JP7282613B2 - flying object - Google Patents

Description

The present invention relates to an aircraft.

BACKGROUND ART When a flying object such as an aircraft or a flying object searches using a radar detection device, the detection device, for example, a radar antenna is installed at the front end or the like. On the other hand, when the radar is irradiated from the front, the radar cross-section (RCS: Radar Cross-Section) is increased by the antenna of the detection device. Techniques for reducing this RCS have been developed.

For example, Patent Literature 1 describes a technique for reducing RCS by installing a frequency selective layer (FSS: Frequency Selective Surface) across a radome.

Patent Document 2 describes a technique for reducing RCS by covering an antenna of a detection device provided on a ship with a polyhedral radome.

Patent Literature 3 describes a technique for improving radio wave transmittance by installing an FSS in contact with an exterior that is present in a direction in which an antenna of a detection device mounted on a vehicle emits radio waves.

Patent Document 4 describes a technique for reducing noise detected by a detection device by providing an FSS having the same shape as the radome inside the radome.

Patent Literature 5 describes a technique of providing a radome with an FSS having high transmittance for a plurality of frequencies. Also, a technique of attaching an FSS to the antenna of the detection device is described in order to reduce noise from the outside.

Non-Patent Document 1 describes a technique for manufacturing an FSS having a free-form surface in order to apply the FSS to a radome of an aircraft.

Japanese Patent Application Laid-Open No. 2001-298322 JP-A-2008-39432 JP 2016-145777 A U.S. Patent Application Publication No. 2013/0009846 U.S. Pat. No. 5,652,631

“Evaluation materials for the development of advanced material technology for aircraft systems”, [online], November 29, 2012, [searched April 22, 2019], Internet (https://www.meti.go.jp/policy /tech_evaluation/c00/C0000000H24/121129_koukuuki/koukuu6-3-4.pdf)

SUMMARY OF THE INVENTION It is an object of the present invention to provide a flying object with a small RCS at a position where a detection device is mounted. Other objects can be understood from the following description and the description of the embodiments.

Means for solving the problems will be described below using the numbers and symbols used in the mode for carrying out the invention. These numbers and symbols are added in parentheses for reference in order to show an example of correspondence between the description of the claims and the mode for carrying out the invention. Therefore, the claims should not be construed as limiting by the parenthesized description.

An aircraft (1) according to one embodiment for achieving the above object comprises a radome (20), a main body (10), an antenna (31) and an antenna cover (40). A body (10) supports a radome. The antenna (31) is covered with a radome and supported by the main body. An antenna cover (40) is supported by the body and covers the antenna. Also, the antenna cover (40) comprises an absorber (42) and a cover plate (41). An absorber (42) is supported by the main body and absorbs radio waves. A cover plate (41) contains a frequency selective layer (46) and is located between the radome and the antenna.

An aircraft (1) according to one embodiment for achieving the above object comprises a radome (20), a main body (10), an antenna (31) and an antenna cover (40). A body (10) supports a radome. The antenna (31) is covered with a radome and supported by the main body. An antenna cover (40) is supported by the body and covers the antenna. The antenna cover (40) also has a cover plate (41). A cover plate (41) contains a frequency selective layer (46) and is located between the radome and the antenna. The cover plate (41) has, at its rear end, a connecting part (43) whose surface is covered with an absorbing material that absorbs radio waves.

According to the present invention, it is possible to realize a flying object with a small RCS at the position where the detection device is mounted.

1 is a schematic diagram of an air vehicle according to one embodiment; FIG. 1 is a schematic cross-sectional view of a forward tip of an aircraft according to one embodiment; FIG. FIG. 3 is a schematic view of the AA cross section in FIG. 2; FIG. 3 is an enlarged view of B in FIG. 2; FIG. 4 is a cross-sectional view of a cover plate according to one embodiment; It is a figure for demonstrating operation|movement of the antenna cover by one Embodiment. FIG. 4 is a diagram showing a configuration example of a portion that joins an antenna cover and a main body; FIG. 4 is a diagram showing a configuration example of a portion that joins an antenna cover and a main body; FIG. 4 is a diagram showing a configuration example of a portion that joins an antenna cover and a main body; FIG. 10 illustrates a cover plate according to one embodiment; FIG. 11 is a schematic view of the A'-A' cross section in FIG. 10; FIG. 4 is a diagram showing a configuration example of a portion that joins an antenna cover and a main body; FIG. 4 is a diagram showing a configuration example on the front surface of the main body;

(Embodiment)
As shown in FIG. 1 , a flying object 1 , such as an aircraft, a flying object according to one embodiment includes a body 10 and a radome 20 . The radome 20 is provided in the traveling direction of the aircraft 1 , that is, at the front end, and is supported by the main body 10 .

As shown in FIG. 2, the body 10 is provided with a detection device 30 and an antenna cover 40 . The detection device 30 includes an antenna 31 provided in front of the main body 10 and a control device 32 that controls radio waves radiated from the antenna 31 . Also, the control device 32 analyzes radio waves detected by the antenna 31 . The control device 32 is provided inside the main body 10, for example. The antenna cover 40 has a frequency selective layer (FSS: Frequency Selective Surface) and is installed so as to cover the antenna 31 . Therefore, the radar cross-section (RCS) at the position where the antenna 31 is mounted is small.

Antenna 31 is provided so as to be covered with radome 20 . The radome 20 has a space 21 inside. Space 21 is, for example, a closed space surrounded by main body 10 and radome 20 . Antenna 31 is provided in space 21 .

Antenna 31 is supported by main body 10 . The main body 10 includes an antenna support base 11 on which an antenna 31 is installed. The antenna support base 11 is provided so as to protrude from the front surface 10 a of the main body 10 . Antenna 31 has on its front surface an antenna surface 31a for radiating or detecting radio waves. The antenna support 11 may have any shape as long as the antenna 31 can be installed thereon, and the antenna support 11 may be provided in a recess formed in the front surface 10a of the main body 10, for example.

Antenna 31 emits radio waves in a direction indicated by control device 32 and detects radio waves reflected by objects. Information representing the detected radio waves is transmitted to the control device 32 and analyzed by the control device 32 . The antenna 31 includes, for example, a phased array antenna having a planar antenna surface 31a that radiates radio waves.

Antenna cover 40 is installed between radome 20 and antenna 31 so as to cover antenna 31 . For example, the antenna 31 may be provided in a closed space formed by the antenna cover 40 and the main body 10 . Antenna cover 40 is supported by main body 10 .

As shown in FIG. 3, the antenna cover 40 may be formed of a polyhedron in which a plurality of planar cover plates 41 are bonded together. For example, the cover plate 41 includes a first cover plate 41-1 installed in front of the antenna 31, and a second cover plate 41-2 to a seventh cover plate 41-7 adjacent to the first cover plate 41-1. consists of The second cover plate 41-2 to the seventh cover plate 41-7 are connected to the first cover plate 41-1 and the main body 10 and are configured to support the first cover plate 41-1. The portions where adjacent cover plates 41 contact each other may be connected by a smooth curved surface. The first cover plate 41-1 is installed so that the plane including the front side surface of the first cover plate 41-1 intersects the plane including the antenna surface 31a of the antenna 31. As shown in FIG. That is, the front surface of the first cover plate 41-1 is not parallel to the antenna surface 31a. Also, the cover plates 41 (the first cover plate 41-1 to the seventh cover plate 41-7) forming the polyhedron may be integrally formed.

As shown in FIG. 4, a sixth cover plate 41-6 installed at the end of the antenna cover 40 is attached to the main body 10. As shown in FIG. The sixth cover plate 41-6 is attached at a position away from the body 10 to which the radome 20 is attached and is not in contact with the radome 20. As shown in FIG. Similarly, a second cover plate 41 - 2 installed at the end of the antenna cover 40 is attached to the main body 10 . The second cover plate 41 - 2 is attached at a position away from the position of the main body 10 to which the radome 20 is attached, and is not in contact with the radome 20 . A third cover plate 41-3, a fourth cover plate 41-4, a fifth cover plate 41-5, and a seventh cover plate 41-7 installed at the end of the antenna cover 40 are attached to the main body 10. installed. The third cover plate 41-3, the fourth cover plate 41-4, the fifth cover plate 41-5, and the seventh cover plate 41-7 are separated from the position of the main body 10 to which the radome 20 is attached. mounted in a raised position and not in contact with the radome 20. In other words, the cover plate 41 is attached to the main body 10 without contacting the radome 20 .

The antenna cover 40 comprises an absorber 42 that covers at least part of the front surface 10a of the main body 10. As shown in FIG. The absorber 42 is installed in a space that does not affect radio waves radiated or detected by the antenna 31 . For example, the space in which the absorber 42 is installed is a space through which radio waves radiated or detected by the antenna 31 do not pass. Further, the absorber 42 is designed or specified beyond the space through which the radio waves radiated or detected by the antenna 31 do not pass. It may be installed in space. For example, the absorber 42 is provided behind the antenna 31, more specifically behind the antenna surface 31a. Since the absorber 42 covers the front surface 10a of the main body 10, the absorber 42 absorbs radio waves from the outside in the vicinity of the antenna 31 of the detection device 30, thereby reducing the RCS.

The absorber 42 may cover the front of the body 10 except for the antenna 31 . Specifically, the absorber 42 is provided so as to cover the area surrounded by the portion 10b to which the cover plate 41 is attached and the portion 10c to which the radome 20 is attached in the front surface 10a of the main body 10. It is The absorber 42 covers at least a part of the front surface 10a of the main body 10 surrounded by the part 10b to which the cover plate 41 is attached, for example, the entire area excluding the part to which the antenna 31 is attached. is provided to cover the The absorber 42 may be provided so as to cover the front of the antenna support 11 . The absorber 42 is provided so as to cover only the area surrounded by the portion 10b to which the cover plate 41 is attached and the portion 10c to which the radome 20 is attached, on the front surface 10a of the main body 10. good too.

The cover plate 41 is formed by laminating a plurality of layers, as shown in FIG. For example, the cover plate 41 is formed by laminating a first substrate 48-1, a foam material 47, and a second substrate 48-2. Specifically, the foam material 47 is formed so as to be sandwiched between the first substrate 48-1 and the second substrate 48-2.

The first substrate 48-1 includes a high dielectric constant substrate 45 and a frequency selective layer 46. As shown in FIG. Specifically, the first substrate 48-1 is formed by laminating a first high dielectric constant substrate 45-1, a first frequency selection layer 46-1, and a second high dielectric constant substrate 45-2. ing. The first frequency selection layer 46-1 is formed so as to be sandwiched between the first high dielectric constant substrate 45-1 and the second high dielectric constant substrate 45-2. For example, the first frequency selective layer 46-1 is a metal layer having a predetermined grid with frequency selectivity. Also, the first frequency selection layer 46-1 may be a metal film printed in a predetermined pattern on the first high dielectric constant substrate 45-1.

The second substrate 48-2 includes a high dielectric constant substrate 45 and a frequency selective layer 46, similar to the first substrate 48-1. Specifically, the second substrate 48-2 is formed by stacking a third high dielectric constant substrate 45-3, a second frequency selection layer 46-2, and a fourth high dielectric constant substrate 45-4. ing. The second frequency selection layer 46-2 is formed so as to be sandwiched between the third high dielectric constant substrate 45-3 and the fourth high dielectric constant substrate 45-4. For example, the second frequency selective layer 46-2 is a metal layer having a predetermined grid with frequency selectivity. Also, the first frequency selection layer 46-1 may be a metal film printed in a predetermined pattern on the fourth high dielectric constant substrate 45-4.

The cover plate 41 is formed by laminating the high dielectric constant substrate 45, the frequency selection layer 46, and the foam material 47 in this way. Cover plate 41 may be formed in any configuration with frequency selective layer 46 .

(Operation of flying object)
The aircraft 1 detects the surrounding conditions using the detection device 30 in order to acquire the surrounding conditions during flight. Specifically, the control device 32 of the detection device 30 controls the antenna 31 to radiate radio waves. The radiated radio waves pass through the antenna cover 40 and the radome 20 and are reflected by surrounding objects. The reflected radio wave passes through the radome 20 and the antenna cover 40 and is detected by the antenna 31 . The control device 32 detects surrounding conditions by analyzing the detected radio waves.

Also, the flying object 1 is irradiated with radio waves from an external radar device. As shown in FIG. 6 , when the aircraft 1 is irradiated with radio waves from the front along the arrow 100 , the irradiated radio waves pass through the radome 20 and reach the cover plate 41 . Since the cover plate 41 has the frequency selective layer 46, it reflects radio waves other than radio waves having a specific frequency. Here, the normal direction of the front surface of the first cover plate 41 - 1 that reflects radio waves is not parallel to the arrow 100 . Therefore, the radio wave is reflected in the direction of arrow 101 that is not parallel to arrow 100 . In other words, radio waves are reflected in a direction different from the direction of arrival. As a result, the reflected radio waves do not return in the direction in which the radio waves were emitted, so the radar cross-section (RCS) of the aircraft 1 becomes smaller.

Thus, the cover plate 41 is provided in a closed space surrounded by the main body 10 and the radome 20 without contacting the radome 20 . Therefore, for the cover plate 41, thermal and aerodynamic constraints are reduced, and a material and configuration with excellent radio wave transmission characteristics and frequency selectivity can be selected. When the aircraft 1 flies at high speed, the radome 20 is affected by aerodynamic loads and aerodynamic heating. However, since the cover plate 41 is provided in a closed space surrounded by the main body 10 and the radome 20, the influence of aerodynamic load and aerodynamic heating is reduced, and it is formed into a shape specialized for reducing the radar cross-sectional area. be able to. As a result, restrictions on the material and structure of the cover plate 41 are reduced, and the cover plate 41 can be manufactured by an easy method, for example, a method of laminating flat plates.

Also, the RCS of the aircraft 1 is small with respect to the frequency passing through the cover plate 41 . When the aircraft 1 is irradiated with radio waves having a frequency that passes through the cover plate 41 , the irradiated radio waves pass through the radome 20 and the cover plate 41 . Since the front surface 10 a of the main body 10 is covered with the absorber 42 , radio waves passing through the cover plate 41 are absorbed by the absorber 42 . Therefore, it is possible to suppress reflection of radio waves from the front surface 10 a of the main body 10 .

Even if radio waves are emitted between the cover plate 41 and the radome 20, the RCS of the aircraft 1 is small. Radio waves passing between the cover plate 41 and the radome 20 along the arrow 110 and reaching the front surface 10a of the main body 10 are also absorbed by the absorber 42, thereby suppressing reflection of the radio waves.

By providing the antenna cover 40 in this way, it is possible to realize the aircraft 1 that is easy to manufacture and has a small RCS. In particular, the antenna cover 40 is useful for the aircraft 1 in which the temperature of the radome 20 becomes high during flight, specifically for the aircraft 1 that flies at a speed equal to or higher than the speed of sound.

(Modification)
The cover plate 41 and absorber 42 can be attached to the main body 10 in various configurations. For example, as shown in FIG. 7, the absorber 42 is surrounded by a portion 10b where the cover plate 41 is attached to the main body 10 except for the portion where the antenna support 11 is attached to the main body 10 on the front surface 10a. It may be provided so as to cover the area. Thereby, the influence of the absorber 42 on the antenna 31 can be reduced.

Moreover, as shown in FIG. 8, the cover plate 41 may be attached to the absorber 42 . In other words, the cover plate 41 may be attached to the main body 10 via the absorber 42 . This can facilitate manufacturing of the aircraft 1 .

Also, the absorber 42 may be installed so as to cover at least a portion of the front surface 10a of the main body 10 . For example, the absorber 42 may be provided so as to cover at least part of the area surrounded by the portion 10c to which the radome 20 is attached, excluding the area to which the antenna 31 is attached, for example. The absorber 42 is surrounded by a portion 10b' of the front surface 10a of the main body 10, which intersects the front surface 10a when the cover plate 41 is stretched, and a portion 10c to which the radome 20 is attached. It may be provided so as to cover only the region. Also, the absorber 42 may be provided so as to cover the front of the antenna support 11 .

As shown in FIG. 9 , a connecting portion 43 may be provided at the rear end of the cover plate 41 . For example, the connecting portion 43 is provided at a portion where the cover plate 41 is attached to the main body 10 . The surface of the connecting portion 43 is covered with an absorber material that absorbs radio waves. For example, the connecting portion 43 may be made of an absorbing material that absorbs radio waves. The connection portion 43 is configured to protrude from the absorber 42 when the cover plate 41 is attached to the main body 10 . When the cover plate 41 is attached to the main body 10 , the distance in the front-rear direction of the connecting portion 43 is longer than the thickness of the absorber 42 . The connecting portion 43 is installed in a space through which radio waves emitted by the antenna 31 do not pass. For example, the connecting portion 43 is provided behind the antenna 31, more specifically behind the antenna surface 31a. As a result, it is possible to reduce the RCS of the flying object 1 because the radio waves emitted from the outside are prevented from being reflected by the cover plate 41 and the radome 20 . Moreover, when the cover plate 41 is attached to the main body 10 via the absorbent body 42 , the connecting portion 43 may be provided at a portion attached to the absorbent body 42 .

The cover plate 41 may have a curved surface. For example, as shown in FIGS. 10 and 11, the antenna cover 40 may be formed by laminating a plurality of cover plates 41 to cover the antenna 31 . Antenna 31 may be provided in a closed space surrounded by cover plate 41 and main body 10 . The cover plate 41 consists of a first cover plate 41-1 installed in front of the antenna 31, and second cover plates 41-2 to fifth cover plates 41-5 adjacent to the first cover plate 41-1. It is configured. The second cover plate 41-2, the third cover plate 41-3, the fourth cover plate 41-4, and the fifth cover plate 41-5 are connected to the first cover plate 41-1 and the main body 10. and configured to support the first cover plate 41-1. A tangential plane 210 of the front side surface of the first cover plate 41-1 at a position intersecting the straight line 200 extending forward from the antenna 31 may intersect a plane including the antenna surface 31a. In other words, the tangential plane 210 need not be parallel to the antenna surface 31a.

Further, the front surface 10a of the main body 10 may be inclined with respect to a plane perpendicular to the longitudinal direction of the aircraft 1 . For example, as shown in FIG. 12, the front surface 10a passes through the portion 10c to which the radome 20 is attached as it goes from the portion 10c to which the radome 20 is attached to the portion 10b to which the cover plate 41 is attached. It may be formed so that the distance from the plane 220 perpendicular to the longitudinal direction of the aircraft 1 is long. As a result, at the end of the front surface 10a, the radio waves emitted from the outside are suppressed from being reflected back to the irradiation source.

Further, as shown in FIG. 13, the normal direction of the front surface 10a may be tilted with respect to the traveling direction of the aircraft 1. FIG. The overall tilting of the forward surface 10 a reduces the radar cross-section of the aircraft 1 even for a particular frequency transmitted through the cover plate 41 . Note that the normal direction of the front surface 10a may be any direction as long as it is inclined with respect to the traveling direction of the aircraft 1 .

Even when the cover plate 41 is attached via the absorber 42 , the front surface 10 a may be inclined with respect to the plane orthogonal to the longitudinal direction of the aircraft 1 . For example, the front surface 10a has the radome 20 attached, proceeding from the portion 10c where the radome 20 is attached to the portion 10b' that intersects the front surface 10a of the body 10 when the cover plate 41 is extended. It may be formed such that the distance from a plane 220 passing through the portion 10c and orthogonal to the longitudinal direction of the aircraft 1 is long. As a result, at the end of the front surface 10a, the radio waves emitted from the outside are suppressed from being reflected back to the irradiation source.

The embodiment and modifications described above are examples, and may be changed within a range that does not hinder the functions. In addition, the configurations described in the respective embodiments and modifications may be arbitrarily changed and/or combined arbitrarily within a range that does not hinder the functions. For example, the cover plate 41 may be connected to the antenna support base 11 of the main body 10 . A plurality of antennas 31 may be provided on the main body 10 . When multiple antennas 31 are provided, one antenna cover 40 may be provided to cover the multiple antennas 31 . Also, when a plurality of antennas 31 are provided, one antenna cover 40 may be provided for each antenna 31 . Alternatively, the antenna 31 may be installed directly on the front surface 10a without providing the antenna support 11. FIG.

For example, the flying object 1 described in each embodiment is understood as follows.

An aircraft according to a first aspect comprises a radome (20), a body (10), an antenna (31), and an antenna cover (40). An antenna cover (40) comprises an absorber (42) and a cover plate (41). The antenna cover is supported by the body and covers the antenna. The absorber is supported by the main body and absorbs radio waves. A cover plate includes a frequency selective layer and is positioned between the radome and the antenna.

Since the absorber and the cover plate suppress the reflection of radio waves from the outside to the irradiation source, the RCS of the aircraft is reduced.

The aircraft according to the second aspect is the aircraft according to the first aspect, wherein the absorber (42) is configured to cover at least part of the front surface (10a) of the main body (10). there is

Covering at least part of the front surface of the main body with the absorber suppresses reflection of radio waves by the front surface of the main body.

A flying object according to a third aspect is the flying object according to the second aspect, wherein the absorber (42) is formed by extending the cover plate (41) of the front surface (10a) of the main body (10). It is configured to cover an area surrounded by portions (10b, 10b') intersecting with the main body (10) and a portion (10c) to which the radome (20) is connected.

By covering the area between the radome and the cover plate on the front surface of the main body with the absorber, reflection of radio waves by the front surface of the main body is suppressed.

A flying object according to a fourth aspect is the flying object according to the first aspect, wherein the absorber (42) is provided in a space through which radio waves radiated or detected by the antenna (31) do not pass. is configured.

Since the absorber is installed in a space through which radio waves radiated by the antenna do not pass, RCS is suppressed while the performance of the detection device is maintained. For example, the absorber is provided behind the antenna. Also, the absorber may be provided behind the antenna surface (31a) that radiates radio waves.

A flying object according to a fifth aspect is the flying object according to the first aspect, in which the connecting part (43) whose surface is covered with an absorbing material that absorbs radio waves is attached to the rear end of the cover plate (41). configured to provide.

The connecting portion suppresses radio waves reflected by the cover plate and the radome, thereby reducing the RCS of the aircraft.

A flying object according to a sixth aspect is the flying object according to the fifth aspect, wherein the connection part (43) is installed in a space through which the radio waves radiated or detected by the antenna (31) do not pass. is configured as follows.

Since the connecting part is installed in a space through which radio waves radiated by the antenna do not pass, RCS is suppressed while the performance of the detection device is maintained. For example, the connecting portion is provided behind the antenna. Also, the connecting portion may be provided behind the antenna surface (31a) that radiates radio waves.

A flying object according to a seventh aspect is the flying object according to the first aspect, wherein the cover plate (41) is installed so as to cover the antenna (31) without coming into contact with the radome (20). is configured.

Since the cover plate is not in contact with the radome, manufacturing of the aircraft is facilitated.

An aircraft according to an eighth embodiment is the aircraft according to the first embodiment, wherein the antenna (31) is provided in a closed space formed by the main body (10) and the cover plate (41). is configured.

Since the antenna is provided in the closed space formed by the main body and the cover plate, reflection of radio waves irradiated from the outside can be suppressed.

A flying object according to a ninth aspect is the flying object according to the first aspect, wherein the antenna (31) has an antenna surface (31a), and the antenna (31) has an antenna surface (31a) at a position intersecting a straight line extending forward from the antenna (31). It is configured such that a tangential plane (210) to the surface of the antenna cover (40) intersects a plane containing the antenna surface (31a).

As a result, it is possible to suppress reflection in the direction in which radio waves emitted from the outside are emitted.

A flying object according to a tenth embodiment is the flying object according to the first embodiment, wherein the antenna (31) has an antenna surface (31a), and the normal direction of the antenna surface (31a) is It is configured so as to be inclined with respect to the traveling direction.

Since the normal direction of the antenna surface is tilted with respect to the traveling direction of the aircraft, radio waves incident from the traveling direction of the aircraft are reflected in a direction different from the direction of incidence, thereby reducing the RCS of the aircraft.

An aircraft according to the eleventh embodiment comprises a radome (20), a main body (10), an antenna (31), and an antenna cover (40). The antenna cover (40) comprises a cover plate (41). The cover plate (41) is provided at its rear end with a connection (43) covered with absorbent material.

The connecting portion suppresses radio waves reflected by the cover plate and the radome, thereby reducing the RCS of the aircraft.

1 Aircraft 10 Main Body 10a Front Surface 11 Antenna Support Base 20 Radome 21 Space 30 Detection Device 31 Antenna 31a Antenna Surface 32 Control Device 40 Antenna Cover 41 Cover Plate 42 Absorber 43 Connection Portion 45 High Dielectric Substrate 46 Frequency Selective Layer 47 Foam material 210 tangential plane 220 plane

Claims (9)

a radome;
a body supporting the radome;
an antenna covered by the radome and supported by the body;
an antenna cover supported by the main body and covering the antenna;
with
The antenna cover is
an absorber that is supported by the main body and absorbs radio waves;
a cover plate including a frequency selective layer and positioned between the radome and the antenna;
with
The absorber covers a region surrounded by a portion of the front surface of the main body that crosses the main body when the cover plate is stretched and a portion to which the radome is connected.
Airplane . The aircraft according to claim 1 , wherein the absorber is installed in a space through which radio waves radiated or detected by the antenna do not pass. a radome;
a body supporting the radome;
an antenna covered by the radome and supported by the body;
an antenna cover supported by the main body and covering the antenna;
with
The antenna cover is
an absorber that is supported by the main body and absorbs radio waves;
a cover plate including a frequency selective layer and positioned between the radome and the antenna;
with
The cover plate has a connecting portion at the rear end, the surface of which is covered with an absorbing material that absorbs radio waves.
Airplane . 4. The aircraft according to claim 3 , wherein the connecting portion is installed in a space through which radio waves radiated or detected by the antenna do not pass. a radome;
a body supporting the radome;
an antenna covered by the radome and supported by the body;
an antenna cover supported by the main body and covering the antenna;
with
The antenna cover is
an absorber that is supported by the main body and absorbs radio waves;
a cover plate including a frequency selective layer and positioned between the radome and the antenna;
with
The cover plate is installed to cover the antenna without contacting the radome.
Airplane . a radome;
a body supporting the radome;
an antenna covered by the radome and supported by the body;
an antenna cover supported by the main body and covering the antenna;
with
The antenna cover is
an absorber that is supported by the main body and absorbs radio waves;
a cover plate including a frequency selective layer and positioned between the radome and the antenna;
with
The antenna is provided in a closed space formed by the main body and the cover plate.
Airplane . The antenna has a planar antenna surface that radiates radio waves,
The aircraft according to any one of claims 1 to 6 , wherein a tangential plane to the surface of the antenna cover at a position intersecting a straight line extending forward from the antenna intersects a plane including the antenna surface. The antenna has an antenna surface formed on a plane that radiates radio waves,
The aircraft according to any one of claims 1 to 7 , wherein the normal direction of the antenna surface is inclined with respect to the traveling direction of the aircraft. a radome;
a body supporting the radome;
an antenna covered by the radome and supported by the body;
an antenna cover supported by the main body and covering the antenna;
the antenna cover includes a frequency selective layer and includes a cover plate positioned between the radome and the antenna;
The cover plate has a connecting part at the rear end part, the surface of which is covered with an absorbing material that absorbs radio waves.

Images