Antenna system and antenna array system

Abstract

To provide an antenna system.SOLUTION: An antenna system exhibits a function of transmitting and receiving electromagnetic waves generated by some of electroconductive constituents and an electricity supply part, by connecting the electricity supply part to some of the electroconductive constituents which an artificial satellite and a rocket loaded with the artificial satellite or the like already have so as to operate an antenna. It is preferable that both ends of some of the constituents are ground so that the antenna functions as a loop antenna, or one sides of some of the constituents are ground so that the antenna functions as a monopole antenna, or L-shape conductive parts are provided on some of the constituents so that the antenna functions as an L-shaped antenna, or F-shaped conductive parts are provided on some of the constituents so that the antenna functions as a reverse F antenna.SELECTED DRAWING: Figure 1A

Description

Technical Field

[0001] The present invention relates to an antenna system and an antenna array system.

Background Art

[0002] In population structures, antennas, which often become protrusions for functional or landscape purposes due to their shape, are often disliked. The antenna structure required for lower frequency antennas becomes larger, and its mountability becomes difficult.

[0003] Situations where such problems occur include, for example, urban design such as residential buildings, and antenna placement in moving objects such as various types of mobility and drones. In cases where they are often designed separately, the location of the antenna installation is adjusted later, and the antenna placement for communication and sensing is restricted, resulting in a problem of generating a dead zone. In particular, in the case of devices such as mobile phones where base stations are abundant and high frequency conversion and miniaturization are easy, rather than in cases where isolation from land is required and long-distance communication and low frequency regions are necessary in a limited environment, the problem becomes prominent. For example, in the case of artificial satellites, additional installation and maintenance are also impossible.

[0004] To address such problems, in natural parks where landscape is highly regarded, the exterior of the antenna can be camouflaged in the surrounding environment with a material that can be radio-wave ignored (see, for example, Non-Patent Document 1). In the case of a building group, for the radio-wave shadow areas that become dead zones, it is possible to add communication relay points or wired networks, or install additional relay antennas or reflectors so that they can reach by being radio-wave reflected (see, for example, Non-Patent Document 2). In cases where long-distance communication is required in a limited environment, unique attempts such as seawater antennas applying drainage in ships have been reported (see, for example, Non-Patent Document 3). Furthermore, in the case of artificial satellites, which are a restricted environment, a method of providing gaps such as grooves and holes in the artificial satellite structure to form a slot antenna has been reported (see, for example, Patent Document 1).

Prior Art Documents

Patent Document

[0005]

Patent Document 1

Non-Patent Document

[0006]

Non-Patent Document 1

Non-Patent Document 2

Non-Patent Document 3

Summary of the Invention

Problems to be Solved by the Invention

[0007] However, in cases where it is difficult to additionally install an antenna and it is also difficult to camouflage, or when there are no available surrounding resources and gaps such as grooves or holes cannot be provided in existing structures, the above means have limitations in solving problems.

[0008] The present invention has been made in consideration of such circumstances, and one of its objectives is to provide an antenna system and an antenna array system that can further improve the means for forming an antenna in a limited environment.

Means for Solving the Problems

[0009] The present invention is an invention made to solve the above problems, and as a means, it has the following configuration. (1) An antenna system according to one embodiment of the present invention is characterized in that a power supply unit is connected to a part of an electrically conductive component already possessed by an artificial satellite or a rocket carrying the artificial satellite so as to operate as an antenna, and the part of the electrically conductive component and the power supply unit exhibit a function of transmitting and receiving electromagnetic waves.

Effects of the Invention

[0010] According to one aspect of the present invention, by connecting a power supply unit to a part of an electrically conductive component already possessed by an artificial satellite or a rocket so as to operate as an antenna, an antenna having a function of transmitting and receiving electromagnetic waves by the part of the electrically conductive component and the power supply unit can be configured. Since a part of an artificial satellite or a rocket can be used as an antenna, an antenna can be added as necessary to an artificial satellite, a rocket, etc. to which an antenna cannot be added by additional installation or maintenance.

Brief Description of the Drawings

[0011]

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Mode for Carrying Out the Invention

[0012] "First Embodiment" Hereinafter, regarding the antenna system according to the first embodiment of the present invention, details will be described with an example, but the present invention is not limited to the embodiments described below. FIG. 1A shows an example in which the antenna system S1 of the first embodiment is applied to an existing structure, a satellite A1. This satellite A1 has a vertically long three-dimensional satellite body 2, a panel 3 is provided on one side of the bottom of the satellite body 2, a panel 4 is provided on the other side of the bottom, a first solar cell paddle 5 is provided on one side of the upper part of the satellite body 2, and a second solar cell paddle 6 is provided on the other side of the upper part. This satellite A1 is launched into space such as a sun-synchronous quasi-circular orbit at an altitude of 600 to 700 km with the bottom side of the satellite body 2 facing the ground, for example.

[0013] The panel 3 is, for example, a synthetic aperture radar in the shape of a rectangular plate in plan view provided so as to face the ground from space. The panel 4 is, for example, a multi-antenna in which dipole antennas are arrayed. The panel 3 has one long side 3a connected to the bottom side of the satellite body 2 and the other long side 3b located on the side away from the satellite body 2 and facing the ground. In this embodiment, an electrically conductive linear support 8 is provided so as to connect the upper part of the satellite structure 2 and the long side 3b side of the panel 3. This support 8 is provided in the form of a metal wire drawing a rectangular loop, and one end of each of the wires (linear structures) 8a, 8b constituting the long side of the rectangular loop is fixed to the upper part of the satellite structure 2, and the other ends of the wires 8a, 8b are fixed to the long side 3b side of the panel 3.

[0014] The panel 3 is supported on the bottom side of the satellite structure 2 at its long side 3a side, and is supported by the wires 8a, 8b at its long side 3b side. The tip sides of the wires 8a, 8b are connected by a wire (linear structure) 8c constituting the short side of the support 8. The base ends of the wires 8a, 8b are connected by a wire (linear structure) 8d incorporating the power supply unit 10. The power supply unit 10 is fixed to, for example, the upper side of the satellite structure 2. Further, the wires 8c, 8d may be configured of a wiring part such as a harness.

[0015] As shown in FIG. 1A, an antenna system S1 shown in FIGS. 1A and 1B that functions as a loop antenna is constructed by providing the electrically conductive wires 8a, 8b, 8c, 8d and the power supply unit 10. In the artificial satellite A1, the wires 8a, 8b for supporting the panel 3 are essential members. By utilizing this member, making the wires 8a, 8b electrically conductive, connecting the tip sides of the wires 8a, 8b with an electrically conductive wire 8c, connecting the base ends of the wires 8a, 8b with an electrically conductive wire 8d, and providing the power supply unit 10, it is possible to effectively utilize the members originally provided in the artificial satellite A1 to construct a loop antenna. An artificial satellite is a device (structure) placed in an environment where means such as adding an antenna later cannot be adopted once it is launched into space. By constructing the antenna system S1 as shown in FIG. 1A, it is possible to effectively utilize the general members provided in the artificial satellite A1 and provide an antenna.

[0016] "Second Embodiment" Figure 2A shows an example in which the antenna system S2 of the second embodiment is applied to an artificial satellite B1, which is an existing structure. This artificial satellite B1 has the same basic structure as the artificial satellite A1 shown in Figure 1A. It has a satellite body 2, includes a panel 3 and a panel 4, and is equipped with a first solar cell paddle 5 and a second solar cell paddle 6. In the antenna system S2 of the second embodiment, a ground G is provided on a part of the side surface 2a of the satellite body 2 as a part of the structure, and a power supply unit 10 is provided on the side where grounding is possible. An antenna system S2 is constructed that functions as a monopole antenna equipped with a wire 8b connected to the power supply unit 10. In the example shown in the figure, a ground G is provided on the side surface 2a between the panel 3 and the panel 4 in the satellite body 2.

[0017] The wire 8a is connected to the side surface of the satellite body 2 where the ground G is not provided and the long side 3b side of the panel 3. The wire 8b may have a structure in which neither end is electrically grounded to the surroundings, or a structure in which only one side is electrically grounded. The wire 8b used as an antenna does not need to be electrically conductive over its entire length, and it is sufficient if the length corresponding to the operating frequency is electrically conductive. As an example, in Figure 2A, a configuration can be adopted in which the thickly shown part of the wire 8b is electrically conductive.

[0018] By providing the electrically conductive wire 8b, the power supply unit 10, and the ground G connected as shown in Figure 2A, it functions as a monopole antenna, and the antenna system S2 shown in Figure 2B is constructed as a circuit. An artificial satellite is a device (structure) placed in an environment where it is not possible to adopt means such as adding an antenna after it is launched into space once. By constructing the antenna system S2 as shown in Figure 2A, general members originally provided in the artificial satellite 1 can be effectively utilized to provide an antenna.

[0019] "Third Embodiment" FIG. 3A shows an example in which the antenna system S3 of the third embodiment is applied to an artificial satellite C1, which is an existing structure. This artificial satellite C1 has the same basic structure as the artificial satellite A1 shown in FIG. 1A. It has a satellite body 2, includes a panel 3 and a panel 4, and is provided with a first solar cell paddle 5 and a second solar cell paddle 6. For the antenna system S3 of the third embodiment, a power supply unit 10 can be provided via a ground G on the side of the satellite body 2 where grounding is possible, and an antenna system S3 can be constructed as an L-shaped antenna including wires (linear structures) 8e and 8b connected to the power supply unit 10. In the example shown in the figure, a ground G is provided on the side surface 2a between the panel 3 and the panel 4. The wire 8a and the wire 8b can be attached to the side surface adjacent to the side surface 2a where the ground G is provided on the outer peripheral surface of the satellite body 2. An artificial satellite is a device (structure) placed in an environment where it is not possible to employ means such as adding an antenna after it has been launched into space once. By constructing the antenna system S3 as shown in FIG. 3A, it is possible to effectively utilize the members originally provided in the artificial satellite C1 and provide an antenna.

[0020] As shown in FIG. 3A, by including the electrically conductive wires 8e and 8b, the power supply unit 10, and the ground G that are connected, it functions as an L-shaped antenna, and the antenna system S3 shown in FIG. 3B is constructed as a circuit. An artificial satellite is a device (structure) placed in an environment where it is not possible to employ means such as adding an antenna after it has been launched into space once. By constructing the antenna system S3 as shown in FIG. 3A, it is possible to effectively utilize the members originally provided in the artificial satellite 1 and provide an antenna.

[0021] "Fourth Embodiment" FIG. 4A shows an example in which the antenna system S4 of the fourth embodiment is applied to an artificial satellite D1, which is an existing structure. This artificial satellite D1 has the same basic structure as the artificial satellite 1 shown in FIG. 1A. It has a satellite body 2, includes a panel 3 and a panel 4, and is provided with a first solar cell paddle 5 and a second solar cell paddle 6. The antenna system S4 of the fourth embodiment is configured such that a power supply unit 10 is provided via a ground G on the side of the satellite structure 2 where grounding is possible, and includes wires (linear structures) 8b and 8e connected to the power supply unit 10, and an inverted-F antenna including an L-shaped wiring part (linear structure) 8f that connects the connection positions of the wires 8b and 8e to the ground G. In the example shown in the figure, a ground G is provided on the side surface 2a between the panel 3 and the panel 4 in the satellite structure 2.

[0022] A circuit shown in FIG. 4B can be configured as an inverted-F antenna. The wire 8a can be attached to a side surface adjacent to the side surface 2a where the ground G is provided on the outer peripheral surface of the satellite structure 2. A satellite is a device placed in an environment where it is impossible to adopt means such as adding an antenna after it is launched into space once. By constructing the antenna system S4 as shown in FIG. 4A, the members originally provided in the artificial satellite 1 can be effectively utilized to provide an antenna.

[0023] As shown in FIGS. 4A and 4B, an antenna system S4 that functions as an inverted-F antenna is constructed by including the electrically conductive wires 8b and 8e, the wiring part 8f, the power supply unit 10, and the ground G that are connected. A satellite is a device (structure) placed in an environment where it is impossible to adopt means such as adding an antenna after it is launched into space once. By constructing the antenna system S4 as shown in FIG. 4A, the members originally provided in the artificial satellite 1 can be effectively utilized to provide an antenna.

[0024] "Fifth Embodiment" FIG. 5 shows an example in which the antenna system S5 of the fifth embodiment is applied to an existing structure, an artificial satellite E1. This artificial satellite E1 has the same basic structure as the artificial satellite A1 shown in FIG. 1A. It has a satellite structure 2, includes a panel 3 and a panel 4, and includes a first solar cell paddle 5 and a second solar cell paddle 6. The antenna system S5 of the fifth embodiment provides a power supply unit 10 on the upper side of the side surface 2a of the satellite structure 2 via an insulating layer, connects a wire 8b to the power supply unit 10, and provides conductive layers 12 and 13 on the upper side surface of the satellite structure 2 where the power supply unit 10 is not provided and on the side surface adjacent to the side surface. The conductive layer 12 and the power supply unit 10 are connected by a wiring part (linear structure) 15, the tip of the wire 8b and the conductive layer 13 are connected by a wiring part (linear structure) 16, and the conductive layer 13 and the conductive layer 12 are connected by a wiring part (linear structure) 17. With the above configuration, the antenna system S5 can be constructed.

[0025] The antenna system S5 shown in FIG. 5 has a power supply unit 10, and a loop antenna is formed by the wire 8b, the wiring part 16, the conductive layer 13, the wiring part 17, the conductive layer 12, and the wiring part 15. The example shown in FIG. 5 is an example estimated and applied in the case where, in an electrical test of a satellite or the like, when there is an antenna effect in the entire system due to electromagnetic interference in the common mode in the electronic devices mounted on the satellite, or when there is an operating frequency through a part where the antenna effect is likely to occur. In the electromagnetic compatibility test of a satellite, in order to prevent the formation of an antenna partially or entirely and the electronic devices from receiving unnecessary noise, measures such as dividing the ground or sufficiently sandwiching insulators may be taken inside the satellite. FIG. 5 has a portion where an insulation treatment is performed to prevent the common mode. A power supply unit 10 is provided for the insulation treatment unit, and the configuration shown in FIG. 5 can be adopted to construct a loop antenna. Once a satellite is launched into space, it is generally a device (structure) placed in an environment where means such as adding an antenna later cannot be adopted unless it is devised to be able to flexibly vary the operating frequency having software radio and a broadband antenna. If each antenna part has a plurality of operating frequencies or broadband characteristics, software radio may be adopted for all the power supply units in the present invention to make the operating frequency switchable. In the structure of FIG. 5, by utilizing the frequency band of the noise received by the electronic devices mounted on the artificial satellite E1 in the common mode and forming a loop antenna with the power supply unit 10, an antenna function is additionally implemented.

[0026] By the way, in the first to fifth embodiments described so far, the antennas were configured using the wires 8a and 8b connected between the satellite structure 2 and the panel 3. However, the elements for configuring the antennas are not limited to these wires. Generally, artificial satellites are provided with wires for deployment operations of various devices and wires for release operations. Therefore, it is also possible to configure an antenna using these wires for deployment operations and wires for release operations. In addition, since a support structure may be provided on a part of the satellite structure 2, a part of this support structure can also be applied to any of the antenna systems S1 to S5 having the above-described structures.

[0027] "Sixth Embodiment" FIG. 6 shows an example in which the antenna system S6 of the sixth embodiment is applied to an artificial satellite F1 which is an existing structure. This artificial satellite F1 has the same basic structure as the artificial satellite A1 shown in FIG. 1A. It has a satellite structure 2, includes a panel 3 and a panel 4, and includes a first solar cell paddle 5 and a second solar cell paddle 6. In the satellite structure 2, the base ends of the wires 8a and 8b are fixed to the side surface adjacent to the side surface 2a between the panel 3 and the panel 4, and the tip ends of the wires 8a and 8b are fixed to the long side 3b side of the panel 3.

[0028] The example shown in FIG. 6 is a structure in which the panel 3, the first solar cell paddle 5, and the second solar cell paddle 6 are deployed after being launched, and is an example suitable for a case where wiring parts such as harnesses necessary for wiring cannot be provided on the panel 3. In the satellite structure 2, a power supply unit 10 and an antenna 20 having a wireless transmission / reception function or serving as a low-gain antenna are mounted on the upper part of the side surface 2a located between the panel 3 and the panel 4. In this example, the antenna 20 is configured to be able to irradiate the entire back surface (upper surface) of the panel 3 with radio waves or receive electromagnetic waves from the back surface of the panel 3, and after receiving on the back surface of the panel 3, re-transmit from the front surface of the panel 3, or re-transmit the signal received on the front surface of the panel 3 from the back surface of the panel 3 to the antenna 20, so that the panel 3 can operate as a high-gain transmit antenna without a harness. The antenna 20 may be an omnidirectional antenna or may have an antenna gain so as to have sensitivity only on the back surface of the panel 3.

[0029] The example shown in FIG. 6 is applicable to an artificial satellite when the panel 3 can be mounted on the structure 2 of the artificial satellite but the panel 3 is a deployable panel on which an antenna harness cannot be mounted. Once an artificial satellite is launched into space, generally, it is a device (structure) placed in an environment where means such as adding an antenna later cannot be adopted unless a device is devised to enable flexible variable operation frequencies with software radio and a broadband antenna. If each antenna unit has a plurality of operating frequencies or broadband characteristics, software radio may be adopted for all the power supply units in the present invention to enable switching of the operating frequencies. An antenna system S6 that functions as a transmit antenna can be constructed by wirelessly transmitting to the back surface (upper surface) of the panel 3 with the antenna 20 provided on the satellite structure 2 of the artificial satellite F1 and re-transmitting from the front surface (the surface on the ground side) of the panel 3 after receiving on the back surface (upper surface) of the panel 3. When functioning as described above, as shown in FIG. 6, by constructing a plurality of laminated structures including a transmit layer, a bias layer, a receive layer, a diode, etc. across the back surface and the front surface of the panel 3, the transmit antenna can be used as a planar array antenna to realize the transmission / reception functions as described above. The panel 3 can transmit / receive or re-transmit / receive partially or over the entire surface or the entire back surface.

[0030] "Seventh Embodiment" FIG. 7 shows an example in which the antenna system S7 of the seventh embodiment is applied to an artificial satellite G1 which is an existing structure. This artificial satellite G1 has a box-shaped satellite body 22, has a propulsion jet thruster 23 on the bottom side of the satellite body 22, and has a first solar cell paddle 25 and a second solar cell paddle 26 on the side of the satellite body 22. The jet thruster 23 is made of, for example, ceramic. A gas injection engine or an ion injection engine or the like is mounted inside the satellite body 22, and an injection flow 27 such as a gas injection flow or an ion injection flow is ejected from the jet thruster 23 so that the artificial satellite G1 can move in space.

[0031] As shown in the cross section of FIG. 8, the jet thruster 23 has a base end portion 23a side connected to the engine, has a circular waveguide 23b following the base end portion 23a, and a horn portion 23c having a shape gradually widening toward the rear end side of the circular waveguide 23b is formed. An electrical power feeding portion 28 is provided inside the circular waveguide 23b, and a transmitting and receiving device 30 is provided via a connection portion 29 to the power feeding portion 28, thereby adding an antenna structure. The side connected to an engine (not shown) from the connection portion 29 has the base end portion 23a functioning as a stub waveguide and a ground structure in the added antenna structure.

[0032] When the artificial satellite G1 ejects the injection flow 27 for propulsion, an antenna system S8 as a linear antenna using the power feeding portion 28 and the injection flow 27 is constructed. Since the injection flow 27 is connected to the artificial satellite G1 via a ground portion, the antenna system S8 is constructed. The jet thruster 23 functions as a device for generating the injection flow (structure) 27 that functions as an antenna. The operating frequency of the linear antenna can be adjusted by the mixing ratio of the conductive component of the jet flow 27 generated by the reaction in the engine. In the case of an ion engine, it can be adjusted by the length of the ion tail generated by the ejecta according to the injection time, or by the shape of the jet flow 27 such as the thickness of the jet flow 27 due to the injection force. Once a satellite is launched into space, it is a device (structure) placed in an environment where means such as adding an antenna later cannot be adopted unless a device is devised to make the operating frequency of the software radio and the broadband antenna flexible and variable. In this embodiment, the ion tail can be utilized as a part of the structure and used as an antenna radiator. If each antenna part has a plurality of operating frequencies or broadband characteristics, software radio may be adopted for all the power feeding parts in the present invention to make the operating frequency switchable.

[0033] Alternatively, in the case of an ion engine, it may be by temperature adjustment that utilizes the property that the conductivity of the plasma is proportional to the three-halves power of the electron temperature. If there is an existing ejecta resource having electrical conductivity and the power feeding part 28 can be installed, the dust tail of a comet can also be used. Therefore, although not shown in the drawings, for a non-artificial object such as a comet, an object moving in space while emitting a dust tail, by landing the aforementioned satellite on it and having the satellite have a transceiver connected to the dust tail via a power feeding part, an antenna system using the dust tail can be constructed via the satellite having a grounding part.

[0034] The operating frequency and radiation efficiency as an antenna can be adjusted by the mixing ratio of the gas flow or ion flow constituting the jet flow 27, the shape and length of the jet flow 27 due to the injection output, or the temperature of the jet flow 27, or a combination thereof. The antenna system S8 shown in FIG. 8 is an example in which a power feeding part 28 is provided at the generation part of a jet flow 27 such as an ion tail generated in the satellite G1, and a transmitting and receiving device 30 is provided in the satellite body 22 so that the jet flow 27 such as the ion tail operates as an antenna radiator. As described above, an antenna radiator can be constructed by utilizing a jet flow having electrical permittivity such as gas or ions for propulsion of the satellite.

[0035] "Eighth Embodiment" Figures 9 and 10 show a horn antenna system S8 configured by connecting a connection part 32 and a transmission / reception device 33 to an injection thruster 23 having the same shape as the injection thruster 23 shown in the seventh embodiment via a mode coupler 31. The mode coupler 31 has a coupling part 31a provided so as to partially surround a part of the outer peripheral wall of the circular waveguide 23b, and constructs an electromagnetic wave transmission / reception path with the circular waveguide 23b on the inner peripheral side via a slit structure 31c. A horn part 23c having a shape that gradually widens toward the rear end side is formed at the rear end side of the circular waveguide 23b.

[0036] "Ninth Embodiment" Figure 11 shows an antenna system S9 of the ninth embodiment in which mode couplers 35, 36, 37, and 38 are provided for an injection thruster 23 having the same shape as the injection thruster 23 shown in the previous seventh embodiment. The basic structures of the mode couplers 35, 36, 37, and 38 are equivalent to that of the mode coupler 31 of the previous embodiment, but their diameters are different. In this example, a mode coupler 35 is provided on the proximal end side of the circular waveguide 23b, a mode coupler 36 is provided on the rear end side of the circular waveguide 23b, a mode coupler 37 is provided on the proximal end side of the horn part 23c, and a mode coupler 38 is provided on the rear end side of the horn part 23c. The mode coupler 35 is connected to a transmission / reception device 39, the mode coupler 36 is connected to a transmission / reception device 40, the mode coupler 37 is connected to a transmission / reception device 41, and the mode coupler 38 is connected to a transmission / reception device 41.

[0037] The mode combiners 35 and 36 have coupling portions with the same diameter, but the diameter of the coupling portion of the mode combiner 37 is formed larger than that of the mode combiners 35 and 36, and the diameter of the coupling portion of the mode combiner 38 is formed larger than that of the mode combiner 37. The mode combiners 35, 36, 37, 38 and the transceiver devices 39, 40, 41, 42 are arranged in an array along the length direction (left - right direction in FIG. 11) of the injection thruster 23. Since the mode combiners 37 and 38 have different outer diameters from the mode combiners 35 and 36, FIG. 11 shows a configuration in which mode combiners with different outer diameters are provided at a plurality of positions with different outer diameters of the injection thruster 23. A satellite is a device (structure) placed in an environment where means such as adding an antenna later cannot be adopted once it is launched into space. In the present embodiment, from the transceiver devices 39, 40, 41, 42 shown in FIG. 11, the mode combiners 35, 36, 37 can be used as power supply parts to energize the circular waveguide 23b, and a linear antenna similar to that of the seventh embodiment can be configured. As shown in FIG. 11, by having the transceiver devices 39, 40, 41, 42 having a plurality of mode combiners 35, 36, 37 adapted to the respective diameters of the injection thruster 23, an antenna with broad - band characteristics can be provided, or the performance as a directional coupler can be enhanced. Also, a part of the coupling degree can be improved, and it can be made into a multi - mode and broad - band.

[0038] "Tenth Embodiment" FIG. 12 shows an antenna system S10 of the tenth embodiment in which an antenna tube 45 is separately provided outside the heat - resistant ceramic layer of the injection thruster 23. The antenna tube 45 has a cylindrical portion 45a with a diameter slightly larger than that of the circular waveguide 23b, and a horn portion 45b with a diameter that expands in a tapered shape from the tip of the cylindrical portion 45a. A mode combiner 44 is provided on the outer periphery of the cylindrical portion 45a, and a transceiver device 48 is connected to the mode combiner 44 via a connection portion 47. Once a satellite is launched into space, it is a device (structure) placed in an environment where measures such as adding an antenna cannot be adopted unless a device is devised to flexibly vary the operating frequency with software radio and a broadband antenna. If each antenna section has multiple operating frequencies or broadband characteristics, software radio may be adopted for all the power supply sections in the present invention to enable switching of the operating frequency. In the present embodiment, mode coupling can be performed from the transmission / reception device 48 shown in FIG. 12 to the circular waveguide 23b using the mode coupler 44 as a power supply section, and a linear antenna or a horn antenna similar to that of the sixth or seventh embodiment can be configured. In the structure shown in the previous FIG. 10, even if there is a diameter mismatch between the ceramic portion of the horn section 23c and the portion of the circular waveguide 23b, the structure shown in FIG. 12 does not cause problems due to the diameter mismatch because an antenna tube 45 is provided separately. Also, the ceramic portion of the horn section 23c can coexist by operating as a dielectric inside the antenna tube 45 as an antenna, and a thruster and an antenna can be formed simultaneously on the coaxial axis.

[0039] "Eleventh Embodiment" FIG. 13 shows an antenna system S11 of the eleventh embodiment in which an antenna tube 46 having a corrugated horn structure is separately provided on the outer peripheral portion of the injection thruster 23. The antenna tube 46 has a cylindrical portion 46a having a slightly larger diameter than the circular waveguide 23b, and a horn portion 46b having a diameter that expands in a tapered shape from the rear end of the cylindrical portion 46a. As shown in FIG. 13, an electromagnetic periodic structure 46c is formed on the inner surface side of the horn portion 46b. Since the horn portion 46b has an electromagnetic periodic structure 46c on its inner peripheral surface, the antenna tube 46 constitutes a corrugated horn. A mode coupler 44 is provided on the outer periphery of the cylindrical portion 46a, and a transmission / reception device 48 is connected to the mode coupler 44 via a connection portion 47.

[0040] Once a satellite is launched into space, it is a device (structure) placed in an environment where means such as adding an antenna cannot be adopted unless a device is devised that can flexibly vary the operating frequency with software radio and a broadband antenna. In this embodiment, mode coupling is performed from the transmitting and receiving device 48 shown in FIG. 13 to the circular waveguide 23b using the mode coupler 44 as a power feeding unit, and a linear antenna or a horn antenna similar to those in the sixth and seventh embodiments can be configured. If each antenna unit has a plurality of operating frequencies or broadband characteristics, software radio may be adopted for all the power feeding units in the present invention to enable switching of the operating frequency. In the structure shown in the previous FIG. 10, even when there is a mismatch in the diameter between the ceramic portion of the horn portion 23c and the circular waveguide 23b, the structure shown in FIG. 13 does not cause problems due to the diameter mismatch because an antenna tube 46 as a corrugated horn is provided separately.

[0041] "Twelfth Embodiment" FIG. 14 shows an antenna system S12 according to the twelfth embodiment that includes both a configuration including the power feeding unit 28, the connection unit 29, and the transmitting and receiving device 30 shown in FIG. 8 and a configuration including the mode coupler 31, the connection unit 32, and the transmitting and receiving device 33 shown in FIG. 10 for the injection thruster 23. In the example shown in FIG. 14, the mode coupler 31 and the connection unit 32 are provided at a position close to the horn portion 23c at the tip of the circular waveguide 23b, and the power feeding unit 28 and the connection unit 29 are provided at a position closer to the center in the length direction of the circular waveguide 23b than the position where the mode coupler 31 is provided.

[0042] Once a satellite is launched into space, it is a device (structure) placed in an environment where means such as adding an antenna cannot be adopted unless it is devised to be able to variably change the operating frequency flexibly with software radio and a broadband antenna. In this embodiment, with the configuration shown in FIG. 14, it is possible to obtain the functions of both a linear antenna using the jet flow 27 and a horn antenna using the horn portion 23c. As a result, as an antenna addition to the same thruster structure, the horn antenna of the seventh embodiment and the linear antenna of the sixth embodiment can be configured simultaneously. If each antenna portion has a plurality of operating frequencies or broadband characteristics, software radio may be adopted for all the power supply portions in the present invention to enable switching of the operating frequency. In the example shown in FIG. 14, the positions where the power supply portion 28 is provided and the position where the mode coupler 31 is provided may be reversed front and back, or a plurality of each of them may be provided.

[0043] "13th Embodiment" FIG. 15 shows the injection thrusters 51 of four ion engines provided on the rear side of the satellite body 50 of the artificial satellite. FIG. 16 shows the antenna system S13 of the 13th embodiment in which a power supply portion 54 is provided for the satellite body 50 provided with a plurality of mounted injection thrusters 51 via a mode coupler 52 and a connection portion 53, respectively. The configuration in which each injection thruster 51 has a circular waveguide 51b and a horn portion 51c is equivalent to the injection thruster 23 of the embodiment described above. Once a satellite is launched into space, it is an apparatus (structure) placed in an environment where measures such as adding an antenna cannot be adopted unless a device is devised that can flexibly vary the operating frequency with software radio and a broadband antenna. In the configuration shown in FIG. 16 of the present embodiment, an antenna system S13 as an array antenna can be constructed by connecting an analog-to-digital converter 55 individually to a power supply unit 54 connected to the injection thrusters 51 of four ion engines and then connecting it to a part of the satellite body 50, enabling beamforming. If each antenna unit has multiple operating frequencies or broadband characteristics, software radio may be adopted for all power supply units in the present invention to enable switching of the operating frequency. With the above configuration, an antenna array system is constructed that functions as a plurality of linear antennas through a ground connection by a satellite.

[0044] "14th Embodiment" FIG. 17 shows an example of a launch rocket carrying a satellite. This rocket 60 has a satellite-mounted puff structure 62 in a frustum ring shape surrounded by a rocket fairing 61 at its tip, and as an example, a plurality of artificial satellites 63, 64, 65, 66 are attached to the puff structure 62 as shown in FIG. 19. The artificial satellites 63, 64, 65, 66 are fixed to the upper surface side of the peripheral wall of the puff structure 62 by pedestals 67, 68, 69, 70.

[0045] The puff structure 62 is assembled by stacking a dummy frame 72, a buffer ring 73, and a mounting adapter 74 shown in FIG. 20 as an example, mounted on the tip side of the rocket 60, and surrounded by the rocket fairing 61. As an example, the rocket 60 has a first-stage engine 60A using liquid hydrogen or the like as fuel as the main engine in the fuselage, and a second-stage engine capable of multiple ignitions as the second stage in the second-stage fuselage. After launching the part of the rocket fairing 61 into space, the two-part rocket fairing 61 can be separated from the fuselage to release the artificial satellites 63, 64, 65, 66 into space.

[0046] After the artificial satellites 63, 64, 65, and 66 are released into space, generally the puff structure 62 becomes a non - used part. However, in this embodiment, this puff structure 62 is utilized as a part of the ring antenna. As an example, after the solar panel 75 of the artificial satellite 63 is deployed in space, as shown in FIG. 21, while the outer peripheral part of the puff structure 62 is connected to the artificial satellite 63, a power supply unit 71 provided via a ground G is provided on the outer peripheral part of the artificial satellite 63, and the power supply unit 71 is connected to the puff structure 62. An artificial satellite is a device (structure) placed in an environment where means such as adding an antenna later cannot be adopted once it is launched into space. In this embodiment, by effectively using the existing puff structure 62, a ring antenna can be provided for the artificial satellite 63 in space. By connecting the puff structure 62 to the power supply unit 71, the antenna system S14 of the 14th embodiment can be constructed.

[0047] "15th Embodiment" FIG. 22 shows another example when an antenna is configured using the aforementioned puff structure 62 and artificial satellite 63. Once an artificial satellite is launched into space, it is a device (structure) placed in an environment where means such as adding an antenna cannot be adopted unless a device is devised to make the operating frequency variable flexibly with software radio and a broadband antenna. In this embodiment, as shown in FIG. 22, the power supply unit 76 of the artificial satellite 63 and the puff structure 62 are connected by a wiring 77 such as a metal wire, and the puff structure 62 is used as a waveguide to improve directivity or to construct a trans - antenna by receiving and re - transmitting. By connecting the puff structure 62 to the power supply unit of the artificial satellite 63 via the wiring 77, the antenna system S15 of the 15th embodiment can be constructed. Also, if the positional relationship between the artificial satellite 63 and the puff structure 62 can be maintained, the wiring 77 may be omitted. If each antenna part has a plurality of operating frequencies or broadband characteristics, software radio may be adopted for all the power supply units in the present invention to make the operating frequency switchable.

[0048] "16th Embodiment" The antenna system S16 of the 16th embodiment utilizes the rocket fairing 61 provided at the tip of the rocket 60 covering the puff structure 62 described above. As an example, as shown in Fig. 23, the rocket fairing 61 is composed of a first segment 61A and a second segment 61B which are vertically split into two. When releasing the artificial satellites 63, 64, 65, 66 into space, after separating the first segment 61A and the second segment 61B as shown in Fig. 23, the artificial satellites 63, 64, 65, 66 are released into space from the puff structure 62.

[0049] The first segment 61A and the second segment 61B are members that are generally not used after the release of the artificial satellites 63, 64, 65, 66. However, in this embodiment, either the first segment 61A or the second segment 61B is utilized as part of the antenna system. As an example, as shown in Fig. 24, when deploying the solar panel paddle 75 of the artificial satellite 63 in space, the antenna system S16 of the 16th embodiment can be constructed by connecting the second segment 61B with a wire 78 such as a metal wire to the mounting part 76' of the artificial satellite 63. For example, a cross dipole antenna 79 is provided on the artificial satellite 63.

[0050] By using the inner surface or the outer surface of the second segment 61B, radio waves or electromagnetic waves transmitted from the artificial satellite 63 can be reflected in an appropriate direction, or a desired reflector antenna can be formed by using the concave curved surface of the fairing. Therefore, a reflector antenna equivalent to a large deployable antenna can be constructed using the second segment 61B. Once a satellite is launched into space, it is a device (structure) placed in an environment where means such as adding an antenna cannot be adopted unless a device is devised to flexibly vary the operating frequency with software radio and a broadband antenna. In this embodiment, by effectively using the second segment 61B as an existing structure, a reflector antenna can be added to the satellite 63 in space. By connecting the second segment 61B to the power supply unit of the satellite 63 via the wire 78, the antenna system S16 of the 16th embodiment can be constructed. Also, if the positional relationship between the satellite 63 and the first segment 61A or the second segment 61B can be maintained, the wire 78 may be omitted. If each antenna section has a plurality of operating frequencies or broadband characteristics, software radio may be adopted for all the power supply units in the present invention to make the operating frequency switchable.

Explanation of Signs

[0051] A1, B1, C1, D1, E1, F1, G1... artificial satellites, S1, S2, S3, S4, S5, S6, S7, S8, S9, S10, S11, S12, S13, S14, S15, S16... antenna systems, G... ground (grounding part), 2, 22... satellite structures (artificial satellite structures), 3... panel, 4... receiver, 5, 6... solar cell paddles, 8... support, 8a, 8b, 8c, 8d... wires, 8f... wiring part, 10... power supply part, 20... omnidirectional antenna, 23... jet thruster, 23b... circular waveguide, 23c... horn part, 27... jet flow, 28... power supply part, 30, 33,... transceiver, 31, 35, 36, 37, 38, 44... mode coupler, 39, 40, 41, 42... transceiver, 45, 46... antenna tubes, 48... transceiver, 51... jet thruster, 51b... circular waveguide, 51c... horn section, 52... mode coupler, 54... power feeding section, 60... rocket, 61... rocket fairing, 61A... first segment, 61B... second segment, 62... puff structure, 63, 64, 65, 66... artificial satellites, 77... wiring, 78... wire, 79... cross dipole antenna.

Claims

1. An antenna system that functions as a transmitter and receiver of electromagnetic waves by connecting a power supply unit to a part of an electrically conductive component already existing in a satellite or a rocket carrying the satellite so that the part of the electrically conductive component operates as an antenna.

2. The antenna system according to claim 1, wherein when a part of the component is a linear structure grounded at both ends and forms a loop as a whole, a power supply part is provided at one of the grounded parts so as to function as a loop antenna.

3. The antenna system according to claim 1, wherein when a part of the component is a linear structure grounded on one side, a power supply part is provided at the grounded part so as to function as a monopole antenna.

4. The antenna system according to claim 1, wherein a part of the component has an L-shaped conductive part and functions as an L-shaped antenna.

5. The antenna system according to claim 1, wherein a part of the component has an F-shaped conductive part and functions as an inverted F antenna.

6. The antenna system according to any one of claims 1 to 5, wherein the component is an electrically conductive support structure that supports a structure such as a satellite, or an electrically conductive wire for deployment operation or opening operation.

7. The antenna system according to any one of claims 1 to 5, wherein the component is an electrically conductive wire for supporting a synthetic aperture radar of a satellite, or for deployment operation or opening operation, and a power supply part is provided at an end of the wire via a ground part of the synthetic aperture radar and the satellite structure, and functions as an antenna.

8. The antenna system according to claim 1, wherein the component is any one of a parachute structure mounted on the rocket, a fairing, or a synthetic aperture radar mounted on the satellite, and functions as a reflector antenna or a transmit antenna that reflects or receives and re-transmits electromagnetic waves from the satellite.

9. Applied to the satellite or the rocket equipped with an electronic device, and an antenna function is achieved by applying the frequency band of the noise received by the electronic device in the common mode and providing a power supply part to an insulation processing part provided in the satellite or the rocket.

10. It is applicable to a satellite having a deployment panel that can implement an antenna but cannot implement an antenna harness. A radio device and a low-gain antenna provided on the structure of the satellite perform wireless transmission and reception with the entire or part of the back surface of the deployment panel, and re-transmit and receive from the entire or part of the front surface of the deployment panel before and after transmission and reception on the back surface of the deployment panel, thereby functioning as a high-gain transmit antenna.

11. The antenna system according to claim 1, wherein the component is an injection thruster that injects gas or ions for propulsion of a satellite or the like, a transmission and reception device is connected, and it functions as a horn antenna.

12. The antenna system according to claim 11, wherein the transmission and reception device is connected to the outer peripheral portion of the injection thruster via a mode coupler.

13. The antenna system according to claim 12, wherein a plurality of transmission and reception devices are arranged in an array via a plurality of mode couplers having different outer diameters at a plurality of positions having different outer diameters of the injection thruster along the length direction of the injection thruster, improving a part of the coupling degree, and being multi-mode and broadband.

14. The antenna system according to claim 11, further comprising an antenna tube covering the outer peripheral surface of the injection thruster made of heat-resistant ceramic, and a transmission and reception device is connected to the outer peripheral portion of the antenna tube via a mode coupler.

15. The antenna system according to claim 14, wherein the antenna tube is a corrugated horn provided with an electromagnetic periodic structure between the inner thruster structure.

16. The antenna system according to claim 1, wherein the component is an injection flow having electrical permittivity such as gas or ions for propulsion of a satellite, a transmission and reception device is connected to the injection thruster to be injected via a power supply unit, the injection flow is used as a part of an antenna radiator, and it functions as a linear antenna via a grounding portion by the satellite.

17. An antenna array system, characterized in that a plurality of injection thrusters for generating components are mounted on a satellite or the like, the component is an injection flow having electrical permittivity such as gas or ions for propulsion of a satellite, a transmission and reception device is connected to each of the injection thrusters via a power supply unit, the injection flow is used as a part of an antenna radiator, and it functions as a linear antenna via a grounding portion by the satellite.

18. The antenna system according to claim 11 or 16, characterized in that, in addition to the power feeding unit, the transmitting and receiving device is connected to the outer peripheral portion of the injection thruster via a mode coupler and has a function as a horn antenna in addition to the function as a linear antenna.

19. The antenna system according to claim 16, wherein the operating frequency and radiation efficiency as an antenna are adjusted by the mixing ratio of the injection flow, the shape and length of the ejecta by the injection output of the injection flow, the temperature of the ejecta, or a combination thereof.

20. An antenna system, characterized in that a transmitting and receiving device is connected to an ion tail generated by a non-artificial object such as a comet in outer space via a power feeding unit, and a power feeding unit is provided to the non-artificial object via a grounding unit so that the ion tail operates as an antenna radiator, and a linear antenna is constructed.

21. The antenna system according to claim 20, wherein the operating frequency and radiation efficiency as an antenna are adjusted by the mixing ratio of the ion tail, the shape and length of the ejecta by the injection output, the temperature of the ejecta, or a combination thereof.

22. The antenna system according to claim 1, wherein when a part of the constituent for which the antenna operates has a plurality of operating frequencies and broadband characteristics, the operating frequency can be switched using software radio for the power feeding unit. The antenna system according to claim 1.

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