CN116014456A

CN116014456A - Bow and rocket telemetry antenna array based on feed phase difference and screw coupling

Info

Publication number: CN116014456A
Application number: CN202211679450.9A
Authority: CN
Inventors: 李冬; 桂苏嘉; 王阳阳; 郭家玉; 张拓
Original assignee: Xian Aerospace Propulsion Institute
Current assignee: Xian Aerospace Propulsion Institute
Priority date: 2022-12-26
Filing date: 2022-12-26
Publication date: 2023-04-25

Abstract

A projectile telemetry antenna array based on feed phase difference and screw coupling, comprising: the device comprises an inverted F antenna, a rocket cabin, a rectifying block, a radio frequency cable and a transmitter; the inverted F antennas are uniformly distributed circumferentially about the central axis of the rocket cabin body, and are fixedly mounted on the outer wall of the rocket cabin body; the inverted F antenna is connected with the transmitter through a radio frequency cable; a rectifying block is arranged above the head of each inverted F antenna; the rectifying block is fixedly arranged on the outer wall of the rocket cabin body; the rectification block is used for guiding flow, so that standing points of pneumatic heating cannot occur on the inverted F antenna. According to the antenna, gain recess in the axis direction of the rocket body is optimized, aerodynamic heat and force protection of the antenna is achieved through the rectifying block arranged in front of the antenna, electromagnetic resonance and induction current are generated through the mounting screw of the rectifying block, and secondary radiation and reflection guiding effects of electromagnetic waves are achieved.

Description

Bow and rocket telemetry antenna array based on feed phase difference and screw coupling

Technical Field

The invention designs a projectile and rocket telemetry antenna array based on feed phase difference and screw coupling, which is used for realizing the rear coverage of telemetry signals when a projectile and rocket flies, so as to ensure the stability and reliability of telemetry links and ensure the reliable reception of telemetry data.

Background

Telemetry is a technology for remotely measuring parameters of an object to be measured, is important in the design and test of missiles and rockets, and has the function of converting high-frequency current into electromagnetic waves and radiating the electromagnetic waves in a specified direction, thereby being one of key components of a missile telemetry system.

During the rocket test flight, the pattern of the telemetry transmitting antenna is very important for the reception of telemetry data. The general rocket telemetry antenna is realized by adopting a microstrip antenna, the annular microstrip antenna is usually arranged in the head cover or embedded in the wall surface of the cabin body, and the head cover is internally provided with a mounting space which occupies the load and needs to use a wave-transparent head cover, thereby increasing the complexity and cost of the processing design of the head cover; microstrip antennas are embedded on the bulkhead, so that weakening of the structural strength of an arrow body and increase of processing complexity are brought; and because the polarization mode of the microstrip antenna is horizontal polarization relative to the surface of the rocket body, the horizontal polarized wave decays very fast along the direction of the surface of the metal projectile body, so that an irreparable gain recess appears at the rear part of the axis of the projectile body, the recess provides higher requirements on the number and the positions of the telemetry data receiving stations, and the cost and the complexity of the telemetry data receiving of a transmitting task are increased.

Disclosure of Invention

The invention solves the technical problems that: the defects of the prior art are overcome, the missile telemetry antenna array is provided, the directional optimization adjustment of an antenna pattern is realized based on screw electromagnetic coupling and feed phase difference, the reliability of telemetry data acquisition is improved, and the station arrangement requirement and cost are reduced.

The technical scheme of the invention is as follows:

a projectile telemetry antenna array based on feed phase difference and screw coupling, comprising: the device comprises an inverted F antenna, a rocket cabin, a rectifying block, a radio frequency cable and a transmitter;

the inverted F antennas are uniformly distributed circumferentially about the central axis of the rocket cabin body, and are fixedly mounted on the outer wall of the rocket cabin body; the inverted F antenna is connected with the transmitter through a radio frequency cable;

a rectifying block is arranged above the head of each inverted F antenna; the rectifying block is fixedly arranged on the outer wall of the rocket cabin body; the rectification block is used for guiding flow, so that standing points of pneumatic heating cannot occur on the inverted F antenna.

Preferably, the length difference of the different radio frequency cables meets the feeding phase difference requirement of the corresponding inverted-F antenna.

Preferably, the number of the inverted F antennas is determined by the radiation pattern simulation result.

Preferably, the mounting position, structure and material of the rectifying block are determined according to the aerodynamic heat protection requirement and the radiation pattern simulation result.

Preferably, the rectifying block is of a semi-conical structure, the axis of the semi-conical structure is parallel to the axis of the rocket cabin, and the vertex angle of the semi-conical structure faces the head of the rocket cabin;

two sides of the semi-conical structure are respectively removed to form two bevel planes.

Preferably, the material of the rectifying block is an epoxy glass cloth laminated board material.

Preferably, the inverted F antenna includes: a radiator, a base plate and a feed connector;

the bottom plate is used for fixing the radiator and the feed connector and fixing the radiator on the outer wall of the rocket cabin;

one end of the feed connector is connected with the radio frequency cable, and the other end of the feed connector is connected with the radiator.

Preferably, the head of the radiator is provided with a slope surface facing the head of the rocket bay.

Preferably, the axes of the different feed connectors are coplanar, and the plane of the axes is perpendicular to the axis of the rocket capsule.

Preferably, the rectifying block is fixedly installed on the outer wall of the rocket cabin body through a fixing screw, the fixing screw is used as a guiding unit, induced current is coupled out and used as a guiding or reflecting vibrator, and the control of the antenna radiation pattern is realized.

Compared with the prior art, the invention has the beneficial effects that:

1) The invention adopts the inverted F antenna form, the antenna structure is simple, the cost is low, the inverted F antenna mounting surface is small, the window opening on the cabin body and the conformal design are not needed, and the mounting position requirement is low. The inverted F antenna has a vertical arrow surface electric field, and can eliminate axial depression of the directional diagram through feeding phase difference.

2) According to the invention, the temperature resistance of the antenna system can be greatly improved through the design of the guide block, the front-back change of the directional diagram can be flexibly regulated through the design of the guide block fixing screw, the electromagnetic wave wavelength in the guide block is shortened through the effect of the guide block dielectric material, and the length required by the resonance of the screw is reduced.

3) According to the invention, the feeding phase difference is realized through the cable length difference, and the design complexity of the power divider is reduced.

Drawings

FIG. 1 is a diagram of the structure of a telemetry antenna array for a projectile arrow according to the present invention.

Fig. 2 (a) is a radial antenna radiation pattern at an azimuth angle of 0 degrees.

Fig. 2 (b) is a radial antenna radiation pattern at an azimuth angle of 90 degrees.

Detailed Description

The design is composed of a plurality of inverted-F antennas 1, the inverted-F antennas 1 are uniformly arranged on the surface of an arrow body, the feed phase difference adjustment between the inverted-F antennas 1 is realized through radio frequency cables with different lengths between the inverted-F antennas 1 and a transmitter, gain recession in the axis direction of the arrow body is optimized, aerodynamic heat and force protection of the antenna is realized through installing a rectifying block in front of the antenna, electromagnetic resonance and induction current are generated through installing screws of the rectifying block, secondary radiation and reflection guiding effect of electromagnetic waves are realized, front-back radiation proportion of the antenna is optimized and adjusted, and rear gain is enhanced. The method is mainly suitable for reliably receiving the telemetry data in the rocket launching flight process.

The invention is further described below with reference to the drawings and specific embodiments.

As shown in fig. 1, the invention consists of an inverted F antenna 1, a rocket cabin 2, a rectifying block 3, a fixing screw 4, a radio frequency cable 5 and a transmitter 6. The inverted F antennas 1 are circumferentially and uniformly distributed about the central shaft of the rocket cabin body, and the inverted F antennas 1 are fixedly arranged on the outer wall of the rocket cabin body 2; the inverted-F antenna 1 is connected with a transmitter 6 through a radio frequency cable 5; a rectifying block 3 is arranged above the head of each inverted F antenna 1; the rectifying block 3 is fixedly arranged on the outer wall of the rocket cabin 2; the rectification block 3 is used for guiding flow, so that a standing point of pneumatic heating cannot occur on the inverted F antenna 1.

The length difference of different radio frequency cables 5 meets the feeding phase difference requirement of the corresponding inverted-F antenna 1. The number of the inverted F antennas 1 is determined by the radiation pattern simulation result. The installation position, structure and material of the rectifying block 3 are determined according to the pneumatic heat protection requirement and the radiation pattern simulation result.

The rectifying block 3 is of a semi-conical structure, the axis of the semi-conical structure is parallel to the axis of the rocket cabin body 2, and the vertex angle of the semi-conical structure faces the head of the rocket cabin body 2; two sides of the semi-conical structure are respectively removed to form two bevel planes. The rectifying block 3 is made of epoxy glass cloth laminated board material.

The inverted-F antenna 1 includes: a radiator 11, a base plate 12 and a feed connector 13; the bottom plate 12 is used for fixing the radiator 11 and the feed connector 13, and fixing the radiator 11 on the outer wall of the rocket cabin 2; one end of the feed connector 13 is connected with the radio frequency cable 5, and the other end of the feed connector is connected with the radiator 11. The head of the radiator 11 is provided with a slope surface which faces the head of the rocket ship body 2.

The axes of the different feed connectors 13 are coplanar, and the plane of the axes is perpendicular to the axis of the rocket ship body 2.

Examples

The antenna consists of two inverted F antennas 1, two radio frequency cables, an antenna heat insulation block and a heat insulation block mounting screw. In the embodiment, the two feed connectors 13 are symmetrical about the central axis of the rocket capsule body, the axes of the two feed connectors 13 are coaxial, the origin of the coordinate system is located at the intersection point of the axis of the rocket capsule body 2 and the axis of the feed connector 13, the Z axis points to the direction of the bullet arrow part, and the Y axis and the X, Z axis are orthogonal to form a right-hand rectangular coordinate system. The diameter of the rocket cabin is 300mm, the number of telemetry antennas is determined according to the cabin size, the number of inverted F antennas 1 in the example is two, the inverted F antennas 1 are composed of a radiator 11, a bottom plate 12 and a feed connector 13, the bottom plate 12 is used for fixing the radiator 11 and the feed connector 13 and fixing the antennas on the surface of the rocket cabin 2, one end of the feed connector 13 is connected with a radio-frequency cable 5, and the other end of the feed connector 13 is connected with the radiator 11. The size structure of the inverted F antenna 1 is obtained by antenna simulation calculation optimization, and the impedance matching of the antenna is mainly considered.

The two inverted F antennas 1 are symmetrically arranged at two sides of the rocket cabin 2 in a mirror image mode in a mode that the head slope faces the direction of the arrow head and the tail opening faces the direction of the tail of the rocket. The connector of the inverted F antenna 1 extends into the position in the rocket cabin 2 through the hole on the rocket cabin 2, the front parts of the two inverted F antennas 1 are provided with semi-conical rectifying blocks 3 according to the conditions of the aerodynamic heat protection requirement, the simulation result of the radiation pattern and the like, the rectifying blocks are in the shape of a semi-conical structure with two inclined planes, the height of a semi-conical structure is 40mm, the radius of the bottom surface is 25mm, the connector is made of epoxy glass laminated board materials, the dielectric constant is 4.3, the loss tangent is 0.019, the wave transmission performance is realized, a mounting hole is arranged at the position 9mm away from the bottom surface of the rectifying blocks, the rectifying blocks 3 are fixed on the rocket cabin through the mounting hole in the rectifying blocks, the mounting position of the fixing screw 4 and the height higher than the surface of the rocket cabin are required to meet the simulation calculation requirement, in the example, the shaft distance between the fixing screw 4 and the antenna feed connector 13 is 44mm, and the screw length is 14mm (3+11 mm). The two radio frequency output interfaces of the transmitter 6 and the radio frequency interfaces of the two inverted-F antennas 1 are connected by using two radio frequency cables with different lengths, the length difference of the two radio frequency cables needs to meet the feeding phase difference requirement of the two inverted-F antennas 1, the feeding phase difference requirement of the embodiment is 180 degrees, for a coaxial line with dielectric material dielectric constant of 2.1, when the center frequency is 2.3GHz, the phase speed is about 14.32mm/rad, the phase is corresponding to 180 degrees, and the two radio frequency cables are corrected by simulation calculation (carried into a connector model), and the length difference of the two radio frequency cables is about 45mm.

The projectile and rocket telemetry antenna array based on the screw electromagnetic coupling and the feed phase difference is subjected to full-wave simulation by adopting ANSYS HFSS electromagnetic simulation software, meanwhile, the antenna array without the rectifying block and the screw and without the feed phase difference is subjected to full-wave simulation by comparison, and the far-field radiation patterns of the projectile and rocket telemetry antenna array based on the screw electromagnetic coupling and the feed phase difference and the antenna array by comparison are obtained as shown in figure 2.

As can be seen from fig. 2 (a), at an operating frequency of 2.3GHz, a solid line represents the variation of gain of the meridian plane of azimuth angle phi=0 deg of the antenna array according to the present invention along with the pitch angle, theta=0 deg is the direction of the bullet arrow part, theta=180 deg is the direction of the bullet tail, the minimum gain is-6.7 dBi, the maximum gain is 7.3dBi, and the angular range of gain greater than-8 dBi is 180deg. The broken line represents the gain of the antenna array azimuth phi=0 deg meridian plane, which is used for comparison and is free of rectifying blocks and screws, and the gain of the antenna array azimuth phi=0 deg meridian plane, which cancels the feed phase difference, is changed along with the pitch angle, the minimum gain of the tail of the rocket is-27.9 dBi, the maximum gain of the rocket is 4.5dBi, and the angle range of the gain of the rocket is 176deg.

As can be seen from fig. 2 (b), at an operating frequency of 2.3GHz, the solid line represents the variation of gain of the meridian plane of azimuth angle phi=90 deg of the antenna array according to the present invention along with the pitch angle, theta=0 deg is the direction of the bullet arrow part, theta=180 deg is the direction of the bullet tail, the minimum gain is 1.6dBi, the maximum gain is 6.4dBi, and the angular range of gain greater than-8 dBi is 180deg. The broken line represents the gain of the antenna array azimuth phi=90 deg meridian plane with the variation of the pitch angle without rectifying block and screw as comparison, the minimum gain of the tail of the rocket is-27.9 dBi, the maximum gain is-4.5 dBi, and the angle range of the gain larger than-8 dBi is 90deg.

The antenna is uniformly arranged on the surface of an arrow body, the feed phase difference adjustment between each inverted-F antenna 1 is realized through radio frequency cables with different lengths between each inverted-F antenna 1 and a transmitter, gain recession in the axis direction of the arrow body is optimized, aerodynamic heat and force protection of the antenna is realized through installing a rectifying block in front of the antenna, electromagnetic resonance and induced current are generated through installing screws of the rectifying block, the secondary radiation and reflection guiding effect of electromagnetic waves are realized, the front-back radiation proportion of the antenna is optimized and adjusted, and the gain at the back is enhanced. The method is mainly suitable for reliably receiving the telemetry data in the rocket launching flight process.

The technical solution of the invention is as follows: and designing a bullet telemetry antenna array to realize good coverage of the tail part of an antenna pattern.

The device working process is as follows, the telemetering transmitter divides the telemetering signal loaded with data information into two paths of equal auxiliary in-phase telemetering radio frequency signals through the power divider, 180-degree reverse feeding of the telemetering signal is realized through the radio frequency cable with the length being different by half an equivalent wavelength, the two paths of reverse feeding signals are output to the two inverted F antennas 1, the heat-insulating wave-transparent conical blocks in front of the inverted F antennas 1 are used for guiding, standing points of pneumatic heating cannot occur on the antennas, the temperature on the antennas is greatly reduced, the fixing screws 4 of the fixed rectifying block 3 are used as guiding units, induced currents are coupled out as guiding or reflecting vibrators, and control of an antenna radiation pattern is realized.

Although the present invention has been described in terms of the preferred embodiments, it is not intended to be limited to the embodiments, and any person skilled in the art can make any possible variations and modifications to the technical solution of the present invention by using the methods and technical matters disclosed above without departing from the spirit and scope of the present invention, so any simple modifications, equivalent variations and modifications to the embodiments described above according to the technical matters of the present invention are within the scope of the technical matters of the present invention. The embodiments of the present application and the technical features in the embodiments may be combined with each other without conflict.

What is not described in detail in the present specification is a well known technology to those skilled in the art.

Claims

1. A projectile-rocket telemetry antenna array based on feed phase difference and screw coupling, comprising: the device comprises an inverted F antenna (1), a rocket cabin (2), a rectifying block (3), a radio frequency cable (5) and a transmitter (6);

the inverted F antennas (1) are circumferentially and uniformly distributed about the central shaft of the rocket cabin, and the inverted F antennas (1) are fixedly mounted on the outer wall of the rocket cabin (2); the inverted F antenna (1) is connected with a transmitter (6) through a radio frequency cable (5);

a rectifying block (3) is arranged above the head of each inverted F antenna (1); the rectifying block (3) is fixedly arranged on the outer wall of the rocket cabin body (2); the rectification block (3) is used for guiding flow, so that standing points of pneumatic heating cannot occur on the inverted F antenna (1).

2. A projectile and rocket telemetry antenna array based on feed phase difference and screw coupling according to claim 1, characterized in that the length difference of different radio frequency cables (5) meets the feed phase difference requirement of the corresponding inverted F antenna (1).

3. A projectile and rocket telemetry antenna array based on feed phase difference and screw coupling as claimed in claim 1, wherein the number of the inverted-F antennas (1) is determined by radiation pattern simulation results.

4. A projectile and rocket telemetry antenna array based on feed phase difference and screw coupling according to claim 1, wherein the installation position, structure and material of the rectifying block (3) are determined according to the aerodynamic heat protection requirements and radiation pattern simulation results.

5. The rocket telemetry antenna array based on feed phase difference and screw coupling according to claim 4, wherein the rectifying block (3) is of a semi-conical structure, the axis of the semi-conical structure is parallel to the axis of the rocket capsule (2), and the vertex angle of the semi-conical structure faces the head of the rocket capsule (2);

6. A projectile and rocket telemetry antenna array based on feed phase difference and screw coupling as claimed in claim 4 wherein the material of the rectifying block (3) is epoxy glass laminated board material.

7. A projectile telemetry antenna array based on feed phase difference and screw coupling as claimed in any one of claims 1 to 6 wherein the inverted F antenna (1) comprises: a radiator (11), a base plate (12) and a feed connector (13);

the bottom plate (12) is used for fixing the radiator (11) and the feed connector (13) and fixing the radiator (11) on the outer wall of the rocket cabin (2);

one end of the feed connector (13) is connected with the radio frequency cable (5), and the other end of the feed connector is connected with the radiator (11).

8. A projectile telemetry antenna array based on feed phase difference and screw coupling as claimed in claim 7, wherein the head of the radiator (11) is machined with a ramp surface facing the head of the projectile capsule (2).

9. A projectile telemetry antenna array based on feed phase difference and screw coupling as claimed in claim 7, wherein the axes of the different feed connectors (13) are coplanar and the plane of the axes is perpendicular to the axis of the projectile capsule (2).

10. The rocket telemetry antenna array based on feed phase difference and screw coupling according to claim 7, wherein the rectifying block (3) is fixedly installed on the outer wall of the rocket cabin body (2) through the fixing screw (4), the fixing screw (4) is used as a guiding unit, induced current is coupled out, and the induced current is used as a guiding or reflecting vibrator, so that control of an antenna radiation pattern is achieved.