Aircraft countering equipment and aircraft control system

Abstract

The invention discloses aircraft countering equipment and an aircraft control system, and relates to the technical field of aircraft control. The aircraft countering device comprises an antenna assembly and a master control assembly, and the antenna assembly is used for transmitting interference signals to interfere with an aircraft; the main control assembly is electrically connected with the antenna assembly and is used for controlling the antenna assembly to transmit interference signals; a first effective coverage angle projected by the interference signal on the first plane is smaller than a second effective coverage angle projected by the interference signal on the second plane, and the first plane is perpendicular to the second plane. When the aircraft countering device is used, firstly, the aircraft countering device needs to be installed on the fixing piece; the main control assembly controls the antenna assembly to send an interference signal to interfere the aircraft, prevent the aircraft from communicating with the flight control terminal, and prevent the aircraft from entering a control area.

Description

Technical Field

[0001] The present application relates to the field of aircraft control technology, and more specifically, to an aircraft countermeasure device. In addition, the present application also relates to an aircraft control system including the above-mentioned aircraft countermeasure device. Background Art

[0002] At present, with the popularity of the drone market, more and more "low, slow and small" aircraft have gradually appeared. For some areas with high confidentiality requirements (such as prisons, places where important government agencies are located, etc.), it is strictly forbidden for aircraft to approach, pass or fly over. In order to protect the safety of the controlled area and prevent aircraft from entering the controlled area, relevant countermeasures need to be set up. However, the current countermeasures will emit strong interference signals in all directions, which can easily affect nearby wireless communications.

[0003] In summary, how to provide a countermeasure device with little impact on wireless communications in nearby areas is an urgent problem to be solved by those skilled in the art. Summary of the invention

[0004] In view of this, an object of an embodiment of the present application is to provide an aircraft countermeasure device that can reduce the impact on wireless communications in nearby areas.

[0005] Another object of an embodiment of the present application is to provide an aircraft control system including the above-mentioned aircraft countermeasure device.

[0006] In order to achieve the above objectives, the embodiments of the present application provide the following technical solutions:

[0007] An aircraft countermeasure device, comprising:

[0008] An antenna assembly, the antenna assembly being used to transmit an interference signal to interfere with the aircraft;

[0009] A main control component, the main control component is electrically connected to the antenna component, and the main control component is used to control the antenna component to transmit the interference signal;

[0010] A first effective coverage angle of the interference signal projected on the first plane is smaller than a second effective coverage angle of the interference signal projected on the second plane, and the first plane is perpendicular to the second plane.

[0011] Optionally, the first plane is perpendicular to the width direction of the antenna assembly, and the second plane is perpendicular to the length direction of the antenna assembly.

[0012] Optionally, the antenna component includes an upper end surface, and the interference signal is emitted from the upper end surface; the edge of the upper end surface along the length direction is parallel to the length direction of the antenna component; the edge of the upper end surface along the width direction is parallel to the width direction of the antenna component.

[0013] Optionally, the aircraft countermeasure device further includes a mounting assembly and a fixing member; the antenna assembly is rotatably mounted on the fixing member via the mounting assembly; and the main control assembly is mounted to the fixing member via the mounting assembly.

[0014] Optionally, the mounting assembly includes: a first mounting structure and a second mounting structure, the antenna assembly is rotatably mounted on the first mounting structure, and the first mounting structure is fixed to the fixing member; the main control assembly is fixed to the second mounting structure, and the second mounting structure is fixed to the fixing member.

[0015] Optionally, the antenna assembly can rotate along the pitch direction relative to the fixing member.

[0016] Optionally, a directional antenna is provided in the antenna assembly;

[0017] Or the antenna assembly is provided with an omnidirectional antenna and a metal reflector.

[0018] An aircraft control system comprises a plurality of aircraft countermeasure devices as described above, wherein the plurality of aircraft countermeasure devices are arranged along the boundary of the control area.

[0019] Optionally, the first plane is perpendicular to a width direction of the antenna assembly, and the second plane is perpendicular to a length direction of the antenna assembly;

[0020] The width direction of at least one of the antenna assemblies is parallel to the boundary of the control area corresponding to the location of the aircraft countermeasure device.

[0021] Optionally, a plurality of the aircraft countermeasure devices are arranged outside the boundary of the control area; the antenna assembly of the aircraft countermeasure device includes an upper end surface, and the interference signal is emitted from the upper end surface; the upper end surface includes a first end and a second end opposite to each other; the distance between the first end and the boundary of the control area corresponding to the location of the flight countermeasure device is smaller than the distance between the second end and the boundary of the control area corresponding to the location of the flight countermeasure device;

[0022] In the upper end surface of at least one of the antenna components, the height of the first end is higher than the height of the second end.

[0023] Optionally, a plurality of the aircraft countermeasure devices are arranged outside the boundary of the control area; the antenna assembly of the aircraft countermeasure device includes an upper end surface, and the interference signal is emitted from the upper end surface; the upper end surface includes a first end and a second end opposite to each other; the distance between the first end and the boundary of the control area corresponding to the location of the flight countermeasure device is smaller than the distance between the second end and the boundary of the control area corresponding to the location of the flight countermeasure device;

[0024] In the upper end surface of at least one of the antenna components, the height of the first end is lower than the height of the second end.

[0025] Optionally, the first plane is perpendicular to a width direction of the antenna assembly, and the second plane is perpendicular to a length direction of the antenna assembly;

[0026] The projection of the side of at least one of the antenna components parallel to the length direction on the horizontal plane is perpendicular to the boundary of the control area corresponding to the location of the aircraft countermeasure device.

[0027] Optionally, the interference signals emitted by the plurality of aircraft countermeasure devices surround the controlled area along the boundary of the controlled area.

[0028] Optionally, the interference signals emitted by two adjacent aircraft countermeasure devices have a signal overlapping area along the boundary of the control area.

[0029] In the aircraft countermeasure device provided in the embodiment of the present application, the main control component controls the antenna component to send an interference signal, and the first effective coverage angle of the interference signal projected on the first plane is smaller than the second effective coverage angle of the interference signal projected on the second plane, that is, the interference signal has a narrower coverage range in one direction and a wider coverage range in another direction. If the aircraft countermeasure device is placed on the boundary of the controlled area, the interference signal can form an effect similar to a signal wall. Therefore, the aircraft countermeasure device proposed in the embodiment of the present application can prevent the aircraft from entering the controlled area while avoiding the emission of strong interference signals in all directions, thereby achieving the effect of reducing the impact on wireless communications in nearby areas.

[0030] In addition, an embodiment of the present application also provides an aircraft control system including the above-mentioned aircraft countermeasure device. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on the provided drawings without paying any creative work.

[0032] Figure 1 A schematic diagram of the structure of a specific embodiment of the aircraft countermeasure device provided in the embodiment of the present application.

[0033] Figure 2 for Figure 1 Schematic diagram of the structure in which the aircraft countermeasure equipment is installed on the fixing part.

[0034] Figure 3 It is a schematic diagram of a first effective coverage angle of an interference signal projected on a first plane.

[0035] Figure 4 It is a schematic diagram of a second effective coverage angle of the interference signal projected on the second plane.

[0036] Figure 5 This is a simulation diagram of the radiation effect of the interference signal on the first plane.

[0037] Figure 6 This is a simulation diagram of the radiation effect of the interference signal on the second plane.

[0038] Figure 7 A schematic diagram of the setting of an aircraft control system at the boundary of a control area provided in an embodiment of the present application.

[0039] Figure 8 for Figure 7 Schematic diagram of the signal wall formed by the aircraft control system.

[0040] Fig. 9 A schematic diagram of another setting of the aircraft control system at the boundary of the control area provided in an embodiment of the present application.

[0041] Fig.10 A schematic diagram of the structure of an antenna assembly provided in one embodiment of the present application.

[0042] Fig.11 for Fig.10 Exploded view of the antenna assembly of the illustrated embodiment.

[0043] Fig.12 for Fig.10 A schematic diagram of the assembly of the directional antennas in the antenna assembly of the illustrated embodiment.

[0044] Fig.13 for Fig.12A schematic diagram of the structure of the mounting bracket within the antenna assembly of the illustrated embodiment.

[0045] Description of Figure Numbers:

[0046] 1 is the aircraft countermeasure equipment.

[0047] 10 is an antenna assembly, 11 is an upper end surface, and 12 is a lower end surface;

[0048] 100a is the outer shell; 100a1 is the radiation surface; 110 is the first end cover; 120 is the outer shell; 130 is the second end cover;

[0049] 140 is a reflector;

[0050] 150 is an antenna, 151 is a first antenna, 152 is a second antenna, 153 is a third antenna, 154 is a fourth antenna, and 155 is a fifth antenna;

[0051] 160 is a mounting frame, 161 is a connecting substrate, 162 is a supporting portion, 162A is a first supporting rib, 162B is a second supporting rib, 162C is a third supporting rib, and 163 is a clamping portion.

[0052] 20 is the main control component.

[0053] 30 is a first installation structure; 301 is a rotating part.

[0054] 40 is a second installation structure.

[0055] 50 is a radio frequency cable.

[0056] 60 is a fixing member.

[0057] A is the first effective coverage angle, and B is the second effective coverage angle.

[0058] L1 is the angular bisector of the first effective coverage angle in the first plane, and L2 is the angular bisector of the second effective coverage angle in the second plane.

[0059] D1 is the length direction of the antenna component, and D2 is the width direction of the antenna component.

[0060] S is the boundary of the control area;

[0061] P1 is the edge of the upper end surface along the length direction; P2 is the edge of the upper end surface along the width direction. DETAILED DESCRIPTION

[0062] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0063] The core of the embodiment of the present application is to provide an aircraft countermeasure device that can prevent aircraft from entering a controlled area by emitting interference signals, and the interference signals can form an effect similar to a virtual wall.

[0064] Another core of an embodiment of the present application is to provide an aircraft control system including the above-mentioned aircraft countermeasure device.

[0065] like Figure 1 As shown, this specific embodiment discloses an aircraft countermeasure device 1, including an antenna assembly 10 and a main control assembly 20, wherein the antenna assembly 10 is used to transmit an interference signal to interfere with the aircraft. The main control assembly 20 is electrically connected to the antenna assembly 10, and the main control assembly 20 is used to control the antenna assembly 10 to transmit the interference signal. The interference signal, for example, spreads from the antenna assembly 10 in a direction away from the antenna assembly 10. The first effective coverage angle A (such as Figure 3 ) is smaller than the second effective coverage angle B (as shown) of the interference signal projected on the second plane Figure 4 As shown), the first plane is perpendicular to the second plane.

[0066] It should be noted that the electrical connection between the antenna assembly 10 and the main control assembly 20 in this specific embodiment can be achieved through a radio frequency cable connection or through a plug-in interface connection, which is determined according to actual conditions and will not be elaborated here.

[0067] The first effective coverage angle A mentioned in the embodiment of the present application may refer to the coverage angle of the signal where the interference signal is greater than the first preset radiation intensity in the first plane projection, for example Figure 5 As shown, the first effective coverage angle A may be an angle within a coverage range of approximately -15° to 15°. The second effective coverage angle B may refer to a coverage angle at which the interference signal is greater than a signal with a second preset radiation intensity in the second plane projection, such as Figure 6 As shown, the second effective coverage angle B can be roughly an angle within the coverage range of -60° to 60°. Among them, if the radiation intensity is greater than the first preset radiation intensity, or greater than the second preset radiation intensity, it means that the radiation intensity of the signal can meet the requirements, for example, it can achieve the effect of interference. Alternatively, it can be understood that the first effective coverage angle is the beam width of the interference signal in the first plane, and the second effective coverage angle is the beam width of the interference signal in the second plane.

[0068] Considering that in the actual use process, the main control component 20 generally needs to output a radio frequency signal to the antenna component 10, the antenna component 10 and the main control component 20 can be connected through a radio frequency cable 50. The main control component 20 outputs a radio frequency signal to the antenna component 10 through the radio frequency cable 50, and the antenna component 10 converts the received radio frequency signal into an electromagnetic wave signal of the corresponding frequency band and transmits it as an interference signal. When the drone flies into the coverage area of ​​the interference signal, the drone cannot operate or work normally. For example, it will not be able to communicate stably with the flight control terminal under the action of the interference signal, resulting in hovering, crashing or returning, etc., to achieve interference effects on the drone. The main control component 20 may include a main controller, a baseband module, a power amplifier module, a power module, etc., wherein the main controller may be a CPU (Central Processing Unit) or an FPGA (Field Programmable Gate Array). In other optional embodiments, the main control component 20 may also be equipped with a receiving antenna (not shown in the figure), which is used to receive electromagnetic wave signals in the air and convert them into corresponding electrical signals and then output them to the main controller. The main controller can obtain the communication information (such as communication channel, communication protocol, communication signal format, etc.) between the drone and the flight control terminal by analyzing and processing the received electrical signals, and the main controller can also generate a radio frequency signal according to the communication information, so that the antenna component 10 can transmit interference signals in a targeted manner, thereby improving the interference effect on the drone. Among them, the specific method of generating the interference signal is not limited in this embodiment, as long as it can interfere with the drone, such as blocking the communication between the drone and the flight control terminal, interfering with the navigation signal, so that the drone cannot be accurately positioned, etc.

[0069] The first plane and the second plane mentioned in this specific embodiment may be planes perpendicular to the upper end surface or the lower end surface of the antenna component 10. For example, the first plane may be perpendicular to the upper end surface or the lower end surface of the antenna component 10. Figure 3 The sides shown are parallel, or the first plane is the antenna assembly 10 as shown in FIG. Figure 3 The second plane may be aligned with the antenna assembly 10 as shown. Figure 4 The side surfaces shown are parallel, or the second plane is the antenna assembly 10 as shown in FIG. Figure 4 Alternatively, the first plane and the second plane may also be planes whose angles with the upper end face or the lower end face of the antenna assembly 10 are greater than 0° and less than 90°. The first plane and the second plane are only a reference plane, the purpose of which is to express the specific beam width of the interference signal from different perspectives. FIG3 shows that the projection of the interference signal on the first plane has a narrow first effective coverage angle A, which can also be regarded as the projection of the interference signal on the first plane. Figure 3From the perspective shown, the beamwidth of the interfering signal is narrow. Figure 4 It shows that the projection of the interference signal on the second plane has a wider second effective coverage angle B, which can also be regarded as Figure 4 From the perspective shown, the beam width of the interference signal is relatively wide. Figure 8 In actual use, unlike the beam-type interference signal, the interference signal in the embodiment of the present application is diffused in a flat shape, for example. Compared with the first plane, the interference signal in the embodiment of the present application has a wider beam in the second plane, which can be used as a "signal wall" to prevent the intrusion of aircraft.

[0070] In the actual use process, it is generally necessary to transmit interference signals through the aircraft countermeasure device 1 of this specific embodiment to interfere with the entry of drones. Since the interference signal has the characteristic that the first effective coverage angle A projected on the first plane is smaller than the second effective coverage angle B projected on the second plane by the interference signal, the interference signal in the embodiment of the present application presents a "wall-shaped" form as a whole. In this way, by setting the aircraft countermeasure device 1 proposed in the embodiment of the present application around the control area, it is possible to make the interference signal act as a signal wall on the boundary of the control area that prevents drones from flying through when using the aircraft countermeasure device 1. Therefore, the aircraft countermeasure device proposed in the embodiment of the present application can prevent aircraft from entering the control area while avoiding the emission of strong interference signals in all directions, thereby achieving the effect of reducing the impact on nearby wireless communications.

[0071] In other optional embodiments, the second plane in the aircraft countermeasure device 1 can be set along the boundary of the controlled area. Since the first effective coverage angle A of the interference signal projected on the first plane is smaller than the second effective coverage angle B of the interference signal projected on the second plane, the overlapping area of ​​the interference signals of adjacent aircraft countermeasure devices 1 can be increased, thereby effectively improving the interference effect.

[0072] Combination Figure 1 , Figure 2 , Figure 3 As shown, the antenna assembly 10 can be set as a nearly rectangular parallelepiped structure. The antenna assembly 10 has an upper end surface 11 and a lower end surface 12. The upper end surface 11 is the end surface from which the interference signal emitted from the antenna assembly 10 diffuses outward, that is, the emission surface. The lower end surface 12 is the end surface of the antenna assembly 10 relative to the upper end surface 11.

[0073] like Figure 3 As shown, D1 is the length direction of the antenna assembly 10. Figure 4 As shown, D2 is the width direction of the antenna assembly 10. Specifically, the first plane is perpendicular to the width direction of the antenna assembly 10, and the second plane is perpendicular to the length direction of the antenna assembly 10. Of course, the antenna assembly 10 can also be set to be other than Figure 1 , Figure 2 Other structures besides the shapes shown are determined according to actual conditions.

[0074] In a specific embodiment, the aircraft countermeasure device further includes a fixing member 60. When using the aircraft countermeasure device 1 provided in this specific embodiment, the aircraft countermeasure device 1 needs to be first installed on the fixing member 60. The main control component 20 controls the antenna component 10 to send an interference signal to interfere with the aircraft and prevent the aircraft from entering the control area.

[0075] Based on the above embodiments, Figure 1 , Figure 2 As shown, the antenna assembly 10 includes an upper end surface 11, and the interference signal is emitted from the upper end surface 11. The side P1 of the upper end surface 11 along the length direction is parallel to the length direction of the antenna assembly 10. The side P2 of the upper end surface 11 along the width direction is parallel to the width direction of the antenna assembly 10. Figure 3 As shown, A is the first effective coverage angle of the interference signal in the first plane, L1 is the angle bisector of the first effective coverage angle A in the first plane, and the angle bisector L1 of the first effective coverage angle A can be perpendicular to the upper end surface 11. In this embodiment, the interference signal radiates to both sides with a smaller coverage range relative to the middle section perpendicular to the upper end surface 11 and the length direction D1, so that the thickness of the "signal wall" is thinner to prevent the interference signal from interfering with the legal equipment in the control area. At the same time, the interference signal generated during the interference work radiates upward, which can effectively interfere with aircraft in the air (such as drones).

[0076] Further, we can Figure 3 As shown, the antenna assembly 10 is also provided with a lower end surface 12 opposite to the upper end surface 11. Of course, the upper end surface 11, the lower end surface 12 and other side surfaces are surrounded to form a shell of the antenna assembly 10. Of course, the antenna assembly 10 can also be other structural forms, which are determined according to actual conditions.

[0077] like Figure 4 As shown, B is the second effective coverage angle of the interference signal in the second plane, and L2 is the angular bisector of the second effective coverage angle B in the second plane. The angular bisector L2 of the second effective coverage angle B is perpendicular to the upper end face 11. In this embodiment, the interference signal radiates to both sides with a larger coverage range relative to the middle section perpendicular to the upper end face 11 and perpendicular to the width direction D2, that is, when the interference work is performed, the signal wall formed by the interference signal extends along the width direction D2, which is convenient for arranging the antenna assembly 10. Among them, the specific method of generating the signal is not limited in this embodiment. If applied to aircraft countermeasures, the interference signal can interfere with the aircraft as long as it can, such as blocking the communication between the drone and the flight control terminal, interfering with the navigation signal, so that the drone cannot be accurately positioned, etc.

[0078] In this specific embodiment, the first plane is parallel to the length direction of the antenna assembly 10, the second plane is parallel to the width direction of the antenna assembly 10, and the dimension of the antenna assembly 10 in the width direction is smaller than the dimension in the length direction. When deploying the aircraft countermeasure device 1, the width direction of the antenna assembly 10 can be set along the boundary of the control area. Since the radiation range of the interference signal along the width direction is relatively wide, adjacent aircraft countermeasure devices 1 can be arranged at a certain interval, as long as the interference signals radiated by the two aircraft countermeasure devices 1 form a continuous coverage range. At the same time, there is a gap between adjacent aircraft countermeasure devices 1, which can also avoid interference between adjacent aircraft countermeasure devices 1 during deployment and installation.

[0079] On the basis of the above-mentioned embodiment that the aircraft countermeasure device 1 includes the fixing member 60, as shown in FIG. Figure 1 , Figure 2 As shown, the aircraft countermeasure device 1 also includes a mounting assembly (not separately marked). The antenna assembly 10 is rotatably mounted on the fixing member 60 through the mounting assembly. The main control assembly 20 is fixedly mounted to the fixing member 60 through the mounting assembly. Among them, the fixing member 60 can be a columnar structure. In this embodiment, the installation angle of the antenna assembly 10 relative to the fixing member 60 can be adjusted. For example, according to actual needs, the antenna assembly 10 is rotated relative to the fixing member 60 in the pitch direction to adjust the transmission direction of the antenna assembly 10, thereby improving the interference effect.

[0080] Specifically, the mounting assembly may include a first mounting structure 30 and a second mounting structure 40. The antenna assembly 10 is rotatably mounted on the first mounting structure 30, and the first mounting structure 30 is fixed to the fixing member 60. The main control assembly 20 is fixed to the second mounting structure 40, and the second mounting structure 40 is fixed to the fixing member 60.

[0081] like Figure 1 As shown, the first mounting structure 30 is sleeved on the fixing member 60, and the mounting position along the height direction of the fixing member 60 is adjustable. The first mounting structure 30 is provided with a rotating part 301, and the rotating part 301 is connected to the antenna assembly 10. The antenna assembly 10 can rotate along the pitch direction relative to the fixing member 60. By adjusting the rotating part 301, the tilt angle of the antenna assembly 10 can be adjusted to adjust the tilt angle of the signal emitted by the antenna assembly 10 according to actual conditions. In other optional embodiments, the fixing member 60 can also be implemented by a pole-shaped facility near the control area, such as a telephone pole or a street light pole.

[0082] Furthermore, a directional antenna may be provided in the antenna assembly 10. Alternatively, an omnidirectional antenna and a metal reflector may be provided in the antenna assembly 10 to achieve the emission of interference signals. The metal reflector may be provided in the back lobe radiation direction of the omnidirectional antenna to reflect the back lobe radiation of the omnidirectional antenna to be superimposed with the front lobe radiation, thereby achieving the effect of directional emission of interference signals.

[0083] Specifically, refer to Fig.10 , 11 The antenna assembly 10 may include an outer shell 100a and a directional antenna assembly, wherein the directional antenna assembly is disposed in the outer shell 100a and is used to transmit signals. The signal transmitted by the directional antenna assembly is projected on a first plane (e.g. Figure 3 The first effective coverage angle A shown in FIG. 1 is smaller than the projection of the signal on the second plane (as shown in FIG. Figure 4 The first plane is perpendicular to the second plane, the first plane is parallel to the length direction of the antenna assembly 10, and the first plane and the second plane are both perpendicular to the radiation surface 100a1 of the outer shell 100a. The radiation surface 100a1 is also the upper end surface 11 mentioned above.

[0084] The radiation surface 100a1 mentioned in the embodiment of the present application is a surface used for transmitting signals in the directional antenna assembly.

[0085] When using the antenna assembly 10 provided in this specific embodiment, as Figures 11 to 13 As shown, the antenna assembly 10 may include a plurality of antennas 150. The plurality of antennas 150 are arranged parallel to each other. When the signal transmitted by the antenna 150 reaches the reflector 140, it will be reflected by the reflector 140, so that the rear lobe of the antenna 150 is reflected and superimposed with the corresponding front lobe, so that the first effective coverage angle A of the signal transmitted by the antenna 150 projected on the first plane is smaller than the second effective coverage angle B of the signal projected on the second plane. The first plane is perpendicular to the second plane. The first plane is a plane arranged along the length direction of the antenna 150, and the second plane is a plane arranged perpendicular to the length direction of the antenna 150.

[0086] Since the effective coverage angles of the signal emitted by this antenna assembly 10 in the first plane and the second plane are different, when applied to aircraft countermeasures equipment, the second plane can be set along the edge of the controlled area, which is beneficial to increase the interference range corresponding to a single aircraft countermeasures equipment. While meeting the requirements, the number of aircraft countermeasures equipment can be effectively reduced.

[0087] Based on the above embodiments, Figures 11 to 13As shown, the directional antenna assembly may specifically include a reflector 140 and an antenna 150, wherein the reflector 140 is provided with a mounting bracket 160. The antenna 150 is provided on the mounting bracket 160, and there is a gap between the antenna 150 and the reflector 140. The antenna 150 is an omnidirectional antenna, and the antenna 150 is located between the radiation surface 100a1 and the reflector 140.

[0088] In actual use, the reflector 140 can be made of metal, and the antenna 150 can be a directional antenna or an omnidirectional antenna. If the antenna 105 is an omnidirectional antenna, the front lobe of the antenna 150 is emitted toward the radiation surface 100a1, and the reflector 140 can reflect the back lobe of the antenna 150 to overlap with the front lobe. Therefore, the signal finally emitted from the radiation surface 100a1 includes both the front lobe of the antenna and the reflected back lobe. For example, when the antenna 150 uses a fiberglass antenna of an omnidirectional antenna, the reflector 140 can not only cooperate with the fiberglass antenna of the omnidirectional antenna to achieve the effect of a directional antenna, but also help to improve the gain of the front lobe of the antenna 150.

[0089] In this specific embodiment, the antenna 150 is disposed on the mounting frame 160, which can effectively support and fix the antenna 150, and can effectively improve the stability of the installation of the antenna 150. In addition, the antenna 150 is an omnidirectional antenna, which has a relatively simple design, a simpler installation process, does not require precise alignment, and has a low cost.

[0090] In a specific embodiment, if Fig.11 As shown, along the length direction of the antenna 150 , at least a portion of the antenna 150 has one end disposed on the outer shell 100 a and the other end disposed on the mounting bracket 160 .

[0091] The length direction of the antenna 150 is parallel to the length direction D1 of the antenna assembly 10. If one end of the antenna 150 is mounted on the outer shell 100a and the other end is mounted on the mounting bracket 160, it is equivalent to that the mounting bracket 160 is located at the end of the antenna 150. Since the main radiation area of ​​the antenna 150 is in the middle, the mounting bracket 160 is located at the end of the antenna 150, which has little effect on the radiation performance of the antenna 150 and can make as many back lobes as possible be reflected to improve the gain of the antenna 150.

[0092] like Fig.11As shown, the antenna assembly 10 may specifically include a first end cap 110, a housing 120, a second end cap 130, a reflector 140, an antenna 150, and a mounting bracket 160. The first end cap 110, the housing 120, and the second end cap 130 constitute the entire external shell portion of the antenna assembly 10. The housing 120 is, for example, barrel-shaped. The first end cap 110 and the second end cap 130 are respectively covered at both ends of the length direction of the housing 120 to form a sealed cavity with the housing 120. The reflector 140, the antenna 150, and the mounting bracket 160 are all arranged in the space formed by the housing 120, the first end cap 130, and the second end cap 110. The antenna 150 may be a columnar fiberglass antenna, one end of the antenna 150 is fixed on the inner side of the second end cap 130 or the first end cap 110, and the other end of the antenna 150 is mounted on the mounting bracket 160, and the mounting bracket 160 is mounted on the reflector 140. In this embodiment, if the lengths of all antennas 150 are similar, the other ends of all antennas 105 can be similar to each other. Fig.11 The other ends of the four antennas 150 on the left side are all mounted on the mounting frame 160. If the length of an antenna 150 is much longer than the length of the other antennas 150, such as Fig.11 Like the rightmost antenna 150 , the other ends of these longer antennas 150 can be suspended in the air or installed on the first end cover 110 or the second end cover 130 , and the middle part thereof can be mounted on the mounting frame 160 .

[0093] In this specific embodiment, the reflector 140, antenna 150, and mounting bracket 160 are all arranged in the space formed by the outer shell 120, the first end cover 130, and the second end cover 110, which can effectively protect the antenna 150 and reduce the impact of the external environment on the life of the antenna 150.

[0094] Specifically, the antenna 150 may be a cylindrical antenna, and the extension direction of the antenna 150 is parallel to the length direction of the radiation surface 100a1, so that the radiation direction of the antenna assembly 10 as a whole can be wider in its width direction and narrower in the length direction. The length direction of the radiation surface 100a1 is parallel to the length direction D1 of the antenna assembly 10. The antenna 150 may be a fiberglass antenna.

[0095] The radiation surface 100a1 mentioned in this specific embodiment is the outer surface of the side wall of the housing 120 that is opposite to and spaced from the reflection plate 140 and radiates signals outward.

[0096] On the basis of the above embodiment, the number of the antennas 150 may be multiple, and the multiple antennas 150 are distributed at intervals in the width direction of the reflector 140 .

[0097] Specifically, the width direction of the reflector 140 is parallel to the width direction D2 of the antenna assembly 10. Fig.12As shown, the antenna 150 includes a first antenna 151, a second antenna 152, a third antenna 153, a fourth antenna 154, and a fifth antenna 155. The frequency band of each antenna 150 can be set to correspond to the communication frequency band of an aircraft. Each antenna 150 is set above the reflector 140 and at a certain distance from the reflector 140. Of course, in actual settings, the number of antennas 150 is not limited to the five used in this solution, and can be more or less than five.

[0098] Specifically, the distance between the center of the cross section of the antenna 150 and the reflector 140 is (1 / 4)*λ, where λ is the wavelength of the frequency band corresponding to the signal transmitted by the antenna 150, so as to better achieve directional transmission. Among them, the distance between each antenna 150 and the reflector 140 depends on the frequency band of its own transmitted signal. Therefore, if different antennas 150 correspond to different frequency bands, the distances between different antennas 150 and the reflector 140 are also different.

[0099] Based on the above embodiments, Fig.13 As shown, the mounting frame 160 specifically includes a connecting substrate 161, a clamping portion 163, and a supporting portion 162, wherein the connecting substrate 161 is used to connect to the reflector 140. The clamping portion 163 is disposed on the side of the connecting substrate 161 that is away from the reflector 140, that is, the clamping portion 163 is closer to the radiation surface 100a1. In addition, the clamping portion 163 is used to clamp the antenna 150. One end of the supporting portion 162 is connected to the connecting substrate 161, and the other end is connected to the clamping portion 163.

[0100] At least one of the clamping portion 163 and the supporting portion 162 is an insulating elastic member, which can effectively fix the antenna 150 and avoid affecting the operation of the antenna 150 compared to metal materials. It can also have a certain anti-vibration effect due to its elasticity.

[0101] On the other hand, since the mounting bracket 160 is located between the antenna 150 and the reflector 140, it may affect the reflective effect of the reflector 140 on the back lobe radiation of the antenna 150. Therefore, the mounting bracket 160 is arranged at the end position in the length direction of the antenna 150. Since the main radiation area of ​​the antenna 150 is in the middle position in the length direction, not at the end position, the antenna mounting bracket 160 installed at the end of the antenna 150 has little effect on the radiation performance of the antenna 150. Specifically, the mounting bracket 160 can be arranged at an end of the reflector 140 away from the second end cover 130. Compared with fixing the mounting bracket 160 at the middle position of the antenna 150, fixing the mounting bracket 160 at the end position in the length direction of the antenna 150 can reduce the influence of the mounting bracket 160 on the reflection effect of the reflector 140.

[0102] Furthermore, the clamping portion 163 may have an opening disposed toward the radiation surface 100a1, and both sides of the opening of the clamping portion 163 may be elastic structures.

[0103] like Fig.12 and Fig.13 As shown, the clamping portion 163 is a "C"-shaped structure. Since the clamping portion 163 is made of plastic material and has a certain elasticity, the antenna 150 can be inserted into the clamping portion 163 through the opening of the "C"-shaped structure. If the antenna 150 is a fiberglass antenna, the "C"-shaped clamping portion 163 is compatible with the axial cross-sectional shape of the fiberglass antenna, so the cylindrical fiberglass antenna can also be effectively clamped and fixed.

[0104] In this specific embodiment, the clamping portion 163 is configured to have an opening toward the radiation surface 100a1, which facilitates placing the antenna 150 in the clamping portion 163 and simplifies the operation process.

[0105] like Fig.13 As shown, the support portion 162 may specifically include a first support rib 162A, a second support rib 162B, and a third support rib 162C. The third support rib 162C is connected between the first support rib 162A and the second support rib 162B, and the thickness of the third support rib 162C is less than or equal to the thickness of the first support rib 162A or the thickness of the second support rib 162B, so as to reduce the weight of the mounting frame 160, which is conducive to achieving lightweight.

[0106] like Figure 2 As shown, the second mounting structure 40 is clamped on the fixing member 60 , and the mounting height of the second mounting structure 40 on the fixing member 60 is adjustable.

[0107] Specifically, the second mounting structure 40 can be implemented by a frame structure formed by a plurality of mounting rods fixedly connected, the main control assembly 20 can be fixed to the outside of the frame structure by a fastening structure, and the fixing member 60 can pass through the middle hollow part of the frame structure. Alternatively, the second mounting structure 40 can also be set as a clamping claw structure. Alternatively, the second mounting structure 40 can also be set as a structure with a mounting sleeve and a tightening member, the mounting sleeve is set on the fixing member 60, and the tightening member passes through the mounting sleeve and tightens to the fixing member 60. Of course, the second mounting structure 40 can also be other structural forms, which are determined according to actual conditions and will not be described in detail here.

[0108] In this embodiment, the main control component 20 can be fixedly mounted on the fixing member 60 through the second mounting structure 40, and the antenna component 10 can be rotatably mounted on the fixing member 60 through the first mounting structure 30. After the antenna component 10 is adjusted to a suitable angle, the antenna component 10 is fixed to the fixing member 60, and then the aircraft countermeasure device 1 can start to perform interference work. Since the coverage range of the interference signal emitted by the antenna component 10 is flat, it can form an effect similar to a "signal wall", which is convenient for protecting the control area.

[0109] In addition to the above-mentioned aircraft countermeasure device 1, an embodiment of the present application also provides an aircraft control system including a plurality of aircraft countermeasure devices 1 mentioned in any of the above items. The plurality of aircraft countermeasure devices 1 are arranged along the boundary S of the control area. For the structure of other parts of the aircraft control system, please refer to the prior art and will not be repeated herein.

[0110] Specifically, multiple aircraft countermeasure devices 1 can all be arranged outside the boundary S of the controlled area, or multiple aircraft countermeasure devices 1 can all be arranged on the boundary S of the controlled area; or, some aircraft equipment 1 can be arranged outside the boundary S of the controlled area, while the remaining aircraft equipment 1 can be arranged on the boundary S of the controlled area.

[0111] like Figure 7 As shown, for example, eight aircraft countermeasures 1 (1A, 1B, 1C, 1D, 1E, 1F, 1G, and 1H) are arranged along the boundary S of the controlled area. In actual use, after these aircraft countermeasures 1 start to interfere, all interference signals form an effect similar to a "signal wall" above the boundary S of the controlled area. If a drone approaches the "signal wall", it may hover, return, or land under the action of the interference signal, thereby preventing the drone from entering the controlled area. In other embodiments, multiple aircraft countermeasures 1 may also be arranged outside the boundary S of the controlled area, that is, multiple aircraft countermeasures 1 are arranged in sequence along the outside of the boundary S of the controlled area, thereby surrounding the controlled area. For example, relative to Figure 8 In general, all aircraft countermeasure devices 1 are moved a certain distance outside the control area. In this way, the area enclosed by all aircraft countermeasure devices 1 will be larger than the control area, and the effect of protecting the control area can still be achieved.

[0112] The control area can be Figure 7 , Figure 8 The shape shown can also be other shapes depending on the actual situation.

[0113] In a specific embodiment, the first plane is perpendicular to the width direction of the antenna assembly 10, and the second plane is perpendicular to the length direction of the antenna assembly 10. The width direction of at least one antenna assembly 10 is parallel to the boundary S of the control area corresponding to the location of the aircraft countermeasure device 1.

[0114] The boundary S of the control area corresponding to the location of the aircraft countermeasure device 1 refers to the boundary S closest to the aircraft countermeasure device 1. Figure 7 For example, for aircraft countermeasure devices 1H and 1G, the corresponding control area boundary S is the boundary on the left; for aircraft countermeasure devices 1C and 1D, the corresponding control area boundary S is the boundary on the right. The width direction D2 of the antenna component 10 can be set to be parallel to the boundary S of the control area corresponding to the location of the aircraft countermeasure device 1, that is, the edge P2 along the width direction of the upper end surface 11 of the antenna component 10 is parallel to the boundary S of the control area. At this time, the second plane is parallel to the boundary S of the control area corresponding to the location of the aircraft countermeasure device 1. Since the first effective coverage angle A of the interference signal projected on the first plane is smaller than the second effective coverage angle B of the interference signal projected on the second plane, that is, Figure 8 As shown, the interference signal covers the boundary S of the control area with a wide beam, that is, the length of the boundary S of the control area that can be covered by the interference signal of a single antenna assembly 10 is increased as much as possible.

[0115] In other embodiments, the width direction of at least one antenna assembly 10 may form a certain angle with the boundary S of the control area corresponding to the location of the aircraft countermeasure device 1, and the angle is less than 45 degrees. In other words, the width direction of the antenna assembly 10 may not be Figure 7 It is shown to be exactly parallel to the boundary S of the control area, and can also be slightly inclined relative to the boundary S of the control area. In this case, the effect of forming a "signal wall" can still be achieved.

[0116] In a specific embodiment, the first plane is perpendicular to the width direction of the antenna assembly 10, and the second plane is perpendicular to the length direction of the antenna assembly 10. The projection of the side of at least one antenna assembly 10 parallel to the length direction D1 on the horizontal plane is perpendicular to the boundary S of the control area corresponding to the position of the aircraft countermeasure device 1. At this time, the first plane is perpendicular to the boundary S of the control area. In this way, the beam of the interference signal radiated by the antenna assembly 10 in the direction perpendicular to the boundary S is narrower, which is equivalent to the thickness of the "signal wall" being thinner, thereby ensuring that the interference signal only exists near the boundary S and does not interfere in the control area. Therefore, the antenna assembly 10 is arranged on the boundary S of the control area in the above manner (that is, the width direction D2 is parallel to the boundary S of the control area corresponding to the position of the aircraft countermeasure device 1, and the projection of the length direction D1 on the horizontal plane is perpendicular to the boundary S of the control area corresponding to the position of the aircraft countermeasure device 1), the beam along the boundary S direction is wider, and the beam perpendicular to the boundary S direction is narrower, so that the interference signal is distributed only along the boundary S as much as possible, and the width extending to the inside and outside of the boundary S of the control area is reduced, so as to form the effect of the "signal wall" as much as possible.

[0117] It should be noted that since the drone is flying in the air, the interference signal emitted by the aircraft countermeasure device 1 needs to cover the required height range of the boundary S of the controlled area. At the same time, the interference signal emitted by the aircraft countermeasure device 1 needs to be located on the boundary S of the controlled area or outside the boundary S of the controlled area to avoid interference with legitimate equipment in the controlled area.

[0118] On the basis of the above embodiment, the angle between the side surface of the aircraft countermeasure device 1 parallel to the second plane and the vertical plane of the boundary S of the control area corresponding to the position of the aircraft countermeasure device 1 can be greater than or equal to 0° and less than 90°, so that the interference signal emitted by the aircraft countermeasure device 1 extends obliquely outside the boundary S relative to the boundary S of the control area or extends along the boundary S of the control area, so that the control area is completely enclosed in the signal wall.

[0119] Specifically, Figure 8 As shown, the angle between the side surface of the aircraft countermeasure device 1 parallel to the second plane and the vertical plane of the boundary S of the control area corresponding to the position of the aircraft countermeasure device 1 is greater than and less than 90°. The signal wall formed by the interference signal emitted by the aircraft countermeasure device 1 is inclined outward relative to the control area. The control area is enclosed inside the signal wall, which can not only appropriately increase the control range, but also avoid interfering with the legitimate equipment inside the control area.

[0120] Or, if Figure 7 , Figure 8On the basis of the above embodiment, the antenna assembly 10 of the aircraft countermeasure device 1 includes an upper end surface 11, and the interference signal is emitted from the upper end surface 11. If the aircraft countermeasure device 1 is located outside the boundary S of the control area, the upper end surface 11 includes a first end 11C and a second end 11D relative to each other, and the distance between the first end 11C and the boundary S of the control area corresponding to the location of the aircraft countermeasure device 1 is less than the distance between the second end 11D and the boundary S of the control area corresponding to the location of the aircraft countermeasure device 1. The distance mentioned here refers to the distance in the horizontal direction. In other words, in the projection on the horizontal plane, the first end 11C is closer to the boundary S of the control area than the second end 11D. In the upper end surface 11 of at least one antenna assembly 10, the height of the first end 11C is higher than the height of the second end 11D.

[0121] In the specific use process, such as Figure 7 As shown, for each aircraft countermeasure device 1, the upper end surface 11 is inclined downward and outward from the first end 11C relative to the control area. In this way, the interference signal emitted by the upper end surface 11 of the antenna assembly 10 can be directed toward the outer side of the boundary S of the control area, thereby avoiding the interference signal from affecting the normal radio communication in the control area. Alternatively, the aircraft countermeasure device 1 can also be located on the inner side of the boundary S of the control area, while the orientation of the upper end surface 11 remains unchanged, that is, obliquely upward toward the outer airspace of the control area (specifically, the height of the upper end surface 11 close to the boundary S of the control area corresponding to the position of the aircraft countermeasure device 1 is lower than the height of the end away from the boundary S of the control area corresponding to the position of the aircraft countermeasure device 1. The closeness and distance here are also determined based on the horizontal distance).

[0122] In another alternative embodiment, referring to Fig. 9 As shown, a plurality of aircraft countermeasure devices 1 are arranged outside the boundary of the control area. The antenna assembly 10 of the aircraft countermeasure device 1 includes an upper end surface 11, and the interference signal is emitted from the upper end surface 11. The upper end surface 11 includes a first end 11C and a second end 11D opposite to each other. The distance between the first end 11C and the boundary of the control area corresponding to the location of the aircraft countermeasure device 1 is smaller than the distance between the second end 11D and the boundary of the control area corresponding to the location of the aircraft countermeasure device 1.

[0123] In the upper end surface 11 of at least one antenna assembly 10 , the height of the first end 11C is lower than the height of the second end 11D.

[0124] According to the needs of different scenarios, if interference needs to be carried out inside the control area, and the area to be protected is outside the control area, the tilt direction of the antenna assembly 10 can be different from Figure 7 The directions shown are opposite. Fig. 9: If the aircraft countermeasure device 1 is still located outside the boundary of the controlled area, the upper end surface 11 includes a first end 11C and a second end 11D relative to each other, and the distance between the first end 11C and the boundary of the controlled area corresponding to the location of the flight countermeasure device 1 is less than the distance between the second end 11D and the boundary of the controlled area corresponding to the location of the flight countermeasure device 1, that is, the first end 11C is closer to the boundary S of the controlled area than the second end 11D. The distance mentioned here refers to the distance in the horizontal direction. Moreover, in the upper end surface 11 of at least one antenna assembly 10, the height of the first end 11C is lower than the height of the second end 11D. In other words, at this time, the inclination direction of the antenna assembly 10 is inclined toward the airspace within the controlled area. Alternatively, in other alternatives, the aircraft countermeasure device 1 may also be located on the inner side of the control area boundary S, but the orientation of the upper end surface 11 remains unchanged, that is, it is still facing the airspace inside the control area (in this case, the height of the upper end surface 11 close to the control area boundary S corresponding to the location of the flight countermeasure device 1 is higher than the height of the upper end surface 11 away from the control area boundary S corresponding to the location of the flight countermeasure device 1).

[0125] Fig. 9 and 8 The difference in the way the graph is set up is that Figure 8 The aircraft control system in the system is to prevent foreign drones from flying into the airspace above the control area. Fig. 9 The aircraft control system in the control area is to control the drones in the area to fly out from the airspace above it. Fig. 9 It can be seen from the arrangement shown that the upper end surface 11 of each drone countermeasure device 1 is obliquely upward toward the airspace within the control area. The difference is that Figure 8 The upper end surface 11 of each UAV countermeasure device 1 is obliquely upward toward the airspace outside the controlled area.

[0126] It is understandable that different drone countermeasure devices 1 can be set at different locations on the border. For example: Fig. 9 In the configuration shown, some of the eight drone countermeasure devices 1 (e.g., 1A, 1B, 1H) are located on the boundary S of the control area, and the remaining devices (e.g., 1C, 1D, 1E, 1F, 1G) are located outside the boundary S of the control area. Fig. 9 In the configuration shown, the first end 11C and the second end 11D of the upper end surface 11 of the drone countermeasure device 1 specifically refer to the ends Figure 8 In the configuration, the first end 11C and the second end 11D of the upper end surface 11 are opposite to each other. Here, according to the height difference, the upper end surface 11 can also be defined as having opposite top and bottom ends along the length direction. Figure 7 , Figure 8In the arrangement shown, the first end 11C of the upper end surface 11 is its top end, and the second end 11D is its bottom end. Fig. 9 In the arrangement shown, the first end 11C of the upper end surface 11 is its bottom end, and the second end 11D is its top end.

[0127] In a specific embodiment, the interference signals emitted by multiple aircraft countermeasures devices 1 surround the control area along the boundary of the control area. In this embodiment, when the aircraft countermeasures devices 1 are arranged along the boundary of the control area, the distance between two adjacent aircraft countermeasures devices 1 must at least ensure that the interference signals generated by the two aircraft countermeasures devices 1 have a continuous coverage range above the boundary, that is, the boundary of the interference signals formed by the two adjacent aircraft countermeasures devices 1 can at least be just connected to form a continuous signal wall. In this way, the air above each side of the boundary is continuously covered with interference signals, so that the control area can be surrounded.

[0128] Furthermore, the interference signals emitted by two adjacent aircraft countermeasure devices 1 may have a signal overlap area along the boundary of the control area. In this way, not only a continuous signal wall can be formed for the control area, but also the interference effect can be enhanced for the overlapping area, thereby improving the interference effect of the signal wall formed by all aircraft countermeasure devices 1.

[0129] Each embodiment in this specification is described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the embodiments can be referenced to each other. Any combination of all embodiments provided in this application is within the scope of protection of this application and will not be described in detail here.

[0130] The above is a detailed introduction to the aircraft countermeasure device 1 and the aircraft control system provided by the present application. Specific examples are used in this article to illustrate the principles and implementation methods of the present application. The description of the above embodiments is only used to help understand the method of the present application and its core idea. It should be pointed out that for ordinary technicians in this technical field, without departing from the principles of the present application, several improvements and modifications can be made to the present application, and these improvements and modifications also fall within the scope of protection of the claims of the present application.

Claims

1. An aircraft countermeasure device, characterized in that: include: An antenna assembly (10), the antenna assembly (10) being used to transmit an interference signal; a main control component (20), the main control component (20) being electrically connected to the antenna component (10), and the main control component (20) being used to control the antenna component (10) to transmit the interference signal; A first effective coverage angle of the interference signal projected on the first plane is smaller than a second effective coverage angle of the interference signal projected on the second plane, and the first plane is perpendicular to the second plane.

2. The aircraft countermeasure device according to claim 1, characterized in that: The first plane is perpendicular to the width direction of the antenna component (10), and the second plane is perpendicular to the length direction of the antenna component (10).

3. The aircraft countermeasure device according to claim 2, characterized in that: The antenna component (10) comprises an upper end surface (11), and the interference signal is emitted from the upper end surface (11); an edge (P1) of the upper end surface (11) along the length direction is parallel to the length direction of the antenna component (10); and an edge (P2) of the upper end surface (11) along the width direction is parallel to the width direction of the antenna component (10).

4. The aircraft countermeasure device according to claim 1, characterized in that: The aircraft countermeasure device further comprises a mounting assembly and a fixing member (60); the antenna assembly (10) is rotatably mounted on the fixing member (60) via the mounting assembly; and the main control assembly (20) is mounted on the fixing member (60) via the mounting assembly.

5. The aircraft countermeasure device according to claim 4, characterized in that: The mounting assembly comprises: a first mounting structure (30) and a second mounting structure (40); the antenna assembly (10) is rotatably mounted on the first mounting structure (30), and the first mounting structure (30) is fixed to the fixing member (60); the main control assembly (20) is fixedly mounted on the second mounting structure (40), and the second mounting structure (40) is fixedly mounted on the fixing member (60).

6. The aircraft countermeasure device according to claim 4, characterized in that: The antenna assembly (10) can rotate along a pitch direction relative to the fixing component (60).

7. The aircraft countermeasure device according to any one of claims 1 to 6, characterized in that: The antenna assembly (10) is provided with a directional antenna; Or the antenna assembly (10) is provided with an omnidirectional antenna and a metal reflector.

8. An aircraft control system, characterized in that: It comprises a plurality of aircraft countermeasure devices (1) according to any one of claims 1 to 7, wherein the plurality of aircraft countermeasure devices (1) are arranged along the boundary of the control area.

9. The aircraft control system according to claim 8, characterized in that: The first plane is perpendicular to the width direction of the antenna component (10), and the second plane is perpendicular to the length direction of the antenna component (10); The width direction of at least one of the antenna assemblies (10) is parallel to the boundary of the control area corresponding to the location of the flight countermeasure device (1).

10. The aircraft control system according to claim 8, characterized in that: A plurality of the aircraft countermeasure devices (1) are arranged outside the boundary of a control area; the antenna assembly (10) of the aircraft countermeasure device (1) comprises an upper end surface (11), and the interference signal is emitted from the upper end surface (11); the upper end surface (11) comprises a first end and a second end opposite to each other; the distance between the first end and the boundary of the control area corresponding to the location of the aircraft countermeasure device (1) is smaller than the distance between the second end and the boundary of the control area corresponding to the location of the aircraft countermeasure device (1); In the upper end surface (11) of at least one of the antenna components (10), the height of the first end is higher than the height of the second end.

11. The aircraft control system according to claim 8, characterized in that: A plurality of the aircraft countermeasure devices (1) are arranged outside the boundary of a control area; the antenna assembly (10) of the aircraft countermeasure device (1) comprises an upper end surface (11), and the interference signal is emitted from the upper end surface (11); the upper end surface (11) comprises a first end and a second end opposite to each other; the distance between the first end and the boundary of the control area corresponding to the location of the aircraft countermeasure device (1) is smaller than the distance between the second end and the boundary of the control area corresponding to the location of the aircraft countermeasure device (1); In the upper end surface (11) of at least one of the antenna components (10), the height of the first end is lower than the height of the second end.

12. The aircraft control system according to claim 8, characterized in that: The first plane is perpendicular to the width direction of the antenna component (10), and the second plane is perpendicular to the length direction of the antenna component (10); The projection of the side of at least one of the antenna components (10) parallel to the length direction on the horizontal plane is perpendicular to the boundary of the control area corresponding to the location of the aircraft countermeasure device (1).

13. The aircraft control system according to claim 8, characterized in that: The interference signals emitted by the plurality of aircraft countermeasure devices (1) surround the controlled area along the boundary of the controlled area.

14. The aircraft control system according to claim 8, characterized in that: The interference signals emitted by two adjacent aircraft countermeasure devices (1) have a signal overlapping area along the boundary of the control area.

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