CN110783693A - Antenna layout method based on amphibious aircraft - Google Patents
Antenna layout method based on amphibious aircraft Download PDFInfo
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- CN110783693A CN110783693A CN201910967976.9A CN201910967976A CN110783693A CN 110783693 A CN110783693 A CN 110783693A CN 201910967976 A CN201910967976 A CN 201910967976A CN 110783693 A CN110783693 A CN 110783693A
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- 238000000034 method Methods 0.000 title claims abstract description 17
- 238000002955 isolation Methods 0.000 claims abstract description 38
- 238000004891 communication Methods 0.000 claims abstract description 24
- 238000010586 diagram Methods 0.000 claims abstract description 20
- 238000004088 simulation Methods 0.000 claims abstract description 20
- 230000005855 radiation Effects 0.000 claims description 23
- 230000035945 sensitivity Effects 0.000 claims description 8
- 230000005540 biological transmission Effects 0.000 claims description 4
- 238000009434 installation Methods 0.000 description 3
- 230000036544 posture Effects 0.000 description 3
- 230000008901 benefit Effects 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 210000001015 abdomen Anatomy 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 230000009429 distress Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000011156 evaluation Methods 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/27—Adaptation for use in or on movable bodies
- H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
- H01Q1/285—Aircraft wire antennas
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/27—Adaptation for use in or on movable bodies
- H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
- H01Q1/286—Adaptation for use in or on aircraft, missiles, satellites, or balloons substantially flush mounted with the skin of the craft
- H01Q1/287—Adaptation for use in or on aircraft, missiles, satellites, or balloons substantially flush mounted with the skin of the craft integrated in a wing or a stabiliser
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q21/00—Antenna arrays or systems
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- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- Physics & Mathematics (AREA)
- Astronomy & Astrophysics (AREA)
- General Physics & Mathematics (AREA)
- Variable-Direction Aerials And Aerial Arrays (AREA)
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- Details Of Aerials (AREA)
Abstract
The application provides an antenna layout method based on an amphibious aircraft, which is used for obtaining characteristic parameters of an airborne communication antenna and a navigation antenna of the amphibious aircraft; simulating the isolation between the ultra-short wave frequency band antennas and the isolation between the L-band antennas of the amphibious aircraft to obtain an isolation simulation result; simulating the directional diagram of the amphibious aircraft after the onboard communication antenna and the navigation antenna are installed to obtain a directional diagram simulation result; and carrying out antenna layout on the amphibious aircraft according to the characteristic parameters, the isolation degree simulation result and the directional diagram simulation result.
Description
Technical Field
The invention belongs to the field of special aircraft system design, and provides an antenna layout method and a solution for a large amphibious aircraft.
Background
The large amphibious aircraft depends on a large number of receiving and transmitting equipment for detection and the like to meet the task requirements of offshore remote communication, navigation and monitoring, data transmission, anti-diving and the like, so that the communication navigation antenna is various and the antenna layout is very complex. The antenna is arranged under the belly of the amphibious aircraft due to the influence of strong water wave impact force, so that certain antenna arrangement difficulty is brought.
Disclosure of Invention
The invention aims to solve the problems that antennae under a special structure of a large amphibious aircraft have compatibility and can fully exert due technical functions, and provides a method and a solution for antenna layout of the large amphibious aircraft.
An optimized antenna layout scheme of a large amphibious aircraft is obtained through characteristic analysis, antenna spacing degree analysis and directional diagram analysis after antenna installation of an onboard communication antenna and a navigation antenna of the large amphibious aircraft.
The application provides an antenna layout method based on an amphibious aircraft,
obtaining characteristic parameters of an airborne communication antenna and a navigation antenna of the amphibious aircraft;
simulating the isolation between the ultra-short wave frequency band antennas and the isolation between the L-band antennas of the amphibious aircraft to obtain an isolation simulation result;
simulating the directional diagram of the amphibious aircraft after the onboard communication antenna and the navigation antenna are installed to obtain a directional diagram simulation result;
and carrying out antenna layout on the amphibious aircraft according to the characteristic parameters, the isolation degree simulation result and the directional diagram simulation result.
Preferably, the characteristic parameters include communication distance, transmission power, reception sensitivity, and radiation directivity.
Preferably, the onboard communication antenna and the navigation antenna include:
a weather radar antenna, a short wave antenna, an ultrashort wave antenna, a ranging antenna, a satellite navigation antenna, a voll/course/glide-down antenna, a radio compass antenna, a pointing beacon antenna, an air pipe response antenna, an air collision avoidance system antenna, a radio altimeter antenna, a life saving radio station antenna, an airborne direction finder antenna and an emergency positioning transmitter antenna.
Preferably, the requirements for simulating the isolation between the ultra-short wave band antennas and the isolation between the L-band antennas of the amphibious aircraft at least include:
the same frequency band or frequency multiplication isolation degree of the ultra-short wave antenna and the very high frequency antenna is not less than 40 dB;
the same frequency band or frequency multiplication isolation degree of the ranging antenna and the L-band antenna is not less than 40 dB;
and the isolation between the frequency multiplication of the ultra-short wave antenna and the frequency of the GPS antenna is not less than the sensitivity dB value of the GPS receiver.
Preferably, the requirements for simulating the installed directional patterns of the onboard communication antenna and the onboard navigation antenna of the amphibious aircraft at least comprise the following steps:
the vertical deflection angle of the short wave antenna towards the upward maximum radiation direction is not more than 60 degrees and not less than 30 degrees;
the downward radiation direction of the ranging antenna is omnidirectional, and the weakest direction is not lower than 20 dB;
the radio compass antenna radiation pattern is required to be omnidirectional within ± 20 degrees elevation;
the radiation direction of the empty pipe response antenna is omnidirectional, and the weakest direction is not lower than 20 dB.
Preferably, the antenna layout for the amphibious aircraft specifically includes:
the short wave antenna is arranged on a dorsal fin of the airplane;
the ultra-short wave antenna is arranged on the highest point of the front machine body and the central wing;
the ranging antenna is arranged on the far end of the wing;
the radio compass antenna is arranged on the front machine body;
the pointing beacon antenna is arranged below the horizontal tail;
the lower hollow pipe response antenna is arranged in the head cover, and the upper hollow pipe response antenna is arranged on the vertical tail;
an upper antenna of the aerial anti-collision system is arranged on the front fuselage, and a lower antenna of the aerial anti-collision system is arranged in the tail cover;
the receiving antenna and the transmitting antenna of the radio altimeter are arranged on the trailing edge of the wing;
the airborne direction finder and the lifesaving radio antenna are both arranged on the far end of the wing.
Preferably, the simulation of the isolation between the ultra-short wave frequency band antennas and the isolation between the L-band antennas of the amphibious aircraft specifically includes:
simulation software FEKO or EMA3D is used for simulating the isolation between the antennas of the amphibious aircraft in the ultra-short wave band and the isolation between the antennas in the L wave band.
Preferably, the simulation of the installed directional patterns of the amphibious aircraft onboard communication antenna and the navigation antenna specifically comprises the following steps:
simulation software FEKO or EMA3D is used for simulating the installed directional patterns of the onboard communication antenna and the onboard navigation antenna of the amphibious aircraft.
The invention has the advantages that: in the design stage of the large amphibious aircraft, the appearance characteristics of the large amphibious aircraft are combined, and the optimal layout position of the antennas under the special structure of the large amphibious aircraft is determined through antenna characteristic analysis, antenna isolation simulation analysis and antenna installation backward direction diagram simulation analysis, so that the antenna arrangement of different conventional aircraft can fully exert the due technical functions, and the compatibility is realized among the antennas, thereby ensuring the overall performance of communication navigation of the large amphibious aircraft. The communication navigation equipment of the large amphibious aircraft can be compatible in the limited external geometric space of the aircraft only through proper antenna arrangement, the due technical functions can be fully exerted, the adjustment repetition is reduced for the test flight of the aircraft, the cost is reduced, and the benefit is improved.
Drawings
FIG. 1 is a schematic diagram of an embodiment of an antenna layout solution solved by the present invention;
wherein: 1 meteorological radar antenna, 2 air pipe response antenna (lower), 3 air collision avoidance system antenna (upper), 4 ultrashort wave antenna (1), 5 radio compass antenna, 6 satellite navigation antenna (1), 7 satellite navigation antenna (2), 8 ultrashort wave antenna (2), 9 emergency positioning transmitter antenna, 10 distance measurement system antenna (1), 11 airborne lifesaving radio station antenna, 12 radio altimeter antenna (transmitting antenna 1), 13 radio altimeter antenna (receiving antenna 1), 14 radio altimeter antenna (transmitting antenna 2), 15 radio altimeter antenna (receiving antenna 2), 16 airborne direction finder antenna, 17 distance measurement system antenna (2), 18 shortwave antenna, 19 volt/course/glide-down antenna (1), 20 volt/course/glide-down antenna (2), 21 air collision avoidance system antenna (lower) 22 pointing beacon antenna (lower), 23 aerial collision avoidance system antenna (below).
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings.
The optimal mounting position of the antenna on the airplane is finally determined by the layout of the antenna of the large amphibious aircraft, and the following requirements are met:
1) ensuring transmitting and receiving functions in connection with an antenna
2) The transmitting and receiving pairs connected with the antenna do not interfere with each other
3) Minimum distortion of antenna mounting rear direction figure
In order to meet the installation position of the antenna under the conditions, the position of the large amphibious aircraft needs to be optimally selected according to the characteristics of the antenna, and the method specifically comprises the following steps:
the method comprises the following steps: and (4) analyzing characteristics of the large amphibious aircraft airborne communication antenna and the large amphibious aircraft navigation antenna. (1) The meteorological radar antenna detects the meteorological condition in front of the airplane, transmits with high power, and receives radiation in the forward direction. (2) The short wave antenna adopts an airplane conformal antenna, and is arranged at a position where the airplane needs to upwards emit to an air ionized layer and can reflect electromagnetic energy through the ionized layer. (3) In any airplane posture, the ultrashort wave radio station can provide clear communication with a ground station, and two pairs of antennas are configured to meet the requirement of the communication distance of 150 kilometers. (4) The ranging system is able to continuously track ground station signals without losing the position where the antenna arrangement must be able to transmit and receive electromagnetic energy downward. (5) The satellite navigation antenna (GPS antenna) has high receiving sensitivity, is in the air of an airplane without shielding, and at least needs to receive signals of 3 stars. (6) The receiving of the heading gliding signals cannot be influenced under all normal pitching postures of the airplane, the Voll frequency band radiation directional diagram is required to be omnidirectional within an elevation angle of +/-20 degrees, and the Voll/heading/gliding antenna is a three-in-one antenna (integrating Voll, heading and gliding functions). (7) The airplane can receive signals by leading downwards under all normal pitching postures and the low sensitivity of a radio compass system and a pointing beacon system. (8) The air traffic control answering system ensures that the airplane enters a field, leaves the field and answers up and down in the air. (9) According to the condition of a large amphibious aircraft, the aerial anti-collision system antenna comprises a directional antenna and an omnidirectional antenna, and the electromagnetic energy transmitted up and down by the aircraft is ensured. (10) The radio altimeter measures the real height below 1500 m, and uses 1 pair of transmitting and receiving antennas to make the directional diagram point to the ground in pen-like mode, and the receiving antenna receives the frequency modulated continuous wave radio frequency echo wave sent by the transmitting antenna and reflected back by the ground. (11) The airborne direction finder antenna and the lifesaving radio station only work when a pilot searches and rescues, and the antenna is required to transmit electromagnetic energy downwards in all directions. (12) The emergency positioning transmitter antenna is used for actively transmitting distress information after the airplane falls due to faults, and is arranged at a position where the airplane is not easy to damage.
Step two: and (4) carrying out simulation analysis on the isolation between the antennae of the large amphibious aircraft. The method comprises the steps of establishing an electromagnetic simulation model of a large amphibious aircraft and an antenna by utilizing commercial electromagnetic simulation software FEKO, EMA3D, E-MIN and the like, arranging the antenna model at a preliminary position, and adjusting the position of a transmitting and receiving antenna according to a software simulation state until the requirements are met. (1) The same frequency band or frequency multiplication isolation degree of the ultra-short wave antenna and other very high frequency antennas is not less than 40 dB. (2) The same frequency band or frequency multiplication isolation degree of the ranging antenna and other L-band antennas is not less than 40 dB. (3) And the isolation between the frequency multiplication of the ultra-short wave antenna and the frequency of the GPS antenna is not less than the sensitivity dB value of the GPS receiver. (4) The Vol/course/gliding antenna is a three-in-one antenna, and the isolation of the ultrashort wave fundamental frequency and the second and third harmonic waves is not less than the dB value of the sensitivity of the comprehensive navigation receiver. (5) The isolation between the air traffic control response antenna and the aerial collision avoidance system antenna is not less than 40 dB. (6) The isolation between the radio transceiver antennas must be satisfied to be not less than 85 dB. (7) The minimum spacing between the airborne direction finder antenna and the lifesaving station antenna and other VHF antennas is 3/8 of the wavelength of the lowest frequency of any antenna.
Step three: and analyzing a directional diagram of the antenna loaded on the large amphibious aircraft. According to the second step, an electromagnetic simulation model of the appearance, the antenna and the antenna position of the large amphibious aircraft is built by using commercial electromagnetic simulation software, directional diagram characteristics of each transmitting antenna and each receiving antenna are calculated, and the radiation and receiving characteristics of the antenna after the large amphibious aircraft platform influences are determined. (1) The meteorological radar antenna directional diagram meets the requirements of forward looking, upward looking and downward looking at the vertical +/-30 degrees and the horizontal +/-60 degrees. (2) The vertical deflection angle of the short-wave antenna towards the upward maximum radiation direction is not more than 60 degrees and not less than 30 degrees. (3) The radiation horizontal direction of the ultra-short wave antenna directional diagram is omni-directional, the weakest direction is not lower than 20dB, and the strongest radiation area is within +/-45 degrees relative to the horizontal plane by taking the axis of the airplane body as a reference. (4) The downward radiation direction of the ranging antenna is basically omnidirectional, and the weakest direction is not lower than 20 dB. (5) The GPS antenna radiation pattern is unobstructed in the upper half of the aircraft, and at least a 4-star signal pattern is received. (6) A volr/course/glide-down antenna, a volr frequency band radiation directional diagram is required to be omnidirectional within an elevation angle of +/-20 degrees, and the directional diagram has no deep zero value and no sharp gain change; and receiving signals in a region with the horizontal plane of the heading and the gliding frequency band above-15 degrees. (7) The radio compass antenna radiation pattern is required to be omnidirectional within ± 20 degrees elevation. (8) The pointing beacon antenna pattern is advanced downward. (9) The radiation direction of the empty pipe response antenna is basically omnidirectional, and the weakest direction is not lower than 20 dB. (10) The radiation direction of the aerial collision avoidance system antenna is basically omnidirectional, and the weakest direction is not lower than 20 dB. (11) The E-plane radiation pattern (3dB) width and null depth of the radio altimeter antenna meet the requirements of a transmitting receiver. (12) The evaluation achieves the function of guaranteeing the transmission and reception technology connected to the antenna.
Step four: and determining a layout scheme of the antenna of the large amphibious aircraft. And obtaining a large amphibious aircraft antenna layout solution according to the analysis results of the second step and the third step. (1) The meteorological radar antenna is arranged in the head cover. (2) The short wave antenna is arranged on a dorsal fin of the aircraft. (3) The ultra-short wave antenna is arranged on the highest point of the front fuselage and the central wing. (4) A ranging antenna is disposed on the distal end of the wing. (5) A satellite navigation antenna (GPS antenna) is arranged on the body. (6) The Vol/course/gliding two antennas are respectively arranged on the left and right of the upper part of the vertical tail by 1 pair. (7) A radio compass antenna is disposed on the front body. (8) The pointing beacon antenna is disposed below the horizontal tail. (9) The lower hollow pipe response antenna is arranged in the head cover, and the upper hollow pipe response antenna is arranged on the vertical tail. (10) The aerial anti-collision system is characterized in that the upper antenna is arranged on the front fuselage, and the lower antenna is arranged in the tail cover. (11) The receiving antenna and the transmitting antenna of the radio altimeter are arranged at the trailing edge of the wing. (12) The airborne direction finder and the lifesaving radio antenna are arranged on the far end of the wing. (13) The emergency positioning transmitter antenna is arranged in front of the dorsal fin in the middle of the machine back.
Claims (8)
1. An amphibious aircraft-based antenna layout method is characterized in that,
obtaining characteristic parameters of an airborne communication antenna and a navigation antenna of the amphibious aircraft;
simulating the isolation between the ultra-short wave frequency band antennas and the isolation between the L-band antennas of the amphibious aircraft to obtain an isolation simulation result;
simulating the directional diagram of the amphibious aircraft after the onboard communication antenna and the navigation antenna are installed to obtain a directional diagram simulation result;
and carrying out antenna layout on the amphibious aircraft according to the characteristic parameters, the isolation degree simulation result and the directional diagram simulation result.
2. The method of claim 1, wherein the characteristic parameters include communication distance, transmission power, reception sensitivity, and radiation directivity.
3. The method of claim 1, wherein the onboard communication antenna and navigation antenna comprise:
a weather radar antenna, a short wave antenna, an ultrashort wave antenna, a ranging antenna, a satellite navigation antenna, a voll/course/glide-down antenna, a radio compass antenna, a pointing beacon antenna, an air pipe response antenna, an air collision avoidance system antenna, a radio altimeter antenna, a life saving radio station antenna, an airborne direction finder antenna and an emergency positioning transmitter antenna.
4. The method according to claim 1, wherein the requirements for simulating the isolation between the antennas of the amphibious aircraft in the ultrashort wave band and the isolation between the antennas in the L band at least comprise:
the same frequency band or frequency multiplication isolation degree of the ultra-short wave antenna and the very high frequency antenna is not less than 40 dB;
the same frequency band or frequency multiplication isolation degree of the ranging antenna and the L-band antenna is not less than 40 dB;
and the isolation between the frequency multiplication of the ultra-short wave antenna and the frequency of the GPS antenna is not less than the sensitivity dB value of the GPS receiver.
5. The method of claim 1, wherein the requirements for simulating installed patterns of communication and navigation antennas onboard an amphibious aircraft include at least:
the vertical deflection angle of the short wave antenna towards the upward maximum radiation direction is not more than 60 degrees and not less than 30 degrees;
the downward radiation direction of the ranging antenna is omnidirectional, and the weakest direction is not lower than 20 dB;
the radio compass antenna radiation pattern is required to be omnidirectional within ± 20 degrees elevation;
the radiation direction of the empty pipe response antenna is omnidirectional, and the weakest direction is not lower than 20 dB.
6. The method according to claim 1, wherein the antenna layout for an amphibious aircraft comprises:
the short wave antenna is arranged on a dorsal fin of the airplane;
the ultra-short wave antenna is arranged on the highest point of the front machine body and the central wing;
the ranging antenna is arranged on the far end of the wing;
the radio compass antenna is arranged on the front machine body;
the pointing beacon antenna is arranged below the horizontal tail;
the lower hollow pipe response antenna is arranged in the head cover, and the upper hollow pipe response antenna is arranged on the vertical tail;
an upper antenna of the aerial anti-collision system is arranged on the front fuselage, and a lower antenna of the aerial anti-collision system is arranged in the tail cover;
the receiving antenna and the transmitting antenna of the radio altimeter are arranged on the trailing edge of the wing;
the airborne direction finder and the lifesaving radio antenna are both arranged on the far end of the wing.
7. The method of claim 1, wherein the simulation of the isolation between the ultra-short wave band antennas and the isolation between the L-band antennas of the amphibious aircraft specifically comprises:
simulation software FEKO or EMA3D is used for simulating the isolation between the antennas of the amphibious aircraft in the ultra-short wave band and the isolation between the antennas in the L wave band.
8. The method according to claim 1, wherein simulating the installed pattern of the onboard communication antenna and the onboard navigation antenna of the amphibious aircraft comprises:
simulation software FEKO or EMA3D is used for simulating the installed directional patterns of the onboard communication antenna and the onboard navigation antenna of the amphibious aircraft.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112103654A (en) * | 2020-08-30 | 2020-12-18 | 西南电子技术研究所（中国电子科技集团公司第十研究所） | Method for increasing airborne ultrashort wave communication distance through double-antenna gain synthesis |
| CN112803173A (en) * | 2021-04-15 | 2021-05-14 | 中航富士达科技股份有限公司 | Coaxial feed network of Ka-band dual-polarized slot antenna |
| CN115655247A (en) * | 2022-10-12 | 2023-01-31 | 中国航空工业集团公司西安飞机设计研究所 | Radio compass data processing method for ultrashort wave interference |
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| CN108319759A (en) * | 2018-01-04 | 2018-07-24 | 北京航空航天大学 | A kind of antenna arrangement method for improving with platform antenna isolation |
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2019
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| WO2009024532A1 (en) * | 2007-08-17 | 2009-02-26 | Thales | Distributed architecture for all radio navigation aids |
| CN105281016A (en) * | 2015-11-06 | 2016-01-27 | 北京航空航天大学 | Unmanned aerial vehicle-borne antenna layout design and verification method |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112103654A (en) * | 2020-08-30 | 2020-12-18 | 西南电子技术研究所（中国电子科技集团公司第十研究所） | Method for increasing airborne ultrashort wave communication distance through double-antenna gain synthesis |
| CN112103654B (en) * | 2020-08-30 | 2023-08-15 | 西南电子技术研究所（中国电子科技集团公司第十研究所） | Method for improving airborne ultrashort wave communication distance by double-antenna gain synthesis |
| CN112803173A (en) * | 2021-04-15 | 2021-05-14 | 中航富士达科技股份有限公司 | Coaxial feed network of Ka-band dual-polarized slot antenna |
| CN112803173B (en) * | 2021-04-15 | 2021-06-22 | 中航富士达科技股份有限公司 | Coaxial feed network of Ka-band dual-polarized slot antenna |
| CN115655247A (en) * | 2022-10-12 | 2023-01-31 | 中国航空工业集团公司西安飞机设计研究所 | Radio compass data processing method for ultrashort wave interference |
| CN115655247B (en) * | 2022-10-12 | 2024-06-11 | 中国航空工业集团公司西安飞机设计研究所 | Radio compass data processing method for ultrashort wave interference |
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Effective date of registration: 20220928 Address after: 519040 building 201, 999 Jinhai Middle Road, Jinwan District, Zhuhai City, Guangdong Province Applicant after: SOUTH CHINA AIRCRAFT INDUSTRY CO., LTD. OF CHINA AVIATION INDUSTRY GENERAL AIRCRAFT Co.,Ltd. Address before: 519040 AVIC Tongfei industrial base, aviation industrial park, Jinwan District, Zhuhai City, Guangdong Province Applicant before: R&D INSTITUTE OF CHINA AVIATION INDUSTRY GENERAL AIRCRAFT Co.,Ltd. |
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Application publication date: 20200211 |