment centered on an axis parallel to the X axis generated by the driving force F due to the action of the radiation pressure of sunlight. Can be done.

Similarly, in the optical device 1, the spacecraft 100 is rotated in the opposite direction to the above by setting the radiation pressure of sunlight to act inwardly with respect to the segment S in the lower half region. be able to. In this way, the optical device 1 can rotate the spacecraft 100 in both directions about an axis parallel to the X axis.

As described above, the optical device 1 can generate a moment with respect to the spacecraft 100 in any direction centered on an axis parallel to the X-axis, the Y-axis, and the Z-axis. As a result, in the optical device 1, the spacecraft 100 can be rotated along an arbitrary axis, that is, efficient attitude control with three degrees of freedom of rotation with respect to the spacecraft 100 becomes possible.

Therefore, by using the optical device 1 according to the present embodiment, it is possible to control the spacecraft 100 with 6 degrees of freedom, which is a combination of 3 translational degrees of freedom and 3 rotational degrees of freedom. As a result, in the spacecraft 100 provided with the optical device 1 according to the present embodiment, precise position control and attitude control can be efficiently performed.

[Application example of optical device 1]
An application example of the optical device 1 according to the present embodiment will be described with reference to FIGS. 22 to 26. The optical device 1 according to the present embodiment is not limited to the following application examples, and can be used for any application in which the above functions can be effectively used. Further, the position and quantity of the optical device 1 according to the present embodiment can be appropriately changed.

FIG. 22 is a perspective view of the artificial satellite 200 provided with the optical device 1. The artificial satellite 200 has a main body 210 and a solar panel 220. The solar panel 220 extends to the outside of the main body 210 and generates electric energy by receiving the incident sunlight. The optical device 1 is provided along the outer surface of the main body 210.

The optical device 1 can perform position control for maintaining the artificial satellite 200 in a predetermined orbit, attitude control for directing the solar panel 220 toward the sun, and the like. The optical device 1 may be provided on the solar panel 220, or may be provided on both the main body 210 and the solar panel 220.

FIG. 23 is a perspective view of the solar sail 300 provided with the optical device 1. The solar sail 300 has a main body 310 and a sail 320. The sail 320 extends two-dimensionally around the main body 310 and obtains propulsive force by receiving the incident sunlight. The optical device 1 is provided on the surface of the sail 320.

The optical device 1 can perform position control for correcting the trajectory of the solar sail 300, attitude control for changing the direction of the sail 320 according to the traveling direction, and the like. The optical device 1 may be provided on the main body 310, or may be provided on both the main body 310 and the sail 320.

FIG. 24 is a perspective view showing a telescope system 400 using the optical device 1. The telescope system 400 includes a detector satellite 410 with a detector 411 and an optical system satellite 420 with an optical system 421. The optical device 1 is provided on the outer surface of the detector satellite 410 and the optical system satellite 420, respectively.

In the telescope system 400, the detector satellite 410 and the optical system satellite 420 that make a formation flight cooperate to function as one telescope. In the formation flight, when the distance between the satellites is sufficiently close, typically several km, the disturbance due to the radiation pressure of sunlight becomes dominant, so that the control by the optical device 1 is particularly effective.

The optical device 1 controls the position and attitude of the optical system satellite 420 so that the light in the direction to be observed is incident on the optical system 421, and the light incident on the optical system 421 is accurately focused on the detector 411. The position control and attitude control of the detector satellite 410 are performed so as to be performed. As a result, the telescope system 400 can generate an observation image in any direction.

In this way, by using the optical device 1, the relative position between the two satellites can be precisely controlled. Therefore, by applying the optical device not only to the telescope system 400 but also to, for example, coronography and exoplanet observation, it becomes possible to operate the optical device without consuming any resources such as propellants.

FIG. 25 is a perspective view of the interferometer system 500 using the optical device 1. The interferometer system 500 has a plurality of receiving satellites 510 equipped with an antenna 511. The antenna 511 is configured to be able to receive radio waves such as microwaves and millimeter waves. The optical device 1 is provided on the outer surface of each receiving satellite 510.

In the interferometer system 500, a plurality of receiving satellites 510 in formation flight cooperate to function as one interferometer. The optical device 1 controls the position and attitude of each receiving satellite 510 so that the desired information can be obtained by the radio wave received by each receiving satellite 510 by the antenna 511.

FIG. 26 is a perspective view of the interferometer system 600 using the optical device 1. The interferometer system 600 includes a detector satellite 610 and a plurality of optical system satellites 620 including an optical system 621. The optical device 1 is provided on the outer surface of the detector satellite 610 and the plurality of optical system satellites 620, respectively.

In the interferometer system 600, the detector satellite 610 and the plurality of optical system satellites 620 that make a formation flight cooperate to function as one interferometer. The optical device 1 controls the position and attitude of the detector satellite 610 and each optical system satellite 620 so that the light incident on each optical system 621 is focused on the detector 611.

In this way, by using the optical device 1, the relative positions between the plurality of satellites can be precisely controlled, and the structure can be established as if the plurality of satellites / parts were not connected. Therefore, by applying the optical device to, for example, a virtual structure or a gravitational wave interferometer, it becomes possible to operate the optical device without consuming any resources such as a propellant.

Further, by using the optical device 1, it is possible to drive with a small amount of electric power, so that it is possible to realize attitude control and position control of a microsatellite whose consumption resources such as propellants and power generation amount are limited. Further, by manufacturing the optical device 1 using a liquid crystal display that can be mass-produced, it is possible to realize a formation flight of a microsatellite at low cost.

As described above, the optical device 1 according to the present embodiment can be particularly suitably used for controlling various spacecraft, but can also be used for other purposes. For example, the function of the optical device 1 according to the present embodiment that can change the optical path of the reflected light due to the inclined surface depending on the energized state of the optical element can be applied to various devices.

For example, in a projector using the optical device 1, it is possible to change the direction in which an image is projected in an instant. Further, in the sign using the optical device 1, the direction in which the visual information is presented can be quickly switched. Further, in the lighting equipment using the optical device 1, the direction of irradiating the light can be easily and quickly changed.

[Other embodiments]
Although each embodiment of the present invention has been described above, the present invention is not limited to the above-described embodiment, and it goes without saying that various modifications can be made without departing from the gist of the present invention.

As an example, the optical control unit of the optical device of the present invention is not limited to the configuration using the liquid crystal layer. For example, the optical control unit may be configured to use an optical shutter capable of blocking light. Examples of the optical shutter include a liquid crystal optical shutter and a piezoelectric optical shutter. The liquid crystal optical shutter typically has a configuration in which a liquid crystal layer is sandwiched between two polarizing plates having orthogonal polarization axes. As the liquid crystal optical shutter method, for example, a TN (Twisted Nematic) method, a VA (Vertical Alignment) method, and an IPS (In-Plane-Switching) method can be adopted.

Further, the optical control unit is not limited to a configuration in which the light transmission to a plurality of inclined surfaces can be changed. For example, the optical control unit may be configured by applying electrochromism, thermochromism, or the like, and using a chromic device having a surface whose light reflectivity can be individually electrically switched. In such an optical control unit, by configuring the surfaces of the plurality of chromic devices as inclined surfaces, the light reflectivity of each inclined surface can be electrically switched individually.

Further, in the optical device of the present invention, the types of the plurality of inclined surfaces provided on the working portion of each optical element may be different from each other. For example, the optical device may be configured by combining an inclined surface having light reflectivity and an inclined surface having light refraction property. This enables the optical device to perform attitude control and position control with higher accuracy.

In addition, in the optical device 1, the acting portion affected by the radiation pressure of light on the inclined surface may not be composed of a plurality of inner electrode layers 10 divided for each optical element. For example, the working portion of the optical device 1 may be configured as an integral member provided with an inclined surface for each optical element.

1 ... Optical device 10 ... Inner electrode layer 20 ... Outer electrode layer 30 ... Liquid crystal layer 31 ... Polymer material 32 ... Droplet Ep, Eq, Er ... Optical element Dp, Dq, Dr ... Inclined surface p, q, r ... Unit Normal vector PS ... Power switch ... Switch

Claims (8)

An optical device that extends along a reference plane
A plurality of inclined surfaces inclined in different directions with respect to the reference surface, and
An optical control unit configured to be able to individually electrically switch the magnitude of the action applied to the plurality of inclined surfaces by the light incident on the optical device.
An optical device equipped with. The optical device according to claim 1.
The optical device is an optical device having at least three inclined surfaces. The optical device according to claim 1 or 2.
The plurality of inclined surfaces are optical devices having light reflectivity. The optical device according to claim 1 or 2.
The plurality of inclined surfaces are optical devices having photorefractive properties. The optical device according to claim 1 or 2.
The plurality of inclined surfaces are an optical device including an inclined surface having light reflectivity and an inclined surface having light refraction. The optical device according to any one of claims 1 to 5.
The optical control unit is an optical device provided on each of the plurality of inclined surfaces and having a plurality of liquid crystal layers formed of a polymer-dispersed liquid crystal. The optical device according to any one of claims 1 to 3.
The optical control unit has a plurality of chromic devices having a surface whose light reflectivity can be individually electrically switched.
An optical device in which the surface of the plurality of chromic devices is configured as the plurality of inclined surfaces. A light receiving surface and an optical device extending along the light receiving surface are provided.
The optical device is
A plurality of inclined surfaces inclined in different directions with respect to the light receiving surface,
An optical control unit configured to be able to individually electrically switch the magnitude of the action applied to the plurality of inclined surfaces by the light incident on the optical device.
Spacecraft with.

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