A C-band pulse antenna for aircraft

Abstract

The invention discloses a C-band pulse antenna for aircraft, comprising a bottom plate, a dielectric substrate, an antenna vibrator and a connector, wherein the dielectric substrate and the connector are arranged on the bottom plate, the antenna vibrator is arranged on the dielectric substrate, a microstrip line is also arranged on the dielectric substrate, the microstrip line connects the antenna vibrator and the connector, the antenna vibrator comprises a first vibrator part and a second vibrator part connected to each other, and the plane formed by the first vibrator part and the second vibrator part is parallel to the bottom plate. The C-band pulse antenna for aircraft is small in size and highly reliable, so that the wireless communication transmission between the aircraft and the ground is more excellent and reliable.

Description

Technical Field

[0001] The invention belongs to the field of antennas, and in particular relates to a C-band pulse antenna used on an aircraft. Background Art

[0002] Most of the existing antennas are large in size, heavy in weight, complex in structure and low in reliability, especially antennas used in aircraft. Aircraft are machines that fly in the atmosphere or in space outside the atmosphere (space). Aircraft need to receive and radiate radio waves. The antennas of existing aircraft are large in size, low in reliability, and the antenna's radiation pattern has low compatibility with the aircraft, which cannot meet the needs.

[0003] Therefore, how to improve the performance of the antenna installed outside the aircraft so that the wireless communication transmission between the aircraft and the ground is better and more reliable is a technical problem that technicians in this technical field need to solve. Summary of the invention

[0004] The main technical problem solved by the present invention is to provide a C-band pulse antenna for use on an aircraft, which solves the problems of low compatibility between the aircraft antenna and the aircraft, insufficient reliability, and large size in the prior art.

[0005] In order to solve the above technical problems, the technical solution adopted by the present invention is to provide a C-band pulse antenna for an aircraft, including a bottom plate, a dielectric substrate, an antenna vibrator and a connector, the dielectric substrate and the connector are arranged on the bottom plate, the antenna vibrator is arranged on the dielectric substrate, a microstrip line is also arranged on the dielectric substrate, the microstrip line connects the antenna vibrator and the connector, the antenna vibrator includes a first vibrator part and a second vibrator part connected to each other, and a first supporting part supporting the first vibrator part and the second vibrator part, and the plane formed by the first vibrator part and the second vibrator part is parallel to the bottom plate.

[0006] Preferably, a vibrator angle is formed between the first vibrator portion and the second vibrator portion, and the range of the vibrator angle is 45°-120°.

[0007] Preferably, the first vibrator portion and the second vibrator portion are in the shape of elongated strips, and the vibrator angle is 90°.

[0008] Preferably, it also includes a boss, which is arranged on the bottom plate, and the medium substrate is arranged on the boss.

[0009] Preferably, a substrate groove is provided on the boss, and the substrate groove is used to accommodate and set the medium substrate.

[0010] Preferably, it also includes a guiding vibrator, which has a vertical portion and a horizontal portion that are connected to each other and perpendicular to each other, the vertical portion is arranged on the boss and perpendicular to the bottom plate, and the horizontal portion is parallel to the bottom plate.

[0011] Preferably, there are multiple guiding vibrators, namely a first guiding vibrator, a second guiding vibrator and a third guiding vibrator. The first guiding vibrator is arranged on the front side of the antenna vibrator, and the second guiding vibrator and the third guiding vibrator are arranged on the rear side of the antenna vibrator in sequence, and the first guiding vibrator, the second guiding vibrator, the third guiding vibrator and the antenna vibrator are arranged in a straight line.

[0012] Preferably, the orientation of the horizontal portion of the first guiding vibrator is the same as the orientation of the bisector of the vibrator angle, the orientation of the horizontal portion of the second guiding vibrator and the orientation of the horizontal portion of the third guiding vibrator are both perpendicular to the bisector of the vibrator angle, and the orientation of the horizontal portion of the second guiding vibrator is opposite to the orientation of the horizontal portion of the third guiding vibrator.

[0013] Preferably, the cross section of the boss is trapezoidal.

[0014] Preferably, a shell is provided on the bottom plate, and the shell is used to cover the boss, the antenna element, the first guiding element, the second guiding element and the third guiding element.

[0015] The beneficial effects of the present invention are as follows: the present invention discloses a C-band pulse antenna for aircraft, comprising a bottom plate, a dielectric substrate, an antenna vibrator and a connector, wherein the dielectric substrate and the connector are arranged on the bottom plate, the antenna vibrator is arranged on the dielectric substrate, a microstrip line is also arranged on the dielectric substrate, the microstrip line connects the antenna vibrator and the connector, the antenna vibrator comprises a first vibrator part and a second vibrator part connected to each other, and the plane formed by the first vibrator part and the second vibrator part is parallel to the bottom plate. The C-band pulse antenna for aircraft is small in size and highly reliable, and can be installed on aerospace aircraft. The antenna cooperates with other components to establish channel transmission between the aircraft and the ground measurement and control center, completes measurement and control and communication, and makes the wireless communication transmission between the aircraft and the ground more excellent and reliable. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a schematic diagram of an embodiment of a C-band pulse antenna used on an aircraft according to the present invention;

[0017] Figure 2 yes Figure 1 An exploded schematic diagram of the illustrated embodiment;

[0018] Figure 3 yes Figure 1 An exploded schematic diagram of the illustrated embodiment (with the housing removed);

[0019] Figure 4 This is a schematic diagram of an aircraft flight according to an embodiment of the present invention, which shows a C-band pulse antenna used on an aircraft;

[0020] Figure 5 It is a schematic diagram of the installation angle of an embodiment of a C-band pulse antenna used on an aircraft according to the present invention;

[0021] Figure 6 It is a schematic diagram of the installation angle of an embodiment of a C-band pulse antenna used on an aircraft according to the present invention;

[0022] Figure 7 It is a schematic diagram of the antenna gain pattern requirements of an embodiment of a C-band pulse antenna used on an aircraft according to the present invention;

[0023] Figure 8 It is a schematic diagram of antenna standing wave ratio simulation of an embodiment of a C-band pulse antenna used on an aircraft according to the present invention;

[0024] Fig. 9 Another embodiment of the C-band pulse antenna for aircraft of the present invention has an antenna element but does not have a directional pattern of the director element;

[0025] Fig.10 Another embodiment of the C-band pulse antenna for aircraft of the present invention has an antenna element but does not have a gain diagram of a guide element;

[0026] Fig.11 The present invention is a C-band pulse antenna for aircraft in another embodiment, wherein the director oscillator has only the directional pattern of the first director oscillator;

[0027] Fig.12 is a gain diagram of another embodiment of the C-band pulse antenna for aircraft of the present invention, in which the director oscillator has only the first director oscillator;

[0028] Fig.13 The present invention is a C-band pulse antenna for aircraft in another embodiment, wherein the director element has only the directional pattern of the second director element;

[0029] Fig.14 is a gain diagram of another embodiment of the C-band pulse antenna for aircraft of the present invention, in which the director oscillator has only the second director oscillator;

[0030] Fig.15 The directional diagram of another embodiment of the C-band pulse antenna for aircraft of the present invention in which the director vibrator has only the third director vibrator;

[0031] Fig.16 The directional pattern of another embodiment of the C-band pulse antenna for aircraft of the present invention, wherein the director oscillator has only the first director oscillator and the second director oscillator;

[0032] Fig.17 The directional diagram of another embodiment of the C-band pulse antenna for aircraft of the present invention, in which the director oscillators only have the first director oscillator and the third director oscillator;

[0033] Fig.18The directional diagram of another embodiment of the C-band pulse antenna for aircraft of the present invention, in which the director oscillators only have the second director oscillator and the third director oscillator;

[0034] Fig.19 In another embodiment of the C-band pulse antenna for aircraft of the present invention, the director vibrator has the directional patterns of the first director vibrator, the second director vibrator and the third director vibrator at the same time;

[0035] Fig. 20 The present invention is a C-band pulse antenna for aircraft in another embodiment, wherein the director oscillator has a gain diagram of the first director oscillator, the second director oscillator and the third director oscillator at the same time;

[0036] Fig.21 This is a directional diagram of another embodiment of the C-band pulse antenna used on an aircraft of the present invention when it does not have a boss. DETAILED DESCRIPTION

[0037] In order to facilitate the understanding of the present invention, the present invention is described in more detail below in conjunction with the accompanying drawings and specific embodiments. Preferred embodiments of the present invention are provided in the accompanying drawings. However, the present invention can be implemented in many different forms and is not limited to the embodiments described in this specification. On the contrary, the purpose of providing these embodiments is to make the understanding of the disclosure of the present invention more thorough and comprehensive.

[0038] It should be noted that, unless otherwise defined, all technical and scientific terms used in this specification have the same meaning as those commonly understood by those skilled in the art of the present invention. The terms used in the specification of the present invention are only for the purpose of describing specific embodiments and are not intended to limit the present invention.

[0039] In the drawings, arrow X indicates the front direction, that is, the front-rear direction, arrow Y indicates the side direction, that is, the left-right direction, and arrow Z indicates the vertical direction, that is, the up-down direction.

[0040] Combination Figure 1 , Figure 2 and Figure 3The C-band pulse antenna for an aircraft includes a bottom plate 1, a dielectric substrate 2, an antenna vibrator 3 and a connector 4. The dielectric substrate 2 and the connector 4 are arranged on the bottom plate 1, and have a high degree of overlap (the dielectric 2 and the connector 4 are arranged on the bottom plate 1, and the bottom plate 1 is used as a central carrier. Various components are arranged and installed around the bottom plate 1, so that the overall overlap of the antenna is high), which is conducive to miniaturization of the antenna. The antenna vibrator 3 is arranged on the dielectric substrate 2. A microstrip line 21 is also arranged on the dielectric substrate 2. The microstrip line 21 connects the antenna vibrator 3 and the connector 4. The antenna vibrator 3 includes a first vibrator part 31 and a second vibrator part 32 that are connected to each other. The plane formed by the first vibrator part 31 and the second vibrator part 32 is parallel to the bottom plate 1. The antenna vibrator 3 is a monopole antenna with a wide coverage of the radiation pattern.

[0041] The C-band pulse antenna of this invention can be installed on an aerospace aircraft. The C-band pulse antenna can cooperate with other components to establish a channel transmission between the aircraft (such as a rocket) and a ground measurement and control center, and complete the measurement and control and communication between the aircraft and the ground.

[0042] Further preferably, the antenna element 3 is made of metal.

[0043] Further preferably, the dielectric substrate 2 is made of epoxy resin, glass cloth or other materials, and the microstrip line 21 on the dielectric substrate 2 is a microstrip line with a length of one quarter wavelength, which is used for matching circuits.

[0044] Preferably, the antenna element 3 also includes a first supporting portion 33, which is columnar and vertically arranged on the dielectric substrate 2. The top end of the first supporting portion 33 connects the first vibrator portion 31 and the second vibrator portion 32. Specifically, an intersection is formed when the first vibrator portion 31 and the second vibrator portion 32 are connected, and the top end of the first supporting portion 33 is connected to the intersection.

[0045] Preferably, a vibrator angle is formed between the first vibrator portion 31 and the second vibrator portion 32 , and the range of the vibrator angle is 45°-120°. Further preferably, the range of the vibrator angle is 70°-110°. Specifically, the range of the vibrator angle is 90°.

[0046] Preferably, the first vibrator portion 31 and the second vibrator portion 32 are in the shape of long strips, and the vibrator angle is 90°, that is, the first vibrator portion 31 is perpendicular to the second vibrator portion 32 .

[0047] Preferably, the joint 4 is arranged at the center position of the lower surface of the base plate 1 .

[0048] Preferably, it also includes a boss 5, which is arranged on the base plate 1, and the dielectric substrate 2 is arranged on the boss 5. Further preferably, the cross-section of the boss 5 is a trapezoid, which is narrow at the top and wide at the bottom. The boss 5 is located in the middle position of the base plate 1, and the materials of the boss 5 and the base plate 1 are both metal. The setting of the boss 5 is to reduce the reflection effect of the base plate 1 on the antenna radiation pattern.

[0049] Preferably, a substrate groove 51 is provided on the boss 5, and the substrate groove 51 is used to accommodate the dielectric substrate 2, which can well protect and hide the dielectric substrate 2, so that the upper surface of the dielectric substrate 2 is lower than the upper surface of the boss 5, or the upper surface of the dielectric substrate 2 is flush with the upper surface of the boss 5, so that the dielectric substrate 2 is prevented from protruding from the upper surface of the boss 5, and the dielectric substrate 2 is well protected to ensure the reliability of the antenna structure.

[0050] Preferably, the height of the boss 5 is 12 mm, the boss 5 is trapezoidal, the upper base is 4 mm, and the lower base is 20 mm. The boss 5 is provided to make the antenna a certain distance away from the base plate 1, thereby reducing the reflection effect of the base plate 1 on the antenna radiation pattern. A space gap is reserved inside the boss 5 so that the wire can be threaded in the gap.

[0051] Preferably, it also includes a guide vibrator 6, which has a vertical portion and a horizontal portion that are interconnected and perpendicular to each other, the vertical portion is arranged on the boss 5 and is perpendicular to the base plate 1, and the horizontal portion is parallel to the base plate 1. The material of the guide vibrator 6 is metal. The function of the guide vibrator 6 is to shape the antenna so that the gain in the direction parallel to the base plate 1 is increased and the distribution of the directional pattern qualification rate is satisfied.

[0052] Preferably, there are multiple guiding vibrators 6, namely a first guiding vibrator 61, a second guiding vibrator 62 and a third guiding vibrator 63. The first guiding vibrator 61 is arranged on the front side of the antenna vibrator 3, and the second guiding vibrator 62 and the third guiding vibrator 63 are arranged on the rear side of the antenna vibrator 3 in sequence, and the first guiding vibrator 61, the second guiding vibrator 62, the third guiding vibrator 63 and the antenna vibrator 3 are arranged in a straight line.

[0053] Preferably, the orientation of the horizontal portion 611 of the first guiding vibrator 61 is the same as the orientation of the bisector of the vibrator angle, the orientation of the horizontal portion 621 of the second guiding vibrator 62 and the orientation of the horizontal portion 631 of the third guiding vibrator 63 are both perpendicular to the bisector of the vibrator angle, and the orientation of the horizontal portion 621 of the second guiding vibrator 62 is opposite to the orientation of the horizontal portion 631 of the third guiding vibrator 63, which can increase the radiation range, improve the gain of the antenna, and enhance the antenna reliability.

[0054] Preferably, a shell 7 is provided on the base plate 1 , and the shell 7 is used to cover the boss 5 , and protect the boss 5 , the antenna element 3 and the guide element 6 .

[0055] Preferably, the net space size of the shell 7 is: 95mm long×70mm wide×21mm high, which can well limit the height. The height of the C-band pulse antenna used on the aircraft is 17mm. The present invention has the advantages of small size, light weight, simple and reliable structure.

[0056] Preferably, the length range of the horizontal part of the first guide vibrator 61 is 2mm-6mm, the length of the horizontal part 611 of the first guide vibrator 61 is 3mm or 5mm, the length range of the horizontal part 621 of the second guide vibrator 62 is 2mm-6mm, the length of the horizontal part 621 of the second guide vibrator 62 is 4mm or 6mm, the length range of the horizontal part 631 of the third guide vibrator 63 is 2mm-6mm, the length of the horizontal part 631 of the third guide vibrator 63 is 4mm or 6mm, and the lengths of the first vibrator part 31 and the second vibrator part 32 are both 7.8mm.

[0057] Preferably, the height of the boss 5 is 12.5 mm, the length of the boss is 70 mm, the height of the first guiding vibrator 61 is 6 mm, the height of the second guiding vibrator 62 is 5 mm, the height of the third guiding vibrator 63 is 7.5 mm, the interval between the first guiding vibrator 61 and the second guiding vibrator 62 is 30 mm, the interval between the second guiding vibrator 62 and the third guiding vibrator 63 is 15 mm, the distance between the first guiding vibrator 61 and the antenna vibrator 3 is 15 mm, the distance between the antenna vibrator 3 and the second guiding vibrator 62 is 15 mm, and the distance between the antenna vibrator 3 and the third guiding vibrator 63 is 30 mm.

[0058] Preferably, the second director vibrator 62 and the third director vibrator 63 have the same height.

[0059] Recombination Figure 4 , Figure 5 and Figure 6 , α is the division angle of the equatorial plane of the aircraft. Looking from the head of the aircraft to the tail of the aircraft, the III quadrant of the rocket body is 0°, rotating counterclockwise, passing through the IV, I, and II quadrants in sequence, a total of 360°, β is the division angle of the meridian plane of the aircraft, with the flight direction of the aircraft as 0°, extending from the head of the aircraft to the tail of the aircraft, a total of 180°.

[0060] Preferably, the split angle α of one antenna is: 219°±1°; the split angle α of another antenna is: 39°±1°.

[0061] Antenna gain pattern requirements are as follows: Figure 7 As shown, from this Figure 7 It can be seen that when the direction angle β is 40°-60°, the antenna gain is greater than -10dB, and when the direction angle β is 140°-150°, the antenna gain is the maximum and is -2dB.

[0062] Recombination Figure 8 , Figure 8 It is a schematic diagram of antenna standing wave ratio simulation of an embodiment of a C-band pulse antenna for aircraft of the present invention. The horizontal axis Freq is the impedance bandwidth, and the vertical axis VSWR is the standing wave ratio. The antenna has lower reflection and standing wave ratio.

[0063] Fig. 9 Another embodiment of the C-band pulse antenna for aircraft of the present invention only has an antenna element and does not have a directional pattern of the guiding element. Fig.10 Another embodiment of the C-band pulse antenna for aircraft of the present invention has an antenna vibrator and does not have a gain diagram of a guide vibrator. Fig. 9 In the figure, the P direction (the direction indicated by the red arrow) is the flight direction, theta represents the angle on the H plane of the antenna, the Q direction (the direction indicated by the green line segment in the figure, and phi should be marked next to the green line segment, and the green line segments in subsequent figures are similar to this, which will not be repeated here) is perpendicular to the flight direction, and phi represents the angle on the E plane. Fig. 9 The symbol annotations in are the same as those in the other subsequent directional diagrams.

[0064] exist Fig.10 In the figure, the horizontal axis theta represents the angle on the H plane of the antenna, the vertical axis Gain represents the gain, and phi represents the angle on the E plane. The H plane is the plane formed by the maximum radiation direction of the antenna and the magnetic field direction, and the E plane is the plane formed by the maximum radiation direction of the antenna and the electric field direction.

[0065] exist Fig. 9 It can be seen that the maximum gain of the antenna is 4.2977dB, and the gain of the upper part is higher and the coverage angle is larger, which basically meets the antenna design requirements. Fig.10 It can be seen that the gains when phi is 30°, 60°, 90°, 120° and 150°, the highest gain basically meets the requirements, but the minimum gain is low and needs further optimization.

[0066] Hereinafter, the directivity pattern and gain of the antenna are changed by setting the first directing element, the second directing element and the third directing element.

[0067] exist Fig. 9 and Fig.10 The embodiment shown has only the antenna element base. Fig.11 In another embodiment of the C-band pulse antenna for aircraft of the present invention, the director vibrator has only the directional pattern of the first director vibrator. Fig.12 This is a gain diagram of another embodiment of the C-band pulse antenna for aircraft of the present invention, in which the guiding oscillator has only the first guiding oscillator; Fig. 9 and Fig.10Compared with the case without the guide oscillator, after adding the first guide oscillator, the maximum gain along its direction (theta=180° direction) is improved, and the maximum radiation direction is shifted along the -Z direction.

[0068] exist Fig. 9 and Fig.10 The embodiment shown has only the antenna element base. Fig.13 The directional pattern of the C-band pulse antenna used on an aircraft in another embodiment of the present invention is that the director vibrator has only the second director vibrator. Fig.14 is a gain diagram of another embodiment of the C-band pulse antenna for aircraft of the present invention in which the director oscillator has only the second director oscillator; and Fig. 9 and Fig.10 Compared with the case without a guide element, after adding the second guide element, the maximum gain along its direction (theta=0° direction) is improved, and the maximum radiation direction is shifted along the +Z direction.

[0069] exist Fig. 9 and Fig.10 The embodiment shown has only the antenna element base. Fig.15 This is the directional diagram of another embodiment of the C-band pulse antenna used on an aircraft of the present invention, in which the director oscillator has only the third director oscillator. Fig.15 In the figure, the area indicated by the first arrow F1 on the left represents that the gain of the antenna in this direction is low, and it is necessary to add a guiding vibrator in the upper half space to improve the gain; while the area indicated by the second arrow F2 on the right represents that the gain of this part of the area is too large, which is significantly larger than the antenna gain of the area indicated by the first arrow F1 on the left, so that the antenna gain of the area indicated by the first arrow F1 on the left is insufficient.

[0070] exist Fig. 9 and Fig.10 The embodiment shown has only the antenna element base. Fig.16 In another embodiment of the present invention, the C-band pulse antenna for aircraft has only the first and second guiding oscillators, which is similar to the above-mentioned Fig.15 compared to, Fig.16 The gain of the area indicated by the middle arrow F1 is slightly improved, so it can be seen that adding the guide vibrator is beneficial.

[0071] exist Fig. 9 and Fig.10 The embodiment shown has only the antenna element base. Fig.17 The directional diagram of another embodiment of the C-band pulse antenna for aircraft of the present invention, wherein the guiding oscillators only have the first guiding oscillator and the third guiding oscillator, Fig.17 The gain of the area indicated by the arrow F1 is low, so it is necessary to Fig.17Adding a second director to the upper half of the space shown improves the gain.

[0072] exist Fig. 9 and Fig.10 The embodiment shown has only the antenna element base. Fig.18 The directional diagram of another embodiment of the C-band pulse antenna for aircraft of the present invention, wherein the director oscillators only have the second director oscillator and the third director oscillator, Fig.18 The area indicated by the first arrow F1 is very steep, and the antenna gain drops rapidly after passing the maximum point. Therefore, it is necessary to add a first guiding element, and the first guiding element is located at Fig.18 The lower half of the space shown in the figure can improve the gain of the antenna so that the antenna meets the requirements; at the same time, Fig.18 The green color of the directional diagram in the area indicated by the second arrow F2 is very obvious. The obvious green area is where the gain is very small, which is called zero depth.

[0073] Fig.19 In another embodiment of the C-band pulse antenna for aircraft of the present invention, the director vibrator has the directional pattern of the first vibrator, the second director vibrator and the third director vibrator at the same time. Fig. 20 In another embodiment of the C-band pulse antenna used on an aircraft of the present invention, the guiding vibrator has the gain diagrams of the first vibrator, the second guiding vibrator and the third guiding vibrator at the same time. After adding three guiding vibrators (i.e., the first guiding vibrator, the second guiding vibrator and the third guiding vibrator), the coverage gain of the antenna in the +Z direction is significantly improved, and the zero depth on the theta=90° plane is improved, and the coverage rate in the specified direction reaches the best effect. After setting the guiding vibrator, the gain will be more average, and the guiding vibrator can convert a large gain in a small range into a small gain in a large range, that is, the guiding vibrator can make the gain more balanced and not too "steep".

[0074] Preferably, combined Figure 2 Embodiment, if no boss is provided, such as Fig.21 As shown, Fig.21 The overall profile of the radiation pattern shown has a steep mutation that is quite obvious, indicating that the spatial distribution of the radiation pattern is uneven and discontinuous, especially the antenna gain cannot meet the antenna gain requirements at theta = 20°-60° and theta = 110°-150°. The reason for the steepness is that the antenna vibrator 3 is very close to the base plate 1 and the height is not increased. By setting the boss 5, the distance between the antenna vibrator 3 and the base plate 1 is increased, and by adding the guide vibrator 6 (including the first guide vibrator 61, the second guide vibrator 62 and the third guide vibrator 63), the antenna radiation pattern can be pulled to the upper and lower areas of the space shown in the figure, so that the antenna gain requirements are better met.

[0075] Based on the above embodiments, the present invention discloses a C-band pulse antenna for aircraft, including a bottom plate, a dielectric substrate, an antenna vibrator and a connector, wherein the dielectric substrate and the connector are arranged on the bottom plate, the antenna vibrator is arranged on the dielectric substrate, a microstrip line is also arranged on the dielectric substrate, the microstrip line connects the antenna vibrator and the connector, the antenna vibrator includes a first vibrator part and a second vibrator part connected to each other, and the plane formed by the first vibrator part and the second vibrator part is parallel to the bottom plate. The C-band pulse antenna for aircraft is small in size and highly reliable, making the wireless communication transmission between the aircraft and the ground more excellent and reliable.

[0076] The above are only embodiments of the present invention, and are not intended to limit the patent scope of the present invention. Any equivalent structural transformations made using the contents of the present invention's specification and drawings, or directly or indirectly applied in other related technical fields, are included in the patent protection scope of the present invention.

Claims

1. A C-band pulse antenna for use on an aircraft, characterized in that: The invention comprises a bottom plate, a dielectric substrate, an antenna element and a connector, wherein the dielectric substrate and the connector are arranged on the bottom plate, the antenna element is arranged on the dielectric substrate, a microstrip line is further arranged on the dielectric substrate, the microstrip line connects the antenna element and the connector, the antenna element comprises a first dipole part and a second dipole part connected to each other, and a first supporting part supporting the first dipole part and the second dipole part, and a plane formed by the first dipole part and the second dipole part is parallel to the bottom plate; A vibrator angle is formed between the first vibrator part and the second vibrator part, the range of the vibrator angle is 45°-120°, and the first vibrator part and the second vibrator part are in the shape of long strips; It also includes a boss, the boss is arranged on the bottom plate, the dielectric substrate is arranged on the boss, a substrate groove is opened on the boss, and the substrate groove is used to accommodate and arrange the dielectric substrate; It also includes a guide vibrator, which has a vertical portion and a horizontal portion that are interconnected and perpendicular to each other, the vertical portion is arranged on the boss and is perpendicular to the base plate, and the horizontal portion is parallel to the base plate. There are multiple guide vibrators, namely a first guide vibrator, a second guide vibrator and a third guide vibrator, the first guide vibrator is arranged on the front side of the antenna vibrator, the second guide vibrator and the third guide vibrator are arranged on the rear side of the antenna vibrator in sequence, and the first guide vibrator, the second guide vibrator, the third guide vibrator and the antenna vibrator are arranged in a straight line.

2. The C-band pulse antenna for aircraft according to claim 1, characterized in that: The orientation of the horizontal portion of the first guiding vibrator is the same as the orientation of the bisector of the vibrator angle, the orientation of the horizontal portion of the second guiding vibrator and the orientation of the horizontal portion of the third guiding vibrator are both perpendicular to the bisector of the vibrator angle, and the orientation of the horizontal portion of the second guiding vibrator is opposite to the orientation of the horizontal portion of the third guiding vibrator.

3. The C-band pulse antenna for aircraft according to claim 2, characterized in that: The cross section of the boss is trapezoidal.

4. The C-band pulse antenna for aircraft according to claim 3, characterized in that: A shell is arranged on the bottom plate, and the shell is used for covering the boss, the antenna element, the first guiding element, the second guiding element and the third guiding element.

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