Aircraft countering equipment and aircraft control system

Abstract

The utility model 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 technical field of aircraft control, in particular to an aircraft countermeasure device. In addition, the present application also relates to an aircraft control system comprising the aircraft countermeasure device. BACKGROUND

[0002] At present, with the prevalence of the unmanned aerial vehicle market, more and more "low, slow and small" aircrafts appear, and some areas with high confidentiality requirements (such as prisons, government important office sites, etc.) are strictly prohibited from approaching, passing or flying over the airspace. In order to protect the safety of the control area and prevent aircrafts from entering the control area, relevant countermeasure devices need to be set up. However, the current countermeasure devices will emit strong interference signals in all directions, which can easily affect the wireless communication of the nearby area.

[0003] In summary, how to provide a countermeasure device with little influence on the wireless communication of the nearby area is a problem that needs to be solved by the technical personnel in the field at present. CONTENT OF THE INVENTION

[0004] Therefore, the purpose of the embodiments of the present application is to provide an aircraft countermeasure device which can reduce the influence on the wireless communication of the nearby area.

[0005] Another purpose of the embodiments of the present application is to provide an aircraft control system comprising the aircraft countermeasure device.

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

[0007] An aircraft countermeasure device comprises:

[0008] An antenna assembly for emitting an interference signal to interfere with an aircraft;

[0009] A main control assembly electrically connected with the antenna assembly, the main control assembly being configured to control the antenna assembly to emit the interference signal;

[0010] The first effective coverage angle of the interference signal projected on a first plane is smaller than the second effective coverage angle of the interference signal projected on a 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 assembly comprises an upper end surface, and the interference signal is emitted from the upper end surface; an edge of the upper end surface along the length direction is parallel to the length direction of the antenna assembly; an edge of the upper end surface along the width direction is parallel to the width direction of the antenna assembly.

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

[0014] Optionally, the mounting assembly comprises a first mounting structure and a second mounting structure; the antenna assembly is rotatably mounted to 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 is rotatable relative to the fixing member along the pitch direction.

[0016] Optionally, the antenna assembly is provided with a directional antenna.

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

[0018] An aircraft control system comprises a plurality of the aircraft countermeasure devices according to any one of the preceding items, and the plurality of aircraft countermeasure devices are arranged along the boundary of the control area.

[0019] 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.

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

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

[0022] The height of the first end of the upper end surface of at least one of the antenna assemblies is higher than the height of the second end.

[0023] Optionally, the plurality of aircraft countermeasure devices are located outside the boundary of the controlled area; the antenna assembly of the aircraft countermeasure device comprises an upper end surface, and the interference signal is emitted from the upper end surface; the upper end surface comprises opposite first and second ends; the distance between the first end and the boundary of the controlled area corresponding to the location of the aircraft countermeasure device is less than the distance between the second end and the boundary of the controlled area corresponding to the location of the aircraft countermeasure device.

[0024] The height of the first end in the upper end surface of at least one of the antenna assemblies is lower than the height of the second end.

[0025] 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.

[0026] The projection of the length direction parallel side of at least one of the antenna assemblies on the horizontal plane is perpendicular to the boundary of the controlled 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 controlled area.

[0029] The aircraft countermeasure device provided by the embodiments of the present application has a main control assembly controlling the antenna assembly to emit an interference signal, and the first effective coverage angle of the interference signal projected on a first plane is less than the second effective coverage angle of the interference signal projected on a 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 a signal wall-like effect. Therefore, the aircraft countermeasure device provided by the embodiments of the present application can prevent aircraft from entering the controlled area while avoiding emitting strong interference signals in all directions, thereby achieving the effect of reducing the influence on wireless communication in the vicinity.

[0030] In addition, the embodiments of the present application also provide an aircraft control system comprising the above-mentioned aircraft countermeasure device. BRIEF DESCRIPTION OF DRAWINGS

[0031] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of this application. For those skilled in the art, other drawings can be obtained based on the provided drawings without creative effort.

[0032] Figure 1 This is a schematic diagram of a specific embodiment of the aircraft countermeasure device provided in this application.

[0033] Figure 2 for Figure 1 A schematic diagram of the structure of the aircraft countermeasure equipment installed on the fixed component.

[0034] Figure 3 This is a schematic diagram of the first effective coverage angle of the interference signal projected onto the first plane.

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

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

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

[0038] Figure 7 This is a schematic diagram of the setting of an aircraft control system at the boundary of a controlled area, as provided in an embodiment of this application.

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

[0040] Figure 9 This is a schematic diagram illustrating another configuration of the aircraft control system provided in this application at the boundary of the controlled area.

[0041] Figure 10 This is a schematic diagram of the structure of an antenna assembly provided in an embodiment of this application.

[0042] Figure 11 for Figure 10 An exploded view of the antenna assembly of the embodiment shown.

[0043] Figure 12 for Figure 10 A schematic diagram of the assembly of each directional antenna within the antenna assembly of the illustrated embodiment.

[0044] Figure 13 for Figure 12Structure diagram of mounting rack in the antenna assembly of the embodiment.

[0045] Explanation of reference numerals:

[0046] 1 is 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 an outer housing, 100a1 is a radiation surface, 110 is a first end cover, 120 is an outer shell, and 130 is a second end cover.

[0049] 140 is a reflector plate.

[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 rack, 161 is a connection substrate, 162 is a support portion, 162A is a first support rib, 162B is a second support rib, 162C is a third support rib, and 163 is a clamping portion.

[0052] 20 is a main control assembly.

[0053] 30 is a first mounting structure, and 301 is a rotation portion.

[0054] 40 is a second mounting structure.

[0055] 50 is a radio frequency cable.

[0056] 60 is a fixing member.

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

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

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

[0060] S is a boundary of a controlled area.

[0061] P1 is an edge of the upper end surface in the length direction, and P2 is an edge of the upper end surface in the width direction. DETAILED DESCRIPTION

[0062] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0063] The core of this application is to provide an aircraft countermeasure device that can emit jamming signals, and the jamming signals can form an effect similar to a virtual wall, preventing aircraft from entering controlled areas.

[0064] Another core aspect of this application is to provide an aircraft control system that includes the aforementioned aircraft countermeasures equipment.

[0065] like Figure 1 As shown in the illustration, this specific embodiment discloses an aircraft countermeasure device 1, including an antenna assembly 10 and a main control assembly 20. The antenna assembly 10 is used to transmit jamming signals to interfere with the aircraft. The main control assembly 20 is electrically connected to the antenna assembly 10 and is used to control the antenna assembly 10 to transmit the jamming signals. The jamming signals, for example, propagate from the antenna assembly 10 in a direction away from the antenna assembly 10. The first effective coverage angle A projected onto a first plane (e.g., ...) is... Figure 3 (As shown) is less than the second effective coverage angle B of the interference signal projected onto the second plane (e.g.) 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 an RF cable connection or through a plug-in interface connection, depending on the actual situation, which will not be elaborated here.

[0067] The first effective coverage angle A mentioned in the embodiments of this application can refer to the coverage angle of the signal whose interference signal is greater than the first preset radiation intensity in the projection of the first plane, for example... Figure 5 As shown, the first effective coverage angle A can be an angle within a coverage range of approximately -15° to 15°. The second effective coverage angle B can refer to the coverage angle of the interfering signal in the projection of the second plane that is greater than the second preset radiation intensity, such as... Figure 6 As shown, the second effective coverage angle B can be approximately within the coverage range of -60° to 60°. Wherein, 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, to achieve the effect of interference. Alternatively, it can be understood that: the first effective coverage angle is the beamwidth of the interfering signal in the first plane, and the second effective coverage angle is the beamwidth of the interfering signal in the second plane.

[0068] In actual use, the main control assembly 20 needs to output a radio frequency signal to the antenna assembly 10, so the antenna assembly 10 and the main control assembly 20 can be connected by a radio frequency cable 50. The main control assembly 20 outputs a radio frequency signal to the antenna assembly 10 through the radio frequency cable 50, and the antenna assembly 10 converts the received radio frequency signal into an electromagnetic wave signal of a 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 normally or work, for example, it cannot communicate stably with the flight control terminal under the action of the interference signal, thereby causing hovering, crashing or returning, etc., to achieve the interference effect on the drone. The main control assembly 20 can include a main control unit, a baseband module, a power amplifier module, a power supply module, etc., wherein the main control unit can be a CPU (Central Processing Unit) or an FPGA (Field Programmable Gate Array). In other optional embodiments, the main control assembly 20 can also be installed with a receiving antenna (not shown in the figure), which is used to receive the electromagnetic wave signal in the air and convert it into a corresponding electrical signal and output it to the main control unit. The main control unit can obtain the communication information (such as communication channel, communication protocol, communication signal standard, etc.) of the drone and the flight control terminal by analyzing and processing the received electrical signal, and the main control unit can also generate a radio frequency signal corresponding to the communication information, so that the antenna assembly 10 can transmit the interference signal in a targeted manner, thereby improving the interference effect on the drone. The specific generation method of 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 the specific embodiment can be planes perpendicular to the upper end face or the lower end face of the antenna assembly 10. For example, the first plane can be parallel to the side face of the antenna assembly 10 as shown in FIG. 1, or the first plane is the plane where the side face of the antenna assembly 10 is located as shown in FIG. 2. The second plane can be parallel to the side face of the antenna assembly 10 as shown in FIG. 1, or the second plane is the plane where the side face of the antenna assembly 10 is located as shown in FIG. 2. Or, the first plane and the second plane can also be planes with an included angle between the upper end face or the lower end face of the antenna assembly 10 greater than 0° and less than 90°. The first plane and the second plane are only a reference plane, and the purpose is to express the specific beam width of the interference signal from different angles. FIG. 3 shows that the projection of the interference signal on the first plane has a relatively narrow first effective coverage angle A, which can also be regarded as a projection of the interference signal on a plane perpendicular to the upper end face or the lower end face of the antenna assembly 10. Figure 3 Figure 3 Figure 4 Figure 4 Figure 3 ​​​​The beam width of the interference signal is narrow from the perspective shown. Figure 4 The projection of the interference signal on the second plane has a wider second effective coverage angle B. It can also be seen that the interference signal is projected on the first plane as a beam with a first effective coverage angle A, and the interference signal is projected on the second plane as a beam with a second effective coverage angle B. Figure 4 The beam width of the interference signal is wide from the perspective shown. Therefore, referring to Figure 8 In actual use, unlike the bundled interference signal, the interference signal in the embodiment of the present application spreads, for example, in a flat shape, and has a wider beam on the second plane compared to the first plane, which can prevent the intrusion of the aircraft as a similar “signal wall”.

[0070] In actual use, the aircraft countermeasure device 1 of the present embodiment generally needs to emit an interference signal to interfere with the entry of a UAV. Since the interference signal has the characteristic that the first effective coverage angle A of the projection on the first plane is smaller than the second effective coverage angle B of the projection on the second plane, the interference signal in the present embodiment presents a “wall type” shape. In this way, by arranging the aircraft countermeasure device 1 of the present embodiment around the perimeter of the controlled area, the interference signal can act as a signal wall that cannot be flown over by the UAV when the aircraft countermeasure device 1 is used. Therefore, the aircraft countermeasure device of the present embodiment can prevent the aircraft from entering the controlled area while avoiding emitting strong interference signals in all directions, thereby achieving the effect of reducing the impact on nearby wireless communication.

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

[0072] In combination with Figure 1 , Figure 2 , Figure 3 As shown, the antenna assembly 10 can be arranged as a near-cuboid structure. The antenna assembly 10 has an upper end face 11 and a lower end face 12. The upper end face 11 is the end face of the interference signal emitted by the antenna assembly 10 that spreads outward, i.e., the emission face. The lower end face 12 is the end face opposite the upper end face 11 of the antenna assembly 10.

[0073] As shown in Figure 3 D1 is the length direction of the antenna assembly 10, as shown in Figure 4 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 arranged in other shapes, such as a sphere, a cylinder, a cone, etc.Figure 1 、 Figure 2 The other structure is shown in the shape other than the shape shown in the figure, and is determined according to the actual situation.

[0074] In a specific embodiment, the aircraft countermeasure device further comprises a fixing member 60. In use of the aircraft countermeasure device 1 provided by the specific embodiment, the aircraft countermeasure device 1 needs to be first installed on the fixing member 60. The main control assembly 20 controls the antenna assembly 10 to send the interference signal to interfere with the aircraft, so as to avoid the aircraft entering the control area.

[0075] On the basis of the above embodiment, as shown in Figure 1 、 Figure 2 The antenna assembly 10 comprises an upper end surface 11, and the interference signal is emitted from the upper end surface 11. The edge P1 of the upper end surface 11 along the length direction is parallel to the length direction of the antenna assembly 10. The edge 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 a first effective coverage angle of the interference signal in the first plane, and L1 is an angular bisector of the first effective coverage angle A in the first plane. The angular bisector L1 of the first effective coverage angle A can be perpendicular to the upper end surface 11. In the embodiment, the interference signal is radiated to both sides with a smaller coverage range relative to the intermediate 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 avoid the interference signal interfering with the legal equipment in the control area. At the same time, the interference signal radiated upward when performing the interference work can effectively interfere with the aircraft (such as the unmanned aerial vehicle) in the air.

[0076] Further, as shown in Figure 3 The antenna assembly 10 is further 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 surround to form the shell of the antenna assembly 10. Of course, the antenna assembly 10 can also be other structure forms, which are determined according to the actual situation.

[0077] As shown in Figure 4 B is a second effective coverage angle of the interference signal in the second plane, and L2 is an 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 surface 11. In the embodiment, the interference signal is radiated to both sides with a larger coverage range relative to the intermediate section perpendicular to the upper end surface 11 and perpendicular to the width direction D2, that is, when performing the interference work, the signal wall formed by the interference signal extends along the width direction D2, which facilitates the arrangement of the antenna assembly 10. The specific generation method of the signal is not limited in the embodiment. If applied to the aircraft countermeasure device, the interference signal only needs to be able to interfere with the aircraft, such as blocking the communication between the unmanned aerial vehicle and the flight control terminal, performing the navigation signal interference, so that the unmanned aerial vehicle cannot be accurately positioned, etc.

[0078] In the 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 direction of the antenna assembly 10 is smaller than the length direction of the antenna assembly 10. When the aircraft countermeasure device 1 is arranged, the width direction of the antenna assembly 10 can be arranged along the boundary of the control area. Since the interference signal has a wide radiation range along the width direction, the 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, the interval between the adjacent aircraft countermeasure devices 1 can also avoid interference between the adjacent aircraft countermeasure devices 1 when arranged and installed.

[0079] In the above embodiment, the aircraft countermeasure device 1 includes the fixing member 60. As shown in Figure 1 、 Figure 2 , the aircraft countermeasure device 1 further 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 installed on the fixing member 60 through the mounting assembly. The fixing member 60 can be a columnar structure. In the embodiment, the installation angle of the antenna assembly 10 relative to the fixing member 60 can be adjusted, for example, the antenna assembly 10 is rotated along the pitch direction relative to the fixing member 60 to adjust the emission direction of the antenna assembly 10, thereby improving the interference effect.

[0080] Specifically, the mounting assembly can 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 on the fixing member 60. The main control assembly 20 is fixedly arranged on the second mounting structure 40, and the second mounting structure 40 is fixedly arranged on the fixing member 60.

[0081] As shown in Figure 1 , the first mounting structure 30 is sleeved on the fixing member 60 and the installation 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 with the antenna assembly 10. The antenna assembly 10 can be rotated along the pitch direction relative to the fixing member 60. The inclination angle of the antenna assembly 10 can be adjusted by adjusting the rotating part 301, so as to adjust the inclination angle of the signal emitted by the antenna assembly 10 according to the actual situation. In other optional embodiments, the fixing member 60 can also be realized by using a pole-shaped facility near the control area, for example, a power pole, a street lamp pole.

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

[0083] Specifically, referring to Figure 10 , 11 , the antenna assembly 10 can include an outer housing 100a and a directional antenna assembly arranged in the outer housing 100a and configured to emit a signal. The signal emitted by the directional antenna assembly has a first effective coverage angle A in a first plane (as shown in Figure 3 ) that is smaller than a second effective coverage angle B in a second plane (as shown in Figure 4 ). The first plane is perpendicular to the second plane, and the first plane is parallel to the length direction of the antenna assembly 10. Both the first plane and the second plane are perpendicular to the radiation surface 100a1 of the outer housing 100a. The radiation surface 100a1 is the upper end surface 11 mentioned above.

[0084] The radiation surface 100a1 mentioned in the embodiments of the present application is the surface of the directional antenna assembly for emitting a signal.

[0085] When the antenna assembly 10 provided by the specific embodiment is used, as shown in Figures 11 to 13 , the antenna assembly 10 can include a plurality of antennas 150. The plurality of antennas 150 are arranged parallel to each other. When the signal emitted by the antenna 150 reaches the reflector 140, it is reflected by the reflector 140, so that the back lobe of the antenna 150 is reflected and superimposed with the corresponding front lobe, thereby achieving that the first effective coverage angle A of the signal emitted by the antenna 150 in the first plane is smaller than the second effective coverage angle B of the signal in the second plane. The first plane is arranged in the length direction of the antenna 150, and the second plane is arranged perpendicular to the length direction of the antenna 150.

[0086] Since the effective coverage angles of the signal emitted by the antenna assembly 10 in the first plane and the second plane are different, when applied to the aircraft countermeasure device, the second plane can be arranged along the edge of the control area, which is beneficial to increase the interference range corresponding to a single aircraft countermeasure device. Under the condition of meeting the requirements, the number of aircraft countermeasure devices can be effectively reduced.

[0087] On the basis of the above-mentioned embodiments, as shown in Figures 11 to 13As shown, the directional antenna assembly can specifically include a reflector plate 140, an antenna 150, and a mounting bracket 160. The antenna 150 is arranged on the mounting bracket 160, and there is a gap between the antenna 150 and the reflector plate 140. The antenna 150 is an omnidirectional antenna, and the antenna 150 is located between the radiation surface 100a1 and the reflector plate 140.

[0088] In actual use, the reflector plate 140 can be made of metal, and the antenna 150 can be selected as a directional antenna or an omnidirectional antenna. If the antenna 105 is an omnidirectional antenna, the front lobe of the antenna 150 emits towards the radiation surface 100a1, and the reflector plate 140 can reflect the back lobe of the antenna 150 to superimpose with the front lobe, so that the signal finally emitted from the radiation surface 100a1 includes both the front lobe and the reflected back lobe. For example, when the antenna 150 is selected as a glass steel antenna, the reflector plate 140 can not only cooperate with the glass steel antenna to realize the effect of a directional antenna, but also be beneficial to improve the gain of the front lobe of the antenna 150.

[0089] In this embodiment, the antenna 150 is arranged on the mounting bracket 160, and the mounting bracket 160 can effectively support and fix the antenna 150, so as to effectively improve the stability of the installation of the antenna 150. Moreover, the antenna 150 is an omnidirectional antenna, and the design of the omnidirectional antenna is relatively simple, the installation process is more convenient, and the cost is relatively low.

[0090] In one embodiment, as shown in Figure 11 along the length direction of the antenna 150, at least part of one end of the antenna 150 is arranged on the outer shell 100a, and the other end is arranged 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 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] As shown in Figure 11As shown, the antenna assembly 10 can specifically include a first end cover 110, an outer shell 120, a second end cover 130, a reflecting plate 140, an antenna 150, and a mounting rack 160. The first end cover 110, the outer shell 120, and the second end cover 130 constitute the entire outer shell part of the antenna assembly 10. The outer shell 120 is, for example, barrel-shaped. The first end cover 110 and the second end cover 130 are respectively arranged at the two ends of the length direction of the outer shell 120 to form a sealed cavity together with the outer shell 120. The reflecting plate 140, the antenna 150, and the mounting rack 160 are all arranged in the space formed by the outer shell 120, the first end cover 130, and the second end cover 110. The antenna 150 can be a columnar glass fiber reinforced plastic antenna. One end of the antenna 150 is fixed to the inner side of the second end cover 130 or the first end cover 110, and the other end of the antenna 150 is mounted on the mounting rack 160, which is mounted on the reflecting plate 140. In the embodiment, if the lengths of all the antennas 150 are similar, the other ends of all the antennas 150 can be mounted on the mounting rack 160 like the four antennas 150 on the left side in FIG. 1. If the length of one of the antennas 150 is much longer than the lengths of the other antennas 150, for example, like the antenna 150 on the rightmost side in FIG. 1, the other end of the antenna 150 can be suspended or mounted on the first end cover 110 or the second end cover 130, and the middle part of the antenna 150 can be mounted on the mounting rack 160. Figure 11 Figure 11

[0093] In the embodiment, arranging the reflecting plate 140, the antenna 150, and the mounting rack 160 in the space formed by the outer shell 120, the first end cover 130, and the second end cover 110 can effectively protect the antenna 150 and reduce the influence of the external environment on the service life of the antenna 150.

[0094] Specifically, the antenna 150 can be a columnar 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 the 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 can be specifically a glass fiber reinforced plastic antenna.

[0095] In the embodiment, the radiation surface 100a1 is the outer surface of the side wall of the outer shell 120 that is opposite to the reflecting plate 140 and spaced apart from the reflecting plate 140 and radiates signals outward.

[0096] Based on the above embodiment, the number of the antennas 150 can be multiple, and the multiple antennas 150 are distributed in the width direction of the reflecting plate 140.

[0097] Specifically, the width direction of the reflecting plate 140 is parallel to the width direction D2 of the antenna assembly 10. For example, Figure 12 ​​As shown, the antennas 150 include 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 one aircraft. Each antenna 150 is arranged above the reflector plate 140 at a position away from the reflector plate 140 by a certain distance. Of course, in actual implementation, the number of antennas 150 can not be limited to five, 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 plate 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. The distance between each antenna 150 and the reflector plate 140 depends on the frequency band of the signal transmitted by the antenna 150 itself. Therefore, if the frequency bands corresponding to different antennas 150 are different, the distances between the different antennas 150 and the reflector plate 140 are also different.

[0099] Based on the above embodiment, as shown in Figure 13 The mounting bracket 160 specifically includes a connecting base plate 161, a clamping portion 163, and a supporting portion 162. The connecting base plate 161 is used to connect with the reflector plate 140. The clamping portion 163 is arranged on the side of the connecting base plate 161 away from the reflector plate 140, i.e., the clamping portion 163 is closer to the radiation surface 100a1. The clamping portion 163 is used to clamp the antenna 150. One end of the supporting portion 162 is connected to the connecting base plate 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 effectively fixes the antenna 150 while avoiding affecting the operation of the antenna 150 compared to a metal material. Due to the elasticity, the insulating elastic member also has a certain anti-vibration effect.

[0101] On the other hand, since the mounting bracket 160 is arranged between the antenna 150 and the reflector plate 140, it can affect the reflection effect of the reflector plate 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, the influence of the mounting bracket 160 arranged at the end position of the antenna 150 on the radiation performance of the antenna 150 is small. Specifically, the mounting bracket 160 can be arranged at one end of the reflector plate 140 away from the second end cover 130. Compared to fixing the middle position of the antenna 150 by the mounting bracket 160, fixing the end position of the antenna 150 in the length direction by the mounting bracket 160 can reduce the influence of the mounting bracket 160 on the reflection effect of the reflector plate 140.

[0102] Further, the clamping portion 163 can be provided with an opening facing the radiation surface 100a1, and both sides of the opening of the clamping portion 163 are provided with elastic structures.

[0103] As shown in Figure 12 and Figure 13 , the clamping portion 163 is in a "C" shape structure. Since the clamping portion 163 is made of plastic material and has a certain elasticity, the antenna 150 can be clamped into the clamping portion 163 from the opening of the "C" shape structure. If the antenna 150 is a glass fiber reinforced plastic antenna, the clamping portion 163 of the "C" shape structure is matched with the axial cross-sectional shape of the glass fiber reinforced plastic antenna, so that the cylindrical glass fiber reinforced plastic antenna can also be effectively clamped and fixed.

[0104] In the embodiment, the clamping portion 163 is provided with an opening facing the radiation surface 100a1, which facilitates the placement of the antenna 150 in the clamping portion 163 and simplifies the operation process.

[0105] As shown in Figure 13 , the support portion 162 can 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 and facilitate the realization of light weight.

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

[0107] Specifically, the second mounting structure 40 can be realized by a frame structure formed by fixedly connecting a plurality of mounting rods. The main control assembly 20 can be fixed to the outside of the frame structure through 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 provided in a clamping jaw structure. Alternatively, the second mounting structure 40 can also be provided in a structure having a mounting sleeve and a tightening member, the mounting sleeve is sleeved on the fixing member 60, and the tightening member passes through the mounting sleeve and tightens the fixing member 60. Of course, the second mounting structure 40 can also be other structure forms, which are determined according to the actual situation, and will not be described here.

[0108] In this embodiment, the main control assembly 20 can be fixedly installed on the fixing member 60 through the second mounting structure 40, and the antenna assembly 10 is rotatably installed on the fixing member 60 through the first mounting structure 30. After the antenna assembly 10 is adjusted to a suitable angle, the antenna assembly 10 is fixed on the fixing member 60, and then the aircraft countermeasure equipment 1 can start to perform the interference work. Since the coverage range of the interference signal emitted by the antenna assembly 10 is flat, a "signal wall" effect can be formed, which facilitates the protection of the control area.

[0109] In addition to the aircraft countermeasure equipment 1 described above, the embodiments of the present application also provide an aircraft control system including a plurality of any of the above-mentioned aircraft countermeasure equipment 1. The plurality of aircraft countermeasure equipment 1 is arranged along the boundary S of the control area. The structures of other parts of the aircraft control system refer to the prior art, and will not be described herein.

[0110] Specifically, the plurality of aircraft countermeasure equipment 1 can be all arranged outside the boundary S of the control area, or the plurality of aircraft countermeasure equipment 1 can also be all arranged on the boundary S of the control area; or, part of the aircraft equipment 1 can be arranged outside the boundary S of the control area, and the remaining part of the aircraft equipment 1 can be arranged on the boundary S of the control area.

[0111] As shown in Figure 7 , eight aircraft countermeasure equipment 1 (1A, 1B, 1C, 1D, 1E, 1F, 1G, 1H) are arranged along the boundary S of the control area. In actual use, after these aircraft countermeasure equipment 1 are turned on and interfere, all the interference signals form a "signal wall" effect above the boundary S of the control area. If the unmanned aerial vehicle approaches the "signal wall", it may hover, return or land under the action of the interference signal, so as to avoid the unmanned aerial vehicle entering the control area. In other embodiments, the plurality of aircraft countermeasure equipment 1 can also be arranged outside the boundary S of the control area, that is, the plurality of aircraft countermeasure equipment 1 are arranged in sequence outside the boundary S of the control area, so as to surround the control area. For example, compared Figure 8 with the above-mentioned embodiment, all the aircraft countermeasure equipment 1 are moved a certain distance outside the control area, so that the area surrounded by all the aircraft countermeasure equipment 1 is greater than the control area, and the effect of protecting the control area can still be achieved.

[0112] The control area can have the shape as shown in Figure 7 , Figure 8 . According to different actual conditions, it can also have other shapes, which are determined according to actual conditions.

[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 the 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. For example, Figure 7 For the aircraft countermeasure devices 1H and 1G, the boundary S of the control area corresponding thereto is the boundary on the left side; for the aircraft countermeasure devices 1C and 1D, the boundary S of the control area corresponding thereto is the boundary on the right side. The width direction D2 of the antenna assembly 10 can be arranged 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 of the upper end surface 11 of the antenna assembly 10 along the width direction is parallel to the boundary S of the control area, and in this case, the second plane is also 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, as shown in Figure 8 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 covered by the interference signal of a single antenna assembly 10 is as long as possible.

[0115] In other embodiments, the width direction of the at least one antenna assembly 10 can also be at an 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 can also not be exactly parallel to the boundary S of the control area as shown in Figure 7 , but can also be slightly inclined relative to the boundary S of the control area, and 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 side of the at least one antenna assembly 10 parallel to the length direction D1 is perpendicular to the projection of the boundary S of the control area corresponding to the position of the aircraft countermeasure device 1 on the horizontal plane, and 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 narrow, and the thickness of the "signal wall" is thin, so that the interference signal only exists near the boundary S and does not interfere with the control area. Therefore, when the antenna assembly 10 is arranged on the boundary S of the control area in the above manner (i.e., 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 in the direction of the boundary S is wide, and the beam perpendicular to the direction of the boundary S is narrow, so that the interference signal is distributed as much as possible only in the air above the boundary S, and the width extending to the inside and outside of the boundary S of the control area is reduced, and the effect of the "signal wall" is formed as much as possible.

[0117] It should be noted that since the UAV 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 control area, and the interference signal emitted by the aircraft countermeasure device 1 needs to be located on the boundary S of the control area or outside the boundary S of the control area to avoid interference with the legal devices in the control area.

[0118] On the basis of the above embodiment, the angle between the side 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 or equal to 0° and less than 90°, so that the interference signal emitted by the aircraft countermeasure device 1 extends outwardly relative to the boundary S of the control area or along the boundary S of the control area, and the control area is completely surrounded by the signal wall.

[0119] Specifically, as shown in Figure 8 , the angle between the side 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 0° and less than 90°, and the signal wall formed by the interference signal emitted by the aircraft countermeasure device 1 is inclined outwardly relative to the control area, so that the control area is surrounded inside the signal wall, which can appropriately increase the control range and avoid interfering with the legal devices inside the control area.

[0120] Alternatively, as shown in Figure 7 , Figure 8On the basis of the above embodiments, the antenna assembly 10 of the aircraft countermeasure device 1 comprises an upper end surface 11 from which the jamming signals are emitted. If the aircraft countermeasure device 1 is located outside the boundary S of the controlled area, the upper end surface 11 comprises an opposite first end 11C and a second end 11D, the distance of the first end 11C from the boundary S of the controlled area corresponding to the location of the aircraft countermeasure device 1 is smaller than the distance of the second end 11D from the boundary S of the controlled 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 controlled area than the second end 11D. The height of the first end 11C is higher than the height of the second end 11D in the upper end surface 11 of at least one antenna assembly 10.

[0121] In the specific use, as shown in Figure 7 , for each aircraft countermeasure device 1, the upper end surface 11 is inclined downward and outward relative to the boundary S of the controlled area from the first end 11C. In this way, the jamming signals emitted by the upper end surface 11 of the antenna assembly 10 can be directed towards the airspace outside the boundary S of the controlled area, so as to avoid the impact of the jamming signals on the normal radio communication within the controlled area. Alternatively, the aircraft countermeasure device 1 can also be located inside the boundary S of the controlled area, while the orientation of the upper end surface 11 remains unchanged, i.e. inclined upward towards the airspace outside the controlled area (specifically, the height of the end of the upper end surface 11 close to the boundary S of the controlled area corresponding to the location of the aircraft countermeasure device 1 is lower than the height of the end of the upper end surface 11 away from the boundary S of the controlled area corresponding to the location of the aircraft countermeasure device 1. The close and away here are also determined based on the distance in the horizontal direction).

[0122] In another alternative embodiment, referring to Figure 9 , a plurality of aircraft countermeasure devices 1 are arranged outside the boundary of the controlled area. The antenna assembly 10 of the aircraft countermeasure device 1 comprises an upper end surface 11 from which the jamming signals are emitted. The upper end surface 11 comprises an opposite first end 11C and a second end 11D. The distance of the first end 11C from the boundary of the controlled area corresponding to the location of the aircraft countermeasure device 1 is smaller than the distance of the second end 11D from the boundary of the controlled area corresponding to the location of the aircraft countermeasure device 1.

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

[0124] According to different scenarios, if it is necessary to interfere with the inside of the controlled area and the area to be protected is the outside of the controlled area, the inclination direction of the antenna assembly 10 can be opposite to the direction shown in Figure 7 . For example Figure 9If the aircraft countermeasure device 1 is still located outside the boundary of the controlled area, the upper end surface 11 includes opposite first and second ends 11C and 11D, the distance between the first end 11C and the boundary of the controlled area corresponding to the location of the aircraft 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 aircraft 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. And the height of the first end 11C of the upper end surface 11 of the at least one antenna assembly 10 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 towards the airspace inside the controlled area. Or, in other alternative solutions, the aircraft countermeasure device 1 can also be located inside the boundary S of the controlled area, but the orientation of the upper end surface 11 remains the same, that is, it is still oriented towards the airspace inside the controlled area (at this time, the height of the end of the upper end surface 11 close to one end of the boundary S of the controlled area corresponding to the location of the aircraft countermeasure device 1 is higher than the height of the end of the upper end surface 11 away from the other end of the boundary S of the controlled area corresponding to the location of the aircraft countermeasure device 1).

[0125] Figure 9 With 8 The difference between the two setting modes is that, Figure 8 The aircraft control system in Figure 9 The aircraft control system in Figure 9 As shown in the setting mode of Figure 8 As shown in the setting mode of

[0126] It can be understood that different aircraft countermeasure devices 1 can be arranged at different positions of the boundary. For example: Figure 9 In the setting mode of Figure 9 In the setting mode of Figure 8 In the setting mode of Figure 7 , Figure 8In the shown arrangement, the first end 11C of the upper end surface 11 is the top end thereof, and the second end 11D is the bottom end thereof. Figure 9 In the shown arrangement, the first end 11C of the upper end surface 11 is the bottom end thereof, and the second end 11D is the top end thereof.

[0127] In one embodiment, the interference signals emitted by the plurality of aircraft countermeasure devices 1 enclose the controlled area along the boundary thereof. In this embodiment, when the aircraft countermeasure devices 1 are arranged along the boundary of the controlled area, the distance between any two adjacent aircraft countermeasure devices 1 is at least sufficient to ensure that the interference signals generated by the two aircraft countermeasure devices 1 have continuous coverage over the boundary, i.e., the boundary of the interference signals generated by the two adjacent aircraft countermeasure devices 1 can be connected to form a continuous signal wall. In this way, the airspace above each side boundary is continuously covered by the interference signals, so as to enclose the controlled area.

[0128] Further, the interference signals emitted by any two adjacent aircraft countermeasure devices 1 can also have an overlapping region along the boundary of the controlled area. In this way, not only a continuous signal wall can be formed over the controlled area, but also the effect of the interference can be enhanced in the overlapping region, so as to improve the interference effect of the signal wall formed by all the aircraft countermeasure devices 1.

[0129] The embodiments in the present specification are 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 mutually referred to. Any combination of the embodiments provided in the present application is within the protection scope of the present application, and will not be repeated here.

[0130] The aircraft countermeasure device 1 and the aircraft control system provided in the present application are described in detail above. The principles and implementation manners of the present application are described by applying specific examples. The above description of the embodiments is only used to help understand the method of the present application and its core idea. It should be noted that, for those skilled in the art, without departing from the principles of the present application, some improvements and modifications can be made to the present application, and these improvements and modifications also fall within the protection scope of the claims of the present application.

Claims

1. An aircraft countermeasure device, characterized by, The application relates to an aircraft countermeasure device. The aircraft countermeasure device comprises: an antenna assembly (10) for emitting an interference signal; and a main control assembly (20) electrically connected with the antenna assembly (10), the main control assembly (20) being used for controlling the antenna assembly (10) to emit the interference signal. The first effective coverage angle of the interference signal projected on a first plane is smaller than the second effective coverage angle of the interference signal projected on a second plane, and the first plane is perpendicular to the second plane. 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).

2. The aircraft countermeasure device of claim 1, wherein, The antenna assembly (10) comprises an upper end surface (11), and the interference signal is emitted from the upper end surface (11); the edge (P1) of the upper end surface (11) along the length direction is parallel to the length direction of the antenna assembly (10); and the edge (P2) of the upper end surface (11) along the width direction is parallel to the width direction of the antenna assembly (10).

3. The aircraft countermeasure device of claim 2, wherein, 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) through the mounting assembly; and the main control assembly (20) is mounted on the fixing member (60) through the mounting assembly.

4. The aircraft countermeasure device of claim 1, wherein, 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 on the fixing member (60); and the main control assembly (20) is fixed on the second mounting structure (40), and the second mounting structure (40) is fixed on the fixing member (60).

5. The aircraft countermeasure device of claim 4, wherein, The antenna assembly (10) can rotate relative to the fixing member (60) along the pitch direction.

6. The aircraft countermeasure device of claim 4, wherein, The antenna assembly (10) is provided with a directional antenna.

7. The aircraft countermeasure device of any of claims 1-6, wherein, Or the antenna assembly (10) is provided with an omnidirectional antenna and a metal reflecting plate. The application relates to a plurality of aircraft countermeasure devices (1) as claimed in any one of claims 1-7, and the plurality of aircraft countermeasure devices (1) are arranged along the boundary of a control area.

8. An aircraft regulation system, characterized in that 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).

9. The aircraft regulation system of claim 8, wherein, The width direction of at least one of the antenna assemblies (10) is parallel to the boundary of the control area corresponding to the position of the aircraft countermeasure device (1). The 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) comprises an upper end surface (11), and the interference signal is emitted from the upper end surface (11); the upper end surface (11) comprises opposite first and second ends; the distance between the first end and the boundary of the control area corresponding to the position 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 position of the aircraft countermeasure device (1).

10. The aircraft regulation system of claim 8, wherein, ​ The height of the first end of the upper end surface (11) of at least one of the antenna assemblies (10) is higher than the height of the second end.

11. The aircraft regulation system of claim 8, wherein, The aircraft countermeasure devices (1) are arranged outside the boundaries of the control area, the antenna assemblies (10) of the aircraft countermeasure devices (1) include upper end surfaces (11), and the interference signals are emitted from the upper end surfaces (11), the upper end surfaces (11) include opposite first ends and second ends, the distance between the first end and the boundary of the control area corresponding to the position 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 position of the aircraft countermeasure device (1). The height of the first end of the upper end surface (11) of at least one of the antenna assemblies (10) is lower than the height of the second end.

12. The aircraft control system according to claim 8, wherein 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 length direction parallel side of at least one of the antenna assemblies (10) on the horizontal plane is perpendicular to the boundary of the control area corresponding to the position of the aircraft countermeasure device (1).

13. The aircraft regulation system of claim 8, wherein, The interference signals emitted by the aircraft countermeasure devices (1) surround the control area along the boundaries of the control area.

14. The aircraft regulation system of claim 8, wherein, The interference signals emitted by adjacent two of the aircraft countermeasure devices (1) have a signal overlapping area along the boundaries of the control area.

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