Layout configuration of four-element detection antenna arrays on two sides of fuselage

Abstract

The invention belongs to the field of overall shape design of airplanes, and relates to a four-element detection antenna array layout configuration on two sides of a fuselage. According to the structure, four-element VHF (very high frequency) interferometer antenna arrays of 30-300 MHz are symmetrically arranged on the two sides of a machine body between 30-31 stringers on the left side and the right side of 11-22 frames; the outer surface of the antenna array is subjected to pneumatic modification design and is in a tongue shape; the antenna array on each side is composed of four trapezoidal antennas which are a first antenna array element, a second antenna array element, a third antenna array element and a fourth antenna array element in sequence from the machine head to the machine tail.

Description

Technical Field

[0001] The present invention belongs to the field of overall aircraft shape design, and relates to a layout configuration of a four-element detection antenna array on both sides of the fuselage. Background Art

[0002] The airborne electronic direction-finding system has the advantages of a large operating range, a long detection distance, and the ability to achieve single-aircraft target positioning. However, due to the limitation of the external dimension of the aircraft platform, the effective space available for arranging the antenna array, the allowable size and quantity of the antenna array elements are very limited. In addition, the metal skin structure of the fuselage will cause changes in the amplitude-phase characteristics of the direction-finding antenna, increasing the difficulty and complexity of the configuration of the airborne direction-finding antenna array. Considering the structural characteristics of the aircraft, the two sides of the front and middle sections of the fuselage are utilized to the maximum extent, and a "two-side four-element parallel" antenna array layout configuration suitable for airborne installation conditions is obtained. Using this direction-finding antenna array, the system has a strong ability to suppress the phase distortion formed by the influence of the metal skin on the airborne antenna, and can better solve the problem of high-precision direction finding of airborne direction-finding equipment in the actual environment. Summary of the Invention

[0003] Object of the Invention: The present invention provides a new layout configuration of a four-element antenna array on both sides of the fuselage for arranging an eight-element detection antenna array on the aircraft body surface. Under the condition of limited layout dimensions of the body structure, it realizes high-precision and fast direction finding in the very high frequency (VHF) range of 30 MHz to 300 MHz, and solves the contradiction between the direction-finding accuracy and the non-ambiguous range of the arrival azimuth angle under the conditions of meeting the detection working frequency and 360-degree direction-finding full coverage.

[0004] Technical Solution:

[0005] A layout configuration of a four-element detection antenna array on both sides of the fuselage is provided, including: symmetrically arranging a four-element 30 MHz to 300 MHz very high frequency (VHF) interferometer antenna array between the 30th and 31st longerons on the left and right sides of the fuselage between the 11th and 22nd frames; the outer surface of the antenna array is aerodynamically shaped and is in the shape of a "tongue".

[0006] Further, each side of the antenna array is composed of 4 trapezoidal antennas, which are the first antenna element, the second antenna element, the third antenna element, and the fourth antenna element in sequence from the nose to the tail of the aircraft.

[0007] Further, a four-element antenna array installation platform is designed between the 30th and 31st longerons on the left and right sides of the fuselage between the 11th and 22nd frames, and the plane of the platform is parallel to the aircraft symmetry plane.

[0008] Further, the antenna array installation platform adopts a non-airtight combined frame structure and is connected to the skin, longeron, and frame edge.

[0009] Further, the installation platform is made of metal material, the surface should be flat and smooth, and at the same time has good electrical conductivity.

[0010] Further, if the distance between the second antenna element and the third antenna element is L, the distance between the first antenna element and the second antenna element is 1.5L, and the distance between the third antenna element and the fourth antenna element is 2.25L.

[0011] Further, the 4 antenna elements on the right side are symmetrically and parallelly arranged with respect to the 4 antenna elements on the left side with respect to the aircraft symmetry plane.

[0012] Further, the four-element detection antenna array on one side is arranged on the maximum width line of the fuselage.

[0013] The beneficial effects are as follows:

[0014] 1) A new optional layout configuration of the "two-side four-element parallel" type is provided by arranging a multi-element detection antenna array (including an eight-element array) on the surface of the aircraft fuselage.

[0015] 2) The four-element detection antenna arrays on both sides of the fuselage are arranged on the maximum width line of the fuselage, solving the problem that the layout size of the antenna array is restricted by the fuselage structure.

[0016] 3) The outer surface of the antenna array is aerodynamically shaped and is in the shape of a "tongue", reducing local airflow separation.

[0017] 4) High-precision and fast direction finding in the very high frequency (VHF) band of 30 MHz to 300 MHz is achieved on the aircraft.

[0018] 5) 360-degree direction finding full coverage is achieved under the condition of meeting the detection working frequency. Description of the Drawings

[0019] Figure 1 It is a layout diagram of a two-side parallel four-element antenna array.

[0020] Figure 2 It is an external view of the antenna array. Detailed Implementation Manner

[0021] According to the antenna installation requirements of the mission system of the present invention, a four-element very high frequency (VHF) interferometer antenna array operating at 30 MHz to 300 MHz is arranged between the 30th and 31st longerons on the left and right sides of the fuselage frames 11 to 22. The antenna array is composed of 4 trapezoidal antennas, and the single external dimension is length × width × height: 630 mm × 140 mm × 420 mm. The four-element detection antenna is shown in Figure 1 .

[0022] A four-element antenna array installation platform is designed between the 30th and 31st longerons on the left and right sides of the fuselage frames 11 to 22. The plane of the platform is parallel to the aircraft symmetry plane, and the observation windows on the left and right sides of the fuselage frames 10 to 11 are cancelled accordingly.

[0023] To ensure the installation requirements of the antenna array and the stiffness of the antenna installation platform, the antenna array installation platform adopts a non-airtight combined frame structure and is connected to the skin, stringers, and frame edges.

[0024] The installation platform is made of metal materials, with a flat and smooth surface and good electrical conductivity.

[0025] The installation platform has good stiffness and strength to ensure the firm and reliable connection between the antenna and the platform. The installation surface between the antenna and the airframe is polished smoothly to achieve airtightness and watertightness.

[0026] The distance between the second antenna element and element 3 is L, the distance between element 1 and element 2 is 1.5L, and the distance between element 3 and element 4 is 2.25L.

[0027] After the antenna elements are installed, they are in a plane on the XOY plane of the aircraft's symmetry plane, and the error between the elements is ≤3 mm.

[0028] The baseline of the antenna element is parallel to the OX axis, and the deviation of the baseline midline is required to be ≤3 mm.

[0029] The feeder of the antenna element directly enters the airtight cabin.

[0030] The antenna is installed according to the heading mark on the antenna.

[0031] To meet the requirements for disassembly during antenna maintenance, the cable needs to retain enough length to facilitate disassembly during antenna unit maintenance.

[0032] The bending radius of the cable is greater than 50 mm.

[0033] To meet the requirements for phase consistency during direction finding, 7 cables are designed with equal lengths.

[0034] The single antenna of the four-element antenna array is a "tongue" - shaped antenna, which is directly installed on the maximum width line on both sides of the fuselage, adopting a "parallel four - element on both sides" layout configuration. Among them, 4 elements on the left side are installed on the maximum width line of the fuselage, and the installation platform is set in the same installation plane, parallel to the aircraft's symmetry plane. The distance between the second antenna element and element 3 is L, the distance between element 1 and element 2 is 1.5L, and the distance between element 3 and element 4 is 2.25L. The 4 elements on the right side are symmetrically and parallelly arranged with respect to the 4 elements on the left side with respect to the aircraft's symmetry plane.

[0035] To ensure the installation accuracy and connection strength of the antenna, an integral machining installation platform is designed at the installation position of each unit antenna on the outer surface of the airframe, and the airframe structure is locally strengthened. The outer surface of the antenna array is aerodynamically shaped to reduce local airflow separation.

Claims

1. A four-element detection antenna array layout configuration on both sides of the fuselage, characterized in that, Comprising: On both sides of the fuselage between the longerons No. 30 and No. 31 on the left and right sides of Frame No. 11 - 22, a four - element VHF (Very High Frequency) interferometer antenna array operating at 30 MHz - 300 MHz is symmetrically arranged; the outer surface of the antenna array has been aerodynamically shaped and is in the shape of a "tongue".

2. According to the configuration described in claim 1, each side of the antenna array is composed of 4 trapezoidal antennas, which are the first antenna element, the second antenna element, the third antenna element, and the fourth antenna element in sequence from the nose to the tail.

3. The configuration according to claim 1, characterized in that, On both sides of the fuselage between the longerons No. 30 and No. 31 on the left and right sides of Frame No. 11 - 22, an installation platform for the four - element antenna array is designed, and the plane of the platform is parallel to the aircraft symmetry plane.

4. The configuration according to claim 2, wherein, The installation platform of the antenna array adopts a non - airtight combined frame structure and is connected to the skin, longerons, and frame edges.

5. The configuration according to claim 3, characterized in that, The installation platform is made of metal materials, and its surface should be flat, smooth, and have good electrical conductivity.

6. The configuration according to claim 1, characterized in that, If the distance between the second antenna element and the third antenna element is L, then the distance between the first antenna element and the second antenna element is 1.5L, and the distance between the third antenna element and the fourth antenna element is 2.25L.

7. According to the configuration described in claim 1, the 4 antenna elements on the right side and the 4 antenna elements on the left side are symmetrically and parallelly arranged with respect to the aircraft symmetry plane.

8. The configuration according to claim 1, characterized in that, One - side four - element detection antenna array is arranged on the maximum width line of the fuselage.

Images