Aircraft countermeasure device and aircraft control system

Abstract

An aircraft countermeasure device and an aircraft control system, which relate to the technical field of aircraft control. The aircraft countermeasure device comprises an antenna assembly and a main control assembly, wherein the antenna assembly is used for transmitting an interference signal to interfere with an aircraft; and the main control assembly is electrically connected to the antenna assembly, and the main control assembly is used for controlling the antenna assembly to transmit the interference signal. A first effective coverage angle of the projection of the interference signal on a first plane is less than a second effective coverage angle of the projection of the interference signal on a second plane, wherein the first plane is perpendicular to the second plane.

Description

Aircraft countermeasure equipment and aircraft control system

[0001] This application claims priority to the Chinese patent applications filed with the China Patent Office on December 4, 2023, with application number 202323289974.X and application name “Aircraft countermeasure equipment and aircraft countermeasure system” and filed with the China Patent Office on November 15, 2024, with application number 202411640124.6 and application name “An aircraft countermeasure equipment and aircraft control system”, the entire contents of which are incorporated by reference into this application. Technical Field

[0002] 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

[0003] With the growing popularity of drones, an increasing number of low-flying, slow-moving, and small aircraft are appearing. These aircraft are strictly prohibited from approaching, passing through, or flying over areas with high security requirements, such as prisons and government offices. To protect the safety of controlled areas and prevent aircraft from entering them, countermeasures are necessary. However, current countermeasures emit strong interference signals in all directions, potentially disrupting nearby wireless communications.

[0004] 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

[0005] Based on this, it is necessary to provide an aircraft countermeasure device.

[0006] An aircraft countermeasure device includes an antenna assembly and a main control assembly. The antenna assembly is configured to transmit a jamming signal to interfere with an aircraft. The main control assembly is electrically connected to the antenna assembly and configured to control the antenna assembly to transmit the jamming signal. A first effective coverage angle of the jamming signal projected on a first plane is smaller than a second effective coverage angle of the jamming signal projected on a second plane, and the first plane is perpendicular to the second plane.

[0007] An aircraft control system includes multiple aircraft countermeasure devices, each of which is arranged along the boundary of a control area. The aircraft countermeasure devices include an antenna assembly and a main control assembly. The antenna assembly is configured to transmit an interference signal to interfere with an aircraft. The main control assembly is electrically connected to the antenna assembly and configured to control the antenna assembly to transmit the interference signal. A first effective coverage angle of the interference signal projected on a first plane is smaller than a second effective coverage angle of the interference signal projected on a second plane, and the first plane is perpendicular to the second plane.

[0008] The details of one or more embodiments of the present application are set forth in the accompanying drawings and the description below. Other features, objects, and advantages of the invention will become apparent from the description, drawings, and claims. BRIEF DESCRIPTION OF THE DRAWINGS

[0009] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, without paying any creative work, they can also obtain drawings of other embodiments based on these drawings.

[0010] FIG1 is a schematic structural diagram of a specific embodiment of an aircraft countermeasure device provided in an embodiment of the present application.

[0011] FIG2 is a schematic structural diagram of the aircraft countermeasure device in FIG1 installed on a fixing member.

[0012] FIG3 is a schematic diagram of a first effective coverage angle of an interference signal projected on a first plane.

[0013] FIG4 is a schematic diagram of a second effective coverage angle of an interference signal projected on a second plane.

[0014] FIG5 is a schematic diagram of a simulation of the radiation effect of the interference signal on the first plane.

[0015] FIG6 is a schematic diagram of a simulation of the radiation effect of the interference signal on the second plane.

[0016] FIG7 is a schematic diagram of a setting of an aircraft control system at a control area boundary provided in an embodiment of the present application.

[0017] FIG8 is a schematic diagram of a signal wall formed by the aircraft control system in FIG7 .

[0018] FIG9 is a schematic diagram of another configuration of the aircraft control system at the control area boundary provided in an embodiment of the present application.

[0019] FIG10 is a schematic structural diagram of an antenna assembly provided in an embodiment of the present application.

[0020] FIG. 11 is an exploded view of the antenna assembly of the embodiment shown in FIG. 10 .

[0021] FIG12 is a schematic diagram of the assembly of the directional antennas in the antenna assembly of the embodiment shown in FIG10 .

[0022] FIG13 is a schematic structural diagram of the mounting bracket inside the antenna assembly of the embodiment shown in FIG12 .

[0023] Explanation of Reference Numerals: 1 represents the aircraft countermeasures device. 10 represents the antenna assembly, 11 represents the upper end surface, and 12 represents the lower end surface. 100a represents the outer shell; 100a1 represents the radiating surface; 110 represents the first end cap; 120 represents the outer shell; 130 represents the second end cap; 140 represents the reflector; 150 represents the antenna; 151 represents the first antenna; 152 represents the second antenna; 153 represents the third antenna; 154 represents the fourth antenna; and 155 represents the fifth antenna. 160 represents the mounting bracket; 161 represents the connecting substrate; 162 represents the supporting portion; 162A represents the first supporting rib; 162B represents the second supporting rib; 162C represents the third supporting rib; and 163 represents the clamping portion. 20 represents the main control assembly. 30 represents the first mounting structure; 301 represents the rotating portion. 40 represents the second mounting structure. 50 represents the RF cable. 60 represents the fixing member. A represents the first effective coverage angle; B represents the second effective coverage angle. L1 is the angle bisector of the first effective coverage angle in the first plane, and L2 is the angle bisector of the second effective coverage angle in the second plane. D1 is the length of the antenna assembly, and D2 is the width of the antenna assembly. S is the boundary of the control area; P1 is the lengthwise edge of the upper end surface; P2 is the widthwise edge of the upper end surface. DETAILED DESCRIPTION

[0024] To facilitate understanding of the present application, a more comprehensive description of the present application will be provided below with reference to the accompanying drawings. The accompanying drawings illustrate preferred embodiments of the present application. However, the present application may be implemented in many different forms and is not limited to the embodiments described herein. Rather, these embodiments are provided to provide a more thorough and comprehensive understanding of the disclosure of the present application.

[0025] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by those skilled in the art to which this application pertains. The terms used in this specification are for the purpose of describing specific embodiments only and are not intended to limit this application. The term "and / or" as used herein includes any and all combinations of one or more of the associated listed items.

[0026] The above description includes examples of one or more embodiments. Of course, it is not possible to describe all possible combinations of components or methods for the purpose of describing the above embodiments, but it will be recognized by those skilled in the art that the various embodiments may be further combined and arranged. Therefore, the embodiments described herein are intended to cover all such changes, modifications and variations that fall within the scope of protection of the appended claims. In addition, to the extent that the term "comprising" is used in the specification or claims, the term is intended to be encompassed in a manner similar to the term "including", as explained by the use of "including" as a transitional word in the claims. In addition, any use of the term "or" in the specification of the claims is intended to mean a "non-exclusive or".

[0027] The core of the embodiment of the present application is to provide an aircraft countermeasure device that can prevent aircraft from entering the controlled area by emitting interference signals, and the interference signals can form an effect similar to a virtual wall.

[0028] Another core of the embodiments of the present application is to provide an aircraft control system including the above-mentioned aircraft countermeasure equipment.

[0029] As shown in Figure 1, 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, diffuses from the antenna assembly 10 in a direction away from the antenna assembly 10. The first effective coverage angle A (as shown in Figure 3) of the interference signal projected on the first plane is smaller than the second effective coverage angle B (as shown in Figure 4) of the interference signal projected on the second plane, and the first plane is perpendicular to the second plane.

[0030] 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.

[0031] The first effective coverage angle A mentioned in the embodiment of the present application may refer to the coverage angle of the signal in which the interference signal is greater than the first preset radiation intensity in the first plane projection. For example, as shown in FIG5 , the first effective coverage angle A may be an angle in the coverage range of approximately -15° to 15°. The second effective coverage angle B may refer to the coverage angle of the signal in which the interference signal is greater than the second preset radiation intensity in the second plane projection. As shown in FIG6 , the second effective coverage angle B may be an angle in the coverage range of approximately -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 interference effect. 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.

[0032] Taking into account that in the actual use process, the main control component 20 generally needs to output a radio frequency signal to the antenna component 10, therefore, the antenna component 10 and the main control component 20 can be connected via a radio frequency cable 50. The main control component 20 outputs a radio frequency signal to the antenna component 10 via 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 will not be able to operate or work normally. For example, it will not be able to communicate stably with the flight control terminal under the influence of the interference signal, resulting in hovering, crashing or returning, etc., achieving an interference effect on the drone. The main control component 20 may include a main controller, a baseband module, a power amplifier module, a power supply 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 an interference signal 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.

[0033] The first and second planes mentioned in this specific embodiment can be planes perpendicular to the upper or lower end surface of the antenna assembly 10. For example, the first plane can be parallel to the side surface of the antenna assembly 10 shown in Figure 3, or the first plane can be the plane on which the side surface of the antenna assembly 10 shown in Figure 3 lies. The second plane can be parallel to the side surface of the antenna assembly 10 shown in Figure 4, or the second plane can be the plane on which the side surface of the antenna assembly 10 shown in Figure 4 lies. Alternatively, the first and second planes can be planes whose angle with the upper or lower end surface of the antenna assembly 10 is greater than 0° and less than 90°. The first and second planes are merely reference planes, intended to illustrate the specific beamwidth of the interference signal from different perspectives. Figure 3 shows that the projection of the interference signal on the first plane has a narrow first effective coverage angle A, which can also be interpreted as indicating a narrow beamwidth of the interference signal from the perspective shown in Figure 3. Figure 4 shows that the projection of the interference signal on the second plane has a wide second effective coverage angle B, which can also be interpreted as indicating a wide beamwidth of the interference signal from the perspective shown in Figure 4. Therefore, referring to 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 act as a "signal wall" to prevent the intrusion of aircraft.

[0034] In the actual use process, it is generally necessary to transmit an interference signal through the aircraft countermeasure device 1 of this specific embodiment to interfere with the entry of the drone. 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, the interference signal in the embodiment of the present application is in a "wall-shaped" form as a whole. In this way, by arranging 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.

[0035] 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.

[0036] As shown in Figures 1, 2, and 3, antenna assembly 10 can be configured as a substantially rectangular parallelepiped. Antenna assembly 10 has an upper end surface 11 and a lower end surface 12. Upper end surface 11 is the end surface from which interference signals emitted from antenna assembly 10 diffuse outward, i.e., the emitting surface. Lower end surface 12 is the end surface of antenna assembly 10 opposite upper end surface 11.

[0037] As shown in Figure 3, D1 represents the length of antenna assembly 10, and as shown in Figure 4, D2 represents the width of antenna assembly 10. Specifically, the first plane is perpendicular to the width of antenna assembly 10, and the second plane is perpendicular to the length of antenna assembly 10. Of course, antenna assembly 10 can also be configured in other configurations besides those shown in Figures 1 and 2, depending on actual circumstances.

[0038] In one embodiment, the aircraft countermeasure device further includes a fixture 60. When using the aircraft countermeasure device 1 provided in this embodiment, the aircraft countermeasure device 1 must first be mounted on the fixture 60. The main control assembly 20 controls the antenna assembly 10 to transmit an interference signal to interfere with the aircraft and prevent it from entering the controlled area.

[0039] On the basis of the above embodiments, as shown in Figures 1 and 2, 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. As shown in Figure 3, 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 is radiated 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, so as to prevent the interference signal from interfering with the legitimate equipment in the controlled area. At the same time, the interference signal generated during the interference work is radiated upward, which can effectively interfere with aircraft in the air (such as drones).

[0040] Furthermore, as shown in FIG3 , the antenna assembly 10 is further provided with a lower end surface 12 opposite the upper end surface 11. Of course, the upper end surface 11, the lower end surface 12, and the other side surfaces enclose the housing of the antenna assembly 10. Of course, the antenna assembly 10 can also have other structural forms, depending on the actual situation.

[0041] As shown in Figure 4, B is the second effective coverage angle of the interference signal in the second plane, and L2 is the angle bisector of the second effective coverage angle B in the second plane. The angle bisector L2 of the second effective coverage angle B is perpendicular to the upper end face 11. In this embodiment, the interference signal is radiated 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 equipment, the interference signal only needs to be able to interfere with the aircraft, 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.

[0042] 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 width dimension of the antenna assembly 10 is smaller than its length dimension. When deploying the aircraft countermeasures device 1, the width direction of the antenna assembly 10 can be set along the boundary of the control area. Since the interference signal has a wide radiation range along the width direction, adjacent aircraft countermeasures devices 1 can be arranged at a certain interval, as long as the interference signals radiated by the two aircraft countermeasures devices 1 form a continuous coverage area. At the same time, the spacing between adjacent aircraft countermeasures devices 1 can also prevent interference between adjacent aircraft countermeasures devices 1 during deployment and installation.

[0043] On the basis that the aircraft countermeasure device 1 includes a fixing part 60 in the above embodiment, as shown in Figures 1 and 2, the aircraft countermeasure device 1 also includes a mounting assembly (not separately marked). The antenna assembly 10 is rotatably mounted on the fixing part 60 through the mounting assembly. The main control assembly 20 is fixedly mounted to the fixing part 60 through the mounting assembly. Among them, the fixing part 60 can be a columnar structure. In this embodiment, the installation angle of the antenna assembly 10 relative to the fixing part 60 can be adjusted. For example, according to actual needs, the antenna assembly 10 is rotated relative to the fixing part 60 in the pitch direction to adjust the transmission direction of the antenna assembly 10, thereby improving the interference effect.

[0044] 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, which is fixed to a fixing member 60. The main control assembly 20 is fixed to the second mounting structure 40, which is fixed to the fixing member 60.

[0045] As shown in Figure 1 , the first mounting structure 30 is mounted on a fixture 60 and is adjustable in height along the fixture 60. The first mounting structure 30 includes a rotating portion 301, which is connected to the antenna assembly 10. The antenna assembly 10 can rotate in the pitch direction relative to the fixture 60. Adjusting the rotating portion 301 allows the tilt angle of the antenna assembly 10 to be adjusted, thereby adjusting the tilt angle of the signal transmitted by the antenna assembly 10 according to actual conditions. In other optional embodiments, the fixture 60 can also be implemented as a pole-like structure near a controlled area, such as a utility pole or street light pole.

[0046] Furthermore, a directional antenna can be provided in the antenna assembly 10. Alternatively, an omnidirectional antenna and a metal reflector can be provided in the antenna assembly 10 to achieve the transmission of interference signals. The metal reflector can be provided in the direction of the back lobe radiation of the omnidirectional antenna to reflect the back lobe radiation of the omnidirectional antenna and superimpose it with the front lobe radiation, thereby achieving the effect of directional transmission of interference signals.

[0047] Specifically, referring to Figures 10 and 11, the antenna assembly 10 may include an outer shell 100a and a directional antenna assembly. The directional antenna assembly is disposed within the outer shell 100a and is used to transmit signals. The first effective coverage angle A of the signal transmitted by the directional antenna assembly, as projected on a first plane (as shown in Figure 3), is smaller than the second effective coverage angle B of the signal projected on a second plane (as shown in Figure 4). The first plane is perpendicular to the second plane and parallel to the length of the antenna assembly 10. Both the first and second planes are perpendicular to the radiating surface 100a1 of the outer shell 100a. The radiating surface 100a1 is also the aforementioned upper end surface 11.

[0048] The radiation surface 100a1 mentioned in the embodiment of the present application is the surface used for transmitting signals in the directional antenna assembly.

[0049] When the antenna assembly 10 provided in this specific embodiment is used, as shown in Figures 11 to 13, 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, causing the back lobe of the antenna 150 to be reflected and superimposed with its 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.

[0050] Since the effective coverage angles of the signal emitted by this antenna assembly 10 are different in the first plane and the second plane, 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.

[0051] Based on the above embodiment, as shown in Figures 11 to 13 , the directional antenna assembly can specifically include a reflector 140 and an antenna 150. The reflector 140 is provided with a mounting bracket 160. Antenna 150 is mounted on mounting bracket 160, with a gap between antenna 150 and reflector 140. Antenna 150 is an omnidirectional antenna, located between the radiating surface 100a1 and the reflector 140.

[0052] In actual use, reflector 140 can be made of metal, and antenna 150 can be a directional antenna or an omnidirectional antenna. If antenna 105 is an omnidirectional antenna, the front lobe of antenna 150 is emitted toward radiating surface 100a1, and reflector 140 can reflect the back lobe of antenna 150 to overlap with the front lobe. Therefore, the signal ultimately emitted from radiating surface 100a1 includes both the front lobe and the reflected back lobe. For example, if antenna 150 is an omnidirectional fiberglass antenna, reflector 140 not only cooperates with the fiberglass antenna to achieve the effect of a directional antenna, but also helps to increase the gain of the front lobe of antenna 150.

[0053] In this embodiment, antenna 150 is mounted on mounting bracket 160, which effectively supports and secures antenna 150, thereby enhancing the stability of antenna 150. Furthermore, antenna 150 is an omnidirectional antenna, which has a relatively simple design, simplifies installation, does not require precise alignment, and is relatively inexpensive.

[0054] In one embodiment, as shown in FIG. 11 , 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 .

[0055] The length direction of antenna 150 is parallel to the length direction D1 of antenna assembly 10. If one end of antenna 150 is mounted to outer housing 100a and the other end is mounted to mounting bracket 160, this is equivalent to mounting bracket 160 being located at the end of antenna 150. Since the primary radiation area of ​​antenna 150 is in the center, positioning mounting bracket 160 at the end of antenna 150 minimizes the radiation performance of antenna 150 and maximizes the reflection of back lobes, thereby improving the gain of antenna 150.

[0056] As shown in Figure 11, 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 together constitute the entire outer shell of the antenna assembly 10. The housing 120 may be, for example, barrel-shaped. The first end cap 110 and the second end cap 130 are respectively attached to the longitudinal ends 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 disposed within the space enclosed by the housing 120, the first end cap 130, and the second end cap 110. The antenna 150 may be a cylindrical fiberglass antenna. One end of the antenna 150 is fixed to 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 to the mounting bracket 160, which is mounted on the reflector 140. In this embodiment, if the lengths of all antennas 150 are not much different, the other ends of all antennas 105 can be mounted on the mounting bracket 160, like the four antennas 150 on the left in Figure 11. However, if the length of an antenna 150 is much longer than that of other antennas 150, such as the antenna 150 on the far right in Figure 11, the other ends of these longer antennas 150 can be suspended in the air or mounted on the first end cover 110 or the second end cover 130, and the middle part thereof can be mounted on the mounting bracket 160.

[0057] 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.

[0058] Specifically, antenna 150 may be a cylindrical antenna, with the extension direction of antenna 150 parallel to the length direction of radiating surface 100a1. This allows the overall radiation direction of antenna assembly 10 to be wider in its width direction and narrower in its length direction. The length direction of radiating surface 100a1 is parallel to length direction D1 of antenna assembly 10. Antenna 150 may be a fiberglass antenna.

[0059] The radiation surface 100 a 1 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.

[0060] Based on the above embodiment, the number of antennas 150 may be multiple, and the multiple antennas 150 are distributed at intervals in the width direction of the reflector 140 .

[0061] Specifically, the width direction of the reflector 140 is parallel to the width direction D2 of the antenna assembly 10. As shown in Figure 12, 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 installed above the reflector 140 and at a certain distance from the reflector 140. Of course, in actual installations, the number of antennas 150 is not limited to the five used in this solution, and can be more or less than five.

[0062] Specifically, the distance between the center of the cross section of antenna 150 and reflector 140 is (1 / 4)*λ, where λ is the wavelength of the frequency band corresponding to the signal transmitted by antenna 150, to achieve better directional transmission. The distance between each antenna 150 and reflector 140 depends on the frequency band of its own transmitted signal. Therefore, if different antennas 150 correspond to different frequency bands, the distance between each antenna 150 and reflector 140 will also be different.

[0063] Based on the above embodiment, as shown in Figure 13, the mounting bracket 160 specifically includes a connecting substrate 161, a clamping portion 163, and a supporting portion 162. The connecting substrate 161 is used to connect to the reflector 140. The clamping portion 163 is located on the side of the connecting substrate 161 facing away from the reflector 140, that is, the clamping portion 163 is closer to the radiating surface 100a1. Furthermore, 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.

[0064] 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. Due to its elasticity, it can also have a certain shock-resistant effect.

[0065] 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 set at the end position in the longitudinal direction of the antenna 150. Since the main radiation area of ​​the antenna 150 is in the middle position in the longitudinal direction, not at the end position, the installation of the antenna mounting bracket 160 at the end of the antenna 150 has a smaller impact on the radiation performance of the antenna 150. Specifically, the mounting bracket 160 can be set at the end of the reflector 140 away from the second end cap 130. Compared with fixing the mounting bracket 160 in the middle position of the antenna 150, fixing the mounting bracket 160 at the end position in the longitudinal direction of the antenna 150 can reduce the impact of the mounting bracket 160 on the reflection effect of the reflector 140.

[0066] Furthermore, the clamping portion 163 may have an opening disposed toward the radiation surface 100 a 1 , and both sides of the opening of the clamping portion 163 may be elastic structures.

[0067] As shown in Figures 12 and 13, clamping portion 163 has a C-shaped structure. Because clamping portion 163 is made of a plastic material with a certain degree of elasticity, antenna 150 can be inserted into clamping portion 163 through the opening of the C-shaped structure. If antenna 150 is a fiberglass antenna, the C-shaped clamping portion 163 conforms to the axial cross-section of the fiberglass antenna, effectively clamping and securing a cylindrical fiberglass antenna.

[0068] In this specific embodiment, the clamping portion 163 is configured to have an opening facing the radiation surface 100 a 1 , which facilitates placement of the antenna 150 in the clamping portion 163 and simplifies the operation process.

[0069] As shown in FIG13 , support portion 162 may specifically include a first support rib 162A, a second support rib 162B, and a third support rib 162C. Third support rib 162C is connected between first support rib 162A and second support rib 162B, and the thickness of third support rib 162C is less than or equal to the thickness of first support rib 162A or second support rib 162B, thereby reducing the weight of mounting bracket 160 and facilitating lightweighting.

[0070] As shown in FIG. 2 , 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.

[0071] Specifically, the second mounting structure 40 can be implemented as a frame-shaped structure formed by a plurality of mounting rods fixedly connected. The main control assembly 20 can be fixed to the outside of the frame-shaped structure via a fastening structure, and the fixing member 60 can extend through the central hollow portion of the frame-shaped structure. Alternatively, the second mounting structure 40 can be configured as a clamping claw structure. Alternatively, the second mounting structure 40 can be configured as a structure comprising a mounting sleeve and a tightening member, wherein the mounting sleeve is mounted on the fixing member 60, and the tightening member passes through the mounting sleeve and tightens against the fixing member 60. Of course, the second mounting structure 40 can also have other structural forms, which are determined according to actual circumstances and are not detailed here.

[0072] In this embodiment, the main control assembly 20 can be fixedly mounted on the fixing member 60 via the second mounting structure 40, and the antenna assembly 10 can be rotatably mounted on the fixing member 60 via the first mounting structure 30. After adjusting the antenna assembly 10 to a suitable angle and then fixing it to the fixing member 60, the aircraft countermeasure device 1 can begin jamming. Because the jamming signal emitted by the antenna assembly 10 has a flat coverage area, it can form a "signal wall" effect, facilitating protection of the controlled area.

[0073] In addition to the above-mentioned aircraft countermeasure device 1, an embodiment of the present application also provides an aircraft control system including multiple aircraft countermeasure devices 1 mentioned in any of the above items. Multiple 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 existing technology and will not be repeated in this article.

[0074] Specifically, multiple aircraft countermeasure devices 1 can all be set up outside the boundary S of the control area, or multiple aircraft countermeasure devices 1 can all be set up on the boundary S of the control area; or, some aircraft equipment 1 can be set up outside the boundary S of the control area, and the remaining aircraft equipment 1 can be set up on the boundary S of the control area.

[0075] As shown in Figure 7, for example, eight aircraft countermeasures 1 (1A, 1B, 1C, 1D, 1E, 1F, 1G, and 1H) are provided along the boundary S of the control area. In actual use, after these aircraft countermeasures 1 are turned on for interference, all interference signals form an effect similar to a "signal wall" above the boundary S of the control 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 control area. In other embodiments, multiple aircraft countermeasures 1 can also be provided outside the boundary S of the control area, that is, multiple aircraft countermeasures 1 are arranged in sequence along the outside of the boundary S of the control area, thereby surrounding the control area. For example, relative to Figure 8, all aircraft countermeasures 1 are moved a certain distance outside the control area. In this way, the area enclosed by all aircraft countermeasures 1 will be larger than the control area, and the effect of protecting the control area can still be achieved.

[0076] The control area can be in the shape shown in Figures 7 and 8. Depending on the actual situation, it can also be in other shapes, which will be determined based on the actual situation.

[0077] In one 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.

[0078] 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. Taking Figure 7 as an example, for aircraft countermeasure devices 1H and 1G, the corresponding boundary S of the control area is the left boundary; for aircraft countermeasure devices 1C and 1D, the corresponding boundary S of the control area is the right boundary. The width direction D2 of the antenna assembly 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 widthwise edge P2 of the upper end surface 11 of the antenna assembly 10 is parallel to the boundary S of the control area. In this case, the second plane is parallel to the boundary S of the control area corresponding to the location of the aircraft countermeasure device 1. Because 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, as shown in Figure 8, the interference signal covers the boundary S of the control area with a wide beam, which maximizes the length of the boundary S of the control area that can be covered by the interference signal of a single antenna assembly 10.

[0079] 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 zone corresponding to the location of the aircraft countermeasure device 1, and the angle may be less than 45 degrees. In other words, the width direction of the antenna assembly 10 may not be exactly parallel to the boundary S of the control zone as shown in Figure 7, but may be slightly inclined relative to the boundary S of the control zone. In this case, the "signal wall" effect can still be achieved.

[0080] In one specific embodiment, the first plane is perpendicular to the width of the antenna assembly 10, and the second plane is perpendicular to the length of the antenna assembly 10. The horizontal projection of at least one side of the antenna assembly 10 parallel to the length direction D1 is perpendicular to the boundary S of the control zone corresponding to the location of the aircraft countermeasure device 1. In this case, the first plane is perpendicular to the boundary S of the control zone. As a result, the interference signal radiated by the antenna assembly 10 has a narrow beam perpendicular to the boundary S, creating a thin "signal wall" that ensures the interference signal exists only near the boundary S and does not interfere within the control zone. Therefore, when the antenna assembly 10 is arranged on the boundary S of the control zone in the aforementioned manner (i.e., the width direction D2 is parallel to the boundary S of the control zone corresponding to the location of the aircraft countermeasure device 1, and the horizontal projection of the length direction D1 is perpendicular to the boundary S of the control zone corresponding to the location of the aircraft countermeasure device 1), the beam along the boundary S is wide, while the beam perpendicular to the boundary S is narrow. This minimizes the distribution of the interference signal along the boundary S, minimizing the width of the interference signal extending inside and outside the boundary S of the control zone, and maximizing the "signal wall" effect.

[0081] 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.

[0082] 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 outward from 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 within the signal wall.

[0083] Specifically, as shown in Figure 8, 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 interference with legitimate equipment inside the control area.

[0084] Alternatively, as shown in Figures 7 and 8 , based on the above-described 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 that are opposite each other. 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 shorter 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, when projected onto a 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.

[0085] During specific use, as shown in FIG7 , for each aircraft countermeasure device 1, the upper end surface 11 is tilted 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 airspace outside 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 inside 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).

[0086] In another alternative embodiment, as shown in Figure 9 , multiple aircraft countermeasure devices 1 are positioned outside the boundary of a controlled area. The antenna assembly 10 of the aircraft countermeasure device 1 includes an upper surface 11, from which the interference signal is emitted. Upper surface 11 includes a first end 11C and a second end 11D that are opposed to each other. The distance between first end 11C and the boundary of the controlled area corresponding to the location of the aircraft countermeasure device 1 is shorter than the distance between second end 11D and the boundary of the controlled area corresponding to the location of the aircraft countermeasure device 1.

[0087] In the upper end surface 11 of at least one antenna assembly 10 , a height of the first end 11C is lower than a height of the second end 11D.

[0088] Depending on the needs of different scenarios, if interference is required within the controlled area, while the area to be protected is outside the controlled area, the tilt direction of the antenna assembly 10 can be opposite to that shown in Figure 7. For example, in Figure 9, if the aircraft countermeasure device 1 is still located outside the controlled area boundary, the upper end surface 11 includes a first end 11C and a second end 11D that are opposite each other. The distance between the first end 11C and the controlled area boundary corresponding to the location of the flight countermeasure device 1 is less than the distance between the second end 11D and the controlled area boundary corresponding to the location of the flight countermeasure device 1. In other words, the first end 11C is closer to the controlled area boundary S than the second end 11D. The distance mentioned here refers to the distance in the horizontal direction. Furthermore, 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, the tilt direction of the antenna assembly 10 is tilted 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).

[0089] The difference between the setups in Figure 9 and Figure 8 is that the aircraft control system in Figure 8 is designed to prevent foreign drones from flying into the airspace above the control area, while the aircraft control system in Figure 9 is designed to prevent drones in the control area from flying out of the airspace above it. Therefore, in the setup shown in Figure 9, it can be seen that the upper end surface 11 of each drone countermeasure device 1 is tilted upward toward the airspace within the control area. In contrast, the upper end surface 11 of each drone countermeasure device 1 in Figure 8 is tilted upward toward the airspace outside the control area.

[0090] It is understandable that different drone countermeasure devices 1 can be set at different locations on the boundary. For example, in the arrangement shown in Figure 9, some of the eight drone countermeasure devices 1 (e.g., 1A, 1B, 1H) are set on the boundary S of the controlled area, while the remaining devices (e.g., 1C, 1D, 1E, 1F, 1G) are outside the boundary S of the controlled area. It should be noted that in the arrangement shown in Figure 9, the specific ends indicated by the first end 11C and the second end 11D of the upper end surface 11 of the drone countermeasure device 1 are opposite to the specific ends indicated by the first end 11C and the second end 11D of the upper end surface 11 in the arrangement shown in Figure 8. Here, based on the height difference, the upper end surface 11 can also be defined as having opposite top and bottom ends along the length direction. In the arrangements shown in Figures 7 and 8, the first end 11C of the upper end surface 11 is its top end, and the second end 11D is its bottom end. In the arrangement shown in Figure 9, the first end 11C of the upper end surface 11 is its bottom end, and the second end 11D is its top end.

[0091] In one specific embodiment, the interference signals emitted by multiple aircraft countermeasure devices 1 surround the controlled area along its border. In this embodiment, when the aircraft countermeasure devices 1 are arranged along the border of the controlled area, the distance between two adjacent aircraft countermeasure devices 1 must at least ensure that the interference signals generated by these two aircraft countermeasure devices 1 have continuous coverage above the border. In other words, the borders of the interference signals generated by the two adjacent aircraft countermeasure devices 1 must at least be connected to form a continuous signal wall. In this way, the air above each side of the border is continuously covered with interference signals, thereby surrounding the controlled area.

[0092] Furthermore, the jamming signals emitted by two adjacent aircraft countermeasure devices 1 may overlap along the boundary of the controlled area. This not only forms a continuous signal wall within the controlled area, but also enhances the jamming effect in the overlapping area, thereby improving the jamming effect of the signal wall formed by all aircraft countermeasure devices 1.

[0093] It should be noted that many of the components mentioned in this application are universal standard parts or components known to those skilled in the art, and their structures and principles can be known to those skilled in the art through technical manuals or conventional experimental methods.

[0094] The technical features of the above-mentioned embodiments can be combined arbitrarily. In order to make the description concise, not all possible combinations of the technical features in the above-mentioned embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0095] The above-described embodiments merely represent several implementation methods of the present application. While the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the patent application. It should be noted that a person of ordinary skill in the art may make various modifications and improvements without departing from the spirit of the present application, and these modifications and improvements fall within the scope of protection of the present application. Therefore, the scope of protection of the present patent application shall be determined by the appended claims.

Claims

1. An aircraft countermeasure device, comprising: An antenna assembly, wherein the antenna assembly is used to transmit an interference signal; 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; 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 assembly, and the second plane is perpendicular to the length direction of the antenna assembly.

3. The aircraft countermeasure device according to claim 2, characterized in that: 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.

4. The aircraft countermeasure device according to claim 1, characterized in that: The aircraft countermeasure device also 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.

5. The aircraft countermeasure device according to claim 4, characterized in that: 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 fixedly mounted on the second mounting structure, and the second mounting structure is fixedly mounted on the fixing member.

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

7. The aircraft countermeasure device according to claim 1, characterized in that: The antenna assembly is provided with a directional antenna.

8. The aircraft countermeasure device according to claim 1, characterized in that: The antenna assembly is provided with an omnidirectional antenna and a metal reflector.

9. The aircraft countermeasure device according to claim 8, characterized in that: The antenna assembly also includes a mounting frame; along the length direction of the omnidirectional antenna, at least one end of a portion of the omnidirectional antenna is arranged on the outer shell of the antenna assembly, and the other end is arranged on the mounting frame.

10. The aircraft countermeasure device according to claim 8, characterized in that: The distance between the center of the cross section of the omnidirectional antenna and the reflector is (1 / 4)*λ, where λ is the wavelength of the frequency band corresponding to the signal emitted by the omnidirectional antenna.

11. An aircraft control system, characterized in that: comprising a plurality of aircraft countermeasure devices, wherein the plurality of aircraft countermeasure devices are arranged along the boundary of the control area; The aircraft countermeasure device comprises: An antenna assembly, wherein the antenna assembly is used to transmit an interference signal; 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; 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.

12. The aircraft control system according to claim 11, characterized in that: 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; 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 flight countermeasure device.

13. The aircraft control system according to claim 11, characterized in that: 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; 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.

14. The aircraft control system according to claim 11, characterized in that: 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; 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.

15. The aircraft control system according to claim 11, characterized in that: 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; 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.

16. The aircraft control system according to claim 11, characterized in that: The interference signals emitted by the plurality of aircraft countermeasure devices surround the controlled area along the boundary of the controlled area.

17. The aircraft control system according to claim 11, characterized in that: The interference signals emitted by two adjacent aircraft countermeasure devices have a signal overlapping area along the boundary of the control area.

18. The aircraft control system according to claim 11, characterized in that: A plurality of the aircraft countermeasure devices are arranged on the inner side of 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 height of the upper end surface close to one end of the boundary of the control area corresponding to the location of the aircraft countermeasure device is lower than the height of the upper end surface away from one end of the boundary of the control area corresponding to the location of the aircraft countermeasure device.

19. The aircraft control system according to claim 11, characterized in that: A plurality of the aircraft countermeasure devices are arranged on the inner side of 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 height of the upper end surface close to one end of the boundary of the control area corresponding to the location of the flight countermeasure device is higher than the height of the upper end surface away from one end of the boundary of the control area corresponding to the location of the flight countermeasure device.

20. The aircraft control system according to claim 11, characterized in that: 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; The width direction of at least one of the antenna assemblies forms an angle with the boundary of the control area corresponding to the location of the flight countermeasure device, and the angle is less than 45 degrees.

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